We found a match
Your institution may have access to this item. Find your institution then sign in to continue.
- Title
Development of Main Propulsion System for Reusable Sounding Rocket: Design Considerations and Technology Demonstration.
- Authors
Masaki SATO; Tomoyuki HASHIMOTO; Satoshi TAKADA; Toshiya KIMURA; Takuo ONODERA; Yoshihiro NARUO; Tsuyoshi YAGISHITA; Ken-ichi NIU; Takao KANEKO; Kimihito OBASE
- Abstract
A fully reusable sounding rocket is proposed in JAXA/ISAS to provide frequent opportunities for atmospheric observation mission with low cost and with short turnaround time, and also to improve technology readiness levels for reusable space transportation systems. This rocket will take off vertically, reach to the high altitude more than 100 km, land on the launch site vertically, and be launched again within 24 hours. The main propulsion system is clustered LOX/LH2 engines with full-time abort capability in spite of the one engine fail. In order to realize the reusable sounding rocket, the main propulsion system should have advanced features of high reliability, reusability, maintainability, and survivability. To fulfill those requirements, followings have been considered and reflected in the engine system design, i.e., optimization of design margins among components for high reliability and reusability, deep throttling capability for vertical landing, and health monitoring capability for abort operation, easy inspection and maintenance for short turnaround time. Those functions and performance are going to be verified and demonstrated through ground engineering tests at Kakuda Space Center/JAXA in 2014. This paper shows the design considerations, the engine system and major components design, and the current status and plan of technology demonstration tests.
- Subjects
SPACE flight propulsion systems; REUSABLE space vehicles; SOUNDING rockets; SPACE vehicle prototype engineering; ROCKET engine design &; construction; SPACE vehicle design &; construction
- Publication
Transactions of the Japan Society of Aeronautical & Space Sciences, Aerospace Technology Japan, 2014, Vol 12, Issue ists 29, p1
- ISSN
1884-0485
- Publication type
Article