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The Rocketdyne H-1 was a 205,000 lbf (910 kN) thrust liquid-propellant rocket engine burning LOX and RP-1.The H-1 was developed for use in the S-I and S-IB first stages of the Saturn I and Saturn IB rockets, respectively, where it was used in clusters of eight engines.
Russia is also working to switch the Soyuz-2 from RP-1 to "naftil" [10] or "naphthyl". [11] [12] After the RP-1 standard, RP-2 was developed. The primary difference is an even lower sulfur content. However, as most users accept RP-1, there was little incentive to produce and stock a second, even rarer and more expensive formulation.
RP-1 / LOX // Jet-A / LOX Gas generator: 53,800 [8] 64 E2 Vacuum USA: ABL Space Systems: RS1: Active 2nd RP-1 / LOX // Jet-A / LOX Gas generator: 57,800 [8] Engine-2 USA: Vast: TBA: Development 1st RP-1 / LOX: Staged, oxidizer-rich: 327 [9] 290 (SL) 100,000 [9] 100 2.62: Engine-2 Vacuum USA: Vast: TBA: Development 2nd RP-1 / LOX: Staged ...
It provides 1.05 meganewtons (240,000 lbf) of thrust burning RP-1 and LOX in a gas-generator cycle. The engine is a modified version of its predecessor, the RS-27; [7] its thrust nozzle has been extended to increase its area ratio from 8:1 to 12:1, which provides greater efficiency at altitude.
Rutherford is a liquid-propellant rocket engine designed by aerospace company Rocket Lab [8] and manufactured in Long Beach, California. [9] The engine is used on the company's own rocket, Electron. It uses LOX (liquid oxygen) and RP-1 (refined kerosene) as its propellants and is the first flight-ready engine to use the electric-pump-fed cycle.
The LR91 was an American liquid-propellant rocket engine, which was used on the second stages of Titan intercontinental ballistic missiles and launch vehicles.While the original version - the LR91-3 - ran on RP-1/LOX (as did the companion LR87-3) on the Titan I, the models that propelled the Titan II and later were switched to Aerozine 50/N 2 O 4.
Instead of liquid oxygen and RP-1, the Titan II used nitrogen tetroxide and Aerozine 50.This change was done for storability at the request of the US Air Force. [3]: 381 The engine was generally lighter and simpler than its predecessor, partly due to the use of hypergolic propellants, which do not need an independent ignition system.
The RD-701 is a tripropellant engine that uses a staged combustion cycle with afterburning of oxidizer-rich hot turbine gas. The RD-701 has two modes. Mode 1 uses three components: LOX as an oxidizer and a fuel mixture of RP-1 / LH2 which is used in the lower atmosphere. Mode 2 also uses LOX, with LH2 as fuel in vacuum where atmospheric ...
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