The XM29 OICW ( Objective Individual Combat Weapon ) was a series of prototypes of a new type of assault rifle that fired 20 mm HE airbursting projectiles . The prototypes were developed as part of the Objective Individual Combat Weapon program in the 1990s. The term SABR ( Selectable Assault Battle Rifle ) was also used at certain points, but is less common.
97-729: Developed by Alliant Techsystems , with Heckler & Koch as a major subcontractor, the most commonly seen version of the XM29 consisted of a semi-automatic 20×28mm smart grenade launcher, an underslung " KE " assault carbine (derived from the HK G36 then in its late developmental stage) firing a standard 5.56×45mm NATO round, and a top-mounted computer-assisted sighting system with integrated laser rangefinder , thermal vision night vision capabilities, and up to 6× optical telescopic sight. Earlier designs used different configurations and setups. The launcher part has been described variously as
194-451: A seismometer and heat flow probe on the surface of Mars to study its early geological evolution. This would bring new understanding of the solar system's terrestrial planets . ATK was awarded a contract to provide its UltraFlex solar arrays for the mission. ATK claims that UltraFlex will provide better performance than typical solar arrays used on spacecraft while accommodating ambitious requirements for low mass and small size. ATK entered
291-514: A consortium to develop a new engine nozzle for the Boeing 787 designed to make its operation more environmentally friendly. The nozzle was made from oxide-oxide ceramic matrix composite (CMC) and tested on the 787 ecoDemonstrator . Boeing's tests show that the nozzle is more heat resistant than previous models and lighter, allowing for potential gains in fuel efficiency. This was the largest part ever made from CMC. The Orion Multi-Purpose Crew Vehicle
388-514: A gearbox. The waste gas, now cooler and at low pressure, was passed back over the gas generator housing to cool it before being dumped overboard. The gearbox drove the fuel pump, its own lubrication pump, and the HPU hydraulic pump. A startup bypass line went around the pump and fed the gas generator using the nitrogen tank pressure until the APU speed was such that the fuel pump outlet pressure exceeded that of
485-502: 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 28 seconds until SRB separation from the orbiter and external tank. The two independent hydraulic systems were connected to
582-571: A launch hold. Electrical 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
679-452: A light semi-automatic 20 mm cannon, a grenade launcher, or an airburst weapon. It poses a classification problem, in that it does not fit neatly into any one category. On one hand, it uses much smaller shells and has a much flatter trajectory than grenade launchers. On the other, while its caliber and velocity is more similar to light cannon, it does share traits with other infantry grenade launchers. Various problems have effectively ended
776-483: 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−5:00, the SRB safe and arm device is rotated to the arm position. The solid rocket motor ignition commands are issued when the three Space Shuttle Main Engines (SSMEs) are at or above 90% of rated thrust, no SSME fail and/or SRB ignition Pyrotechnic Initiator Controller (PIC) low voltage
873-441: A one-inch longer barrel, integral mount to increase first round hit probability by up to 10 percent, and dual recoil system to enhance accuracy and cope with future hotter propellants. It can have a next-round select, linkless feed system. The 30 mm chain gun can fire Mk310 Programmable Air Burst Munition rounds to attack targets in defilade. The United States Army Research, Development and Engineering Command helped enhance
970-440: A predetermined time, an isolating valve would be selected, excluding it from the force-sum entirely. Failure monitors were provided for each channel to indicate which channel had been bypassed, and the isolation valve on each channel could be reset. Each actuator ram was equipped with transducers for position feedback to the thrust vector control system. Within each servoactuator ram was a splashdown load relief assembly to cushion
1067-407: A product of ATK since 2002. The AN/AAR-47 passively detects missiles by their infrared signature, and uses algorithms to differentiate between incoming missiles and false alarms. Newer versions also have laser warning sensors and are capable of detecting a wider range of threats. After processing the nature of the threat, the system gives the pilot an audio and visual warning, and tells the direction of
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#17328018304921164-530: A renovated ammunition production facility at the LCAAP in December 2014. The renovations improved efficiency and quality control. The Army and ATK invested $ 11 million to modernize "Building 65" for the production of 20 millimeter ammunition. These large caliber rounds are usually fired from automatic cannons mounted on ground vehicles and aircraft. Building 65 housed 20 millimeter round production until 1997, when it
