Hypergolic propellant

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The hypergolic fuel hydrazine being loaded onto the MESSENGER space probe. Note the safety suit the technician is wearing.

A hypergolic rocket propellant combination used in a rocket engine is one where the propellants spontaneously ignite when they come into contact with each other. The two propellant components usually consist of a fuel and an oxidizer. Although hypergolic propellants tend to be difficult to handle because of their extreme toxicity and/or corrosiveness, they can typically be stored as liquids at room temperature and hypergolic engines are easy to ignite reliably and repeatedly.

In contemporary usage, the terms "hypergol" or "hypergolic propellant" usually mean the most common such propellant combination, dinitrogen tetroxide plus hydrazine and/or its relatives monomethyl hydrazine and unsymmetrical dimethylhydrazine.

History[edit]

Soviet rocket engine researcher Valentin Glushko experimented with hypergolic fuel as early as 1931. It was initially used for "chemical ignition" of engines, starting kerosene/nitric acid engines with an initial charge of phosphorus dissolved in carbon disulfide.

Starting in 1935, Prof. O. Lutz of the German Aeronautical Institute experimented with over 1000 self-igniting propellants. He assisted the Walter Company with the development of C-Stoff which ignited with concentrated hydrogen peroxide. BMW developed engines burning a hypergolic mix of nitric acid with various combinations of amines, xylidines and anilines.[1]

Hypergolic propellants were discovered independently, for the third time, in the US by GALCIT and Navy Annapolis researchers in 1940. They developed engines powered by aniline and nitric acid.[2] Robert Goddard, Reaction Motors and Curtiss-Wright worked on aniline/nitric acid engines in the early 1940s, for small missiles and jet assisted take-off (JATO).[3]

In Germany from the mid-1930s through World War II, rocket propellants were broadly classed as monergols, hypergols, non-hypergols and lithergols. The ending ergol is a combination of Greek ergon or work, and Latin oleum or oil, later influenced by the chemical suffix -ol from alcohol.[Note 1] Monergols were monopropellants, while non-hypergols were bipropellants which required external ignition, and lithergols were solid/liquid hybrids. Hypergolic propellants (or at least hypergolic ignition) were far less prone to hard starts than electric or pyrotechnic ignition. The "hypergole" terminology was coined by Dr. Wolfgang Nöggerath, at the Technical University of Brunswick, Germany.[4] The only rocket-powered fighter ever deployed, the Messerschmitt Me 163B Komet, depended on its methanol/hydrazine fueled, high test peroxide consuming HWK 109-509A rocket motor, using its hypergolic propellants for its fast climb and quick-hitting tactics, at the cost of having a supremely volatile power system capable of causing a massive explosion, with any degree of inattention at any time.

The earliest ballistic missiles, such as the Soviet R-7 that launched Sputnik 1 and the US Atlas and Titan-1, used kerosene and liquid oxygen. Although they are preferred in space launchers, the difficulties of storing a cryogen like liquid oxygen in a missile that had to be kept launch ready for months or years at a time led to a switch to hypergolic propellants in the US Titan II and in most Soviet ICBMs such as the R-36.[citation needed] But the difficulties of such corrosive and toxic materials, including leaks and explosions in Titan-II silos, led to their near universal replacement with solid-fuel boosters, first in Western submarine-launched ballistic missiles and then in land-based US and Soviet ICBMs.[5]

The trend among western space launch agencies is away from large hypergolic rocket engines and toward hydrogen/oxygen engines with higher performance. Ariane 1 through 4, with their hypergolic first and second stages (and optional hypergolic boosters on the Ariane 3 and 4) have been retired and replaced with the Ariane 5, which uses a first stage fueled by liquid hydrogen and liquid oxygen. The Titan II, III and IV, with their hypergolic first and second stages, have also been retired. Hypergolic rockets are still widely used in upper stages when multiple burn-coast periods are required.[citation needed]

Characteristics[edit]

Hypergolic propellant tanks of the Orbital Maneuvering System of Space Shuttle Endeavour

Advantages[edit]

Hypergolic rockets are usually simple and reliable because they need no ignition system. Although larger hypergolic engines in some launch vehicles use turbopumps, most hypergolic engines are pressure fed. A gas, usually helium, is fed to the propellant tanks under pressure through a series of check and safety valves. The propellants in turn flow through control valves into the combustion chamber; there, their instant contact ignition prevents a mixture of unreacted propellants from accumulating and then igniting in a potentially catastrophic hard start.

