This paper investigates the attitude and orbit control for the combined spacecraft formed after a target spacecraft without the autonomous control ability is captured by a service spacecraft.The optimal controller of ...This paper investigates the attitude and orbit control for the combined spacecraft formed after a target spacecraft without the autonomous control ability is captured by a service spacecraft.The optimal controller of fully-actuated system is proposed to realize the attitude and orbit stabilization control of combined spacecraft.The stability of the system is proved by introducing Lyapunov function.Numerical simulation of the combined spacecraft and physical experiment based on the combined spacecraft simulator(CSS)are completed.Both simulation and experiment results demonstrate the effectiveness and practicability of the optimal controller of fully-actuated system.展开更多
This study presents an improved data-driven Model-Free Adaptive Control(MFAC)strategy for attitude stabilization of a partially constrained combined spacecraft with external disturbances and input saturation. First, a...This study presents an improved data-driven Model-Free Adaptive Control(MFAC)strategy for attitude stabilization of a partially constrained combined spacecraft with external disturbances and input saturation. First, a novel dynamic linearization data model for the partially constrained combined spacecraft with external disturbances is established. The generalized disturbances composed of external disturbances and dynamic linearization errors are then reconstructed by a Discrete Extended State Observer(DESO). With the dynamic linearization data model and reconstructed information, a DESO-MFAC strategy for the combined spacecraft is proposed based only on input and output data. Next, the input saturation is overcome by introducing an antiwindup compensator. Finally, numerical simulations are carried out to demonstrate the effectiveness and feasibility of the proposed controller when the dynamic properties of the partially constrained combined spacecraft are completely unknown.展开更多
In this paper, we propose a novel anti-disturbance attitude control law for combined spacecraft with an improved closed-loop control allocation scheme. More specifically, a saturated approach is adopted to guarantee t...In this paper, we propose a novel anti-disturbance attitude control law for combined spacecraft with an improved closed-loop control allocation scheme. More specifically, a saturated approach is adopted to guarantee the global asymptotic stability under control input saturation.To enhance the robustness of the system, a nonlinear disturbance observer is constructed to compensate the disturbances caused by inertial parameter uncertainty and unmodeled dynamics. Next,the quadratic programming algorithm is used to obtain an optimal open-loop control allocation scheme, where both energy consumption and actuator saturation have been considered in the allocation of the virtual control command. Then, a modified closed-loop control allocation scheme is proposed to reduce the allocation error under the actuator uncertainty. Finally, stability analysis of the closed-loop system with the proposed allocation scheme is provided. Simulation results confirm the effectiveness of the proposed control scheme.展开更多
Solar radiation pressure(SRP)impinging on spacecraft is usually regarded as a disturbance for attitude motion,but it can be harnessed to solve the very problem it creates.Active SRP control is possible with solar radi...Solar radiation pressure(SRP)impinging on spacecraft is usually regarded as a disturbance for attitude motion,but it can be harnessed to solve the very problem it creates.Active SRP control is possible with solar radiation powered thin-film devices such as reflectivity control devices or liquid crystal devices with reflective microstructure.Thermal radiation pressure(TRP)can likewise be used to solve flight attitude problems caused by SRP,TRP,or other factors.TRP on solar cells can be controlled by switching regulators under the control of them,resulting in temperature change.These SRP/TRP controls are free from mechanisms,such as reaction wheels,and thus they do not produce internal disturbances.In addition,the magnitude of SRP/TRP torques is generally much smaller than internal disturbance torques produced by reaction wheels,which creates a potential for precision far beyond that achieved with mechanical controls.This paper summarizes how SRP/TRP can be used by means of numerical simulations of typical control methods.The usefulness of this mechanism-free attitude control is verified for future use on both Earth orbiting satellites and interplanetary spacecraft including solar sails.展开更多
空间太阳能电站(Space Solar Power Station,SSPS),是指能够在轨道上将太阳能通过工程技术手段有效采集、转化并传输到地面,再转化成为电能供地面使用的系统。聚光是空间太阳能收集的途径之一,多种SSPS方案采用了聚光方式。文章介绍了...空间太阳能电站(Space Solar Power Station,SSPS),是指能够在轨道上将太阳能通过工程技术手段有效采集、转化并传输到地面,再转化成为电能供地面使用的系统。聚光是空间太阳能收集的途径之一,多种SSPS方案采用了聚光方式。文章介绍了聚光式SSPS的研究现状,对现有SSPS方案中的不同聚光技术方案进行了综述分析,将空间太阳能电站聚光技术划分为3个层次,总结成4种模式,详细分析了每种模式的优点与技术难点,并对聚光式空间太阳能电站的发展提出建议。展开更多
基金This paper was supported in part by the National Natural Science Foundation of China under Grant Nos.62173255 and 62188101.
