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ownload as pdf printable version in other projects wikidata item appearance move to sidebar hide from wikipedia the free encyclopedia this article needs more citations please help improve this article by adding citations to reliable sources unsourced material may be challenged and removed find sources monopropellant rocket news newspapers books scholar jstor august 2011 learn how and when to remove this message rocket that uses a single propellant with a catalyst a monopropellant rocket or monochemical rocket is a rocket that uses a single chemical as its propellant contradictory 1 monopropellant rockets are commonly used as small altitude and trajectory control rockets in satellites rocket upper stages crewed spacecraft and spaceplanes 2 chemical reaction based edit the simplest monopropellant rockets depend on the chemical decomposition of a storable propellant after passing it over a catalyst bed 3 the power for the thruster comes from the high pressure gas created during the decomposition reaction that allows a rocket nozzle to speed up the gas to create thrust hydrazine edit the most commonly used monopropellant is hydrazine n 2 h 4 or h 2 n nh 2 a compound unstable in the presence of a catalyst and which is also a strong reducing agent the decomposition is highly exothermic and produces a 1 000 c 1 830 f gas that is a mixture of nitrogen hydrogen and ammonia according to the three following reactions 4 reaction 1 n 2 h 4 n 2 2 h 2 reaction 2 3 n 2 h 4 4 nh 3 n 2 reaction 3 4 nh 3 n 2 h 4 3 n 2 8 h 2 the most common catalyst is granular alumina aluminum oxide al 2 o 3 coated with iridium these coated granules are usually under the commercial labels aerojet s 405 previously made by shell 5 or w c heraeus h kc 12 ga previously made by kali chemie 6 there is no igniter with hydrazine aerojet s 405 is a spontaneous catalyst that is hydrazine decomposes on contact with the catalyst the main limiting factor of the monopropellant rocket is its life which mainly depends on the life of the catalyst the catalyst may be subject to catalytic poisoning and catalytic attrition which results in the catalyst failure hydrogen peroxide edit another monopropellant is hydrogen peroxide which when purified to 90 or higher concentration is self decomposing at high temperatures or when a catalyst is present in general edit most chemical reaction monopropellant rocket systems consist of a fuel tank usually a titanium or aluminium sphere with an ethylene propylene rubber container or a surface tension propellant management device filled with the fuel the tank is then pressurized with helium or nitrogen which pushes the fuel out to the motors a pipe leads from the tank to a poppet valve and then to the decomposition chamber of the rocket motor typically a satellite will have not just one motor but two to twelve each with its own valve the attitude control rocket motors for satellites and space probes are often very small 25 mm 0 98 in or so in diameter and mounted in groups that point in four directions within a plane the rocket is fired when the computer sends direct current through a small electromagnet that opens the poppet valve the firing is often very brief a few milliseconds and if operated in air would sound like a pebble thrown against a metal trash can if on for long it would make a piercing hiss chemical reaction monopropellants are not as efficient as some other propulsion technologies engineers choose monopropellant systems when the need for simplicity and reliability outweigh the need for high delivered impulse if the propulsion system must produce large amounts of thrust or have a high specific impulse as on the main motor of an interplanetary spacecraft other technologies are used solar thermal based edit a concept to provide low earth orbit leo propellant depots that could be used as way stations for other spacecraft to stop and refuel on the way to beyond leo missions has proposed that waste gaseous hydrogen an inevitable byproduct of long term liquid hydrogen storage in the radiative heat environment of space would be usable as a monopropellant in a solar thermal propulsion system the waste hydrogen would be productively utilized for both orbital station keeping and attitude control as well as providing limited propellant and thrust to use for orbital maneuvers to better rendezvous with other spacecraft that would be inbound to receive fuel from the depot 7 solar thermal monopropellant thrusters are also integral to the design of a next generation cryogenic upper stage rocket proposed by u s company united launch alliance ula the advanced common evolved