Orbital propellant depot

<h2 id="leo-depot-fuels">LEO depot fuels</h2>
For rockets and space vehicles, propellants usually take up 2/3 or more of their total mass.
Large upper-stage rocket engines generally use a <a href="/facts/Cryogenic_fuel/4RHxUvG8">cryogenic fuel</a> like <a href="/facts/Liquid_hydrogen/Vpk3Gb8P">liquid hydrogen</a> and <a href="/facts/Liquid_oxygen/qnI0KDTb">liquid oxygen</a> (LOX) as an oxidizer because of the large specific impulse possible, but must carefully consider a problem called "boil off," or the evaporation of the cryogenic propellant. The boil off from only a few days of delay may not allow sufficient fuel for higher orbit injection, potentially resulting in a mission abort. Lunar or Mars missions will require weeks to months to accumulate tens of thousands to hundreds of thousands of kilograms of propellant, so additional equipment may be required on the transfer stage or the depot to mitigate boiloff.
Non-cryogenic, earth-storable <a href="/facts/Liquid_rocket_propellants/s0KadvqW">liquid rocket propellants</a> including <a href="/facts/RP-1/wDI7vNdu">RP-1</a> (<a href="/facts/Kerosene/DoHPYXKp">kerosene</a>), <a href="/facts/Hydrazine/G7P5ITzU">hydrazine</a> and <a href="/facts/Nitrogen_tetroxide/01WfnHJh">nitrogen tetroxide</a> (NTO), and mildly cryogenic, space-storable propellants like <a href="/facts/Liquid_methane/kBHneYnh">liquid methane</a> and <a href="/facts/Liquid_oxygen/qnI0KDTb">liquid oxygen</a>, can be kept in liquid form with less boiloff than the cryogenic fuels, but also have lower specific impulse.<a class="footnote-ref" id="fnref:7" href="#fn:7">7</a> Additionally, gaseous or supercritical propellants such as those used by <a href="/facts/Ion_thruster/cjt6M89p">ion thrusters</a> include <a href="/facts/Xenon/9E3XR69R">xenon</a>, <a href="/facts/Argon/QX6NRH6d">argon</a>,<a class="footnote-ref" id="fnref:8" href="#fn:8">8</a><a class="footnote-ref" id="fnref:9" href="#fn:9">9</a> and <a href="/facts/Bismuth/75FLjkoX">bismuth</a>.<a class="footnote-ref" id="fnref:10" href="#fn:10">10</a>

<h2 id="propellant-launch-costs">Propellant launch costs</h2>
Ex-NASA administrator Mike Griffin commented at the 52nd AAS Annual Meeting in Houston, Texas, November 2005, that "at a conservatively low government price of $10,000 per kg in LEO, 250 MT of fuel for two missions per year is worth $2.5 billion, at government rates."<a class="footnote-ref" id="fnref:11" href="#fn:11">11</a>

<h2 id="cryogenic-depot-architectures-and-types">Cryogenic depot architectures and types</h2>
In the depot-centric architecture, the depot is filled by tankers, and then the propellant is transferred to an upper stage prior to orbit insertion, similar to a gas station filled by tankers for automobiles. By using a depot, the launch vehicle size can be reduced and the flight rate increased. Since the accumulation of propellant may take many weeks to months, careful consideration must be given to boiloff mitigation.
In simple terms, a passive cryogenic depot is a transfer stage with stretched propellant tanks, additional insulation, and a sun shield. In one concept, hydrogen boiloff is also redirected to reduce or eliminate liquid oxygen boiloff and then used for attitude control, power, or reboost. An active cryogenic depot is a passive depot with additional power and refrigeration equipment/cryocoolers to reduce or eliminate propellant boiloff.<a class="footnote-ref" id="fnref:12" href="#fn:12">12</a> Other active cryogenic depot concepts include electrically powered attitude control equipment to conserve fuel for the end payload.

<h2 id="heavy-lift-versus-depot-centric-architectures">Heavy lift versus depot-centric architectures</h2>
In the heavy lift architecture, propellant, which can be two-thirds or more of the total mission mass, is accumulated in fewer launches and possibly shorter time frame than the depot centric architecture. Typically the transfer stage is filled directly and no depot is included in the architecture. For cryogenic vehicles and cryogenic depots, additional boiloff mitigation equipment is typically included on the transfer stage, reducing payload fraction and requiring more propellant for the same payload unless the mitigation hardware is expended.
Heavy Lift is compared with using Commercial Launch and Propellant Depots in this power point by Dr. Alan Wilhite given at FISO Telecon.<a class="footnote-ref" id="fnref:13" href="#fn:13">13</a>

<h2 id="feasibility-of-propellant-depots">Feasibility of propellant depots</h2>
Both theoretical studies and funded development projects that are currently underway aim to provide insight into the feasibility of propellant depots. Studies have shown that a depot-centric architecture with smaller launch vehicles could be US$57 billion less expensive than a heavy-lift architecture over a 20-year time frame.<a class="footnote-ref" id="fnref:14" href="#fn:14">14</a> The cost of large launch vehicles is so high that a depot able to hold the propellant lifted by two or more medium-sized launch vehicles may be cost effective and support more payload mass on <a href="/facts/Beyond_Earth_orbit/l5bSKRcJ">beyond-Earth orbit</a> trajectories.
In a 2010 NASA study, an additional flight of an <a href="/facts/Ares_V/k6fxyVKV">Ares V heavy</a> launch vehicle was required to stage a US government Mars reference mission due to 70 tons of boiloff, assuming 0.1% boiloff/day for <a href="/facts/Hydrolox/s0KadvqW">hydrolox</a> propellant.<a class="footnote-ref" id="fnref:15" href="#fn:15">15</a> The study identified the need to decrease the design boiloff rate by an order of magnitude or more.
Approaches to the design of <a href="/facts/Low_Earth_orbit/rq1TwayJ">low Earth orbit</a> (LEO) propellant depots were also discussed in the <a href="/facts/Review_of_United_States_Human_Space_Flight_Plans_Committee/YyjpuvKh">2009 Augustine report</a> to <a href="/facts/NASA/TIMCV0yV">NASA</a>, which "examined the [then] current concepts for in-space refueling."<a class="footnote-ref" id="fnref:16" href="#fn:16">16</a> The report determined there are essentially two approaches to refueling a <a href="/facts/Spacecraft/YQqQaUw0">spacecraft</a> in LEO:<a class="footnote-ref" id="fnref:17" href="#fn:17">17</a>

<ul><li>Propellant tanker delivery. In this approach, a single tanker performs a rendezvous and docking with an on-orbit spacecraft. The tanker then transfers propellant and departs. This approach is "much like an <a href="/facts/Aerial_refueling/VMV3xXlW">airborne tanker</a> refuels an aircraft."</li>
<li>In-space depot. An alternative approach is for many tankers to rendezvous and transfer propellant to an orbital depot. Then, at a later time, a spacecraft may dock with the depot and receive a propellant load before departing Earth orbit.</li></ul>
Both approaches were considered feasible with 2009 spaceflight technology, but anticipated that significant further engineering development and in-space demonstration would be required before missions could depend on the technology. Both approaches were seen to offer the potential of long-term life-cycle savings.<a class="footnote-ref" id="fnref:18" href="#fn:18">18</a>
In 2010 <a href="/facts/United_Launch_Alliance/yWev1ndb">United Launch Alliance</a> (ULA) proposed their <a href="/facts/Advanced_Cryogenic_Evolved_Stage/JJuqn6Tq">Advanced Cryogenic Evolved Stage</a> (ACES) tanker, a concept that dates to work by Boeing in 2006,<a class="footnote-ref" id="fnref:19" href="#fn:19">19</a> sized to transport up to 73 tonnes (161,000 lb) of propellant—in early design, a first flight was proposed for no earlier than 2023, with initial usage as a propellant tanker potentially beginning in the mid-2020s.<a class="footnote-ref" id="fnref:20" href="#fn:20">20</a><a class="footnote-ref" id="fnref:21" href="#fn:21">21</a> ACES was not funded, but some of the ideas were used in the Centaur stage of the <a href="/facts/Vulcan_Centaur/ItQaJHkk">Vulcan Centaur</a> rocket.
Beyond theoretical studies, since at least 2017, <a href="/facts/SpaceX/2tKHsVdJ">SpaceX</a> has undertaken funded <a href="/facts/New_product_development/ogcXTIco">development</a> of an <a href="/facts/Interplanetary_spaceflight/4HGDAA2g">interplanetary</a> set of technologies. While the interplanetary mission architecture consists of a combination of <a href="/facts/SpaceX_Mars_transportation_infrastructure/zjbYEwHv">several elements that are considered by SpaceX to be key</a> to making long-duration <a href="/facts/Beyond_Earth_orbit/l5bSKRcJ">beyond Earth orbit</a> (BEO) spaceflights possible by reducing the cost per ton delivered to Mars by multiple <a href="/facts/Orders_of_magnitude/cWzRP2dM">orders of magnitude</a> over what NASA approaches have achieved,<a class="footnote-ref" id="fnref:22" href="#fn:22">22</a><a class="footnote-ref" id="fnref:23" href="#fn:23">23</a><a class="footnote-ref" id="fnref:24" href="#fn:24">24</a> refilling of propellants in orbit is one of the four key elements. In a novel mission architecture, the SpaceX design intends to enable the long-journey spacecraft to expend almost all of its propellant load during the launch to <a href="/facts/Low_Earth_orbit/rq1TwayJ">low Earth orbit</a> while it serves as the <a href="/facts/Second_stage/WNrmgztj">second stage</a> of the <a href="/facts/SpaceX_Starship/zkm1P9kA">SpaceX Starship</a>, and then after refilling on orbit by multiple Starship tankers, provide the large amount of <a href="/facts/Delta-V/eM4TaG9d">energy</a> required to put the spacecraft onto an interplanetary trajectory. The Starship tanker is designed to transport approximately 100 tonnes (220,000 lb) of propellant to low Earth orbit.<a class="footnote-ref" id="fnref:25" href="#fn:25">25</a>[better source needed] In April 2021, NASA selected the SpaceX <a href="/facts/Starship_HLS/1bjx1dx2">Lunar Starship</a> with in-orbit refueling for their initial lunar human landing system.<a class="footnote-ref" id="fnref:26" href="#fn:26">26</a>

<h2 id="advantages">Advantages</h2>
Because a large portion of a rocket is propellant at time of launch, proponents point out several advantages of using a propellant depot architecture. Spacecraft could be launched unfueled and thus require less structural mass,<a class="footnote-ref" id="fnref:27" href="#fn:27">27</a> or the depot tanker itself could serve as the second-stage on launch when it is reusable.<a class="footnote-ref" id="fnref:28" href="#fn:28">28</a> An on-orbit market for refueling may be created where competition to deliver propellant for the lowest price takes place, and it may also enable an economy of scale by permitting existing rockets to fly more often to refuel the depot.<a class="footnote-ref" id="fnref:29" href="#fn:29">29</a> If used in conjunction with a <a href="/facts/Colonization_of_the_Moon/Sc13PEu3">mining facility on the moon</a>, <a href="/facts/Lunar_water/TKfE5qLU">water</a> or propellant could be exported back to the depot, further reducing the cost of propellant.<a class="footnote-ref" id="fnref:30" href="#fn:30">30</a><a class="footnote-ref" id="fnref:31" href="#fn:31">31</a> An exploration program based on a depot architecture could be less expensive and more capable, not needing a specific rocket or a heavy lift such as the <a href="/facts/Space_Launch_System/DbGCgH1W">SLS</a><a class="footnote-ref" id="fnref:32" href="#fn:32">32</a><a class="footnote-ref" id="fnref:33" href="#fn:33">33</a><a class="footnote-ref" id="fnref:34" href="#fn:34">34</a><a class="footnote-ref" id="fnref:35" href="#fn:35">35</a><a class="footnote-ref" id="fnref:36" href="#fn:36">36</a> to support multiple destinations such as the Moon, Lagrange points, asteroids, and Mars.<a class="footnote-ref" id="fnref:37" href="#fn:37">37</a>
NASA studies in 2011 showed lower cost and faster alternatives than the Heavy Lift Launch System and listed the following advantages:<a class="footnote-ref" id="fnref:38" href="#fn:38">38</a>

