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.
| AR2 | |
|---|---|
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| |
| AR2 installation of the Lockheed NF-104A | |
| Type | liquid-fuelled rocket engine |
| National origin | United States |
| Manufacturer | Rocketdyne |
| First run | 1950s |
| Major applications | Lockheed NF-104A North American F-86F(R) |
Design and development edit
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 edit
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]
Variants edit
Applications edit
Specifications (AR2-3) edit
Data from Astronautix : AR2-3 [3] and Aircraft engines of the World 1964/65.[1]
General characteristics
- Type: liquid-fuelled rocket engine
- Length:
- 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 catalyst
Performance
- 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 seconds
- Burn time:
References edit
- ^ a b c Wilkinson, 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.
- ^ 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 & Sons Ltd. p. 38.
- ^ a b Bridgman, 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.
External links edit
Media related to Rocketdyne AR2 at Wikimedia Commons
