Atttiude Estimation for Small, Agile Spacecraft

小型敏捷航天器的姿态估计

• 批准号: RGPIN-2015-05584
• 负责人: Enright, John
• 金额: $ 1.82万
• 依托单位: Ryerson University
• 依托单位国家: 加拿大
• 项目类别: Discovery Grants Program - Individual
• 财政年份: 2019
• 资助国家: 加拿大
• 起止时间: 2019-01-01 至 2020-12-31
• 项目状态: 已结题
• 来源: https://www.nserc-crsng.gc.ca/ase-oro/Details-Detailles_eng.asp?id=680305
• 关键词: Atttiude; Estimation; Small; Agile; Spacecraft

Very small spacecraft are increasingly seen as a valid platform for cost-effective and responsive space missions. Once considered suitable only for technology demonstrations cubesat and nanosatellite class spacecraft now have significant flight heritage in demanding environments. As the capabilities of these spacecraft expand, designers require better performance from the satellites' subsystems. This push towards improved performance is particularly acute in the area of spacecraft attitude estimation.***This proposal examines the challenges encountered in designing sensors and integrated attitude estimation systems for very small spacecraft. Not only do these missions demand precise knowledge of spacecraft orientation but many emerging applications for Earth-Observation (EO) satellite servicing, and missions beyond Low Earth Orbit (LEO) require that this attitude knowledge be available when the satellite is undergoing rapid motion. Accommodating these technical and operational challenges requires design approaches significantly different than what is encountered in traditional satellite engineering. The proposed research combines design trade-studies with detailed analysis of single-sensor and multi-sensor estimation systems. ***The proposed program of research relies on a number of complementary methodologies. High-level simulations are used to conduct system-level trade studies and design optimization. More detailed sensor processing and estimation techniques are first evaluated analytically and then validated with detailed simulations of sensor operation using Matlab and Zemax. New processing algorithms can be evaluated and tested in laboratory experiments on a variety of engineering-model star trackers and LIDAR systems. This comprehensive approach to development and validation helps mature innovations to the point that they are suitable for follow-on projects in conjunction with industry partners.***We expect that this research will lead to improvements in the practice of high-performance attitude estimation for agile cubesats and nanosatellites. These advances will benefit mission designers (better trade studies and design tools), attitude determination and control engineers (tailored estimation and signal processing algorithms), and avionics developers (motion compensation and other sensor-specific innovations).********

非常小的航天器越来越被视为具有成本效益和响应迅速的太空任务的有效平台。立方体卫星和纳米卫星级航天器曾经被认为仅适用于技术演示，现在在苛刻的环境中具有重要的飞行传统。随着这些航天器功能的扩展，设计人员要求卫星子系统具有更好的性能。这种对性能改进的推动在航天器姿态估计领域尤其重要。***该提案研究了为小型航天器设计传感器和集成姿态估计系统时遇到的挑战。这些任务不仅需要精确了解航天器方向，而且地球观测 (EO) 卫星服务的许多新兴应用以及近地轨道 (LEO) 以外的任务都要求在卫星快速运动时提供这种姿态知识。应对这些技术和操作挑战需要采用与传统卫星工程中遇到的明显不同的设计方法。拟议的研究将设计权衡研究与单传感器和多传感器估计系统的详细分析结合起来。 ***拟议的研究计划依赖于许多互补的方法。高级模拟用于进行系统级权衡研究和设计优化。首先对更详细的传感器处理和估计技术进行分析评估，然后使用 Matlab 和 Zemax 对传感器操作进行详细模拟进行验证。新的处理算法可以在各种工程模型星跟踪器和激光雷达系统的实验室实验中进行评估和测试。这种全面的开发和验证方法有助于成熟的创新，使其适合与行业合作伙伴一起进行后续项目。***我们预计这项研究将改进高性能态度估计的实践敏捷的立方体卫星和纳米卫星。这些进步将使任务设计师（更好的权衡研究和设计工具）、姿态确定和控制工程师（定制的估计和信号处理算法）以及航空电子设备开发人员（运动补偿和其他特定于传感器的创新）受益。******** *