<ul><li>Tens of billions of dollars of cost savings to fit the budget profile</li>
<li>Allows first NEA/Lunar mission by 2024 using conservative budgets</li>
<li>Launch every few months rather than once every 12–18 months</li>
<li>Allows multiple <a href="/facts/Market_competition/zscsQx5l">competitors</a> for propellant delivery</li>
<li>Reduced critical path mission complexity (AR&Ds, events, number of unique elements)</li></ul>
<h2 id="history-and-plans">History and plans</h2>
<h3>USA</h3>
Propellant depots were proposed as part of the <a href="/facts/Space_Transportation_System/1F1esWNk">Space Transportation System</a> (along with nuclear "tugs" to take payloads from LEO to other destinations) in the mid-1960s.<a class="footnote-ref" id="fnref:39" href="#fn:39">39</a>
In October 2009, the U.S. <a href="/facts/U.S._Air_Force/7MxWBYlc">Air Force</a> and <a href="/facts/United_Launch_Alliance/yWev1ndb">United Launch Alliance</a> (ULA) performed an experimental <a href="/facts/Low_Earth_orbit/rq1TwayJ">on-orbit</a> demonstration on a modified <a href="/facts/Centaur_(rocket_stage)/ryg96uIF">Centaur upper stage</a> on the <a href="/facts/DMSP-18/zsXW89Nl">DMSP-18</a> <a href="/facts/Atlas_V/5SNgegyt">launch</a> to improve "understanding of <a href="/facts/Propellant_depot/srD0zEyR">propellant settling</a> and <a href="/facts/Slosh_dynamics/QCA6sDJy">slosh</a>, pressure control, <a href="/facts/RL10/xNrFPF99">RL10</a> chilldown and RL10 two-phase shutdown operations." "The light weight of DMSP-18 allowed 12,000 pounds (5,400 kg) of remaining liquid O2 and liquid H2 propellant, 28% of Centaur's capacity," for the <a href="/facts/Low_Earth_orbit/rq1TwayJ">on-orbit</a> demonstrations. The post-spacecraft mission extension ran 2.4 hours before executing the <a href="/facts/Orbital_maneuver/HAlEFRSJ">deorbit burn</a>.<a class="footnote-ref" id="fnref:40" href="#fn:40">40</a>
NASA's <a href="/facts/Launch_Services_Program/sUJToucI">Launch Services Program</a> is working on an ongoing <a href="/facts/Launch_Services_Program/sUJToucI">slosh fluid dynamics experiments</a> with partners called CRYOTE. As of 2010, ULA is also planning additional in-space laboratory experiments to further develop <a href="/facts/Centaur_(rocket_stage)/ryg96uIF">cryogenic fluid management</a> technologies using the Centaur upper stage after primary payload separation. Named CRYOTE, or CRYogenic Orbital TEstbed, it will be a testbed for demonstrating a number of technologies needed for cryogenic propellant depots, with several small-scale demonstrations planned for 2012–2014.<a class="footnote-ref" id="fnref:41" href="#fn:41">41</a> As of August 2011, ULA said this mission could launch as soon as 2012 if funded.<a class="footnote-ref" id="fnref:42" href="#fn:42">42</a> The ULA CRYOTE small-scale demonstrations are intended to lead to a ULA large-scale cryo-sat <a href="/facts/Flagship_technology_demonstrations/vMw3l3fP">flagship technology demonstration</a> in 2015.<a class="footnote-ref" id="fnref:43" href="#fn:43">43</a>
The Future In-Space Operations (FISO) Working Group, a consortium of participants from NASA, industry and academia, discussed propellant depot concepts and plans on several occasions in 2010,<a class="footnote-ref" id="fnref:44" href="#fn:44">44</a> with presentations of optimal depot locations for human space exploration beyond low Earth orbit,<a class="footnote-ref" id="fnref:45" href="#fn:45">45</a> a proposed simpler (single vehicle) first-generation propellant depot<a class="footnote-ref" id="fnref:46" href="#fn:46">46</a> and six important propellant-depot-related technologies for reusable cislunar transportation.<a class="footnote-ref" id="fnref:47" href="#fn:47">47</a>
NASA also has plans to mature techniques for enabling and enhancing space flights that use propellant depots in the "CRYOGENIC Propellant STorage And Transfer (CRYOSTAT) Mission". The CRYOSTAT vehicle was expected to be launched to LEO in 2015.<a class="footnote-ref" id="fnref:48" href="#fn:48">48</a>
The CRYOSTAT architecture comprises technologies in the following categories:<a class="footnote-ref" id="fnref:49" href="#fn:49">49</a>

<ul><li>Storage of Cryogenic Propellants</li>
<li>Cryogenic Fluid Transfer</li>
<li>Instrumentation</li>
<li>Automated Rendezvous and Docking (AR&D)</li>
<li>Cryogenic Based Propulsion</li></ul>
The "Simple Depot" mission was proposed by NASA in 2011 as a potential first PTSD mission, with launch no earlier than 2015, on an <a href="/facts/Atlas_V/5SNgegyt">Atlas V 551</a>. Simple Depot would use the "used" (nearly-emptied) <a href="/facts/Centaur_(rocket_stage)/ryg96uIF">Centaur</a> upper stage LH2 tank for long-term storage of LO2 while LH2 would be stored in the Simple Depot LH2 module, which would be launched with only ambient-temperature gaseous Helium in it. The SD LH2 tank was to be 3 metres (9.8 ft) diameter and 16 metres (52 ft) long, 110 cubic metres (3,900 cu ft) in volume, and store 5 mT of LH2. "At a useful mixture ratio (MR) of 6:1 this quantity of LH2 can be paired with 25.7 mT of LO2, allowing for 0.7 mT of LH2 to be used for vapor cooling, for a total useful propellant mass of 30 mT. ... the described depot would have a boil-off rate approaching 0.1 percent per day, consisting entirely of hydrogen."<a class="footnote-ref" id="fnref:50" href="#fn:50">50</a>
In September 2010, ULA released a Depot-Based Space Transportation Architecture concept to propose propellant depots that could be used as way-stations for other spacecraft to stop and refuel—either in <a href="/facts/Low_Earth_orbit/rq1TwayJ">low Earth orbit</a> (LEO) for beyond-LEO missions, or at <a href="/facts/Lagrangian_point/XCAN4o3P">Lagrangian point</a> <a href="/facts/Lagrange_point/XCAN4o3P">L2</a> for interplanetary missions—at the <a href="/facts/AIAA/fVbwtwh8">AIAA</a> Space 2010 conference. The concept proposes that waste gaseous <a href="/facts/Hydrogen/BoYHjl0J">hydrogen</a>—an inevitable byproduct of long-term <a href="/facts/Liquid_hydrogen/Vpk3Gb8P">liquid hydrogen</a> storage in the <a href="/facts/Radiative_heat_transfer/1PD9jtCv">radiative heat</a> environment of <a href="/facts/Outer_space/R3LRKyFs">space</a>—would be usable as a <a href="/facts/Monopropellant_rocket/P6kj4xvT">monopropellant</a> in a <a href="/facts/Solar_thermal_rocket/bXWbqTxo">solar-thermal propulsion system</a>. The waste hydrogen would be productively used for both <a href="/facts/Orbital_stationkeeping/tNNee2Dm">orbital stationkeeping</a> and <a href="/facts/Spacecraft_attitude_control/hE6aMu26">attitude control</a>, as well as providing limited propellant and thrust to use for <a href="/facts/Orbital_maneuver/HAlEFRSJ">orbital maneuvers</a> to better <a href="/facts/Space_rendezvous/8KlcQyyf">rendezvous</a> with other spacecraft that would be inbound to receive fuel from the depot.<a class="footnote-ref" id="fnref:51" href="#fn:51">51</a> As part of the Depot-Based Space Transportation Architecture, ULA has proposed the <a href="/facts/Advanced_Common_Evolved_Stage/JJuqn6Tq">Advanced Common Evolved Stage</a> (ACES) <a href="/facts/Upper_stage/WNrmgztj">upper stage</a> <a href="/facts/Rocket/b6j4keIl">rocket</a>. ACES hardware is designed from the start as an in-space propellant depot that could be used as way-stations for other rockets to stop and refuel on the way to beyond-LEO or <a href="/facts/Interplanetary_mission/4HGDAA2g">interplanetary</a> missions, and to provide the <a href="/facts/Delta_v/eM4TaG9d">high-energy</a> technical capacity for the cleanup of <a href="/facts/Space_debris/X7YSKlXl">space debris</a>.<a class="footnote-ref" id="fnref:52" href="#fn:52">52</a>
In August 2011, NASA made a significant contractual commitment to the development of propellant depot technology<a class="footnote-ref" id="fnref:53" href="#fn:53">53</a> by funding four aerospace companies to "define demonstration missions that would validate the concept of storing cryogenic propellants in space to reduce the need for large launch vehicles for deep-space exploration."<a class="footnote-ref" id="fnref:54" href="#fn:54">54</a> These study contracts for storing/transferring cryogenic propellants and cryogenic depots were signed with <a href="/facts/Analytical_Mechanics_Associates/srD0zEyR">Analytical Mechanics Associates</a>, <a href="/facts/Boeing_Defense%2c_Space_%2526_Security/aVM9hjR1">Boeing</a>, <a href="/facts/Lockheed_Martin/URp9BQpA">Lockheed Martin</a> and <a href="/facts/Ball_Aerospace/uNA3asxb">Ball Aerospace</a>. Each company was to receive <a href="/facts/United_States_dollar/naEEDUhC">US$</a>600,000 under the contract.<a class="footnote-ref" id="fnref:55" href="#fn:55">55</a>[needs update]
In April 2021, NASA selected the SpaceX <a href="/facts/Starship_HLS/1bjx1dx2">Lunar Starship</a> with in-orbit refuelling for their initial lunar human landing system.<a class="footnote-ref" id="fnref:56" href="#fn:56">56</a> In 2022, a larger propellant-depot Starship was being planned for Lunar Starship HLS.

<h3>Rest of world</h3>
The <a href="/facts/Chinese_Space_Agency/q3s4bGYt">Chinese Space Agency</a> (CNSA) performed its first satellite-to-satellite on-orbit refueling test in June 2016.<a class="footnote-ref" id="fnref:57" href="#fn:57">57</a>

<h2 id="engineering-design-issues">Engineering design issues</h2>
There are a number of design issues with propellant depots, as well as several tasks that have not, to date, been tested in space for <a href="/facts/On-orbit_satellite_servicing/k8mwdQhx">on-orbit servicing</a> missions. The design issues include propellant settling and transfer, propellant usage for attitude control and reboost, the maturity of the refrigeration equipment/cryocoolers, and the power and mass required for reduced or zero boiloff depots with refrigeration.

<h3>Propellant settling</h3>
Transfer of liquid propellants in <a href="/facts/Microgravity/3bwWnSlj">microgravity</a> is complicated by the uncertain distribution of liquid and gasses within a tank. Propellant settling at an in-space depot is thus more challenging than in even a slight gravity field. ULA plans to use the <a href="/facts/Defense_Meteorological_Satellite_Program/zsXW89Nl">DMSP</a>-18 mission to flight-test centrifugal propellant settling as a cryogenic fuel management technique that might be used in future propellant depots.<a class="footnote-ref" id="fnref:58" href="#fn:58">58</a> The proposed Simple Depot PTSD mission would use several techniques to achieve adequate settling for propellant transfer.<a class="footnote-ref" id="fnref:59" href="#fn:59">59</a>

<h3>Propellant transfer</h3>
In the absence of gravity, propellant transfer is somewhat more difficult, since liquids can float away from the inlet.
As part of the <a href="/facts/Orbital_Express/3eVDG0Tw">Orbital Express</a> mission in 2007, <a href="/facts/Hydrazine/G7P5ITzU">hydrazine</a> propellant was successfully transferred between two single-purpose designed technology demonstration spacecraft. The <a href="/facts/Boeing/tF5sMe9F">Boeing</a> servicing spacecraft <a href="/facts/ASTRO_(satellite)/69PxGnTf">ASTRO</a> transferred propellant to the <a href="/facts/Ball_Aerospace/uNA3asxb">Ball Aerospace</a> serviceable client spacecraft <a href="/facts/NEXTSat/RKRgymgS">NEXTSat</a>. Since no crew were present on either spacecraft, this was reported as the first autonomous spacecraft-to-spacecraft fluid transfer.<a class="footnote-ref" id="fnref:60" href="#fn:60">60</a>

<h3>Refilling</h3>
After propellant has been transferred to a customer, the depot's tanks will need refilling. Organizing the construction and <a href="/facts/Space_logistics/3D6pBpHD">launch of the tanker rockets bearing the new fuel</a> is the responsibility of the propellant depot's operator. Since space agencies like NASA hope to be purchasers rather than owners, possible operators include the aerospace company that constructed the depot, manufacturers of the rockets, a specialist space depot company, or an oil/chemical company that refines the propellant. By using several tanker rockets the tankers can be smaller than the depot and larger than the spacecraft they are intended to resupply. Short range chemical propulsion tugs belonging to the depot may be used to simplify docking tanker rockets and large vehicles like Mars Transfer Vehicles.
Transfers of propellant between a LEO depot, reachable by rockets from Earth, and the possible deep space ones such as at the <a href="/facts/Lagrange_Point/XCAN4o3P">Lagrange Points</a> and Phobos depots could be performed using <a href="/facts/Solar_electric_propulsion/UHLjgpPq">Solar electric propulsion</a> (SEP) tugs.<a class="footnote-ref" id="fnref:61" href="#fn:61">61</a>
Two missions are currently under development or proposed to support propellant depot refilling. 

