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| 1 | Improved differential geometric guidance commands for endoatmospheric interception of high-speed targets显示文摘Pure proportional navigation(PPN) is suitable for endoatmospheric interceptions,for its commanded acceleration is perpendicular to interceptor velocity.However,if the target is much faster than the interceptor,the homing performance of PPN will be degraded badly.True proportional navigation(TPN) does not have this problem,but its commanded acceleration is perpendicular to the line of sight(LOS),which is not suitable for endoatmospheric interceptions.The commanded acceleration of differential geometric guidance commands(DGGC) is perpendicular to the interceptor velocity,while the homing performance approximates the LOS referenced guidance laws(PPN series).Therefore,DGGC is suitable for endoatmospheric interception of high-speed targets.However,target maneuver information is essential for the construction of DGGC,and the guidance commands are complex and may be without robustness.Through the deep analysis of three-dimensional engagement,a new construction method of DGGC is proposed in this paper.The target maneuver information is not needed any more,and the robustness of DGGC is guaranteed,which makes the application of DGGC possible. | LI KeBo CHEN Lei TANG GuoJin | 2013 | Science China(Technological Sciences)2013，56，2： | 22 |
| 2 | Research on the strategy of angles-only relative navigation for autonomous rendezvous显示文摘This paper considers the problem of angles-only relative navigation for autonomous rendezvous. Methods for determining degree of observability (DOO) and latent range information of orbital maneuver are proposed for analyzing and enhancing the precision of relative position and velocity estimation. The equations of angles-only relative navigation are set forth on the condition that optical camera is the only viable sensor for relative measurement, and expressions for the DOO of relative navigation are obtained by using the Newton iterative method. The latent range information of orbital maneuver is analyzed, which is employed to enhance the DOO of angles-only relative navigation. Simulation result shows that DOO is effective to describe the observability level of relative position and velocity, and the latent range information is useful in enhancing the DOO of the angles-only relative navigation. | LI JiuRen LI HaiYang TANG GuoJin LUO YaZhong | 2011 | Science China(Technological Sciences)2011，54，7： | 13 |
| 3 | Survey of orbital dynamics and control of space rendezvous显示文摘Rendezvous orbital dynamics and control(RODC) is a key technology for operating space rendezvous and docking missions. This paper surveys the studies on RODC. Firstly,the basic relative dynamics equation set is introduced and its improved versions are evaluated. Secondly,studies on rendezvous trajectory optimization are commented from three aspects: the linear rendezvous,the nonlinear two-body rendezvous,and the perturbed and constrained rendezvous. Thirdly,studies on relative navigation are briefly reviewed,and then close-range control methods including automated control,manual control,and telecontrol are analyzed. Fourthly,advances in rendezvous trajectory safety and robust analysis are surveyed,and their applications in trajectory optimization are discussed. Finally,conclusions are drawn and prospects of studies on RODC are presented. | Luo Yazhong Zhang Jin Tang Guojin | 2014 | Chinese Journal of Aeronautics2014，27，1： | 13 |
| 4 | Algebraic solution of differential geometric guidance command and time delay control显示文摘According to the three-dimensional geometry of the engagement,the explicit algebraic expression of differential geometric guidance command(DGGC)is proposed.Compared with the existing solutions,the algebraic solution is much simpler and better for the further research of the characteristics of DGGC.Time delay control(TDC)is a useful method to tackle the uncertainty problem of a control system.Based on TDC,taking the target maneuvering acceleration as a disturbance,the estimation algorithm of the target maneuvering acceleration is presented,which can be introduced in DGGC to improve its performance.Then,the augmented DGGC(ADGGC)is obtained.The numerical simulation of intercepting a high maneuvering target is conducted to demonstrate the effectiveness of ADGGC. | LI KeBo CHEN Lei TANG GuoJin | 2015 | Science China(Technological Sciences)2015，58，3： | 13 |
