Multi-pulse region hovering method based on small planetary surface observation

Abstract

The invention relates to a multi-pulse region hovering method based on small planetary surface observation, and belongs to the technical field of aerospace. The multi-pulse region hovering method based on small planetary surface observation considers small planetary irregular gravity and solar radiation pressure perturbation, and designs a hovering track meeting a small planetary surface hoveringarea constraint based on a targeting method; and the optimal power consumption is the performance index, and the obtained hovering track is minimum in total speed increment under a specific correctionduration constraint. The method has the advantages of being small in required speed increment, few in application pulse times, wide in application range, capable of meeting the hovering area constraint of different sizes, and suitable for hovering track design under the constraint condition of a small planetary surface hovering area.

Description

technical field [0001] The invention relates to a multi-pulse area hovering method based on asteroid surface observation, in particular to a multi-pulse area hovering method considering initial state errors and asteroid irregular gravitational influences, belonging to the field of aerospace technology and suitable for detection The multi-pulse area hovering orbit design of the spacecraft under the constraints of a certain range on the surface of the asteroid. Background technique [0002] Hovering detection on the asteroid surface is a very important stage of asteroid surface observation. Hovering detection means that the relative position of the probe to the target asteroid remains unchanged or only moves within a very small range. Considering that the actual observation task does not require a strict fixed-point observation position, the area hovering on the surface of the asteroid has broad application prospects and is easy to realize. During the hovering detection phase...

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Problems solved by technology

[0003] At present, the prior art for the design of regional hovering orbits [1] (see Zhou Haipan. Design and control of regional relative hovering orbits [J]. Journal of Nanyang Institute of Technology, 2015) proposes the use of single pulse control to achieve relative hovering orbit optimization Design method, which can realize the single-pulse hover trajectory design from boundary to boundary in the specified hover area, but there is a maximum flight time limit when there is relative motion between any two points in the area, and the detector is in the hover area There is no datum point in middle movement

[0004] The prior art [2] (see Gao Xiaoqing, Xi Jiaqi, Han Chao, et al. Simulation Research on Relative Motion Control of Continuous Small Thrust Hover Configuration [J]. Computer Simulation, 2019), proposed a multi-stage continuous constant value small Based on the relative motion model of relative orbital elements and the Gaussian perturbation equation of orbital elements, a constant thrust multi-arc control strategy that satisfies regional hovering constraints is designed. This method can effectively realize mission spaceflight hovering in the area where the spacecraft is relative to the target spacecraft, but the control time of this method accounts for more than half of the total time during the hovering period, and the control thrust acceleration is too small, so it is not easy to realize

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