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Small celestial body attachment detection descending trajectory optimization method

A trajectory optimization, small celestial body technology, applied in the field of aerospace, can solve problems such as poor efficiency of gravitational acceleration, difficulty in estimating and solving initial co-state values, etc., to avoid complex derivation, simple derivation steps, and high computational efficiency.

Active Publication Date: 2017-05-31
BEIJING INSTITUTE OF TECHNOLOGYGY
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Problems solved by technology

[0005] The purpose of the present invention is to solve the problem that the existing small celestial body attachment detection descent trajectory optimization method is poor in efficiency due to the use of a polyhedral gravitational field model; Provide a small celestial body attachment detection descent trajectory optimization method

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  • Small celestial body attachment detection descending trajectory optimization method
  • Small celestial body attachment detection descending trajectory optimization method
  • Small celestial body attachment detection descending trajectory optimization method

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Embodiment 1

[0054] A method for optimizing the descent trajectory of small celestial body attachment detection, comprising the following steps:

[0055] Step 1. Estimate the spherical harmonic coefficients of the inner spherical harmonic gravitational field model by the least square method:

[0056] The inner Brillouin sphere is constructed outside the small celestial body, and the constructed inner Brillouin sphere should be tangent to the target landing point on the surface of the small celestial body, and the center of the sphere should be selected to ensure that the landing trajectory of the lander is included in the inner Brillouin sphere. Take N arbitrarily inside the Nebrillouin sphere data points, N calculated by the polyhedron model data point gravitational acceleration, and construct 3N from the gravitational acceleration data ×1-dimensional matrix The spherical harmonic coefficients of the inner spherical harmonic gravity model are calculated by the least square method.

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Abstract

The invention relates to a small celestial body attachment detection descending trajectory optimization method, and belongs to the field of aviation and aerospace. According to the method, an internal spherical harmonic gravitational field model is adopted for estimating gravitational acceleration near a target small celestial body, and a convex optimization algorithm is adopted for solving the optimal control problem. By adopting the internal spherical harmonic gravitational field model for estimating the gravitational acceleration near the target small celestial body, the advantage of being high in computational efficiency is achieved. By adopting the convex optimization algorithm for solving the optimal fuel control problem, the problems that derivation of a indirection method is complicated, and co-state variables are free of physical meaning and not likely to guess are avoided, the derivation step is simple, the computing time is saved, the estimation optimization method is rapid and high in precision, and the obtained result conforms to initial and end state constraint, dynamic constraint and control constraint.

Description

technical field [0001] The invention relates to a method for optimizing a descent track of a small celestial body attachment detection, which belongs to the field of aerospace. Background technique [0002] As an important way for humans to understand the formation and evolution of the solar system, the origin and evolution of life, and to defend against impacts from foreign celestial bodies, the detection of small celestial bodies will be one of the main contents of future deep space exploration activities. Way. The descent stage is a key stage for the lander to attach to a small celestial body or complete sampling and return detection. It plays a decisive role in whether it can safely and accurately reach the preset target area with scientific exploration value. Guidance and control both put forward high demands. The descent process of the small body lander can be transformed into a trajectory optimization problem and a tracking control problem of the nominal trajectory....

Claims

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Application Information

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IPC IPC(8): G06F19/00
CPCG16Z99/00
Inventor 崔平远刘延杰朱圣英于正湜高艾
Owner BEIJING INSTITUTE OF TECHNOLOGYGY
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