US1376316A - Projectile - Google Patents

Projectile Download PDF

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Publication number
US1376316A
US1376316A US259556A US25955618A US1376316A US 1376316 A US1376316 A US 1376316A US 259556 A US259556 A US 259556A US 25955618 A US25955618 A US 25955618A US 1376316 A US1376316 A US 1376316A
Authority
US
United States
Prior art keywords
projectile
combustible
air
receptacle
heating
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
US259556A
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English (en)
Inventor
Chilowsky Constantin
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
Original Assignee
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.)
Filing date
Publication date
Priority to GB132068D priority Critical patent/GB132068A/en
Priority to FR503934A priority patent/FR503934A/fr
Application filed by Individual filed Critical Individual
Priority to US259556A priority patent/US1376316A/en
Priority to FR21684A priority patent/FR21684E/fr
Priority to GB19131/20A priority patent/GB147104A/en
Application granted granted Critical
Publication of US1376316A publication Critical patent/US1376316A/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
    • 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
    • F42B10/32—Range-reducing or range-increasing arrangements; Fall-retarding means
    • F42B10/38—Range-increasing arrangements
    • F42B10/40—Range-increasing arrangements with combustion of a slow-burning charge, e.g. fumers, base-bleed projectiles

Definitions

  • the applicant for arriving at the same end, takes into consideration the fact that the resistance to Hight depends as much upon the properties of the air as on those of the projectile and increases the range by -dealing with the medium traversed, for example by changing its temperature, its density and its composition.
  • the present invention has for its object a system of reducing the resistance to .the Hight of a projectile by heating the air through which it passes.
  • appropriate means of which several different forms will be hereinafter described, are arranged on the front portion of the projectile, which means have for their object the heating of the air by discharging into the atmosphere for a considerable distance in front of the projectile, combustible, substances which are discharged from a'receptacle specially provided for the purpose in the projectile.
  • the substances act on the air only through their calorific capacity.
  • the substances act both through their calorilic capacity as well as throughA their heat due to combination with oxygen which makes their calorific value greater for a given thermic mass, carried by the projectile.
  • the combustible should be brought to a state such that its combustion can be produced in a current of air of high velocityand maintained in a continuous and regular manner. If the combustible naturally has pyrophoric properties, it will suice to project it in a pulverized form. In any other case, it is necessary before projecting it into the atmosphere to bring it to an appropriate state, of liquid, vapor or gas 'at a suitably high temperature, by the application of heat. Moreover, in order that the combustion may be suiicientlyuperfect the combustible should be mixed rapidly and intimately wlth the air current. This 1s attained b an atomizer or diffuser which emits the ombustible in the form of small jets or thin sheets, or which projects it in small drops.
  • combustible substances those hav.- ing pyrophoric properties, such'as red phosphorus, or the solution of white phosphorus 1n carbon bisulHd orgaseous phosphoreted hydrogen, are suitable.
  • the ways of projecting, heating and vaporizin the com# bustible substances vary accor ing to the nature of the substance employed. Liquid combustibles can be projected and atomlzed by the action of a gaseous pressure. Solid combustibles can be brought to a gaseous, j
  • vaporous or liquid state by partial combust1on in the interior of the receptacle which can-be effected by the addition of a proper quantity of a suitable oxid, such as, for example, one of the metallic oxids, a nitrate or sulfur.
  • a suitable oxid such as, for example, one of the metallic oxids, a nitrate or sulfur.
  • Thermal substances liberating vapoi's-v of incandescent metal may also be conveniently used.
  • bi-oxid of manganese reduced by powder of magnesium or aluminium liberates manganese vapors.
  • Incandescent metallic vapors have par* ticular advantages, owing to their sponta.
  • thermal substances can also be utilized for vaporizing" other combustibles, solid or liquid, when they are placed in contact withzthem, either directly or through the intermediary of metallic walls.
  • substances of imperfect c0mbl ⁇ 1s tion can be advantageously employed as they contain in the heated products of combustion unburnt combustible matter, such as for example celluloid not containing too much camphor.
  • Figure 1 is a cross sectional view of one embodiment of the invention with a receptacle forming the nose piece.
  • Fig. 2 is a cross sectional view of another embodiment showing a receptacle mounted on the nose of the projectile.
  • Fig. 3 is a cross sectional view of another embodiment showing a receptacle mounted in the body of the projectile.
  • Fig. 4 is a cross sectional view of another embodiment showing a receptacle and burner mounted in the nose of the projec-l tile.
  • Fig. 5 is a cross sectional view of another embodiment showing a double chambered receptacle.
  • Fig. 6 is a cross sectional view of another embodiment showing a receptacle having means for forcing the combustible through the burner.
  • Fig. 7 is a cross sectional View of the preferred embodiment of the invention showing a receptacle mounted on the nose of the shell and a burner.
  • Fig. 1 shows a shell provided in front with a receptacle mounted in the place of the usual pointed nose piece.
  • the explosive charge of the shell is contained in the member 2.
