GB1468814A - Rocket propulsion motors - Google Patents

Rocket propulsion motors

Info

Publication number
GB1468814A
GB1468814A GB4494473A GB4494473A GB1468814A GB 1468814 A GB1468814 A GB 1468814A GB 4494473 A GB4494473 A GB 4494473A GB 4494473 A GB4494473 A GB 4494473A GB 1468814 A GB1468814 A GB 1468814A
Authority
GB
United Kingdom
Prior art keywords
restrictor
motor
stage charge
pressure
diaphragm
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
GB4494473A
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.)
UK Secretary of State for Defence
Original Assignee
UK Secretary of State for Defence
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 UK Secretary of State for Defence filed Critical UK Secretary of State for Defence
Priority to GB4494473A priority Critical patent/GB1468814A/en
Publication of GB1468814A publication Critical patent/GB1468814A/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
    • F42B15/36—Means for interconnecting rocket-motor and body section; Multi-stage connectors; Disconnecting means
    • 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
    • F02K9/74—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof combined with another jet-propulsion plant
    • F02K9/76—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof combined with another jet-propulsion plant with another rocket-engine plant; Multistage rocket-engine plants
    • F02K9/763—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof combined with another jet-propulsion plant with another rocket-engine plant; Multistage rocket-engine plants with solid propellant
    • 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

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • General Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Diaphragms And Bellows (AREA)

Abstract

1468814 Rocket motors DEFENCE SECRETARY OF STATE FOR 3 Dec 1974 [25 Sept 1973] 44944/73 Heading F3A A rocket motor comprises: a first stage charge 7; a second stage charge 2; a diaphragm 17 closing a blast tube 5; and a restrictor 12 in a nozzle 6. The restrictor is secured by adhesive or by a spring 16 that abuts against a plate 8. A ring 10 holds the motor in a launching tube 3. When the first stage charge is ignited, the pressure P of the combustion gases breaks bolts 9 to discard the plate 8 and accelerates the motor. The gases also enter the blast tube 5 through an aperture 15 in the restrictor and, when the pressure P<SP>1</SP> exceeds the pressure P, owing to the forward movement of the motor, the restrictor is discarded within the launching tube so as not to present a hazard to the operator. The diaphragm is ruptured only when the second stage charge is fired.
GB4494473A 1974-12-03 1974-12-03 Rocket propulsion motors Expired GB1468814A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
GB4494473A GB1468814A (en) 1974-12-03 1974-12-03 Rocket propulsion motors

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB4494473A GB1468814A (en) 1974-12-03 1974-12-03 Rocket propulsion motors

Publications (1)

Publication Number Publication Date
GB1468814A true GB1468814A (en) 1977-03-30

Family

ID=10435328

Family Applications (1)

Application Number Title Priority Date Filing Date
GB4494473A Expired GB1468814A (en) 1974-12-03 1974-12-03 Rocket propulsion motors

Country Status (1)

Country Link
GB (1) GB1468814A (en)

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2584456A1 (en) * 1985-07-03 1987-01-09 Poudres & Explosifs Ste Nale TEMPORARY CLOSURE DEVICE FOR AN INTERNAL ORIFICE OF A PROPELLER
FR2650639A1 (en) * 1989-08-04 1991-02-08 Thomson Brandt Armements Unlockable fastening system for two elements, particularly for two elements of a munition
EP0508851A1 (en) * 1991-04-10 1992-10-14 AEROSPATIALE Société Nationale Industrielle Shock absorber for a jet propulsion system
CN100419245C (en) * 2004-12-08 2008-09-17 中国北方工业公司 Delay igniter for composite enhanced distance bullet rocket engine
RU212932U1 (en) * 2022-06-30 2022-08-12 федеральное государственное бюджетное образовательное учреждение высшего образования "Казанский национальный исследовательский технический университет им. А.Н.Туполева-КАИ" Nozzle plug for solid propellant rocket engine

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2584456A1 (en) * 1985-07-03 1987-01-09 Poudres & Explosifs Ste Nale TEMPORARY CLOSURE DEVICE FOR AN INTERNAL ORIFICE OF A PROPELLER
EP0211703A1 (en) * 1985-07-03 1987-02-25 Societe Nationale Des Poudres Et Explosifs Plug for a solid propellant with two combustion chambers
FR2650639A1 (en) * 1989-08-04 1991-02-08 Thomson Brandt Armements Unlockable fastening system for two elements, particularly for two elements of a munition
EP0508851A1 (en) * 1991-04-10 1992-10-14 AEROSPATIALE Société Nationale Industrielle Shock absorber for a jet propulsion system
FR2675207A1 (en) * 1991-04-10 1992-10-16 Aerospatiale FLUID FLOW SYSTEM WITH BRUTAL PRESSURE, ESPECIALLY A PROPULSION SYSTEM, PROVIDED WITH AN INSTANTANEOUS SHOCK ABSORBER.
CN100419245C (en) * 2004-12-08 2008-09-17 中国北方工业公司 Delay igniter for composite enhanced distance bullet rocket engine
RU212932U1 (en) * 2022-06-30 2022-08-12 федеральное государственное бюджетное образовательное учреждение высшего образования "Казанский национальный исследовательский технический университет им. А.Н.Туполева-КАИ" Nozzle plug for solid propellant rocket engine

Similar Documents

Publication Publication Date Title
GB1364728A (en) Launching tube for a missile
GB768295A (en) Improvements in and relating to a projectile
ES336633A1 (en) Rifle grenade
GB1162158A (en) Improvements in Caseless Ammunition
GB1465550A (en) Projectile launching device
GB1454009A (en) Cartridge for small arms
GB1468814A (en) Rocket propulsion motors
GB1470906A (en) Safety devices for projectiles
GB933114A (en) Improved projectile for a mortar having a non-rifled bore
GB1098020A (en) Recoil-free weapon
GB1274632A (en) A projectile
GB1227891A (en)
GB1221553A (en) Improvements relating to mortars and projectiles
GB1483478A (en) Spinning projectile
GB1222501A (en) Tubular-shaped launcher for projectiles, in particular fr guided missiles
GB1267679A (en) Launching device for rockets
US2938482A (en) Solid propellant starter for liquid fuel monopropellant torpedo propulsion system
GB961001A (en) Improvements in propulsion units having a plurality of reaction propulsion nozzles
GB1255339A (en) A missile launcher for use on aircraft
GB1412390A (en) Missile with a rocket propulsion device and a barrel from which the missile can be fired
GB1265112A (en)
GB824759A (en) Improvements in or relating to supersonic barrel-fired projectiles carrying propulsion units
GB951969A (en) Improvements in and relating to a gyratory self-propelled projectile
GB855591A (en) Arrangement of rocket drive mechanisms on flying objects
FR2290648A1 (en) Projectile launching equipment - has braking propellant with ballast behind gunpowder charge

Legal Events

Date Code Title Description
PS Patent sealed
PCNP Patent ceased through non-payment of renewal fee