fully axisymmetric airbreather concept for space launcher first application to a micro-space launcher
- Paper number
IAC-08.C4.5.6
- Author
Mr. Francois FALEMPIN, MBDA France, France
- Year
2008
- Abstract
A possible application for the high-speed airbreathing propuslion is the fully or partially reusable Space Launcher. Indeed, by combining the high-speed airbreathing propulsion with a conventional rocket engine (combined cycle or combined propulsion system), it should be possible to improve the average installed specific impulse along the ascent trajectory and then make possible more performing launchers and, hopefully, a fully reusable one. During the last 15 years, a lot of system studies have been performed in France on that subject within the framework of different and consecutive programs. Nevertheless, these studies never clearly demonstrated that a space launcher could take advantage of using a combined propulsion system. As a matter of fact, past studies were performed sometimes by different teams with different tools and hypothesis, sometimes with particular purpose. For example, the purpose of system studies led in the framework of the National PREPHA program was not to assess the feasibility of a fully reusable Single-Stage-To-Orbit (SSTO) space launcher but only to determine some general technical requirements for such a vehicle in order to provide guidelines for the study of a scramjet system. By another way, these studies used systematically a very conservative approach in term of vehicle airframe configuration and it is doubtable that the best trade-off between airbreathing propulsion mode needs and the mandatory low dry mass for the vehicle and its propulsion system was obtained with the considered vehicle concepts. During last years, the interest of airbreathing propulsion for space application has been revisited. During this review, and taking into account technologies development activities already in progress in Europe, clear priorities have been identified regarding a minimum complementary Research and Technology program addressing specific needs of space launcher application. By another way, it was also clearly identified the need to restart system studies taking advantage of recent progress made regarding knowledge, tools and technology and focusing on more innovative airframe/propulsion system concepts enabling better trade-off between structural efficiency and propulsion system performance. In that field, a fully axisymmetric configuration has been considered for a micro-space launcher (10 kg payload). The vehicle is based on a main stage powered by airbreathing propulsion, combined or not with liquid rocket mode. A “kick stage”, powered by a solid rocket engine provides the final acceleration. A preliminary design has been performed for different variant : one using a separated booster and a purely airbreathing main stage, a second one using a booster and a main stage combining airbreathing and rocket mode, a third one without separated booster, the main stage ensuring the initial acceleration in liquid rocket mode and a complementary acceleration phase in rocket mode beyond the airbreathing propulsion system operation. Finally, the liquid rocket engine of this third variant can be replaced by a continuous detonation wave rocket engine. The paper will describe the main guidelines for the design of these variants and will provide their main characteristics. On this basis, the achievable performance, estimated by trajectory simulation, will be detailed. Moreover some specific issues will be addressed as dynamic stability of the powered vehicle and overall thermal management.
- Abstract document
- Manuscript document
IAC-08.C4.5.6.pdf (🔒 authorized access only).
To get the manuscript, please contact IAF Secretariat.