用真实飞轮在环测试卫星姿态控制器，验证其自适应与故障估计能力。
Real-time Testing of Satellite Attitude Control With a Reaction Wheel Hardware-In-the-Loop Platform
- 搭建飞轮在环测试平台，集成真实电机与通信总线
- 实现飞轮故障模拟与控制器实时响应验证
- 适合航天器控制算法研发与可靠性验证人员
本文提出一种基于硬件在环（HIL）的自适应卫星姿态控制系统的实时测试方法，具备反应轮健康状态估计功能。此前的仿真与软件在环测试已推动进一步实验，以验证控制器在真实动量交换装置参与下的有效性。该工作是构建航天器姿态控制算法完整验证框架的重要一步。所提出的HIL测试平台包含无刷直流电机及驱动器、通过CAN总线通信的嵌入式计算机，以及生成模拟传感器数据、估计姿态状态并响应外部执行器动作的卫星仿真器。本文还提出了对反应轮进行人为故障注入的方法，并总结了相关问题与经验教训。
原文摘要 · Abstract (English)
We propose the Hardware-in-the-Loop (HIL) test of an adaptive satellite attitude control system with reaction wheel health estimation capabilities. Previous simulations and Software-in-the-Loop testing have prompted further experiments to explore the validity of the controller with real momentum exchange devices in the loop. This work is a step toward a comprehensive testing framework for validation of spacecraft attitude control algorithms. The proposed HIL testbed includes brushless DC motors and drivers that communicate using a CAN bus, an embedded computer that executes control and adaptation laws, and a satellite simulator that produces simulated sensor data, estimated attitude states, and responds to actions of the external actuators. We propose methods to artificially induce failures on the reaction wheels, and present related issues and lessons learned.
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