A Coning Angle Sensor for Spin Stabilized Spacecraft.
ROYAL AIRCRAFT ESTABLISHMENT FARNBOROUGH (ENGLAND)
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A sensor is described which measures the spin axis position in body axes of a spin stabilized satellite, using the sun as an external reference. The theory of the sensor is presented, together with some analysis of the effects of errors in the principal parameters. Results for a prototype sensor are discussed and it is concluded that they are generally satisfactory, but that a proper assessment cannot be made due to test gear limitations, the sun simulator performance is particular being inadequate. Author
- Unmanned Spacecraft