This paper is concerned with the derivation of the equations of motion for maneuvering flexible spacecraft both in orbit and in an earth-based laboratory. The structure is assumed to undergo large rigid-body maneuvers and small elastic deformations. A perturbation approach is presented in which the quantities defining the rigid-body maneuver are regarded as the unperturbed motion and the elastic motions and deviations from the rigid-body motions are regarded as the perturbed motion. The perturbation equations are linear, non-self-adjoint, and with time-dependent coefficients. A maneuver force distribution exciting the least amount of elastic deformation of the spacecraft is developed. Numerical results highlight the vibration caused by rotational maneuvers.
Equations of motion for maneuvering flexible spacecraft
1987-10-01
Sonstige
Keine Angabe
Englisch
Equations of motion for maneuvering flexible spacecraft
AIAA | 1987
|Maneuvering of flexible spacecraft
AIAA | 1986
|Maneuvering and Vibration Control of Flexible Spacecraft
NTIS | 1987
|Maneuvering and vibration control of flexible spacecraft
NTRS | 1987
|Maneuvering and vibration control of flexible spacecraft
NTRS | 1987
|