An electric propulsion deployment and thrust direction adjustment mechanism

Abstract

The invention relates to an electric propulsion expansion and thrust direction adjustment mechanism, and relates to the field of spacecraft propulsion adjustment. The electric propulsion expansion andthrust direction adjustment mechanism comprises a mounting bottom plate, an elastic expansion joint, a first expansion arm, locking mechanisms, a single-degree-of-freedom revolute joint, a second expansion arm, a double-degree-of-freedom revolute joint and a thruster mounting plate. The axial end of the first expansion arm is fixedly connected with the upper surface of the mounting bottom plate through the elastic expansion joint, the locking mechanisms are fixedly mounted on the lower surface of the first expansion arm, and the single-degree-of-freedom revolute joint is fixedly mounted on the other axial end of the first expansion arm. The axial end of the second expansion arm is connected with the first expansion arm through the single-degree-of-freedom revolute joint, the double-degree-of-freedom revolute joint is fixedly mounted on the other axial end of the second expansion arm, and the double-degree-of-freedom revolute joint is fixedly connected with the lower bottom surface ofthe thruster mounting plate. According to the electric propulsion expansion and thrust direction adjustment mechanism, the backup capability of an electric thruster is improved, and the consumption ofa propellant under the condition of fault ignition is reduced; and at the same time, the efficiency of the electric thruster to maintain the north-south position can be improved.

Description

technical field [0001] The invention relates to the field of spacecraft propulsion adjustment, in particular to an electric propulsion deployment and thrust direction adjustment mechanism. Background technique [0002] The spacecraft in geostationary orbit (GEO) is in a static state relative to any observer on the earth, and it is widely used in communication, broadcasting, meteorology and other fields. In actual operation, due to perturbations such as the gravitational force of the sun and the moon, solar radiation pressure, and the non-spherical shape of the earth, geostationary orbit satellites do not exist in a static state, but drift in two directions: north-south (latitude) and east-west (longitude). According to application requirements, on-orbit position keeping should be implemented to limit the drift of the satellite in the north-south and east-west directions within a specified range. In most cases, for negative accelerations (south corrections), the optimum mome...

AI Technical Summary

Problems solved by technology

[0007] 1. The electric thruster cannot form a complete backup; when an electric thruster fails, the failure ignition strategy is used to work, and the propellant consumption will reach more than 1.5 times that of the normal ignition strategy, which reduces the effective carrying capacity of the spacecraft

[0008] 2. The actual installation position of the electric thruster is limited by the position of the center of mass of the spacecraft and the size of the back floor. Its efficiency in maintaining the north-south position is low, and the normal (north-south) acceleration can only account for about 0.5 times the total acceleration. lower utilization rate

Images