US3581662A - Solid propellant igniter - Google Patents

Solid propellant igniter Download PDF

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Publication number
US3581662A
US3581662A US814076A US81407669A US3581662A US 3581662 A US3581662 A US 3581662A US 814076 A US814076 A US 814076A US 81407669 A US81407669 A US 81407669A US 3581662 A US3581662 A US 3581662A
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US
United States
Prior art keywords
igniter
cavities
axial bore
set forth
charge
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 - Lifetime
Application number
US814076A
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English (en)
Inventor
Robert Omer Emmanuel Grebert
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ARMY FRANCE
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ARMY FRANCE
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Publication date
Application filed by ARMY FRANCE filed Critical ARMY FRANCE
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Publication of US3581662A publication Critical patent/US3581662A/en
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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42C—AMMUNITION FUZES; ARMING OR SAFETY MEANS THEREFOR
    • F42C19/00—Details of fuzes
    • F42C19/08—Primers; Detonators
    • F42C19/0823—Primers or igniters for the initiation or the propellant charge in a cartridged ammunition
    • F42C19/0826—Primers or igniters for the initiation or the propellant charge in a cartridged ammunition comprising an elongated perforated tube, i.e. flame tube, for the transmission of the initial energy to the propellant charge, e.g. used for artillery shells and kinetic energy penetrators
    • 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

Definitions

  • An igniter suitable for use with solid propellant rockets comprises a substantially cylindrical body formed of a flexible plastic material having an axial bore and axially extending cylindrical cavities symmetrically distributed around the axial bore with the axes of the cavities lying on at least one ring centered on the bore axis. Radial passages connect the cavities with the axial bore and with the outside of the body.
  • a primary charge, preferably of black powder contained in a latticework casing, and means for assembling the primary charge are located in the axial bore, and an ignition charge comprising alumino-thennic pellets are symmetrically located in the cavities.
  • One type of conventional igniter for solid propellant systems consists of a primary charge of gunpowder-type black powder and an ignition charge of alumino-thermic pellets, the pellets being loosely placed in a perforate, rigid plastics material cage surrounding the primary charge.
  • This type of igniter has a poor resistance to vibration, to temperature variations, and gives irreproducible results with respect to the pressure and duration of the ignition. Since the pellets are loosely disposed in the rigid plastics cage they are liable to break or crumble, particularly on mechanical impact.
  • an igniter suitable for use with solid propellant rockets which comprises a substantially cylindrical body, formed ofa flexible plastics material, having an axial bore and axially extending cylindrical cavities symmetrically distributed around the axial bore with the axes of the cavities lying on at least one ring centered on the bore axis, radial passages connecting the cavities to the axial bore and to the outside of the body, a primary charge and means for assembling the primary charge located in the axial bore, and an ignition charge comprising alumino-thermic pellets symmetrically located in the cavities.
  • the primary charge may be a black powder of the gunpowder-type or one which does not give a high detonation pressure (e.g. alumino-thermic powders such as ALCLO which is a trade designation of Aerojet-General Corporation).
  • the primary charge is contained in a latticework casing having a plastics cover, the charge being detonated by an electric ignition device associated with a pyrotechnic system or by a purely pyrotechnic system.
  • the ignition charge comprises alumino-thermic pellets symmetrically disposed in the cavities.
  • the diameter of the cavities is preferably between 0.l and 0.4 times the diameter of the igniter and is preferably substantially equal to that of the pellets so that they are held closely in the cavities.
  • the diameter of the pellets is typically from I to30 mm.
  • FIG. I is a partially sectional elevation of a preferred embodiment of an igniter according to the invention.
  • FIG. 2 is a graph of the ignition pressure against ignition duration showing the reproducibility of ignition using igniters according to the invention.
  • the igniter comprises a substantially cylindrical body 1 made of flexible plastics material, eg a polyurethane containing an alkaline-earth metal oxalate filler, having an axial bore 2 holding the primary charge and cylindrical cavities 3 symmetrically distributed in an annular relationship around the axial bore and holding the ignition charge. Radial holes 4 and 5 are provided to connect the cavities to the axial bore and to the exterior of the igniter.
  • the axial bore holds a primary charge consisting of 1.7 g of gunpowder-type black powder 6 in a latticework cage 7 having a polyethylene cover, the charge being detonated by an electric ignition device 8 via a pyrotechnic system 9.
  • the ignition charge consists of 25 g of alumino-thermic ignition pellets 10 (comprising a mixture of potassium perchlorate, aluminum and a binder such as aluminum stearate).
  • the pellets are 9.5 mm. in diameter, 2.5 mm. thick, and weight 0.26 g each, and are symmetrically stacked in the cylindrical cavities 3 around the central bore 2.
  • the igniter body- is sealed at one end by a stopper ll, and the other end is secured to an adapter 12 for assembling the i gniter in the front part of the propulsion unit.
  • the primary charge is attached to a tube support 13 which in turn is rigidly secured to a member 14.
  • the point 15 where the wires of the electric ignition device enter the tube support is sealed by packing materials, and the point where the wires enter the adapter is also sealed by conventional sealing compounds.
  • the flexible plastics igniter body can be manufactured by molding in an open mold and. by subsequently piercing the shaped body with radial holes.
  • the flexible plastics material can be any of the known plastics which do not deteriorate under the conditions produced by the combustion of the propergol blocks.
  • Polyurethane resin containing an alkaline-earth metal oxalate filler is particularly suitable, since it is very easily worked, is extremely flexible, and has a high resistance to elevated temperatures, with the result that it need not be ejected from the unit in use. If, in fact, the igniter is ejected, then there is no danger that the pipe will be destroyed.
  • This igniter has an improved mechanical resistance to vibration and to temperature variations. It also gives results which are closely reproducible with regard to ignition duration and pressure characteristics. Typical ignition duration and pressure variations do not exceed 15 percent and I0 percent of the average values, respectively, whereas for a conventional igniter the variations are more than 39 percent and 23 percent, respectively.
  • the time scatter is 3 ms, 5 ms., 18 ms. and 20 ms.
  • the pressure scatter is 0. l3 bar and 0.77 bar.
  • the igniter was also subjected to vibration under very sever conditions without any dust being produced from the charges, whereas a conventional igniter subjected to much less severe vibration conditions produced 2.5 percent of dust. Furthermore, no pellet was broken in the igniter according to the invention, whereas in the conventional igniter the number of broken pellets was relatively high.
  • An igniter suitable for use with solid propellant rockets which comprises i. a substantially cylindrical body formed of a flexible plastics material,
  • said body having axially extending cylindrical cavities therein symmetrically distributed around said axial bore with the axes of said cavities lying on at least one ring centered on said bore axis, and
  • said body having radial passages therein connecting said cavities to said axial bore and to the outside of said body
  • an ignition charge comprising alumino-thermic pellets symmetrically located in said cavities.

