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Low-thrust long-term position keeping method for geostationary orbit satellite

A geostationary orbit, low-thrust technology, applied in the direction of aerospace vehicle guidance devices, aerospace equipment, space navigation equipment, etc., can solve the problem of not fully utilizing the long-term characteristics of satellite perturbation motion, lack of coordination state initial value guessing method and position maintenance Optimization algorithm convergence stability and convergence speed and other issues

Active Publication Date: 2020-11-27
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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  • Low-thrust long-term position keeping method for geostationary orbit satellite
  • Low-thrust long-term position keeping method for geostationary orbit satellite
  • Low-thrust long-term position keeping method for geostationary orbit satellite

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Embodiment 1

[0123] Such as figure 1 As shown, this embodiment discloses a low-thrust long-term position keeping method for geostationary satellites. In order to verify the method, firstly, a satellite operating in 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: Through spherical coordinates, establish the motion model of the geostationary orbit satellite in the space including the orbital plane and the outer plane under the influence of environmental perturbation, and analyze the periodic motion law of the geostationary orbit satellite;

[0128] The band harmonics and field harmonic coefficients used to calculate the Earth's non-spherical perturbation are shown in the following table:

[0129] Table 2 Principal term coefficient of the earth's gravitational field

[0130]

[0131] Bringing the parameters in Table 1 and Table 2...

Embodiment 2

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

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

[0157] Step 5.1: Calculate the pulse thrust ΔV required for position maintenance through the deviation of the initial and final orbital elements * = 5.987m / s and the action position of pulse thrust

[0158] Step 5.2: Search for Longitudes Containing Pulsed Thrust Actions The continuous thrust arc segment, so that the satellite can complete with the application of pulsed thrust ΔV * After =5.987m / s, the position of 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 =200mN and ...

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Abstract

The invention discloses a low-thrust long-term position keeping method for a geostationary orbit satellite. The method comprises the following steps establishing an in-plane and out-plane average orbital motion model of a satellite orbit through spherical coordinates; giving a long-period movement rule of the geostationary orbit satellite in the plane and out of the plane through a phase plane analysis method; on the basis, selecting a fixed-point position keeping window of the geostationary orbit satellite, and acquiring a periodic motion trail, namely a drifting section trail, of the satellite in an uncontrolled state in the fixed-point window; and designing a small thrust control law to obtain a motion trail, namely a thrust section trail, of the satellite in a controlled state so thatthe thrust section trail and the drift section trail form a closed-loop trail together, and small-thrust long-term position maintenance of the geostationary orbit satellite is completed.

Description

technical field [0001] The invention relates to a small-thrust long-term position maintenance method for geostationary orbit satellites, in particular to the long-term motion rule analysis of geostationary orbit satellites, and important technologies such as small-thrust position maintenance inside / outside the orbital plane, belonging to the field of spacecraft orbital dynamics and control . Background technique [0002] A spacecraft operating in a geostationary orbit (Geostationary Orbit, GEO) has a large coverage area and is stationary relative to the ground, and has extremely high economic value. The development of geostationary orbit spacecraft mainly presents three "big" trends: First, the flexible parts carried by the spacecraft are getting larger and larger (50-meter-long solar panels, 100-meter-level antennas, and dual robotic arms above 2 meters, etc.); The second is that the spacecraft body will become larger and larger, and its mass will reach tens or even hundre...

Claims

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Application Information

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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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