小卫星姿控xPC半物理仿真系统设计

Design of xPC semi-physical simulation system for small-satellite attitude control

针对利用反作用飞轮作为执行机构的小卫星姿控系统,设计了基于xPC实时仿真环境、高精度单轴气浮转台、姿控计算机、光纤陀螺和反作用飞轮的卫星姿态控制系统半物理仿真实验平台,并利用该平台系统对使用反作用飞轮的小卫星姿态控制机动模式进行了半物理仿真验证,在50 s内使姿态机动了31.57°,且有较好的指向精度和稳定度。结果表明,根据光纤陀螺和反作用飞轮现有特性,用设计的姿态控制算法进行姿态机动能够满足控制系统性能指标。

To take advantage of the reaction flywheel to build an attitude control system for a small satellite,a semi-physical simulation plate system was designed based on the xPC real-time environment, single-axis air-bearing platform, attitude control computer, optical fiber gyro and reaction flywheel. With the system, a semi-physical simulation was verified for the small satellite control maneuver mode concerned to the reaction flywheel. The results of the simulation indicate that small-satellite attitude is maneuvered 31.57° within 50 s in better pointing accuracy and stability. The conclusion shows that according to the characteristics of the gyroscope and the reaction flywheel, the designed algorithm can meet the requirement of the maneuver on the small-satellite attitude control.