A Two-Pulse Planet Capture Orbit Method Based on Weak Stability Boundary

A weakly stable, planetary technology, applied in the aerospace field, can solve problems such as infeasibility, and achieve the effect of large application range, small speed increment, and fuel saving.

Active Publication Date: 2017-04-05
BEIJING INSTITUTE OF TECHNOLOGYGY
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  • Summary
  • Abstract
  • Description
  • Claims
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Problems solved by technology

This method is not feasible in the short term due to the fact that no transfer station has been established near the planetary balance point

Method used

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  • A Two-Pulse Planet Capture Orbit Method Based on Weak Stability Boundary
  • A Two-Pulse Planet Capture Orbit Method Based on Weak Stability Boundary
  • A Two-Pulse Planet Capture Orbit Method Based on Weak Stability Boundary

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Embodiment 1

[0041] Such as figure 2 As shown, the present invention discloses a two-pulse planet capture orbit method based on weak stability boundary, comprising the following steps:

[0042] Step 1: Establish the motion equation of the probe under the sun-planet barycenter rotation system.

[0043] The origin of the coordinate system is the center of mass of the system, the X axis coincides with the sun and the line connecting the planets, and the sun points to Mars, the Z axis coincides with the angular velocity direction of the system rotation, and the Y axis is perpendicular to the X and Z axes to form a right-handed coordinate system.

[0044] The motion equation of the detector under this system can be expressed as

[0045]

[0046] where μ=m 2 / (m 1 +m 2 ) represents the mass coefficient of the system, m 1 is the mass of the sun, m 2 is the mass of the planet, . is the distance between the detector and the sun, is the distance between the probe and the planet.

[00...

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Abstract

The present invention discloses a two-pulse planet capture orbit method based on weak stability boundary, relates to a capture orbit method when a prober is captured by a target heavenly body during interstellar travel and enters into a task orbit, and belongs to the technical field of aerospace. The two-pulse planet capture orbit method comprises the following steps of: establishing motion equation of the prober in sun-planet centroid rotation systems; determining the weak stability boundary of the sun-planet system; selecting a weak stability boundary coefficient e, a distance r0 between the prober and the planet, and an included angle [theta] of the prober and the planet according to the target task orbit; applying first engine drive to the prober to enable the prober to enter into a weak stability boundary transfer orbit from a hyperbola orbit; and applying second engine drive to the prober to enable the prober to enter into the target task orbit from the weak stability boundary transfer orbit, and finally obtaining orbit capture. Atmosphere information of the planet is not required to be considered, and the two-pulse planet capture orbit method is high in reliability without being influenced by planetary atmosphere uncertainty. In addition, required speed increment is small, application range is large, and the two-pulse planet capture orbit method has better capture orbit effect for a task orbit having higher height.

Description

technical field [0001] The invention relates to a method for designing a planet capture orbit, in particular to a method for capturing an orbit when a probe is captured by a target celestial body and enters a mission orbit during an interstellar voyage, and belongs to the technical field of aerospace. Background technique [0002] The detection of planets in the solar system such as Mars and Venus is one of the key points of deep space exploration. The detection of planets usually requires the probe to reach the vicinity of the target celestial body through interstellar voyage after being launched from the earth, and be captured by the target celestial body through orbital maneuvering, forming an orbit around the target celestial body to realize the detection of planets. Therefore, the orbit of the exploration mission can be divided into four stages: the Earth escape stage, the interstellar transfer stage, the planet capture stage and the planet detection stage. Among them,...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B64G1/24
Inventor 乔栋李翔宇崔平远尚海滨李斌
Owner BEIJING INSTITUTE OF TECHNOLOGYGY
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