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Rocketdyne AR2

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AR2
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)

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.

Design and development

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]

Variants

AR-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

Specifications (AR2-3)

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

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

  1. ^ a b c Wilkinson, Paul H. (1964). Aircraft engines of the World 1964/65 (20th ed.). London: Sir Isaac Pitman & Sons Ltd. p. 40.
  2. ^ "North American F-86F-30-NA Sabre. (sn 52-4608)-Rocket-assisted take-off". Alamy. Retrieved 15 December 2019.
  3. ^ a b "AR2-3". www.astronautix.com. Retrieved 15 December 2019.
  4. ^ "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.
  5. ^ a b Wilkinson, Paul H. (1966). Aircraft engines of the World 1966/67 (22nd ed.). London: Sir Isaac Pitman & Sons Ltd. p. 38.
  6. ^ a b Bridgman, Leonard, ed. (1959). Jane's All the World's Aircraft 1959-60. London: Sampson Low, Marston & Co. Ltd.
  7. ^ Wilkinson, Paul H. (1966). Aircraft engines of the World 1966/67 (22nd ed.). London: Sir Isaac Pitman & Sons Ltd.
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