1. Asketch of a TWThaving characteristics that could be typical of the unit to be flown on the CTSis shownin Fig. 8. The sketch also shows the power Processor electrical interfaces. The linear electron beamthat flows from the cathode to the multi-stage depressed collector (MDC)interacts with the RFinput, and as a result of this interaction, the RFsianal is amplified in the cavity reoion. /l. sketch of an exoerimental model of an outout tube is shownin Figure 9.(1)
2. The power processor will have two power inputs. The main bus from the solar array will supply a minimumof 471 watts at 67 -7 volts. The 28 volt bus will supply 16 watts at 28 -0.3 volts during sunlight for the cathode heater and the instrumentation, and 5 watts of spacecraft battery power at 27 -0.3 volts during eclipse operation for the cathode heater and instrumentation. Forty-six instrumentation measurements and sixteen commandchannels are being provided.
3. a) mechanical (5 Ib box, 6-3/4 x 6-3/4 x 13-3/4
4. The principal on-station environmental disturbance torque is due to solar pressure which is predicted to have a maximumvalue of 1.5 x lQ-5 ft-lbs about the roll and yawaxes. and 0.75 x 10-5 ft-lbs about the pitch axis. For these disturbance torques, pointing errors with the attitude control system in its primary mode, will not exceed -0.1° about the pitch and roll axes, and -1.10 about the yawaxis.