Interplanetary low-thrust transfer orbit design method based on polynomial approximation

Abstract

The invention relates to an interplanetary low-thrust transfer orbit design method based on polynomial approximation. Firstly, variable initial value guess is designed, the initial value guess of the transfer orbit design is given, then, the beginning and tail end boundary conditions of a detector are calculated, next, a second type Chebyshev polynomial is adopted for fitting the transfer orbit of the detector, the performance indexes and the constrained conditions are calculated, finally, whether the feasibility conditions are met or not is judged according to the calculated thrust restriction in accordance with whether the calculated performance indexes meet the optimum conditions or not, if all requirements are met, the optimization is successful, the optimum transfer orbit is obtained, and if one requirement is not met, the initial value guess of the design variable in the first step is regulated until the optimization is successful. The method utilizes the Chebyshev polynomial for approximating the low-thrust transfer orbit shape, the time is used as the independent variable, and the flight time restriction is avoided. The polynomial factor is determined through the beginning and tail end orbit state restriction of the detector, and the method has the advantage that the fast design on the low-thrust transfer orbits in different task types can be realized according to the given beginning and tail end boundary conditions.

Description

technical field [0001] The invention relates to a polynomial-based rapid design method of an interplanetary low-thrust transfer orbit, which is suitable for the initial design of an interplanetary low-thrust transfer orbit and belongs to the technical field of deep space exploration transfer orbits. Background technique [0002] In interplanetary exploration missions, how much fuel the probe needs to consume to reach the target star is the primary concern of mission design. Compared with traditional chemical propulsion systems, small-thrust engines have the characteristics of high specific impulse and light weight. Interplanetary probes can effectively save fuel consumption when using them to achieve orbit transfer. Since the small-thrust engine needs to work for a long time to achieve the purpose of changing the orbit, the orbit of the detector is a typical strongly nonlinear non-Kepler orbit. Many theories and methods in the traditional pulse orbit design are no longer app...

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Problems solved by technology

[0005] Aiming at the problems of thrust direction assumption, poor robustness and low efficiency in the current design of interplanetary low-thrust transfer orbits based on shape curves, the present invention provides a design method for interplanetary small-thrust transfer orbits based on polynomial approximation, which directly avoids time-of-flight constraints for improved robustness

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