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the range rate information obtained from the lasers was sporatic and basically unusable. Range information appeared to be relatively good out to approximately 200 feet. The laser system needs to be modified to eliminate failure and provide good range rate information if it is to become dependable and accurate system (R).

FLIGHT SUPPORT SYSTEM (FSS)

The FSS was designed to allow either repair or return of the Solar Maximum Satellite, and it had generic application for use with other compatibly designed deployable or repairable/retrievable payloads. Extensive testing and checkout of the FSS was accomplished at both Goddard Space Flight Center (GSFC) and Kennedy Space Center (KSC). The crew participated in the Final Test at KSC. Participation in both of these tests was necessary and allowed the crew valuable hands-on experience with the flight hardware which could not be obtained elsehwere. 

The Solar Maximum FSS performed flawlessly from a crew standpoint. There were no apparent failures in the system. All of the FSS mechanisms worked smoothly. The operating times were within the limits provided to the crew perflight. The interfaces between the FSS and the Orbiter; and, the FSS and Solar Maximum Satellite appeared nominal, both mechanically and electrically. 

PAYLOAD DEPLOYMENT and RETRIEVAL SYSTEM (PDRS)

The checkout of the RMS on day 1 was entirely nominal with the exception of the a shoulder pitch position error that occurred on selection. This was not unexpected and did not reoccur during an operations other than the power-ups.

The RMS operations on day 2 were in support of the LDEF deployment and are described in that section of this report. 

On day 3 several unsuccessful attempts to grapple the tumbling Solar Maximum Satellite were made, and the RMS performed flawlessly. Several weeks prior to the mission, simulations showed that by lowering the poise-for-capture position from  -850 to -800, a wider track-and-capture envelope was available for the rotating grapple. The lower position was used and the writs was also rolled to place the camera on the bottom as an aid for nulling relative translations during proximity operations. The rotation of the Solar Maximum Satellite was difficult to predict but could be described as a -X roll of about 1 degree per second (opposite to the roll that was used in training)and a wide coning motion of 1 to 2 degrees per second that coupled between pitch and yaw. Four attempts were made where RMS was typically flown in ORB UNLOADED, looking out the aft window until the grapple fixture was in view, then switching to END EFFECTOR to attempt the track-and-capture. Two attempts looked promising but ended in wrist pitch and elbow pitch reach limits. Some primary reaction control system (PRCS) jet firings were required before the RMS could be flown out of its reach limits. Other grapple attempts were frustrated by sun glint in the wrist camera and by insufficient RMS rates in vernier. Simulations indicated that track-and-captures with coarse rates were not required for the Solar Maximum Satellite. In retrospect, the two attempts that ended in