Characteristic analysis and design of near moon abort trajectory for manned lunar landing mission

Huang, Wende; Xi, Xiaoning; Wang, Wei

doi:10.1007/s11431-010-4118-x

Cited by 10 publications

(5 citation statements)

References 2 publications

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“…Although the error is only about 6% of the flight distance in the earth centered phase, it is more than 30% of the radius of the lunar gravity influence zone in the moon centered phase. The precision of results will be very low if ignoring the influence of the moon's non-circular orbit [13]. To provide an accurate solution, the moon's position and velocity at any time are obtained by using ephemeris DE405 during the calculation employing the patched-conic method in this section.…”

Section: Initial Orbit Designmentioning

confidence: 99%

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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Section: Initial Orbit Designmentioning

confidence: 99%

Free return orbit design and characteristics analysis for manned lunar mission

Peng

Shen

2011

Sci. China Technol. Sci.

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“…Its difficulties come from the multiple celestial bodies' perturbation and strict constraints at the re-entry point. Lots of studies have been carried out on these problems: Huang et al [1] proposed an algorithm for the direct abort trajectory but the re-entry constraints are not considered. some studies [2][3] addressed the reentry constraint by iteratively adjusting the design variables.…”

Section: Introductionmentioning

confidence: 99%

Design and analysis of direct abort trajectory for a crewed lunar mission based on the quasi-lambert problem

Dong

Wang

Luo

et al. 2023

J. Phys.: Conf. Ser.

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A direct design method for direct abort trajectory based on the quasi-lambert problem is proposed. The re-entry constraint is analytically addressed via a quasi-lambert problem instead of variables iteration and optimization method in the past. Then a new parameter is introduced to determine the plane. The exact solution is determined by differential correction based on the initial solution. Numerical simulation is carried out to test the validity and efficiency of the method. The comparison with STK verifies its reliability. Additionally, the characteristics of direct abort trajectory and their application in the option strategy for different abort ways are studied. The flight time and abort point affect the abort trajectories’ velocity increment and the latitude of the landing area.

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“…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. Ocampo and Saudemont 25 established the initial value calculation model of the multi-impulse contingency return trajectory.…”

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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Characteristic analysis and design of near moon abort trajectory for manned lunar landing mission

Cited by 10 publications

References 2 publications

Free return orbit design and characteristics analysis for manned lunar mission

Free return orbit design and characteristics analysis for manned lunar mission

Design and analysis of direct abort trajectory for a crewed lunar mission based on the quasi-lambert problem

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

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