Solid propulsion for space exploration landing systems
- Paper number
IAC-09.D2.3.4
- Author
Mr. Frédéric DAUCH, SNPE, France
- Coauthor
Mrs. Julia Saramago, SNPE Materiaux Energetiques, France
- Year
2009
- Abstract
Several space exploration missions are currently under investigations in the frame of ESA Aurora programme. Some of these missions (ExoMars, Next, MSR…) require propulsive braking systems for their landing modules. This paper highlights the benefits of solid propulsion for such space exploration landers and reviews its main advantages for different mission requirements in terms of performances, reliability and technological maturity based on an extensive background. In the frame of the ExoMars mission, preliminary design studies (Phase B) performed by SNPE Matériaux Energétiques has shown on recent work that a solid propulsion system combined with a liquid monopropellant thrusters system could be a mature solution to the Entry Descent and Landing System requirements. In such system, solid retrorockets will achieve the main vertical braking effort, whereas the liquid engines will allow adjusting the vertical thrust and performing the Lander attitude control. A solid retrorockets system preliminary design for the ExoMars Reaction Control System is presented in this paper, as well as other design trade-offs performed for other landing requirements such as hard and soft landings. A multi stage vehicle for re-ascent missions with in orbit rendez-vous or direct return to earth has also been analyzed. These design studies shows that already available solid propulsion systems can be used for exploration missions such as ExoMars and future exploration missions part of Aurora program (Next, MSR).
- Abstract document
- Manuscript document
(absent)