<ul><li>In addition to refueling and servicing <a href="/facts/Geostationary/VBq1v5Kr">geostationary</a> communications satellites with the fuel that is initially launched with the MDA <a href="/facts/Space_Infrastructure_Servicing/poqymNfM">Space Infrastructure Servicing</a> vehicle, the SIS vehicle is being designed to have the ability to <a href="/facts/Orbital_maneuver/HAlEFRSJ">orbitally maneuver</a> to <a href="/facts/Space_rendezvous/8KlcQyyf">rendezvous</a> with a replacement fuel canister after transferring the 2000 kg of fuel in the launch load, enabling further refueling of additional satellites after the initial multi-satellite servicing mission is complete.<a class="footnote-ref" id="fnref:62" href="#fn:62">62</a></li>
<li>The proposed Simple Depot cryogenic PTSD (Propellant Transfer and Storage Demonstration) mission would uses "remote berthing arm and docking and fluid transfer ports" both for propellant transfer to other vehicles, as well as for refilling the depot up to the full 30 tonne propellant capacity.<a class="footnote-ref" id="fnref:63" href="#fn:63">63</a> It was proposed in 2010, for launch in 2015.[needs update]</li></ul>
In 1962, S.T. Demetriades<a class="footnote-ref" id="fnref:64" href="#fn:64">64</a> proposed a method for refilling by collecting atmospheric gases. Moving in <a href="/facts/Low_Earth_orbit/rq1TwayJ">low Earth orbit</a>, at an altitude of around 120 km, Demetriades' proposed depot extracts air from the fringes of the atmosphere, compresses and cools it, and extracts liquid oxygen. The remaining nitrogen is used as propellant for a nuclear-powered <a href="/facts/Magnetohydrodynamics/7mQbJPPD">magnetohydrodynamic</a> engine, which maintains the orbit, compensating for atmospheric <a href="/facts/Drag_(physics)/vdl4jF7I">drag</a>.<a class="footnote-ref" id="fnref:65" href="#fn:65">65</a> This system was called "PROFAC" (<a href="/facts/Propulsive_Fluid_Accumulator/1u6VWfHs">PROpulsive Fluid ACcumulator</a>).<a class="footnote-ref" id="fnref:66" href="#fn:66">66</a> There are, however, safety concerns with placing a nuclear reactor in low Earth orbit.
Demetriades' proposal was further refined by Christopher Jones and others<a class="footnote-ref" id="fnref:67" href="#fn:67">67</a> In this proposal, multiple collection vehicles accumulate propellant gases at around 120 km altitude, later transferring them to a higher orbit. However, Jones' proposal does require a network of <a href="/facts/Space-based_solar_power/sQsRh0VI">orbital power-beaming satellites</a>, to avoid placing nuclear reactors in orbit.
Asteroids can also be processed to provide liquid oxygen.<a class="footnote-ref" id="fnref:68" href="#fn:68">68</a>

<h3>Orbital planes and launch windows</h3>
Propellant depots in LEO are of little use for transfer between two low earth orbits when the depot is in a different orbital plane than the target orbit. The <a href="/facts/Delta-v/eM4TaG9d">delta-v</a> to make the necessary <a href="/facts/Orbital_inclination_change/WeGWjHB1">plane change</a> is typically extremely high. On the other hand, depots are typically proposed for exploration missions, where the change over time of the depot's orbit can be chosen to align with the departure vector. This allows one well-aligned departure time minimizing fuel use that requires a very precisely-timed departure. Less efficient departure times from the same depot to the same destination exist before and after the well-aligned opportunity, but more research is required to show whether the efficiency falls off quickly or slowly. By contrast, launching directly in only one launch from the ground without orbital refueling or docking with another craft already on orbit offers daily launch opportunities though it requires larger and more expensive launchers.<a class="footnote-ref" id="fnref:69" href="#fn:69">69</a>
The restrictions on departure windows arise because low earth orbits are susceptible to significant perturbations; even over short periods they are subject to <a href="/facts/Nodal_regression/y0C7XwpN">nodal regression</a> and, less importantly, <a href="/facts/Precession/44Sk1PMD">precession</a> of perigee. Equatorial depots are more stable but also more difficult to reach.<a class="footnote-ref" id="fnref:70" href="#fn:70">70</a>
New approaches have been discovered for LEO to interplanetary orbital transfers where a three-burn orbital transfer is used, which includes a plane change at apogee in a highly-elliptical phasing orbit, in which the incremental delta-v is small—typically less than five percent of the total delta-v—"enabling departures to deep-space destinations [taking] advantage of a depot in LEO" and providing frequent departure opportunities.<a class="footnote-ref" id="fnref:71" href="#fn:71">71</a> More specifically, the 3-burn departure strategy has been shown to enable a single LEO depot in an <a href="/facts/International_Space_Station/VNPUBz9m">ISS</a>-inclination orbit (51 degrees) to dispatch nine spacecraft to "nine different <a href="/facts/Interplanetary_spaceflight/4HGDAA2g">interplanetary</a> targets [where the depot need not] perform any phasing maneuvers to align with any of the departure asymptotes ... [including enabling] extending the economic benefits of dedicated <a href="/facts/Smallsat/vXN5EwvX">smallsat</a> launch to interplanetary missions."<a class="footnote-ref" id="fnref:72" href="#fn:72">72</a>

<h3>Specific issues of cryogenic depots</h3>
<h4>Boil-off mitigation</h4>
Boil-off of <a href="/facts/Cryogenic/cw7dHAkp">cryogenic</a> propellants in space may be mitigated by both technological solutions as well as system-level <a href="/facts/Space_logistics/3D6pBpHD">planning and design</a>. From a technical perspective: for a propellant depot with passive insulation system to effectively store <a href="/facts/Cryogenic/cw7dHAkp">cryogenic</a> fluids, boil-off caused by heating from <a href="/facts/Radiative_heat_transfer/1PD9jtCv">solar</a> and other sources must be mitigated, eliminated,<a class="footnote-ref" id="fnref:73" href="#fn:73">73</a> or used for economic purposes.<a class="footnote-ref" id="fnref:74" href="#fn:74">74</a> For non-cryogenic propellants, boil-off is not a significant design problem.
Boil-off rate is governed by heat leakage and by the quantity of propellant in the tanks. With partially filled tanks, the percentage loss is higher. Heat leakage depends on surface area, while the original mass of propellant in the tanks depends on volume. So by the <a href="/facts/Cube-square_law/nq45ymy6">cube-square law</a>, the smaller the tank, the faster the liquids will boil off. Some propellant tank designs have achieved a liquid hydrogen boil off rate as low as approximately 0.13% per day (3.8% per month) while the much higher temperature cryogenic fluid of liquid oxygen would boil off much less, about 0.016% per day (0.49% per month).<a class="footnote-ref" id="fnref:75" href="#fn:75">75</a>
It is possible to achieve zero boil-off (ZBO) with cryogenic propellant storage using an active thermal control system. Tests conducted at the NASA <a href="/facts/Glenn_Research_Center/H3cpgMVT">Lewis Research Center</a>'s Supplemental Multilayer Insulation Research Facility (SMIRF) over the summer of 1998 demonstrated that a hybrid thermal control system could eliminate boiloff of cryogenic propellants. The hardware consisted of a pressurized 50 cu ft (1,400 litres) tank insulated with 34 <a href="/facts/Multi-layer_insulation/3yn2DFYe">layers of insulation</a>, a condenser, and a <a href="/facts/Cryocooler/7cs7ygf2">Gifford-McMahon (GM) cryocooler</a> that has a cooling capacity of 15 to 17.5 watts (W). Liquid hydrogen was the test fluid. The test tank was installed into a vacuum chamber, simulating space vacuum.<a class="footnote-ref" id="fnref:76" href="#fn:76">76</a>
In 2001, a cooperative effort by NASA's <a href="/facts/Ames_Research_Center/DQUsdLam">Ames Research Center</a>, <a href="/facts/Glenn_Research_Center/H3cpgMVT">Glenn Research Center</a>, and <a href="/facts/Marshall_Space_Flight_Center/Q5XqseqT">Marshall Space Flight Center</a> (MSFC) was implemented to develop ZBO concepts for in-space cryogenic storage. The main program element was a large-scale, ZBO demonstration using the MSFC multipurpose hydrogen test bed (MHTB) – 18.10 m3 LH2 tank (about 1300 kg of H2). A commercial cryocooler was interfaced with an existing MHTB spray bar mixer and insulation system in a manner that enabled a balance between incoming and extracted thermal energy.<a class="footnote-ref" id="fnref:77" href="#fn:77">77</a>
Another NASA study in June 2003 for conceptual Mars mission showed mass savings over traditional, passive-only cryogenic storage when mission durations are 5 days in LEO for oxygen, 8.5 days for methane and 64 days for hydrogen. Longer missions equate to greater mass savings. Cryogenic xenon saves mass over passive storage almost immediately. When power to run the ZBO is already available, the break-even mission durations are even shorter, e.g. about a month for hydrogen. The larger the tank, the fewer days in LEO when ZBO has reduced mass.<a class="footnote-ref" id="fnref:78" href="#fn:78">78</a>
In addition to technical solutions to the challenge of excessive boil-off of cryogenic rocket propellants, system-level solutions have been proposed. From a systems perspective, reductions in the standby time of the <a href="/facts/LH2/Vpk3Gb8P">liquid H2</a> cryogenic storage in order to achieve, effectively, a <a href="/facts/Just_in_time_(business)/h4dNAj42">just in time</a> delivery to each customer, matched with the balanced <a href="/facts/Oil_refinery/yeaW0UMv">refinery</a> technology to split the long-term storable feedstock—water—into the <a href="/facts/Stoichiometric/I5p9cJzV">stoichiometric</a> <a href="/facts/LOX/qnI0KDTb">LOX</a>/<a href="/facts/LH2/Vpk3Gb8P">LH2</a> necessary, is theoretically capable of achieving a system-level solution to boil-off. Such proposals have been suggested as supplementing good technological techniques to reduce boil-off, but would not replace the need for efficient technological storage solutions.<a class="footnote-ref" id="fnref:79" href="#fn:79">79</a>

<h4>Sun shields</h4>
<a href="/facts/United_Launch_Alliance/yWev1ndb">United Launch Alliance</a> (ULA) has proposed a cryogenic depot which would use a conical sun shield to protect the cold propellants from solar and Earth radiation. The open end of the cone allows residual heat to radiate to the cold of deep space, while the closed cone layers attenuates the radiative heat from the Sun and Earth.<a class="footnote-ref" id="fnref:80" href="#fn:80">80</a>

<h4>Other issues</h4>
Other issues are <a href="/facts/Hydrogen_embrittlement/J3JCu2Y6">hydrogen embrittlement</a>, a process by which some metals (including <a href="/facts/Iron/QK1JYy8E">iron</a> and <a href="/facts/Titanium/53ArnDoy">titanium</a>) become brittle and fracture following exposure to hydrogen. The resulting leaks make storing cryogenic propellants in zero gravity conditions difficult.<a class="footnote-ref" id="fnref:81" href="#fn:81">81</a>

<h2 id="in-space-refueling-demonstration-projects">In-space refueling demonstration projects</h2>
In the early 2010s, several in-space refueling projects got underway. Two <a href="/facts/Private_spaceflight/9rSz8Lhh">private initiatives</a> and a government sponsored test mission were in some level of <a href="/facts/New_product_development/ogcXTIco">development</a> or testing as of 2010.

<h3>Robotic Refueling Mission</h3>
The NASA <a href="/facts/Robotic_Refueling_Mission/cIKPz109">Robotic Refueling Mission</a> (RRM) was launched in 2011 and successfully completed a series of <a href="/facts/Robotics/wkmvodJz">robotically actuated</a> <a href="/facts/Propellant_transfer/srD0zEyR">propellant transfer</a> experiments on the exposed facility platform of the International Space Station in January 2013.<a class="footnote-ref" id="fnref:82" href="#fn:82">82</a>
The set of experiments included a number of propellant <a href="/facts/Valve/EwgqAwlJ">valves</a>, <a href="/facts/Nozzle/9z8wqmEC">nozzles</a> and <a href="/facts/Seal_(mechanical)/fS9VcknS">seals</a> similar to those used on many satellites and a series of four <a href="/facts/Prototype/q0yPLYdb">prototype</a> tools that could be attached to the distal end of a Space Station <a href="/facts/Robotic_arm/hGezrM9c">robotic arm</a>. Each tool was a prototype of "devices that could be used by future satellite servicing missions to refuel spacecraft in orbit. RRM is the first in-space refueling demonstration using a platform and fuel valve representative of most existing satellites, which were never designed for refueling. Other satellite servicing demos, such as the U.S. military's <a href="/facts/Orbital_Express/3eVDG0Tw">Orbital Express</a> mission in 2007, transferred propellant between satellites with specially-built pumps and connections."<a class="footnote-ref" id="fnref:83" href="#fn:83">83</a>