1261-654: A rocket or part of it with on-board explosives by remote command if the rocket is out of control, in order to limit the danger to people on the ground from crashing pieces, explosions, fire, poisonous substances, etc. The RSS was only activated once – during the Space Shuttle Challenger disaster (37 seconds after the breakup of the vehicle, when the SRBs were in uncontrolled flight). The shuttle vehicle had two RSS, one in each SRB. Both were capable of receiving two command messages (arm and fire) transmitted from
1358-478: A specific energy density of about 31.0 MJ/kg . The propellant had an 11-pointed star-shaped perforation in the forward motor segment and a double-truncated- cone perforation in each of the aft segments and aft closure. This configuration provided high thrust at ignition and then reduced the thrust by approximately a third 50 seconds after lift-off to avoid overstressing the vehicle during maximum dynamic pressure (max. Q). SRB ignition can occur only when
1455-507: A speed of 3,094 mph (4,979 km/h) along with the main engines. The SRBs committed the shuttle to liftoff and ascent, without the possibility of launch abort, until both motors had fully consumed their propellants and had simultaneously been jettisoned by explosive jettisoning bolts from the remainder of the vehicle. Only then could any conceivable set of launch or post-liftoff abort procedures be contemplated. In addition, failure of an individual SRB's thrust output or ability to adhere to
1552-478: A switching valve that allowed the hydraulic power to be distributed from either HPU to both actuators if necessary. Each HPU served as the primary hydraulic source for one servoactuator, and a secondary source for the other servoactuator. Each HPU possessed the capacity to provide hydraulic power to both servoactuators within 115% operational limits in the event that hydraulic pressure from the other HPU should drop below 2,050 psi (14.1 MPa). A switch contact on
1649-754: A switchover was made from the SRB RGAs to the orbiter RGAs. The SRB RGA rates passed through the orbiter flight aft multiplexers/demultiplexers to the orbiter GPCs. The RGA rates were then mid-value-selected in redundancy management to provide SRB pitch and yaw rates to the user software. The RGAs were designed for 20 missions. Made out of 2-cm-thick D6AC high-strength low-alloy steel . The rocket propellant mixture in each solid rocket motor consisted of ammonium perchlorate ( oxidizer , 69.6% by weight), atomized aluminum powder ( fuel , 16%), iron oxide ( catalyst , 0.4%), PBAN (binder, also acts as fuel, 12.04%), and an epoxy curing agent (1.96%). This propellant
1746-410: A tax-free basis. The spinoff was immediately followed by an all-stock merger of ATK's Aerospace and Defense Groups with Orbital Sciences; Orbital shareholders received ATK common stock as consideration. The combined company was named Orbital ATK Inc. On October 28, 2014, ATK announced that it would be seeking approval of issuance of shares to Orbital stockholders on December 9. ATK responded to news of
1843-646: A warhead for the Guided Multiple Launch Rocket System . The contract includes engineering, manufacturing, and development. ATK's work will focus on system performance, warhead qualification, and producibility. In 2012, ATK was selected by the United States Army to continue operating and maintaining the Lake City Army Ammunition Plant (LCAAP) for an additional seven to ten years. The LCAAP
1940-538: Is 200 rounds per minute. The weapon has an effective range of 3,000 metres (9,800 ft ), depending on the type of ammunition used. The Mk44 Bushmaster II is a 30 mm chain gun also manufactured by ATK. It is a derivative of the 25 mm M242 referenced above and uses 70% of the same parts as the M242. The Mk 44 Bushmaster II is the standard primary armament of the Bionix-II AFV currently in service with
2037-583: Is a spacecraft intended to carry a crew of up to four astronauts to destinations beyond- low Earth orbit . Currently under development by NASA, for launch on the Space Launch System , Orion will facilitate human exploration of the Moon , asteroids and Mars . ATK developed the launch abort motor that sits on top of the Orion capsule. This device would pull the capsule and its crew up and away from
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#17328018304922134-492: Is a United States Army program to develop a precision guidance system for existing 155 mm artillery shells . The prime contractor is Alliant Techsystems and the project team includes Interstate Electronics Corporation. In operation the PGK will screw into the nose of the projectile much like the existing fuze . However, as well as the fuzing function it will provide a GPS guidance package and control surfaces to correct
2231-502: Is a federally owned facility in Independence, Missouri. It was built by Remington Arms in 1941 to manufacture and test small-caliber ammunition for the army. As of July 2007, the plant produced about 1.5 billion rounds of ammunition per year. The LCAAP still tests ammunition and is the largest producer of small-arms ammunition for the U.S. military. ATK has operated the LCAAP since April 2001. The United States Army and ATK opened
