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Method of damping nutation motion with minimum spin axis attitude disturbance
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Copyright Year | 1983 |
| Description | In a method of and apparatus for damping nutation of a spinning spacecraft, spin axis attitude disturbances are substantially reduced by controlling at least one nutation damping gas thruster to fire with nonuniform gas pulses. During the beginning of a nutation control sequence, the duration of successive gas pulses is gradually increased (up pulsed) from zero to a predetermined maximum duration. The duration of successive pulses is then maintained constant for a time period. Finally, at the end of the nutation control sequence, the duration of successive gas pulses is gradually reduced to zero (down pulsed). Up pulsing of the gas thruster is initiated in response to a predetermined maximum nutation angle measured by an accelerometer. Down pulsing of the thruster is initiated in response to a predetermined minimum nutation angle. |
| File Size | 599402 |
| Page Count | 10 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19830019793 |
| Archival Resource Key | ark:/13960/t7vm9334m |
| Language | English |
| Publisher Date | 1983-06-07 |
| Access Restriction | Open |
| Subject Keyword | Spacecraft Design, Testing And Performance Attitude Stability Oscillation Dampers Nutation Dampers Rocket Engines Control Stability Spacecraft Stability Gyroscopes Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aerodynamics Aircraft Aerospace Engineering Aerospace Aeronautic Space Science |
| Content Type | Text |
| Resource Type | Patent |
