A low-energy trapping orbit method for many-body systems considering start-end constraints

Abstract

The invention discloses a low-energy orbit capture method for a multi-body system taking into account initial and terminal constraints and particularly relates to the low-energy orbit capture method for the multi-body system taking into account the constraints of initial and terminal states. The invention belongs to the technical field of aeronautics and astronautics. The low-energy orbit capturemethod for the multi-body system taking into account the initial and terminal constraints achieves the orbit capture design which satisfies the terminal constraints based on the multi-body system andthe theory of weak stability boundary, by virtue of the gravitational action of the sun for assisting planet capture and by screening the inclination of a hyperbolic orbit of an arrived celestial bodyand applying orbital correction. An interplanetary transfer orbit starting from the earth can be accurately matched with a weak stability boundary orbit by virtue of B-plane parameters. A detector can eventually enter a mission orbit through two-time braking and one-time orbital correction. The low-energy orbit capture method for the multi-body system taking into account the initial and terminalconstraints has the advantages of small required speed increment, wide application range and easy implementation of the method.

Description

technical field [0001] The invention relates to a method for capturing orbits of detectors in a multi-body system, in particular to a method for capturing orbits with low energy considering initial and terminal state constraints, which belongs to the field of aerospace technology and is suitable for detectors starting from the earth in deep space exploration The orbit design for being captured by the target celestial body into the mission orbit. Background technique [0002] The detection of extraterrestrial celestial bodies such as planets, satellites and asteroids usually requires the probe to reach the vicinity of the target celestial body through interstellar voyage after being launched from the earth, be captured by the target celestial body through orbital maneuvering, and move within the daily gravitational field of the target to carry out detection activities. Therefore, the design of the capture orbit is very important, which will determine whether the probe can be ...

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Problems solved by technology

[0004] The prior technology [2] (see a two-pulse planet capture orbit method based on a weakly stable boundary, Qiao Dong, Li Xiangyu, Cui Pingyuan, patent number: ZL201510599566.5, April 5, 2017) proposed to use a weakly stable boundary The planet capture orbit method, establishes the motion equation of the probe under the sun-planet barycenter rotation system, determines the optimal phase angle for capture, and realizes mission orbit capture through two pulses. This method can reduce the incremental demand for capture speed, but due to the The movement is considered in the center of mass rotation system, and it is difficult to match the capture orbit with the interstellar transfer orbit and mission orbit in the inertial system, which brings difficulties to practical applications and cannot be applied to mission orbits with terminal constraints

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