2328-553: Is a program to re-integrate the two components. The XM8 was developed in an attempt to meet Increment One requirements. Instead a new program known as Lightweight Small Arms Technologies (LSAT) was begun. Meanwhile, the XM25 25×40mm airburst launcher began development to meet the Increment Two requirements. Increment Three will not be initiated until after One and Two are completed. The OICW Increment One Request for Proposals
2425-474: Is commonly referred to as ammonium perchlorate composite propellant (APCP). This mixture gave the solid rocket motors a specific impulse of 242 seconds (2.37 km/s) at sea level or 268 seconds (2.63 km/s) in a vacuum. Upon ignition, the motor burned the fuel at a nominal chamber pressure of 906.8 psi (6.252 MPa). Aluminum was chosen as a propellant due to high volumetric energy density, and its resilience to accidental ignition. Aluminum has
2522-552: Is designed for deep space operations, including missions to Mars. After ATK finishes testing, avionics will be delivered to NASA's Marshall Space Flight Center . The first launch is expected in 2017. ATK produces composite stringers and frames for the Airbus A350 XWB-1000 variant at its facility in Clearfield, Utah. As of 2014, ATK has delivered more than 10,000 components to Airbus . ATK participated in
2619-400: Is held for four seconds, and SRB thrust drops to less than 60,000 lbf (270 kN). The SRBs separate from the external tank within 30 milliseconds of the ordnance firing command. The forward attachment point consists of a ball (SRB) and socket (External Tank; ET) held together by one bolt. The bolt contains one NSD pressure cartridge at each end. The forward attachment point also carries
2716-574: Is indicated and there are no holds from the Launch Processing System (LPS). The solid rocket motor ignition commands are sent by the orbiter computers through the Master Events Controllers (MECs) to the safe and arm device NASA standard detonators (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
2813-434: Is less than or equal to 50 psi (340 kPa). A backup cue is the time elapsed from booster ignition. The separation sequence is initiated, commanding the thrust vector control actuators to the null position and putting the main propulsion system into a second-stage configuration (0.8 seconds from sequence initialization), which ensures the thrust of each SRB is less than 100,000 lbf (440 kN). Orbiter yaw attitude
2910-470: Is publicly traded and headquartered in Utah. The group provided: ATK's outdoor products brands included: Federal Premium Ammunition , Bushnell , Savage Arms , BLACKHAWK!, Primos, Final Approach, Uncle Mike's, Hoppe's, RCBS , Alliant Powder, CCI , Speer, Champion Targets, Gold Tip Arrows, Weaver Optics, Outers, Bolle, Cebe, and Serengeti. As of 2013, ATK's sporting business accounted for nearly 45 percent of
3007-506: Is used to study carbon dioxide concentrations and distributions in the atmosphere. ATK produced the OCO-2's Variable Conductance Heat Pipes, an important part of its thermal control system, solar arrays, and solar array substrates. InSight is a robotic lander mission to Mars originally planned for launch in March 2016. The mission's objective is to place a stationary lander equipped with
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3104-574: The Atlas V and Delta IV starting in 2014 and continuing into early 2018. There is an option for additional deliveries in 2017 and 2018. ATK will provide fairings, payload adapters and diaphragms, interstages, nose cones, and thermal/aerodynamic protection components. All the structures will be produced at ATK's Large Structures Center of Excellence in Iuka, Mississippi . ATK produces avionics for NASA's Space Launch System program. The Space Launch System
3201-864: The Singapore Army , the KTO Rosomak in Polish service as well as that of the CV90 AFVs in Finnish , Norwegian and Swiss service. Some United States Navy vessels, such as the new San Antonio -class amphibious transport dock are armed with the Bushmaster II for surface threat defense. The XM813 Bushmaster, also produced by ATK Defense, is based on the Mk44 and is offered as an upgrade for M1126 Stryker and M2 Bradley . Improvements include
3298-589: The Air Force occurred due to concerns about whether the RD-180 would be available in the future due to increasing tensions with Russia. The Graphite-Epoxy Motor (GEM) is a solid rocket motor produced by ATK using epoxy composite casing . GEMs are used as boosters for the Delta II , Delta III , and Delta IV launch vehicles . The use of composite materials allows for booster casings several times lighter than
3395-584: The Atlantic Ocean, where they were recovered , examined, refurbished, and reused . The Space Shuttle SRBs were the most powerful solid rocket motors to ever launch humans. The Space Launch System (SLS) SRBs, adapted from the shuttle, surpassed it as the most powerful solid rocket motors ever flown, after the launch of the Artemis 1 mission in 2022. Each Space Shuttle SRB provided a maximum 14.7 MN (3,300,000 lbf ) thrust, roughly double
