Аннотация
At the current stage of space exploration development, missions to the Moon and geostationary orbit are relevant. Enhancing of power supply level of such missions requires innovative technology development. Nuclear rocket engines and engines with use of solar energy are considered among such technologies. In a number of projects, such engines use intermediate heat energy accumulators, which complicates and increases the cost of construction. This embodiment uses a circuit that enables solar engine to operate with any orientation of the thrust direction towards the sun. The dependence of specific thrust of such engine on maximum heating temperature of working fluid (hydrogen) is shown. Such engines provide the ability to return to Earth at a speed of 8 km/s instead of 11 km/s, which increases flight safety and makes propulsion system reuse efficient.