  • This double fu'se may comprise for example two firing pins, the
  • Fig. 2 represents a modified arrangement of mounting the receptacle 1, in which the receptacle is arranged outside of the shell casing and in such a manner that the outlet holes 11 cause an incandescent layer 9 to be formed in front of the point 12 at the pointed end of the shell in order that the heating of the air may be more perfect for the passage of the shell.
  • the device for igniting the combustible in the receptacle is situated in front at 4, while that which causes the explosion of the charge is behind at 5.
  • the receptacle 1 is housed in the chamber containing the explosive 3 to which it is screwed in a manner similar to that of an ordinary fuse. It has an outside extension comprising a tubulure 13 which carries the ignition device.4 and an ignition retarding appliance' 14 which may be constituted by a column of powder adapted to slowly light the combustible 7 at a certain distance from the gun.
  • the combustible 7 which can be a solid substance such a-s red phosphorus, is vaporized by means of a thermal core 15, such as aluminium powder with oxid of iron, which disengages from the vapor incandescent phosphorus.
  • the heat insulator 10 is placed lnside the receptacle 1.
  • the discharge exit for the incandescent layer 9 is constituted byan annular slot 16 communicating by means of ducts 18, which debouch into a chamber 17, with the duct 13.
  • the receptacle 1 contains a series of charges 7a, 7b, 7 c, 7d, each of a different nature, adapted to produce variations in the progress of the combustion.
  • the exit is represented as being made through an axial twyer 8, having a ring of holes 1l.
  • Fig. 5 an arrangement of the same kind, as in Fig. 4, is formed with two receptacles 1a and lb containing respectively the combustible charges 7a. and 7". Between these two charges, a pyrotechnic device 19 is arranged in such a manner that the ignition of 7b is only effected at a predetermined time after the end of the combustion of the charge 7a.
  • the incandescent layer 9 may be thus produced only at the beginning and end of the flight of the projectile and may be suppressed during the intermediate period of the passage of the projectile in regions of high altitude, where the air is of low density. Such arrangement gives rise to material economy in the use of combustible in long flight projectiles.
  • the heat insulator 10 is here shown outside the part 1*.
  • the liquid placed in 21 would be ejected through the orifices 8 and ll of the diffuser, under the actiom of a gas pressure produced in the primer 20.
  • the concussion at the firing of the gun sets up in primer 20, either the liberation of compressed or liquified gas or a chemical reaction between the substances yielding as residues high pressure gases.
  • the liquid jets passing through holes 11 are atomized into a sheet of drops by collision with the opposing solid walls.
  • a heavy stopper 22 is placed overv the duct feeding the several orifices. Its inertia at the firing of the gun, will automaticallyremove it and cause a passageway to be left.
  • liquid combustible employed is not pyrophoric
  • a petrol burner with heated walls may be provided for preliminarily heating it.
  • the orifices may be projected in such a way that the flames cannot be extinguished.
  • the stopper for the orifices for the liquid can be constituted by a highly combustiblebody or be self-destructive in any suitable manner at the firing of the gun.
  • Fig. 7 relates to an application of th'e invention to a tracer shell.
  • the shell represented is a tracing and incendiary one; it is filled with a combustible mixture of phosphorus and oXid of copper.
  • the concussion fuse 4 is placed in the upper part at the base of the tube 22 which is connected and terminates with the outlet orifices at an appropriate distance in front of the shell nose. This provision of empty tubes at the front part of the projectiles can also be applied to the other arrangements described. It is convenient, in each particular application, to determine the best form to adopt to produce the maximum efficiency.
  • the ejection of the combustible should occur generally at a4 distance from the shell appropriately determined for heating the air sufiiciently in front of the projectile.
  • the best distance varies according to the velocity of the projectile, its form, its caliber and also on the combustible employed.
  • a projectile having means for heating the air in advance thereof.
  • a projectile having means for heating the air in advance thereof, said heating means comprising a fuel resvoir and a burner in the front of the projectile.
  • a projectile having means for heating the air in advance thereof, said heating means comprising 'a fuel reservoir and a burner in the front of the projectile, said burner projecting from the front of the axis of the projectile.
  • a projectile having means for heating the air in advance thereof, said heating means comprising a fuel reservoir and a burner in the front of the projectile, said 6.
  • a projectile having means for heating the air in advance thereof, said projectile having a hollow interior.
  • a projectile having means for heating .the air in advance thereof, said projectile 8.
  • vA projectile having means for reducing the resistance to its flight by heating the air around the nose of the projectile, comprising a receptacle for combustible conneeted'to the for igniting the combustible and means for front of the projectile, means directing the burning gases of combustion around the nose of the projectile.
  • said igniting means comprising al pyrotechnic device having an orifice.
  • a projectile according to claim 8 said means for directing the gases comprising a chambered nose portion having a longitudinal bore.
  • a projectile according to claim 8 said means for directing the gases comprising a' tubular extension having communicating transverse bores near its outer end.

