A Multi-constraint Attitude Control Scheme for Micro-nano Satellite During On-Orbit Standby

In this paper, the attitude control problem of a class of micro-nano satellites in low Earth orbit without solar array driving mechanism is studied. Firstly, based on the attitude dynamics, a three-axis decoupled attitude control law is proposed so that each channel can be designed independently. Then, various constraints in satellite attitude design during on-orbit standby were analyzed. Under the constraints of energy security, a satellite attitude maneuver was proposed to ensure the sun orientation of the solar array. During the design process, multiple constraints such as attitude reference guarantee and thermal control condition guarantee were introduced. For different orbital characteristics, methods were proposed to determine the orientation attitude towards the sun by combining the geocentric vector, orbital normal vector, and solar vector, as well as the on-orbit standby control strategy of sun orientation in the sun light area with earth orientation in the shadow area. Then the optimal maneuver strategy and angular velocity planning method was proposed in the aspect of large angle attitude maneuver, which makes the attitude control of satellites safe and stable during on-orbit standby. The mathematical simulation results show that the scheme proposed in this paper is applicable to low Earth orbit micro-nano satellites with various inclinations, which verifies the effectiveness of the method proposed in this paper.