Monopropellant Rotory Liquid Propulsion
- Paper number
IAC-06-C4.P.1.09
- Author
Prof. Sergey Finogenov, Moscow Aviation Institute (MAI), Russia
- Coauthor
Prof. Valery P. Burdakov, Moscow Aviation Institute (MAI), Russia
- Coauthor
Prof. Alexander A. Sergienko, Moscow Aviation Institute (MAI), Russia
- Year
2006
- Abstract
Results of the researches, which are continuation of the authors’ works on liquid-propellant rocket engines with both rotary turbo-pump unit (earlier presented by the authors at the previous IAF Congresses) and monopropellant use, employing single-tank design, as applied to reusable single-stage-to-orbit vehicle (see, for instance, the authors’ previous Paper IAC-05-C.4.1.07), are discussed in the present paper. It is shown that expedient parameters of such monopropellant rocket engine with rotory turbopump unit quite correspond to possibilities of its creation employing state-of-the-art technical level. Preliminary design of the considered monopropellant liquid propulsion with rotory turbopump unit was carried out. It is seen in the paper that the presented propulsion system includes the following subsystems: propellant acquisition device; bottom thermal shield; bearing support; magnetic bearing; rotor disk; propellant duct; gasifier; combustion chamber; ejector chamber; rotor blades; stator blades; mount frame; engine air inlet; superconductor elevators.
- Abstract document