GB1176956A - Incrementally-Controllable Thrust Propulsion Device - Google Patents

Incrementally-Controllable Thrust Propulsion Device

Info

Publication number
GB1176956A
GB1176956A GB32782/67A GB3278267A GB1176956A GB 1176956 A GB1176956 A GB 1176956A GB 32782/67 A GB32782/67 A GB 32782/67A GB 3278267 A GB3278267 A GB 3278267A GB 1176956 A GB1176956 A GB 1176956A
Authority
GB
United Kingdom
Prior art keywords
layers
separator
fuel
pulse
layer
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
GB32782/67A
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.)
Compagnie Francaise Thomson Houston SA
Original Assignee
Compagnie Francaise Thomson Houston SA
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 Compagnie Francaise Thomson Houston SA filed Critical Compagnie Francaise Thomson Houston SA
Publication of GB1176956A publication Critical patent/GB1176956A/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
    • F02K9/94—Re-ignitable or restartable rocket- engine plants; Intermittently operated rocket-engine plants
    • 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
    • F02K9/26—Burning control

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Solid Fuels And Fuel-Associated Substances (AREA)
  • Laminated Bodies (AREA)

Abstract

1,176,956. Solid fuel motors. COMPAGNIE FRANCAISE THOMSON HOUSTON-HOTCHKISS BRANDT. 17 July, 1967 [26 July, 1966], No. 32782/67. Heading F3A. Incrementally - controllable thrust propulsion device for manoeuvering space vehicles, comprising a casing 1, e.g. of stainless steel, containing alternating combustible fuel layers 4 and separator layers 5, and a single control means such as an electrode 6 for generating pulses of thermal energy to decompose and/or evaporate or sublimate an adjacent separator layer and expose a fuel layer to the pulse to enable it to be ignited, the combustion, of the fuel layer acting to expose a further separator layer which prevents communication of combustion to a next fuel layer until a further pulse is generated. The electrode is urged towards the separator layers by a spring 8, and can be powered by a solar battery E. The separator layers are made of electrically conductive material such as aluminium foil, and form part of the igniting circuit. An automatic or remote controlled switch S operating by a radio link or gyroscopic and inertial means, closes the igniting circuit. The layers 4 and 5 may be flat, concave or cylindrical. In the latter case the layers surround a magnetic core and the separator layers serve as the secondary coils of a transformer, the coils being vaporized upon generation of a current pulse in the primary coil. In other embodiments, the pulse generating means comprise a resistance wire which can be associated with a reflector, a source of radioactivity, or a shutter for allowing sunlight to enter through a transparent portion of the casing. The separator layers used with these latter means include polyvinylchloride, polystyrene, cellulose acetate, urea-formed resins, methacrylates, polyesters, polysulphides, polyurethanes and polybutadiene. The fuel comprises compositions of ammonium perchlorate and asphalt or polyurethane; ammonium nitrate and cellulose acetate; or nitrocellulose, nitroglycerine and plasticizer.
GB32782/67A 1966-07-26 1967-07-17 Incrementally-Controllable Thrust Propulsion Device Expired GB1176956A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR70865A FR1502732A (en) 1966-07-26 1966-07-26 Controllable Thrust Space Thruster Improvements

Publications (1)

Publication Number Publication Date
GB1176956A true GB1176956A (en) 1970-01-07

Family

ID=8614119

Family Applications (1)

Application Number Title Priority Date Filing Date
GB32782/67A Expired GB1176956A (en) 1966-07-26 1967-07-17 Incrementally-Controllable Thrust Propulsion Device

Country Status (4)

Country Link
US (1) US3457726A (en)
BE (1) BE701441A (en)
FR (1) FR1502732A (en)
GB (1) GB1176956A (en)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2326701A (en) * 1994-06-17 1998-12-30 Forsvarets Forsknings Initiating and control of propellent charge burning

Families Citing this family (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2096975B1 (en) * 1970-07-22 1974-05-03 Onera (Off Nat Aerospatiale)
US4357795A (en) * 1980-04-14 1982-11-09 General Dynamics, Pomona Division Multi-burn solid fuel restartable rocket and method of use
US4630437A (en) * 1985-01-29 1986-12-23 The United States Of America As Represented By The Secretary Of The Air Force Optical control method for solid fuel rocket burn rate
US4587805A (en) * 1985-01-29 1986-05-13 The United States Of America As Represented By The Secretary Of The Air Force Electro-optical control of solid fuel rocket burn rate
EP0767872B1 (en) * 1994-04-29 2000-06-28 Cordant Technologies Inc. Solid propellant dual phase rocket motor
US6705075B1 (en) 2000-06-05 2004-03-16 Alliant Techsystems Inc. Digital solid rocket motor and gas generator

Family Cites Families (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB627722A (en) * 1946-11-01 1949-08-15 John Richard Marsden Improvements in or relating to gas-turbine-engines
US2640417A (en) * 1946-12-18 1953-06-02 Us Sec War Ignition safety device for induction fired rockets
US2918871A (en) * 1953-08-04 1959-12-29 Beckman Instruments Inc Electrical detonator
US3033716A (en) * 1955-03-07 1962-05-08 Hercules Powder Co Ltd Gas producing charge
US3000175A (en) * 1955-05-13 1961-09-19 Aerojet General Co Burning rate acceleration catalysts for solid propellant compositions
US3002830A (en) * 1959-01-02 1961-10-03 Olin Mathieson Method of manufacturing solid propellants having a polymeric fuel-binder using a plurality of crosslinking agents
US3128600A (en) * 1960-05-18 1964-04-14 Thiokol Chemical Corp Multilevel solid propellant rocket motor
US3293855A (en) * 1963-10-16 1966-12-27 Gen Motors Corp Reignitable rocket
US3247796A (en) * 1964-03-23 1966-04-26 Howard A Kirshner High pressure sparking device
US3249049A (en) * 1964-07-31 1966-05-03 Zimmerman Theodore Ballistic primer
US3248875A (en) * 1964-10-27 1966-05-03 Robert D Wolcott Re-startable solid fuel rocket motor
US3358452A (en) * 1965-10-21 1967-12-19 Gca Corp Valveless rocket motor using subliming solids

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2326701A (en) * 1994-06-17 1998-12-30 Forsvarets Forsknings Initiating and control of propellent charge burning
GB2326701B (en) * 1994-06-17 1999-03-24 Forsvarets Forsknings Initiating and control of propellent charge burning

Also Published As

Publication number Publication date
FR1502732A (en) 1967-11-24
BE701441A (en) 1968-01-17
US3457726A (en) 1969-07-29

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