US2775863A - Process for initiating the ignition of rocket fuels - Google Patents

Process for initiating the ignition of rocket fuels Download PDF

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Publication number
US2775863A
US2775863A US247246A US24724651A US2775863A US 2775863 A US2775863 A US 2775863A US 247246 A US247246 A US 247246A US 24724651 A US24724651 A US 24724651A US 2775863 A US2775863 A US 2775863A
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US
United States
Prior art keywords
ignition
initiating
combustion chamber
rocket
propellants
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Expired - Lifetime
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US247246A
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English (en)
Inventor
Traverse Georges
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
D'ETUDE de la PROPULSION PAR REACTION Ste
SOC ET PROPULSION PAR REACTION
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SOC ET PROPULSION PAR REACTION
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Publication date
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    • C—CHEMISTRY; METALLURGY
    • C06—EXPLOSIVES; MATCHES
    • C06C—DETONATING OR PRIMING DEVICES; FUSES; CHEMICAL LIGHTERS; PYROPHORIC COMPOSITIONS
    • C06C9/00—Chemical contact igniters; Chemical lighters
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
    • F02K9/95—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof characterised by starting or ignition means or arrangements

Definitions

  • the present invention relatesto rockets controlled by propellants and has for its object a method for carrying out the initial ignition of the propellant or propellants of such rockets.
  • This initial ignition is brought aboutby itself when hypergolic propellants are used, i. e. propellants the mutual contact of which produces an exothermic reaction capable of igniting the mixture.
  • auxiliary means should be provided for carrying out this ignition.
  • a monergol such. as the t P ten mononitromethane
  • the method according to the invention which is particularly advantageous in the case of monergol rockets, such as mononitromethane rockets, cuts out these drawbacks and has further the advantage of insuring a large security, which is the fundamental criterion when a monergol is used.
  • This method consists in bringing into contact with the propellant or propellants in the combustion chamber of the rocket a complex organo-metallic compound adapted to burn upon contact with oxygen or oxygenated compounds, or a mixture of such compounds.
  • the organometallic compound or compounds ignite: the gas from the reaction bring the reacting medium into the conditions suited for the ignition of the monergol or the non-hypergolic mixture, which ignition is next kept up by itself in proportion to the introduction of said monergol or mixture.
  • the total weight of the products necesice --the ethyl zinc iodide, the ethyl aluminum di-iodide, the
  • the method according to the invention causes a very small delay in the ignition. Consequently, the problem of the progressivity of admission of the propellants in the combustion chamber is not serious and the adjustment of the injectors is very simple; variations of the ignition pressure are very weak, risks of explosion when the ignition occurs being thus practically eliminated. It is not necessary to provide oxygen, and the absence of nitric acid, in the case of a monergol, warrants the good resistance to deterioration of the material forming the walls of the combustion chamber.
  • the bringing into contact of the composite organometallic derivative with the propellant or propellants may be effected, when the compound is liquid, by injecting the latter at the same time as the propellant or propellants.
  • the complex organmetallic compound may also be placed before the monergol in the combustion chamber.
  • the latter is preferably made during a very short time, less than one second for instance; for this injection, one may use an auxiliary tank filled with the ignition liquid and connected to the combustion chamber so as to inject into it the ignition liquid in the same direction as the propellants.
  • This latter arrangement has the advantage of allowing as many startings of the propeller as desired, the said propeller being thus completely self-contained.
  • the plate may be arranged so as to melt as soon as the device begins to operate.
  • this compound may be placed, if it is liquid, either in a flange secured to the inner wall of the combustion chamber, or along a tube maintaining the ignition liquid above the neck of the nozzle, or simply along the inner wall of the chamber between the bottom and the nozzle of said chamber, if the latter is horizontal.
  • the flange or tube may be arranged so as to melt as soon as the device begins to operate.
  • a solid ignition product it may be fixed on the inner wall of the combustion chamber, in all suitable points according to the direction of the jet or jets of propellants which ought to meet this solid ignition porduct.
  • the ignition liquid contained in a tank 5 is 3 injected into the chamber 1 through a pipe in the same direction as the propellant.
  • the ignition liquid is injected into the chamber 1 through the nozzle 2 by means of an injeetqr 1 fastened to the ground for instance, which simplifies the combustion chamber and the propeller.
  • a deflecting plate 8 which sprays the ignition liquid before it comes into contact with the propellant. This plate 8 may be such that it melts after a few seconds operation.
  • the injector of Fig. 2 is aproyided with holes 9. 4) suitably orientated so as to direct the ignition f l to d the 1' of P9P M fi The eflss insr ats is omitted.
  • ignition q d is rs igus y Biase in in a cupel 11 secured to the wallet the chamber 1 and w ch m y be r a ae as t me at h beg n ng of the operation.
  • a tube 13 is fitted in the neck of the nozzle, 2 and is used for maintaining in 14 the ignition liquid W e ow the mwst qn ease t Pass th eueh the nozzle; this tube 13 melts at the beginning ot the operation.
  • propellant enters the chamber 1 under the shape of divergent jetsingorder tofco'm e into contact of the ignition chamber 1A in a better manner.
  • Fig'. 7 the combustion chamber is horizontal; the ignition liquid is previously placed in 15 against the inner wall of the chamber 1; w
  • Fig. 8 there was used as an ignition agent a solid product containing chiefly organo-rnetallic compounds such as, for instance, diethyl aluminum bromide; this product may be then fixed against the inner of the chamber'l" under the shape of a sleeve 16 which will hitby the divergent propellant jets coming from the openings 12 in the bottom 3.
  • step consisting of contacting said mononitromethane, within tlie' ioinbiistion"chaiiiber of a" 'roc ketf wi tli an ignition-initiating amount of at least one complex organometallic compound of the formula RMeX, in which R is at least one lower alkyl radical from the group consisting of methyl and ethyl radicals, Me is a metal from the group consisting of aluminum and zinc and .
  • X is at least one halogen from the group consisting of iodine and bromine.

