Vorentwurf eines Mondlandefahrzeugs mit hybridem Raketenantriebssystem für eine Probenrückführungsmission - Preliminary Design of a Hybrid Propulsion Lunar Lander for a Sample Return Mission

Abstract

Due to their high performance, inherent safety, restart and throttling capability, hybrid rocket motors are particularly suitable for impulsive orbital maneuvers and applications as kick stage or upper stage motors.Within the scope of this diploma thesis a preliminary design of a hybrid propulsion spacecraft for a sample return mission to the Moon is developed. Liquid oxygen (LOX) and hydrogen peroxide (H2O2) based hybrids with the liquefying para�n-based fuel are set as reference. According to the predefined mission parameters and assumptions two multistage spacecraft designs are presented and compared. For the determination of the hybrid propulsion system and other vehicle parameters a Python-based softwaretool has been established and developed. The combustion parameters of the propellant combinations are determined with CEA. The orbit analysis and the stage optimisation are performed using the software ASTOS. The performance parameters of the hybrid engines with thrust levels of 12,5 kN, 4 kN and 750 N and their detailed mass and dimensions overview are presented and compared. The performed analysis indicates the storable propellant combination H2O2/Para�n to be highly promising for space applications and future hybrid engine developments.