Technical characteristics of oxygen-hydrogen liquid rocket propulsion system of interorbital space vehicle

In the article the results of working out of technical shape of LOX-LH2 Expander Cycle Liquid Rocket Engine (LRE) for expandable Orbital Transfer Vehicle, by means of mathematical model of multi-criteria optimization of design pa- rameters, are described. As the criteria of optimization, the maximum weight of a payload and the minimum specific cost of transferring of a payload into a target orbit, are chosen. The calculation of optimum design parameters of LRE for expandable Orbital Transfer Vehicle for four problems of orbital transfer, defined in the characteristic speeds of inter-orbital transition, is resulted: 2500 km/s, 3500 km/s, 4800 km/s and 7000 km/s. On the received optimum design parameters, the design parameters of units of LRE are calculated and the technical shape is constructed.