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Tangent-impulse transfer from elliptic orbit to an excess velocity vector

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Chinese Journal of Aeronautics 2014年第3期27卷 577-583页

作者： Zhang Gang Zhang Xiangyu Cao Xibin Research center of satellite technology Harbin Institute of Technology National and Local United Engineering Research center of Small satellite technology

The two-body orbital transfer problem from an elliptic parking orbit to an excess veloc-ity vector with the tangent impulse is studied. The direction of the impulse is constrained to be aligned with the velocity vector, then speed changes are enough to nullify the relative velocity. First, if one tangent impulse is used, the transfer orbit is obtained by solving a single-variable function about the true anomaly of the initial orbit. For the initial circular orbit, the closed-form solution is derived. For the initial elliptic orbit, the discontinuous point is solved, then the initial true anomaly is obtained by a numerical iterative approach; moreover, an alternative method is proposed to avoid the singularity. There is only one solution for one-tangent-impulse escape trajectory. Then, based on the one-tangent-impulse solution, the minimum-energy multi-tangent-impulse escape trajectory is obtained by a numerical optimization algorithm, e.g., the genetic method. Finally, several examples are provided to validate the proposed method. The numerical results show that the minimum-energy multi-tangent-impulse escape trajectory is the same as the one-tangent-impulse trajectory.

关键词： Elliptic orbit Escape trajectory Excess velocity vector Orbital transfer Tangent impulse

Response regimes of narrow-band stochastic excited linear oscillator coupled to nonlinear energy sink

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Chinese Journal of Aeronautics 2015年第2期28卷 457-468页

作者： Xiong Huai Kong Xianren Yang Zhenguo Liu Yuan Research center of satellite technology Harbin Institute of Technology

This paper draws attention to the issue of the vibration absorption of nonlinear mechani- cal system coupled to nonlinear energy sink （NES） under the impact of the narrow band stochastic excitation. Firstly, based on the complex-averaging method and frequency detuning methodology, response regimes of oscillators have been researched under the linear impact of coupling a nonlinear attachment with less relativistic mass and an external sinusoidal forcing, of which results turn out that the quasi-periodicity response regime of system which occurs when the external excitation amplitude exceeds the critical values will be the precondition of the targeted energy transfer. Secondly, basing on the path integration method, vibration suppression of NES has been researched when it is affected by a main oscillator with a narrow band stochastic force in the form of trigono- metric functions, of which results show that response regimes are affected by the amplitude of stochastic excitation and the disturbance strength. Finally, all these conclusions have been approved by the numerical verification and coincided with the theoretical analysis; meanwhile, after the com- paring analysis with the optimal linear absorber, it turns out that the NES which is affected by the narrow band stochastic force could also suppress the vibration of system with a better effect.

关键词： Nonlinear energy sink Path integration method Stochastic excitation Targeted energy transfer Vibration absorption

Super twisting controller for on-orbit servicing to non-cooperative target

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Chinese Journal of Aeronautics 2015年第1期28卷 285-293页

作者： Chen Binglong Geng Yunhai Research center of satellite technology Harbin Institute of Technology

A relative position and attitude coupled controller is proposed for rendezvous and docking between two docking ports located in different spacecraft. It is concerned with servicing to a tumbling non-cooperative target spacecraft in arbitrary orbit subjected to external *** considering both kinematic and dynamical coupled effects of relative rotation on relative translation, a coupled dynamic model is established to represent the relative motion of docking port on target spacecraft with respect to another on the service spacecraft. The spacecraft control is based on the second order sliding mode algorithm of super twisting（ST）. It is schemed to manipulate the relative position and attitude synchronously. A formal proof of the finite time convergence property of the closed-loop system is derived theoretically by the second method of Lyapunov. Numerical simulations with the designed ST controller are presented to validate the analytic analysis by contrast with the twisting control algorithm. Simulation results demonstrate that the proposed relative position and attitude integrated controller is characterized by high precision, strong robustness and high reliability.

关键词： spacecraft orbit cooperative attitude robustness kinematic sliding dynamical rotation concerned

Modified super twisting controller for servicing to uncontrolled spacecraft

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Journal of Systems Engineering and Electronics 2015年第2期26卷 334-345页

作者： Binglong Chen Yunhai Geng Research center of satellite technology Harbin Institute of Technology

A relative position and attitude coupled sliding mode controller is proposed by combining the standard super twisting （ST） control and basic linear algorithm for autonomous rendezvous and docking. It is schemed for on-orbit servicing to a tumbling non- cooperative target spacecraft subjected to external disturbances. A coupled dynamic model is established including both kinemati- cal and dynamic coupled effect of relative rotation on relative translation, which illustrates the relative movement between the docking port located in target spacecraft and another in service spacecraft. The modified super twisting （MST） control algorithm containing linear compensation items is schemed to manipulate the relative position and attitude synchronously. The correction provides more robustness and convergence velocity for dealing with linearly growing perturbations than the ST control algorithm. Moreover, the stability characteristic of closed-loop system is ana- lyzed by Lyapunov method. Numerical simulations are adopted to verify the analysis with the comparison between MST and ST control algorithms. Simulation results demonstrate that the pro- posed MST controller is characterized by high precision, strong robustness and fast convergence velocity to attenuate the linearly increasing perturbations.

