US1276892A - Projectile. - Google Patents

Projectile. Download PDF

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Publication number
US1276892A
US1276892A US21157918A US21157918A US1276892A US 1276892 A US1276892 A US 1276892A US 21157918 A US21157918 A US 21157918A US 21157918 A US21157918 A US 21157918A US 1276892 A US1276892 A US 1276892A
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United States
Prior art keywords
projectile
wings
shaft
slit
slots
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
US21157918A
Inventor
Brown Fender
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.)
Individual
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Individual
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.)
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Publication date
Application filed by Individual filed Critical Individual
Priority to US21157918A priority Critical patent/US1276892A/en
Application granted granted Critical
Publication of US1276892A publication Critical patent/US1276892A/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
    • F42B5/00—Cartridge ammunition, e.g. separately-loaded propellant charges
    • F42B5/02—Cartridges, i.e. cases with charge and missile
    • F42B5/03—Cartridges, i.e. cases with charge and missile containing more than one missile
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D14/00—Burners for combustion of a gas, e.g. of a gas stored under pressure as a liquid
    • F23D14/46—Details, e.g. noise reduction means
    • F23D14/62—Mixing devices; Mixing tubes
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
    • F42B10/00—Means for influencing, e.g. improving, the aerodynamic properties of projectiles or missiles; Arrangements on projectiles or missiles for stabilising, steering, range-reducing, range-increasing or fall-retarding
    • F42B10/02—Stabilising arrangements
    • F42B10/14—Stabilising arrangements using fins spread or deployed after launch, e.g. after leaving the barrel
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
    • F42B12/00—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material
    • F42B12/02—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material characterised by the warhead or the intended effect
    • F42B12/36—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material characterised by the warhead or the intended effect for dispensing materials; for producing chemical or physical reaction; for signalling ; for transmitting information
    • F42B12/56—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material characterised by the warhead or the intended effect for dispensing materials; for producing chemical or physical reaction; for signalling ; for transmitting information for dispensing discrete solid bodies
    • F42B12/58—Cluster or cargo ammunition, i.e. projectiles containing one or more submissiles
    • F42B12/62—Cluster or cargo ammunition, i.e. projectiles containing one or more submissiles the submissiles being ejected parallel to the longitudinal axis of the projectile
    • F42B12/64—Cluster or cargo ammunition, i.e. projectiles containing one or more submissiles the submissiles being ejected parallel to the longitudinal axis of the projectile the submissiles being of shot- or flechette-type
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10S—TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10S102/00—Ammunition and explosives
    • Y10S102/703—Flechette

Definitions

  • jectile and the objects of the invention are first, to provide an elongated projectile, second, to provide means for keeping the projectile to its course, third, to provide a simple and eflicient projectile.
  • Fig. 2 is a view in elevation partly in section showing the wings in their retracted V osition, and in open position in dotted mes;
  • Fig. 3 is a cross section on the line 3-3 of Fig. 2;
  • Fig. 4 is a fragmental view in longitudinal section of a gun barrel with a number of projectiles therein.
  • an elongated shaft 1 is provided, the rear portion of which is tubular to reduce its weight and which is slit longitudinally as at 2 to form a bifurcated rear end.
  • the shaft may be made of case hardened steel or other suitable material and has a tip 3 of lead or other heavy metal.
  • Each win is formed with outwardly and rearward y sloping slots 5.
  • Pins 6. are secured in" the rear portion of the shaft 1 and bridge the slit 2 extending through the slots 5 of the win s.
  • Notches 7 may be formed in the edges 0 the Wings to take over the pins 6' when the wings are moved to their innermost positions.
  • a compression spring 8 is located in the tubular portion of the shaft with its rear end abutting the forward ends of the wings for the purpose of forcing the wings rearwardly which causes them to be guided outwardly by the pins -6 and slots 5.
  • a number of these projectiles may be loaded in a gun 9 with a wad or disk 10 interposed between their rear ends and the powder 11.
  • these projectiles may have their rear ends encircled by a cartridge (not shown).
  • a projectile comprising an elongated shaft tubular at its rear end and provided with a longitudinal slit, wings slidably mounted in the slit, said win having inclined slots, pins secured in t e shaft and passing through the slots, and a resilient element within the shaft and abutting the forward ends of the wings to force the win rearwardly, whereby the pins and slots w1 guide the wings outwardly to extended positions.

