引力波探测器控制
深入探究探测器的动力学与控制技术对于确保空间引力波探测平台能够达到超静超稳状态并圆满完成科学探测任务至关重要，这是“空间引力波探测”项目成功的基础理论保障。目前，空间引力波探测任务中控制的难点主要包括实现检验质量的超低扰动多级释放控制、双检验质量探测器的无拖曳控制、超大尺度无拖曳探测器编队的协同控制等。本专题主要针对空间引力波探测无拖曳及编队控制任务，全面综述了空间引力波探测无拖曳控制技术国内外研究现状及趋势，深入研究了基于径向力平衡飞行控制的航天器高精度轨道捕获技术、超大尺度星座构形的协同捕获控制策略、双检验质量无拖曳系统的平动控制问题。
鉴于此，《国防科技大学学报》组织策划“引力波探测器控制”专题。专题发表于《国防科技大学学报》2024年第2期，包含1篇综述性论文，3篇技术性论文。专题文章由中山大学天琴计划教育部重点实验室联合航空航天学院、人工智能学院团队撰写，旨在针对空间引力波探测中超静超稳航天器控制问题，通过国内外研究现状剖析、先进控制理论与方法应用等，让读者能够了解和掌握空间引力波探测无拖曳及编队控制思路与方法。
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2024, 46(2):1-17.
DOI: 10.11887/j.cn.202402001
Abstract:
The drag-free control of the spacecraft is one of the key technologies to realize the ultra-static and ultra-stable operation of science platform for gravitational wave space detection. At present, the dynamics and control of the spacecraft system have been studied deeply by various research institutions at domestic and overseas, and different detection tasks have been proposed according to the requirements of different detection frequency bands. The design and control of spacecraft formation were introduced and analyzed in detail according to the exploration mission, and the principles and theoretical methods of drag-free and attitude control, high-precision inertial sensors and actuators involved were deeply dissected. The overall situation of demonstration and verification of drag-free spacecraft in orbit for space-based gravitational wave detection was detailed and analyzed. On this basis, the key problems required to be solved in the research of follow-up related were presented, and the research hotspots and trends in the methods of future dynamics and control of drag-free spacecraft systems were also pointed out.
The drag-free control of the spacecraft is one of the key technologies to realize the ultra-static and ultra-stable operation of science platform for gravitational wave space detection. At present, the dynamics and control of the spacecraft system have been studied deeply by various research institutions at domestic and overseas, and different detection tasks have been proposed according to the requirements of different detection frequency bands. The design and control of spacecraft formation were introduced and analyzed in detail according to the exploration mission, and the principles and theoretical methods of drag-free and attitude control, high-precision inertial sensors and actuators involved were deeply dissected. The overall situation of demonstration and verification of drag-free spacecraft in orbit for space-based gravitational wave detection was detailed and analyzed. On this basis, the key problems required to be solved in the research of follow-up related were presented, and the research hotspots and trends in the methods of future dynamics and control of drag-free spacecraft systems were also pointed out.
2024, 46(2):18-26.
DOI: 10.11887/j.cn.202402002
Abstract:
Aiming at the cooperative acquisition control problem of geocentric very high orbit constellations, a cooperative acquisition control strategy was designed on the basis of the virtual formation method, and a three-pulse burnup optimal trajectory planning algorithm was used to coordinate the trajectory of the conformation acquisition. And the adaptive whole integral sliding mode controller was combined to track and control the transfer trajectory of the satellites. Taking the three-star constellation configuration capture at an orbital altitude of 100 000 km as an example for simulation verification, simulation results show that this strategy can be effectively applied to the configuration control of the constellation with very high geocentric orbit. It can make the satellites in the constellation reach their nominal positions at the same time with less burn up, and at the same time has high accuracy.
