Optimal Multi-Objective Linearized Impulsive Rendezvous

Luo, Yuling; Tang, Guojian; Lei, Yiyan

doi:10.2514/1.21433

Cited by 88 publications

(49 citation statements)

References 20 publications

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“…Introduction C ONTROL of space vehicles for proximity operations, such as rendezvous and docking, is a problem of great interest for future manned missions [1], autonomous guidance of satellite swarms [2], onorbit servicing missions operated by free-flyer robotic spacecraft for refueling, monitoring or removing satellites [3][4][5], or for the autonomous onorbit assembly of a large space structure [6].…”

mentioning

confidence: 99%

Lyapunov-Based Thrusters' Selection for Spacecraft Control: Analysis and Experimentation

Curti

Romano

Bevilacqua

2010

Journal of Guidance, Control, and Dynamics

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This paper introduces a method for spacecraft rotation and translation control by on-off thrusters with guaranteed Lyapunov-stable tracking of linear dynamic models. In particular, the proposed control method switches on, at each time step, only those thrusters needed to maintain stability. Furthermore, the strategy allocates the configuration so that the minimum number of actuators is used. One of the benefits of the proposed method is that it substitutes both the thruster mapping and the pulse modulation algorithms typically used for real-time allocation of the firing thrusters and for determining the duration of the firing. The proposed approach reduces the computational burden of the onboard computer versus the use of classical thruster mapping algorithms, which typically involve iterative matrix operations. The paper presents analytical demonstrations, numerical simulations on a six-degree-offreedom spacecraft, and experimental tests on a hardware-in-the-loop three-degree-of-freedom spacecraft simulator floating over air pads on a flat floor. The method proves to be effective and easy to implement in real time.Received 21 September 2009; revision received 10 March 2010; accepted for publication 12 March 2010. This material is declared a work of the U.S. Government and is not subject to copyright protection in the United States. Copies of this paper may be made for personal or internal use, on condition that the copier pay the $10.00 per-copy fee to the Copyright Clearance Center, Inc., 222 Rosewood Drive, Danvers, MA 01923; include the code 0731-5090/10 and $10.00 in correspondence with the CCC.

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mentioning

confidence: 99%

Lyapunov-Based Thrusters' Selection for Spacecraft Control: Analysis and Experimentation

Curti

Romano

Bevilacqua

2010

Journal of Guidance, Control, and Dynamics

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“…C-W equations, derived by Clohessey and Wiltshire in 1960 [5], have been widely used to describe the linear relative motion between two neighboring spacecraft if the target orbit is approximately circular and the distance between them is much smaller than the orbit radius. For example, [13], [18] and [25] studied the optimal impulsive rendezvous problem based on C-W equations, and [17] utilized annealing algorithm to design orbital controllers for the rendezvous model depicted by C-W equations. In recent years, with the development of control theory, many advanced methods have been utilized to solve the rendezvous control problem.…”

Section: Introductionmentioning

confidence: 99%

Multi-Objective Robust $H_{\infty}$ Control of Spacecraft Rendezvous

Gao

Yang

Shi

2009

IEEE Trans. Contr. Syst. Technol.

200

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Based on the relative motion dynamic model illustrated by C-W equations, the problem of robust H 1 control for a class of spacecraft rendezvous systems is investigated, which contain parametric uncertainties, external disturbances and input constraints. An H 1 state-feedback controller is designed via a Lyapunov approach, which guarantees the closed-loop system to meet the multi-objective design requirements. The existence conditions for admissible controllers are formulated in the form of liner matrix inequalities (LMIs), and the controller design is cast into a convex optimization problem subject to LMI constraints. An illustrative example is provided to show the e¤ectiveness of the proposed control design method.

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“…The non-dominated sorting genetic algorithm (NSGA) is one of the common methods. However, the drawbacks are obvious, such as the high computational complexity of ) O MN , which resulted in better performance than NSGA [25,26]. This paper studied the multi-objective optimal trajectory planning of the operational robot based on NSGA-2.…”

Section: Multi-objective Optimal Trajectory Planning Algorithmmentioning

confidence: 99%

Optimal Trajectory Planning and Coordinated Tracking Control Method of Tethered Space Robot Based on Velocity Impulse

Huang

Meng

2014

International Journal of Advanced Robotic Systems

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The tethered space robot (TSR) is a new concept of space robot which consists of a robot platform, space tether and operation robot. This paper presents a multi-objective optimal trajectory planning and a coordinated tracking control scheme for TSR based on velocity impulse in the approaching phase. Both total velocity impulse and flight time are included in this optimization. The non-dominated sorting genetic algorithm is employed to obtain the optimal trajectory Pareto solution using the TSR dynamic model and optimal trajectory planning model. The coordinated tracking control scheme utilizes optimal velocity impulse. Furthermore, the PID controller is designed in order to compensate for the distance measurement errors. The PID control force is optimized and distributed to thrusters and the space tether using a simulated annealing algorithm. The attitude interferential torque of the space tether is compensated a using time-delay algorithm through reaction wheels. The simulation results show that the multi-objective optimal trajectory planning method can reveal the relationships among flight time, fuel consumption, planar view angle and velocity impulse number. This method can provide a series of optimal trajectory according to a number of special tasks. The coordinated control scheme can significantly save thruster fuel for tracking the optimal trajectory, restrain the attitude interferential torque produced by space tether and maintain the relative attitude stability of the operation robot.

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Optimal Multi-Objective Linearized Impulsive Rendezvous

Cited by 88 publications

References 20 publications

Lyapunov-Based Thrusters' Selection for Spacecraft Control: Analysis and Experimentation

Lyapunov-Based Thrusters' Selection for Spacecraft Control: Analysis and Experimentation

Multi-Objective Robust $H_{\infty}$ Control of Spacecraft Rendezvous

Optimal Trajectory Planning and Coordinated Tracking Control Method of Tethered Space Robot Based on Velocity Impulse

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