Communication coverage constraint-oriented earth-moon balance point task orbit rapid determination method

A technology for determining a method and a balance point, applied in the aerospace field, can solve problems such as the constraints and inapplicability of communication between orbits and the lunar surface, and achieve the effects of wide application, improved accuracy, and guaranteed communication coverage.

Active Publication Date: 2020-08-21
BEIJING INSTITUTE OF TECHNOLOGYGY
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Problems solved by technology

[0004] Prior Technology [2] (Refer to: Liang Weiguang, Liu Lei, Liu Yong, et al. Research on the influence of the shadow of the relay star at the Earth-Moon L2 point [J]. Journal of Deep Space Exploration, 2019, 6(1):52-56.) The shadow covera

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  • Communication coverage constraint-oriented earth-moon balance point task orbit rapid determination method
  • Communication coverage constraint-oriented earth-moon balance point task orbit rapid determination method
  • Communication coverage constraint-oriented earth-moon balance point task orbit rapid determination method

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Embodiment 1

[0052] In this embodiment, the lunar surface longitude 170°E and latitude 45°S are chosen as the landing point to quickly analyze the constraints of the relay orbit communication.

[0053] Such as figure 1 As shown, the method for quickly determining the mission orbit of the Earth-Moon balance point disclosed in this embodiment is oriented to communication coverage constraints. The specific implementation steps are as follows:

[0054] Step 1: Establish the earth-moon rotation coordinate system, determine the approximate analytical solution of the Halo orbit and use the differential correction method to obtain the exact solution, and generate several Halo orbits for the calculation of the amplitude of the communication constraints.

[0055] The Halo orbit is established in the earth-moon rotating coordinate system, that is, the origin is the center of mass of the earth-moon system, the X-axis points from the earth to the moon, the Z-axis is in the same direction as the angular...

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Abstract

The invention discloses a communication coverage constraint-oriented earth-moon balance point task orbit rapid determination method, and belongs to the technical field of aerospace. The implementationmethod comprises the steps of establishing an earth-moon rotating coordinate system, determining an approximate analytical solution of a Halo orbit, obtaining an accurate solution by utilizing a differential correction method, and generating a plurality of Halo orbits for communication constraint amplitude calculation; conducting meshing on a back area of the moon, and calculating the geometricalrelationship between feature sample points and the Halo orbits; selecting characteristic geometric parameters according to communication constraint indexes, constructing a regression equation for thecommunication coverage constraint, and determining a quantitative relation between the communication constraint and the orbit amplitude as well as the landing point through the regression equation; and according to the task constraints, rapidly evaluating communication conditions by utilizing the regression equation, and realizing relay task orbit determination. The method can achieve the quick determination of task orbits with different communication constraints, guarantees the communication coverage of a landing point at the far side of the moon, and has the advantage of high orbit determination efficiency.

Description

technical field [0001] The invention relates to a method for quickly determining the mission orbit of the Earth-Moon balance point facing communication coverage constraints, in particular to a method for determining the mission orbit of a relay satellite under different communication constraints, and belongs to the field of aerospace technology. Background technique [0002] The moon is the natural satellite of the earth, which has important scientific research and engineering value. However, affected by the tidal force, the rotation period and revolution of the moon are synchronized, so the back of the moon is always invisible. In order to realize the detection of the back of the moon, it is necessary to be near the L2 point of the earth and the moon Deploy relay stars to realize relay communication. The choice of the relay satellite mission orbit is a problem that needs to be studied in depth. Mission trajectory selection is limited by various constraints, including fuel ...

Claims

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Application Information

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IPC IPC(8): B64G1/10B64G1/24G06F17/11G06F17/15
CPCB64G1/242B64G1/105G06F17/11G06F17/15B64G1/1064
Inventor 吴伟仁张哲乔栋李翔宇
Owner BEIJING INSTITUTE OF TECHNOLOGYGY
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