<h3>MDA in-space refueling demonstration project</h3>
Main article: <a href="/facts/MDA_Space_Infrastructure_Servicing_vehicle/poqymNfM">MDA Space Infrastructure Servicing vehicle</a>
As of March 2010, a small-scale refueling demonstration project for <a href="/facts/Reaction_control_system/YfqBrd7h">reaction control system</a> (RCS) fluids was under development. <a href="/facts/Canada/cWWFM8oc">Canada</a>-based <a href="/facts/MDA_Corporation/f0kV7rVF">MDA Corporation</a> announced in early 2010 that they were designing a single spacecraft that would refuel other spacecraft in orbit as a satellite-servicing demonstration. "The business model, which is still evolving, could ask customers to pay per kilogram of fuel successfully added to their satellite, with the per-kilogram price being a function of the additional revenue the operator can expect to generate from the spacecraft's extended operational life."<a class="footnote-ref" id="fnref:84" href="#fn:84">84</a>
The plan is that the fuel-depot vehicle would <a href="/facts/Orbital_maneuver/HAlEFRSJ">maneuver</a> to an operational <a href="/facts/Communications_satellite/y5RXPMDT">communications satellite</a>, dock at the target satellite's <a href="/facts/Apogee_kick_motor/Tf9SgQFP">apogee-kick motor</a>, remove a small part of the target spacecraft's thermal protection blanket, connect to a fuel-pressure line and deliver the propellant. "MDA officials estimate the docking maneuver would take the communications satellite out of service for about 20 minutes."<a class="footnote-ref" id="fnref:85" href="#fn:85">85</a>
As of March 2011, MDA had secured a major customer for the initial demonstration project. <a href="/facts/Intelsat/uktuBLn9">Intelsat</a> agreed to purchase one-half of the 2,000 kilograms (4,400 lb) of propellant payload that the MDA spacecraft would carry into <a href="/facts/Geostationary_orbit/VBq1v5Kr">geostationary orbit</a>. Such a purchase would add somewhere between two and four years of additional service life for up to five Intelsat satellites, assuming 200 kg of fuel is delivered to each one.<a class="footnote-ref" id="fnref:86" href="#fn:86">86</a> As of March 2010, the spacecraft could be ready to begin refueling communication satellites by 2015.<a class="footnote-ref" id="fnref:87" href="#fn:87">87</a> As of January 2013, no customers had signed up for an MDA refueling mission.<a class="footnote-ref" id="fnref:88" href="#fn:88">88</a>
In 2017, MDA announced that it was restarting its satellite servicing business, with Luxembourg-based satellite owner/operator <a href="/facts/SES_S.A./rmak3edy">SES S.A.</a> as its first customer.<a class="footnote-ref" id="fnref:89" href="#fn:89">89</a>

<h3>Space tug alternatives to direct refueling</h3>
<a href="/facts/Competition/FpQaEhHv">Competitive</a> design alternatives to in-space <a href="/facts/Reaction_control_system/YfqBrd7h">RCS</a> fuel transfer exist. It is possible to bring additional propellant to a space asset, and use the propellant for attitude control or orbital velocity change, without ever <a href="/facts/Propellant_transfer/srD0zEyR">transferring</a> the propellant to the target space asset.
The <a href="/facts/ViviSat/5nM5QDyy">ViviSat</a> <a href="/facts/Mission_Extension_Vehicle/5nM5QDyy">Mission Extension Vehicle</a>, also under development since the early 2010s, illustrates one alternative approach that would connect to the target satellite similarly to MDA SIS, via the kick motor, but would not transfer fuel. Rather, the Mission Extension Vehicle would use "its own thrusters to supply <a href="/facts/Spacecraft_attitude_control/hE6aMu26">attitude control</a> for the target."<a class="footnote-ref" id="fnref:90" href="#fn:90">90</a> ViviSat believes their approach is more simple and can operate at lower cost than the MDA propellant transfer approach, while having the technical ability to dock with and service a greater number (90 percent) of the approximately 450 <a href="/facts/Geostationary_orbit/VBq1v5Kr">geostationary</a> satellites in orbit.<a class="footnote-ref" id="fnref:91" href="#fn:91">91</a> As of January 2013, no customers had signed up for a ViviSat-enabled mission extension.<a class="footnote-ref" id="fnref:92" href="#fn:92">92</a>
In 2015, <a href="/facts/Lockheed_Martin/URp9BQpA">Lockheed Martin</a> proposed the <a href="/facts/Jupiter_(spacecraft)/M83Y1lAJ">Jupiter</a> <a href="/facts/Space_tug/TSHIGzdX">space tug</a>. If built, Jupiter would operate in <a href="/facts/Low_Earth_orbit/rq1TwayJ">low Earth orbit</a> shuttling <a href="/facts/Exoliner/M83Y1lAJ">cargo carriers</a> to and from the <a href="/facts/International_Space_Station/VNPUBz9m">International Space Station</a>, remaining on orbit indefinitely, and refueling itself from subsequent transport ships carrying later cargo carrier modules.<a class="footnote-ref" id="fnref:93" href="#fn:93">93</a>

<h3>New Space Involvement</h3>
In December 2018, <a href="/facts/Orbit_Fab/4Vr6aeh7">Orbit Fab</a>, a silicon valley startup company founded in early 2018, flew the first of a series of experiments to the ISS in order to test and demonstrate technologies to allow for commercial in space refueling. These first rounds of testing used water as a propellant simulant.<a class="footnote-ref" id="fnref:94" href="#fn:94">94</a> In June 2021, <a href="/facts/Orbit_Fab/4Vr6aeh7">Orbit Fab</a> flew the first propellant depot, Tanker-001 Tenzing, carrying <a href="/facts/Hydrogen_Peroxide/vju6HBIc">Hydrogen Peroxide</a> in <a href="/facts/Sun-synchronous_orbit/3HonupUd">Sun-synchronous orbit</a>.<a class="footnote-ref" id="fnref:95" href="#fn:95">95</a>

<h2 id="gallery">Gallery</h2>

<h2 id="see-also">See also</h2>
<ul><li><a href="/facts/Progress_(spacecraft)/l9GvvKLs">Progress (spacecraft)</a></li>
<li><a href="/facts/Automated_Transfer_Vehicle/sHdKC0wv">Automated Transfer Vehicle</a></li>
<li><a href="/facts/Liquid_rocket_propellants/s0KadvqW">Liquid rocket propellants</a></li>
<li><a href="/facts/Asteroid_mining/jT1XUpBn">Asteroid mining</a></li>
<li><a href="/facts/Propulsive_Fluid_Accumulator/1u6VWfHs">Propulsive Fluid Accumulator</a>, satellite that gathers oxygen and other gasses to supply the depot</li>
<li><a href="/facts/Flexible_path/Hx97fsmB">Flexible path</a> option of the <a href="/facts/Review_of_United_States_Human_Space_Flight_Plans_Committee/YyjpuvKh">Review of United States Human Space Flight Plans Committee</a></li>
<li><a href="/facts/In-situ_resource_utilization/nfgDk04a">In-situ resource utilization</a></li>
<li><a href="/facts/Shackleton_Energy_Company/uwME0lwS">Shackleton Energy Company</a></li>
<li><a href="/facts/Aquarius_Launch_Vehicle/MRKI105x">Aquarius Launch Vehicle</a></li>
<li><a href="/facts/Quicklaunch/ARGQ9loa">Quicklaunch</a></li></ul>

<h2 id="external-links">External links</h2>

Wikimedia Commons has media related to Orbital propellant depots.

<h3>Text</h3>
<ul><li><a href="https://acuriousguy.blogspot.com/2011/04/backgrounder-for-on-orbit-satellite.html">A Backgrounder for On-Orbit Satellite Servicing</a>, March 2011</li>
<li><a href="https://www.lpi.usra.edu/meetings/leag2007/presentations/20071003.bienhoff.pdf">Presentation of Boeing's proposed LEO Propellant Depot</a>, 2007</li>
<li><a href="https://www.newspacewatch.com/docs/IAC-12.D3.2.3.x15379-NASAStudy.pdf">Evolved Human Space Exploration Architecture Using Commercial Launch/Propellant Depots</a>, Wilhite/Arney/Jones/Chai, October 2012</li>
<li><a href="https://www.ulalaunch.com/uploads/docs/Published_Papers/Extended_Duration/Distributed-Launch-2015.pdf">Distributed Launch – Enabling Beyond LEO Missions</a> <a href="https://web.archive.org/web/20161020011636/http://www.ulalaunch.com/uploads/docs/Published_Papers/Extended_Duration/Distributed-Launch-2015.pdf">Archived</a> October 20, 2016, at the <a href="/facts/Wayback_Machine/nmQ3a6JC">Wayback Machine</a>, United Launch Alliance, September 2015</li></ul>
<h3>Video</h3>
<ul><li><a href="https://www.youtube.com/watch?v=MD9D3xQfqtw">Animation of a Boeing depot launch and refuel operation</a>, November 2011 (1 min)</li>
<li><a href="https://www.youtube.com/watch?v=6kIlepnvCa4">NASA Cryogenic Propellant Depot – Mission Animation</a>, May 2013 (1 min)</li>
<li><a href="https://www.youtube.com/watch?v=WkOZWhSImGg">Advantages of a depot architecture</a>, <a href="/facts/Jeff_Greason/ybwBMggX">Jeff Greason</a> of XCOR Aerospace, Augustine Commission meeting, July 2009 (25 min)</li>
<li><a href="https://www.youtube.com/watch?v=Wy2kIPLsUn0">A Settlement Strategy for NASA</a>, <a href="/facts/Jeff_Greason/ybwBMggX">Jeff Greason</a> of XCOR Aerospace, ISDC 2011 (42 min)</li>
<li><a href="https://www.youtube.com/watch?v=wF5COztiRjI">Cislunar Space, The Next Frontier</a>, Dr. <a href="/facts/Paul_Spudis/FhVTI0Xd">Paul Spudis</a> of the Lunar and Planetary Institute, ISDC 2011 (25 min)</li>
<li><a href="https://www.youtube.com/watch?v=ccrN-tW1YSY">Plan to mine water on the moon using depots</a>, Bill Stone of the <a href="/facts/Shackleton_Energy_Company/uwME0lwS">Shackleton Energy Company</a>, TED 2011 (7 min)</li></ul>