Landscapes

  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Air Bags (AREA)
  • Pharmaceuticals Containing Other Organic And Inorganic Compounds (AREA)
US259556A 1918-10-24 1918-10-24 Projectile Expired - Lifetime US1376316A (en)

Priority Applications (5)

Application Number Priority Date Filing Date Title
GB132068D GB132068A (fr) 1918-10-24
FR503934A FR503934A (fr) 1918-10-24 1917-11-28 Procédé et dispositifs pour diminuer la résistance de l'air à l'avancement des projectiles
US259556A US1376316A (en) 1918-10-24 1918-10-24 Projectile
FR21684A FR21684E (fr) 1918-10-24 1918-11-27 Procédé et dispositifs pour diminuer la résistance de l'air à l'avancement des projectiles
GB19131/20A GB147104A (en) 1918-10-24 1920-07-07 Improvements in or relating to projectiles

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US259556A US1376316A (en) 1918-10-24 1918-10-24 Projectile
FR21684T 1918-11-27

Publications (1)

Publication Number Publication Date
US1376316A true US1376316A (en) 1921-04-26

Family

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Family Applications (1)

Application Number Title Priority Date Filing Date
US259556A Expired - Lifetime US1376316A (en) 1918-10-24 1918-10-24 Projectile

Country Status (3)

Country Link
US (1) US1376316A (fr)
FR (2) FR503934A (fr)
GB (2) GB147104A (fr)

Cited By (26)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2504648A (en) * 1941-10-25 1950-04-18 Edward F Chandler Projectile
US2522114A (en) * 1947-02-01 1950-09-12 Daniel And Florence Guggenheim Means for cooling projected devices
US2624281A (en) * 1947-09-10 1953-01-06 James A Mcnally Projectile
US2737889A (en) * 1941-06-20 1956-03-13 Maurice E Barker Incendiary shell
US2802332A (en) * 1955-12-28 1957-08-13 Gen Electric High energy gas producer
US2995317A (en) * 1955-09-14 1961-08-08 Metallbau Semler G M B H External combustion stato-jet engine
US3001473A (en) * 1956-03-26 1961-09-26 William L Shepheard Rocket construction
US3008669A (en) * 1955-01-05 1961-11-14 Frank I Tanczos Ramjet missile
US3026806A (en) * 1957-03-22 1962-03-27 Russell Mfg Co Ballistic missile nose cone
US3063376A (en) * 1959-11-12 1962-11-13 Powell Edward Baden Slug for shotgun
US3067682A (en) * 1960-02-18 1962-12-11 Aerojet General Co Gyro pull rocket
US3067685A (en) * 1957-04-10 1962-12-11 Sfindex Supersonic barrel-fired projectiles carrying propulsion units
US3075301A (en) * 1961-07-13 1963-01-29 Willy A Fiedler Launch and underwater trajectory test vehicle
US3075302A (en) * 1961-08-17 1963-01-29 Willy A Fiedler Underwater pitch-over launch test vehicle
US3113750A (en) * 1958-11-28 1963-12-10 Nat Res Associates Inc Method of providing deceleration and lift for re-entry body
US3259065A (en) * 1959-04-30 1966-07-05 Massachusetts Inst Technology Shock wave inducing means for supersonic vehicles
US3425352A (en) * 1967-11-09 1969-02-04 Us Army Projectile fuze capable of self-destruction
US3601053A (en) * 1969-10-27 1971-08-24 Us Navy Signal projectile configured for improved penetrability of foliage
US3970003A (en) * 1974-10-16 1976-07-20 Avco Corporation Pyrophoric flare
US3994234A (en) * 1975-03-07 1976-11-30 The United States Of America As Represented By The Secretary Of The Army Projectile
US4353303A (en) * 1978-03-20 1982-10-12 Thiokol Corporation Projectile for dispensing gaseous material
US4436036A (en) 1979-09-28 1984-03-13 Thiokol Corporation Projectile for dispensing gaseous material
US5233128A (en) * 1992-07-31 1993-08-03 David Lai Barrel-cleaning bullet
US7743706B1 (en) * 2006-11-21 2010-06-29 David Lai Bullet cleaner for a gun barrel
US20180252502A1 (en) * 2015-10-20 2018-09-06 Daicel Corporation Smoke screen generator
WO2023272387A1 (fr) * 2021-06-29 2023-01-05 Next Dynamics Corp. Système de balle ayant de multiples capacités de réduction de traînée

