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J'-'II _ ML, # M_,_ ] L Figure 2-19 control to a problem, special failure the problem control. The Placement the STOCC investigation while the investigation sating team as a data or flight produced inconsistencies will classify expected performance, as a flight The data how If possible, the to correct STOCC be classified investigation Telescope from the lem. If the situation STOCC may nance mission. the problem. will adjust the an unplanned the Space the progression of sating contingency depending upon Telescope.
See Figure 2-16 for the configuration of the reaction wheel assemblies. Figure 2-15 FHST Door three fine guidance The more detail later, of a star. pointing make adjustments, the guidance pointing, tional while Chapter the the angular accurate sensors the third of This discussed most function is Two Figure2-16 for posi- stars, called PCS data Computer. uses management the The DF-224 subsystem Reaction discussed in The magnetic the reaction-wheel against reaction _L J_ LI_ : Wheel Assembly pointing computer to control in the calculate 2-13 tum.
It weighs 86 OPERATIONS ! _cOFTWARE HARDWARE% Ii GYRO I ONTROL • INITIATE SAFING • INITIATE SI PAYLOAD SEQUENCE ST LOAD SHEDDING i • REASONABLENESS CHECK ORIENT SEQUENCE SA TO + V3 AXIS I 1 J STOCC COMMAND CAUSES LOSS OF KEEP ALIVES • BATTERY DCHG. >50% FAIL • TWO • SPC LIST EXHAUSTED GYROS FAIL CHECK • NO COMMANDS • MEMORY TESTS FAIL (PARITY ERROR INTERRUPT AND WRITE • FOR PROTECT CPU AND FAIL 100 HOURS I HARDWARE SUN POINT I t + V3 AXIS TO THE SUN) r SUN CHECKS (ENABLE/DISABLE BY STOCC) STOCC COMMAND GRADIENT GRAVITY INERTIAL HOLD • MAGNETIC TORQUER DUTY CYCLE CHECK EXCEEDED SOFTWARE SUN • WHEELSPEED EXCEEDED • BATTERY DISCHARGE >50% ANGLE TO SOLAR ARRAY PERPENDICULARITY CHECK EXCEEDED VIOLATION) TIMING POINT (+ V3 AXIS ORIENT SA TO + V3 AXIS Figure TO THE SUN) _] 2-20 Sating 2-18 40 electronic printed-board circuits with redundant electronics to run the HST even in the case this condi- FOLLOWING • TESTS it.
astronomy - hubble space telescope media guide by nasa