stage aces is intended as a lower cost more capable and more flexible upper stage that would supplement and perhaps replace the existing ula centaur and ula delta cryogenic second stage dcss upper stage vehicles the aces integrated vehicle fluids option eliminates all hydrazine and helium from the space vehicle normally used for attitude control and station keeping and depends instead on solar thermal monopropellant thrusters using waste hydrogen 8 history edit lunar landing research vehicle with 18 hydrogen peroxide monopropellant thrusters soviet designers had begun experimenting with monopropellant rockets as early as 1933 9 they believed their monopropellant mixes of nitrogen tetroxide with gasoline or toluene and kerosene would lead to an overall simpler system however they ran into problems with violent explosions with pre mixed fuel and oxidizer serving as a monopropellant that led the designers to abandon this approach 9 german engineer helmuth walter was an early pioneer of monopropellant rockets using hydrogen peroxide as fuel 10 initially developing a peroxide gas turbine for use in submarines monopropellant motors of his design were used to power the heinkel he 176 the first aircraft solely powered by a liquid rocket motor and early messerschmitt me 163 komet prototypes the only operational rocket powered fighter 10 after world war ii the british continued to experiment with hydrogen peroxide monopropellants 10 they developed the de havilland sprite a motor that could produce 5000lbf 22 2 kn of thrust over 16 seconds this rocket was tested on 30 flights on the de havilland comet 1 the first commercial jet airliner in an effort to boost hot and high takeoff performance but was never used operationally 11 in the united states when nasa began studying monopropellants at the jet propulsion laboratory jpl the properties of the existing propellants demanded that the thrusters be impractically large 12 the addition of a catalyst and pre heating propellant made them more efficient but raised concerns over safety and handling of hazardous propellants like anhydrous hydrazine 12 however the simplicity of the thrusters designed around early monopropellants offered many simplicities and were first tested in 1959 on the able 4 mission 13 this test allowed for the ranger and mariner missions to use a similar thruster for correction maneuvers 13 and in the orbital insertion of telstar considered by the national air and space museum to be the most significant communications satellite in the beginning of the space race 14 centaur iii upper stage with 12 hydrazine monopropellant thrusters in 1964 nasa began use of the lunar landing research vehicle to train apollo astronauts in piloting the lunar excursion module lem using an attitude control system consisting of 16 hydrogen peroxide monopropellant thrusters to steer the lem to the lunar surface 15 upper stage vehicles began using monopropellant thrusters as a convenient control device in the early 1960s when general dynamics proposed the centaur upper stage to the united states airforce 16 of which versions are still in use in united launch alliance s atlas and vulcan rockets 17 new developments edit nasa is developing a new monopropellant propulsion system for small cost driven spacecraft with delta v requirements in the range of 10 150 m s this system is based on a hydroxylammonium nitrate han water fuel monopropellant blend which is extremely dense environmentally benign and promises good performance and simplicity 18 the eurenco bofors company produced lmp 103s as a 1 to 1 substitute for hydrazine by dissolving 65 ammonium dinitramide nh 4 n no 2 2 in 35 water solution of methanol and ammonia lmp 103s has 6 higher specific impulse and 30 higher impulse density than hydrazine monopropellant additionally hydrazine is highly toxic and carcinogenic while lmp 103s is only moderately toxic lmp 103s is un class 1 4s allowing for transport on commercial aircraft and was demonstrated on the prisma satellite in 2010 special handling is not required lmp 103s could replace hydrazine as the most commonly used monopropellant 19 20 see also edit monopropellant hypergolic propellant liquid propellant rocket mars reconnaissance orbiter reaction wheel nitrous oxide fuel blend rocket propulsion technologies disambiguation references edit united states army elements of aircraft and missile propulsion department of defense united states army material command july 1969 pp 1 11 retrieved march 1 2024 sutton george biblarz oscar rocket propulsion elements 7th ed wiley interscience p 259 isbn 0 471 32642 9 price t evans d february 15 1968 the status of monopropellant hydrazine