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A low-thrust long-term position keeping method for geostationary satellites

A static orbit, low-thrust technology, applied in the direction of aerospace vehicle guidance devices, instruments, aerospace vehicles, etc., can solve the problem of lack of co-state initial value guessing method, position maintenance optimization algorithm convergence stability and convergence speed, underutilization Problems such as the long-term characteristics of satellite perturbation motion can solve the problem of small thrust position maintenance, reduce labor costs and equipment loss, and reduce fuel consumption.

Active Publication Date: 2022-06-28
BEIJING INSTITUTE OF TECHNOLOGYGY
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

The current position keeping strategy focuses on offsetting the influence of geostationary orbit perturbation on satellite motion, and does not make full use of the long-term characteristics of satellite perturbation motion; on the other hand, it lacks a set of universal initial value guessing methods to improve Convergence Stability and Convergence Speed ​​of Position Preserving Optimization Algorithm

Method used

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  • A low-thrust long-term position keeping method for geostationary satellites
  • A low-thrust long-term position keeping method for geostationary satellites
  • A low-thrust long-term position keeping method for geostationary satellites

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Embodiment 1

[0123] like figure 1 As shown, this embodiment discloses a method for maintaining a low-thrust long-term position of a geostationary orbit satellite. In order to verify the method, first, a satellite operating in a geostationary orbit is selected as the main research object. The basic parameters of the satellite are shown in the table below.

[0124] Table 1 Satellite parameters

[0125]

[0126]

[0127] Step 1: Establish the motion model of the geostationary orbit satellite in the space including the orbital plane and the outer plane under the action of the environment perturbation through spherical coordinates, and analyze the periodic motion law of the geostationary orbit satellite;

[0128] The band harmonic term and field harmonic term coefficients used to calculate the aspherical perturbation of the earth are shown in the following table:

[0129] Table 2 The main term coefficients of the Earth's gravitational field

[0130]

[0131] Bringing the parameters ...

Embodiment 2

[0155] The first four steps of Example 2 are the same as the first four steps of Example 1.

[0156] Step 5: Solve the two-point boundary value problem described in step 4 through the co-state initial value guessing method, and bring the result into step 4 to obtain the time-optimal and fuel-optimal control laws for maintaining the low-thrust position:

[0157] Step 5.1: Calculate the pulse thrust ΔV required to maintain the position through the deviation of the number of orbital elements at the beginning and end * =5.987m / s and the action position of the pulse thrust

[0158] Step 5.2: Search for longitudes containing pulse thrust effects of continuous thrust arcs, enabling the satellite to complete the thrust with the applied pulse ΔV * = After 5.987m / s, the position with the same effect is maintained, and the right ascension of the startup and shutdown of the continuous thrust arc is recorded. and the total boot time Δt * =47649s; using continuous thrust F const = 20...

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Abstract

The invention discloses a low-thrust long-term position keeping method for a geostationary orbit satellite, which establishes the average orbital motion model of the satellite orbit in-plane and out-of-plane through spherical coordinates; and gives the in-plane and out-of-plane motion model of the geostationary orbit satellite through the phase plane analysis method. Long-period motion law; on this basis, by selecting the fixed-point position maintenance window of the geostationary orbit satellite, the periodic motion trajectory of the satellite in the uncontrolled state within the fixed-point window is obtained, that is, the trajectory of the drift segment; the small thrust control law is designed to obtain satellite control. The trajectory of the motion under the state, that is, the trajectory of the thrust section, makes the trajectory of the thrust section and the trajectory of the drift section form a closed-loop trajectory, thereby completing the long-term position keeping of the geostationary orbit satellite with low thrust.

Description

technical field [0001] The invention relates to a long-term position maintaining method with small thrust of a stationary orbit satellite, in particular to the analysis of the long-term motion law of a stationary orbit satellite, and important technologies such as the position maintaining of a small thrust in the orbital plane / outside of the orbit, and belongs to the field of spacecraft orbit dynamics and control . Background technique [0002] The spacecraft running on the Geostationary Orbit (GEO) has the characteristics of large coverage area and stationary relative to the ground, and has extremely high economic value. The development of geostationary orbiting spacecraft mainly presents three "big" trends: First, the flexible components carried by the spacecraft are getting larger and larger (50-meter-long solar panels, 100-meter-level antennas, double robotic arms over 2 meters, etc.); Second, the spacecraft body will become larger and larger, and its mass will be as hi...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B64G1/24G06F30/20G06F30/15G06F119/14G06F111/04
CPCB64G1/242G06F30/20G06F30/15G06F2119/14G06F2111/04
Inventor 李林澄张景瑞陈国玖张尧
Owner BEIJING INSTITUTE OF TECHNOLOGYGY
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