US3071073A - Projectiles to be launched by means of a firearm and including an auxiliary propulsion motor - Google Patents

Projectiles to be launched by means of a firearm and including an auxiliary propulsion motor Download PDF

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Publication number
US3071073A
US3071073A US27631A US2763160A US3071073A US 3071073 A US3071073 A US 3071073A US 27631 A US27631 A US 27631A US 2763160 A US2763160 A US 2763160A US 3071073 A US3071073 A US 3071073A
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US
United States
Prior art keywords
projectile
motor
barrel
firearm
auxiliary
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
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US27631A
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English (en)
Inventor
Ammann Rudolf
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.)
Brevets Aero Mecaniques SA
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Brevets Aero Mecaniques SA
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Publication date
Application filed by Brevets Aero Mecaniques SA filed Critical Brevets Aero Mecaniques SA
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Publication of US3071073A publication Critical patent/US3071073A/en
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Expired - Lifetime legal-status Critical Current

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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
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
    • F42B30/00—Projectiles or missiles, not otherwise provided for, characterised by the ammunition class or type, e.g. by the launching apparatus or weapon used
    • F42B30/04—Rifle grenades

Definitions

  • the present invention relates to projectiles intended to be slidably fitted on the end of a firearm barrel so as to be launched in the manner known for rifle grenades, said projectile being further provided with an auxiliary propulsion motor, advantageously of the rocket type.
  • the object of the present invention is to provide a projectile of this kind which is better adapted to meet the requirements of practice than those used up to now and in particular which is such that the recoil resulting from launching is reduced.
  • the chief feature of the present invention consists in making the auxiliary propulsion motor slidable axially with respect to the projectile proper between a front abutment and a rear abutment both carried by said projectile, and this in such manner that when the firearm is fired only the projectile is initially accelerated when the firearm is fired and thus is the only part to give rise to a recoil, means being provided to ignite said auxiliary propulsion motor in response to the launching of the projectile so that said auxiliary motor quickly comes to bear against the front abutment of the projectile and then transmits its thrust thereto.
  • said motor is such, and ignited in such manner, that, upon launching, it is accelerated sufiiciently quickly not to be contacted by the rear abutment of the projectile.
  • FIG. 1 is a diagrammatic axial sectional view of a projectile made according to the present invention, fitted on the muzzle end of a rifle barrel.
  • FIG. 2 is an enlarged view of a portion of the structure shown by FIG. 1.
  • the rifle barrel is shown at 1.
  • the warhead 2 of the projectile is provided with a rearward tubular extension 3 adapted to be mounted With a sliding fit on the muzzle end of barrel 1.
  • This tubular extension 3 carries, coaxially mounted in a slidable manner around it, an annular rocket motor 4.
  • This rocket motor 4 includes an annular chamber 5, closed at the front and communicating at the rear with the atmosphere through an annular nozzle 6 (or a plurality of separate nozzles distributed about tube 1).
  • the frontward axial displacements of rocket motor 4 with respect to extension 3 are limited by a front abutment element, consisting in the example shown, of the rear face of the warhead and adapted to cooperate with a corresponding abutment element 19 consisting for instance of the front edge of rocket motor 4.
  • Means are provided to ignite the propelling charge of rocket motor 4 and preferably the whole is arranged in such manner that the thrust of the rocket is sufficient to prevent abutment element 7 from coming into contact with abutment element 8, abutment element It) coming to bear upon abutment element 9 to transmit the thrust of said rocket to the projectile.
  • the means for igniting the charge of the rocket motor may be of any kind, for instance they may be electric means.
  • the front end of tubular extension 3 is provided with a passage 11 capable, after the projectile has moved a short distance relatively to rocket motor 4, of communicating through a conduit 12 with the front end of the chamber 5 of said rocket motor.
  • the propelling charge of the rocket motor will be ignited as soon as the projectile has just started moving, the communication between passage 11 and conduit 12 being subsequently closed by further relative forward movement of the projectile.
  • passage 11 may quite well communicate with the outside as long as it is cleared by the rearward relative movement of the rocket motor with respect to the projectile. During this period, some technical advantages will be obtained due to the existence of passage 11, such as relatively smooth disengagement of tubular extension 3 from barrel 1, a propelling action exerted on the projectile by the reaction due to the gases issuing through passage 11 and possibly a rotation imparted to the projectile about its axis if the direction of the outlet of passage 11 is suitably chosen.