3492-604: The Delta II rocket as a subcontractor for the United Launch Alliance. As of June 2014, ATK has produced 987 solid rocket boosters for Delta II missions. These strap-on boosters, known as GEM-40s, add 434,000 pounds to the Delta II's maximum thrust. The GEM-40s can be used in groups of three, four, and nine depending on the weight of the payload. The composite structures supplied by ATK increase performance by reducing weight. In addition to composite booster cases for
3589-638: The FA-18C/D, FA-18E/F, EA-18G, and Tornado ECR aircraft and later on the F-35 . The AGM-88E development program was proceeded on schedule and did not exceed its budget. In August 2014, the United States Navy awarded a full-rate production contract to ATK to produce to AARGM. Under this contract ATK will also provide captive air training missiles for both the United States and Italy. This is
3686-606: The GEM-40s, ATK produces a 10-foot wide composite payload fairing that covers and protects satellites during launch. ATK also produces the titanium diaphragm propellant tanks and pressurant tank for each Delta II vehicle. ATK produces Graphite Epoxy Motors and numerous other components for the Delta IV rocket. For example, for the Delta IV that carried the Wideband Global SATCOM satellite (WGS-6) into orbit for
3783-567: The PIC to generate the pyro firing output. These signals, arm, fire 1 and fire 2, originate in the orbiter general-purpose computers (GPCs) 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 GPC launch sequence also controls certain critical main propulsion system valves and monitors
3880-547: The PMBSS holds the telescope's main instruments, including its mirrors. The BSF was designed and manufactured at ATK's facilities in Magna, Utah. ATK designed and fabricated more than 10,000 parts for the PMBSS. PMBSS is made primarily of lightweight graphite, but numerous other materials including invar , titanium , and other composite materials were used. ATK produces Graphite Epoxy Motors (GEM) and largest composite fairings for
3977-424: The SRB. The solid rocket motor ignition commands were issued by the orbiter's 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 16 seconds before launch. PIC low voltage would initiate
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4074-486: The SRBs from the external tank. The solid rocket motors in each cluster of four are ignited by firing redundant NSD pressure cartridges into redundant confined detonating fuse manifolds. The separation commands issued from the orbiter by the SRB separation sequence initiate the redundant NSD pressure cartridge in each bolt and ignite the BSMs to effect a clean separation. A range safety system (RSS) provides for destruction of
4171-487: The SRBs, as well as for the integration of all the components and retrieval of the spent SRBs, was USBI, a subsidiary of Pratt & Whitney . The contract was subsequently transitioned to United Space Alliance , a joint venture of Boeing and Lockheed Martin . Out of 270 SRBs launched over the Shuttle program, all but four were recovered – those from STS-4 (due to a parachute malfunction) and STS-51-L ( terminated by
4268-528: The Sporting Group to create Vista Outdoor and the merger leading to the creation of Orbital ATK were completed on February 9, 2015. The companies began operations as separate entities on February 20, 2015. Orbital ATK was bought by Northrop Grumman in 2018. ATK was launched as an independent company in 1990 after Honeywell spun off its defense businesses to shareholders. The former Honeywell businesses had supplied defense products and systems to
4365-528: The Sporting Group to create Vista Outdoor and the merger leading to the creation of Orbital ATK were completed on February 9, 2015; both companies began operations as separate entities on February 20, 2015. Orbital ATK was bought by Northrop Grumman in June 2018. In July 2022, Northrop CEO Kathy Warden was forced to deny reports that the Federal Trade Commission (FTC) would break up
4462-562: The U.S. Air Force, ATK supplied the interstage connector that linked the Common Booster Core and the cryogenic second stage, a centerbody that connects the liquid oxygen tank to liquid hydrogen tanks, a thermal shield for the RS-68 engine, the composite payload fairing, and numerous pieces of hardware for securing the payload. The Orbiting Carbon Observatory 2 (OCO-2) is an American environmental science satellite. The spacecraft
4559-549: The U.S. and its allies for 50 years, including the first electronic autopilot for the B-17 aircraft's bombing missions during World War II. In 1995, ATK entered the aerospace market with the acquisition of the Hercules Aerospace Co., a division of Hercules Inc. Since then ATK has become a supplier of aerospace and defense products to the U.S. government and its allies, and to their contractors. It also carries on