文摘This paper investigates the attitude and orbit control for the combined spacecraft formed after a target spacecraft without the autonomous control ability is captured by a service spacecraft.The optimal controller of fully-actuated system is proposed to realize the attitude and orbit stabilization control of combined spacecraft.The stability of the system is proved by introducing Lyapunov function.Numerical simulation of the combined spacecraft and physical experiment based on the combined spacecraft simulator(CSS)are completed.Both simulation and experiment results demonstrate the effectiveness and practicability of the optimal controller of fully-actuated system.
基金supported by National Natural Science Foundation of China(Nos.61603114,61673135)the Fundamental Research Funds for the Central Universities of China(No.HIT.NSRIF.201826)
文摘This study presents an improved data-driven Model-Free Adaptive Control(MFAC)strategy for attitude stabilization of a partially constrained combined spacecraft with external disturbances and input saturation. First, a novel dynamic linearization data model for the partially constrained combined spacecraft with external disturbances is established. The generalized disturbances composed of external disturbances and dynamic linearization errors are then reconstructed by a Discrete Extended State Observer(DESO). With the dynamic linearization data model and reconstructed information, a DESO-MFAC strategy for the combined spacecraft is proposed based only on input and output data. Next, the input saturation is overcome by introducing an antiwindup compensator. Finally, numerical simulations are carried out to demonstrate the effectiveness and feasibility of the proposed controller when the dynamic properties of the partially constrained combined spacecraft are completely unknown.
基金co-supported by the National Natural Science Foundation of China (Nos. 61627810, 61320106010, 61633003, 61661136007, 61603021)the Program for Changjiang Scholars and Innovative Research Team (No. IRT_16R03)Innovative Research Team of National Natural Science Foundation of China (No. 61421063)
文摘In this paper, we propose a novel anti-disturbance attitude control law for combined spacecraft with an improved closed-loop control allocation scheme. More specifically, a saturated approach is adopted to guarantee the global asymptotic stability under control input saturation.To enhance the robustness of the system, a nonlinear disturbance observer is constructed to compensate the disturbances caused by inertial parameter uncertainty and unmodeled dynamics. Next,the quadratic programming algorithm is used to obtain an optimal open-loop control allocation scheme, where both energy consumption and actuator saturation have been considered in the allocation of the virtual control command. Then, a modified closed-loop control allocation scheme is proposed to reduce the allocation error under the actuator uncertainty. Finally, stability analysis of the closed-loop system with the proposed allocation scheme is provided. Simulation results confirm the effectiveness of the proposed control scheme.
文摘Solar radiation pressure(SRP)impinging on spacecraft is usually regarded as a disturbance for attitude motion,but it can be harnessed to solve the very problem it creates.Active SRP control is possible with solar radiation powered thin-film devices such as reflectivity control devices or liquid crystal devices with reflective microstructure.Thermal radiation pressure(TRP)can likewise be used to solve flight attitude problems caused by SRP,TRP,or other factors.TRP on solar cells can be controlled by switching regulators under the control of them,resulting in temperature change.These SRP/TRP controls are free from mechanisms,such as reaction wheels,and thus they do not produce internal disturbances.In addition,the magnitude of SRP/TRP torques is generally much smaller than internal disturbance torques produced by reaction wheels,which creates a potential for precision far beyond that achieved with mechanical controls.This paper summarizes how SRP/TRP can be used by means of numerical simulations of typical control methods.The usefulness of this mechanism-free attitude control is verified for future use on both Earth orbiting satellites and interplanetary spacecraft including solar sails.
文摘空间太阳能电站(Space Solar Power Station,SSPS),是指能够在轨道上将太阳能通过工程技术手段有效采集、转化并传输到地面,再转化成为电能供地面使用的系统。聚光是空间太阳能收集的途径之一,多种SSPS方案采用了聚光方式。文章介绍了聚光式SSPS的研究现状,对现有SSPS方案中的不同聚光技术方案进行了综述分析,将空间太阳能电站聚光技术划分为3个层次,总结成4种模式,详细分析了每种模式的优点与技术难点,并对聚光式空间太阳能电站的发展提出建议。