<h2 id="references">References</h2>

<ol>
<li id="fn:1">Pittman, Bruce; Rasky, Dan; Harper, Lynn (2012). "Infrastructure Based Exploration – An Affordable Path To Sustainable Space Development" (PDF). IAC – 12, D3, 2, 4, x14203: IAC. Archived (PDF) from the original on March 21, 2016. Retrieved October 14, 2014.{{cite web}}: CS1 maint: location (link) <a href="https://cammpus.s3.amazonaws.com/resource/file/5351/IAC_Paper_Commercial_Space.pdf" target="_blank">https://cammpus.s3.amazonaws.com/resource/file/5351/IAC_Paper_Commercial_Space.pdf</a> <a href="#fnref:1" class="footnote-back-ref">↩</a></li>
<li id="fn:2">Choi, Charles Q. (January 19, 2012). "Plans Scrapped for Private Robotic Gas Station in Space". Space.com. Archived from the original on November 16, 2018. Retrieved January 24, 2017. <a href="http://www.space.com/14287-satellite-refueling-deal-scrapped-mda-intelsat.html" target="_blank">http://www.space.com/14287-satellite-refueling-deal-scrapped-mda-intelsat.html</a> <a href="#fnref:2" class="footnote-back-ref">↩</a></li>
<li id="fn:3">Goff, Jon; et al. (2009). "Realistic Near-Term Propellant Depots" (PDF). American Institute of Aeronautics and Astronautics. p. 13. Archived (PDF) from the original on February 24, 2020. Retrieved September 23, 2009. <a href="http://selenianboondocks.com/wp-content/uploads/2009/09/NearTermPropellantDepots.pdf" target="_blank">http://selenianboondocks.com/wp-content/uploads/2009/09/NearTermPropellantDepots.pdf</a> <a href="#fnref:3" class="footnote-back-ref">↩</a></li>
<li id="fn:4">"NASA Artemis Mission Progresses with SpaceX Starship Test Flight – NASA". March 14, 2024. Retrieved April 13, 2024. <a href="https://www.nasa.gov/directorates/esdmd/artemis-campaign-development-division/human-landing-system-program/nasa-artemis-mission-progresses-with-spacex-starship-test-flight/" target="_blank">https://www.nasa.gov/directorates/esdmd/artemis-campaign-development-division/human-landing-system-program/nasa-artemis-mission-progresses-with-spacex-starship-test-flight/</a> <a href="#fnref:4" class="footnote-back-ref">↩</a></li>
<li id="fn:5">Clark, Stephen (April 30, 2024). "NASA lays out how SpaceX will refuel Starships in low-Earth orbit". Ars Technica. Retrieved October 13, 2024. <a href="https://arstechnica.com/space/2024/04/nasa-exploration-chief-lays-out-next-steps-for-starship-development/" target="_blank">https://arstechnica.com/space/2024/04/nasa-exploration-chief-lays-out-next-steps-for-starship-development/</a> <a href="#fnref:5" class="footnote-back-ref">↩</a></li>
<li id="fn:6">Clark, Stephen (April 30, 2024). "NASA lays out how SpaceX will refuel Starships in low-Earth orbit". Ars Technica. Retrieved October 13, 2024. <a href="https://arstechnica.com/space/2024/04/nasa-exploration-chief-lays-out-next-steps-for-starship-development/" target="_blank">https://arstechnica.com/space/2024/04/nasa-exploration-chief-lays-out-next-steps-for-starship-development/</a> <a href="#fnref:6" class="footnote-back-ref">↩</a></li>
<li id="fn:7">Thunnissen, Daniel P.; Guernsey, C. S.; Baker, R. S.; Miyake, R. N. (July 2004). Advanced Space Storable Propellants for Outer Planet Exploration. 40th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit, Ft. Lauderdale, Florida, July 11–14, 2004. hdl:2014/37950. AIAA 2004-0799. <a href="/wiki/Hdl_(identifier)" target="_blank">/wiki/Hdl_(identifier)</a> <a href="#fnref:7" class="footnote-back-ref">↩</a></li>
<li id="fn:8">Wright, Mike (April 6, 1999). "Ion Propulsion – 50 Years in the Making". NASA.gov. Archived from the original on May 29, 2020. Retrieved July 12, 2017. <a href="https://science.nasa.gov/science-news/science-at-nasa/1999/prop06apr99_2/" target="_blank">https://science.nasa.gov/science-news/science-at-nasa/1999/prop06apr99_2/</a> <a href="#fnref:8" class="footnote-back-ref">↩</a></li>
<li id="fn:9">"Technology". Ad Astra Rocket Company. Archived from the original on May 22, 2013. <a href="https://web.archive.org/web/20130522003114/http://www.adastrarocket.com/aarc/Technology" target="_blank">https://web.archive.org/web/20130522003114/http://www.adastrarocket.com/aarc/Technology</a> <a href="#fnref:9" class="footnote-back-ref">↩</a></li>
<li id="fn:10">Massey, Dean R.; King, Lyon B.; Makela, Jason M. (July 2008). "Development of a Direct Evaporation Bismuth Hall Thruster". 44th AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit. 44th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit, Hartford, Connecticut, July 21–23, 2008. doi:10.2514/6.2008-4520. ISBN 978-1-60086-992-1. AIAA 2008-4520. Archived from the original on April 30, 2019. Retrieved May 12, 2020. <a href="978-1-60086-992-1" target="_blank">978-1-60086-992-1</a> <a href="#fnref:10" class="footnote-back-ref">↩</a></li>
<li id="fn:11">NASA.gov Archived June 22, 2017, at the Wayback Machine Remarks For AIAA Space 2005 Conference & Exhibition. <a href="https://www.nasa.gov/pdf/138033main_griffin_aas1.pdf" target="_blank">https://www.nasa.gov/pdf/138033main_griffin_aas1.pdf</a> <a href="#fnref:11" class="footnote-back-ref">↩</a></li>
<li id="fn:12">Goff, Jon; et al. (2009). "Realistic Near-Term Propellant Depots" (PDF). American Institute of Aeronautics and Astronautics. Archived (PDF) from the original on February 24, 2020. Retrieved September 23, 2009. page 10 <a href="http://selenianboondocks.com/wp-content/uploads/2009/09/NearTermPropellantDepots.pdf" target="_blank">http://selenianboondocks.com/wp-content/uploads/2009/09/NearTermPropellantDepots.pdf</a> <a href="#fnref:12" class="footnote-back-ref">↩</a></li>
<li id="fn:13">Wilhite, Alan. "A Sustainable Evolved Human Space Exploration Architecture Using Commercial Launch and Propellant Depots" (PDF). FISO Telecon (February 13, 2013). Archived from the original (PDF) on July 4, 2014. Retrieved February 21, 2013. <a href="https://web.archive.org/web/20140704093405/http://spirit.as.utexas.edu/~fiso/telecon/Wilhite_2-13-13/Wilhite_2-13-13.pdf" target="_blank">https://web.archive.org/web/20140704093405/http://spirit.as.utexas.edu/~fiso/telecon/Wilhite_2-13-13/Wilhite_2-13-13.pdf</a> <a href="#fnref:13" class="footnote-back-ref">↩</a></li>
<li id="fn:14">"Near Term Space Exploration with Commercial Launch Vehicles Plus Propellant Depot" (PDF). Georgia Institute of Technology / National Institute of Aerospace. 2011. Archived (PDF) from the original on February 4, 2016. Retrieved January 30, 2012. <a href="http://images.spaceref.com/news/2011/F9Prop.Depot.pdf" target="_blank">http://images.spaceref.com/news/2011/F9Prop.Depot.pdf</a> <a href="#fnref:14" class="footnote-back-ref">↩</a></li>
<li id="fn:15">Holiday, J.; et al. (November 1, 2010). "Ares V Utilization in Support of a Human Mission to Mars". Archived from the original on June 18, 2016. Retrieved October 19, 2016. <a href="https://ntrs.nasa.gov/search.jsp?R=20100042324" target="_blank">https://ntrs.nasa.gov/search.jsp?R=20100042324</a> <a href="#fnref:15" class="footnote-back-ref">↩</a></li>
<li id="fn:16">HSF Final Report: Seeking a Human Spaceflight Program Worthy of a Great Nation Archived February 16, 2019, at the Wayback Machine, October 2009, Review of U.S. Human Spaceflight Plans Committee, pp. 65–66. <a href="https://www.nasa.gov/pdf/396093main_HSF_Cmte_FinalReport.pdf" target="_blank">https://www.nasa.gov/pdf/396093main_HSF_Cmte_FinalReport.pdf</a> <a href="#fnref:16" class="footnote-back-ref">↩</a></li>
<li id="fn:17">HSF Final Report: Seeking a Human Spaceflight Program Worthy of a Great Nation Archived February 16, 2019, at the Wayback Machine, October 2009, Review of U.S. Human Spaceflight Plans Committee, pp. 65–66. <a href="https://www.nasa.gov/pdf/396093main_HSF_Cmte_FinalReport.pdf" target="_blank">https://www.nasa.gov/pdf/396093main_HSF_Cmte_FinalReport.pdf</a> <a href="#fnref:17" class="footnote-back-ref">↩</a></li>
<li id="fn:18">HSF Final Report: Seeking a Human Spaceflight Program Worthy of a Great Nation Archived February 16, 2019, at the Wayback Machine, October 2009, Review of U.S. Human Spaceflight Plans Committee, pp. 65–66. <a href="https://www.nasa.gov/pdf/396093main_HSF_Cmte_FinalReport.pdf" target="_blank">https://www.nasa.gov/pdf/396093main_HSF_Cmte_FinalReport.pdf</a> <a href="#fnref:18" class="footnote-back-ref">↩</a></li>
<li id="fn:19">Zegler, Frank; Kutter, Bernard (September 2, 2010). Evolving to a Depot-Based Space Transportation Architecture (PDF). AIAA SPACE 2010 Conference & Exposition. American Institute of Aeronautics and Astronautics. Archived from the original (PDF) on June 24, 2014. Retrieved October 31, 2016. ACES design conceptualization has been underway at ULA for many years. It leverages design features of both the Centaur and Delta Cryogenic Second Stage (DCSS) upper stages and intends to supplement and perhaps replace these stages in the future. The baseline ACES will contain twice the Centaur or 4m DCSS propellant load, providing a significant performance boost compared to our existing upper stages. The baseline 41-mT propellant load is contained in a 5m diameter, common bulkhead stage that is about the same length as ULA's existing upper stages. ACES will become the foundation for a modular system of stages to meet the launch requirements of a wide variety of users. A common variant is a stretched version containing 73t of propellant. <a href="https://web.archive.org/web/20140624125633/http://www.ulalaunch.com/uploads/docs/Published_Papers/Exploration/DepotBasedTransportationArchitecture2010.pdf" target="_blank">https://web.archive.org/web/20140624125633/http://www.ulalaunch.com/uploads/docs/Published_Papers/Exploration/DepotBasedTransportationArchitecture2010.pdf</a> <a href="#fnref:19" class="footnote-back-ref">↩</a></li>
<li id="fn:20">Ray, Justin (April 14, 2015). "ULA chief explains reusability and innovation of new rocket". Spaceflight Now. Archived from the original on April 17, 2015. Retrieved October 31, 2016. <a href="http://spaceflightnow.com/2015/04/14/ula-chief-explains-reusability-and-innovation-of-new-rocket/" target="_blank">http://spaceflightnow.com/2015/04/14/ula-chief-explains-reusability-and-innovation-of-new-rocket/</a> <a href="#fnref:20" class="footnote-back-ref">↩</a></li>
<li id="fn:21">Boyle, Alan (April 13, 2015). "United Launch Alliance Boldly Names Its Next Rocket: Vulcan!". NBC. Archived from the original on April 14, 2015. Retrieved October 31, 2016. <a href="http://www.nbcnews.com/science/space/united-launch-alliance-boldly-names-its-next-big-rocket-vulcan-n340881" target="_blank">http://www.nbcnews.com/science/space/united-launch-alliance-boldly-names-its-next-big-rocket-vulcan-n340881</a> <a href="#fnref:21" class="footnote-back-ref">↩</a></li>
<li id="fn:22">Elon Musk (September 27, 2016). Making Humans a Multiplanetary Species (video). IAC67, Guadalajara, Mexico: SpaceX. Event occurs at 9:20–10:10. Archived from the original on December 20, 2021. Retrieved October 18, 2016. So it is a bit tricky. Because we have to figure out how to improve the cost of the trips to Mars by five million percent ... translates to an improvement of approximately 4 1/2 orders of magnitude. These are the key elements that are needed in order to achieve a 4 1/2 order of magnitude improvement. Most of the improvement would come from full reusability—somewhere between 2 and 2 1/2 orders of magnitude—and then the other 2 orders of magnitude would come from refilling in orbit, propellant production on Mars, and choosing the right propellant.{{cite AV media}}: CS1 maint: location (link) <a href="https://www.youtube.com/watch?v=H7Uyfqi_TE8" target="_blank">https://www.youtube.com/watch?v=H7Uyfqi_TE8</a> <a href="#fnref:22" class="footnote-back-ref">↩</a></li>
<li id="fn:23">"Making Humans a Multiplanetary Species" (PDF). SpaceX. September 27, 2016. Archived from the original (PDF) on September 28, 2016. Retrieved October 9, 2016. <a href="https://web.archive.org/web/20160928040332/http://www.spacex.com/sites/spacex/files/mars_presentation.pdf" target="_blank">https://web.archive.org/web/20160928040332/http://www.spacex.com/sites/spacex/files/mars_presentation.pdf</a> <a href="#fnref:23" class="footnote-back-ref">↩</a></li>
<li id="fn:24">"Seeker – YouTube". www.youtube.com. Retrieved May 15, 2024. <a href="https://www.youtube.com/channel/UCzWQYUVCpZqtN93H8RR44Qw" target="_blank">https://www.youtube.com/channel/UCzWQYUVCpZqtN93H8RR44Qw</a> <a href="#fnref:24" class="footnote-back-ref">↩</a></li>
<li id="fn:25">Richardson, Derek (September 27, 2016). "Elon Musk Shows Off Interplanetary Transport System". Spaceflight Insider. Archived from the original on October 1, 2016. Retrieved October 18, 2016. <a href="http://www.spaceflightinsider.com/organizations/space-exploration-technologies/elon-musk-shows-off-interplanetary-transport-system/" target="_blank">http://www.spaceflightinsider.com/organizations/space-exploration-technologies/elon-musk-shows-off-interplanetary-transport-system/</a> <a href="#fnref:25" class="footnote-back-ref">↩</a></li>