4656-500: The XM813 mainly for safety and turret integration. By changing five parts, the gun caliber can be increased to 40 mm. As of November 2013, the XM813 was being tested at Aberdeen Proving Ground . ATK's Sporting Group offered products under several brands for sport-shooting enthusiasts, police, and military customers around the world. In 2015, this group was spun off to form the independent company, Vista Outdoor Inc. Vista Outdoor
4753-569: The acquisition of the ammunition businesses of Blount International. This acquisition made ATK the nation's largest manufacturer of ammunition. In 2009, ATK acquired Eagle Industries and in 2010 ATK acquired Blackhawk Industries Products Group Unlimited, LLC, diversifying into the security and law enforcement market. On 29 April 2014, ATK announced that its board unanimously approved a plan to create two independent, public companies composed of ATK's current businesses and Orbital Sciences Corporation. ATK spun off its Sporting Group to ATK shareholders on
4850-423: The bypass line, at which point all the fuel was supplied to the fuel pump. When the APU speed reached 100%, the APU primary control valve closed, and the APU speed was controlled by the APU controller electronics. If the primary control valve logic failed to the open state, the secondary control valve assumed control of the APU at 112% speed. Each HPU on an SRB was connected to both servoactuators on that SRB by
4947-489: The commands to each servoactuator of the main engines and SRBs. Four independent flight control system channels and four ATVC channels controlled six main engine and four SRB ATVC drivers, with each driver controlling one hydraulic port on each main and SRB servoactuator. Each SRB servoactuator consisted of four independent, two-stage servovalves that received signals from the drivers. Each servovalve controlled one power spool in each actuator, which positioned an actuator ram and
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#17328018304925044-731: The company a $ 50 million contract to complete engineering development and risk reduction tests as part of the Advanced Concept Booster Development for the Space Launch System (SLS). In April 2014, ATK received a contract from the United Launch Alliance , worth $ 178 million, to produce composite structures for the United States Air Force's Evolved Expendable Launch Vehicle program. ATK will deliver parts for
5141-469: The company's revenue. Space Shuttle Solid Rocket Booster The Space Shuttle Solid Rocket Booster ( SRB ) was the first solid-propellant rocket to be used for primary propulsion on a vehicle used for human spaceflight . A pair of them provided 85% of the Space Shuttle 's thrust at liftoff and for the first two minutes of ascent. After burnout, they were jettisoned, and parachuted into
5238-1006: The competition to replace the Russian-made rocket engine on the Atlas V rocket in September 2014. The Atlas V is used to launch most U.S. military satellites. ATK entered the competition in response to a request for proposals from the Air Force Space and Missile Defense Center issued in 2013 for the RD-180 rocket engine. ATK already supplies rocket engines used in heavier version of the Atlas V. ATK says that solid rocket motors are more reliable and deliver more thrust. ATK said, "Solid rocket motors are optimal for first-stage performance as they provide high lift-off thrust, allowing for more payload margin. They also require less ground and launch infrastructure, resulting in fewer launch scrubs." The RD-180 engines use kerosene for fuel. The request from
5335-520: The designed performance profile was probably not survivable. The SRBs were the largest solid-propellant motors ever flown and the first of such large rockets designed for reuse. Each is 149.16 ft (45.46 m) long and 12.17 ft (3.71 m) in diameter. Each SRB weighed approximately 1,300,000 lb (590 t) at launch. The two SRBs constituted about 69% of the total lift-off mass. The primary propellants were ammonium perchlorate ( oxidizer ) and atomized aluminum powder ( fuel ), and
5432-511: The engine ready indications from the SSMEs. The MPS start commands are issued by the onboard computers at T−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% thrust within three seconds; otherwise, an orderly shutdown is commanded and safing functions are initiated. Normal thrust buildup to
5529-474: The event one orbiter main bus failed. The nominal operating voltage was 28 ± 4 volts DC. There were two self-contained, independent Hydraulic Power Units (HPUs) on each SRB, used to actuate the thrust vector control (TVC) system. Each HPU consisted of an auxiliary power unit (APU), fuel supply module, hydraulic pump , hydraulic reservoir and hydraulic fluid manifold assembly. The APUs were fueled by hydrazine and generated mechanical shaft power to drive
5626-424: The explosion occurred before ignition of the second stage. On November 17, 2014 ATK stated that its due-diligence assessment of its merger with Orbital Sciences undertaken in response to the failure of Orbital's Antares rocket found that the transaction remained in the best interest of its shareholders. Both firms rescheduled shareholder votes on the merger from December 9, 2014 to January 27, 2015. The spinoff of