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  • Chemical & Material Sciences (AREA)
  • Engineering & Computer Science (AREA)
  • Chemical Kinetics & Catalysis (AREA)
  • General Chemical & Material Sciences (AREA)
  • Organic Chemistry (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Organic Low-Molecular-Weight Compounds And Preparation Thereof (AREA)
US247246A 1950-09-25 1951-09-19 Process for initiating the ignition of rocket fuels Expired - Lifetime US2775863A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR1024900T 1950-09-25

Publications (1)

Publication Number Publication Date
US2775863A true US2775863A (en) 1957-01-01

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US247246A Expired - Lifetime US2775863A (en) 1950-09-25 1951-09-19 Process for initiating the ignition of rocket fuels

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US (1) US2775863A (fr)
FR (2) FR1024900A (fr)
GB (1) GB718029A (fr)

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2867081A (en) * 1956-06-07 1959-01-06 Koppers Co Inc Hydrocarbon fuel composition and the method of operating a jet engine therewith
US2994189A (en) * 1954-01-04 1961-08-01 Phillips Petroleum Co Method of producing immediate thrust using fast burning fuels
US3177652A (en) * 1961-02-27 1965-04-13 Ethyl Corp Ignition system for propellants
US4072699A (en) * 1973-03-28 1978-02-07 Merkl George Aluminum organoiodides
US5223651A (en) * 1990-03-08 1993-06-29 Avco Corporation Supersonic combustion engine and method of combustion initiation and distribution
US20190072054A1 (en) * 2016-03-07 2019-03-07 Arianegroup Sas Rocket engine with ground-based ignition

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3300975A (en) * 1955-06-13 1967-01-31 Garrett Corp Protective apparatus for a rocket motor
US2959007A (en) * 1957-02-13 1960-11-08 Curtiss Wright Corp Jet engine ignition system utilizing pyrophoric fuel
US3127735A (en) * 1960-07-05 1964-04-07 North American Aviation Inc Propellant compositions

Citations (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE608242C (de) * 1930-04-13 1935-01-21 E H C W Paul Heylandt Dr Ing Verfahren zur Erzeugung von Treibgasen zum Fortbewegen von Fahrzeugen mittels Reaktionswirkung
US2433943A (en) * 1944-03-11 1948-01-06 Aerojet Engineering Corp Operation of jet propulsion motors with nitroparaffin
US2433932A (en) * 1944-03-11 1948-01-06 Aerojet Engineering Corp Fuel combustion
US2474685A (en) * 1945-04-12 1949-06-28 Stewart Warner Corp Jet propulsion apparatus
US2500334A (en) * 1944-06-19 1950-03-14 Aerojet Engineering Corp Jet motor operable by monopropellant and method of operating it
US2505798A (en) * 1946-06-20 1950-05-02 Leslie A Skinner Liquid fuel jet propulsion system
US2520434A (en) * 1946-03-15 1950-08-29 Power Jets Res & Dev Ltd Control system for turbojet engines with reheat fuel supply system
US2542953A (en) * 1945-09-13 1951-02-20 Stewart Warner Corp Combustion turbine having mixing tube to aspirate, compress, and preheat the air-fuel mixture
US2648190A (en) * 1948-03-05 1953-08-11 Aerojet General Co Initiation of propellant decomposition

Patent Citations (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE608242C (de) * 1930-04-13 1935-01-21 E H C W Paul Heylandt Dr Ing Verfahren zur Erzeugung von Treibgasen zum Fortbewegen von Fahrzeugen mittels Reaktionswirkung
US2433943A (en) * 1944-03-11 1948-01-06 Aerojet Engineering Corp Operation of jet propulsion motors with nitroparaffin
US2433932A (en) * 1944-03-11 1948-01-06 Aerojet Engineering Corp Fuel combustion
US2500334A (en) * 1944-06-19 1950-03-14 Aerojet Engineering Corp Jet motor operable by monopropellant and method of operating it
US2474685A (en) * 1945-04-12 1949-06-28 Stewart Warner Corp Jet propulsion apparatus
US2542953A (en) * 1945-09-13 1951-02-20 Stewart Warner Corp Combustion turbine having mixing tube to aspirate, compress, and preheat the air-fuel mixture
US2520434A (en) * 1946-03-15 1950-08-29 Power Jets Res & Dev Ltd Control system for turbojet engines with reheat fuel supply system
US2505798A (en) * 1946-06-20 1950-05-02 Leslie A Skinner Liquid fuel jet propulsion system
US2648190A (en) * 1948-03-05 1953-08-11 Aerojet General Co Initiation of propellant decomposition

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2994189A (en) * 1954-01-04 1961-08-01 Phillips Petroleum Co Method of producing immediate thrust using fast burning fuels
US2867081A (en) * 1956-06-07 1959-01-06 Koppers Co Inc Hydrocarbon fuel composition and the method of operating a jet engine therewith
US3177652A (en) * 1961-02-27 1965-04-13 Ethyl Corp Ignition system for propellants
US4072699A (en) * 1973-03-28 1978-02-07 Merkl George Aluminum organoiodides
US5223651A (en) * 1990-03-08 1993-06-29 Avco Corporation Supersonic combustion engine and method of combustion initiation and distribution
US20190072054A1 (en) * 2016-03-07 2019-03-07 Arianegroup Sas Rocket engine with ground-based ignition

Also Published As

Publication number Publication date
GB718029A (en) 1954-11-10
FR1024900A (fr) 1953-04-08
FR61977E (fr) 1955-06-01

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