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Earth-moon Trajectory Optimization Using solar electric propulsion

Chinese Journal of Aeronautics 2007年第5期20卷 452-463页

作者： Gao Yang Academy of Opto-Electronics Chinese Academy of Sciences Beijing 100080 China

The optimization of the Earth-moon trajectory using solar electric propulsion is presented. A feasible method is proposed to optimize the transfer trajectory starting from a low Earth circular orbit （500 km altitude） to a low lunar circular orbit （200 km altitude）. Due to the use of low-thrust solar electric propulsion, the entire transfer trajectory consists of hundreds or even thousands of orbital revolutions around the Earth and the moon. The Earth-orbit ascending （from low Earth orbit to high Earth orbit） and lunar descending （from high lunar orbit to low lunar orbit） trajectories in the presence of J2 perturbations and shadowing effect are computed by an analytic orbital averaging technique. A direct/indirect method is used to optimize the control steering for the trans-lunar trajectory segment, a segment from a high Earth orbit to a high lunar orbit, with a fixed thrust-coast-thrust engine sequence. For the trans-lunar trajectory segment, the equations of motion are expressed in the inertial coordinates about the Earth and the moon using a set of nonsingular equinoctial elements inclusive of the gravitational forces of the sun, the Earth, and the moon. By way of the analytic orbital averaging technique and the direct/indirect method, the Earth-moon transfer problem is converted to a parameter optimization problem, and the entire transfer trajectory is formulated and optimized in the form of a single nonlinear optimization problem with a small number of variables and constraints. Finally, an example of an Earth-moon transfer trajectory using solar electric propulsion is demonstrated.

关键词： trajectory optimization solar electric propulsion analytic orbital averaging technique direct/indirect method

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Fuel-optimal trajectory design using solar electric propulsion under power constraints and performance degradation

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Science China(Physics,Mechanics & Astronomy) 2014年第6期57卷 1090-1097页

作者： ZHANG Peng LI JunFeng GONG ShengPing School of Aerospace Tsinghua University Science and Technology on Aerospace Flight Dynamic Laboratory Beijing Aerospace Control Center

The fuel-optimal transfer trajectories using solar electric propulsion are designed considering the power constraints and solar array performance *** different performance degradation models including linear,positive and negative exponential degradations are used in the analysis of three typical rendezvous missions including Apophis,Venus and Ceres,*** optimal control problem is formulated using the calculus of variations and Pontryagin’s maximum principle,which leads to a bang-bang control that is solved by indirect method combined with a homotopic *** demonstrating the effects of the power constraints and solar array performance degradation on the power budget and fuel consumption,the time histories of the power profile and the fuel consumptions are compared for the three *** study indicates that it is necessary to consider the power constraints and solar array performance degradation for the SEP-based low-thrust trajectory design,espacially for long-duration outbound flights.

关键词： fuel-optimal trajectory solar electric propulsion power constraints performance degradation

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Trajectory design for a solar-sail mission to asteroid 2016 HO_(3)

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Astrodynamics 2019年第3期3卷 231-246页

作者： Jeannette Heiligers Juan M.Fernandez Olive R.Stohlman W.Keats Wilkie Faculty of Aerospace Engineering Delft University of TechnologyKluyverweg 12629 HSDelftthe Netherlands Structural Dynamics Branch Langley Research CenterNational Aeronautics and Space AdministrationHamptonVirginia23681-2199USA

This paper proposes the use of solar-sail technology currently under development at NASA Langley Research Center for a CubeSat rendezvous mission with asteroid 2016 HO_(3),a quasi-satellite of ***-optimal trajectories are sought for within a 2022–202_(3) launch window,starting from an assumed launcher ejection condition in the Earth-Moon *** optimal control problem is solved through a particular implementation of a direct pseudo-spectral method for which initial guesses are generated through a relatively simple and straightforward genetic algorithm search on the optimal launch date and sail *** results show that the trajectories take 2.16–4.21 years to complete,depending on the assumed solar-sail reflectance model and solar-sail *** assess the performance of solar-sail propulsion for this mission,the trajectory is also designed assuming the use of solar electric *** resulting fuel-optimal trajectories take longer to complete than the solar-sail trajectories and require a propellant consumption that exceeds the expected propellant capacity onboard the *** comparison demonstrates the superior performance of solar-sail technology for this mission.

关键词： asteroid 2016 HO_(3) solar sail solar electric propulsion trajectory design trajectory optimization

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