5723-423: The explosion of a rocket built by Orbital in an earnings call . ATK stated it would conduct a "thorough evaluation of any potential implications resulting from the incident, including current operating plans, long-term strategies, and the proposed transaction". ATK also said that it was taking a careful look at its Castor 30XL motor, which is used in the second stage of Orbital's Antares rocket. ATK further noted that
5820-401: The flight deck aboard the orbiter), as the flight reference computers translate navigation commands (steering to a particular waypoint in space, and at a particular time) into engine and motor nozzle gimbal commands, which orient the vehicle about its center of mass. As the forces on the vehicle change due to propellant consumption, increasing speed, changes in aerodynamic drag, and other factors,
5917-469: The flight of the shell. This is analogous to the addition of a Joint Direct Attack Munition (JDAM) tail-kit to a dumb iron bomb, creating a precision guided munition . Production started in 2009. The M242 Bushmaster is a 25 mm (25×137mm) chain-fed autocannon . It is used extensively by the United States and NATO forces in ground combat vehicles and watercraft. Originally, the weapon
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#17328018304926014-476: The flight stack (orbiter, external tank, SRBs) over onto the external tank. That rotating moment is initially countered by the hold-bolts. Prior to release of the vehicle stack for liftoff, the SRBs must simultaneously ignite and pressurize their combustion chambers and exhaust nozzles to produce a thrust-derived, net counter-rotating moment exactly equal to the SSME's rotating moment. With the SRBs reaching full thrust,
6111-407: The force to expel (positive expulsion) the fuel from the tank to the fuel distribution line, maintaining a positive fuel supply to the APU throughout its operation. In the APU, a fuel pump boosted the hydrazine pressure and fed it to a gas generator. The gas generator catalytically decomposed the hydrazine into hot, high-pressure gas; a two-stage turbine converted this into mechanical power, driving
6208-411: The ground launch sequence is terminated. Timing sequence referencing in ignition is critical for a successful liftoff and ascent flight. The explosive hold-down bolts relieve (through the launch support pedestals and pad structure) the asymmetric vehicle dynamic loads caused by the SSME ignition and thrust buildup, and applied thrust bearing loads. Without the hold-down bolts the SSMEs would violently tip
6305-430: The hold-down bolts are blown, releasing the vehicle stack, the net rotating moment is zero, and the net vehicle thrust (opposing gravity) is positive, lifting the orbiter stack vertically from the launch pedestal, controllable through the coordinated gimbal movements of the SSMEs and the SRB exhaust nozzles. During ascent, multiple all-axis accelerometers detect and report the vehicle's flight and orientation (referencing
6402-402: The hold-down stud. The stud traveled downward because of the release of tension in the stud (pretensioned before launch), NSD gas pressure and gravity. The stud was stopped by the stud deceleration stand, which contained sand. The hold-down stud was 28 in (710 mm) long and 3.5 in (89 mm) in diameter. The frangible nut was captured in a blast container mounted on the aft skirt of
6499-442: The incoming threat. It also sends a signal to the aircraft's infrared countermeasures system, which can then for example deploy flares. The development of the original AN/AAR-47(V)1 began in 1983 by Loral. ATK became a second production source in the mid 90s and eventually became the primary contractor. In 1998 ATK began production of the improved AN/AAR-47(V)2, which added laser warning functionality. The Precision Guidance Kit (PGK)
6596-578: The manufacture and sale of the Hercules gunpowder lines. In 2001, ATK acquired Thiokol , renaming it ATK Launch Systems in 2006, though it is still known within the industry by its original name. Thiokol was the sole manufacturer of the reusable Solid Rocket Motor used to launch the NASA Space Shuttle , which is being adapted for NASA's Space Launch System . Also in 2001, ATK entered the sporting and law enforcement ammunition market with
6693-479: 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 1986) and heat-resistant putty. Each solid rocket booster had four hold-down posts that fit into corresponding support posts on
6790-518: The merger. ATK's Aerospace Group covered space, defense and commercial aerospace products and capabilities. The group offered propulsion for space exploration, commercial launch vehicles and strategic and missile defense. ATK Aerospace was headquartered in Magna, Utah . It also specialized in: In November 2010, ATK was selected by NASA for potential contracts in heavy lift launch vehicle systems and other propulsion technologies. In 2012, NASA awarded
6887-411: The mobile launcher platform. Hold-down studs held the SRB and launcher platform posts together. Each stud had a nut at each end, the top one being a frangible nut . The top nut contained two explosive charges initiated by NASA standard detonators (NSDs), which were ignited at solid rocket motor ignition commands. When the two NSDs were ignited at each hold down, the frangible nut fractured, releasing