technology tr 32 1227 pasadena california national aeronautics and space administration pp 1 2 haws jl harden dg 1965 thermodynamic properties of hydrazine journal of spacecraft and rockets 2 6 972 974 bibcode 1965jspro 2 972h doi 10 2514 3 28327 aerojet rocketdyne 12 jun 2003 aerojet announces licensing and manufacture of spontaneous monopropellant catalyst s 405 aerojetrocketdyne com archived from the original on 5 december 2017 retrieved 9 jul 2015 wilfried ley klaus wittmann willi hallmann 2009 handbook of space technology john wiley sons p 317 isbn 978 0 470 74241 9 zegler frank bernard kutter 2010 09 02 evolving to a depot based space transportation architecture pdf aiaa space 2010 conference exposition aiaa p 3 archived from the original pdf on 2011 10 20 retrieved 2011 01 25 the waste hydrogen that has boiled off happens to be the best known propellant as a monopropellant in a basic solar thermal propulsion system for this task a practical depot must evolve hydrogen at a minimum rate that matches the station keeping demands zegler and kutter 2010 p 5 1 2 sutton george 2006 history of liquid propellant rocket engines reston virginia american institute of aeronautics and astronautics pp 533 534 isbn 1563476495 1 2 3 stokes p r 14 january 1998 hydrogen peroxide for power and propulsion pdf archived from the original pdf on 15 february 2006 retrieved 24 january 2024 birtles 1970 p 125 1 2 price t w evans d d february 15 1968 the status of monopropellant hydrazine technologies pdf tr 32 1227 national aeronautics and space administration pp 1 2 retrieved march 21 2024 1 2 price t w evans d d february 15 1968 the status of monopropellant hydrazine technologies pdf tr 32 1227 national aeronautics and space administration pp 1 2 retrieved march 21 2024 telstar national air and space museum retrieved march 8 2024 55 years ago the first flight of the lunar landing research vehicle national aeronautics and space administration october 30 2019 retrieved march 8 2024 arrighi robert december 12 2012 centaur america s workhorse in space national aeronautics and space administration retrieved april 19 2024 atlas v users guide pdf united launch alliance 2010 retrieved april 19 2024 jankovsky robert s july 1 3 1996 han based monopropellant assessment for spacecraft 32nd joint propulsion conference lake buena vista florida nasa nasa technical memorandum 107287 aiaa 96 2863 green propellant lmp 103s ecaps se archived from the original on april 25 2024 retrieved april 25 2024 high performance green propulsion lmp 103s ecaps space archived from the original on june 7 2023 retrieved february 3 2023 external links edit technical reports on hydrogen peroxide as a monopropellant for rockets uspat 20090133788 nitrous oxide fuel blend monopropellants dead link v t e spacecraft propulsion concepts rocket rocket engine reaction engine reaction mass thrust specific impulse delta v staging rocket equation propellantless propulsion physical propulsion cold gas thruster thermal rocket water rocket steam rocket solar sail diffractive electric sail magnetic sail solar thermal rocket photon rocket wine chemical propulsion state liquid propellant rocket solid propellant rocket hybrid propellant rocket propellants liquid propellant cryogenic hypergolic monopropellant bipropellant tripropellant power cycles staged combustion cycle expander cycle gas generator cycle tap off cycle intake mechanisms pressure fed engine pump fed engine electric pump fed engine electrical propulsion electrostatic colloid thruster ion thruster gridded hall effect thruster field emission electric propulsion electromagnetic pulsed inductive thruster magnetoplasmadynamic thruster electrodeless plasma thruster plasma magnet electrothermal pulsed plasma thruster vacuum arc thruster helicon double layer thruster arcjet rocket resistojet rocket microwave electrothermal thruster vasimr other atmosphere breathing electric propulsion high power electric propulsion magbeam mass driver nuclear propulsion closed system direct fusion drive nuclear electric rocket nuclear thermal rocket radioisotope salt water gas core lightbulb nuclear photonic rocket open system nuclear pulse propulsion antimatter catalyzed pulsed nuclear thermal rocket fusion rocket bussard ramjet fission fragment rocket fission sail external power beam powered propulsion laser propulsion tethers related concepts aerobraking aerocapture aerogravity assist alcubierre drive atmospheric entry gravity assist non rocket spacelaunch oberth effect orbital mechanics orbital maneuver reactionless drive space launch warp drive spaceflight portal retrieved 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