A hypergolic propellant is a rocket propellant combination used in a rocket engine , whose components spontaneously ignite when they come into contact with each other.
25-609: The Orbital Maneuvering System ( OMS ) is a system of hypergolic liquid-propellant rocket engines used on the Space Shuttle and the Orion MPCV . Designed and manufactured in the United States by Aerojet , the system allowed the orbiter to perform various orbital maneuvers according to requirements of each mission profile: orbital injection after main engine cutoff, orbital corrections during flight, and
50-412: A fuel and an oxidizer . The main advantages of hypergolic propellants are that they can be stored as liquids at room temperature and that engines which are powered by them are easy to ignite reliably and repeatedly. Common hypergolic propellants are difficult to handle due to their extreme toxicity or corrosiveness . In contemporary usage, the terms "hypergol" and "hypergolic propellant" usually mean
75-499: A 29,000-kilogram (64,000 lb) payload. It was never built, but to augment the OMS an OMS Payload Bay Kit was proposed. It would have used one, two or three sets of OMS tanks, installed in the payload bay, to provide an extra 150 m/s, 300 m/s or 450 m/s( (500 ft, 1000 ft/s or 1500 ft/s) of delta-V to the orbiter. The orbiter control panels had related switches and gauges but they were nonfunctional. Following
100-424: A density of 1.55 g/ml and 1.45 g/ml respectively. LH2 fuel offers extremely high performance, yet its density only warrants its usage in the largest of rocket stages, while mixtures of hydrazine and UDMH have a density at least ten times higher. This is of great importance in space probes , as the higher propellant density allows the size of their propellant tank to be reduced significantly, which in turn allows
125-415: A hypergolic mix of nitric acid with various combinations of amines, xylidines and anilines . Hypergolic propellants were discovered independently, for the second time, in the U.S. by GALCIT and Navy Annapolis researchers in 1940. They developed engines powered by aniline and red fuming nitric acid (RFNA). Robert Goddard , Reaction Motors , and Curtiss-Wright worked on aniline/nitric acid engines in
150-566: Is 1.65-to-1, The expansion ratio of the nozzle exit to the throat is 55-to-1, and the chamber pressure of the engine is 8.6 bar. The dry weight of each engine is 118kg (260lb). Each engine could be reused for 100 missions and was capable of a total of 1,000 starts and 15 hours of burn time. These pods also contained the Orbiter's aft set of reaction control system (RCS) engines, and so were referred to as OMS/RCS pods. The OM engine and RCS both burned monomethylhydrazine (MMH) as fuel, which
175-457: 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 . As hypergolic rockets do not need an ignition system, they can fire any number of times by simply opening and closing
200-754: The J-2 on the Saturn V . The RP-1 /LOX Merlin on the Falcon 9 can also be restarted. 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 has so far limited their practical use to space launch vehicles where they need to be stored only briefly. As
225-536: The Abort to Orbit procedure. The OMS consists of two pods mounted on the orbiter's aft fuselage, on either side of the vertical stabilizer . Each pod contains a single AJ10-190 engine, based on the Apollo Service Module 's Service Propulsion System engine, which produces 26.7 kilonewtons (6,000 lb f ) of thrust with a specific impulse ( I sp ) of 316 seconds. The oxidizer-to-fuel ratio
250-789: 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 for the Atlas V (RP-1/oxygen) and Delta IV (hydrogen/oxygen). Hypergolic propellants are still used in upper stages, when multiple burn-coast periods are required, and in launch escape systems . Hypergolically-fueled rocket engines 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 ,
275-521: The Soviet R-7 that launched Sputnik 1 and the U.S. 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 U.S. Titan II and in most Soviet ICBMs such as the R-36 . But
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#1732772646369300-637: The aniline. 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 . 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
325-798: The cost of being very volatile and capable of exploding with any degree of inattention. Other proposed combat rocket fighters like the Heinkel Julia and reconnaissance aircraft like the DFS 228 were meant to use the Walter 509 series of rocket motors, but besides the Me 163, only the Bachem Ba 349 Natter vertical launch expendable fighter was ever flight-tested with the Walter rocket propulsion system as its primary sustaining thrust system for military-purpose aircraft. The earliest ballistic missiles , such as
350-524: The deadliest rocketry accident in history, the Nedelin catastrophe . Common hypergolic propellant combinations include: Less-common or obsolete hypergolic propellants include: Pyrophoric substances, which ignite spontaneously in the presence of air, are also sometimes used as rocket fuels themselves or to ignite other fuels. For example a mixture of triethylborane and triethylaluminium (which are both separately and even more so together pyrophoric),
