Free return orbit design and characteristics analysis for manned lunar mission

Peng, Qibo; Shen, Hong-Xin; Li, Haiyang

doi:10.1007/s11431-011-4622-7

Cited by 18 publications

(11 citation statements)

References 5 publications

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“…In contrast, if the probe enters above the upper boundary (overshoot), then it may skip off the atmosphere and fly back into space [24]. Actually, h en can be up to 122 km with flight path angle from − 5°to − 10°for the Earth re-entry mission [15]; however, current work assumed 122 km and − 6°as a baseline throughout the simulation, except for the extended analysis shown in Sect. 4.3.…”

Section: Simulation Setup and Assumptionsmentioning

confidence: 99%

“…For example, Huang et al analyzed a near-Moon abort trajectory to prepare for potential mission failure [14]. Peng et al studied the optimal free Earth-Moon-Earth return orbit design [15]. Li et al determined M-E trajectories using an analytical method using the double two-body model [13], whereas Feng and Zhang have designed the lunar south-pole return trajectory using the improved multi-conic patched method [16].…”

Section: Introductionmentioning

confidence: 99%

“…The three-step approach is proposed and adapted to optimize the given problem to serve as a useful tool to generate trajectory in real-world mission preparation or further to be adopted in real-flight operations. Usually, the double two-body model [19] is adopted as the basic dynamic model, and the analytic method [5,6] is used to design and analyze the lunar return trajectory [3,7,15]. Additionally, most of the previous return trajectory analyses focused on investigating the M-E transfer trajectory expressed in an Earth-centered frame, rather than the characteristics of the lunar parking orbit expressed in a Moon-centered frame.…”

Section: Introductionmentioning

confidence: 99%

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Optimal Lunar Point Return Orbit Design and Analysis via a Numerical Three-Step Approach

Song

Kim

et al. 2020

Int. J. Aeronaut. Space Sci.

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Herein, the characteristics of the Moon-to-Earth (M-E) trajectory satisfying the point return orbit (PRO) conditions are analyzed and optimized. A numerical three-step approach is proposed to serve as a useful tool to generate trajectory while preparing for real-world missions. To formulate the given problem, each step properly adapts different equations of motion with design parameters suitable to each step's primary objective. Three-and N-body equations of motion are used as a basis, and PRO is constrained by the parking orbit at the Moon and Earth re-entry corridor associated with the re-entry position. Consequently, the major trans-Earth-injection (TEI) maneuver condition at the Moon is optimized together with the right ascension of the ascending node and the argument of the latitude. Moreover, the TEI maneuver magnitude with its execution date and required time of flight is optimized to form PRO. Adopting this three-step approach, the effect of the Moon's relative motion with respect to the Earth to form the optimal TEI condition is clearly analyzed. In addition, direct insight on the TEI condition is obtained by expressing the ME rotating frame, which is expected to save time and effort while generating initial guesses for TEI conditions.

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Section: Simulation Setup and Assumptionsmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

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Optimal Lunar Point Return Orbit Design and Analysis via a Numerical Three-Step Approach

Song

Kim

et al. 2020

Int. J. Aeronaut. Space Sci.

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“…The method is based on solving a series of subproblems designed to minimize a quadratic model of the objective subject to a linearization of the constraints. 13,14) It is widely used to solve the NLP, 15) and the interested readers can consult the bibliography for references to the principles of SQP.…”

Section: Initial Values Solution With Gpmmentioning

confidence: 99%

Hybrid Optimization of Powered Descent Trajectory for Manned Lunar Mission

Peng

Shen

et al. 2013

Trans. Japan Soc. Aero. S Sci.

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The lunar landing stage can be divided into three phases: de-orbit, powered descent and terminal approach. Most fuel is consumed during the powered descent phase. Therefore, the optimization problem of minimum energy is typically focused on this phase. In this paper, a highly precise three-dimensional descent dynamics model is derived, and the main constraints for a manned lunar mission are presented. To solve this complex optimization problem with strict constraints, a hybrid optimization method which combines the collocation method-Gauss pseudospectral method (GPM) and shooting method is proposed. In this approach the GPM is used to provide an initial guess for the shooting method, which is then used to obtain the final optimal solution. The simulation results show that the proposed method can solve the lunar powered descent optimization problem effectively with the solution obtained satisfying all the input constraints and having high precision.

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“…Luo et al 16) discussed a double lunar swing-by trajectory. Peng et al 17) proposed a serial strategy using particle swarm optimization (PSO) and D2BPCM to get an initial value, then using of sequential quadratic programming (SQP) and high-precision dynamic modeling to further optimize the circumlunar free-return parameter. Luo et al 18) devised a method based on the pseudo-state theory and extended differential-correction method.…”

Section: Introductionmentioning

confidence: 99%

Solution Domain Analysis of Earth-Moon Quasi-Symmetric Free-Return Orbits

Zhou

2017

Trans. Japan Soc. Aero. S Sci.

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The solution domain of the Earth-Moon quasi-symmetric free-return orbits (EMQSFRO) is analyzed using a novel strategy proposed in this paper applying the Jet Propulsion Laboratory (JPL) ephemeris dynamic model. EMQSFRO is constrained by altitude at the time of trans-lunar injection (TLI), lunar swing-by altitude and Earth atmosphere re-entry angle. A vehicle on such an orbit can return to Earth without need of additional impulse after TLI. The present research on EMQSFRO and its technical applications are first summarized. Then a novel direct design strategy for EMQSFRO is proposed using a sequential quadratic programming algorithm, which applies the orbital parameters in the Moon perilune inertial coordinate system as design variables, and computes the objective orbital parameters in the TLI and re-entry time using the forward and backward numerical integral method. A simulation example indicates that the method has excellent convergence performance and precision. According to further simulation results, the solution domain cross-profile characteristics of four kinds of the EMQSFRO are discovered, which can give a deeper insight into the dynamic principle of EMQSFRO generation and supply references to the orbit design of aerospace missions.

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Free return orbit design and characteristics analysis for manned lunar mission

Cited by 18 publications

References 5 publications

Optimal Lunar Point Return Orbit Design and Analysis via a Numerical Three-Step Approach

Optimal Lunar Point Return Orbit Design and Analysis via a Numerical Three-Step Approach

Hybrid Optimization of Powered Descent Trajectory for Manned Lunar Mission

Solution Domain Analysis of Earth-Moon Quasi-Symmetric Free-Return Orbits

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