Magnetic

'NONSPINNING EARTH SENSOR ASSEMBLY (SIC SECTION 6.7) ^PROPOSED SPACECRAFT.

^REGISTERED TRADEMARK OP ITNACO CORPORATION. (SEE SECTION BJ1 4ACR0NVM POR WHEEL CONTROL (SEE SEASAT DISCUSSION IN TEXT)

'NONSPINNING EARTH SENSOR ASSEMBLY (SIC SECTION 6.7) ^PROPOSED SPACECRAFT.

^REGISTERED TRADEMARK OP ITNACO CORPORATION. (SEE SECTION BJ1 4ACR0NVM POR WHEEL CONTROL (SEE SEASAT DISCUSSION IN TEXT)

* Direct yaw control can be achieved using a gyroscope, as in inertial guidance systems; using either onboard processing of Sun sensor or star tracker data; or using ground commands to periodically Update the yaw reference.

latitude when the satellite is traveling north and 180 deg minus the latitude when the satellite is traveling south).

GEOS-3. The GEOS-3 control system is described in Table 18-2 and the spacecraft is shown in Fig. 19-17. The control torque from the magnetic eddy current damper is (see Section 18.4 and [Pettus, 1968))

where kD is the damper constant, the geomagnetic field is

Substitution of Eqs. (18-48) and (18-65) into Eq. ( 18-64) gives the damper torque in body coordinates as

1Sc=-kD

0 0

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