| 5 | Motion Planning for Vibration Reducing of Free-floating Redundant Manipulators Based on Hybrid Optimization Approach显示文摘这份报纸涉及最佳的运动为颤动减少免费漂浮的灵活冗余的操纵者计划。第一,系统的动态模型基于 Lagrange 方法被建立,并且为颤动减少计划模型的运动被建议。第二,采用高斯 pseudospectral 方法(GPM ) 的一条混合优化途径和直接射击方法(DSM ) ,被建议解决计划的运动问题。在这条途径,计划问题的运动用 GPM 被转变成一个非线性的参数优化问题,并且基因算法(GA ) 被采用定位近似解决方案。随后,一个优化模型基于 DSM 被提出,并且顺序的二次的编程(SQP ) 算法被用来获得精确解决方案,与象一个起始的引用解决方案的近似解决方案。最后,几数字模拟被调查,并且灵活连接的全球颤动或剩余颤动被被混合优化途径获得的联合轨道显然减少。数字模拟结果显示途径对计划颤动减少的问题的运动有效、稳定。 | LIAO Yihuan LI Daokui TANG Guojin | 2011 | Chinese Journal of Aeronautics2011，24，4： | 8 |
| 6 | Hybrid planning for LEO long-duration multi-spacecraft rendezvous mission显示文摘For the low-earth-orbit(LEO) long-duration multi-spacecraft rendezvous mission,a mixed integer nonlinear programming(MINLP) model is built with consideration of the J2 perturbation and the time window constraints based on lighting condition.A two-level hybrid optimization approach is proposed.The up-level problem uses the visiting sequence,the orbital transfer duration and the service time after each rendezvous as design variables,and employs the mix-coded genetic algorithm to search the optimal solution;the low-level problem uses the maneuver time and impulses in each rendezvous as design vari-ables,and employs the downhill simplex method to search the optimal solution.To improve the solving efficiency of the low-level problem,a linear dynamic model with J2 perturbation is derived,and the approximate strategy of the low-level prob-lem is then proposed.The proposed method has been applied to several numerical problems.The results lead to three major conclusions:(1) The MINLP model for LEO long-duration multi-spacecraft rendezvous mission is effective,and the proposed hybrid optimization strategy can obtain good solutions that satisfy time window constraints;(2) The derived linear dynamic equations are good first-order approximation to the long-duration rendezvous trajectory under J2 perturbation;(3) Under J2 perturbation,the long-duration rendezvous problem has multiple local minimums either in the duration of multiple orbits or in a single orbit,and it agrees with the problem's characteristic to use the mix-coded genetic algorithm. | ZHANG Jin LUO YaZhong TANG GuoJin | 2012 | Science China(Technological Sciences)2012，55，1： | 8 |
| 7 | Optimal multi-objective trajectory design based on close-looped control for autonomous rendezvous显示文摘This paper considers the problem of optimal multi-objective trajectory design for autonomous rendezvous.Total velocity cost and relative state robustness of close-looped control are selected as the objective functions.Based on relative dynamics equations,the state equations and measurement equations for angles-only relative navigation between spacecrafts are set forth.According to the method of linear covariance analysis,the close-looped control covariance of the true relative state from the reference relative state is analyzed,and the objective functions of relative state robustness are formulated.Considering the total velocity cost and the relative state robustness,the multi-objective optimization algorithm of NSGA-II is employed to solve this multi-impulsive rendezvous problem.Lastly,the validity of the objective functions and the covariance results are demonstrated through 100 times Monte Carlo simulation. | LI JiuRen LI HaiYang TANG GuoJin | 2011 | Science China(Technological Sciences)2011，54，11： | 6 |
| 8 | A new approach for teleoperation rendezvous and docking with time delay显示文摘Teleoperation rendezvous and docking can be used as a backup for autonomous rendezvous and docking (RVD) for an unmanned spacecraft or for guiding the chaser docking with an uncooperative target.The inherent teleoperation time delay is a rigorous problem,especially when the chaser is teleoperated on the ground.To eliminate the effect of time delay,a new approach for teleoperation RVD is studied.The characteristics of teleoperation RVD are analyzed by comparisons with the teleoperation robot and with manually controlled RVD;the relative motion of the chaser is predicted based on the C-W equation;and the processed measure information with time delay through the Kalman filter is utilized to correct the current prediction.Experimental results verify that the approach produces an 18% enhanced success rate of teleoperation RVD compared with direct visual feedback,and consumes less time and fuel.The developed approach also solves the time delay problem effectively.Teleoperation RVD using this method can be applied as a useful backup for autonomous RVD. | ZHOU JianYong JIANG ZiCheng TANG GuoJin | 2012 | Science China(Physics,Mechanics & Astronomy)2012，55，2： | 6 |