<li id="fn:26">Foust, Jeff (April 16, 2021). "NASA selects SpaceX to develop crewed lunar lander". SpaceNews. Archived from the original on May 21, 2021. Retrieved April 18, 2021. <a href="https://spacenews.com/nasa-selects-spacex-to-develop-crewed-lunar-lander/" target="_blank">https://spacenews.com/nasa-selects-spacex-to-develop-crewed-lunar-lander/</a> <a href="#fnref:26" class="footnote-back-ref">↩</a></li>
<li id="fn:27">Simberg, Rand (November 4, 2011). "The SLS Empire Strikes Back". Competitivespace.org. Archived from the original on July 3, 2017. Retrieved November 10, 2011. <a href="http://www.competitivespace.org/2011/11/04/the-sls-empire-strikes-back/" target="_blank">http://www.competitivespace.org/2011/11/04/the-sls-empire-strikes-back/</a> <a href="#fnref:27" class="footnote-back-ref">↩</a></li>
<li id="fn:28">Richardson, Derek (September 27, 2016). "Elon Musk Shows Off Interplanetary Transport System". Spaceflight Insider. Archived from the original on October 1, 2016. Retrieved October 18, 2016. <a href="http://www.spaceflightinsider.com/organizations/space-exploration-technologies/elon-musk-shows-off-interplanetary-transport-system/" target="_blank">http://www.spaceflightinsider.com/organizations/space-exploration-technologies/elon-musk-shows-off-interplanetary-transport-system/</a> <a href="#fnref:28" class="footnote-back-ref">↩</a></li>
<li id="fn:29">Simberg, Rand (November 4, 2011). "The SLS Empire Strikes Back". Competitivespace.org. Archived from the original on July 3, 2017. Retrieved November 10, 2011. <a href="http://www.competitivespace.org/2011/11/04/the-sls-empire-strikes-back/" target="_blank">http://www.competitivespace.org/2011/11/04/the-sls-empire-strikes-back/</a> <a href="#fnref:29" class="footnote-back-ref">↩</a></li>
<li id="fn:30">Spudis, Paul D.; Lavoie, Anthony R. (September 29, 2011). "Using the resources of the Moon to create a permanent, cislunar space faring system" (PDF). AIAA Space 2011 Conference & Exposition. 1646: 80. Bibcode:2011LPICo1646...80S. doi:10.2514/6.2011-7185. ISBN 978-1-60086-953-2. Archived (PDF) from the original on January 30, 2012. Retrieved November 10, 2011. <a href="978-1-60086-953-2" target="_blank">978-1-60086-953-2</a> <a href="#fnref:30" class="footnote-back-ref">↩</a></li>
<li id="fn:31">Charania, A. C. (2007). "ECONOMIC ANALYSIS OF A LUNAR IN-SITU RESOURCE UTILIZATION (ISRU) PROPELLANT SERVICES MARKET" (PDF). space works engineering. Archived (PDF) from the original on March 25, 2012. Retrieved March 14, 2012. <a href="http://www.sei.aero/eng/papers/uploads/archive/IAC-07-A5.1.03_present.pdf" target="_blank">http://www.sei.aero/eng/papers/uploads/archive/IAC-07-A5.1.03_present.pdf</a> <a href="#fnref:31" class="footnote-back-ref">↩</a></li>
<li id="fn:32">"Near Term Space Exploration with Commercial Launch Vehicles Plus Propellant Depot" (PDF). Georgia Institute of Technology / National Institute of Aerospace. 2011. Archived (PDF) from the original on February 4, 2016. Retrieved January 30, 2012. <a href="http://images.spaceref.com/news/2011/F9Prop.Depot.pdf" target="_blank">http://images.spaceref.com/news/2011/F9Prop.Depot.pdf</a> <a href="#fnref:32" class="footnote-back-ref">↩</a></li>
<li id="fn:33">Simberg, Rand (November 4, 2011). "The SLS Empire Strikes Back". Competitivespace.org. Archived from the original on July 3, 2017. Retrieved November 10, 2011. <a href="http://www.competitivespace.org/2011/11/04/the-sls-empire-strikes-back/" target="_blank">http://www.competitivespace.org/2011/11/04/the-sls-empire-strikes-back/</a> <a href="#fnref:33" class="footnote-back-ref">↩</a></li>
<li id="fn:34">Cowing, Keith (October 12, 2011). "Internal NASA Studies Show Cheaper and Faster Alternatives to the Space Launch System" (PDF). SpaceRef.com. Archived (PDF) from the original on October 1, 2021. Retrieved November 10, 2011. <a href="http://images.spaceref.com/news/2011/21.jul2011.vxs.pdf" target="_blank">http://images.spaceref.com/news/2011/21.jul2011.vxs.pdf</a> <a href="#fnref:34" class="footnote-back-ref">↩</a></li>
<li id="fn:35">Mohney, Doug (October 21, 2011). "Did NASA Hide In-space Fuel Depots To Get a Heavy Lift Rocket?". Satellite Spotlight. Archived from the original on March 3, 2016. Retrieved November 10, 2011. <a href="http://satellite.tmcnet.com/topics/satellite/articles/230642-did-nasa-hide-in-space-fuel-depots-get.htm" target="_blank">http://satellite.tmcnet.com/topics/satellite/articles/230642-did-nasa-hide-in-space-fuel-depots-get.htm</a> <a href="#fnref:35" class="footnote-back-ref">↩</a></li>
<li id="fn:36">"Propellant Depot Requirements Study" (PDF). HAT Technical Interchange Meeting. SpaceRef.com/nasawatch.com. July 21, 2011. Archived (PDF) from the original on May 5, 2015. Retrieved April 1, 2012. <a href="http://images.spaceref.com/news/2011/21.jul2011.pdf" target="_blank">http://images.spaceref.com/news/2011/21.jul2011.pdf</a> <a href="#fnref:36" class="footnote-back-ref">↩</a></li>
<li id="fn:37">Smitherman, David; Woodcock, Gordon (September 26, 2011). "Space Transportation Infrastructure Supported By Propellant Depots – AIAA Space 2011 – 26 pages" (PDF). ntrs.nasa.gov. Archived (PDF) from the original on September 14, 2020. Retrieved July 7, 2017. <a href="https://ntrs.nasa.gov/archive/nasa/casi.ntrs.nasa.gov/20120001435_2012001131.pdf" target="_blank">https://ntrs.nasa.gov/archive/nasa/casi.ntrs.nasa.gov/20120001435_2012001131.pdf</a> <a href="#fnref:37" class="footnote-back-ref">↩</a></li>
<li id="fn:38">Cowing, Keith (October 12, 2011). "Internal NASA Studies Show Cheaper and Faster Alternatives to the Space Launch System" (PDF). SpaceRef.com. Archived (PDF) from the original on October 1, 2021. Retrieved November 10, 2011. <a href="http://images.spaceref.com/news/2011/21.jul2011.vxs.pdf" target="_blank">http://images.spaceref.com/news/2011/21.jul2011.vxs.pdf</a> <a href="#fnref:38" class="footnote-back-ref">↩</a></li>
<li id="fn:39">Dewar, James. "To The End Of The Solar System: The Story Of The Nuclear Rocket". Apogee, 2003. <a href="#fnref:39" class="footnote-back-ref">↩</a></li>
<li id="fn:40">Successful Flight Demonstration Conducted by the Air Force and United Launch Alliance Will Enhance Space Transportation: DMSP-18, United Launch Alliance, October 2009, accessed January 10, 2011. Archived July 17, 2011, at the Wayback Machine. <a href="http://www.ulalaunch.com/site/docs/publications/SuccessfulFlightDemonstrationConductedbytheAirForceandUnitedLaunchAllianceWillEnhanceSpaceTransportation_.pdf" target="_blank">http://www.ulalaunch.com/site/docs/publications/SuccessfulFlightDemonstrationConductedbytheAirForceandUnitedLaunchAllianceWillEnhanceSpaceTransportation_.pdf</a> <a href="#fnref:40" class="footnote-back-ref">↩</a></li>
<li id="fn:41">Kutter, Bernard. Propellant Depots Made Simple Archived February 6, 2011, at the Wayback Machine, United Launch Alliance, FISO Colloquium, 2010-11-10, accessed January 10, 2011. <a href="http://spirit.as.utexas.edu/~fiso/telecon/Kutter_11-10-10/Kutter_11-10-10.pdf" target="_blank">http://spirit.as.utexas.edu/~fiso/telecon/Kutter_11-10-10/Kutter_11-10-10.pdf</a> <a href="#fnref:41" class="footnote-back-ref">↩</a></li>
<li id="fn:42">Warwick, Graham (August 10, 2011). "ULA Proposes On-Orbit Gas Stations for Space Exploration". Aviation Week. Retrieved September 11, 2011.[permanent dead link] <a href="http://www.aviationweek.com/aw/generic/story_channel.jsp?channel=space&id=news/ULA08109.xml" target="_blank">http://www.aviationweek.com/aw/generic/story_channel.jsp?channel=space&id=news/ULA08109.xml</a> <a href="#fnref:42" class="footnote-back-ref">↩</a></li>
<li id="fn:43">Kutter, Bernard. Propellant Depots Made Simple Archived February 6, 2011, at the Wayback Machine, United Launch Alliance, FISO Colloquium, 2010-11-10, accessed January 10, 2011. <a href="http://spirit.as.utexas.edu/~fiso/telecon/Kutter_11-10-10/Kutter_11-10-10.pdf" target="_blank">http://spirit.as.utexas.edu/~fiso/telecon/Kutter_11-10-10/Kutter_11-10-10.pdf</a> <a href="#fnref:43" class="footnote-back-ref">↩</a></li>
<li id="fn:44">Future In-Space Operations (FISO) Working Group presentations Archived June 15, 2011, at the Wayback Machine, FISO, 2011-01-07, accessed January 10, 2011. <a href="http://www.hobbyspace.com/nucleus/index.php?itemid=26273" target="_blank">http://www.hobbyspace.com/nucleus/index.php?itemid=26273</a> <a href="#fnref:44" class="footnote-back-ref">↩</a></li>
<li id="fn:45">Adamo, Daniel R. Potential Propellant Depot Locations Supporting Beyond-LEO Human Exploration Archived March 17, 2012, at the Wayback Machine, FISO Colloquium, 2010-10-13, accessed August 22, 2011. <a href="http://spirit.as.utexas.edu/~fiso/telecon/Adamo_10-13-10/Adamo_10-13-10%20revised.pdf" target="_blank">http://spirit.as.utexas.edu/~fiso/telecon/Adamo_10-13-10/Adamo_10-13-10%20revised.pdf</a> <a href="#fnref:45" class="footnote-back-ref">↩</a></li>
<li id="fn:46">Kutter, Bernard. Propellant Depots Made Simple Archived February 6, 2011, at the Wayback Machine, United Launch Alliance, FISO Colloquium, 2010-11-10, accessed January 10, 2011. <a href="http://spirit.as.utexas.edu/~fiso/telecon/Kutter_11-10-10/Kutter_11-10-10.pdf" target="_blank">http://spirit.as.utexas.edu/~fiso/telecon/Kutter_11-10-10/Kutter_11-10-10.pdf</a> <a href="#fnref:46" class="footnote-back-ref">↩</a></li>
<li id="fn:47">Bienhoff, Dallas. Top 10 Technologies for Reusable Cislunar Transportation Archived July 20, 2011, at the Wayback Machine, Boeing, FISO Colloquium, 2010-12-01, accessed January 10, 2011. <a href="http://spirit.as.utexas.edu/~fiso/telecon/Bienhoff_12-1-10/Bienhoff-1_12-1-10.pdf" target="_blank">http://spirit.as.utexas.edu/~fiso/telecon/Bienhoff_12-1-10/Bienhoff-1_12-1-10.pdf</a> <a href="#fnref:47" class="footnote-back-ref">↩</a></li>
<li id="fn:48">Davis, Stephan. CRYOGENIC Propellant STorage And Transfer (CRYOSTAT) Mission Archived November 18, 2011, at the Wayback Machine, MSFC, NASA, May 2010. <a href="https://www.nasa.gov/pdf/458814main_FTD_CRYOGENICPropellantSTorageAndTransferMission.pdf" target="_blank">https://www.nasa.gov/pdf/458814main_FTD_CRYOGENICPropellantSTorageAndTransferMission.pdf</a> <a href="#fnref:48" class="footnote-back-ref">↩</a></li>
<li id="fn:49">Davis, Stephan. CRYOGENIC Propellant STorage And Transfer (CRYOSTAT) Mission Archived November 18, 2011, at the Wayback Machine, MSFC, NASA, May 2010. <a href="https://www.nasa.gov/pdf/458814main_FTD_CRYOGENICPropellantSTorageAndTransferMission.pdf" target="_blank">https://www.nasa.gov/pdf/458814main_FTD_CRYOGENICPropellantSTorageAndTransferMission.pdf</a> <a href="#fnref:49" class="footnote-back-ref">↩</a></li>
<li id="fn:50">Bergin, Chris (August 10, 2011). "NASA interest in an interplanetary highway supported by Propellant Depots". NASA Spaceflight. Archived from the original on August 12, 2011. Retrieved August 11, 2011. a LO2/LH2 PTSD (Propellant Transfer and Storage Demonstration) mission by 2015. ... it would be launched on an Atlas 551 ... [which] would provide ~12 mT of Centaur residuals (combined LH2 and LO2) in a 28.5 degrees by 200 nm circular LEO. <a href="http://www.nasaspaceflight.com/2011/08/nasa-interest-interplanetary-highway-supported-propellant-depots/" target="_blank">http://www.nasaspaceflight.com/2011/08/nasa-interest-interplanetary-highway-supported-propellant-depots/</a> <a href="#fnref:50" class="footnote-back-ref">↩</a></li>
<li id="fn:51">Zegler, Frank; Kutter, Bernard (September 2, 2010). "Evolving to a Depot-Based Space Transportation Architecture" (PDF). AIAA SPACE 2010 Conference & Exposition. AIAA. p. 3. Archived from the original (PDF) on July 17, 2011. Retrieved January 25, 2011. the waste hydrogen that has boiled off happens to be the best known propellant (as a monopropellant in a basic solar-thermal propulsion system) for this task. A practical depot must evolve hydrogen at a minimum rate that matches the station keeping demands. <a href="https://web.archive.org/web/20110717150155/http://www.ulalaunch.com/site/docs/publications/DepotBasedTransportationArchitecture2010.pdf" target="_blank">https://web.archive.org/web/20110717150155/http://www.ulalaunch.com/site/docs/publications/DepotBasedTransportationArchitecture2010.pdf</a> <a href="#fnref:51" class="footnote-back-ref">↩</a></li>