375-570: The difficulties of such corrosive and toxic materials, including injury-causing leaks and the explosion of a Titan-II in its silo, led to their near universal replacement with solid-fuel boosters, first in Western submarine-launched ballistic missiles and then in land-based U.S. and Soviet ICBMs. The Apollo Lunar Module , used in the Moon landings , employed hypergolic fuels in both the descent and ascent rocket engines. The Apollo spacecraft used
400-457: The early 1940s, for small missiles and jet assisted take-off ( JATO ). The project resulted in the successful assisted take off of several Martin PBM and PBY bombers, but the project was disliked because of the toxic properties of both fuel and oxidizer, as well as the high freezing point of aniline. The second problem was eventually solved by the addition of small quantities of furfuryl alcohol to
425-559: The final deorbit burn for reentry . From STS-90 onwards the OMS were typically ignited part-way into the Shuttle's ascent for a few minutes to aid acceleration to orbital insertion. Notable exceptions were particularly high-altitude missions such as those supporting the Hubble Space Telescope (STS-31) or those with unusually heavy payloads such as Chandra (STS-93). An OMS dump burn also occurred on STS-51-F , as part of
450-447: The largest issue with the usage of cryogenic propellants in interplanetary space is boil-off, which is largely dependent on the scale of spacecraft, for larger craft such as Starship this is less of an issue. Another advantage of hypergolic propellants is their high density compared to cryogenic propellants. LOX has a density of 1.14 g/ml, while on the other hand, hypergolic oxidizers such as nitric acid or nitrogen tetroxide have
475-607: The most common such propellant combination: dinitrogen tetroxide plus hydrazine . In 1935, Hellmuth Walter discovered that hydrazine hydrate was hypergolic with high-test peroxide of 80–83%. He was probably the first to discover this phenomenon, and set to work developing a fuel. Prof. Otto Lutz assisted the Walter Company with the development of C-Stoff which contained 30% hydrazine hydrate, 57% methanol , and 13% water, and spontaneously ignited with high strength hydrogen peroxide . BMW developed engines burning
500-653: The probe to fit within a smaller payload fairing . Relative to their mass, traditional hypergolic propellants possess a lower calorific value than cryogenic propellant combinations like LH2 / LOX or LCH4 / LOX . 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 carcinogenicity of traditional hypergolics necessitate expensive safety precautions. Failure to follow adequate safety procedures with an exceptionally dangerous UDMH-nitric acid propellant mixture nicknamed "Devil's Venom" , for example, resulted in
525-512: 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 non-hypergolic rocket engines nevertheless exist, notably the cryogenic (oxygen/hydrogen) RL-10 on the Centaur and
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#1732772646369550-673: The retirement of the Shuttle , these engines were repurposed for use on the Orion spacecraft's service module . This variant uses Monomethylhydrazine as fuel, with MON-3 Mixed Oxides of Nitrogen as oxidizer. It is planned to be used for the first six flights of the Artemis program , afterwards it would be replaced by a new "Orion Main Engine" starting Artemis 7. Hypergolic propellant The two propellant components usually consist of
575-580: The same combination for the Service Propulsion System . Those spacecraft and the Space Shuttle (among others) used hypergolic propellants for their reaction control systems . The trend among Western space launch agencies is away from large hypergolic rocket engines and toward hydrogen/oxygen engines or methane/oxygen and RP-1 /oxygen engines for various advantages and disadvantages . Ariane 1 through 4, with their hypergolic first and second stages (and optional hypergolic boosters on
600-543: Was coined by Dr. Wolfgang Nöggerath, at the Technical University of Brunswick , Germany. The only rocket-powered fighter ever deployed was the Messerschmitt Me 163 B Komet . The Komet had a HWK 109-509 , a rocket motor which consumed methanol/hydrazine as fuel and high test peroxide T-Stoff as oxidizer. The hypergolic rocket motor had the advantage of fast climb and quick-hitting tactics at
625-474: Was oxidized with MON-3 ( mixed oxides of nitrogen , 3% nitric acid), with the propellants being stored in tanks within the OMS/RCS pod, alongside other fuel and engine management systems. When full, the pods together carried around 4,087 kilograms (9,010 lb) of MMH and 6,743 kilograms (14,866 lb) of MON-3, allowing the OMS to produce a total delta-v of around 305 metres per second (1,000 ft/s) with
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