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GOKUL LAKSHMANAN
M.TEC H TH ER MA L A N D FLU ID EN GIN EER IN G
NASA’S SPACE LAUNCH SYSTEM:
AHEAVY-LIFT PLATFORM FOR ENTI...
Contents
 Solid Rocket Booster (SRB)
 SRB testing
 Components
 Operation sequence
 Range safety system
Solid Rocket Booster (SRB)
 2 Solid fuel rocket boosters
used for primary
propulsion
 Provided the majority of
the thrus...
 Burns up to an altitude of about 45 km
 Non - reusable
 Material : Aluminum / Steel and composite materials
 Operatio...
SRB Testing
Components
1. Hold-down posts
 Each solid rocket booster has four hold-down posts
 Hold-down bolts hold the SRB and laun...
2. Electrical power distribution
 DC power is distributed to each SRB via SRB buses
labeled A, B and C
 SLS main DC buse...
3. Hydraulic power units
 Two self-contained, independent Hydraulic Power
Units (HPUs) on each SRB
 HPU consisted of an ...
 Hydrazine is feed into a gas generator. The gas
generator decompose the hydrazine into hot, high-
pressure gas
 A turbi...
 Each HPU is connected to servo actuators
 The hydraulic pump speed was 3600 rpm and
supplied hydraulic pressure of 21.0...
4. Thrust vector control
 Each SRB had two hydraulic servo actuators, to
move the nozzle up/down and side-to-side.
 This...
5. Propellant
Component Description % by weight
Ammonium
Perchlorate
oxidizer 69.6% by weight
Aluminum fuel 16%
Iron oxid...
OPERATION SEQUENCE
1. Ignition
 Ignition can occur only when a manual lock pin from
each SRB has been removed.
 The grou...
 The fire commands
cause the NSDs on the
SRB to fire.
 This ignites a pyro
booster charge.
 The booster charge
ignites ...
 This ignites the solid
rocket propellant along
its entire surface area
instantaneously.
 At t minus zero, the two
SRBs ...
 Separation of the four
explosive bolts on each SRB
is initiated
 The two umbilical cords are
retracted
 The onboard ma...
2. Separation
 The SRBs are jettisoned from SLS at altitude, about
45 km.
 SRB separation is initiated when chamber pres...
 The forward attachment point consists a nut-bolt
system. It contains one NSD pressure cartridge.
 The aft attachment po...
3. Descent and Recovery
 The SRBs are jettisoned
from the SLS at 2 minutes
and an altitude of about 45
km.
 After contin...
 Nose cap separation occurs at a nominal altitude of
5km, about 218 seconds after SRB separation.
 This triggers the par...
SRB Flash Down into Ocean
Range safety system
 A range safety system provides destruction of rocket or
its parts with on-board explosives by remote...
 Two confined detonating fuse manifolds (CDF)
 The NSDs provide the spark to ignite the CDF which
results in booster des...
NASA SLS Solid Rocket Booster - Complete Explanation
NASA SLS Solid Rocket Booster - Complete Explanation
NASA SLS Solid Rocket Booster - Complete Explanation
NASA SLS Solid Rocket Booster - Complete Explanation
NASA SLS Solid Rocket Booster - Complete Explanation
NASA SLS Solid Rocket Booster - Complete Explanation
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NASA SLS Solid Rocket Booster - Complete Explanation

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Solid Rocket Boosters provide the main thrust to lift the rockets off the pad.

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NASA SLS Solid Rocket Booster - Complete Explanation

