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Validation tests of attitude determination software for nanosatellite embedded systems

机译：纳米卫星嵌入式系统姿态确定软件的验证测试

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This article presents an assessment step of the development of a fault tolerant attitude determination system (SDATF) for nanosatellites. This system will be flight validated as payload of the NanosatC-BR2, a 2U-size cubesat that is being developed by the Brazilian Institute for Space Research (INPE) and partner universities. The SDATF has been designed with the purpose of providing real time, accurate and reliable attitude information to the attitude control system. Its technical features include fault tolerance techniques and triple redundancy in data processing to prevent problems caused by exposition of integrated circuits to space radiation. In the present phase of work, the tests consist of numerical simulations of the main algorithms before the software installation in the SDATF board. The analyzed algorithms are the attitude determination (the QUEST method), the computation of the Sun direction vector in inertial coordinates, the computation of the geomagnetic direction vector in North-East-Down local coordinates, and other auxiliary algorithms. The most critical aspect of these algorithms is the necessity of truncation and simplification of mathematical models in reason of the strong restrictions in the onboard processing, time of computation, and memory limitations. The obtained results can be considered compatible with the ones seen in other systems developed for other nanosatellite missions, and the performance of the attitude determination software is adequate to the requirements of the system.
机译：本文介绍了纳米替肽的容错姿态确定系统（SDATF）的评估步骤。该系统将被验证为纳米水溶 - BR2的有效载荷，这是由巴西空间研究所（INPE）和合作大学开发的2U尺寸的CubeSat。 SDATF设计的目的是为姿态控制系统提供实时，准确和可靠的态度信息。其技术特征包括数据处理中的容错技术和三重冗余，以防止由集成电路的阐述引起的空间辐射引起的问题。在本工作阶段，测试包括在SDATF板软件安装之前的主要算法的数值模拟。分析的算法是姿态确定（Quest方法），惯性坐标中的太阳方向向量的计算，北向下局部坐标的地磁方向向量的计算，以及其他辅助算法。这些算法的最关键方面是由于车载处理，计算时间和内存限制的强制限制而导致的数学模型的截断和简化的必要性。获得的结果可以与在为其他纳米卫星任务开发的其他系统中看到的结果相容，并且姿态确定软件的性能足以满足系统的要求。

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