Families Citing this family (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CH261411A (fr) * 1944-02-10 1949-05-15 Energa Projectile explosif perforant.
DE1022913B (de) * 1954-09-15 1958-01-16 Schoppe Fritz Einrichtung zur Erzeugung eines Vortriebes oder einer Bremsung an einem relativ zu einem Stroemungsmittel bewegten Koerper
US3345949A (en) * 1965-09-27 1967-10-10 Nosler Partition Bullet Compan Bullet
BE1006592A3 (fr) * 1992-08-11 1994-10-25 Rion Raymond Allumeur pyrotechnique pour moteur de reduction de trainee.

Cited By (27)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2737889A (en) * 1941-06-20 1956-03-13 Maurice E Barker Incendiary shell
US2504648A (en) * 1941-10-25 1950-04-18 Edward F Chandler Projectile
US2522114A (en) * 1947-02-01 1950-09-12 Daniel And Florence Guggenheim Means for cooling projected devices
US2624281A (en) * 1947-09-10 1953-01-06 James A Mcnally Projectile
US3008669A (en) * 1955-01-05 1961-11-14 Frank I Tanczos Ramjet missile
US2995317A (en) * 1955-09-14 1961-08-08 Metallbau Semler G M B H External combustion stato-jet engine
US2802332A (en) * 1955-12-28 1957-08-13 Gen Electric High energy gas producer
US3001473A (en) * 1956-03-26 1961-09-26 William L Shepheard Rocket construction
US3026806A (en) * 1957-03-22 1962-03-27 Russell Mfg Co Ballistic missile nose cone
US3067685A (en) * 1957-04-10 1962-12-11 Sfindex Supersonic barrel-fired projectiles carrying propulsion units
US3113750A (en) * 1958-11-28 1963-12-10 Nat Res Associates Inc Method of providing deceleration and lift for re-entry body
US3259065A (en) * 1959-04-30 1966-07-05 Massachusetts Inst Technology Shock wave inducing means for supersonic vehicles
US3063376A (en) * 1959-11-12 1962-11-13 Powell Edward Baden Slug for shotgun
US3067682A (en) * 1960-02-18 1962-12-11 Aerojet General Co Gyro pull rocket
US3075301A (en) * 1961-07-13 1963-01-29 Willy A Fiedler Launch and underwater trajectory test vehicle
US3075302A (en) * 1961-08-17 1963-01-29 Willy A Fiedler Underwater pitch-over launch test vehicle
US3425352A (en) * 1967-11-09 1969-02-04 Us Army Projectile fuze capable of self-destruction
US3601053A (en) * 1969-10-27 1971-08-24 Us Navy Signal projectile configured for improved penetrability of foliage
US3970003A (en) * 1974-10-16 1976-07-20 Avco Corporation Pyrophoric flare
US3994234A (en) * 1975-03-07 1976-11-30 The United States Of America As Represented By The Secretary Of The Army Projectile
US4353303A (en) * 1978-03-20 1982-10-12 Thiokol Corporation Projectile for dispensing gaseous material
US4436036A (en) 1979-09-28 1984-03-13 Thiokol Corporation Projectile for dispensing gaseous material
US5233128A (en) * 1992-07-31 1993-08-03 David Lai Barrel-cleaning bullet
US7743706B1 (en) * 2006-11-21 2010-06-29 David Lai Bullet cleaner for a gun barrel
US20180252502A1 (en) * 2015-10-20 2018-09-06 Daicel Corporation Smoke screen generator
US10443986B2 (en) * 2015-10-20 2019-10-15 Daicel Corporation Smoke screen generator
WO2023272387A1 (fr) * 2021-06-29 2023-01-05 Next Dynamics Corp. Système de balle ayant de multiples capacités de réduction de traînée

Also Published As

Publication number Publication date
FR503934A (fr) 1920-06-21
FR21684E (fr) 1921-01-11
GB147104A (en) 1921-06-09
GB132068A (fr)

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