SRB Ignition
SRB
ignition can occur only when a manual lock pin from each SRB safe
and arm device has been removed. The ground crew removes the pin
during prelaunch activities. At T minus five minutes, the SRB safe
and arm device is rotated to the arm position. The solid rocket
motor ignition commands are issued when the three SSMEs are at or
above 90-percent rated thrust, no SSME fail and/or SRB ignition
PIC low voltage is indicated and there are no holds from the LPS.
The solid rocket motor
ignition commands are sent by the orbiter computers through the
MECs to the safe and arm device NSDs in each SRB. A PIC single-channel
capacitor discharge device controls the firing of each pyrotechnic
device. Three signals must be present simultaneously for the PIC
to generate the pyro firing output. These signals- arm, fire 1
and fire 2-originate in the orbiter general- purpose computers
and are transmitted to the MECs. The MECs reformat them to 28-volt
dc signals for the PICs. The arm signal charges the PIC capacitor
to 40 volts dc (minimum of 20 volts dc).
The fire 2 commands cause
the redundant NSDs to fire through a thin barrier seal down a
flame tunnel. This ignites a pyro booster charge, which is retained
in the safe and arm device behind a perforated plate. The booster
charge ignites the propellant in the igniter initiator; and combustion
products of this propellant ignite the solid rocket motor initiator,
which fires down the length of the solid rocket motor igniting
the solid rocket motor propellant.
The GPC launch sequence
also controls certain critical main propulsion system valves and
monitors the engine- ready indications from the SSMEs. The MPS
start commands are issued by the onboard computers at T minus
6.6 seconds (staggered start- engine three, engine two, engine
one- all approximately within 0.25 of a second), and the sequence
monitors the thrust buildup of each engine. All three SSMEs must
reach the required 90-percent thrust within three seconds; otherwise,
an orderly shutdown is commanded and safing functions are initiated.
Normal thrust buildup
to the required 90-percent thrust level will result in the SSMEs
being commanded to the lift- off position at T minus three seconds
as well as the fire 1 command being issued to arm the SRBs. At
T minus three seconds, the vehicle base bending load modes are
allowed to initialize (movement of approximately 25.5 inches measured
at the tip of the external tank, with movement towards the external
tank).
At T minus zero, the
two SRBs are ignited, under command of the four onboard computers;
separation of the four explosive bolts on each SRB is initiated
(each bolt is 28 inches long and 3.5 inches in diameter); the
two T-0 umbilicals (one on each side of the spacecraft) are retracted;
the onboard master timing unit, event timer and mission event
timers are started; the three SSMEs are at 100 percent; and the
ground launch sequence is terminated.
The solid rocket motor
thrust profile is tailored to reduce thrust during the maximum
dynamic pressure region.
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