Modeling fuel slosh effects accurately and completely on spinning spacecraft has been a long standing concern within the aerospace community. Gyroscopic stiffness is obtained by spinning spacecraft as it is launched from one of the upper stages before it si placed in orbit. Unbalances in the spacedraft causes it to percess (wobble). The oscillatory motions are caused in the fuel due to this precession. This prenomenon is called 'fuel slosh' and the dynamic forces induced could adversely affect the stability and control of a spacecraft that spins about one of its minor moments of inertia axes. An equivalent mechanical model of fuel slosh is developed using springs and dampers that are connected to the rigid fuel tank. The stiffness are damping coefficients are the parameters that need to be identified in the fuel slosh mechanical model.
Parameter Estimation of Spacecraft Nutation Growth Model
2004
8 pages
Report
No indication
English
Parameter Estimation of Spacecraft Nutation Growth Model
NTRS | 2003
|An active nutation damper for spacecraft
TIBKAT | 1977
|An Active Nutation Damper for Spacecraft
NTIS | 1977
|An active nutation damper for spacecraft
NTRS | 1977
|