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  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • Air Bags (AREA)
US814076A 1968-04-10 1969-04-07 Solid propellant igniter Expired - Lifetime US3581662A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR147595 1968-04-10

Publications (1)

Publication Number Publication Date
US3581662A true US3581662A (en) 1971-06-01

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ID=8648796

Family Applications (1)

Application Number Title Priority Date Filing Date
US814076A Expired - Lifetime US3581662A (en) 1968-04-10 1969-04-07 Solid propellant igniter

Country Status (5)

Country Link
US (1) US3581662A (de)
DE (1) DE1918046C3 (de)
FR (1) FR1575687A (de)
GB (1) GB1228309A (de)
SE (1) SE337142B (de)

Cited By (15)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3757692A (en) * 1970-04-24 1973-09-11 Etat Francais Defense National Igniting device for a rocket, and its mounting thereon and manufacture
US4080901A (en) * 1976-04-20 1978-03-28 The United States Of America As Represented By The Aministrator Of The National Aeronautics And Space Administration Molded composite pyrogen igniter for rocket motors
US4495866A (en) * 1981-12-28 1985-01-29 Dynamit Nobel Aktiengesellschaft Flash guide tube arrangement for propellant charge igniters
US4539910A (en) * 1983-09-19 1985-09-10 Morton Thiokol, Inc. Igniter pellet cup
US4574699A (en) * 1983-11-17 1986-03-11 Thiokol Corporation Extendible wafer igniter with perforations adjacent the foot portion
US4674405A (en) * 1985-01-23 1987-06-23 Dynamit Nobel Aktiengesellschaft Partially combustible propellant charge igniter
US4770099A (en) * 1976-10-23 1988-09-13 Dynamit Nobel Ag Propellant charge igniter
US5400715A (en) * 1993-03-15 1995-03-28 The Secretary Of State For Defence In Her Britannic Majesty's Government Of The United Kingdom Of Great Britain And Northern Ireland Two part ammunition round
US20090235640A1 (en) * 2008-02-19 2009-09-24 Cavalleri Robert J Pellet Loaded Attitude Control Rocket Motor
US20100011742A1 (en) * 2008-07-17 2010-01-21 Cavalleri Robert J Rocket Motor Containing Multiple Pellet Cells
US20110006152A1 (en) * 2009-02-23 2011-01-13 Olden Thomas A Modular Divert and Attitude Control System
US20110024165A1 (en) * 2009-07-31 2011-02-03 Raytheon Company Systems and methods for composite structures with embedded interconnects
RU2445502C1 (ru) * 2010-08-23 2012-03-20 Государственное образовательное учреждение высшего профессионального образования "Тульский государственный университет" (ТулГУ) Воспламенительное устройство зарядов ракетных двигателей твердого топлива
US8667776B2 (en) 2009-02-23 2014-03-11 Raytheon Company Pellet-loaded multiple impulse rocket motor
US8826640B2 (en) 2010-11-12 2014-09-09 Raytheon Company Flight vehicles including electrically-interconnective support structures and methods for the manufacture thereof

