Optimization of Multiple-Impulse, Multiple-Revolution, Rendezvous- Phasing Maneuvers

Luo, Yuling; Tang, Guojian; Lei, Yiyan; Li, Haiyang

doi:10.2514/1.25620

Cited by 53 publications

(20 citation statements)

References 8 publications

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“…studied the multiple impulsive fuel optimal orbit rendezvous problem under the linear [1] and nonlinear [2] dynamics, they directly applied the simplex, quadratic, genetic [3] and simulated annealing algorithms [4] to optimize the impulse vectors. Simulation results show that combining with the meta optimization method and the SQP method can effectively solve the problem [5]. Lawden, etc. proposed the principal vector theory to determine the trajectory optimal property [6] and added the coast stage or middle impulse to achieve the fuel optimal trajectory [7].…”

Section: Introductionmentioning

confidence: 90%

Revisiting the two-side optimization problem in satellite pursuit-evasion

Zhang

et al. 2017

MATEC Web Conf.

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Abstract. In the present paper two-side optimization problem where the intercepting satellite pursuits the target satellite was studied. In the pursuit-evasion game the continuous thruster and the simple central gravity with J2 perturbation were involved for two satellites. With applying the functional extremum condition, the optimal control outputs of both side satellites were obtained by building the systems Hamilton function. Further, the two side optimal problem was transformed to the TPBVP, which contributed the solution with the mixed numerical method. Finally, the proposed method was validated by the numerical simulation, where the optimal interception and escaping trajectories were illustrated.

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Section: Introductionmentioning

confidence: 90%

Revisiting the two-side optimization problem in satellite pursuit-evasion

Zhang

et al. 2017

MATEC Web Conf.

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“…If the value of J δ below zero, the additional impulse is increased to improve the orbit, and the greatest improvement in cost can be realized by applying the additional impulse at the time when primer magnitude reaches its maximum and in the direction of the maximum primer vector [2] . In the procedure of the optimization applying indirect approach, constraint of relative position at scheduled rendezvous point Q is handled by multiple-revolution Lambert homing algorithm [7] [8] . Genetic algorithm is adopted to solve the unconstraint optimization problem.…”

Section: Final and Initial Coastsmentioning

confidence: 99%

“…Where j X is the state of chaser spacecraft at j t satisfied (8) or (9). cf r is the position vector of chaser spacecraft at rendezvous time f t .…”

Section: B Optimal Schemementioning

confidence: 99%

Research on optimal strategy of fixed-time rendezvous

Liu

Yan

Zhou

et al. 2010

2010 3rd International Symposium on Systems and Control in Aeronautics and Astronautics

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Fuel optimization of fixed time hard rendezvous problem is studied. Optimal fuel is calculated by indirect and direct approaches respectively. The indirect approach is based on primer vector theory, and primer vector of transfer orbit is calculated and improved. A nonlinear optimization model is formulated for the problem of multiple-impulse rendezvous optimizing by direct approach, and the optimal number of impulses, their times and magnitude are obtained numerically. Finally, the optimal transfer strategy for studied type of rendezvous problem is put forward.

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“…Meanwhile, some researchers employed optimization algorithm for orbit design and obtained good results [10]. Following this research, a systematic study of optimization design of FRO is presented in this paper.…”

Section: Introductionmentioning

confidence: 98%

Free return orbit design and characteristics analysis for manned lunar mission

Peng

Shen

2011

Sci. China Technol. Sci.

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A circumlunar free return orbit design model that satisfies manned lunar mission constraints is established. By combining analytical method with numerical method, a serial orbit design strategy from initial value design to precision solution is proposed. A simulation example is given, and the conclusion indicates that the method has excellent convergence performance and precision. According to a great deal of simulation results solved by the method, the free return orbit characters such as accessible moon orbit parameters, return orbit parameters, transfer delta velocity, etc. are analyzed, which can supply references to constitute manned lunar mission orbit scheme. manned lunar mission, free return orbit, orbit design, orbit characters Citation:Peng Q B, Shen H X, Li H Y. Free return orbit design and characteristics analysis for manned lunar mission.

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Optimization of Multiple-Impulse, Multiple-Revolution, Rendezvous- Phasing Maneuvers

Cited by 53 publications

References 8 publications

Revisiting the two-side optimization problem in satellite pursuit-evasion

Revisiting the two-side optimization problem in satellite pursuit-evasion

Research on optimal strategy of fixed-time rendezvous

Free return orbit design and characteristics analysis for manned lunar mission

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