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Halo orbit on-orbit keeping method considering amplitude constraint

An orbit and amplitude technology, which is applied in the aerospace field and can solve problems such as the change of the Halo orbit amplitude.

Inactive Publication Date: 2017-05-17
BEIJING INSTITUTE OF TECHNOLOGYGY
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  • Summary
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  • Description
  • Claims
  • Application Information

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Problems solved by technology

The speed increment obtained by this method is small, and the calculation is simple, but as the on-orbit retention time increases, the amplitude of the Halo orbit will change greatly

Method used

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  • Halo orbit on-orbit keeping method considering amplitude constraint
  • Halo orbit on-orbit keeping method considering amplitude constraint
  • Halo orbit on-orbit keeping method considering amplitude constraint

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Embodiment 1

[0074] The present invention discloses a Halo orbit maintenance method considering the amplitude constraint. Here, the restrictive three-body system composed of the earth-moon-probe is chosen as an example, and the balance point is selected as L2 point. The scheme flow diagram is as follows figure 1 As shown, the on-orbit design method of the Halo orbit includes the following steps:

[0075] Step 1: Establish a dynamic equation under the restricted three-body model composed of the Earth-Moon-probe, and determine the position of the equilibrium point of the three-body system composed of the Earth-Moon-probe.

[0076] Select the earth and the moon as the main celestial body S 1 and S 2 , to establish the dynamic equation in the centroid rotating coordinate system. The coordinate system selects the center of mass of the earth-moon system as the origin, the x-axis direction points from the origin to the moon, the z-axis is the moon’s revolution direction, and the y-axis and x, z...

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Abstract

The invention provides a Halo orbit on-orbit keeping method considering amplitude constraint, and belongs to the aerospace technology field. The method comprises the steps that by establishing a kinetic equation under a limited three-body model composed of two main celestial bodies and a detector, the position of a balance point of a three-body system composed of the two celestial bodies and the detector is determined; a Halo orbit, near the balance point, in the three-body system composed of the big and small celestial bodies and the detector is determined; a differential correction algorithm for Halo orbit keeping is designed according to the disturbance variable; a Halo orbit on-orbit keeping strategy is designed according to the differential correction algorithm; in a real ephemeris environment, measurement errors and execution errors are considered, the speed increment of each time of orbit correction is obtained according to the orbit keeping strategy through the differential correction algorithm, orbit correction control is conducted according to the speed increments. Accordingly, Halo orbit on-orbit keeping considering amplitude constraint can be achieved, and consumption of fuel needed in orbit keeping can be reduced as much as possible.

Description

technical field [0001] The invention relates to an on-orbit maintenance method of a Halo orbit considering the amplitude constraint, which is suitable for the on-orbit maintenance control of the Halo orbit at a balance point under the condition of a real ephemeris environment and considering measurement and execution errors, and belongs to the technical field of aerospace. Background technique [0002] The equilibrium point is a point with special properties in the three-body system composed of the detector and two main celestial bodies surrounding each other, and the object at the equilibrium point can remain relatively stationary relative to the main celestial body. Near the equilibrium point, there is a periodic orbit around the equilibrium point that satisfies certain velocity and position constraints, and the objects on the periodic orbit also keep relatively large and small-mass celestial bodies in a basically unchanged positional relationship. At the same time, compar...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G06F17/50B64G7/00
CPCB64G7/00G06F30/20
Inventor 唐玉华孙超吴伟仁乔栋李翔宇
Owner BEIJING INSTITUTE OF TECHNOLOGYGY
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