  1. 1. GOKUL LAKSHMANAN M.TEC H TH ER MA L A N D FLU ID EN GIN EER IN G NASA’S SPACE LAUNCH SYSTEM: AHEAVY-LIFT PLATFORM FOR ENTIRELY NEW MISSIONS
  2. 2. Contents  Solid Rocket Booster (SRB)  SRB testing  Components  Operation sequence  Range safety system
  3. 3. Solid Rocket Booster (SRB)  2 Solid fuel rocket boosters used for primary propulsion  Provided the majority of the thrust during the first two minutes of flight.  Thrust :16000 kN  Burn time 124 seconds  Fuel : Poly-butadiene acrylonitrile, Ammonium perchlorate composite propellant
  4. 4.  Burns up to an altitude of about 45 km  Non - reusable  Material : Aluminum / Steel and composite materials  Operation : Igniting, Steering and Jettison of the boosters
  5. 5. SRB Testing
  6. 6. Components 1. Hold-down posts  Each solid rocket booster has four hold-down posts  Hold-down bolts hold the SRB and launcher platform together  Hold down nuts contains NASA Standard Detonators(NSD) which were ignited at SRB ignition commands  NSD ignite and splits the nut into two or more parts  Hold-down bolt travels downward  Bolt were stopped by the stud deceleration stand which contains sand  The SRB bolt is 710 mm long and 89 mm in diameter
  7. 7. 2. Electrical power distribution  DC power is distributed to each SRB via SRB buses labeled A, B and C  SLS main DC buses A, B and C supplies power to corresponding SRB buses A, B and C.  In addition, SLS main DC bus C supplied backup power to SRB buses A and B, and SLS bus B supplied backup power to SRB bus C.  This electrical power distribution arrangement allowed all SRB buses to remain powered in the event one SLS main bus failed  The nominal operating voltage was 28±4 volts DC.
  8. 8. 3. Hydraulic power units  Two self-contained, independent Hydraulic Power Units (HPUs) on each SRB  HPU consisted of an auxiliary power unit, hydraulic pump, hydraulic reservoir and hydraulic fluid manifold  The APUs were fueled by hydrazine  Generates mechanical shaft power to drive a hydraulic pump that produced hydraulic pressure for the SRB hydraulic system.
  9. 9.  Hydrazine is feed into a gas generator. The gas generator decompose the hydrazine into hot, high- pressure gas  A turbine converted this into mechanical power, driving a gearbox.  The gearbox drive the fuel pump, its own lubrication pump, and the HPU hydraulic pump.  The waste gas from gas generator now cooler and at low pressure, was passed back over the gas generator housing to cool it before being dumped overboard.
  10. 10.  Each HPU is connected to servo actuators  The hydraulic pump speed was 3600 rpm and supplied hydraulic pressure of 21.03 ± 0.34 Mpa  Hydraulic pressure is used to drive Thrust vector controller  The hydraulic system is operated from T minus 28 seconds until SRB separation from the SLS
  11. 11. 4. Thrust vector control  Each SRB had two hydraulic servo actuators, to move the nozzle up/down and side-to-side.  This provided thrust vectoring to help control the vehicle in all three axes (roll, pitch, and yaw).  Each SRB servo actuator consist of four independent, servo valves that receive signals from the drivers.  Each servo valve control one actuator ram and thus nozzle to control the direction of thrust.
  12. 12. 5. Propellant Component Description % by weight Ammonium Perchlorate oxidizer 69.6% by weight Aluminum fuel 16% Iron oxide a catalyst 0.4% Poly butadiene acrylonitrile Serves as a binder that hold the mixture together and acted as secondary fuel 12.04%
  13. 13. OPERATION SEQUENCE 1. Ignition  Ignition can occur only when a manual lock pin from each SRB has been removed.  The ground crew removes the pin during prelaunch activities at T minus five minutes  The solid rocket booster ignition commands are issued when four cryogenic engines are at or above 90% rated thrust  The solid rocket ignition commands were sent by the on-board computers
  14. 14.  The fire commands cause the NSDs on the SRB to fire.  This ignites a pyro booster charge.  The booster charge ignites the propellant in the SRB which fires down the entire vertical length
  15. 15.  This ignites the solid rocket propellant along its entire surface area instantaneously.  At t minus zero, the two SRBs are ignited, under command of the four onboard computers
  16. 16.  Separation of the four explosive bolts on each SRB is initiated  The two umbilical cords are retracted  The onboard master timing unit and event timer are started  The four cryogenic engines are at 100% and the ground launch sequence is terminated and liftoff occurs
  17. 17. 2. Separation  The SRBs are jettisoned from SLS at altitude, about 45 km.  SRB separation is initiated when chamber pressure of both SRBs is less than or equal to 340 kPa.  The SRBs separate from the SLS within 30 milliseconds of the firing command.
  18. 18.  The forward attachment point consists a nut-bolt system. It contains one NSD pressure cartridge.  The aft attachment points consist of three separate struts: upper, diagonal and lower. Each strut contains one bolt with an NSD pressure cartridge at each end.  Detonating the NSD via electrical system separates the SRB’s
  19. 19. 3. Descent and Recovery  The SRBs are jettisoned from the SLS at 2 minutes and an altitude of about 45 km.  After continuing to rise to about 67 km the SRBs begin to fall back to earth  Once back in the atmosphere are slowed by a parachute system to prevent damage on ocean impact
  20. 20.  Nose cap separation occurs at a nominal altitude of 5km, about 218 seconds after SRB separation.  This triggers the parachute to open and SRB falls to ocean  A command is sent from the SNS to the SRB just before separation to apply battery power to the recovery logic network  SRB is recovered by US Navy
  21. 21. SRB Flash Down into Ocean
  22. 22. Range safety system  A range safety system provides destruction of rocket or its parts with on-board explosives by remote command if the rocket is out of control  This limits the danger to people on the ground from crashing pieces, explosions, fire, poisonous substances, etc.  Two RSSs one in each SRB.  Capable of receiving command messages transmitted from the ground station.  The RSS was used only when the shuttle vehicle violates launch trajectory
  23. 23.  Two confined detonating fuse manifolds (CDF)  The NSDs provide the spark to ignite the CDF which results in booster destruction.  The safe and arm device provides mechanical isolation between the NSDs and the CDF before launch and during the SRB separation sequence.

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