RCS
Quantity Monitor
The RCS quantity monitor sequence uses the general-purpose computer
to calculate the usable percent of fuel and oxidizer in each RCS
module. The RCS quantities are computed based on the pressure,
volume and temperature method, which requires that pressure and
temperature measurements be combined with a unique set of constants
to calculate the percent remaining in each of the six propellant
tanks. Correction factors are included for residual tank propellant
at depletion, gauging inaccuracy and trapped line propellant.
The computed quantity represents the usable (rather than total)
quantity for each module and makes it possible to determine if
the difference between each pair of tanks exceeds a preset tolerance
(leakage detection).
The calculations include effects of helium gas compressibility,
helium pressure vessel expansion at high pressure, oxidizer vapor
pressure as a function of temperature, and oxidizer and fuel density
as a function of temperature and pressure. The sequence assumes
that helium flows to the propellant tanks to replace propellant
leaving. As a result, the computed quantity remaining in a propellant
tank will be decreased by normal usage, propellant leaks or helium
leaks.
The left, right and forward RCS quantities are displayed to the
flight crew on panel O3. When the rotary switch on panel O3 is
positioned to the RCS fuel or oxid position, the RCS/OMS qty meters
on panel O3 will indicate, in percent, the amount of fuel or oxidizer.
If the switch is positioned to RCS lowest, the gauging system
selects whichever is lower (fuel or oxidizer) for display on the
RCS/OMS prplt qty, left, fwd and right meter.
The left, right and forward RCS quantities also are sent to the
cathode ray tube, and in the event of failures, substitution of
alternate measurements and the corresponding quantity will be
displayed on the CRT. If no substitute is available, the quantity
calculation for that tank is suspended with a fault message.
The sequence also provides automatic closure of the high-pressure
helium isolation valves on orbit when the propellant tank ullage
pressure is above 312 psia. The caution and warning red light
on panel F7 is illuminated for the respective forward, left or
right RCS, and a fault message is sent to the CRT. When the tank
ullage pressure returns below this limit, the close command is
removed.
Exceeding a preset absolute difference of 12.6 percent between
the fuel and oxidizer propellant masses will illuminate the respective
left RCS, right RCS or fwd RCS red caution and warning light on
panel F7; activate the backup caution and warning light; and cause
a fault message to be sent to the CRT. A bias of 12.6 percent
is added when a leak is detected so that subsequent leaks in that
same module may be detected.
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