A thruster layout method for all-electric propulsion satellites

Abstract

The invention discloses a thruster arrangement method for an integrated electric propulsion satellite. The thruster arrangement method includes the steps that three electric thrusters are arranged on one side, close to a south plate, of a satellite backland plate, three electric thrusters are arranged on one side, close to a north plate, of the satellite backland plate, and then the satellite is launched to a synchronous transfer orbit through a carrier rocket; after the satellite is separated from the carrier rocket, a satellite orbit transfer task is completed through electric propulsion according to the working conditions of all the electric thrusters till the satellite is transferred to a geostationary orbit from the synchronous transfer orbit; according to the working conditions of all the electric thrusters, the corresponding electric thrusters ignite in an adaption area to complete satellite position keeping. According to the thruster arrangement method, a rail transfer task and the orbit transfer task in the service life period of the satellite are completed through combination of the four thrusters, the requirements of the integrated electric propulsion satellite for the thrust size and the service life of the thrusters can be effectively reduced, electric-thruster adaptation of the integrated electric propulsion satellite is increased, and the thruster arrangement method has the advantages that the thruster arrangement method is basically invariable for the ignition position before and after failure of a single satellite thruster, propellant consuming and the like.

Description

technical field [0001] The invention relates to a layout method of electric thrusters for three-axis stable geostationary orbit satellites, in particular to a layout method of thrusters for all-electric propulsion satellites, aiming at completely utilizing electric propulsion to complete the transfer orbit change task, synchronous orbit attitude and orbit control mission's all-electric propulsion satellite. Background technique [0002] For a geostationary orbit satellite launched to a synchronous transfer orbit using a launch vehicle, the satellite needs to carry enough propellant to complete tasks such as transfer orbit change, synchronous orbit attitude, and orbit control. For satellites using chemical propulsion, the amount of propellant carried will generally reach 55% or higher of the total launch weight. Electric propulsion has gradually become the standard configuration of geostationary orbit satellites due to its high specific impulse and fuel-saving characteristic...

AI Technical Summary

Problems solved by technology

[0008] The technical problem solved by the present invention is to overcome the deficiencies of the prior art, provide a thruster layout method for all-electric propulsion satellites, solve the problem of excessive redundancy of thruster layout in existing all-electric propulsion satellites, and have the advantages of good use value

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