Fuel-Optimal Low-Thrust Trajectory Optimization Using Indirect Method and Successive Convex Programming

Tang, Gao; Jiang, Fanghua

doi:10.1109/taes.2018.2803558

Cited by 71 publications

(25 citation statements)

References 30 publications

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“…o R can be expressed as (12), as shown at the bottom of this page, where σ = [σ 1 σ 2 σ 3 ] T is the Modified Rodrigues Parameter (MRP) vector. MRP has the advantage in avoiding singularity [25], therefore it is adopted to depict the attitude of the spacecraft, and σ = σ .…”

Section: ) Equations Of Orbital Motionmentioning

confidence: 99%

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Trajectory Optimization for Asteroid Landing Considering Gravitational Orbit-Attitude Coupling

et al. 2019

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This paper proposes a trajectory optimization method considering gravitational orbit-attitude coupling (GOAC) for asteroid landing. First, by modeling the spacecraft as a rigid body rather than a point mass, and using the polyhedral method to describe the irregular gravitational field of the asteroid, GOAC is fully embedded into the 6 degree-of-freedom (DOF) dynamic model of the spacecraft. Second, attitude control, which is assumed to consume electric energy, is introduced into the optimization, the indirect method is adopted to formulate the 6-DOF fuel-optimal control problem, and the boundary conditions are modified to expand the search space of the problem. Third, a two-phase homotopic approach is proposed to realize a smooth continuation from the 6-DOF energy-optimal problem to the fuel-optimal problem. Finally, a numerical example is presented to demonstrate the feasibility of the proposed method, and the comparison results show that the obtained 6-DOF optimal trajectory can guarantee the fuel-optimality of the landing mission under GOAC. INDEX TERMS Asteroid, landing mission, orbit-attitude coupling, trajectory optimization.

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Section: ) Equations Of Orbital Motionmentioning

confidence: 99%

“…Various trajectory optimization methods have been proposed, e.g. direct method [9], indirect method [10], evolutionary algorithms [11], convex optimization [12], etc. Among them, the indirect method has its distinct advantages on high accuracy and guarantee of optimality [13].…”

Section: Introductionmentioning

confidence: 99%

Trajectory Optimization for Asteroid Landing Considering Gravitational Orbit-Attitude Coupling

et al. 2019

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“…With the development of low-thrust propulsion systems, 1–6 for the optimal trajectory design problem, the design variables gradually change from finite to infinite. 7,8 Low-thrust mission design 9–12 requires a method to approximate the trajectory and mission cost, which are very important.…”

Section: Introductionmentioning

confidence: 99%

Initial design of low-thrust trajectories based on the Bezier curve-based shaping approach

Fan

Huo

et al. 2020

Proceedings of the Institution of Mechanical Engineers, Part G:

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This paper presents a method to use the Bezier curve to rapidly generate three-dimensional low-thrust trajectories, which can provide a suitable initial approximation to be used for more accurate trajectory optimal control tools. Two missions, from Earth to Mars and the asteroid Dionysus, are considered to evaluate the performance of the method. In order to verify the advantages of this method, it is compared with the finite Fourier series method. Numerical results show that the Bezier method can get better performance index in shorter computation time compared with the finite Fourier series method. The applicability of the solution obtained by Bezier method is evaluated by introducing the obtained solution into the Gauss pseudospectral method as an initial guess. The simulation results show that the Bezier method can rapidly generate a very suitable three-dimensional initial trajectory for the optimal solver. This is very important for rapid evaluation of the feasibility of a large number of low-thrust flight schemes in the preliminary mission design stage.

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“…Considerable research has been conducted for short-duration trajectory optimization and the effectiveness of convex programming has been fully proved in comparison with traditional methods. For the transfer trajectory optimization of lowthrust spacecraft, Tang (Tang et al 2018) proposed a successive convex programming method and provided an accurate estimation of the initial costates of the indirect method. However, to the authors' best knowledge, there is no publication available in the literature that addresses the convex programming for the optimization of solar-sail interplanetary transfer trajectories.…”

Section: Introductionmentioning

confidence: 99%

Solar-sail deep space trajectory optimization using successive convex programming

Song

Gong

2019

Astrophys Space Sci

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This paper presents a novel methodology for solving the time-optimal trajectory optimization problem for interplanetary solar-sail missions using successive convex programming. Based on the non-convex problem, different convexification technologies, such as change of variables, successive linearization, trust regions and virtual control, are discussed to convert the original problem into the formulation of successive convex programming. Because of the free final-time, successive linearization is performed iteratively for the nonconvex terminal state constraints. After the convexification process, each of problems becomes a convex problem, which can be solved effectively. An augmented objective function is introduced to ensure the convergence performance and effectiveness of our algorithm. After that, algorithms are designed to solve the discrete sub-problems in a successive solution procedure. Finally, numerical results demonstrate the effectiveness and accuracy of our algorithms.

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Fuel-Optimal Low-Thrust Trajectory Optimization Using Indirect Method and Successive Convex Programming

Cited by 71 publications

References 30 publications

Trajectory Optimization for Asteroid Landing Considering Gravitational Orbit-Attitude Coupling

Trajectory Optimization for Asteroid Landing Considering Gravitational Orbit-Attitude Coupling

Initial design of low-thrust trajectories based on the Bezier curve-based shaping approach

Solar-sail deep space trajectory optimization using successive convex programming

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