Families Citing this family (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE2355255C2 (de) * 1973-11-05 1984-05-10 Gianni Verga Milano Casati Anzündvorrichtung für Artillerietreibladungen
DE2914975A1 (de) * 1979-02-05 1980-10-23 Heko Elektronik Gmbh & Co Kg Elektrische anzuendeinheit
DE3002072A1 (de) * 1980-01-21 1981-07-23 Friedrich Wilhelm Dipl.-Kfm. 4600 Dortmund Sobbe Druckgasgenerator mit einem elektrischen zuender
DE3217976A1 (de) * 1982-05-13 1983-11-17 Bundesamt für Wehrtechnik u. Beschaffung, 5400 Koblenz Treibladungsanzuender fuer treibladungen extrem hoher ladedichte
DE3226269C2 (de) * 1982-07-14 1986-04-17 Dynamit Nobel Ag, 5210 Troisdorf Teilverbrennbarer Treibladungsanzünder
DE3416736C2 (de) * 1984-05-07 1986-10-02 Dynamit Nobel Ag, 5210 Troisdorf Treibladungsanzünder
DE3512942A1 (de) * 1985-04-11 1986-10-16 Bundesrepublik Deutschland, vertreten durch den Bundesminister der Verteidigung, dieser vertreten durch den Präsidenten des Bundesamtes für Wehrtechnik und Beschaffung, 5400 Koblenz Treibladungsanzuender
CN106014690A (zh) * 2016-07-22 2016-10-12 北京航空航天大学 一种固液火箭发动机烧蚀式非金属点火器

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2995088A (en) * 1959-06-29 1961-08-08 Bermite Powder Company Multi-stage igniter charge
US3062147A (en) * 1959-09-28 1962-11-06 Du Pont Igniter for solid propellant grains
US3151447A (en) * 1960-08-12 1964-10-06 Aerojet General Co Igniter device

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2995088A (en) * 1959-06-29 1961-08-08 Bermite Powder Company Multi-stage igniter charge
US3062147A (en) * 1959-09-28 1962-11-06 Du Pont Igniter for solid propellant grains
US3151447A (en) * 1960-08-12 1964-10-06 Aerojet General Co Igniter device

Cited By (18)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3757692A (en) * 1970-04-24 1973-09-11 Etat Francais Defense National Igniting device for a rocket, and its mounting thereon and manufacture
US4080901A (en) * 1976-04-20 1978-03-28 The United States Of America As Represented By The Aministrator Of The National Aeronautics And Space Administration Molded composite pyrogen igniter for rocket motors
US4770099A (en) * 1976-10-23 1988-09-13 Dynamit Nobel Ag Propellant charge igniter
US4495866A (en) * 1981-12-28 1985-01-29 Dynamit Nobel Aktiengesellschaft Flash guide tube arrangement for propellant charge igniters
US4539910A (en) * 1983-09-19 1985-09-10 Morton Thiokol, Inc. Igniter pellet cup
US4574699A (en) * 1983-11-17 1986-03-11 Thiokol Corporation Extendible wafer igniter with perforations adjacent the foot portion
US4674405A (en) * 1985-01-23 1987-06-23 Dynamit Nobel Aktiengesellschaft Partially combustible propellant charge igniter
US5400715A (en) * 1993-03-15 1995-03-28 The Secretary Of State For Defence In Her Britannic Majesty's Government Of The United Kingdom Of Great Britain And Northern Ireland Two part ammunition round
US20090235640A1 (en) * 2008-02-19 2009-09-24 Cavalleri Robert J Pellet Loaded Attitude Control Rocket Motor
US8127534B2 (en) * 2008-02-19 2012-03-06 Raytheon Company Pellet loaded attitude control rocket motor
US20100011742A1 (en) * 2008-07-17 2010-01-21 Cavalleri Robert J Rocket Motor Containing Multiple Pellet Cells
US20110006152A1 (en) * 2009-02-23 2011-01-13 Olden Thomas A Modular Divert and Attitude Control System
US8242422B2 (en) 2009-02-23 2012-08-14 Raytheon Company Modular divert and attitude control system
US8667776B2 (en) 2009-02-23 2014-03-11 Raytheon Company Pellet-loaded multiple impulse rocket motor
US20110024165A1 (en) * 2009-07-31 2011-02-03 Raytheon Company Systems and methods for composite structures with embedded interconnects
US8809689B2 (en) 2009-07-31 2014-08-19 Raytheon Company Systems and methods for composite structures with embedded interconnects
RU2445502C1 (ru) * 2010-08-23 2012-03-20 Государственное образовательное учреждение высшего профессионального образования "Тульский государственный университет" (ТулГУ) Воспламенительное устройство зарядов ракетных двигателей твердого топлива
US8826640B2 (en) 2010-11-12 2014-09-09 Raytheon Company Flight vehicles including electrically-interconnective support structures and methods for the manufacture thereof

Also Published As

Publication number Publication date
DE1918046C3 (de) 1979-05-03
DE1918046A1 (de) 1969-10-23
SE337142B (de) 1971-07-26
FR1575687A (de) 1969-07-25
DE1918046B2 (de) 1978-08-24
GB1228309A (de) 1971-04-15

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