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A Rapid Design Method for Earth-Moon l1 Lagrangian Point Transfer Orbit

A technology for transferring orbits and design methods, applied in calculation, instrumentation, geometric CAD, etc., which can solve the problems of long flight cycle and long calculation time of the detector, and achieve the effects of good practicability, fuel saving, and improvement of design reliability

Active Publication Date: 2018-11-27
BEIJING INSTITUTE OF TECHNOLOGYGY
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

Designing this type of orbit requires a long calculation time, the engine is often on during the entire mission and the probe has a long flight period

Method used

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  • A Rapid Design Method for Earth-Moon l1 Lagrangian Point Transfer Orbit
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  • A Rapid Design Method for Earth-Moon l1 Lagrangian Point Transfer Orbit

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Embodiment 1

[0043] Such as figure 1 As shown, a rapid design method of the earth-moon L1 Lagrangian point transfer orbit disclosed in the present invention is aimed at the small normal amplitude A z =The design steps of the 5000km target Halo track are as follows:

[0044] Step 1. The probe applies the first maneuvering pulse at the ideal orbit entry point of the target Halo orbit, and reversely deduces from the L1 Lagrangian point Halo orbit to the perilunar point position that satisfies the leverage constraint;

[0045] When designing the orbit of the probe, it is necessary to consider the influence of the gravitational force of the earth and the moon in the barycentric rendezvous coordinate system, and the dynamic equation can be expressed as:

[0046]

[0047] Such as figure 2 As shown, the origin of the coordinate system is the center of mass of the earth-moon system, the X-axis coincides with the line connecting the earth and the moon, and points from the earth to the moon, th...

Embodiment 2

[0067] Such as figure 1 As shown, a rapid design method of the earth-moon L1 Lagrangian point transfer orbit disclosed in the present invention is aimed at the large normal amplitude A z =The design steps of the 30000km target Halo track are as follows:

[0068] Step 1. The probe applies the first maneuvering pulse at the ideal orbit entry point of the target Halo orbit, and reversely deduces from the L1 Lagrangian point Halo orbit to the perilunar point position that satisfies the leverage constraint;

[0069] When designing the orbit of the probe, it is necessary to consider the influence of the gravitational force of the earth and the moon in the barycentric rendezvous coordinate system, and the dynamic equation can be expressed as:

[0070]

[0071] Such as figure 2 As shown, the origin of the coordinate system is the center of mass of the earth-moon system, the X-axis coincides with the line connecting the earth and the moon, and points from the earth to the moon, t...

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Abstract

The invention relates to a quick design method of an earth-moon L1 Lagrange point transfer orbit, and belongs to the technical field of spacecraft orbit design and optimization. The quick design method comprises the following steps: a detector applies a first-time maneuvering pulse to the ideal orbit entering point of a Halos orbit, and carries out reverse recursion on the first-time maneuvering pulse to a perilune position which meets leveraging constraints from the Halo orbit of the L1 Lagrange point; the detector applies a second-time maneuvering pulse to the perilune, and enters an earth-moon transfer orbit segment; and the detector applies a third-time maneuvering pulse and finally realizes earth parking orbit capture. Since the design method adopts an inverse integration strategy, a practical detector track departs from the earth, and finally, the Halo orbit of the earth-moon L1 Lagrange point can be achieved. The quick design method aims at different constraint sets, can automatically regulate the target orbit entering point of the Halos orbit, avoids the selection uncertainty of the orbit entering point, and has good reliability and practicality. In addition, speed increment required for finishing a task is small.

Description

technical field [0001] The invention relates to a rapid design method for the transfer orbit of the Earth-Moon L1 Lagrangian point, in particular to a constraint selection method when a probe uses celestial bodies during interstellar navigation, and belongs to the technical field of spacecraft orbit design and optimization. Background technique [0002] As a solid satellite orbiting the earth and the closest to the earth in the solar system, the moon has become a research focus in the field of aerospace engineering and applications. The L1 translation point orbit that exists near the moon and is visible to the earth can be used as an ideal place for probes to observe the moon and maintain communication with the earth (Farquhar, R.W.The utilization of haloorbits in advanced lunar operations[R].Technical Report NASA TN D- 6365, 1973). For the Earth-Moon L1 Lagrangian point transfer orbit mission, it can usually be divided into four stages: the Earth escape stage, the Moon lev...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G06F17/50
CPCG06F30/15G06F30/367
Inventor 张景瑞曾豪祁瑞胡权张尧
Owner BEIJING INSTITUTE OF TECHNOLOGYGY
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