Design method of escape orbit starting from Halo track and used for detecting deep space target

A technology of escape orbit and design method, which is applied in the field of aerospace and can solve the problems of large fuel consumption, unstable inner extension, and long flight time of escape orbit.

Inactive Publication Date: 2013-09-04
BEIJING INSTITUTE OF TECHNOLOGYGY
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Problems solved by technology

[0005] In order to solve the problems of large fuel consumption, long flight time, and constrained by celestial body ephemeris constraints of the escape orbit designed by the existing method, t

Method used

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  • Design method of escape orbit starting from Halo track and used for detecting deep space target
  • Design method of escape orbit starting from Halo track and used for detecting deep space target
  • Design method of escape orbit starting from Halo track and used for detecting deep space target

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Example Embodiment

[0032] The following is from the sun-earth system L 1 Take the Halo orbit to probe Mars as an example, and the implementation of the present invention will be described in detail with reference to the accompanying drawings.

[0033] The specific steps of this embodiment are as follows:

[0034] Step 1: Calculate the near arch point state of the unstable disturbance manifold in the Halo orbit

[0035] The Halo orbit given by the mission is northward, and the amplitude in the Z direction is 1.6×10 5 km. In a Halo orbit period, select 100 discrete points uniformly distributed on the Halo orbit. Set the perturbation speed range to [10 -6 , 300]m / s, 50 discrete perturbation velocities are uniformly selected in this range. For each discrete point on the Halo orbit, 50 discrete perturbation velocities ΔV 1 Respectively applied to the direction of the internally unstable eigenvectors, the corresponding internally unstable disturbed manifolds are integrated by a numerical algorithm until re...

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Abstract

The invention relates to a design method of an escape orbit starting from a Halo track and used for detecting a deep space target. The method is especially suitable for design of the escape orbit starting from the Halo track and used for conducting a deep space detecting task and belongs to the technical field of aerospace engineering. First, a minor celestial body periapsis state of interior extent unstable disturbance manifold of a task given Halo track is obtained through calculation; then, according to minor celestial body escaping hyperbola overspeed required by interplanetary transfer required by the task, maneuvering pulse required to be exerted at the position of disturbance manifold periapsis is solved, and flying time from the periapsis to a minor celestial body affecting ball is solved; and finally, contour maps of velocity increment and flying time are drawn respectively, and the escape orbit meeting a task requirement is selected from the contour maps. On the basis of low fuel consumption, flying time for escaping from the Halo track is shortened, and ephemeris constraint of other celestial bodies is not required to be introduced. The degree of freedom of the escape orbit starting from the Halo track is increased by introducing the disturbance manifold, and solution space of a traditional design method is expanded.

Description

technical field [0001] The invention relates to a method for designing escape orbits of deep-space probes, which is particularly suitable for the design of escape orbits for deep-space exploration missions starting from Halo orbits, and belongs to the technical field of aerospace. Background technique [0002] The Halo orbit is a special kind of three-dimensional periodic orbit that exists near the collinear Lagrangian point of the three-body dynamic system. It has important application value in deep space exploration, especially as a transfer station for deep space exploration missions. Save fuel consumption for exploration missions. How to escape from the Halo orbit in order to meet the desired interplanetary transfer requirements is a key technology for deep space exploration based on the Halo orbit, which directly affects the two important indicators of fuel consumption and flight time, and determines the feasibility of the exploration mission plan. The design of escape...

Claims

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Application Information

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IPC IPC(8): B64G99/00
Inventor 尚海滨崔平远王帅乔栋窦强
Owner BEIJING INSTITUTE OF TECHNOLOGYGY
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