Indirect Optimization of Three-Dimensional Multiple-Impulse Moon-to-Earth Transfers

Shen, Hong Xin; Casalino, Lorenzo

doi:10.1007/s40295-014-0018-9

Cited by 23 publications

(5 citation statements)

References 29 publications

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“…17. This characteristic is consistent with the conclusion obtained by the indirect method in [33]. As observed in Fig.…”

Section: ) Velocity Increment Characteristicsupporting

confidence: 93%

“…It can be concluded that when the direction of the connection between the ascending node and the descending node of LPO is nearly vertical to the direction of the moon-Earth connection, the impulse consumption is small and can be selected as the optimal departure position, while the impulse consumption is large when the direction of the connection between the ascending node and the descending node of LPO is close to the direction of the Moon-Earth connection. The above variation rule is consistent with the results obtained by the indirect method in [33], but the impulse consumption is relatively large due to the consideration of the constraint of the landing site in this paper. In addition, the result of numerical optimization is compared with that of the preliminary analysis using the convenient method described in Sect.…”

Section: ) Velocity Increment Characteristicsupporting

confidence: 89%

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Three-Impulse Return Orbit Design and Characteristic Analysis for Manned Lunar Missions

2020

IEEE Access

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Return orbit design and characteristic analysis are very important issues in manned lunar missions. In this paper, a three-impulse return orbit scheme is studied. First, a convenient method based on the conical surface of the hyperbolic excess velocity is proposed, which can effectively perform an approximate analysis of the velocity increment characteristic. Second, a serial orbit design strategy is presented to determine the entire return orbit from the lunar parking orbit to the intended landing site. In the initial design, a three-segment orbit patched method based on the pseudo-perilune parameters is applied. Backward and forward calculations are conducted in the hybrid orbit model and the patched-conic model respectively, with the perilune of the lunar escape orbit as the dividing point. In the accurate design, a twosegment orbit patched method is employed in the high-fidelity model. Finally, numerical simulations are used to verify the effectiveness and feasibility of the orbit design strategy. According to many simulation results achieved by this strategy, the characteristics of fixed-point return window and velocity increment are further analyzed.INDEX TERMS Manned lunar mission, return orbit, conical surface of the hyperbolic excess velocity, pseudo-perilune parameters, orbit characteristic analysis.

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“…17. This characteristic is consistent with the conclusion obtained by the indirect method in [33]. As observed in Fig.…”

Section: ) Velocity Increment Characteristicsupporting

confidence: 93%

Section: ) Velocity Increment Characteristicsupporting

confidence: 89%

Three-Impulse Return Orbit Design and Characteristic Analysis for Manned Lunar Missions

2020

IEEE Access

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show abstract

“…Shen and Casalino adopted the indirect method to determine a contingency return trajectory during the lunar parking stage (Shen and Casalino 2014). Peng et al proposed the calculation model of lunar descending trajectory considering contingency constraints, and presented a design algorithm on the basis of Gauss pseudo-spectral method (Peng et al 2010).…”

Section: Introductionmentioning

confidence: 99%

Investigation on reachable domain of contingency return trajectories in the circumlunar flight phase based on interval analysis

Zhou²,

et al. 2022

Preprint

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The investigation on reachable domain based on interval analysis is performed, which is aimed for the contingency return trajectories during the circumlunar flight stage for manned lunar landing engineering. First, the issue of contingency return trajectory which adopts a non-coplanar maneuver during the circumlunar flight phase is described. The mathematics model of the reachable domain of contingency return trajectories is established. Second, the contingency return trajectory is designed. An improved interval branch and bound algorithm is introduced and a reachable domain calculation method of the contingency return trajectories is proposed. Third, in numerical simulations, by comparing the reachable domain obtained by the traditional brute force method, the accuracy of the method presented in this paper is verified. It also indicates that this method has a higher calculation efficiency. Finally, abundant simulations are performed to discuss the parameter characteristic of reachable domain by adopting this method. The study conclusions can serve as an important reference for the selection and decision of contingency return trajectory plans in the future manned lunar landing engineering.

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“…Peng et al 21 established a lunar landing trajectory calculation model considering contingency constraint conditions and presented an optimization design algorithm based on the Gauss pseudospectral method. Shen and Casalino 22 designed the contingency return trajectory in the circumlunar flight phase by using the indirect method. Huang et al 23,24 analyzed the characteristics of the contingency return trajectory in the near-Earth phase and near-Moon phase by adopting the two-body trajectory calculation model.…”

Section: Introductionmentioning

confidence: 99%

Design of contingency point return trajectory in the lunar orbit insertion phase for crewed lunar exploration missions

Zhou²,

et al. 2022

Proceedings of the Institution of Mechanical Engineers, Part G:

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To satisfy the requirement of contingency rescue in the lunar orbit insertion phase for crewed lunar exploration missions, this paper designs the contingency point return trajectory. First, according to different failure situations of the main propulsion system in the lunar orbit insertion phase, different types of contingency return modes are analyzed and summarized. Second, considering the terminal constraints of point return, a calculation model of the contingency point return trajectory is established, and a serial optimization process is adopted to obtain a high-fidelity solution. Finally, a numerical simulation is used to verify the model. The simulation results indicate that this model can be applied to determine the contingency point return trajectories under different situations in the lunar orbit insertion phase and demonstrate the validity and feasibility of the trajectory calculation model proposed in this paper. The research conclusions can provide a reference for the design of contingency rescue schemes in the lunar orbit insertion phase for crewed lunar exploration missions.

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Indirect Optimization of Three-Dimensional Multiple-Impulse Moon-to-Earth Transfers

Cited by 23 publications

References 29 publications

Three-Impulse Return Orbit Design and Characteristic Analysis for Manned Lunar Missions

Three-Impulse Return Orbit Design and Characteristic Analysis for Manned Lunar Missions

Investigation on reachable domain of contingency return trajectories in the circumlunar flight phase based on interval analysis

Design of contingency point return trajectory in the lunar orbit insertion phase for crewed lunar exploration missions

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