  • a second passage 11 may be provided, such as shown in dot-and-dash lines at 11 on FIG. 2, this passage l1 opening into the wall of tubular extension 3 at a point diametrally opposed to that Where passage 11 opens.
  • means are provided so that, before the projectile has moved a distance X relatively to the rocket motor, the gases which up to then were entrapped in the firearm barrel are allowed to escape to the outside.
  • safety means are provided between abutment elements and it so that, as long as these elements have not come into contact with each other as a consequence of the projectile being launched, said projectile cannot burs
  • a push-piece I14 as long as it has not been pushed back by contact element 10, prevents the operation of the electric fuze of the projectile.
  • the projectile is provided with conventional stabilizing fins carried by the rear end of rocket Furthermore, barrel It is advantageously provided with a deflecting shield 16 intended to act as a protection against the combustion gases issuing from nozzle 6.
  • a projectile intended to be launched from a firearm barrel which comprises, in combination, a body forming the projectile proper, means rigid with said body for slidably engaging the launching firearm barrel to transmit to said body the thrust of powder gases in said barrel, an auxiliary jet motor for propulsion of said projectile mounted slidable in the fore and aft direction with respect to said body, said jet motor being di posed laterally of the above-mentioned means so as to undergo no propelling action from the powder gases in said barrel, two abutments, a front one and a rear one, carried by said body in fixed position with respect thereto, said abutments being mounted to cooperate with portions of said auxiliary motor to limit the sliding displacements thereof with respect to said body, the portion of said auxiliary motor cooperating with the rear abutment being at a distance from said rear abutment when said projectile is set for launching, and means responsive to the initial forward accelerution of said projectile upon launching for starting said auxiliary motor into operation as soon as said projectile has moved
  • a projectile intended to be launched from a firearm barrel which comprises, in combination, a body forming the projectile proper, means rigid with said body for slidably engaging the launching firearm barrel to transmit to said body the thrust of powder gases in said barrel, an auxiliary jet motor for propulsion of said projectile mounted slidable in the fore and aft direction with respect to said body, said jet motor being disposed laterally of the above-mentioned means so as to undergo no propelling action from the powder gases in said barrel, two abutments, a front one and a rear one, carried by said body in fixed position with respect thereto, said abutments being mounted to cooperate with portions of said auxiliary motor to limit the sliding displacement thereof with respect to said body, the portion of said auxiliary motor cooperating with the rear abutment being at a distance from said rear abutment when said projectile is set for launching, and means responsive to the initial forward acceleration of said projectile upon launching for starting said auxiliary motor into operation as soon as said projectile has moved forward, whereby said
  • a projectile intended to be launched from a firearm barrel which comprises, in combination, a body forming the projectile proper, a tubular rearward extension of said body rigid therewith along the axis thereof, said tubular extension being adapted to fit slidably on the end of the launching firearm barrel to transmit to said body the thrust of powder gases in said barrel, auxiliary motor means for propulsion of said projectile consisting of an annular rocket motor surrounding said tubular extension coaxially therewith and undergoing no propelling action from the powder gases in said barrel, the annular nozzle of said rocket motor being at the rear thereof, said rocket motor being slidable longitudinally with respect to said extension, a rear abutment carried by said extension in fixed position and adapted to cooperate with a portion of said rocket motor to limit relative displacements of said rocket motor toward the rear with respect to said extension, a front abutment carried by said projectile in fixed position thereon and adapted to cooperate with said rocket motor to limit relative displacements of said rocket motor toward the front with respect to said projectile, said rocket motor being at
  • said means for igniting said rocket motor includes a passage extending through the front end of said tubular extension, said rocket motor being provided with a corresponding conduit capable of connecting said passage with the inside of the rocket motor after the projectile has moved a sma l distance forwardly with respect to said rocket motor, whereby the rocket motor is ignited by the powder gases from the barrel of the firearm.
  • a projectile according to claim 1 further including means for connecting the inside of said tubular extension with the external atmosphere after the projectile has moved forwardly with respect to the auxiliary motor a distance smaller than the total relative displacement permitted by said abutments.
  • a projectile according to claim 1 further including means for preventing burs-ting of said projectile as long as said auxiliary motor has not come into contact with said front abutment.