6984-498: The most powerful single- combustion chamber liquid-propellant rocket engine ever flown, the Rocketdyne F-1 . With a combined mass of about 1,180 t (1,160 long tons; 1,300 short tons), they comprised over half the mass of the 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
7081-467: The nozzle at water splashdown and prevent damage to the nozzle flexible bearing. Each SRB contained three rate gyro assemblies (RGAs), with each RGA containing one pitch and one yaw gyro. These provided an output proportional to angular rates about the pitch and yaw axes to the orbiter computers and guidance, navigation and control system during first-stage ascent flight in conjunction with the orbiter roll rate gyros until SRB separation. At SRB separation,
7178-432: The nozzle rock and tilt servoactuators . The HPU controller electronics were located in the SRB aft integrated electronic assemblies (IEAs ) on the aft external tank attach rings. The HPUs and their fuel systems were isolated from each other. Each fuel supply module (tank) contained 22 lb (10.0 kg) of hydrazine. The fuel tank was pressurized with gaseous nitrogen at 400 psi (2.8 MPa ), which provided
7275-417: The nozzle to control the direction of thrust. The four servovalves operating each actuator provided a force-summed majority-voting arrangement to position the power spool. With four identical commands to the four servovalves, the actuator force-sum action prevented, instantaneously, a single erroneous input affecting power ram motion. If differential-pressure sensing detected the erroneous input persisting over
7372-405: The program as it was originally envisioned, including weight, bulk, and lack of effectiveness of the 20×28 mm airburst round. Upon cancellation in 2004, it was split into three related programs. OICW Increment One is a program to develop a family of light kinetic energy weapons, OICW Increment Two is a program to develop the airburst grenade launcher as a standalone component, and OICW Increment Three
7469-477: The range during the Challenger disaster ). Over 5,000 parts were refurbished for reuse after each flight. The final set of SRBs that launched STS-135 included parts that had flown on 59 previous missions, including STS-1 . Recovery also allowed post-flight examination of the boosters, identification of anomalies, and incremental design improvements. The two reusable SRBs provided the main thrust to lift
7566-542: The range safety system cross-strap wiring connecting each SRB Range Safety System (RSS) and the ET RSS with each other. 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. The upper strut also carries the umbilical interface between its SRB and the external tank and on to the orbiter. There are four booster separation motors (BSMs) on each end of each SRB. The BSMs separate
7663-415: 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 entire vertical length of the solid rocket motor igniting
7760-442: The required 90% thrust level will result in the SSMEs being commanded to the lift off position at T−3 seconds as well as the fire 1 command being issued to arm the SRBs. At T−3 seconds, the vehicle base bending load modes are allowed to initialize (referred to as the "twang", movement of approximately 25.5 in (650 mm) measured at the tip of the external tank, with movement towards the external tank). The fire 2 commands cause
7857-529: The rocket in the event of major fault on the launch pad or during ascent. ATK also developed numerous composite parts that provide heat protection for Orion. ATK worked with Northrop Grumman to produce the backplane support frame (BSF) for the James Webb Space Telescope. The BSF, center section, and wings form what is called the primary mirror backplane support system (PMBSS). The BSF is the primary load-bearing structure during launch and
7954-495: The shuttle off the launch pad and up to an altitude of about 150,000 ft (28 mi; 46 km). 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 launcher platform . Each booster had a liftoff thrust of approximately 2,800,000 pounds-force (12 MN ) at sea level, increasing shortly after liftoff to about 3,300,000 lbf (15 MN). They were ignited after
8051-418: The solid rocket motor propellant along its entire surface area instantaneously. At T−0, the two SRBs are ignited, under command of the four onboard computers; separation of the four explosive bolts on each SRB is initiated; 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%; and
8148-486: The steel casings of the Castor 4 solid rocket motors they replaced. The first flight of a GEM occurred in 1990 on a Delta II 7925. ATK's Defense Group produced ammunition, precision and strike weapons, missile-warning solutions and tactical rocket motors across air, sea and land-based systems. ATK Defense Group develops products and services for: As of April 2014, ATK had a three-year contract with Lockheed to develop
