Bristol Siddeley Gamma
| Country of origin | Britain |
|---|---|
| Manufacturer | Bristol Siddeley |
| Application | 1st stage booster |
| Predecessor | Armstrong Siddeley Stentor |
| Successor | Gamma 301 |
| Liquid-fuel engine | |
| Propellant | Hydrogen peroxide / kerosene |
| Mixture ratio | 8:1 (approx.) |
| Configuration | |
| Chamber | 4, gimballed in opposed pairs |
| Performance | |
| Thrust (SL) | 16,860 lbf (75.0 kN)[1] |
 Black Knight tail showing engines | |
| Application | 1st stage booster |
|---|---|
| Predecessor | Gamma 201 |
| Successor | Gamma 8 |
| Liquid-fuel engine | |
| Propellant | Hydrogen peroxide / kerosene |
| Mixture ratio | 8:1 (approx.) |
| Configuration | |
| Chamber | 4, gimballed in opposed pairs |
| Performance | |
| Thrust (SL) | 16,860 lbf (75.0 kN)-21,000 lbf (93 kN)[2] |
| Specific impulse | 250 seconds (2.5 km/s) |
| Burn time | 120 seconds |
 Gamma 2 rocket engine, used for the second stage | |
| Application | 2nd stage |
|---|---|
| Predecessor | Gamma 301 |
| Successor | Larch (rocket engine) |
| Liquid-fuel engine | |
| Propellant | Hydrogen peroxide / kerosene |
| Configuration | |
| Chamber | 2, extended |
| Performance | |
| Thrust (SL) | 14,523 lbf (64.60 kN)[3] |
| Burn time | 110–120 seconds |
 Gamma 8 rocket engine on Black Arrow 1st stage | |
| Application | 1st stage booster |
|---|---|
| Predecessor | Gamma 301 |
| Liquid-fuel engine | |
| Propellant | Hydrogen peroxide / kerosene |
| Configuration | |
| Chamber | 8, gimballed in pairs |
| Performance | |
| Thrust (SL) | 52,785 lbf (234.80 kN)[4] |
| Burn time | 125 seconds |
The Armstrong Siddeley, later Bristol Siddeley Gamma was a family of rocket engines used in British rocketry, including the Black Knight and Black Arrow launch vehicles. They burned kerosene fuel and hydrogen peroxide. Their construction was based on a common combustion chamber design, used either singly or in clusters of up to eight.
They were developed by Armstrong-Siddeley in Coventry, which later became Bristol Siddeley in 1959, and finally Rolls-Royce in 1966.[5]
Engine static testing was carried out at High Down Rocket Test Site, near The Needles on the Isle of Wight (50°39′38.90″N 1°34′38.25″W / 50.6608056°N 1.5772917°W).[6][7] (Spadeadam in Cumbria wasn't used for testing until Blue Streak, after Gamma).
Advantages of kerosene / peroxide engines
Use of kerosene / hydrogen peroxide engines has been a particularly British trait in rocket development, there being few comparable engines (such as the LR-40) from the USA.[8]
The combustion of kerosene with hydrogen peroxide is given by the formula
- CH2 + 3H2O2 → CO2 + 4H2O
where CH2 is the approximate formula of kerosene (see RP-1 for a discussion of kerosene rocket fuels). This compares with the combustion of kerosene and liquid oxygen (LOX)
- CH2 + 1.5O2 → CO2 + H2O
showing that the exhaust from kerosene / peroxide is predominantly water. This results in a very clean exhaust (second only to cryogenic LO2/LH2) and a distinctive clear flame.[9] The low molecular mass of water also helps to increase rocket thrust performance.[10]
The oxidiser used with Gamma was 85% high-test peroxide (HTP), H2O2. Gamma used a silver-plated on nickel-gauze catalyst to first decompose the peroxide.[11] For higher concentrations of H2O2 another catalyst would have been required, such as platinum. No ignition source was required since the very hot decomposed H2O2 is hypergolic (will spontaneously combust) with kerosene. Due to the high ratio (8:1) of the mass of H2O2 used compared to the kerosene, and also its superior heat characteristics, the H2O2 may also be used to regeneratively cool the engine nozzle before combustion. Any pre-combustion chamber used to power the pump turbines needs only to decompose H2O2 to provide the energy. This gives the efficiency advantages of closed cycle operation, without its usual major engineering problems.