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  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Combustion & Propulsion (AREA)
  • Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
  • Portable Nailing Machines And Staplers (AREA)
  • Toys (AREA)
US27631A 1959-05-21 1960-05-09 Projectiles to be launched by means of a firearm and including an auxiliary propulsion motor Expired - Lifetime US3071073A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
LU37220A LU37220A1 (es) 1959-05-21 1959-05-21

Publications (1)

Publication Number Publication Date
US3071073A true US3071073A (en) 1963-01-01

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US27631A Expired - Lifetime US3071073A (en) 1959-05-21 1960-05-09 Projectiles to be launched by means of a firearm and including an auxiliary propulsion motor

Country Status (9)

Country Link
US (1) US3071073A (es)
BE (1) BE590248A (es)
CH (1) CH361738A (es)
DE (1) DE1126281B (es)
ES (1) ES257651A1 (es)
FR (1) FR1257480A (es)
GB (1) GB872588A (es)
LU (1) LU37220A1 (es)
NL (2) NL104594C (es)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3388666A (en) * 1966-03-22 1968-06-18 Karlsruhe Augsburg Iweka Rifle grenade
US3479956A (en) * 1966-09-14 1969-11-25 Brevets Aero Mecaniques Self-propelled rifle grenade capable of being launched by bullet impact
US5069135A (en) * 1988-12-08 1991-12-03 Aktiebolaget Bofors Ignition system

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
BE885618R (fr) * 1979-11-30 1981-04-10 Herstal Sa Projectile telescopique
IL260886B (en) * 2018-07-30 2021-04-29 Rafael Advanced Defense Systems Ltd Rocket armament that can be launched from a tubular launcher with non-ignition security outside the launcher and engine separation in flight

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2700337A (en) * 1952-02-28 1955-01-25 James M Cumming Liquid propellent rocket
US2753801A (en) * 1952-02-28 1956-07-10 James M Cumming Combination liquid and solid propellent rocket
US2770904A (en) * 1950-10-24 1956-11-20 Brevets Aero Mecaniques Grenade launching device for a firearm having a muzzle brake
US2801586A (en) * 1953-09-03 1957-08-06 Mongello Thomas Subcaliber mortar trainer shell
FR1171438A (fr) * 1957-01-15 1959-01-26 Perfectionnements relatifs à des projectiles auto-propulsés et à des engins analogues

Family Cites Families (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
AT201476B (de) * 1957-01-17 1959-01-10 Latham Valentine Stewa Blacker Durch Rückstoß angetriebener Körper

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2770904A (en) * 1950-10-24 1956-11-20 Brevets Aero Mecaniques Grenade launching device for a firearm having a muzzle brake
US2700337A (en) * 1952-02-28 1955-01-25 James M Cumming Liquid propellent rocket
US2753801A (en) * 1952-02-28 1956-07-10 James M Cumming Combination liquid and solid propellent rocket
US2801586A (en) * 1953-09-03 1957-08-06 Mongello Thomas Subcaliber mortar trainer shell
FR1171438A (fr) * 1957-01-15 1959-01-26 Perfectionnements relatifs à des projectiles auto-propulsés et à des engins analogues

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3388666A (en) * 1966-03-22 1968-06-18 Karlsruhe Augsburg Iweka Rifle grenade
US3479956A (en) * 1966-09-14 1969-11-25 Brevets Aero Mecaniques Self-propelled rifle grenade capable of being launched by bullet impact
US5069135A (en) * 1988-12-08 1991-12-03 Aktiebolaget Bofors Ignition system

Also Published As

Publication number Publication date
NL251775A (es)
ES257651A1 (es) 1960-10-01
BE590248A (fr) 1960-10-28
DE1126281B (de) 1962-03-22
FR1257480A (fr) 1961-03-31
NL104594C (es)
GB872588A (en) 1961-07-12
CH361738A (fr) 1962-04-30
LU37220A1 (es) 1960-11-21

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