<li id="fn:52">Zegler, Frank; Kutter, Bernard (September 2, 2010). Evolving to a Depot-Based Space Transportation Architecture (PDF). AIAA SPACE 2010 Conference & Exposition. American Institute of Aeronautics and Astronautics. Archived from the original (PDF) on June 24, 2014. Retrieved October 31, 2016. ACES design conceptualization has been underway at ULA for many years. It leverages design features of both the Centaur and Delta Cryogenic Second Stage (DCSS) upper stages and intends to supplement and perhaps replace these stages in the future. The baseline ACES will contain twice the Centaur or 4m DCSS propellant load, providing a significant performance boost compared to our existing upper stages. The baseline 41-mT propellant load is contained in a 5m diameter, common bulkhead stage that is about the same length as ULA's existing upper stages. ACES will become the foundation for a modular system of stages to meet the launch requirements of a wide variety of users. A common variant is a stretched version containing 73t of propellant. <a href="https://web.archive.org/web/20140624125633/http://www.ulalaunch.com/uploads/docs/Published_Papers/Exploration/DepotBasedTransportationArchitecture2010.pdf" target="_blank">https://web.archive.org/web/20140624125633/http://www.ulalaunch.com/uploads/docs/Published_Papers/Exploration/DepotBasedTransportationArchitecture2010.pdf</a> <a href="#fnref:52" class="footnote-back-ref">↩</a></li>
<li id="fn:53">Pittman, Bruce; Rasky, Dan; Harper, Lynn (2012). "Infrastructure Based Exploration – An Affordable Path To Sustainable Space Development" (PDF). IAC – 12, D3, 2, 4, x14203: IAC. Archived (PDF) from the original on March 21, 2016. Retrieved October 14, 2014.{{cite web}}: CS1 maint: location (link) <a href="https://cammpus.s3.amazonaws.com/resource/file/5351/IAC_Paper_Commercial_Space.pdf" target="_blank">https://cammpus.s3.amazonaws.com/resource/file/5351/IAC_Paper_Commercial_Space.pdf</a> <a href="#fnref:53" class="footnote-back-ref">↩</a></li>
<li id="fn:54">Morring, Frank Jr. (August 10, 2011). "NASA To Study Cryo Storage In Space". Aviation Week. Retrieved September 11, 2011.[permanent dead link] <a href="http://www.aviationweek.com/aw/generic/story.jsp?id=news/asd/2011/08/10/07.xml" target="_blank">http://www.aviationweek.com/aw/generic/story.jsp?id=news/asd/2011/08/10/07.xml</a> <a href="#fnref:54" class="footnote-back-ref">↩</a></li>
<li id="fn:55">Morring, Frank Jr. (August 10, 2011). "NASA To Study Cryo Storage In Space". Aviation Week. Retrieved September 11, 2011.[permanent dead link] <a href="http://www.aviationweek.com/aw/generic/story.jsp?id=news/asd/2011/08/10/07.xml" target="_blank">http://www.aviationweek.com/aw/generic/story.jsp?id=news/asd/2011/08/10/07.xml</a> <a href="#fnref:55" class="footnote-back-ref">↩</a></li>
<li id="fn:56">Foust, Jeff (April 16, 2021). "NASA selects SpaceX to develop crewed lunar lander". SpaceNews. Archived from the original on May 21, 2021. Retrieved April 18, 2021. <a href="https://spacenews.com/nasa-selects-spacex-to-develop-crewed-lunar-lander/" target="_blank">https://spacenews.com/nasa-selects-spacex-to-develop-crewed-lunar-lander/</a> <a href="#fnref:56" class="footnote-back-ref">↩</a></li>
<li id="fn:57">"Space: China Achieves Orbital Refueling". StrategyPage. July 6, 2016. Archived from the original on July 10, 2016. Retrieved July 10, 2016. <a href="http://strategypage.com/htmw/htspace/20160706.aspx" target="_blank">http://strategypage.com/htmw/htspace/20160706.aspx</a> <a href="#fnref:57" class="footnote-back-ref">↩</a></li>
<li id="fn:58">Goff, Jon; et al. (2009). "Realistic Near-Term Propellant Depots" (PDF). American Institute of Aeronautics and Astronautics. Archived (PDF) from the original on February 24, 2020. Retrieved September 23, 2009. <a href="http://selenianboondocks.com/wp-content/uploads/2009/09/NearTermPropellantDepots.pdf" target="_blank">http://selenianboondocks.com/wp-content/uploads/2009/09/NearTermPropellantDepots.pdf</a> <a href="#fnref:58" class="footnote-back-ref">↩</a></li>
<li id="fn:59">Bergin, Chris (August 10, 2011). "NASA interest in an interplanetary highway supported by Propellant Depots". NASA Spaceflight. Archived from the original on August 12, 2011. Retrieved August 11, 2011. a LO2/LH2 PTSD (Propellant Transfer and Storage Demonstration) mission by 2015. ... it would be launched on an Atlas 551 ... [which] would provide ~12 mT of Centaur residuals (combined LH2 and LO2) in a 28.5 degrees by 200 nm circular LEO. <a href="http://www.nasaspaceflight.com/2011/08/nasa-interest-interplanetary-highway-supported-propellant-depots/" target="_blank">http://www.nasaspaceflight.com/2011/08/nasa-interest-interplanetary-highway-supported-propellant-depots/</a> <a href="#fnref:59" class="footnote-back-ref">↩</a></li>
<li id="fn:60">"Boeing Orbital Express Conducts First Autonomous Spacecraft-to-Spacecraft Fluid and Component Transfer". Boeing. April 17, 2007. Archived from the original on May 5, 2007. <a href="https://web.archive.org/web/20070505101041/http://www.boeing.com/news/releases/2007/q2/070417c_nr.html" target="_blank">https://web.archive.org/web/20070505101041/http://www.boeing.com/news/releases/2007/q2/070417c_nr.html</a> <a href="#fnref:60" class="footnote-back-ref">↩</a></li>
<li id="fn:61">"Human Lunar Exploration Mission Architectures, page 22" (PDF). NASA. March 1–2, 2004. Archived (PDF) from the original on June 5, 2011. Retrieved March 19, 2010. <a href="http://www.lpi.usra.edu/lunar_knowledge/connolly.pdf" target="_blank">http://www.lpi.usra.edu/lunar_knowledge/connolly.pdf</a> <a href="#fnref:61" class="footnote-back-ref">↩</a></li>
<li id="fn:62">de Selding, Peter B. (March 18, 2011). "Intelsat Signs Up for MDA's Satellite Refueling Service". Space News. Archived from the original on March 21, 2012. Retrieved March 20, 2011. more than 40 different types of fueling systems ... SIS will be carrying enough tools to open 75 percent of the fueling systems aboard satellites now in geostationary orbit. ... the SIS spacecraft is designed to operate for seven years in orbit but that it is likely to be able to operate far longer than that. Key to the business model is MDA's ability to launch replacement fuel canisters that would be grappled by SIS and used to refuel dozens of satellites over a period of years. These canisters would be much lighter than the SIS vehicle and thus much less expensive to launch. <a href="https://archive.today/20120321160118/http://www.sbv.spacenews.com/satellite_telecom/110318intelsat-signs-for-mdas-satellite-refueling-service.html" target="_blank">https://archive.today/20120321160118/http://www.sbv.spacenews.com/satellite_telecom/110318intelsat-signs-for-mdas-satellite-refueling-service.html</a> <a href="#fnref:62" class="footnote-back-ref">↩</a></li>
<li id="fn:63">Bergin, Chris (August 10, 2011). "NASA interest in an interplanetary highway supported by Propellant Depots". NASA Spaceflight. Archived from the original on August 12, 2011. Retrieved August 11, 2011. a LO2/LH2 PTSD (Propellant Transfer and Storage Demonstration) mission by 2015. ... it would be launched on an Atlas 551 ... [which] would provide ~12 mT of Centaur residuals (combined LH2 and LO2) in a 28.5 degrees by 200 nm circular LEO. <a href="http://www.nasaspaceflight.com/2011/08/nasa-interest-interplanetary-highway-supported-propellant-depots/" target="_blank">http://www.nasaspaceflight.com/2011/08/nasa-interest-interplanetary-highway-supported-propellant-depots/</a> <a href="#fnref:63" class="footnote-back-ref">↩</a></li>
<li id="fn:64">Demetriades, S.T. (March 1962). "The Use of Atmospheric and Extraterrestrial Resources in Space Propulsion Systems". Electric Propulsion Conference. <a href="#fnref:64" class="footnote-back-ref">↩</a></li>
<li id="fn:65">Demetriades, S.T. (March 1962). "The Use of Atmospheric and Extraterrestrial Resources in Space Propulsion Systems". Electric Propulsion Conference. <a href="#fnref:65" class="footnote-back-ref">↩</a></li>
<li id="fn:66">Demetrades, S.T. (April 1962). "Plasma Propulsion". Journal of the British Interplanetary Society. 18 (10): 392. Bibcode:1962JBIS...18..392D. <a href="/wiki/Bibcode_(identifier)" target="_blank">/wiki/Bibcode_(identifier)</a> <a href="#fnref:66" class="footnote-back-ref">↩</a></li>
<li id="fn:67">Jones, C., Masse, D., Glass, C., Wilhite, A., and Walker, M. (2010), "PHARO: Propellant harvesting of atmospheric resources in orbit," IEEE Aerospace Conference. <a href="#fnref:67" class="footnote-back-ref">↩</a></li>
<li id="fn:68">Massonnet, Didier; Meyssignac, Benoît (July–September 2006). "A captured asteroid: Our David's stone for shielding earth and providing the cheapest extraterrestrial material". Acta Astronautica. 59 (1–5): 77–83. Bibcode:2006AcAau..59...77M. doi:10.1016/j.actaastro.2006.02.030. <a href="/wiki/Bibcode_(identifier)" target="_blank">/wiki/Bibcode_(identifier)</a> <a href="#fnref:68" class="footnote-back-ref">↩</a></li>
<li id="fn:69">Livingston, David M.; Adamo, Dan (September 6, 2010). "Broadcast 1420 (Special Edition)". The Space Show. Archived from the original on February 5, 2018. Retrieved February 5, 2018. <a href="http://www.thespaceshow.com/show/06-sep-2010/broadcast-1420-special-edition" target="_blank">http://www.thespaceshow.com/show/06-sep-2010/broadcast-1420-special-edition</a> <a href="#fnref:69" class="footnote-back-ref">↩</a></li>
<li id="fn:70">Livingston, David M.; Adamo, Dan (September 6, 2010). "Broadcast 1420 (Special Edition)". The Space Show. Archived from the original on February 5, 2018. Retrieved February 5, 2018. <a href="http://www.thespaceshow.com/show/06-sep-2010/broadcast-1420-special-edition" target="_blank">http://www.thespaceshow.com/show/06-sep-2010/broadcast-1420-special-edition</a> <a href="#fnref:70" class="footnote-back-ref">↩</a></li>
<li id="fn:71">Loucks, Michel; Goff, Jonathan; Carrico, John (2017). Practical Methodologies for Low Delta-V Penalty, On-Time Departures to Arbitrary Interplanetary Destinations From a Medium-Inclination Low-Earth Orbit Depot. 2017 AAS/AIAA Astrodynamics Specialist Conference. 20–24 August 2017. Stevenson, Washington. AAS 17-696. Archived from the original on October 1, 2021. Retrieved August 13, 2019. <a href="https://www.researchgate.net/publication/323986775_Practical_Methodologies_For_Low_Delta-V_Penalty_On-Time_Departures_To_Arbitrary_Interplanetary_Destinations_From_A_Medium-Inclination_Low-Earth_Orbit_Depot" target="_blank">https://www.researchgate.net/publication/323986775_Practical_Methodologies_For_Low_Delta-V_Penalty_On-Time_Departures_To_Arbitrary_Interplanetary_Destinations_From_A_Medium-Inclination_Low-Earth_Orbit_Depot</a> <a href="#fnref:71" class="footnote-back-ref">↩</a></li>
<li id="fn:72">Loucks, Michel; Goff, Jonathan; Carrico, John; Hardy, Brian (2018). "RAAN-agnostic 3-burn Departure Methodology for Deep Space Missions from LEO Depots [AAS 18-447]" (PDF). AAS. American Astronautical Society. Archived (PDF) from the original on August 13, 2019. Retrieved August 13, 2019. <a href="https://selenianboondocks.com/wp-content/uploads/2018/09/RAAN-Agnostic_3-BurnPaperV2_AAS-18-447-1.pdf" target="_blank">https://selenianboondocks.com/wp-content/uploads/2018/09/RAAN-Agnostic_3-BurnPaperV2_AAS-18-447-1.pdf</a> <a href="#fnref:72" class="footnote-back-ref">↩</a></li>
<li id="fn:73">Goff, Jon; et al. (2009). "Realistic Near-Term Propellant Depots" (PDF). American Institute of Aeronautics and Astronautics. Archived (PDF) from the original on February 24, 2020. Retrieved September 23, 2009. <a href="http://selenianboondocks.com/wp-content/uploads/2009/09/NearTermPropellantDepots.pdf" target="_blank">http://selenianboondocks.com/wp-content/uploads/2009/09/NearTermPropellantDepots.pdf</a> <a href="#fnref:73" class="footnote-back-ref">↩</a></li>
<li id="fn:74">Zegler, Frank; Kutter, Bernard (September 2, 2010). Evolving to a Depot-Based Space Transportation Architecture (PDF). AIAA SPACE 2010 Conference & Exposition. American Institute of Aeronautics and Astronautics. Archived from the original (PDF) on June 24, 2014. Retrieved October 31, 2016. ACES design conceptualization has been underway at ULA for many years. It leverages design features of both the Centaur and Delta Cryogenic Second Stage (DCSS) upper stages and intends to supplement and perhaps replace these stages in the future. The baseline ACES will contain twice the Centaur or 4m DCSS propellant load, providing a significant performance boost compared to our existing upper stages. The baseline 41-mT propellant load is contained in a 5m diameter, common bulkhead stage that is about the same length as ULA's existing upper stages. ACES will become the foundation for a modular system of stages to meet the launch requirements of a wide variety of users. A common variant is a stretched version containing 73t of propellant. <a href="https://web.archive.org/web/20140624125633/http://www.ulalaunch.com/uploads/docs/Published_Papers/Exploration/DepotBasedTransportationArchitecture2010.pdf" target="_blank">https://web.archive.org/web/20140624125633/http://www.ulalaunch.com/uploads/docs/Published_Papers/Exploration/DepotBasedTransportationArchitecture2010.pdf</a> <a href="#fnref:74" class="footnote-back-ref">↩</a></li>
