Module Support Structure Coupled To Transition Adaptor

& PROVIDED WITH HEATERS TO PREVENT DISTORTION IF NECESSARY

Fig. 22-4. Multi-Mission Spacecraft (MMS) Design (From GSFC [1975])

fourth wheel). In addition, 100 A m2 electromagnets will be used for initial acquisition and momentum maintenance and will provide a minimum reorientation rate of 0.2 deg/sec for spacecraft with moments of inertia up to 400 kg-m2. The MMS spacecraft includes an onboard computer described in Section 6.9 that processes all attitude data and, in conjunction with other stored information, generates control commands.

The first of the MMS missions, SMM, has an attitude accuracy requirement of S arc-seconds (0.001 deg) in pitch and yaw and 0.1 deg in roll. The attitude support anticipated for SMM will be based on considerable interaction between the

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