Low-thrust trajectory optimization of asteroid sample return mission with multiple revolutions and moon gravity assists

Tang, Gao; Jiang, FanHuag; Li, Junfeng

doi:10.1007/s11433-015-5699-y

Sci. China Phys. Mech. Astron.

2015

DOI: 10.1007/s11433-015-5699-y

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Low-thrust trajectory optimization of asteroid sample return mission with multiple revolutions and moon gravity assists

Gao Tang

FanHuag Jiang

Junfeng Li

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Cited by 10 publications

(1 citation statement)

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“…For initial analysis, it is a common practice to consider simplified models for SEP systems. A single engine is assumed to operate at effective constant specific impulse and efficiency values [26,27,28,29,30]. However, the actual performance of SEP systems depends on the input power, which has to be taken into consideration for obtaining more realistic trajectories [31,32,33,34,35,36,37,38,39,40].…”

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confidence: 99%

A novel approach for optimal trajectory design with multiple operation modes of propulsion system, part 2

et al. 2020

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Equipping a spacecraft with multiple solar-powered electric engines (of the same or different types) compounds the task of optimal trajectory design due to presence of both real-valued inputs (power input to each engine in addition to the direction of thrust vector) and discrete variables (number of active engines).Each engine can be switched on/off independently and "optimal" operating power of each engine depends on the available solar power, which depends on the distance from the Sun. Application of the Composite Smooth Control (CSC) framework to a heliocentric fuel-optimal trajectory optimization from the Earth to the comet 67P/Churyumov-Gerasimenko is demonstrated, which presents a new approach to deal with multiple-engine problems. Operation of engine clusters with 4, 6, 10 and even 20 engines of the same type can be optimized.Moreover, engine clusters with different/mixed electric engines are considered with either 2, 3 or 4 different types of engines. Remarkably, the CSC framework allows us 1) to reduce the original multi-point boundary-value problem to a two-point boundary-value problem (TPBVP), and 2) to solve the resulting TP-BVPs using a single-shooting solution scheme and with a random initialization of the missing costates. While the approach we present is a continuous neighbor of the discontinuous extremals, we show that the discontinuous necessary conditions are satisfied in the asymptotic limit. We believe this is the first indirect method to accommodate a multi-mode control of this level of complexity with realistic engine performance curves. The results are interesting and promising for dealing with a large family of such challenging multi-mode optimal control problems.

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A novel approach for optimal trajectory design with multiple operation modes of propulsion system, part 2

et al. 2020

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Homotopy method for optimization of variable-specific-impulse low-thrust trajectories

Chi

Yang

Chen

et al. 2017

Astrophys Space Sci

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An identifier-actor-optimizer policy learning architecture for optimal control of continuous-time nonlinear systems

Cheng

Wang

2020

Sci. China Phys. Mech. Astron.

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Low-thrust trajectory optimization of asteroid sample return mission with multiple revolutions and moon gravity assists

Cited by 10 publications

References 35 publications

A novel approach for optimal trajectory design with multiple operation modes of propulsion system, part 2

A novel approach for optimal trajectory design with multiple operation modes of propulsion system, part 2

Homotopy method for optimization of variable-specific-impulse low-thrust trajectories

An identifier-actor-optimizer policy learning architecture for optimal control of continuous-time nonlinear systems

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