1,360
edits
Space Shuttle Avionics: Difference between revisions
Jump to navigation
Jump to search
→HYD THERMAL (DISP 87)
| Line 488: | Line 488: | ||
This may come as a surprise, but all pressure and temperature readings of the display are real, i.e. reflect the actual simulated thermal state of the hydraulics system. | This may come as a surprise, but all pressure and temperature readings of the display are real, i.e. reflect the actual simulated thermal state of the hydraulics system. | ||
=== PRPLT THERMAL (DISP 89) === | |||
[[File:Shuttle avionics disp89.jpg|600px|PRPLT THERM display of the Space Shuttle avionics]] | |||
The thermal properties of the propellant feedlines for RCS and OMS thrusters can be monitored on DISP 89. It shows various temperature sensor readings distributed across the aft OMS pods and the forward RCS system. The heating elements are supposed to maintain temperatures between 55 and 75 F in the feedlines, temperature readings outside this range indicate a problem and potentially a frozen feedline. The fuel injector temperature is special in that it measures the temperature of the fuel after it has been circulated through the engine nozzle for cooling, hence it reflects the efficiency of OMS engine cooling. During engine operations, it increases and should be around 220 F. | |||
In FG, the temperature readings are all meaningful represent the action of the heating element simulation in combination with the ambient temperature simulation. | |||
=== PDRS CONTROL (SPEC 94) === | === PDRS CONTROL (SPEC 94) === | ||