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Rapid high-precision calculation method for electric propulsion transfer of geostationary satellite

A technology of geostationary satellites and calculation methods, applied in three-dimensional position/channel control, space navigation vehicle guidance devices, etc., can solve problems such as the difficulty of multi-circle orbit optimization, and achieve easy engineering implementation, simple control process, and optimal solution difference. small effect

Active Publication Date: 2022-04-26
CHINA XIAN SATELLITE CONTROL CENT
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  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

[0004] The purpose of the present invention is to provide a fast and high-precision calculation method for electric propulsion transfer of geostationary satellites, which solves the problem that the multi-turn orbit optimization of synchronous satellites with full electric propulsion into orbit is difficult

Method used

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  • Rapid high-precision calculation method for electric propulsion transfer of geostationary satellite
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  • Rapid high-precision calculation method for electric propulsion transfer of geostationary satellite

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Embodiment

[0036] Assume that the initial conditions for the geostationary satellite to orbit are as follows: perigee height h p0 = 200km, apogee height h a0 =10000km, inclination i 0 =20.8°, right ascension of ascending node Ω 0 =0°, argument of perigee ω=180°, mean anomaly M=2°. It can be seen that the eccentricity is about 0.73, and the apogee height of the satellite entering orbit after the separation of the satellite and the rocket is equal to the synchronous orbit height of 35786km. The initial mass of the satellite is 4000kg, the specific impulse is 3500s, and the thrust is 350mN. So the initial acceleration is 0.875×10 -4 m / s 2 .

[0037] By adopting the fast and high-precision calculation method for geostationary satellite electric propulsion transfer of the present invention, an optimal suboptimal solution of 343.7 days is obtained, including 463 orbit transfers, and the yaw angle β=32.8° is adopted. Using the same initial conditions and the most time-saving performance ...

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Abstract

The invention discloses a rapid high-precision calculation method for electric propulsion transfer of a geostationary satellite, which comprises the following steps of: determining a control design variable yaw angle, and establishing a normal control law; reducing the inclination angle, establishing a first-stage in-plane control law to change the semi-major axis until the semi-major axis reaches the synchronous orbit height, ending numerical integration in the stage, and turning to the next step; continuously reducing the inclination angle, and meanwhile, establishing a second-stage in-plane control law to change the eccentricity rate until the eccentricity rate reaches 0, and terminating the numerical integration in the stage; the yaw angle is changed to update the normal control law, the change rate of the dip angle is adjusted and changed until the dip angle is equal to 0 at the termination moment, iteration convergence is represented, that is, the semi-major axis, the eccentricity rate and the dip angle meet the synchronous orbit condition at the numerical integration termination moment at the same time, and finally a result is output. According to the rapid and high-precision calculation method for the electric propulsion transfer of the geostationary satellite, the control law has a simple analytical solution, the control process is simple, engineering implementation is facilitated, and the difference between the control law and the optimal solution is small.

Description

technical field [0001] The invention belongs to the technical field of aerospace dynamics and control, and in particular relates to a fast and high-precision calculation method for geostationary satellite electric propulsion transfer. Background technique [0002] With the mature development of electric propulsion technology, the application of electric propulsion technology has gradually changed from position maintenance to the completion of the entire orbit transfer control task. In the past, the traditional method was that after the rocket launched the geostationary satellite into the geostationary transfer orbit (GTO), the chemical propulsion engine was usually used to perform 3-5 orbit changes at the apogee to change the GTO orbit into geostationary orbit (GEO). If electric propulsion is used instead of chemical propulsion, a large amount of fuel can be saved due to the high specific impulse of electric propulsion. However, the thrust of the electric propulsion system ...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G05D1/10B64G1/24
CPCG05D1/101B64G1/242Y02T90/00
Inventor 沈红新张天骄蒯政中黄岸毅李昭
Owner CHINA XIAN SATELLITE CONTROL CENT
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