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Application of low-thrust control in geostationary satellite orbit inclination maintenance

A geostationary and satellite orbit technology, applied in the field of geostationary satellites, can solve problems such as the inability to find trajectory optimization methods, the inability to study small thrust control models, and the inability to formulate orbit keeping strategies

Active Publication Date: 2019-04-02
中科星图测控技术股份有限公司
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  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

[0003] The present invention provides an application of small thrust control in maintaining the inclination angle of the geostationary satellite orbit, which can effectively solve the problem of being unable to study the control model under the action of small thrust proposed in the above background technology, unable to find a method for trajectory optimization, and unable to formulate a new method. The problem of track keeping strategy

Method used

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  • Application of low-thrust control in geostationary satellite orbit inclination maintenance
  • Application of low-thrust control in geostationary satellite orbit inclination maintenance
  • Application of low-thrust control in geostationary satellite orbit inclination maintenance

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Embodiment 1

[0088] Embodiment 1: as Figure 1-4 Shown, the present invention provides a kind of technical scheme, a kind of application of small thrust control in geostationary satellite orbit inclination angle maintenance, the speed increment that small thrust thruster produces once switch can be expressed as following formula:

[0089]

[0090] A total of N thrusters are installed on the satellite to complete the orbit control, and the thrust generated by the ith thruster is F i , the inclination angle of the ith thruster in the body coordinate system is γ i , the rotation angle is σ i , the acceleration formula generated by the i-th thruster is:

[0091]

[0092] where Γ represents the installation matrix of the thruster, expressed as:

[0093]

[0094] The thruster system can provide thrust in four directions, assuming that the thrust is F=[F NW f NE f SW f SE ] T , ignoring the coincidence between the orbital coordinate system and the body coordinate system when t...

Embodiment 2

[0164] Embodiment 2: as Figure 1-4 As shown in , a small thrust control is applied in geostationary satellite orbit inclination maintenance, assuming that the start-up time of the corresponding thruster is [t 01 t 02 … t 010 ] T , the shutdown time is [t f1 t f2 … t f10 ] T , the total thruster working time The control objective is to minimize the startup time of the thruster, that is, to select the appropriate startup and shutdown times so that And the satellite inclination vector at the terminal moment meets the management requirements, which is -0.05°≤i≤0.05°.

[0165] According to the above-mentioned technical scheme, the inclination maintenance problem of small thrust is converted into the parameter optimization problem of nonlinear programming of design thruster switching time;

[0166] The satellite improved vernal equinox root at the initial moment is the following formula:

[0167] X(t 0 ) = [p(t 01 ) f(t 01 ) g(t 01 ) h(t 01 ) k(t 01 ) L(t 01 ...

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Abstract

The invention discloses an application of low-thrust control in geostationary satellite orbit inclination maintenance. A simulation procedure includes the steps that an initial satellite status vectorand an estimated thruster work period are input, an objective function and a constraint function are written according to an inclination control objective and an optimal objective, numerical integration calculation is conducted, the optimal thruster work period is solved according to a parameter optimization method, and a post-control objective and an optimal control vector are output. The application is scientific and reasonable, use is safe and convenient, adaptability analysis is conducted through establishment of an inclination maintenance optimized mathematical model based on three methods of the minimum principle, phase plane control and parameter optimization, simulation verification is conducted on the parameter optimization method, a simulation result indicates that a low-thrustcontrol strategy meets an orbit inclination maintenance requirement, the low-thrust control strategy can be used as a reference in following satellite management, and the simulation result indicates that a low-thrust optimization control method is adaptable in geostationary satellite inclination maintenance.

Description

technical field [0001] The invention relates to the technical field of synchronous satellites, in particular to the application of small thrust control in maintaining the orbit inclination of geostationary synchronous satellites. Background technique [0002] Electromagnetic propulsion is an ideal propulsion method for artificial earth satellites and interplanetary vehicles. It uses the interaction force between the current and the magnetic field in the conductive gas to make the gas eject at high speed to generate thrust. The working medium used is Ionized high-temperature gas—plasma, so it is also called plasma propulsion. Compared with traditional chemical thrusters, electric thrusters have the advantages of small thrust, high specific impulse, small volume and light weight, so the use of electric thrusters will Increasing the carrying capacity of satellite payloads to a large extent will give better play to the role of satellites. Electric propulsion is used in satellite...

Claims

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Application Information

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IPC IPC(8): B64G1/24B64G1/40
CPCB64G1/24B64G1/40
Inventor 牛威张浩章文兴闫碧聪
Owner 中科星图测控技术股份有限公司
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