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Moon landing satellite formation initialization method

An initialization method and satellite formation technology, which are applied in the field of satellite formation initialization and satellite formation in the moon-going moon, and can solve the problems of difficult application of satellite formations.

Active Publication Date: 2018-01-16
BEIJING INSTITUTE OF TECHNOLOGYGY
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  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

The above technologies are all suitable for the formation of earth satellites, but it is difficult to apply to the formation of satellites that reach the moon through the transfer of the earth and the moon

Method used

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  • Moon landing satellite formation initialization method
  • Moon landing satellite formation initialization method

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Embodiment 1

[0063] The present embodiment discloses a method for initializing a satellite formation to the moon, establishing satellite dynamic equations in the inertial systems of the earth and the moon respectively; through multiple multi-target orbit corrections, it is ensured that multiple satellites realize formation initialization. By adding midway correction during the earth-moon transfer, ensure that the orbital inclination of each satellite is the same, and the height of the perigee point is the same, and the time of reaching the perigee point is close; the maneuver is applied at the perimeno point to ensure that the satellite's aphelion height is the same; the reference star is determined, and the rest The satellite is a tracking star, and the phase angle of the tracking star is guaranteed to be the same as that of the reference star by using two near-moon point adjustment movements; finally, the optimal two-pulse or multi-pulse rendezvous is used to make the speed and position of...

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Abstract

The invention discloses a moon landing satellite formation initialization method and belongs to the aerospace technical field. The specific implementation process of the method of the invention includes the following steps that: satellite dynamics equations are respectively established under the inertial system of the earth and the inertial system of the moon; the formation initialization of a plurality of satellites is ensured through a plurality of times of multi-target orbit correction; mid-course correction is additionally adopted in earth-moon transfer, so that the orbital inclination angles of the satellites can be ensured, the heights of the perilunes of the satellites are identical, and time for the satellites to arrive at the perilunes is close to each other; maneuvering is applied at the perilunes, so that the heights of the apocynthions of the satellites can be identical; a reference satellite is determined, the other satellites are tracking satellites, and two times of perilune phase adjustment maneuvering is adopted to ensure that the phase angles of the tracking satellites are the same as the reference satellite; and optimal two-pulse or multi-pulse intersection is adopted to make the speeds and positions of the tracking satellites and reference satellite meet formation constraints, so that the formation initialization of the moon landing satellites can be realized. With the orbital formation initialization method adopted, after the plurality of satellites fly to the moon separately, the satellites can realize a moon formation. The method has the advantages ofhigh efficiency and low fuel consumption.

Description

technical field [0001] The invention relates to a method for initializing a satellite formation to reach the moon, in particular to a method for forming a satellite formation for satellites that are transferred to the moon through the earth and the moon, and belongs to the technical field of aerospace. Background technique [0002] Lunar exploration has important scientific value and engineering significance. Using multiple satellites to form a formation to carry out scientific exploration of the moon can obtain more scientific data and complete tasks that cannot be completed by a single satellite, such as gravity field measurement, ultra-long wave detection, etc. . The satellite can be launched on the same carrier rocket, and the satellite and the rocket can be independently transferred to the moon after separation. Due to the different separation states of the satellite and the rocket, the orbits formed after reaching the moon are also different. There may also be errors i...

Claims

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Application Information

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IPC IPC(8): G05D1/10
Inventor 乔栋李翔宇胡勃钦杜燕茹孙超
Owner BEIJING INSTITUTE OF TECHNOLOGYGY
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