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GB944355A - A solid propellant rocket motor and a method of manufacturing same - Google Patents

A solid propellant rocket motor and a method of manufacturing same

Info

Publication number
GB944355A
GB944355A GB2579461A GB2579461A GB944355A GB 944355 A GB944355 A GB 944355A GB 2579461 A GB2579461 A GB 2579461A GB 2579461 A GB2579461 A GB 2579461A GB 944355 A GB944355 A GB 944355A
Authority
GB
United Kingdom
Prior art keywords
charge
chamber
motor
tapered portion
sleeve
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
GB2579461A
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.)
GOTEX AB
Original Assignee
GOTEX AB
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 GOTEX AB filed Critical GOTEX AB
Publication of GB944355A publication Critical patent/GB944355A/en
Expired legal-status Critical Current

Links

Classifications

    • 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
    • F02K9/36—Propellant charge supports
    • 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
    • F02K9/10—Shape or structure of solid propellant charges
    • F02K9/20—Shape or structure of solid propellant charges of the external-burning type
    • 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
    • F02K9/24—Charging rocket engines with solid propellants; Methods or apparatus specially adapted for working solid propellant charges
    • 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
    • F02K9/34—Casings; Combustion chambers; Liners thereof

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Testing Of Engines (AREA)

Abstract

944,355. Solid propellant rocket motors. GOTEX A. B. July 17, 1961 [July 28, 1960], No. 25794/61. Heading F3A. A rocket motor has the forward end of its propellant charge and combustion chamber tapered and the charge, wedged or secured, through the intermediary of an insulating layer, to the tapered portion of the chamber, a space being left between the combustion chamber wall and the remainder of the charge. In manufacturing the motor, the propellant charge 1, 1<SP>1</SP> is first fitted with the insulating sleeve 3 which may be formed by winding paper strip to give a lower burning rate to the sleeve than the charge. The assembled sleeve and charge are then supported in a hollow closed end mandrel and the tapered portion 1<SP>1</SP>, 3 forced into the tapered portion of the chamber by a thrust in excess of that to be developed by the motor. Finally, the nozzle 5 is inserted and the end portion 6 of the chamber spun over. A 2 inch gap at the forward end of the charge is desirable in case any slight forward movement of the charge occurs during operation. Cone angle may vary between 3 and 30 degrees, although for the embodiment described, used in a metal chamber, an angle between 4 and 6 degrees is specified.
GB2579461A 1960-07-28 1961-07-17 A solid propellant rocket motor and a method of manufacturing same Expired GB944355A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
SE730660 1960-07-28

Publications (1)

Publication Number Publication Date
GB944355A true GB944355A (en) 1963-12-11

Family

ID=20270999

Family Applications (1)

Application Number Title Priority Date Filing Date
GB2579461A Expired GB944355A (en) 1960-07-28 1961-07-17 A solid propellant rocket motor and a method of manufacturing same

Country Status (2)

Country Link
DE (1) DE1210257B (en)
GB (1) GB944355A (en)

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN114483376A (en) * 2021-12-31 2022-05-13 北京灵动飞天动力科技有限公司 Internal supporting device for vertical storage engine and application of internal supporting device
EP4159999A1 (en) * 2021-09-29 2023-04-05 Siec Badawcza Lukasiewicz-Instytut Lotnictwa Rocket solid propellant grain
CN117072346A (en) * 2023-10-17 2023-11-17 沈阳航天新光集团有限公司 Device for connecting combustion chamber and injector in thrust chamber
RU2808186C1 (en) * 2023-01-17 2023-11-24 Акционерное общество "Корпорация "Московский институт теплотехники" (АО "Корпорация "МИТ") Solid-fuel ramjet engine and method for controlling thrust of a solid-fuel ramjet engine
CN118188219A (en) * 2024-05-16 2024-06-14 西安现代控制技术研究所 Composite heat insulation structure for large-caliber engine charging combustion chamber

Family Cites Families (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR1143581A (en) * 1954-05-14 1957-10-02 Soc Tech De Rech Ind Powder thruster

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP4159999A1 (en) * 2021-09-29 2023-04-05 Siec Badawcza Lukasiewicz-Instytut Lotnictwa Rocket solid propellant grain
CN114483376A (en) * 2021-12-31 2022-05-13 北京灵动飞天动力科技有限公司 Internal supporting device for vertical storage engine and application of internal supporting device
CN114483376B (en) * 2021-12-31 2023-03-28 北京灵动飞天动力科技有限公司 Internal supporting device for vertical storage engine and application of internal supporting device
RU2808186C1 (en) * 2023-01-17 2023-11-24 Акционерное общество "Корпорация "Московский институт теплотехники" (АО "Корпорация "МИТ") Solid-fuel ramjet engine and method for controlling thrust of a solid-fuel ramjet engine
RU2808186C9 (en) * 2023-01-17 2024-03-11 Акционерное общество "Корпорация "Московский институт теплотехники" (АО "Корпорация "МИТ") Solid-fuel ramjet engine and method for controlling thrust of a solid-fuel ramjet engine
CN117072346A (en) * 2023-10-17 2023-11-17 沈阳航天新光集团有限公司 Device for connecting combustion chamber and injector in thrust chamber
CN118188219A (en) * 2024-05-16 2024-06-14 西安现代控制技术研究所 Composite heat insulation structure for large-caliber engine charging combustion chamber

Also Published As

Publication number Publication date
DE1210257B (en) 1966-02-03

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