To reveal some dynamic properties of the deploying process for the solar power satellite via an arbitrarily large phased array （SPS-ALPHA） solar receiver, the symplectic Runge-Kutta method is used to simulate the si...To reveal some dynamic properties of the deploying process for the solar power satellite via an arbitrarily large phased array （SPS-ALPHA） solar receiver, the symplectic Runge-Kutta method is used to simulate the simplified model with the consideration of the Rayleigh damping effect. The system containing the Rayleigh damping can be separated and transformed into the equivalent nondamping system formally to insure the application condition of the symplectic Runge-Kutta method. First, the Lagrange equation with the Rayleigh damping governing the motion of the system is derived via the variational principle. Then, with some reasonable assumptions on the relations among the damping, mass, and stiffness matrices, the Rayleigh damping system is equivalently converted into the nondamping system formally, so that the symplectic Runge-Kutta method can be used to simulate the deploying process for the solar receiver. Finally, some numerical results of the symplectic Runge-Kutta method for the dynamic properties of the solar receiver are reported. The numerical results show that the proposed simplified model is valid for the deploying process for the SPS-ALPHA solar receiver, and the symplectic Runge-Kutta method can preserve the displacement constraints of the system well with excellent long-time numerical stability.展开更多
This paper proposes a self-tuning iterative learning control method for the attitude control of a flexible solar power satellite,which is simplified as an Euler-Bernoulli beam moving in space.An orbit-attitude-structu...This paper proposes a self-tuning iterative learning control method for the attitude control of a flexible solar power satellite,which is simplified as an Euler-Bernoulli beam moving in space.An orbit-attitude-structure coupled dynamic model is established using absolute nodal coordinate formulation,and the attitude control is performed using two control moment gyros.In order to improve control accuracy of the classic proportional-derivative control method,a switched iterative learning control method is presented using the control moments of the previous periods as feedforward control moments.Although the iterative learning control is a model-free method,the parameters of the controller must be selected manually.This would be undesirable for complicated systems with multiple control parameters.Thus,a self-tuning method is proposed using fuzzy logic.The control frequency of the controller is adjusted according to the averaged control error in one control period.Simulation results show that the proposed controller increases the control accuracy greatly and reduces the influence of measurement noise.Moreover,the control frequency is automatically adjusted to a suitable value.展开更多
To deal with the vibration problem of the solar power satellite(SPS),the distributed vibration control approach is investigated in this paper.Taking the Multi-Rotary joints SPS as the research objective,the control un...To deal with the vibration problem of the solar power satellite(SPS),the distributed vibration control approach is investigated in this paper.Taking the Multi-Rotary joints SPS as the research objective,the control unit(CU)and the location relationship matrix are rstly de ned for distributed controller design according to the con guration of SPS.The dynamic model of each CU is therefore established based on the nite element method.The dynamic model of the whole SPS structure is then developed using the CU models,and is updated along with on-orbit assembly.The distributed cooperative controller,using proportional and di erential feedback and the interaction feedback among adjacent CUs,is proposed to suppress vibration.The close-loop distributed cooperative control system is then achieved by integrating all distributed controllers,and the asymptotic stability is proofed by the Lyapunov's stability theorem.To verify the feasibility of the proposed control system,three numerical cases are nally presented.The results demonstrate that the distributed cooperative controllers can e ectively suppress vibration during on-orbit assembly and operation after assembly,and the closed-loop system has good fault tolerance.展开更多
基金supported by the National Natural Science Foundation of China(Nos.11432010,11672241,and 11502202)the Open Foundation of the State Key Laboratory of Structural Analysis of Industrial Equipment of China(No.GZ1605)
文摘To reveal some dynamic properties of the deploying process for the solar power satellite via an arbitrarily large phased array （SPS-ALPHA） solar receiver, the symplectic Runge-Kutta method is used to simulate the simplified model with the consideration of the Rayleigh damping effect. The system containing the Rayleigh damping can be separated and transformed into the equivalent nondamping system formally to insure the application condition of the symplectic Runge-Kutta method. First, the Lagrange equation with the Rayleigh damping governing the motion of the system is derived via the variational principle. Then, with some reasonable assumptions on the relations among the damping, mass, and stiffness matrices, the Rayleigh damping system is equivalently converted into the nondamping system formally, so that the symplectic Runge-Kutta method can be used to simulate the deploying process for the solar receiver. Finally, some numerical results of the symplectic Runge-Kutta method for the dynamic properties of the solar receiver are reported. The numerical results show that the proposed simplified model is valid for the deploying process for the SPS-ALPHA solar receiver, and the symplectic Runge-Kutta method can preserve the displacement constraints of the system well with excellent long-time numerical stability.
基金supported by the Guangdong Basic and Applied Basic Research Foundation(No.2019A1515110730)the Young Elite Scientists Sponsorship Program by China Association for Science and Technology(No.2021QNRC001)the Fundamental Research Funds for the Central Universities of Sun Yat-sen University(No.22qntd0703)。
文摘This paper proposes a self-tuning iterative learning control method for the attitude control of a flexible solar power satellite,which is simplified as an Euler-Bernoulli beam moving in space.An orbit-attitude-structure coupled dynamic model is established using absolute nodal coordinate formulation,and the attitude control is performed using two control moment gyros.In order to improve control accuracy of the classic proportional-derivative control method,a switched iterative learning control method is presented using the control moments of the previous periods as feedforward control moments.Although the iterative learning control is a model-free method,the parameters of the controller must be selected manually.This would be undesirable for complicated systems with multiple control parameters.Thus,a self-tuning method is proposed using fuzzy logic.The control frequency of the controller is adjusted according to the averaged control error in one control period.Simulation results show that the proposed controller increases the control accuracy greatly and reduces the influence of measurement noise.Moreover,the control frequency is automatically adjusted to a suitable value.
基金This work was supported by the National Natural Science Foundation of China(Grant Nos.11432010 and 11502040)the Fundamental Research Funds for the Central Universities of China(Grant No.DUT18GF304).
文摘To deal with the vibration problem of the solar power satellite(SPS),the distributed vibration control approach is investigated in this paper.Taking the Multi-Rotary joints SPS as the research objective,the control unit(CU)and the location relationship matrix are rstly de ned for distributed controller design according to the con guration of SPS.The dynamic model of each CU is therefore established based on the nite element method.The dynamic model of the whole SPS structure is then developed using the CU models,and is updated along with on-orbit assembly.The distributed cooperative controller,using proportional and di erential feedback and the interaction feedback among adjacent CUs,is proposed to suppress vibration.The close-loop distributed cooperative control system is then achieved by integrating all distributed controllers,and the asymptotic stability is proofed by the Lyapunov's stability theorem.To verify the feasibility of the proposed control system,three numerical cases are nally presented.The results demonstrate that the distributed cooperative controllers can e ectively suppress vibration during on-orbit assembly and operation after assembly,and the closed-loop system has good fault tolerance.
