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首页> 外文会议>4th ESA International Conference on Spacecraft Guidance, Navigation and Control Systems, 4th, Oct 18-21, 1999, ESTEC, Noordwijk, The Netherlands >CONTROL DESIGN FOR A CRITICAL LEO EARTH OBSERVATION SATELLITE, BASED ON GNSS SENSORS FOR ORBIT AND ATTITUDE DETERMINATION
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CONTROL DESIGN FOR A CRITICAL LEO EARTH OBSERVATION SATELLITE, BASED ON GNSS SENSORS FOR ORBIT AND ATTITUDE DETERMINATION

机译：基于GNSS传感器进行轨道和姿态确定的关键的地球观测卫星的控制设计。

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This paper summarises the Spacecraft control characterisation and design process for a critical LEO Earth Observation satellite, which uses GNSS as the baseline for such a system, and requires special design due to the implications in mission and vehicle management. The presented activity was performed under an ESA/ESTEC project, with SENER(E) covering the control system analysis and design, and GMV addressing the mission and verification aspects. The usage of GNSS for both Position-Velocity-Time Determination and Attitude Determination will allow real-time on-board determination of the spacecraft state, and consequently the possibility for autonomous and flexible management of the vehicle and the mission. This will have significant implications on the control design and will require a very specific and elaborated Spacecraft Control capability. The control design and its properties determine the autonomous planning capabilities for the selected S/C activity scheduling, in order to acquire the desired targets, with the appropriate position, pointing and stability requirements. This paper will show the complete process in order to obtain an adequate control system. The early configurations of the spacecraft, which was used as baseline for the presented work, had solar panels introducing a very significant flexibility coupling effect, which leads to an additional control design constraint considered as well within the current paper. For the design of the control algorithms a set of control design methods were considered. The selected approach included hybrid techniques, with PID, LQR, FeedForward, phase advancement, and a-posteriori singular values analysis, which guarantee stable control systems, with suitable algorithms for evaluation of configuration changes, and valid for every S/C mode. For the verification of the system a complete modelling of the control and the plant was performed, including detailed modelling of the solar panels with NASTRAN models of a virtual panel derived from similar designs, and introduction of these properties on a flexible dynamics simulator.
机译：本文总结了关键LEO地球观测卫星的航天器控制特性和设计过程，该卫星使用GNSS作为该系统的基线，由于其在任务和飞行器管理方面的影响，因此需要进行特殊设计。所介绍的活动是在ESA / ESTEC项目下进行的，SENER（E）涵盖了控制系统的分析和设计，而GMV解决了任务和验证方面。将GNSS用于位置-速度-时间确定和姿态确定将允许实时在船上确定航天器状态，从而有可能对车辆和任务进行自主和灵活的管理。这将对控制设计产生重大影响，并且将需要非常具体且详尽的航天器控制功能。控制设计及其属性确定用于选定S / C活动计划的自主计划能力，以便获得具有适当位置，指向和稳定性要求的期望目标。本文将展示完整的过程，以便获得适当的控制系统。该航天器的早期配置被用作本研究的基准，其太阳能电池板引入了非常显着的柔韧性耦合效应，这导致了本文中也考虑的其他控制设计约束。对于控制算法的设计，考虑了一组控制设计方法。选择的方法包括混合技术，包括PID，LQR，前馈，相位超前和后验奇异值分析，这些技术可确保稳定的控制系统，并具有用于评估配置更改的合适算法，并且对每种S / C模式均有效。为了验证系统，对控件和工厂进行了完整的建模，包括使用从类似设计衍生的虚拟面板的NASTRAN模型对太阳能面板进行详细建模，并将这些特性引入灵活的动力学模拟器中。

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