Thruster layout method for truss type GEO (geostationary orbit) satellite adopting subdivision optimization design

Abstract

The invention discloses a thruster layout method for a truss type GEO (geostationary orbit) satellite adopting subdivision optimization design. Basic demands of truss type GEO satellite thrusters for subdivision modular design in thrusting service module layout are met, and layout azimuth angles of four 10N thrusters mounted at four corners of a thrusting service module back plate are designed according to demands of highest possible satellite orbital maneuver efficiency, enough capability of overcoming disturbance torque of a high-thrust orbit maneuver engine, combination of sedimentation of propellants and three-axis attitude control, angular momentum unloading and the like; under the adverse condition that the centroid of the whole satellite is remarkably higher than the upper end of a thrusting service module, a thrust vector slant and parallel layout method for 10N thrusters in pairs is adopted for layout of thrusters for east-west station keeping and south-north station keeping, so that layout of the thrusters for east-west station keeping combines functions of pitch attitude control and angular momentum unloading, layout of the thrusters for south-north station keeping combines functions of rolling, pitching, off-course attitude control and angular momentum unloading, and propellants for attitude control and angular momentum unloading are saved.

Description

technical field [0001] The invention relates to a layout method of a truss-type GEO satellite thruster with an optimized design of compartments, and belongs to the technical field of spacecraft control. Background technique [0002] Geostationary orbit (GEO) satellites are usually equipped with a large-thrust orbit-changing engine and more than 12 chemical thrusters to complete satellite orbit changing, fixed-point, east-west and north-south position maintenance, attitude control, and angular momentum unloading. The thruster layout should take into account the installation constraints of the satellite structure, the influence of the thruster plume, and the requirements of the control subsystem. [0003] For GEO communication satellites with a central load-bearing cylinder structure, the two propellant tanks are installed along the Z-axis, the lighter fuel tank is in the upper cabin, the heavier oxygen tank is in the lower cabin, and the thrusters are generally installed on t...

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Problems solved by technology

[0003] For GEO communication satellites with a central load-bearing cylinder structure, the two propellant tanks are installed along the Z-axis, the lighter fuel tank is in the upper cabin, the heavier oxygen tank is in the lower cabin, and the thrusters are generally installed on the opposite floor and the back. Floor, the back floor is located at the bottom of the propulsion service compartment, and the opposite floor is located at the top of the load compartment, so the pipeline of the thruster passes through the propulsion service compartment and also passes through the load compartment. The installation, testing and disassembly of the thruster and pipeline require the load compartment It is not convenient to carry out the modular design of subdivision for operation

[0004] The heavy propellant tanks and batteries of the truss-type GEO satellite with optimized subdivision design are usually in the propulsion service compartment, and the thrusters and pipelines are in the propulsion service compartment. It is possible to carry out modular design of subdivision, but the mechanical coordinates The Z-axis coordinates of the center of mass of the entire star in the system are still significantly higher than the Z-axis coordinates of the upper end of the propulsion service module. The thrusters in the east, west, south and north positions are arranged in the propulsion service module. Installed on the opposite floor and the back floor, nor can it be installed on the waist of the star according to the height of the center of mass, nor can it be centered on the Z-axis coordinate of the center of mass of the whole star in the middle of its life, and be symmetrically arranged up and down at the four corners of the satellite, so that the thruster layout of the compartment modularization It is very difficult to optimize

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