| 翻訳と辞書 |
| Lunar Module Descent Engine ： ウィキペディア英語版 |
Descent Propulsion System
The Descent Propulsion System (''DPS'') or ''LMDE'' (Lunar Module Descent Engine) is a variable throttle hypergolic rocket engine developed by Space Technology Laboratories (TRW) for use in the Apollo Lunar Module Descent Stage. It used Aerozine 50 fuel and N2O4 oxidizer. This engine used a pintle injector, a design also used later in the SpaceX Merlin engine.
== Requirements ==
The propulsion system for the descent stage of the Lunar Module was designed to transfer the vehicle, containing two crewmen, from a lunar parking orbit to a descent orbit, then provide a powered descent to the lunar surface, with hover time above the lunar surface to select the exact landing site. To accomplish these maneuvers, a propulsion system was developed that used hypergolic propellants and a gimballed pressure-fed ablative cooled engine that was capable of being throttled. A lightweight cryogenic helium pressurization system was also used. The exhaust nozzle extension was designed to crush without damaging the LM if it struck the surface, which happened on Apollo 15.
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「Descent Propulsion System」の詳細全文を読む
スポンサード リンク
| 翻訳と辞書 : 翻訳のためのインターネットリソース |
Copyright(C) kotoba.ne.jp 1997-2016. All Rights Reserved.
|
|