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GB1050086A - - Google Patents

Info

Publication number
GB1050086A
GB1050086A GB1050086DA GB1050086A GB 1050086 A GB1050086 A GB 1050086A GB 1050086D A GB1050086D A GB 1050086DA GB 1050086 A GB1050086 A GB 1050086A
Authority
GB
United Kingdom
Prior art keywords
sleeve
gap
rocket
feb
cast
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
Publication date
Publication of GB1050086A publication Critical patent/GB1050086A/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
    • F02K9/24—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
    • F02K9/10—Shape or structure of solid propellant charges
    • F02K9/18—Shape or structure of solid propellant charges of the internal-burning type having a star or like shaped internal cavity
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
    • F42B33/00—Manufacture of ammunition; Dismantling of ammunition; Apparatus therefor
    • F42B33/02—Filling cartridges, missiles, or fuzes; Inserting propellant or explosive charges
    • F42B33/0214—Filling cartridges, missiles, or fuzes; Inserting propellant or explosive charges by casting

Landscapes

  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • Manufacturing & Machinery (AREA)
  • Testing Or Calibration Of Command Recording Devices (AREA)

Abstract

1,050,086. Rocket motors. SOCI•T• NATIONALE D'ETUDE ET DE CONSTRUCTION DE MOTEURS D'AVIATION. Feb. 10, 1964 [Feb. 13, 1963], No. 5425/64. Heading F3A. A rocket motor comprises a sleeve 1 with a thermal protection lining 2 itself lined with an inhibitor 3 so machined that it is thicker at the ends and middle of the sleeve. Flanges may be formed at the ends of the sleeve, so that it may be joined to similar sleeves by means of rings 5. Propellant charges 6, 6<SP>1</SP> are cast in the sleeve in such a way that an axial gap e exists between them and a e gap - is left at each end of the sleeve. Propel- 2 lant 6 may be introduced from one end around a core to form the axial passage 8, the sleeve then being inverted to introduce propellant 6<SP>1</SP> from the other end. The gap between the charges is maintained by placing in the sleeve a body which can be removed after casting by a solvent, or a body made of removable parts, or a rapidly combustible body which is burnt out on firing the rocket. More than two grains may be cast in the sleeve. The lining 2 may be omitted.
GB1050086D Expired GB1050086A (en)

Publications (1)

Publication Number Publication Date
GB1050086A true GB1050086A (en) 1900-01-01

Family

ID=1755570

Family Applications (1)

Application Number Title Priority Date Filing Date
GB1050086D Expired GB1050086A (en)

Country Status (1)

Country Link
GB (1) GB1050086A (en)

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2162927A (en) * 1977-10-27 1986-02-12 Bayern Chemie Gmbh Flugchemie A solid rocket propulsion system
FR2704280A1 (en) * 1993-03-15 1994-10-28 United Technologies Corp Strain suppression system in a solid fuel rocket engine.
RU2215170C1 (en) * 2002-04-05 2003-10-27 Федеральный центр двойных технологий "Союз" Mockup engine for determining burning rate of rocket solid propellant
RU2327052C2 (en) * 2006-07-26 2008-06-20 Федеральное государственное унитарное предприятие "Федеральный центр двойных технологий "Союз" (ФГУП "ФЦДТ "Союз") Method of pressure gasdynamic stabilisation in pilot engine chamber with solid-propellant charges with high combustion rate susceptibility to pressure
RU2376490C1 (en) * 2008-06-11 2009-12-20 Федеральное государственное унитарное предприятие "Федеральный центр двойных технологий "Союз" (ФГУП "ФЦДТ" "Союз") Method of instantaneous determination of minimum operating pressure stability in solid propellant rocket engine

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2162927A (en) * 1977-10-27 1986-02-12 Bayern Chemie Gmbh Flugchemie A solid rocket propulsion system
FR2704280A1 (en) * 1993-03-15 1994-10-28 United Technologies Corp Strain suppression system in a solid fuel rocket engine.
RU2215170C1 (en) * 2002-04-05 2003-10-27 Федеральный центр двойных технологий "Союз" Mockup engine for determining burning rate of rocket solid propellant
RU2327052C2 (en) * 2006-07-26 2008-06-20 Федеральное государственное унитарное предприятие "Федеральный центр двойных технологий "Союз" (ФГУП "ФЦДТ "Союз") Method of pressure gasdynamic stabilisation in pilot engine chamber with solid-propellant charges with high combustion rate susceptibility to pressure
RU2376490C1 (en) * 2008-06-11 2009-12-20 Федеральное государственное унитарное предприятие "Федеральный центр двойных технологий "Союз" (ФГУП "ФЦДТ" "Союз") Method of instantaneous determination of minimum operating pressure stability in solid propellant rocket engine

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