Design Method of Earth-Moon Free Return Orbit Based on Cylindrical Velocity Parameter Section

A return orbit, cylindrical technology, used in computing, electrical digital data processing, special data processing applications, etc.

Active Publication Date: 2018-02-23
NAT UNIV OF DEFENSE TECH
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  • Abstract
  • Description
  • Claims
  • Application Information

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There is currently no published literature on such methods

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  • Design Method of Earth-Moon Free Return Orbit Based on Cylindrical Velocity Parameter Section
  • Design Method of Earth-Moon Free Return Orbit Based on Cylindrical Velocity Parameter Section
  • Design Method of Earth-Moon Free Return Orbit Based on Cylindrical Velocity Parameter Section

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Embodiment Construction

[0108] Concrete implementation process of the present invention is as follows:

[0109] The first step: give constraints according to the actual engineering background;

[0110] Second step: adopt cylindrical velocity parameter section method to determine the existence of free return track;

[0111] The third step: use the cylindrical velocity parameter section method to quickly solve the free return orbit.

[0112] Adopt the present invention can reach following technical effect:

[0113] 1. Compared with the traditional splicing method of lunar influence sphere parameters, the present invention selects the parameters describing the orbit to have actual physical meaning;

[0114] 2. The present invention clearly provides the judging conditions for the existence of the free return orbit, and for the first time theoretically expounds the real reason why the previous solution methods do not converge;

[0115] 3. The present invention does not need to solve nonlinear equations...

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Abstract

The invention relates to a design method of an earth-moon free return orbit based on a cylindrical velocity parameter section, and belongs to the field of spacecraft dynamics and control of aerospace science and technology. This method first gives the definition and characteristics of the cylindrical velocity parameter section of the Earth-Moon transfer orbit, then gives the existence analysis method for the free return orbit solution based on the hyperbolic residual velocity loop, and finally gives the solution strategy for the free return orbit solution. The present invention analytically provides the judging condition for the existence of the free-return orbit solution, and the method is fast and efficient; at the same time, it provides a solution strategy for using the analytical method to solve the initial value and iteratively performing precise orbit calculation with a high-precision dynamic model. The method is simple, reliable, and The calculation speed is fast and has important application prospects.

Description

technical field [0001] The invention relates to a simple analytical method for designing the free return orbit of the earth and the moon, which belongs to the field of spacecraft orbit dynamics and control of aerospace science and technology. Background technique [0002] The Earth-Moon free return orbit is the flight orbit adopted to improve safety in the early stage of the manned mission to the Moon. If the manned lunar exploration vehicle uses this type of orbit to fly, it can glide to the vicinity of the Moon after the Earth-Moon transfer into orbit, and Orbit the Moon at a lower perilunar altitude and return to the Earth's atmosphere with certain reentry conditions without any additional orbital control. Traditional design methods include analytical methods and numerical methods. [0003] In the analytical method, the concept of the lunar influence sphere is firstly introduced, and the earth-moon transfer orbit is divided into two two-body orbits, the earth-centered se...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G06F17/50
Inventor 李海阳贺波勇王华
Owner NAT UNIV OF DEFENSE TECH
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