GB739417A - Improvements in rocket motors - Google Patents

Improvements in rocket motors

Info

Publication number
GB739417A
GB739417A GB3661/54A GB366154A GB739417A GB 739417 A GB739417 A GB 739417A GB 3661/54 A GB3661/54 A GB 3661/54A GB 366154 A GB366154 A GB 366154A GB 739417 A GB739417 A GB 739417A
Authority
GB
United Kingdom
Prior art keywords
grid
plug
propellant
openings
casing
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Expired
Application number
GB3661/54A
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.)
Anstalt Fuer die Entwicklung von Erfindungen und Gewerblichen Anwendungen ENERGA
Original Assignee
Anstalt Fuer die Entwicklung von Erfindungen und Gewerblichen Anwendungen ENERGA
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Anstalt Fuer die Entwicklung von Erfindungen und Gewerblichen Anwendungen ENERGA filed Critical Anstalt Fuer die Entwicklung von Erfindungen und Gewerblichen Anwendungen ENERGA
Publication of GB739417A publication Critical patent/GB739417A/en
Expired legal-status Critical Current

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
    • F42B15/00—Self-propelled projectiles or missiles, e.g. rockets; Guided missiles
    • 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
    • F02K9/08—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using solid propellants
    • F02K9/30—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using solid propellants with the propulsion gases exhausting through a plurality of nozzles
    • 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
    • F02K9/08—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using solid propellants
    • F02K9/32—Constructional parts; Details not otherwise provided for
    • 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

Abstract

739,417. Rocket motors. ANSTALT FUR DIE ENTWICKLUNG VON ERFINDUNGEN UND GEWERBLICHEN ANWENDUNGEN ENERGA. Feb. 8, 1954 [March 14, 1953], No. 3661/54. Class 9(2). Fig. 2 shows a rocket motor comprising a cylindrical chamber 1 containing tubular sticks 2 of propellant supported by the base of a frustoconical grid 4 and into which is screwed a plug 5 through which extend convergent-divergent openings forming exit nozzles 6 for the propellant gases. The narrow end 7 of the grid has force fit in the plug and surrounds an igniter 10 extending into the grid, but held at a distance from the propellant, from a metal casing 11 which is screwed into the plug. The grid has a base flange 9 extending to the inner wall of the casing and the openings 13 may be at least 15 per square cm. each having a diameter less than 2 mms. For a rocket motor operating with maximum pressures of 200 to 300 kg/sq. cm. at least 600 and preferably more than 1000 openings are provided. The semi-vertical angle of the conical grid is preferably between 3 and 10 degrees. An annular wad 15 obturating the nozzles 6 is adapted to yield at a predetermined pressure. A detonator 12 projecting from the plug 5 is adapted to initiate the igniter, which may contain an alumino-thermic mixture, by percussion. Stabilising fins 16 are fixed to the casing 1.
GB3661/54A 1953-03-14 1954-02-08 Improvements in rocket motors Expired GB739417A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CH739417X 1953-03-14

Publications (1)

Publication Number Publication Date
GB739417A true GB739417A (en) 1955-10-26

Family

ID=4533013

Family Applications (1)

Application Number Title Priority Date Filing Date
GB3661/54A Expired GB739417A (en) 1953-03-14 1954-02-08 Improvements in rocket motors

Country Status (5)

Country Link
BE (1) BE525998A (en)
CH (1) CH324499A (en)
DE (1) DE934996C (en)
FR (1) FR1154410A (en)
GB (1) GB739417A (en)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2456217A1 (en) * 1979-05-11 1980-12-05 Raytheon Co MOTOR-ROCKET
CN113202563A (en) * 2021-04-22 2021-08-03 沈阳航空航天大学 Coaxial reverse two-stage turbine device for weakening energy of tail flame emitted by missile

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE1104867B (en) * 1958-02-11 1961-04-13 J G W Berckholtz Fa Rocket with stabilizer
DE1154978B (en) * 1961-06-12 1963-09-26 Rheinmetall Gmbh Propellant for solid rockets, especially for short-flame missiles

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2456217A1 (en) * 1979-05-11 1980-12-05 Raytheon Co MOTOR-ROCKET
CN113202563A (en) * 2021-04-22 2021-08-03 沈阳航空航天大学 Coaxial reverse two-stage turbine device for weakening energy of tail flame emitted by missile
CN113202563B (en) * 2021-04-22 2022-08-16 沈阳航空航天大学 Coaxial reverse rotation two-stage turbine device for weakening missile launching tail flame energy

Also Published As

Publication number Publication date
DE934996C (en) 1955-11-10
BE525998A (en)
CH324499A (en) 1957-09-30
FR1154410A (en) 1958-04-10

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