The maximum spacecraft launch mass is $3230$ kg $.$ The required propellant load is $1788$ kg and the pressurant mass is $8$ kg $.$ Make the following calculations for this spacecraft.

$($a$)$ Establish a mass contingency using the AIAA recommendations; use category CW $,$ new spacecraft in the bid phase. Estimate launch vehicle adapter mass. Establish an on$-$orbit dry mass budget for each subsystem.

Partial solution: Structure dry mass budget $\backslash (=239\backslash$mathrm$\{$~kg$\}\backslash ).$

$($b$)$ Prepare a spreadsheet the project might use for a running comparison of subsystem on$-$orbit dry mass budget to the current estimate.

$($c$)$ Estimate the total power requirement for the spacecraft. Set aside power contingency using AIAA recommendations and allocate subsystem power budgets $($power to the loads$).($In this case, add margin on top of the estimated subsystem power. The total power estimate will be used to design the power system; the object is to make sure the power system is big enough. The mass limit is absolute$.)$

Partial solution: Attitude control power budget is $61$ W $.$

$2\mathrm{.}2$ You plan to use an existing, qualified computer in a spacecraft design. It has been qualified for a temperature range of $5$ to $\backslash (62^\{\backslash$circ$\}\backslash$mathrm$\{$C$\}\backslash ).$ What are the thermal control requirements for the computer compartment using the recommended margin requirements $($Fig$.2\mathrm{.}12)?$

Fig. $2\mathrm{.}12$ Recommended thermal margin system.