Accurate orbit transfer method for asteroid detection based on sun-earth rotating coordinate system

A technology of rotating coordinate system and transfer method, which is applied in the field of aerospace, can solve problems such as the inapplicability of detection track design, and achieve the effect of improving precision, high efficiency and high precision

Inactive Publication Date: 2020-01-31
BEIJING INSTITUTE OF TECHNOLOGYGY
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Problems solved by technology

[0005] Prior technology [2] (see: Wang Y., Qiao D., Cui P..Design of Optimal ImpulseTransfers from the Sun-Earth Libration Point to Asteroid[J].Advance in SpaceResearch.2015,56(1):176 -186) proposed the orbit design method for detecting sma

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  • Accurate orbit transfer method for asteroid detection based on sun-earth rotating coordinate system
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  • Accurate orbit transfer method for asteroid detection based on sun-earth rotating coordinate system

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Embodiment 1

[0066] like figure 1 As shown, taking the detection target asteroid 2016HO3 as an example, the precise orbit transfer method for asteroid detection based on the sun-earth rotating coordinate system disclosed in this embodiment, the specific implementation steps are as follows:

[0067] Step 1: According to the selected detection target, use launch opportunity search to determine the optimal interstellar transfer opportunity under the two-body model.

[0068] Determine the detection target according to the detection mission, given the search interval of the launch time of 2024-2025 and the transfer time of less than 400 days, for any launch time T s and transfer time T f , according to the ephemeris to determine the earth position velocity r at the departure time E (T s ), v E (T s ) and the position r of the small celestial body at the time of arrival a (T s +T f ), v a (T s +T f ). By solving the Lambert problem, the speed increment Δv required for the transfer is...

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Abstract

The invention discloses an accurate orbit transfer method for asteroid detection based on a sun-earth rotating coordinate system, and belongs to the technical field of aerospace. An implementation method comprises the following steps: searching an optimal interstellar transfer opportunity by using a contour map; establishing the sun-earth rotating coordinate system, and converting the optimal transfer opportunity to the rotating coordinate system; correcting an orbit under the rotating system through a second-order differential correction algorithm on the basis of an elliptic restrictive three-body kinetic equation by considering the starting height constraint of the earth; and converting the transfer orbit into an inertial system, completing design of the accurate transfer orbit for asteroid detection, obtaining an accurate earth-asteroid transfer orbit in the geocentric inertial system, and carrying out orbit transfer according to the accurate earth-asteroid transfer orbit. Thus, a detector can realize orbit transfer from the earth to the target asteroid precisely and effectively. The earth escape orbit and the heliocentric transfer orbit are considered at the same time, conicalorbit splicing is not needed, and the orbit design precision can be improved.

Description

technical field [0001] The invention relates to a method for asteroid detection orbit transfer under the sun-earth rotating coordinate system, in particular to a high-precision asteroid detection and transfer method suitable for considering real ephemeris, and belongs to the field of aerospace technology. Background technique [0002] Asteroids are known as the living fossils of the solar system. The study of asteroids will help humans understand key information about the formation and evolution of the solar system and the origin of life. At the same time, observations have shown that asteroids are rich in resources. Asteroid detection will help in the future Therefore, asteroid detection is a hot topic in the field of deep space exploration. [0003] The design of the interstellar transfer orbit for asteroid exploration is the premise of carrying out the asteroid exploration mission, which will determine the total speed increment of the exploration mission, and then determi...

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Application Information

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IPC IPC(8): G01C21/24G01C21/02G01C21/16
CPCG01C21/02G01C21/16G01C21/24
Inventor 乔栋李翔宇黄江川贾飞达
Owner BEIJING INSTITUTE OF TECHNOLOGYGY
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