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所在平台: Coursera |
课程主页: https://www.coursera.org/learn/capstone-mars-mission
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课程名称：航天器动力学顶点项目：火星任务 概述：本课程旨在运用在刚体运动学、动力学与控制课程中所学到的技能，进行一项令人激动的双航天器火星任务设计。该项目涉及一母航天器与一处于不同轨道的子航天器之间的通信。主要挑战包括确定轨道框架及多个期望参考框架的运动学，数值模拟航天器在轨道上的姿态动力学，并实施反馈控制以驱动航天器进入不同的任务模式，包括太阳指向以进行能量生成、天底指向以进行科学探测、母航天器指向以实现通信和数据传输。最终，课程将开发一个集成的任务模拟，应用这些姿态模式并探讨其自主闭环表现。 课程大纲： 1. **任务介绍**：本课程目的是结合刚体运动学、动力学和控制课程中学到的技能，完成一个即将进行的双航天器火星任务的设计。 2. **轨道**：任务1和2利用三维运动学创建与任务相关的轨道模拟及其相关轨道框架，确保卫星运动正确，同时评估轨道框架相对于行星的方向。 3. **参考框架方向**：任务3至5创建三种姿态指向模式（太阳指向、天底指向和母航天器指向）的必要姿态参考框架，以确保反馈控制将卫星引导至期望的方向。 4. **姿态评估与模拟器**：任务6到7创建模拟例程，评估机体固定框架与当前姿态模式的特定参考框架之间的姿态跟踪误差，并通过数值模拟评估惯性姿态动力学。 5. **完成任务**：任务8至11模拟三种姿态模式的闭环姿态表现，前期任务分别单独模拟每种姿态，最后任务开发全面的姿态任务模拟，考虑航天器相对于行星位置的自主模式切换。 请注意，完成本模块及相应任务所需的时间较之前模块有所增加。
Name:Introduction to the Mission
Description:The goal of this capstone spacecraft dynamics project is to employ the skills developed in the rigid body kinematics, kinetics and control courses. An exciting two-spacecraft mission to Mars is considered where a primary mother craft is in communication with a daughter vehicle in another orbit. The challenges include determining the kinematics of the orbit frame and several desired reference frames, numerically simulating the attitude dynamics of the spacecraft in orbit, and implementing a feedback control that then drives different spacecraft body frames to a range of mission modes including sun pointing for power generation, nadir pointing for science gathering, mother spacecraft pointing for communication and data transfer. Finally, an integrated mission simulation is developed that implements these attitude modes and explores the resulting autonomous closed-loop performance.
Name:Orbits
Description:Tasks 1 and 2 use three-dimensional kinematics to create the mission related orbit simulation and the associated orbit frames. The introductory step ensures the satellite is undergoing the correct motion, and that the orbit frame orientation relative to the planet is being properly evaluated.
Name:Reference Frame Orientation
Description:Tasks 3 through 5 create the required attitude reference frame for the three attitude pointing modes called sun-pointing, nadir-pointing and GMO-pointing. The reference attitude frame is a critical component to ensure the feedback control drives the satellite to the desired orientation. The control employed remains the same for all three pointing modes, but the performance is different because different attitude reference frames are employed.
Name:Attitude Evaluation and Simulator
Description:Tasks 6 through 7 create simulation routines to first evaluate the attitude tracking error between a body-fixed frame and a particular reference frame of the current attitude mode. Next the inertial attitude dynamics is evaluated through a numerical simulation to be able to numerically analyze the control performance.
Name:Complete the Mission
Description:Tasks 8-11 simulate the closed-loop attitude performance for the three attitude modes. Tasks 8 through 10 first simulate a single attitude at a time, while tasks 11 develops a comprehensive attitude mission simulation which considers the attitude modes switching autonomously as a function of the spacecraft location relative to the planet. Please note that the time it will take you to complete this module and the requisite tasks has increased from prior modules.
The goal of this capstone spacecraft dynamics project is to employ the skills developed in the rigid body Kinematics, Kinetics and Control courses. An exciting two-spacecraft mission to Mars is considered where a primary mother craft is in communication with a daughter vehicle in another orbit. The challenges include determining the kinematics of the orbit frame and several desired reference frames, numerically simulating the attitude dynamics of the spacecraft in orbit, and implementing a feedback control that then drives different spacecraft body frames to a range of mission modes including sun pointing for power generation, nadir pointing for science gathering, mother spacecraft pointing for communication and data transfer. Finally, an integrated mission simulation is developed that implements these attitude modes and explores the resulting autonomous closed-loop performance. Tasks 1 and 2 use three-dimensional kinematics to create the mission related orbit simulation and the associated orbit frames. The introductory step ensures the satellite is undergoing the correct motion, and that the orbit frame orientation relative to the planet is being properly evaluated. Tasks 3 through 5 create the required attitude reference frame for the three attitude pointing modes called sun-pointing, nadir-pointing and GMO-pointing. The reference attitude frame is a critical component to ensure the feedback control drives the satellite to the desired orientation. The control employed remains the same for all three pointing modes, but the performance is different because different attitude reference frames are employed. Tasks 6 through 7 create simulation routines to first evaluate the attitude tracking error between a body-fixed frame and a particular reference frame of the current attitude mode. Next the inertial attitude dynamics is evaluated through a numerical simulation to be able to numerically analyze the control performance. Tasks 8-11 simulate the closed-loop attitude performance for the three attitude modes. Tasks 8 through 10 first simulate a single attitude at a time, while tasks 11 develops a comprehensive attitude mission simulation which considers the attitude modes switching autonomously as a function of the spacecraft location relative to the planet.