The most common hypergolic fuels, hydrazine, monomethylhydrazine and unsymmetrical dimethylhydrazine, and oxidizer, nitrogen tetroxide, are all liquid at ordinary temperatures and pressures. They are therefore sometimes called storable liquid propellants. They are suitable for use in spacecraft missions lasting many years. The cryogenity of liquid hydrogen and liquid oxygen limits their practical use to space launch vehicles where they need to be stored only briefly.

Because hypergolic rockets do not need an ignition system, they can fire any number of times by simply opening and closing the propellant valves until the propellants are exhausted and are therefore uniquely suited for spacecraft maneuvering and well suited, though not uniquely so, as upper stages of such space launchers as the Delta II and Ariane 5, which must perform more than one burn. Restartable cryogenic (oxygen/hydrogen) rocket engines nevertheless exist, notably the RL-10 on the Centaur and the J-2 on the Saturn V.

Disadvantages[edit]

Relative to their mass, traditional hypergolic propellants are less energetic than such cryogenic propellant combinations as liquid hydrogen / liquid oxygen or liquid methane / liquid oxygen. A launch vehicle that uses hypergolic propellant must therefore carry a greater mass of fuel than one that uses these cryogenic fuels.

The corrosivity, toxicity, and carcinogeneity of traditional hypergolics necessitate expensive safety precautions.

Hypergolic combinations[edit]

Common[edit]

The corrosiveness of nitrogen tetroxide can be reduced by adding several percent nitric oxide (NO), forming mixed oxides of nitrogen (MON).[10]

Less common and obsolete[edit]

Related technology[edit]

Although not hypergolic in the strict sense (but rather pyrophoric), triethylborane, which ignites spontaneously in the presence of air, was used for engine starts in the SR-71 Blackbird, the F-1 engines used in the Saturn V rocket, and the Merlin engines used in the SpaceX Falcon 9 rockets.

Notes[edit]

  1. ^ "-ergol", Oxford English Dictionary

References[edit]

Citations
  1. ^ O. Lutz, in History of German Guided Missiles Development, 1957
  2. ^ Sutton, George P., History of Liquid Propellant Rocket Engines
  3. ^ The Papers of Robert H. Goddard
  4. ^ Botho Stüwe, Peene Münde West, Weltbildverlag ISBN 3-8289-0294-4, 1998 page 220, German
  5. ^ Clark (1972), p.214
  6. ^ Clark (1972), p.45
  7. ^ T.A. Heppenheimer, Development of the Shuttle, 1972–1981. Smithsonian Institution Press, 2002. ISBN 1-58834-009-0.
  8. ^ "Space Launch Report: Ariane 5 Data Sheet". 
  9. ^ "SpaceX Updates — December 10, 2007". SpaceX. 2007-12-10. Retrieved 2010-02-03. 
  10. ^ "ROCKET PROPELLANTS". Retrieved 4 January 2014. 
  11. ^ Brown, Charles D. (2003). Elements of spacecraft design. AIAA. p. 211. ISBN 978-1-56347-524-5. 
  12. ^ "High Test Peroxide" (pdf). Retrieved July 2014. 
Bibliography
  • Clark, John (1972). Ignition! An Informal History of Liquid Rocket Propellants. New Brunswick, New Jersey: Rutgers University Press. p. 14. ISBN 0-8135-0725-1. 
  • Modern Engineering for Design of Liquid-Propellant Rocket Engines, Huzel & Huang, pub. AIAA, 1992. ISBN 1-56347-013-6.
  • History of Liquid Propellant Rocket Engines, G. Sutton, pub. AIAA 2005. ISBN 1-56347-649-5.

External links[edit]