GB2402462A - Method and device for a multiple step rocket - Google Patents

Method and device for a multiple step rocket Download PDF

Info

Publication number
GB2402462A
GB2402462A GB0309642A GB0309642A GB2402462A GB 2402462 A GB2402462 A GB 2402462A GB 0309642 A GB0309642 A GB 0309642A GB 0309642 A GB0309642 A GB 0309642A GB 2402462 A GB2402462 A GB 2402462A
Authority
GB
United Kingdom
Prior art keywords
rocket
rocket engine
engine
ignition
exhaust nozzle
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.)
Granted
Application number
GB0309642A
Other versions
GB2402462B (en
Inventor
Lars Nilsson
Lars Ax
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.)
Saab AB
Original Assignee
Saab 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 Saab AB filed Critical Saab AB
Priority claimed from PCT/SE2001/002381 external-priority patent/WO2002036955A1/en
Publication of GB2402462A publication Critical patent/GB2402462A/en
Application granted granted Critical
Publication of GB2402462B publication Critical patent/GB2402462B/en
Anticipated expiration legal-status Critical
Expired - Lifetime 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
    • F02K9/08—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using solid propellants
    • 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
    • F02K9/95—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof characterised by starting or ignition means or arrangements
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2250/00—Geometry
    • F05D2250/20—Three-dimensional
    • F05D2250/23—Three-dimensional prismatic
    • F05D2250/232—Three-dimensional prismatic conical

Abstract

The present invention relates to a method and an arrangement for, in multi-stage rockets (3) provided with a number of successively ignitable rocket engines (7, 13) arranged one in front of another in the flying direction of the rocket and joined together detachably with one another, each following rocket engine (13) in the ignition sequence depending, for its ignition, on being initiated after a preceding rocket engine (7) has been able to bun out, causing each preceding rocket engine (7) included in the ignition sequence to be jettisoned by virtue of the next engine having reached its working pressure. According to the invention, each preceding rocket engine is designed with a preferably conical guide part (11) which is directed forwards in the flying direction of the rocket and geometrically adapted to the exhaust nozzle (12) of the following rocket engine (13) and which, in the initial position, is fitted into said exhaust nozzle (12) and fixed in this position by means of at least one blocking part (15) which is deformable or capable of elastic recovery.

Description

GB 2402462 A continuation (74) Agent and/or Address for Service: Lloyd
Wise Commonwealth House, 1-19 New Oxford Street, LONDON, WC1A 1LW, United Kingdom
GB0309642A 2000-10-31 2001-10-30 Method and device for a multiple step rocket Expired - Lifetime GB2402462B (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
SE0039636 2000-10-31
PCT/SE2001/002381 WO2002036955A1 (en) 2000-10-31 2001-10-30 Method and device for a multiple step rocket

Publications (2)

Publication Number Publication Date
GB2402462A true GB2402462A (en) 2004-12-08
GB2402462B GB2402462B (en) 2005-08-31

Family

ID=33448609

Family Applications (1)

Application Number Title Priority Date Filing Date
GB0309642A Expired - Lifetime GB2402462B (en) 2000-10-31 2001-10-30 Method and device for a multiple step rocket

Country Status (1)

Country Link
GB (1) GB2402462B (en)

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN103122807B (en) * 2013-01-16 2014-11-12 西北工业大学 Multichannel solid rocket engine ignition sequence control method

Family Cites Families (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2724237A (en) * 1946-03-05 1955-11-22 Clarence N Hickman Rocket projectile having discrete flight initiating and sustaining chambers
US3385063A (en) * 1962-03-19 1968-05-28 Air Force Usa Multi-stage solid propellant motor
DE1298369B (en) * 1966-07-30 1969-06-26 Messerschmitt Boelkow Blohm Multi-stage solid rocket
FR2376301A1 (en) * 1976-12-28 1978-07-28 Luchaire Sa SELF-PROPELLED MACHINE WITH SEPARABLE STAGES
DE3686321T2 (en) * 1985-10-31 1992-12-17 British Aerospace EXHAUST DRIVE FOR AIRCRAFT.
US6352030B1 (en) * 1998-11-12 2002-03-05 Cordant Technologies Inc. Gas generating eject motor

Also Published As

Publication number Publication date
GB2402462B (en) 2005-08-31

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Legal Events

Date Code Title Description
PE20 Patent expired after termination of 20 years

Expiry date: 20211029