| 9 | Planning for space station long-duration orbital mission under multi-constraints显示文摘An integrated nonlinear planning(NLP) model is built for space station long-duration orbital missions considering both the vehicle visiting schedules and the interaction effects between target phasing,vehicle return adjusting and Earth observation aiming.A two-level optimization approach is proposed to solve this complicated problem.The up-level problem employs the launch times of visiting vehicles as design variables,considers the constraints of crew rotations,resource resupplies and rendezvous launch windows,and is solved by a genetic algorithm.The low-level problems employ the maneuver impulses and burn times within each orbital mission as design variables,and a high-efficient shooting iteration method is proposed based on an analytical equation for the phase angle correction considering the J 2 perturbation.The results indicate that the integrated NLP model for space station long-duration orbital missions is effective,and the proposed optimization approach can obtain the optimal solutions that satisfy the multiple constraints and reduce the total propellant consumption. | LIN KunPeng LUO YaZhong ZHANG Jin TANG GuoJin | 2013 | Science China(Technological Sciences)2013，56，5： | 5 |
| 10 | Translational zero-disturbance curve and its application to zero-disturbance motion planning of space manipulator system显示文摘A new motion planning method is proposed for enlarging the solvable space of zero-disturbance motion planning for the space free-floating manipulator system. First, a class of translational zero-disturbance curves is put forward for the first time. The equation of translational zero-disturbance curve is deduced using the nonholonomic constraint of the manipulator system, and its characteristics are also discussed. Second, the zero-disturbance curve of the whole operating process is divided into two segments. The first one is a translational zero-disturbance curve which passes through the target point. Another one is a common zero-disturbance curve which passes through the original point and intersects with the translational zero-disturbance curve. Finally, the common zero-disturbance curve is obtained by a hybrid programming strategy based on Gauss pseudo-spectral method (GPM) and direct shooting method (DSM). The numerical simulation results indicate that the proposed method is effective, and that the solvable space of this method almost covers the whole work space of the manipulator system. | LIAO YiHuan LI DaoKui TANG GuoJin | 2011 | Science China(Technological Sciences)2011，54，5： | 4 |
| 11 | Human control model in teleoperation rendezvous显示文摘This paper proposes a human control model in teleoperation rendezvous on the basis of human information processing(perception, judgment, inference, decision and response). A predictive display model is introduced to provide the human operator with predictive information of relative motion. By use of this information, the longitudinal and lateral control models for the operator are presented based on phase plane control method and fuzzy control method, and human handling qualities are analyzed. The integration of these two models represents the human control model. Such a model can be used to simulate the control process of the human operator, which teleoperates the rendezvous with the aid of predictive display. Experiments with human in the loop are carried out based on the semi-Physical simulation system to verify this human control model. The results show that this human control model can emulate human operators' performance effectively,and provides an excellent way for the analysis, evaluation and design of the teleoperation rendezvous system. | ZHANG Bo LI HaiYang TANG GuoJin | 2014 | Science China(Information Sciences)2014，57，11： | 3 |
