EXAMPLE OF DANMOE STRATEGY APPLICATION For this purpose, we will consider the initial Space Station and compare the sizing results using the conventional and new approach in terms of masses of the solar array and batteries, array area, and bus power capabilities. The following assumptions are made: (1) use of flexible array with Si cells and Ni-H^ batteries, (2) system configuration illustrated in Fig. 3 and parameter values in Tables 2 and 3, and (3) 127 w/m2 array power density. Table 5 shows the results of sizing calculation along with the bus power capabilities for the following cases: Note that Cases 1 through 4 above illustrate the effects of increasing the day/night load ratio on P and P„_ as the average bus power (P ) is held constant. The reduction in the battery mass which is proportioned to the reduction in the nighttime load (P^^) is much greater than the decrease in the solar array mass as o is increased. The method indicated in Case 5 is probably the best way of arriving at the system size because day and night loads are more easily definable and useful as system specifications than the values of P and o. o In all cases, the orbital average bus power capability (P ) will vary from the minimum value stated in Table 5 to the maximum value as the eclipse duration varies from 36 minutes to zero. That is, during the continuous-sunlight orbits, Equation (6) reduces to P = K P^. (135 kW for Cases 1 through 4 in Table 5). The DANMOE concept can be effectively applied to a system that has been sized for a constant bus load. Consider Case 1 above for the initial Space Station designed for the constant 75-kW load. If, during the orbital operation, the actual nighttime load is held at 50 kW, the daytime bus power capability would be at least 90.5 kW (see Fig. 11). This capability, of course, can be used only if the Space Station is appropriately designed to utilize that much power during the daytime portion of the orbit.
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