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RD-701 ((ロシア語:''Раке́тный дви́гатель 701''), Rocket Engine 701) - liquid-fuel rocket engine developed by Energomash, Russia. It was proposed to propel the reusable MAKS space plane before cancellation of this project. The ''RD-701'' is a tripropellant engine that uses staged combustion cycle afterburning of oxidizer-rich hot turbine gas. This engine has two modes. ''Mode #1'' uses three components: LOX as an oxidizer and a fuel mixture of RP-1 / LH2 which is applied for near earth surface conditions. ''Mode #2'' also uses LOX, with LH2 as fuel in vacuum where atmospheric influence is negligible. The use of less dense fuel components at maximum efficiency conditions allows minimizing the volume of fuel tanks and subsequently their mass down to 30%. As of 2009 the engine is characterized by highest value of pressure, 300 bar, ever used in combustion chamber of rocket engines when running in ''Mode #1'' with mixture of fuel components. The ''RD-701'' became the base model for RD-704 with one combustion chamber. == Specifications == Two-chamber ''RD-701'' has two modes. The first one uses three components: RP-1 (mass flow — 73.7 kg/s), LH2 (mass flow — 29.5 kg/s) and LOX (mass flow — 388.4 kg/s). This mode is applied in lower atmosphere to minimize fuel tanks volume. The total thrust for altitude 10 km is 2х1,890.2 KN and specific impulse is 3,845 m/s. The second mode uses just two components: LH2 (mass flow — 24.7 kg/s) and LOX (mass flow — 148.5 kg/s). This mode applied for near space conditions and gives thrust 2х784.5 KN, specific impulse — 4,532 m/s. The mixing block of the main combustion chamber has three groups of injectors, one for each of the three available components. When running in ''Mode #2'' the engine doesn't use the kerosene group. The engine uses regenerative cooling by liquid hydrogen. 抄文引用元・出典: フリー百科事典『 ウィキペディア（Wikipedia）』 ■ウィキペディアで「RD-701」の詳細全文を読む スポンサード リンク
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