US3238877A - Priming device for igniting the main charge of a missile - Google Patents

Priming device for igniting the main charge of a missile Download PDF

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Publication number
US3238877A
US3238877A US362884A US36288464A US3238877A US 3238877 A US3238877 A US 3238877A US 362884 A US362884 A US 362884A US 36288464 A US36288464 A US 36288464A US 3238877 A US3238877 A US 3238877A
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US
United States
Prior art keywords
charge
main charge
priming
disk
missile
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
US362884A
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English (en)
Inventor
Simmons Bjorn Herman Olof
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 Bofors AB
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Bofors AB
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Filing date
Publication date
Application filed by Bofors AB filed Critical Bofors AB
Application granted granted Critical
Publication of US3238877A publication Critical patent/US3238877A/en
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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Classifications

    • 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
    • F42C19/0807—Primers; Detonators characterised by the particular configuration of the transmission channels from the priming energy source to the charge to be ignited, e.g. multiple channels, nozzles, diaphragms or filters
    • 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
    • F42—AMMUNITION; BLASTING
    • F42C—AMMUNITION FUZES; ARMING OR SAFETY MEANS THEREFOR
    • F42C19/00—Details of fuzes
    • 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
    • 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
    • F42C19/0838—Primers or igniters for the initiation or the explosive charge in a warhead

Definitions

  • the present invention relates to a device for igniting the main charge of a missile by hot gases generated by igniting a priming charge.
  • the main charge of the missile may be a luminous or illuminating charge, that is a light-generating charge, as used for instance in star shells, a propellant charge as used in rockets or any other charge of the type which is ignited by hot gases genera-ted by a priming charge and which, in turn, generates heat when ignited.
  • a problem common to all missiles of the general kind above referred to is to effect a rapid and substantially uniformly distributed ignition of the main charge by the priming charge upon ignition of thelatter.
  • FIG. 2 is a perspective View, partly in section, of the device proper on an enlarged scale, and
  • FIG. 3 is an exploded view of the device.
  • FIG. 1 shows a shell or projectile 1 with afuze 2 in its nose cone.
  • the main charge such as a combustible luminous composition 3 is enclosed in a casing 4 which, in turn, is placed in the outer shell of the missile.
  • the composition of the main charge should be visualized as being conventional and does not constitute part of the invention, provided only that the main charge 3 is ignitable by hot gases and in turn generates heat when ignited. Many suitable compositions of thiskind are well known in the art.
  • Casing 4 is headed over at its rim to form a flange 5 for retaining a circular disk 6.
  • a spacer ring 11 between disk 6 and the top surface 3a of the main charge is provided to define a narrow, circular space 13 between the bottom side of disk 6 and the top side of charge 3.
  • a boss 7 rises from the center portion of the disk. The boss is hollow to form a priming hole 9 communicating with space 13.
  • An'annular priming charge 8 of suitable and conventional composition is inserted into the cavity small quantities of the so-called powder pellet type.
  • primary charges of this kind are not very effective. In some instances, in particular for the ignition of light generating compositions, it is desired to obtain a Widely distributed and substantially instant ignition of the pyrotechnical main charge.
  • a more specific object of the invention is to provide a novel and improved device for igniting the main charge of missiles of the general kind above referred to, which device distributes the hot gases generated upon ignition of the priming charge substantially over the surface of the main charge exposed to the hot gases, thereby effecting a substantially simultaneous ignition of said surface.
  • FIG. 1 is a perspective view of an illuminating shell such as a star shell equipped with an igniting device according to the invention.
  • Disk -6 includes a ring of circumferentially spaced apertures 10 preferably placed concentric with priming hole 9.
  • the diameter of the ring of apertures is such that the ring is close to the outer periphery of disk 6 and particularly to the inner perimeter of flange 5.
  • the outer rim of spacer ring 11 coincides substantially with the outer diameter of disk 6 and the inner rim of the ring is outside the outer circle defined by holes 10.
  • the priming charge 8 is ignited through its priming hole 9 upon activation of fuze 2 in a manner not shown in detail but well understood in the art.
  • the flame and the hot gases now generated by priming charge 8 escape to a small extent through priming hole 9 but the large portion of the hot gases flows outwardly within space 13 as defined by surfaces 3a and 12 and escapes through apertures 10 as it is indicated in FIG. 3 by outwardly pointing arrows.
  • the hot gases or flames generated by the priming charge come in intimate contact with substantially the entire surface 3a within the area encircled by spacer ring 11 and thus cause substantially simultaneous ignition of this area.
  • the circumferential spacing between aperture 10 in the disk and the disk material itself are such that the hot gases of the priming charge will not burn or otherwise destroy the disk so that the disk will remain substantially intact even after the priming charge has burned completely.
  • the ignition of the main charge 3, such as a luminous composition results in the generation of a more intense flow of heat and such intensified flow will destroy the disk material between adjacent apertures 10.
  • the inner portion of the disk as defined by the ring of apertures 10 will become separated from the remaining outer ring of the disk, aided by reinforcement of the outer disc ring flange 5 and spacer ring 11.
  • the device of the invention when applied to illuminating missiles has the advantage that the full luminous intensity of the missile is obtained practically immediately upon ignition of the composition 3. Obviously, it is of great importance for missiles such as star shells to utilize to the fullest extent the illuminating capability of the charge.
  • the principle of the invention can be applied to other missiles also such as rockets, or wherever a rapid ignition of a main charge is essential.
  • the function of the device for all types of missiles is automatically and substantially improved when the missile is fired from a rifled barrel to impart a spin to the missile during its trajectory. As it is evident, such spin will substantially increase the rate of flow of the hot gases within space 13.
  • a device for igniting the main charge of a missile comprising a casing open at one end and containing the main charge to be ignited, a closure disk closing said open end of the casing spaced apart from the charge therein to define a shallow space between the closure disk and the adjacent top surface of the main charge, a priming charge generating a flow of hot gases when ignited disposed at the outside of said closure disk, and a central inlet duct leading from said priming charge into said space for directing the gases generated by said priming charge into said space and into contact with said main charge to ignite the same, said closure disk including several apertures disposed about said inlet duct, whereby said flow of gases is guided through said space along the top surface of the main charge substantially parallel thereto and discharged through said apertures.
  • a device wherein said casing has a circular cross section and said main charge fills the same at least adjacent to said closure disk, and wherein said disk is a circular disk, said disk apertures defining a concentric ring about said central duct.
  • a device wherein a reinforcing ring portion overlies the peripheral portion of the disk radially outside of said ring of apertures to reinforce said outer peripheral portion of the disk.
  • a device wherein the rim at the open end of the casing is beaded over said disk to form said reinforcing ring portion.
  • a device in the form of a hollow boss rising from the center of said disk at the outside thereof and in communication with said space, said priming charge being disposed in said hollow boss.
  • a device wherein the apertures in said closure disk define a concentric ring of circumferentially spaced apertures closely adjacent to the peripheral rim of the disk, and a reinforcing ring overlies the peripheral portion of the disk outside of said ring of apertures, the material of the disk, at least between said apertures, being resistant to the action of the hot gases generated upon ignition of the priming charge and being destroyed by the action of the heat generated upon ignition of the main charge whereby the portion of the disk within said ring of apertures becomes detached from the peripheral disk portion outside of said ring of apertures.

