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GB927675A - Improvements relating to jet propelled missiles - Google Patents

Improvements relating to jet propelled missiles

Info

Publication number
GB927675A
GB927675A GB13744/61A GB1374461A GB927675A GB 927675 A GB927675 A GB 927675A GB 13744/61 A GB13744/61 A GB 13744/61A GB 1374461 A GB1374461 A GB 1374461A GB 927675 A GB927675 A GB 927675A
Authority
GB
United Kingdom
Prior art keywords
nozzle
missile
bolkow
throat
april
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
GB13744/61A
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.)
Individual
Original Assignee
Individual
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 Individual filed Critical Individual
Publication of GB927675A publication Critical patent/GB927675A/en
Expired legal-status Critical Current

Links

Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
    • B64D27/02—Aircraft characterised by the type or position of power plants
    • B64D27/023—Aircraft characterised by the type or position of power plants of rocket type, e.g. for assisting taking-off or braking
    • 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
    • F02K9/97—Rocket nozzles
    • F02K9/978—Closures for nozzles; Nozzles comprising ejectable or discardable elements
    • 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
    • F42B15/36—Means for interconnecting rocket-motor and body section; Multi-stage connectors; Disconnecting means

Landscapes

  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • General Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)

Abstract

927,675. Self-propelled missiles. L. BOLKOW, [trading as BOLKOW - ENTWICKLUNGEN KOMM.-GES.]. April 17, 1961 [April 16, 1960], No. 13744/61. Class 9 (2). [Also in Group XXVI] A self-propelled missile has a detachable nozzle, the point of separation being at, or slightly in front of, that part of the nozzle having minimum cross-sectional area. At Fig. 3, part 13 of the nozzle is push-fitted on to part 12, which part is constituted by the rear of the missile body. During burning of the propellant charge internal pressure retains part 13, but on termination of burning it is forced off by external air pressure. Various embodiments are described including providing parts 12, 13 with cylindrical members, external to the throat of the nozzle, which engage with a tight push-fit, and welding or soldering around the joint of parts 12, 13, the welds melting during passage of the propellent gases. Also, the nozzle may be made as one unit and have an annular groove around the throat which causes separation after being heated. Additionally the groove may contain a ring of explosive which is ignited as the thrust terminates or a predetermined time afterwards. At Fig. 7, after detachment of part 42, spring plates 44 come together to close the end of the missile and improve its aerodynamic shape.
GB13744/61A 1960-04-16 1961-04-17 Improvements relating to jet propelled missiles Expired GB927675A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DEB57516A DE1122380B (en) 1960-04-16 1960-04-16 Flying body with recoil engine

Publications (1)

Publication Number Publication Date
GB927675A true GB927675A (en) 1963-05-29

Family

ID=6971727

Family Applications (1)

Application Number Title Priority Date Filing Date
GB13744/61A Expired GB927675A (en) 1960-04-16 1961-04-17 Improvements relating to jet propelled missiles

Country Status (2)

Country Link
DE (1) DE1122380B (en)
GB (1) GB927675A (en)

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4301707A (en) * 1979-10-29 1981-11-24 Mcdonnell Douglas Corporation Embedded explosive severance of non-metallic materials
CN105736185A (en) * 2014-12-09 2016-07-06 上海新力动力设备研究所 Half-and-half threaded connection structure of diffusing section of jet pipe of solid rocket engine
CN107492753A (en) * 2017-07-19 2017-12-19 贵州航天风华精密设备有限公司 A kind of safe escape mechanism for guided missile electrical fitting
CN115711188A (en) * 2022-11-21 2023-02-24 北京中科宇航技术有限公司 Structure for improving sealing performance of bonding interface of integral die-pressing spray pipe

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2629583B1 (en) * 1988-03-30 1993-06-18 Aerospatiale AIRCRAFT PROVIDED WITH AT LEAST ONE WIDTHABLE PROPELLER
CN102950351B (en) * 2012-11-02 2015-10-28 首都航天机械公司 Hydrogen peroxide thrust chamber body portion diffusion brazing manufacture method

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4301707A (en) * 1979-10-29 1981-11-24 Mcdonnell Douglas Corporation Embedded explosive severance of non-metallic materials
CN105736185A (en) * 2014-12-09 2016-07-06 上海新力动力设备研究所 Half-and-half threaded connection structure of diffusing section of jet pipe of solid rocket engine
CN107492753A (en) * 2017-07-19 2017-12-19 贵州航天风华精密设备有限公司 A kind of safe escape mechanism for guided missile electrical fitting
CN115711188A (en) * 2022-11-21 2023-02-24 北京中科宇航技术有限公司 Structure for improving sealing performance of bonding interface of integral die-pressing spray pipe
CN115711188B (en) * 2022-11-21 2024-06-04 北京中科宇航技术有限公司 Structure for improving sealing performance of bonding interface of integral molded spray pipe

Also Published As

Publication number Publication date
DE1122380B (en) 1962-01-18
DE1122380C2 (en) 1962-08-09

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