## 1 Introduction
[17] studied the control strategies of each attitude actuator. In 2019, a novel passive sun-oriented control method using solar radiation pressure torques was proposed by [PERSON] et al. [18], which can be used as a low-cost backup for emergencies. In the same year, [PERSON] et al. [19] proposed a sun-oriented spin-stabilized attitude control method based on pure magnetic control for the satellite equipped with a sun sensor and a magnetometer as attitude sensors and three magnetic torquers (MTQs) as attitude actuators. The modification of the above method is also investigated in [20]. In 2020, in view of the satellite in the sun-synchronous dawn-dusk orbit, [PERSON] et al. [21] proposed an attitude control method from the perspective of minimal system configuration for sun orientation. The method makes full use of the satellite's orbit characteristics and achieves the sun-oriented spin-stabilized attitude by using the pitch-axis spin-up method. However, most of the existing attitude control methods for sun orientation do not consider the influence of the shadow zone of the orbit, offset installation of sun sensor and solar panel, limitation of the field of view of the sun sensor, environmental disturbance torques, and other factors that may affect the performance of the attitude control. Therefore, the application scope of these methods is limited. Based on the above discussions, we focus on the sun-oriented spin-stabilized attitude control for micro/nano satellites using only magnetic control. The proposed method is motivated by [19; 20] while the influence of the shadow zone of the orbit, offset installation of the sun sensor and solar panel, limitation of the field of view of the sun sensor, and environmental disturbance torques are all considered in the proposed method. Different from the traditional spin-stabilized satellites (their spinning angular rate is generally as high as tens of revolutions per minute, even hundreds of revolutions per minute [22]), the proposed method can be applied to the case that the satellite spins at a relatively low angular rate (about several degrees per second). The proposed method is applicable to most Earth-orbit satellites for which the geomagnetic field can provide sufficient attitude control torque. The numerical simulation results show that the proposed method is applicable to the micro/nano satellite equipped with a sun sensor and a 3-axis magnetometer (TAM) as attitude sensors and three MTQs installed orthogonally as attitude actuators. In addition,the proposed method effectively guarantees the smooth implementation of satellite equipment debugging, energy acquisition, and other flight missions. Even in space exploration missions, the proposed method can be used as a good primary or backup solution for some phases of these missions [23; 24; 25; 26]. The paper is organized as follows. In Section 2, the overview and mathematical model of micro/nano satellite's ADCS are introduced. Then, the sun-oriented spin-stabilized attitude control method is proposed in Section 3 including the rate filter design and the attitude controller design. The numerical simulation and results analysis are presented in Section 4. Finally, the conclusion is summarized in Section 5.