By 1993 NSREC SHORT COURSE
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96 1- (1 RI Rz R3 R4)2 - is found (13) for the telemetry subsystem. It is fully subsystem is shown in Figure 50. for the antenna which has a very low failure rate Each operating unit has a spare, so there is 2 for 1 (1 FIT). There is also cross-strapping, so that spare units can redundancy. be used in any combination. D. ). Despun encoder AZ model 1989. TM transmitter A3 — Horn antenna and coupler )q of a telemetry Reprinted I-53 subsystem by permission (Copyof John 1993 NSREC , Command receiver AZ = 1200 Despun decoder — Spinning decoder - As = 2000 - ~ = 2000 Omni antenna A,=l L Www I I L Figure 50 Reliability model of right, Morgan and Gordon, 1989.
The concept and parts of a simple attitude control system are shown in Figure 25. A sensor detects an error in pointing by a sensor, and this is corrected by changing the speed (or axis) of a rotating wheel. If the wheels have reached their limit, thrusters are used to increase (or decrease) their speed. A practical attitude control system must operate with three axes, and have a variety of controls. 01”. Figure 26 shows a block diagram of an attitude control system. A sensor detects any error in pointing, which is corrected by changing the speed (or axis direction) of a rotating wheel.
The body can measurement, then be considered to have “reached” equilibrium. This may take from one to perhaps five time constants, depending on whether a factor of l/e or a factor of 1/100 is required. Thus , determining the temperature for an elapsed time longer than five time constants requires only the steady-state solution. The time constant for a large compact satellite is many hours. When a geostationary satellite goes into a l-hr eclipse the equilibrium temperature is around 70 K, but the satellite never gets close to equilibrium.