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Nanosatellites have serious limitations on the onboard energy. Therefore, it is necessary to find a method of constructing a nominal reorientation trajectory that will optimally use the resources available onboard. In this paper the process of constructing of a nominal reorientation trajectory in the plane of nanosatellite orbit is considered. The problem of constructing a nominal reorientation trajectory was solved using the inverse dynamic problem method and Pontryagin maximum principle. A comparison of the results obtained using these two methods was made. As a result, it was noted that the solution obtained by the inverse dynamic problem method is close to the solution obtained using the Pontryagin maximum principle. This allows us to speak about the optimality of the inverse dynamics problem method.

This work aims to simulate the flight of a spacecraft with an electric propulsion system to the near-Earth asteroid 2011ES4. A control law was formed that ensures the minimum fuel consumption when the engine is running without shutdowns. The simulation of the flight of the spacecraft to the point of the asteroid’s orbit closest to the Earth is carried out. An additional study was also carried out, which simulates the flight of a spacecraft with a liquid-propellant engine. A comparison of the flight simulation results using two different propulsion systems was made. A comparison of the mass flow rate, the relative velocity between the spacecraft and the asteroid, and the flight times using these propulsion systems is made.