Aiming at the cooperative acquisition control problem of geocentric very high orbit constellations, a cooperative acquisition control strategy was designed on the basis of the virtual formation method, and a three-pulse burnup optimal trajectory planning algorithm was used to coordinate the trajectory of the conformation acquisition. And the adaptive whole integral sliding mode controller was combined to track and control the transfer trajectory of the satellites. Taking the three-star constellation configuration capture at an orbital altitude of 100 000 km as an example for simulation verification, simulation results show that this strategy can be effectively applied to the configuration control of the constellation with very high geocentric orbit. It can make the satellites in the constellation reach their nominal positions at the same time with less burn up, and at the same time has high accuracy.
2024, 46(2):27-35.
DOI: 10.11887/j.cn.202402003
Abstract:
In order to acquire the accurate adjustment of the orbit shape and height of the detector, a new method of spacecraft continuous thrust control based on radial force equilibrium flight was proposed. The dynamic polar coordinate model of continuous thrust equilibrium flight was established, and the analytical orbit solution under special conditions was derived, the boundary conditions were further analyzed, and the control law of continuous thrust was given. Using this equilibrium flight control theory, the optimal control strategy for orbit capture can be constructed. Considering the thrust level of thrusters, the integrated adjustment of orbit shape, orbit height and orbit phase can be adjusted through one or more control processes. Numerical simulations show that the space gravitational wave detector with micro thruster can achieve high-precision orbit capture by using the orbit control method of equilibrium flight. This method has the advantages of analytical control process, small calculation, simple and practical.
In order to acquire the accurate adjustment of the orbit shape and height of the detector, a new method of spacecraft continuous thrust control based on radial force equilibrium flight was proposed. The dynamic polar coordinate model of continuous thrust equilibrium flight was established, and the analytical orbit solution under special conditions was derived, the boundary conditions were further analyzed, and the control law of continuous thrust was given. Using this equilibrium flight control theory, the optimal control strategy for orbit capture can be constructed. Considering the thrust level of thrusters, the integrated adjustment of orbit shape, orbit height and orbit phase can be adjusted through one or more control processes. Numerical simulations show that the space gravitational wave detector with micro thruster can achieve high-precision orbit capture by using the orbit control method of equilibrium flight. This method has the advantages of analytical control process, small calculation, simple and practical.
2024, 46(2):36-48.
DOI: 10.11887/j.cn.202402004
Abstract:
An on-orbit drag-free control technique for spaceborne gravitational wave detection missions was discussed. Based on the analysis and design of a possible future geocentric orbit detection mission, the relative motion dynamics and coupling characteristics between the spacecraft and mass blocks of an on-orbit drag-free system with with two test masses were modeled. At the same time, the performance index and perturbation of the drag-free system in the mission were preliminarily analyzed, and a relative translational control law based on frequency domain H∞ optimal control theory was designed. Numerical simulation results show that when the test masses of the two-test-mass on-orbit drag-free system are arranged according to the breathing angle of laser rangefinder, without a fixed tracking point strategy and without suspension control input along the non-sensitive axis, the spacecraft can achieve tracking of the reference point while meeting the frequency domain performance index of the system. At the same time, the time domain displacement of each test mass can be controlled to the micron level, thus obtaining the pure gravitational reference required by the mission.
An on-orbit drag-free control technique for spaceborne gravitational wave detection missions was discussed. Based on the analysis and design of a possible future geocentric orbit detection mission, the relative motion dynamics and coupling characteristics between the spacecraft and mass blocks of an on-orbit drag-free system with with two test masses were modeled. At the same time, the performance index and perturbation of the drag-free system in the mission were preliminarily analyzed, and a relative translational control law based on frequency domain H∞ optimal control theory was designed. Numerical simulation results show that when the test masses of the two-test-mass on-orbit drag-free system are arranged according to the breathing angle of laser rangefinder, without a fixed tracking point strategy and without suspension control input along the non-sensitive axis, the spacecraft can achieve tracking of the reference point while meeting the frequency domain performance index of the system. At the same time, the time domain displacement of each test mass can be controlled to the micron level, thus obtaining the pure gravitational reference required by the mission.
