| タイトル | Advanced Development Program for a 625 lbf thrust engine for Ares First Stage Roll Control System |
| 著者（英） | Brewster, Gerry; Bullard, Brad; Fuller, Ray; Frei, Tom; Dawson, Matt; Chenevert, Blake |
| 著者所属（英） | NASA Marshall Space Flight Center |
| 発行日 | 2009-11-02 |
| 言語 | eng |
| 内容記述 | NASA's new Ares Launch Vehicle will require twelve thrusters to provide roll control of the vehicle during the first stage firing. All twelve roll control thrusters will be located at the inter-stage segment that separates the solid rocket booster first stage from the second stage. NASA selected a mono propellant hydrazine solution and as a result awarded Aerojet-General a contract in 2007 for an advanced development program for an MR-80- series 625 Ibf vacuum thrust monopropellant hydrazine thruster. This thruster has heritage dating back to the 1976 Viking Landers and most recently for the 2011 Mars Science Laboratory. Prior to the Ares application, the MR-80-series thrusters had been equipped with throttle valves and not typically operated in pulse mode. The primary objective of the advanced development program was to increase the technology readiness level and retire major technical risks for the future flight qualification test program. Aerojet built on their heritage MR-80 rocket engine designs to achieve the design and performance requirements. Significant improvements to cost and lead-time were achieved by applying Design for Manufacturing and Assembly (DFMA) principles. AerojetGeneral has completed Preliminary and Critical Design Reviews, followed by two successful rocket engine development test programs. The test programs included qualification random vibration and firing lite that significantly exceed the flight qualification requirements. This paper discusses the advanced development program and the demonstrated capability of the MR-80C engine. Y; |
| NASA分類 | Spacecraft Propulsion and Power |
| レポートNO | M10-0087 |
| 権利 | Copyright |
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