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为了提高航天器的有效载荷比,针对目前姿态控制系统中采用有线连接的问题,以单轴气浮台为仿真平台,基于无线自组织网络构建了一种刚体航天器姿态控制半实物仿真系统,提高航天器设计的灵活性和可靠性。首先详细介绍了该系统的总体构成和方案设计,星载计算机采用双ARM冗余的体系结构,光纤陀螺、星载计算机、反作用飞轮以及动力学仿真机之间通过无线自组织网络节点互连。其次,介绍了姿态控制系统的数学模型及控制算法。最后,利用该系统对航天器三轴正常姿态稳定控制进行了半实物仿真。仿真结果表明,姿态控制精度能够满足任务需求,同时校验了仿真系统设计的合理性和正确性。
In order to improve the payload ratio of the spacecraft, aiming at the problem of wired connection in the current attitude control system, a single-axis flotation platform is used as a simulation platform to build a semi-physical simulation system for attitude control of a rigid-body spacecraft based on a wireless self-organizing network. Improve spacecraft design flexibility and reliability. First of all, the system’s overall structure and scheme design are introduced in detail. The dual-ARM redundancy architecture is adopted in on-board computer. FOG, spaceborne computer, reaction flywheel and dynamic simulator are interconnected by wireless self-organizing network nodes. Secondly, the mathematical model and control algorithm of attitude control system are introduced. Finally, a semi-physical simulation of the three-axis spacecraft’s normal attitude stability control is carried out by using this system. The simulation results show that the attitude control accuracy can meet the task requirements and verify the rationality and correctness of the simulation system design.