Space Shuttle Solid Rocket Booster.The Space Shuttle Solid Rocket Boosters SRBs were the first solid fuel motors to be used for primary propulsion on a vehicle used for human spaceflight1 and provided the majority of the Space Shuttles thrust during the first two minutes of flight.After burnout, they were jettisoned and parachuted into the Atlantic Ocean where they were recovered, examined, refurbished, and reused.AU4juGUS8/hqdefault.jpg' alt='Activation Code For Free Ares Download Program' title='Activation Code For Free Ares Download Program' />The SRBs were the most powerful rocket motors ever flown.Each provided a maximum 1.N 3,1.Rocketdyne F 1.With a combined mass of about 1,1.Shuttle stack at liftoff.The motor segments of the SRBs were manufactured by Thiokol of Brigham City, Utah, which was later purchased by ATK.The prime contractor for most other components of the SRBs, as well as for the integration of all the components and retrieval of the spent SRBs, was USBI, a subsidiary of Pratt and Whitney.This contract was subsequently transitioned to United Space Alliance, a limited liability company joint venture of Boeing and Lockheed Martin.Out of 2.SRBs launched over the Shuttle program, all but four were recovered those from STS 4 due to a parachute malfunction and STS 5.L Challenger disaster.Over 5,0.The final set of SRBs that launched STS 1.STS 1.Recovery also allowed post flight examination of the boosters,5 identification of anomalies, and incremental design improvements.Overviewedit.Solid Rocket Booster SRB separation.The two reusable SRBs provided the main thrust to lift the shuttle off the launch pad and up to an altitude of about 1.While on the pad, the two SRBs carried the entire weight of the external tank and orbiter and transmitted the weight load through their structure to the mobile launch platform.Each booster had a liftoff thrust of approximately 2,8.MN at sea level, increasing shortly after liftoff to about 3,1.MN.They were ignited after the three Space Shuttle Main Engines thrust level was verified.Seventy five seconds after SRB separation, SRB apogee occurred at an altitude of approximately 2.SRBs were recovered.The SRBs helped take the Space Shuttle to an altitude of 2.The SRBs were the largest solid propellant motors ever flown and the first of such large rockets designed for reuse.Each is 1.The SRBs committed the shuttle to liftoff and ascent to orbit flight, without the possibility of launch or liftoffascent abort, until both motors had fully, and simultaneously, fulfilled their functions, consumed their propellants, were producing zero net reaction thrust and had been jettisoned again simultaneously by explosive jettisoning bolts from the remainder of the vehicle launch stack shuttle wengines fueloxidizer tank.Only then could any conceivable set of launch or post liftoff abort procedures be contemplated.In addition, failure of an individual SRBs thrust output or ability to adhere to the designed performance profile was not survivable.Each SRB weighed approximately 1,3.The two SRBs constituted about 6.The propellant for each solid rocket motor weighed approximately 1,1.The inert weight of each SRB was approximately 2.Usage Statistics for communitygaze.Summary Period September 2016 Search String Generated 08Oct2017 0209 PDT.Primary elements of each booster were the motor including case, propellant, igniter and nozzle, structure, separation systems, operational flight instrumentation, recovery avionics, pyrotechnics, deceleration system, thrust vector control system, and range safety destruct system.While the terms solid rocket motor and solid rocket booster are often used interchangeably, in technical use they have specific meanings.The term solid rocket motor applied to the propellant, case, igniter and nozzle.Solid rocket booster applied to the entire rocket assembly, which included the rocket motor as well as the recovery parachutes, electronic instrumentation, separation rockets, range safety destruct system, and thrust vector control.Each booster was attached to the external tank at the SRBs aft frame by two lateral sway braces and a diagonal attachment.The forward end of each SRB was attached to the external tank at the forward end of the SRBs forward skirt.On the launch pad, each booster also was attached to the mobile launcher platform at the aft skirt by four frangible nuts that were severed at lift off.The boosters were composed of seven individually manufactured steel segments.These were assembled in pairs by the manufacturer, and then shipped to Kennedy Space Center by rail for final assembly.The segments were fixed together using circumferential tang, clevis, and clevis pin fastening, and sealed with O rings originally two, changed to three after the Challenger Disaster in 1.ComponentseditHold down postseditEach solid rocket booster had four hold down posts that fit into corresponding support posts on the mobile launcher platform.Install_build/08_extracting.jpg' alt='Activation Code For Free Ares Download Program' title='Activation Code For Free Ares Download Program' />Hold down bolts held the SRB and launcher platform posts together.Each bolt had a nut at each end, the top one being a frangible nut.The top nut contained two NASA standard detonators NSDs, which were ignited at solid rocket motor ignition commands.When the two NSDs were ignited at each hold down, the hold down bolt traveled downward because of the release of tension in the bolt pretensioned before launch, NSD gas pressure and gravity.The bolt was stopped by the stud deceleration stand, which contained sand.The SRB bolt was 2.The frangible nut was captured in a blast container.The solid rocket motor ignition commands were issued by the orbiters computers through the master events controllers to the hold down pyrotechnic initiator controllers PICs on the mobile launcher platform.They provided the ignition to the hold down NSDs.The launch processing system monitored the SRB hold down PICs for low voltage during the last 1.PIC low voltage would initiate a launch hold.Electrical power distributioneditElectrical power distribution in each SRB consisted of orbiter supplied main DC bus power to each SRB via SRB buses labeled A, B and C.Orbiter main DC buses A, B and C supplied main DC bus power to corresponding SRB buses A, B and C.In addition, orbiter main DC bus C supplied backup power to SRB buses A and B, and orbiter 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 orbiter main bus failed.The nominal operating voltage was 2.DC.Hydraulic power unitseditThere were two self contained, independent Hydraulic Power Units HPUs on each SRB.Each HPU consisted of an auxiliary power unit APU, fuel supply module, hydraulicpump, hydraulic reservoir and hydraulic fluid manifold assembly.The APUs were fueled by hydrazine and generated mechanical shaft power to drive a hydraulic pump that produced hydraulic pressure for the SRB hydraulic system.The two separate HPUs and two hydraulic systems were located on the aft end of each SRB between the SRB nozzle and aft skirt.The HPU components were mounted on the aft skirt between the rock and tilt actuators.The two systems operated from T minus 2.SRB separation from the orbiter and external tank.The two independent hydraulic systems were connected to the rock and tilt servoactuators.Free Memory Card Restoration Software '>Free Memory Card Restoration Software . 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