<li id="fn:75">"Drawbacks of Cryogenic Propellants". Space Travel Guide on Oracle ThinkQuest Education Foundation. Archived from the original on June 28, 2010. <a href="https://web.archive.org/web/20100628054254/http://library.thinkquest.org/03oct/02144/text/propulsion/propellents/crydraw.htm" target="_blank">https://web.archive.org/web/20100628054254/http://library.thinkquest.org/03oct/02144/text/propulsion/propellents/crydraw.htm</a> <a href="#fnref:75" class="footnote-back-ref">↩</a></li>
<li id="fn:76">"Zero Boiloff Storage of Cryogenic Propellants Achieved at Lewis' Supplemental Multilayer Insulation Research Facility". Glenn Research Center. Archived from the original on September 22, 2008. <a href="https://web.archive.org/web/20080922224443/http://www.grc.nasa.gov/WWW/RT/RT1998/5000/5870plachta.html" target="_blank">https://web.archive.org/web/20080922224443/http://www.grc.nasa.gov/WWW/RT/RT1998/5000/5870plachta.html</a> <a href="#fnref:76" class="footnote-back-ref">↩</a></li>
<li id="fn:77">"Large-Scale Demonstration of Liquid Hydrogen Storage With Zero Boiloff for In-Space Applications" (PDF). Glenn Research Center. Archived (PDF) from the original on October 1, 2021. Retrieved September 16, 2020. <a href="https://ntrs.nasa.gov/api/citations/20110004377/downloads/20110004377.pdf" target="_blank">https://ntrs.nasa.gov/api/citations/20110004377/downloads/20110004377.pdf</a> <a href="#fnref:77" class="footnote-back-ref">↩</a></li>
<li id="fn:78">"An Updated Zero Boil-Off Cryogenic Propellant Storage Analysis Applied to Upper Stages or Depots in an LEO Environment" (PDF). Glenn Research Center. Archived (PDF) from the original on April 26, 2010. Retrieved July 7, 2017. <a href="https://ntrs.nasa.gov/archive/nasa/casi.ntrs.nasa.gov/20030067928_2003079547.pdf" target="_blank">https://ntrs.nasa.gov/archive/nasa/casi.ntrs.nasa.gov/20030067928_2003079547.pdf</a> <a href="#fnref:78" class="footnote-back-ref">↩</a></li>
<li id="fn:79">Shackleton Energy's cislunar economic development plans Archived January 5, 2013, at the Wayback Machine David Livingston interview with James Keravala, The Space Show, December 14, 2012, at 1:08:20-1:09:50, accessed January 3, 2013. <a href="http://www.thespaceshow.com/detail.asp?q=1914" target="_blank">http://www.thespaceshow.com/detail.asp?q=1914</a> <a href="#fnref:79" class="footnote-back-ref">↩</a></li>
<li id="fn:80">Kutter, Bernard F.; et al. (September 9–11, 2008). "A Practical, Affordable Cryogenic Propellant Depot Based on ULA's Flight Experience". AIAA SPACE 2008 Conference & Exposition. AIAA SPACE 2008 Conference & Exposition. San Diego, California: AIAA. doi:10.2514/6.2008-7644. hdl:2060/20130010201. ISBN 978-1-62410-002-4. <a href="978-1-62410-002-4" target="_blank">978-1-62410-002-4</a> <a href="#fnref:80" class="footnote-back-ref">↩</a></li>
<li id="fn:81">Jewett, R. P. (1973). Hydrogen Environment Embrittlement of Metals. NASA CR-2163. <a href="#fnref:81" class="footnote-back-ref">↩</a></li>
<li id="fn:82">Clark, Stephen (January 25, 2013). "Satellite refueling testbed completes demo in orbit". Spaceflight Now. Archived from the original on January 29, 2013. Retrieved January 26, 2013. <a href="http://www.spaceflightnow.com/news/n1301/25rrm/#.UQQMpvJ5GIR" target="_blank">http://www.spaceflightnow.com/news/n1301/25rrm/#.UQQMpvJ5GIR</a> <a href="#fnref:82" class="footnote-back-ref">↩</a></li>
<li id="fn:83">Clark, Stephen (January 25, 2013). "Satellite refueling testbed completes demo in orbit". Spaceflight Now. Archived from the original on January 29, 2013. Retrieved January 26, 2013. <a href="http://www.spaceflightnow.com/news/n1301/25rrm/#.UQQMpvJ5GIR" target="_blank">http://www.spaceflightnow.com/news/n1301/25rrm/#.UQQMpvJ5GIR</a> <a href="#fnref:83" class="footnote-back-ref">↩</a></li>
<li id="fn:84">de Selding, Peter B. (March 3, 2010). "MDA Designing In-orbit Servicing Spacecraft". Space News. Archived from the original on January 5, 2013. Retrieved March 14, 2011. the refueling vehicle would dock at the target satellite's apogee-kick motor, peel off a section of the craft's thermal protection blanket, connect to a fuel-pressure line and deliver the propellant. MDA officials estimate the docking maneuver would take the communications satellite out of service for about 20 minutes. ... The servicing robot would have an in-orbit life of about five years, and would carry enough fuel to perform 10 or 11 satellite-refueling or orbital-cleanup missions. <a href="https://archive.today/20130105074228/http://spacenews.com/satellite_telecom/100303-mda-planning-inorbit-servicing-demo.html" target="_blank">https://archive.today/20130105074228/http://spacenews.com/satellite_telecom/100303-mda-planning-inorbit-servicing-demo.html</a> <a href="#fnref:84" class="footnote-back-ref">↩</a></li>
<li id="fn:85">de Selding, Peter B. (March 3, 2010). "MDA Designing In-orbit Servicing Spacecraft". Space News. Archived from the original on January 5, 2013. Retrieved March 14, 2011. the refueling vehicle would dock at the target satellite's apogee-kick motor, peel off a section of the craft's thermal protection blanket, connect to a fuel-pressure line and deliver the propellant. MDA officials estimate the docking maneuver would take the communications satellite out of service for about 20 minutes. ... The servicing robot would have an in-orbit life of about five years, and would carry enough fuel to perform 10 or 11 satellite-refueling or orbital-cleanup missions. <a href="https://archive.today/20130105074228/http://spacenews.com/satellite_telecom/100303-mda-planning-inorbit-servicing-demo.html" target="_blank">https://archive.today/20130105074228/http://spacenews.com/satellite_telecom/100303-mda-planning-inorbit-servicing-demo.html</a> <a href="#fnref:85" class="footnote-back-ref">↩</a></li>
<li id="fn:86">de Selding, Peter B. (March 14, 2011). "Intelsat Signs Up for Satellite Refueling Service". Space News. Archived from the original on May 24, 2012. Retrieved March 15, 2011. if the MDA spacecraft performs as planned, Intelsat will be paying a total of some $200 million to MDA. This assumes that four or five satellites are given around 200 kilograms each of fuel. ... The maiden flight of the vehicle would be on an International Launch Services Proton rocket, industry officials said. One official said the MDA spacecraft, including its 2,000 kilograms of refueling propellant, is likely to weigh around 6,000 kilograms at launch. <a href="https://archive.today/20120524111321/http://www.spacenews.com/satellite_telecom/intelsat-signs-for-satellite-refueling-service.html" target="_blank">https://archive.today/20120524111321/http://www.spacenews.com/satellite_telecom/intelsat-signs-for-satellite-refueling-service.html</a> <a href="#fnref:86" class="footnote-back-ref">↩</a></li>
<li id="fn:87">"Intelsat Picks MacDonald, Dettwiler and Associates Ltd. for Satellite Servicing". press release. CNW Group. Archived from the original on May 12, 2011. Retrieved March 15, 2011. MDA plans to launch its Space Infrastructure Servicing ("SIS") vehicle into near geosynchronous orbit, where it will service commercial and government satellites in need of additional fuel, re-positioning or other maintenance. ... MDA and Intelsat will work together to finalize specifications and other requirements over the next six months before both parties authorize the build phase of the program. The first refueling mission is to be available 3.5 years following the commencement of the build phase. ... The services provided by MDA to Intelsat under this agreement are valued at more than US$280 million. <a href="https://web.archive.org/web/20110512175952/http://www.canadanewswire.ca/en/releases/archive/March2011/15/c2866.html" target="_blank">https://web.archive.org/web/20110512175952/http://www.canadanewswire.ca/en/releases/archive/March2011/15/c2866.html</a> <a href="#fnref:87" class="footnote-back-ref">↩</a></li>
<li id="fn:88">Clark, Stephen (January 25, 2013). "Satellite refueling testbed completes demo in orbit". Spaceflight Now. Archived from the original on January 29, 2013. Retrieved January 26, 2013. <a href="http://www.spaceflightnow.com/news/n1301/25rrm/#.UQQMpvJ5GIR" target="_blank">http://www.spaceflightnow.com/news/n1301/25rrm/#.UQQMpvJ5GIR</a> <a href="#fnref:88" class="footnote-back-ref">↩</a></li>
<li id="fn:89">Henry, Caleb (June 29, 2017). "MDA restarts satellite servicing business with SES as first customer". SpaceNews. Archived from the original on October 1, 2021. Retrieved July 15, 2019. <a href="https://spacenews.com/mda-restarts-satellite-service-business-with-ses-as-first-customer/" target="_blank">https://spacenews.com/mda-restarts-satellite-service-business-with-ses-as-first-customer/</a> <a href="#fnref:89" class="footnote-back-ref">↩</a></li>
<li id="fn:90">Morring, Frank Jr. (March 22, 2011). "An End To Space Trash?". Aviation Week. Retrieved March 21, 2011. ViviSat, a new 50-50 joint venture of U.S. Space and ATK, is marketing a satellite-refueling spacecraft that connects to a target spacecraft using the same probe-in-the-kick-motor approach as MDA, but does not transfer its fuel. Instead, the vehicle becomes a new fuel tank, using its own thrusters to supply attitude control for the target. ... [the ViviSat] concept is not as far along as MDA. <a href="http://www.aviationweek.com/aw/generic/story.jsp?id=news/awst/2011/03/21/AW_03_21_2011_p23-297586.xml&headline=An%20End%20to%20Space%20Trash?&channel=awst" target="_blank">http://www.aviationweek.com/aw/generic/story.jsp?id=news/awst/2011/03/21/AW_03_21_2011_p23-297586.xml&headline=An%20End%20to%20Space%20Trash?&channel=awst</a> <a href="#fnref:90" class="footnote-back-ref">↩</a></li>
<li id="fn:91">Morring, Frank Jr. (March 22, 2011). "An End To Space Trash?". Aviation Week. Retrieved March 21, 2011. ViviSat, a new 50-50 joint venture of U.S. Space and ATK, is marketing a satellite-refueling spacecraft that connects to a target spacecraft using the same probe-in-the-kick-motor approach as MDA, but does not transfer its fuel. Instead, the vehicle becomes a new fuel tank, using its own thrusters to supply attitude control for the target. ... [the ViviSat] concept is not as far along as MDA. <a href="http://www.aviationweek.com/aw/generic/story.jsp?id=news/awst/2011/03/21/AW_03_21_2011_p23-297586.xml&headline=An%20End%20to%20Space%20Trash?&channel=awst" target="_blank">http://www.aviationweek.com/aw/generic/story.jsp?id=news/awst/2011/03/21/AW_03_21_2011_p23-297586.xml&headline=An%20End%20to%20Space%20Trash?&channel=awst</a> <a href="#fnref:91" class="footnote-back-ref">↩</a></li>
<li id="fn:92">Clark, Stephen (January 25, 2013). "Satellite refueling testbed completes demo in orbit". Spaceflight Now. Archived from the original on January 29, 2013. Retrieved January 26, 2013. <a href="http://www.spaceflightnow.com/news/n1301/25rrm/#.UQQMpvJ5GIR" target="_blank">http://www.spaceflightnow.com/news/n1301/25rrm/#.UQQMpvJ5GIR</a> <a href="#fnref:92" class="footnote-back-ref">↩</a></li>
<li id="fn:93">Foust, Jeff (March 13, 2015). "Lockheed Martin Pitches Reusable Tug for Space Station Resupply". Space News. Archived from the original on October 1, 2021. Retrieved March 21, 2015. <a href="http://spacenews.com/lockheed-martin-pitches-reusable-tug-for-space-station-resupply/" target="_blank">http://spacenews.com/lockheed-martin-pitches-reusable-tug-for-space-station-resupply/</a> <a href="#fnref:93" class="footnote-back-ref">↩</a></li>
<li id="fn:94">Foust, Jeff (November 6, 2018). "Orbit Fab to test refueling technology on ISS". SpaceNews. Archived from the original on October 1, 2021. Retrieved March 28, 2019. <a href="https://spacenews.com/orbit-fab-to-test-refueling-technology-on-iss/" target="_blank">https://spacenews.com/orbit-fab-to-test-refueling-technology-on-iss/</a> <a href="#fnref:94" class="footnote-back-ref">↩</a></li>
<li id="fn:95">Tangermann, Victor (September 14, 2021). "Startup Launches Refueling Station Into Orbit, Gets $10 Million in Funding". Futurism. Retrieved August 30, 2022. <a href="https://futurism.com/startup-launched-refueling-station-orbit/" target="_blank">https://futurism.com/startup-launched-refueling-station-orbit/</a> <a href="#fnref:95" class="footnote-back-ref">↩</a></li>
</ol>

Orbital propellant depot open-in-new

Orbital propellant depot