Method for optimum thrust distribution of position keeping of conical layout electric propulsion satellite in fault mode

A technology of satellite failure and mode position, which is applied in the direction of aerospace vehicle propulsion system devices, aerospace safety/emergency devices, aerospace vehicle guidance devices, etc., can solve the problem of affecting the life of the thruster, not considering the optimal fuel consumption, excess fuel Consumption and other issues

Active Publication Date: 2018-04-10
BEIJING INST OF CONTROL ENG
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

Although this method is simple and intuitive, it has the following disadvantages when applied to the satellite: ①This allocation method does not consider the optimal

Method used

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  • Method for optimum thrust distribution of position keeping of conical layout electric propulsion satellite in fault mode
  • Method for optimum thrust distribution of position keeping of conical layout electric propulsion satellite in fault mode
  • Method for optimum thrust distribution of position keeping of conical layout electric propulsion satellite in fault mode

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Experimental program
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Effect test

Embodiment 1

[0150] Assume that the thrust of a single electric thruster is 100mN, the three-axis thrust direction is 0.19, 0.5, 0.84., and the mass of the satellite is 4458kg. The date is January 1, 2017. Thruster SW failure.

[0151] Fault judgment is carried out in (1), specifically:

[0152] It is known that the thruster SW is faulty, and the NW and SE thruster pairs are selected for control.

[0153] In the step (2), two possible distribution modes of the target thruster pair combination are calculated.

[0154] ①Calculate the position retention coefficient as

[0155] A 0 =0.0676

[0156] B1 0 =1.25e-4

[0157] B2 0 =2.73e-4

[0158] E. 0 =1.66e-4

[0159] The coefficients of failure mode position-holding control for NW and SE are:

[0160] A NW =A 0 , B1 NW = B1 0 , B2 NW =B2 0 ,E NW =E 0 ;

[0161] A SE =-A 0 , B1 SE =-B1 0 , B2 SE =B2 0 ,E SE =-E 0 ;

[0162] Known position holding inclination control amount di x 、di y , the position-preserving dire...

Embodiment 2

[0174] Assume that the longitude of the fixed point of the satellite is 80°E, the faulty thruster is SW, and the simulation time is 1 year. Simulation results such as Figure 4 As shown, the thruster allocation method provided by the present invention can keep the satellite within the "dead zone" range of ±0.05° of fixed-point latitude and longitude.

Embodiment 3

[0176] Set the daily east-west and north-south positions to maintain a certain amount of control, use the traditional analysis of the four orbit changes, use the optimization algorithm to perform a large number of iterations to calculate the arbitrary right ascension, the optimal four orbit changes of any jet duration, and the three times of the present invention. The thruster allocation methods generated by orbital strategy are compared, and the simulation time is 2 years. Figure 5 It is the ratio of the daily fuel consumption of the traditional 4-time orbit change distribution method and the 3-time orbit-change method in the present invention. It can be seen that the fuel consumption of the 3-time orbit-change method of the present invention is significantly smaller than that of the four-time orbit-change method. Figure 6 It is the ratio of the daily fuel consumption of the four allocation methods optimized by numerical value. It can be seen that the wall ratio is close to ...

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Abstract

The invention provides a method for optimum thrust distribution of position keeping of a conical layout electric propulsion satellite in a fault mode. According to the method, an analytical method isadopted for conducting position keeping control distribution of electric thrusters in a conical layout fault mode; firstly, a pair of thrusters which have no faults and are used for position keeping control are selected according to a thruster with faults; secondly, two different distribution modes of the thruster pair are obtained and selected; finally, the startup time of the electric thrustersis changed to avoid a shadow zone. According to the method, the completely analytical mode is adopted, and the distribution purpose of the electric propulsion position keeping thrusters in the fault mode is achieved, so that the fuel consumption is optimized, the startup frequency of the thrusters within an orbital period is reduced at the same time, and therefore the effective thruster distribution method is provided for electric propulsion position keeping of the geostationary orbit satellite in the fault mode.

Description

technical field [0001] The invention relates to an electric propulsion position keeping control thruster distribution method, which is mainly used on geostationary orbit satellites whose electric thrusters are in a conical layout, and is used for position keeping control thrust distribution in the case of a certain thruster failure, and belongs to Satellite attitude and orbit control technology field. Background technique [0002] For electric propulsion satellites used for geosynchronous orbit position maintenance control, the installation configuration of the electric thrusters adopts a conical layout, and four thrusters are installed in pairs and symmetrically obliquely on the four sides of the back floor. This type of thruster configuration has less redundancy. When all four thrusters can work normally, the four thrusters will spray air successively within one orbital cycle to generate the control force needed to maintain the north-south and east-west positions of the g...

Claims

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Application Information

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IPC IPC(8): B64G1/24B64G1/40B64G1/52
CPCB64G1/242B64G1/407B64G1/52B64G1/245
Inventor 马雪石恒胡少春韩冬汤亮刘潇翔陈守磊
Owner BEIJING INST OF CONTROL ENG
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