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  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
  • Toys (AREA)
US362884A 1963-06-28 1964-04-27 Priming device for igniting the main charge of a missile Expired - Lifetime US3238877A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
SE719663 1963-06-28

Publications (1)

Publication Number Publication Date
US3238877A true US3238877A (en) 1966-03-08

Family

ID=20270685

Family Applications (1)

Application Number Title Priority Date Filing Date
US362884A Expired - Lifetime US3238877A (en) 1963-06-28 1964-04-27 Priming device for igniting the main charge of a missile

Country Status (9)

Country Link
US (1) US3238877A (da)
BE (1) BE648075A (da)
CH (1) CH413664A (da)
DK (1) DK112431B (da)
ES (1) ES298825A1 (da)
FI (1) FI41628C (da)
FR (1) FR1394581A (da)
GB (1) GB1067124A (da)
NL (1) NL6405861A (da)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3578011A (en) * 1969-01-29 1971-05-11 Us Army Pyro fluidic relay
US4488490A (en) * 1983-08-29 1984-12-18 The United States Of America As Represented By The Secretary Of The Army Percussion initiated spotting charge
US8607708B1 (en) 2011-05-31 2013-12-17 The United States Of America As Represented By The Secretary Of The Air Force Impact igniting incendiary device for projectiles

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1943292A (en) * 1926-03-11 1934-01-16 Us Government Illuminating projectile
US2342096A (en) * 1941-08-21 1944-02-15 Louis J Zimmerman Illuminating projectile
US2604849A (en) * 1947-05-20 1952-07-29 Reconstruction Finance Corp Illuminating projectile
US2995088A (en) * 1959-06-29 1961-08-08 Bermite Powder Company Multi-stage igniter charge
US3000311A (en) * 1956-11-06 1961-09-19 Standard Oil Co Igniter for rocket propellant

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1943292A (en) * 1926-03-11 1934-01-16 Us Government Illuminating projectile
US2342096A (en) * 1941-08-21 1944-02-15 Louis J Zimmerman Illuminating projectile
US2604849A (en) * 1947-05-20 1952-07-29 Reconstruction Finance Corp Illuminating projectile
US3000311A (en) * 1956-11-06 1961-09-19 Standard Oil Co Igniter for rocket propellant
US2995088A (en) * 1959-06-29 1961-08-08 Bermite Powder Company Multi-stage igniter charge

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3578011A (en) * 1969-01-29 1971-05-11 Us Army Pyro fluidic relay
US4488490A (en) * 1983-08-29 1984-12-18 The United States Of America As Represented By The Secretary Of The Army Percussion initiated spotting charge
US8607708B1 (en) 2011-05-31 2013-12-17 The United States Of America As Represented By The Secretary Of The Air Force Impact igniting incendiary device for projectiles

Also Published As

Publication number Publication date
FI41628B (da) 1969-09-01
NL6405861A (da) 1964-12-29
FR1394581A (fr) 1965-04-02
DK112431B (da) 1968-12-09
ES298825A1 (es) 1964-08-16
CH413664A (de) 1966-05-15
GB1067124A (en) 1967-05-03
FI41628C (fi) 1969-12-10
BE648075A (da) 1964-09-16

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