The Rocketdyne AR2, also known by the military designation LR42, was a family of liquid-fuelled rocket engines designed and produced in the United States (US) during the 1950s and 1960s.
The Rocketdyne division of North American Aviation developed a relatively small liquid-fuelled rocket engine for thrust augmentation of manned aircraft during the late 1950s. The AR2 is a single-chamber rocket engine burning kerosene (JP-4 or JP-5) jet fuel, oxidised with 90% High Test Peroxide (H2O2 / HTP), allowing the engine to use the same fuel as an aircraft fuel system.[1] The variable-thrust AR2 is a direct development of the fixed thrust AR1, which was given the military designation LR36.
The AR2-3 had variable-thrust and single lever throttle control, regulating flow of oxidiser to the turbo-pump gas-generator and thus flow of propellants to the combustion chamber.[1]
Operational history
Initial flight trials were carried out attached to the belly of North American F-86F-30-NA Sabre (52-4608 / FU-608) re-designated F-86F(R), boosting performance to a top speed of M1.22 at 60,000 ft (18,288 m).[2]
The AR2-3 was evaluated in 1999 as part of the Future-X Demonstrator Engine project, for possible use in the Boeing X-37 Reusable Upper Stage Vehicle at a thrust of 6,600 lbf (29.34 kN), with a specific impulse of 245 seconds.[3][4]
^ abcWilkinson, Paul H. (1964). Aircraft engines of the World 1964/65 (20th ed.). London: Sir Isaac Pitman & Sons Ltd. p. 40.
^"North American F-86F-30-NA Sabre. (sn 52-4608)-Rocket-assisted take-off". Alamy. Retrieved 15 December 2019.
^ ab. www.astronautix.com. Archived from the original on December 28, 2016. Retrieved 15 December 2019.
^. National Aeronautics and Space Administration. NASA. 24 July 2009. Archived from the original on 21 July 2011. Retrieved 15 December 2019.
^ abWilkinson, Paul H. (1966). Aircraft engines of the World 1966/67 (22nd ed.). London: Sir Isaac Pitman & Sons Ltd. p. 38.
^ abBridgman, Leonard, ed. (1959). Jane's All the World's Aircraft 1959-60. London: Sampson Low, Marston & Co. Ltd.
^Wilkinson, Paul H. (1966). Aircraft engines of the World 1966/67 (22nd ed.). London: Sir Isaac Pitman & Sons Ltd.
February 04, 2023
rocketdyne, also, known, military, designation, lr42, family, liquid, fuelled, rocket, engines, designed, produced, united, states, during, 1950s, 1960s, ar2ar2, installation, lockheed, 104atype, liquid, fuelled, rocket, enginenational, origin, united, statesm. The Rocketdyne AR2 also known by the military designation LR42 was a family of liquid fuelled rocket engines designed and produced in the United States US during the 1950s and 1960s AR2AR2 installation of the Lockheed NF 104AType liquid fuelled rocket engineNational origin United StatesManufacturer RocketdyneFirst run 1950sMajor applications Lockheed NF 104ANorth American F 86F R Contents 1 Design and development 2 Operational history 3 Variants 4 Applications 5 Specifications AR2 3 5 1 General characteristics 5 2 Components 5 3 Performance 6 ReferencesDesign and development EditThe Rocketdyne division of North American Aviation developed a relatively small liquid fuelled rocket engine for thrust augmentation of manned aircraft during the late 1950s The AR2 is a single chamber rocket engine burning kerosene JP 4 or JP 5 jet fuel oxidised with 90 High Test Peroxide H2O2 HTP allowing the engine to use the same fuel as an aircraft fuel system 1 The variable thrust AR2 is a direct development of the fixed thrust AR1 which was given the military designation LR36 The AR2 3 had variable thrust and single lever throttle control regulating flow of oxidiser to the turbo pump gas generator and thus flow of propellants to the combustion chamber 1 Operational history EditInitial flight trials were carried out attached to the belly of North American F 86F 30 NA Sabre 52 4608 FU 608 re designated F 86F R boosting performance to a top speed of M1 22 at 60 000 ft 18 288 m 2 The AR2 3 was evaluated in 1999 as part of the Future X Demonstrator Engine project for possible use in the Boeing X 37 Reusable Upper Stage Vehicle at a thrust of 6 600 lbf 29 34 kN with a specific impulse of 245 seconds 3 4 Variants EditAR 1 YLR36 NA 2 Initial fixed thrust variant 5 AR2 1 YLR42 NA 2 prototype test and development variable thrust engines 6 5 AR2 2 test and development engines 6 AR2 3 Production engines for research and development projects like the NF 104A 7 Applications EditNorth American F 86F R Lockheed NF 104ASpecifications AR2 3 EditData from Astronautix AR2 3 3 and Aircraft engines of the World 1964 65 1 General characteristics Type liquid fuelled rocket engineLength Diameter Dry weight Fuel Kerosene JP 4 JP 5 Oxidiser High test peroxide H2O2 Components Pumps turbopumps driven by High test peroxide H2O2 decomposed by a catalystPerformance Thrust 3 000 lbf 13 34 kN to 6 000 lbf 26 69 kN Combustion chamber temperature 4 600 F 2 811 K 2 538 C Combustion chamber pressure 560 psi 3 861 kPa Specific impulse 245 secondsBurn time References Edit a b c Wilkinson Paul H 1964 Aircraft engines of the World 1964 65 20th ed London Sir Isaac Pitman amp Sons Ltd p 40 North American F 86F 30 NA Sabre sn 52 4608 Rocket assisted take off Alamy Retrieved 15 December 2019 a b AR2 3 www astronautix com Archived from the original on December 28 2016 Retrieved 15 December 2019 Peroxide H2O2 test programs AR2 3 flight certification National Aeronautics and Space Administration NASA 24 July 2009 Archived from the original on 21 July 2011 Retrieved 15 December 2019 a b Wilkinson Paul H 1966 Aircraft engines of the World 1966 67 22nd ed London Sir Isaac Pitman amp Sons Ltd p 38 a b Bridgman Leonard ed 1959 Jane s All the World s Aircraft 1959 60 London Sampson Low Marston amp Co Ltd Wilkinson Paul H 1966 Aircraft engines of the World 1966 67 22nd ed London Sir Isaac Pitman amp Sons Ltd Retrieved from https en wikipedia org w index php title Rocketdyne AR2 amp oldid 1084022622, wikipedia, wiki, book, books, library,
