Titan II GLV

<p>The Titan II GLV (Titan II Gemini Launch Vehicle) or Gemini-Titan II was an American <a href="/facts/Expendable_launch_system/CaW43W5z">expendable launch system</a> derived from the <a href="/facts/LGM-25C_Titan_II/xrfcxWFj">Titan II missile</a>, which was used to launch twelve <a href="/facts/Project_Gemini/7PYE3AV4">Gemini</a> missions for <a href="/facts/NASA/TIMCV0yV">NASA</a> between 1964 and 1966. Two uncrewed launches followed by ten crewed ones were conducted from <a href="/facts/Cape_Canaveral_Air_Force_Station_Launch_Complex_19/uLb0CYFB">Launch Complex 19</a> at the <a href="/facts/Cape_Canaveral_Air_Force_Station/dwJ9MCPH">Cape Canaveral Air Force Station</a>, starting with <a href="/facts/Gemini_1/8PhKzfxp">Gemini 1</a> on April 8, 1964.
</p><p>The Titan II was a two-stage <a href="/facts/Liquid-fuel_rocket/TAonrVDn">liquid-fuel rocket</a>, using a <a href="/facts/Hypergolic_propellant/p0Goa3rn">hypergolic propellant</a> combination of <a href="/facts/Aerozine_50/WPBKUnMV">Aerozine 50</a> fuel and <a href="/facts/Nitrogen_tetroxide/01WfnHJh">nitrogen tetroxide</a> oxidizer. The first stage was powered by an <a href="/facts/LR87/Vrx7zHeX">LR87</a> engine (with two combustion chambers and nozzles, fed by separate sets of turbomachinery), and the second stage was propelled by an <a href="/facts/LR91/5auEs9B5">LR91</a> engine.
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Titan II GLV open-in-new

Titan II GLV