| 12 | Robust nonlinear control of spacecraft formation flying using constraint forces显示文摘A robust nonlinear control method is presented for spacecraft precise formation flying.With the constraint forces and consid-ering nonlinearity and perturbations,the problem of the formation keeping is changed to the Lagrange systems with the holonomic constraints and the differential algebraic equations (DAE).The nonlinear control laws are developed by solving the DAE.Because the traditional numerical solving methods of DAE are very sensitive to the various errors and the resulting con-trol laws are not robust in engineering application,the robust control law designed method is further developed by designing the correct coefficients to correct the errors of the formation array constraints.A numeral study simulated the robustness of this method for the various errors in the formation flying mission,including the initial errors of spacecraft formation,the reference satellite orbit determination errors,the relative perturbation forces model errors,and so on. | XING JianJun TANG GuoJin CHENG WenKe LEI YongJun | 2011 | Science China(Technological Sciences)2011，54，9： | 2 |
| 13 | Finite element method for viscoelastic medium with damage and the application to structural analysis of solid rocket motor grain显示文摘This paper studies the damage-viscoelastic behavior of composite solid propellants of solid rocket motors(SRM).Based on viscoelastic theories and strain equivalent hypothesis in damage mechanics,a three-dimensional(3-D)nonlinear viscoelastic constitutive model incorporating with damage is developed.The resulting viscoelastic constitutive equations are numerically discretized by integration algorithm,and a stress-updating method is presented by solving nonlinear equations according to the Newton-Raphson method.A material subroutine of stress-updating is made up and embedded into commercial code of Abaqus.The material subroutine is validated through typical examples.Our results indicate that the finite element results are in good agreement with the analytical ones and have high accuracy,and the suggested method and designed subroutine are efficient and can be further applied to damage-coupling structural analysis of practical SRM grain. | DENG Bin SHEN ZhiBin DUAN JingBo TANG GuoJin | 2014 | Science China(Physics,Mechanics & Astronomy)2014，57，5： | 2 |
| 14 | Nonlinear control of multiple spacecraft formation flying using the constraint forces in Lagrangian systems显示文摘Getting inspiration from the constraint forces in the classical mechanics, we presented the nonlinear control method of multiple spacecraft formation flying to accurately keep the desired formation arrays. Considering nonlinearity and perturbation, we changed the question of the formation array control to the Lagrange equations with the holonomic constraints and the differential algebraic equations (DAE), and developed the nonlinear control for design of the follower spacecraft tracking control laws by solving the DAE. Because of using the idea of the constraint forces, this approach can adequately utilize the characteristic of the dynamic equations, i.e., the space natural forces, and accurately keep the arbitrary formation array. Simulation results of the circular formation keeping with the linear and nonlinear dynamical equations were included to illuminate the control performance. | XING JianJun LEI YongJun CHENG WenKe TANG GuoJin | 2009 | Science China(Technological Sciences)2009，52，10： | 2 |
| 15 | Spacecraft optimal rendezvous controller design using simulated annealing显示文摘 | LUO Yazhong TANG Guojin | 2005 | Aerospace Science and Technology2005，9，8： | 1 |
| 16 | Optimization of multiple-impulse,multiple-revolution,rendezvous-phasing maneuvers显示文摘 | Luo Yazhong Tang Guojin Lei Yongjun | | 0，，04： | 1 |
| 17 | Optimal multi-objective linearized rendezous 显示文摘 | LUO Yazhong TANG Guojin LEI Yongjun | 2007 | Journal of Guidance Control and Dynamics2007，30，2： | 1 |
| 18 | Remarks on a benchmark nonlinear constrained optimization problem显示文摘Remarks on a benchmark nonlinear constrained optimization problem are made. Due to a citation error, two absolutely different results for the benchmark problem are obtained by independent researchers. Parallel simulated annealing using simplex method is employed in our study to solve the benchmark nonlinear constrained problem with mistaken formula and the best-known solution is obtained, whose optimality is testified by the Kuhn-Tucker conditions. | Luo Yazhong Lei Yongjun Tang Guojin | 2006 | Journal of Systems Engineering and Electronics2006，17，3： | 1 |
| 19 | Hybrid Approach to Optimize a Rendezvous Phasing Strategy 显示文摘 | Luo Yazhong Li Haiyang Tang Guojin | 2007 | Journal of Guidance Control and Dynamics2007，30，2： | 1 |
| 20 | Optimal Mnlti-Objective Linearized Impulsive Rendezvous显示文摘 | LuoYaZhong Tang GuoJin and Lei YongJun | 2007 | Journal of Guidance Control and Dynamics (S0731-5090)2007，30，2： | 1 |
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