energy safeguard design method for an inertial space observation satellite

The invention provides an energy safeguard design method for an inertial space observation satellite. The energy safeguard design method comprises the following steps: (1) determining an inertial space observation satellite body coordinate system and a fixed sun-facing surface according to a satellite basic configuration and a solar wing mounting direction; (2) designing an attitude control algorithm on the basis of a fixed sun alignment surface, and minimizing an included angle between a solar vector and a vertical plane of a sailboard mounting shaft in a single observation process on the premise of ensuring observation direction and observation coverage required by observation; (3) designing a solar wing tracking algorithm according to the change rule of solar vectors based on an attitude control algorithm design result, so that the whole satellite obtains the maximum energy in the whole observation process; And (4) judging whether the energy design requirement is met by the satellites in the whole observat