All of these characteristics lead to kerosene / hydrogen peroxide engines being simpler and more reliable to construct than other liquid propellant chemistries. Gamma had a remarkably reliable service record for a rocket engine. Of the 22 Black Knight and 4 Black Arrow launchers, involving 128 Gamma engines, there were no engine failures.[10]
Stentor
The Gamma began as the smaller cruise chamber of the two-chamber Stentor rocket engine produced by Armstrong-Siddeley for the Blue Steel stand-off missile.[12]
Gamma 201
Bristol-Siddeley developed this stand-alone four-chamber engine from 1955 to 1957 for the Black Knight test vehicles.[13] Gamma 201 was used for the first twelve Black Knight launches (14 in total), Gamma 301 for most of the later flights.[14]
The initial Black Knight vehicles were single-stage rockets designed to test prototype re-entry heads for the proposed Blue Streak strategic ballistic missile. Testing of the Black Knight began at Woomera, Australia in 1958, but the Blue Streak project was cancelled in 1960. The rockets continued to be tested until 1965, as part of a planned two-stage space launcher, using the Gamma 201 for the first stage until August 1962, when it was replaced by the more powerful Gamma 301.[15][16][17][18][19][20][21][22][23][24][25]
Gamma 301
This was basically the same as the Gamma 201, but had automatic mixture-ratio control for improved thrust.[26] There were nine initial test firings of the Gamma 301 engine at High Down from 16 April to 31 May 1957, all of which were largely successful. Black Knight launches BK16 and BK18 used the Gamma 301. These two were the beginning of the Project Dazzle high-speed re-entry vehicle trials, where a solid fuel Cuckoo was mounted pointing downwards in the second stage, so as to increase re-entry speeds. Eight Gamma 301 launches were made in total.[14]
Gamma 2 / Double Gamma
A two chamber version of Gamma, used for the second stage of the Black Arrow satellite launch vehicle. As the only Gamma not required to operate at sea level, the nozzles were extended to allow better expansion.[16][27]
Gamma 8
This was an 8 chamber development of Gamma, used for the first stage of the Black Arrow satellite launch vehicle. Gamma thrust chambers were mounted in pairs radially, each pair on a one-axis tangential gimbal. Collective movement gave roll control, differential movement pitch.[27]
Gallery
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References
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Wikimedia Commons has media related to Bristol Siddeley Gamma. |
- ↑ "Gamma 201". Astronautix.com. Retrieved 2016-11-13.
- ↑ "Gamma 301". Astronautix.com. Retrieved 2016-11-13.
- ↑ "Gamma 2". Astronautix.com. Retrieved 2016-11-13.
- ↑ "Gamma 8". Astronautix.com. Retrieved 2016-11-13.
- ↑ "Rolls-Royce Heritage: Coventry". Archived from the original on 18 May 2008.
- ↑ "High Down testing site".
- ↑ Black Knight Testing at The Needles Archived 27 March 2008 at the Wayback Machine.
- ↑ Hydrogen Peroxide – Optimal For Turbomachinery and Power Applications (PDF). 43rd IAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit. Cincinnati, OH: American Institute of Aeronautics and Astronautics, Inc. July 2007.
- ↑ "Black Arrow". Nicholas Hill., The "levitation" picture, showing the R3 / Prospero launch lifting off on Gamma's invisibly transparent exhaust plume.
- 1 2 Pietrobon, Steven S. (May–June 1999). "High Density Liquid Rocket Boosters for the Space Shuttle" (PDF). J. British Interplanetary Society. 52: 163–168,.
- ↑ D. Andrews & H. Sunley (July 1990). "The Gamma rocket engines for Black Knight". J. British Interplanetary Society. 43: 301–310.
- ↑ "Avro Blue Steel stand-off missile". Archived from the original on 8 February 2004.
- ↑ C.N. Hill (2001). A Vertical Empire: The History of the UK Rocket and Space Programme, 1950–1971. Imperial College Press. ISBN 1-86094-268-7.
- 1 2 "Black Knight Flight Data".
- ↑ "Gamma 201 rocket engine, c. 1957". Science Museum.
- 1 2 "Gamma rocket motor". Archived from the original on 8 May 2008.
- ↑ Harlow, John (1993). Alpha, Beta and RTV-1, The Development of Early British Liquid Propellant Rocket Engines. Congress of the International Astronautical Federation (IAA). Graz, Austria.
- ↑ Harlow, John (November 1999). Hydrogen Peroxide Engines – Early Work on Thermal Ignition at Westcott. International Hydrogen Peroxide Propulsion Conference, Purdue University,. pp. 211–219.
- ↑ Andrews, D.; Sunley, H. (July 1990). "The Gamma Rocket Engines for Black Knight". J. British Interplanetary Society. London. 43 (7): 301–310.
- ↑ Andres & Sunley (1990), pp. 283–290.
- ↑ Harlow, John (20–24 July 1998). Hydrogen Peroxide – A U.K. Perspective. University of Surrey Symposium on Hydrogen Peroxide.
- ↑ Robinson, H. G. R. (July 1990). "Overview of the Black Knight Project: Black Knight, its Genesis". J. British Interplanetary Society. London. 43 (7): 291–296.
- ↑ Scragg, J. (July 1990). "A Contractor's View of the Black Knight Programme". J. British Interplanetary Society. London. 43 (7): 297–300.
- ↑ Harlow, J. (July 1990), "Black Knight Upper Stages", J. British Interplanetary Society, London, Vol. 43, No. 7: 311–316
- ↑ Robinson, H. G. R. (July 1990), "Suggested Developments of Black Knight", J. British Interplanetary Society, London, Vol. 43, No. 7: 317–318
- ↑ H.W.B. Gordon B.A. & L.W. Parkin MSc (February 1964). A Summary of "Black Knight" Flight Data from 1958 to 1962. UK gov. Original may be found in the Public Record Office, Kew (part of AVIA 6 17362), the on-web link is to a precis by Nicholas Hill.
- 1 2 Douglas Millard (2001). Black Arrow rocket: A History of a Satellite Launch Vehicle and its Engines. London: Science Museum. ISBN 1-900747-41-3.
