Study on influence of initial deviation on motion attitude of spacecraft
Year: 2025
Type: article
Abstract: Deployable spacecraft have been widely used, while the motion state under the disturbance is still unknown. A test device is designed to simulate the motion of deployable spacecraft in this paper, and the ballistic characteristics of solid rocket are tested. The test results show that the total impulse deviation of the solid rocket can be effectively reduced by controlling the propellant mass, but the spacecraft would still produce a large precession angle and precession angular rate. The influence of launch disturbance and deployment disturbance on the aircraft is larger than that of spin rocket deviation. The ratio between the transverse moment of inertia and the axial moment of inertia should be increased as much as possible during the design of the spacecraft, otherwise a small disturbance would produce a large precession angle. The test results have certain reference significance for the study of the spacecraft micro-motion.
Language: English
Subfield: Aerospace Engineering
Field: Engineering
Domain: Physical Sciences
Open Access status: gold
Estimated APC paid: $2,420
OpenAlex ID: W4417080377