关键词： autonomous rendezvous and docking coupled dynamic model modified super twisting Lyapunov method

Integrated modeling of spacecraft relative motion dynamics using dual quaternion

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Journal of Systems Engineering and Electronics 2018年第2期29卷 367-377页

作者： PENG Xuan SHI Xiaoping GONG Yupeng Control and Simulation center Harbin Institute of Technology Research center of satellite technology Harbin Institute of Technology

To realize high accurate control of relative position and attitude between two spacecrafts, the coupling between position and attitude must be fully considered and a more precise model should be established. This paper breaks the traditional divide and conquer idea, and uses a mathematical tool, namely dual quaternion to establish the integrated 6 degree-of-freedom(6-DOF) model of relative position and attitude, which describes the coupled relative motion in a compact and efficient form and needs less information of the target. Considering the complex operation rules and the unclarity of the current relative motion model in dual quaternion, necessary mathematical foundations are given at first, followed by clear and detailed modeling process and analysis. Finally a generalized proportion-derivative(PD) controller law is designed. The simulation results show that based on the integrated model established by dual quaternion, this control law can achieve a high control accuracy of relative motion.

关键词： relative motion dual quaternion position and attitude coupling integrated modeling

Singularity radius gradient-based rapid singularity-escape steering law for SGCMGs

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Chinese Journal of Aeronautics 2020年第10期33卷 2728-2742页

作者： Tao YI Yunhai GENG Baolin WU Research center of satellite technology Harbin Institute of TechnologyHarbin 150080China

In order to visualize singularity of SGCMGs in gimbal angle space,a novel continuous bounded singularity parameter--Singularity Radius,whose sign can distinctly determine singularity type,is *** a rapid singularity-escape steering law is proposed basing on gradient of Singularity Radius and residual base vector to drive the SGCMG system to neighboring singular boundary,and quickly escape elliptic ***,simulation results on Pyramid-type and skew-type configuration demonstrate the effectiveness and rapidness of the proposed steering law.

关键词： Gaussian curvature Rapid singularity escape Single gimbal control moment gyroscope Singularity-escape steering law Singularity parameter Singularity type

Fast calculation method for mission opportunities in orbital interception and rendezvous problems

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Chinese Journal of Aeronautics 2023年第6期36卷 201-212页

作者： Huidong MA Gang ZHANG Research center of satellite technology Harbin Institute of TechnologyHarbin 150080China

This paper proposes a fast calculation method to solve all mission opportunities for orbital interception and orbital rendezvous under the impulse-magnitude *** from the existing search methods,the proposed method does not need to solve Lambert's problem in the whole *** cases are considered for either departure time or transfer time being free,or both being *** fixed departure time,the feasible windows of transfer time are obtained by solving a single-variable nonlinear equation only of terminal true ***,for fixed interception(or rendezvous)time,the feasible windows of departure time are *** free departure time and free transfer time,all mission opportunities are obtained by using a onedimensional search *** hyperbolic-transfer and the multiple-revolution cases are also *** results show that the proposed method is superior to the typical pork-chop plot method and the two-dimensional launch window method in computational time.

关键词： Mission opportunity Impulse-magnitude constraint Orbital interception Orbital rendezvous Pork-chop plot

Concurrent multi-task pre-processing method for LEO mega-constellation based on dynamic spatio-temporal grids

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Chinese Journal of Aeronautics 2023年第11期36卷 233-248页

作者： Xibin CAO Ning LI Shi QIU Research center of satellite technology Harbin Institute of TechnologyHarbin 150080China

The Low Earth Orbit(LEO)remote sensing satellite mega-constellation has the characteristics of large quantity and various types which make it have unique superiority in the realization of concurrent multiple ***,the complexity of resource allocation is increased because of the large number of tasks and ***,the primary problem of implementing concurrent multiple tasks via LEO mega-constellation is to pre-process tasks and observation *** address the challenge,we propose a pre-processing algorithm for the mega-constellation based on highly Dynamic Spatio-Temporal Grids(DSTG).In the first stage,this paper describes the management model of mega-constellation and the multiple ***,the coding method of DSTG is proposed,based on which the description of complex mega-constellation observation resources is *** the third part,the DSTG algorithm is used to realize the processing of concurrent multiple tasks at multiple levels,such as task space attribute,time attribute and grid task importance ***,the simulation result of the proposed method in the case of constellation has been given to verify the effectiveness of concurrent multi-task pre-processing based on *** autonomous processing process of task decomposition and task fusion and mapping to grids,and the convenient indexing process of time window are verified.

关键词： LEO mega-constellation Concurrent multiple tasks Tasks pre-processing Highly dynamic spatiotemporal grids Multi-task fusion merging Importance evaluation

Robust image-based coordinated control for spacecraft formation flying

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Chinese Journal of Aeronautics 2022年第9期35卷 268-281页

作者： Dayong HU Xiangtian ZHAO Shijie ZHANG Research center of satellite technology Harbin Institute of TechnologyHarbin 150080China

This paper addresses a coordinated control problem for Spacecraft Formation Flying(SFF). The distributed followers are required to track and synchronize with the leader *** using the feature points in the two-dimensional image space, an integrated 6-degree-of-freedom dynamic model is formulated for spacecraft relative motion. Without sophisticated threedimensional reconstruction, image features are directly utilized for the controller design. The proposed image-based controller can drive the follower spacecraft in the desired configuration with respect to the leader when the real-time captured images match their reference counterparts. To improve the precision of the formation configuration, the proposed controller employs a coordinated term to reduce the relative distance errors between followers. The uncertainties in the system dynamics are handled by integrating the adaptive technique into the controller, which increases the robustness of the SFF system. The closed-loop system stability is analyzed using the Lyapunov method and algebraic graph theory. A numerical simulation for a given SFF scenario is performed to evaluate the performance of the controller.

关键词： Algebraic graph theory Coordinated control Image-based visual servoing Robust control Spacecraft formation flying