Description

B. FENDER.
PROJECTILE.
APPLICATION FILED JAN. I2. I918.
Patented Aug. 27, 1918.
v 6 .70 flaw/alkyd? amveutoz w Llf'l woa v A BROWN FENDER, OF KAUFMAN, TEXAS.
rnoincrrnn.
Specification of Letters Patent.
Patented Aug. 2'7, 1918.
Application filed January 12, 1918. Serial No. 211,579.
jectile, and the objects of the invention are first, to provide an elongated projectile, second, to provide means for keeping the projectile to its course, third, to provide a simple and eflicient projectile.
With the foregoing and other objects in view, which will appear as the description proceeds, the invention resides in the combination and arrangement of parts and in the details of construction hereinafter described and claimed, it being understood that changes in the precise embodiment of the invention herein disclosed, can be made Within the scope of what is claimed, without departing from the spirit of the invention.
A practical embodiment of the invention.
is shown in the accompanying drawings, wherein Figure 1 is a perspective view of the projectile as the same appears in flight;
Fig. 2 is a view in elevation partly in section showing the wings in their retracted V osition, and in open position in dotted mes;
Fig. 3 is a cross section on the line 3-3 of Fig. 2;
Fig. 4 is a fragmental view in longitudinal section of a gun barrel with a number of projectiles therein.
Referring to the drawings by-numerals of reference In carrying out the invefition an elongated shaft 1 is provided, the rear portion of which is tubular to reduce its weight and which is slit longitudinally as at 2 to form a bifurcated rear end. The shaft may be made of case hardened steel or other suitable material and has a tip 3 of lead or other heavy metal.
mounted to lie side by si e and be housed within the slit when forcedto their innermost positions. Each win is formed with outwardly and rearward y sloping slots 5. Pins 6. are secured in" the rear portion of the shaft 1 and bridge the slit 2 extending through the slots 5 of the win s. Notches 7 may be formed in the edges 0 the Wings to take over the pins 6' when the wings are moved to their innermost positions.
A compression spring 8 is located in the tubular portion of the shaft with its rear end abutting the forward ends of the wings for the purpose of forcing the wings rearwardly which causes them to be guided outwardly by the pins -6 and slots 5.
As shown in Fig. 4, a number of these projectiles may be loaded in a gun 9 with a wad or disk 10 interposed between their rear ends and the powder 11. For convenience these projectiles may have their rear ends encircled by a cartridge (not shown).
It will be understood that as soon as the projectiles are expelled from the mouth of the gun the wings open under the force of the spring 8 and guide the projectile in its course, preventing it from upsetting.
Having thus described the invention, what is claimed as new and sought by Letters Patent is 1. A projectile compri an elongated shaft tubular at its rear en and rovided with a longitudinal slit, a weighte tip on the shaft, wings slidably mounted in the slit, and a resilient element within the shaft and abutting the forward ends of the to force the wings to extended position.
2. A projectile comprising an elongated shaft tubular at its rear end and provided with a longitudinal slit, wings slidably mounted in the slit, said win having inclined slots, pins secured in t e shaft and passing through the slots, and a resilient element within the shaft and abutting the forward ends of the wings to force the win rearwardly, whereby the pins and slots w1 guide the wings outwardly to extended positions.
In testimony that I claim the foregoing as my own, I have hereto aflixed my signature.
BROWN FENDER.
US21157918A 1918-01-12 1918-01-12 Projectile. Expired - Lifetime US1276892A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
US21157918A US1276892A (en) 1918-01-12 1918-01-12 Projectile.

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US21157918A US1276892A (en) 1918-01-12 1918-01-12 Projectile.

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US1276892A true US1276892A (en) 1918-08-27

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US21157918A Expired - Lifetime US1276892A (en) 1918-01-12 1918-01-12 Projectile.

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Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3048109A (en) * 1958-11-12 1962-08-07 John R Feemster Wing assembly
US3404669A (en) * 1966-01-04 1968-10-08 Army Usa Missiles and discharge apparatus therefor
US3427976A (en) * 1966-10-19 1969-02-18 Singer General Precision Ordnance projectile
US3599568A (en) * 1965-03-31 1971-08-17 Olin Mathieson Long-range shotshell
US3851590A (en) * 1966-12-30 1974-12-03 Aai Corp Multiple hardness pointed finned projectile
US5040746A (en) * 1990-08-14 1991-08-20 The United States Of America As Represented By The Secretary Of The Army Finned projectile with supplementary fins
US20050173588A1 (en) * 2002-11-08 2005-08-11 Giat Industries Method of correcting the trajectory of a spin-stabilised projectile and projectile implementing one such method

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3048109A (en) * 1958-11-12 1962-08-07 John R Feemster Wing assembly
US3599568A (en) * 1965-03-31 1971-08-17 Olin Mathieson Long-range shotshell
US3404669A (en) * 1966-01-04 1968-10-08 Army Usa Missiles and discharge apparatus therefor
US3427976A (en) * 1966-10-19 1969-02-18 Singer General Precision Ordnance projectile
US3851590A (en) * 1966-12-30 1974-12-03 Aai Corp Multiple hardness pointed finned projectile
US5040746A (en) * 1990-08-14 1991-08-20 The United States Of America As Represented By The Secretary Of The Army Finned projectile with supplementary fins
US20050173588A1 (en) * 2002-11-08 2005-08-11 Giat Industries Method of correcting the trajectory of a spin-stabilised projectile and projectile implementing one such method

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