Design method of earth-moon free return orbit based on cylindrical speed parameter cross sections

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

Active Publication Date: 2015-05-27
NAT UNIV OF DEFENSE TECH
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  • Abstract
  • Description
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  • Application Information

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  • Design method of earth-moon free return orbit based on cylindrical speed parameter cross sections
  • Design method of earth-moon free return orbit based on cylindrical speed parameter cross sections
  • Design method of earth-moon free return orbit based on cylindrical speed parameter cross sections

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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] Step 2: Use the cylindrical velocity parameter section method to determine the existence of the free return orbit;

[0111] Step 3: 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, numer...

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Abstract

The invention relates to a design method of an earth-moon free return orbit based on cylindrical speed parameter cross sections, and belongs to the field of aircraft dynamics and control of aeronautic and astronautic science and technology. The design method comprises the following steps of firstly, giving the definition and characteristic description of the cylindrical speed parameter cross sections of the earth-moon transfer orbit; according to a double-curve residual velocity loop, giving a free return orbit solution existence analyzing method; finally, giving a free return orbit solution solving strategy. The design method has the advantages that the free return orbit solution existence judging condition is analyzed and given, the method is quick, and the efficiency is high; the analyzing method is adopted to solve the initial value, a high-accuracy dynamics model performs iterating to obtain the solving strategy for the accurate orbit calculating, the method is simple and reliable, the calculating speed is high, and the application prospect is important.

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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IPC IPC(8): G06F17/50
Inventor 李海阳贺波勇王华
Owner NAT UNIV OF DEFENSE TECH
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