Spacecraft Control Systems: Hybrid Continuous/Impulsive Control

航天器控制系统：混合连续/脉冲控制

• 批准号: RGPIN-2015-06363
• 负责人: Damaren, Christopher
• 金额: $ 3.13万
• 依托单位: University of Toronto
• 依托单位国家: 加拿大
• 项目类别: Discovery Grants Program - Individual
• 财政年份: 2015
• 资助国家: 加拿大
• 起止时间: 2015-01-01 至 2016-12-31
• 项目状态: 已结题
• 来源: https://www.nserc-crsng.gc.ca/ase-oro/Details-Detailles_eng.asp?id=591013
• 关键词: Spacecraft; Control; Systems; Hybrid; Continuous

Spacecraft exhibit three distinct types of motion.   The evolution of their position in space is the subject of orbital dynamics.  The evolution of their orientation with respect to some reference, such as the Earth, is described by attitude dynamics.  Larger spacecraft can be  quite flexible and one is also concerned with their structural dynamics which describes vibrational type behaviour.    Usually, feedback control systems are required to control spacecraft motion which use sensors to monitor the spacecraft motion and then correct errors using appropriate actuators which produce forces and torques. An example where one wants to control the spacecraft orbit is formation flying where the relative motion between multiple satellites needs to be controlled. A possible force actuator in this case is a thruster which uses the mass expulsion of fuel to produce reaction forces on the spacecraft.  The problem with this approach is that it relies on an expendable (the fuel) which is often in short supply.  An innovative source of force is the Lorentz force produced by a magnetic field on the charge carried by a spacecraft.   It turns out that not all of the relative motion in a spacecraft formation can be controlled with the Lorentz force - some of it is uncontrollable.  This suggests that one might combine the Lorentz force, which acts continuously,  with the use of thrusters.  Thrusters can be used over short durations; we say that they act impulsively.  We wish to solve this hybrid control problem where one wants to minimize the use of both continuous and impulsive control inputs.  Another spacecraft control problem is the magnetic attitude control  problem.  Here one uses the torques  produced by the Earth's magnetic field acting on current-carrying loops of wire on-board the satellite in conjunction with  impulsive torques produced by pairs of thrusters.

航天器表现出三种不同类型的运动。​它们在空间中的位置的演变是轨道动力学的主题。​它们相对于某些参照物（例如地球）的演化可以通过姿态动力学来描述。​非常灵活，并且还关注其描述振动类型行为的结构动力学。通常，需要反馈控制系统来控制航天器运动，该系统使用传感器来监测航天器运动，然后使用产生力和扭矩的适当执行器来纠正错误一个例子想要控制航天器轨道的情况是需要控制多颗卫星之间的相对运动，在这种情况下，可能的力执行器是推进器，它利用燃料的质量排出来在航天器上产生反作用力。这种方法的问题在于它依赖于经常短缺的消耗品（燃料）​一种创新的力源是由航天器携带的电荷产生的洛伦兹力。不是全部航天器编队中的相对运动可以用洛伦兹力来控制——其中一些是不可控制的，这表明我们可以在短时间内使用推进器来连续作用。我们希望解决这种混合控制问题，其中人们希望最小化连续和脉冲控制输入的使用，另一个航天器控制问题是磁姿态控制问题。地球磁场作用在卫星载流线圈上产生的扭矩，与一对推进器产生的脉冲扭矩相结合。