8245-495: The switching valve closed when the valve was in the secondary position. When the valve was closed, a signal was sent to the APU controller, that inhibited the 100% APU speed control logic and enabled the 112% APU speed control logic. The 100-percent APU speed enabled one APU/HPU to supply sufficient operating hydraulic pressure to both servoactuators of that SRB. The APU 100-percent speed corresponded to 72,000 rpm, 110% to 79,200 rpm, and 112% to 80,640 rpm. The hydraulic pump speed
8342-468: 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
8439-527: The third contract for the AARGM won by ATK and it is worth $ 96.2 million. The AN/AAR-47 Missile Approach Warning System (MWS) is used on slow moving aircraft such as helicopters and military transport aircraft to notify the pilot of threats and to trigger the aircraft's countermeasures systems. Its main users are the U.S. Army, Navy and Air Force, but is also operated by other countries. Originally developed by Loral Space & Communications , it has been solely
8536-511: The three RS-25 main engines' thrust level was verified. Seventy-five seconds after SRB separation, SRB apogee occurred at an altitude of approximately 220,000 ft (42 mi; 67 km); parachutes were then deployed and impact occurred in the ocean approximately 122 nautical miles (226 km ) downrange, after which the two SRBs were recovered. The SRBs helped take the Space Shuttle to an altitude of 28 miles (45 km) and
8633-507: The total propellant for each solid rocket motor weighed approximately 1,100,000 lb (500 t) (see § Propellant ). The inert weight of each SRB was approximately 200,000 pounds (91 t). 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
8730-404: The vehicle automatically adjusts its orientation in response to its dynamic control command inputs. The SRBs are jettisoned from the space shuttle at an altitude of about 146,000 ft (45 km). SRB separation is initiated when the three solid-rocket motor-chamber pressure transducers are processed in the redundancy-management middle-value select and the head-end chamber pressure of both SRBs
8827-502: The vehicle in all three axes (roll, pitch, and yaw). The ascent thrust vector control portion of the flight control system directed the thrust of the three shuttle main engines and the two SRB nozzles to control shuttle attitude and trajectory during lift-off and ascent. Commands from the guidance system were transmitted to the Ascent Thrust Vector Control (ATVC) drivers, which transmitted signals proportional to
8924-470: Was 3,600 rpm and supplied hydraulic pressure of 3,050 ± 50 psi (21.03 ± 0.34 MPa). A high pressure relief valve provided overpressure protection to the hydraulic system and relieved at 3,750 psi (25.9 MPa). The APUs/HPUs and hydraulic systems were reusable for 20 missions. Each SRB had two hydraulic gimbal servoactuators, to move the nozzle up/down and side-to-side. This provided thrust vectoring to help control
9021-472: Was an American aerospace and arms manufacturer headquartered in Arlington County, Virginia . The company operated across 22 states, Puerto Rico , and internationally. ATK revenue in fiscal year 2014 was about US$ 4.8 billion. On April 29, 2014, ATK announced that it would spin off its Sporting Group and merge its Aerospace and Defense Groups with Orbital Sciences Corporation . The spinoff of
9118-508: Was attached to the external tank at the SRB's 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 SRB's forward skirt. On the launch pad, each booster also was attached to the mobile launcher platform at the aft skirt by four holddown studs, with frangible nuts that were severed at liftoff. The boosters were composed of seven individually manufactured steel segments. These were assembled in pairs by
9215-521: Was cancelled in October 2005, while development of the 25×40mm XM25 continued, and the 25×59mm OCSW program as well until its termination. It is not clear if LSAT is intended to meet the goals of OICW Increment One or if it is a standalone weapon system. However, for all intents and purposes, the OICW program is no longer under development. Alliant Techsystems Alliant Techsystems Inc. ( ATK )
9312-590: Was designed and manufactured by McDonnell Douglas . It is an externally powered, chain driven, single-barrel weapon which may be fired in semi-automatic, burst, or automatic modes. It is fed by a metallic link belt and has dual-feed capability. The term "chain gun" derives from the use of a roller chain that drives the bolt back and forth. The gun can destroy lightly armored vehicles and aerial targets, such as helicopters and slow-flying aircraft. It can also suppress enemy positions such as exposed troops, dug-in positions, and occupied built-up areas. The standard rate of fire
9409-503: Was moved to Building 3. About 50 people are employed on this line. The AGM-88E Advanced Anti-Radiation Guided Missile (AARGM) is an upgrade to the AGM-88 High-speed Anti-Radiation Missile (HARM). The AARGM is the result of cooperation between the United States and Italy. It is produced by ATK. In September 2013, ATK delivered the 100th AARGM to the U.S. Navy. It will be initially integrated onto
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