US2206809A - Projectile - Google Patents

Projectile Download PDF

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Publication number
US2206809A
US2206809A US216406A US21640638A US2206809A US 2206809 A US2206809 A US 2206809A US 216406 A US216406 A US 216406A US 21640638 A US21640638 A US 21640638A US 2206809 A US2206809 A US 2206809A
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US
United States
Prior art keywords
projectile
casing
shell
charge
nozzles
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
US216406A
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English (en)
Inventor
Denoix Paul Emile Joseph
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.)
SAGEB SA
Original Assignee
SAGEB SA
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
Application filed by SAGEB SA filed Critical SAGEB SA
Application granted granted Critical
Publication of US2206809A publication Critical patent/US2206809A/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
    • F42B15/00—Self-propelled projectiles or missiles, e.g. rockets; Guided missiles

Definitions

  • Shells enclosing a reaction propulsion charge The forward portion of the complete projectile which discharges either into a central nozzle or may advantageously comprise a point having an 35 into lateral nozzles have already been proposed. inflected curve, of the type described in my cor- 5
  • the nozzles may be directed parallel to the ion-- responding U. S. patent application 192,411 filed gitudinal axis of the shell, in which case the reon February 24,1938. action eflect imparts thereto only an accelera-
  • the shell may be fired with the aid of a weak tion of translation; particularly when they are initial firing charge, imparting only a minimum disposed on the periphery of the projectile, said of reaction to the apparatus.
  • the latter can 10 nozzles may also be inclined relatively to the thus be mounted without inconvenience on an axial plane of the shell, with a view to having at v aircraft, which will be able to discharge bomb the same time the eifect of increasing or reducing projectiles, at great distances, at the objectives its velocity of gyration. that it desires to hit.
  • the projectiles of the present invention are Further features and advantages of the invencharacterised in that the lateral propulsive noztion" will become apparent from the following zles, with which they are provided, are disposed description taken in conjunction with the acnear or slightly in front of the centre of gravity companying drawing which illustrates diagram-' of the charged projectile.
  • Figure 1 is an axial section of one form of the ciable manner by a defect of symmetry in the invention.
  • thrusts applied by the nozzleadue for example, Figure 2 is an axial section of a modified form to an irregularity in their discharge or to imof the invention. 2 perfect centering.
  • Figure 2 is an axial section of a modified form to an irregularity in their discharge or to imof the invention. 2 perfect centering.
  • plete shell consists of an outer casing, in which the complete shell is constituted by a casing or is centred an internal shell I, cyllndro-ogival in body of optimum aerodynamic or streamline shape and disposed near the centre of gravity shape enclosing a projectile of any desired G of the complete charged shell.
  • the casing is shape, and, if desired, an ordinary projectile of streamline shape and has the greatest part 30 suitably immobilised and centred near the centre of its longitudinal exterior profile in the form of of gravity of the whole arrangement. a tip decreasing from the portion of maximum In one embodiment, the centering of the indiameter of the casing to the front end thereof.
  • the casing comprises a base 2 fixed on a nozzlewith the aid of the nozzle-carrier member, on carrier ring 3, which serves at the same time for 35 which the internal projectile is fastened by any centering the shell I.
  • the lateral nozzles l, 5 are suitable means.
  • this arrangement promotes the destrucof gravity G.
  • the forward portion 6 of the castion of the nozzle-carrier member and ensures its ing has preferably an inflected curve, in order embacious utilisation on impact, when explosion to facilitate the penetration of the air, as deoccurs. scribed in the aforesaid specification No. 192,- 40
  • the front and rear portions of the casing The compartments 1 and 8 bounded by the hold reactive charges which discharge into the casing in front of and behind the shell i hold nozzles placed level with or in front of the centre a reaction charge.
  • the rear charge discharges 45 of gravity. 7 into the nozzles 5 and the front charge into the This concentration of the mass of the entire nozzles t. projectile on its periphery and near the centre
  • the ofl'ensive charge 9 enclosed in the shell i of gravity enables excellent stability to be 010- is insulated from its walls by means of a layer tained and retained during the trajectory, despite Ill of suitable heat-insulating material.
  • the shell may, furthermore, contain a base at the two ends of the projectile and has the effuze M.
  • C 55 The rear reaction charge is brought into operation with the aid of Y an ignition fuze l5 or any other suitable device. A similar fuze, preferably placed at Ila ignites the reaction charge in the compartment 1.
  • fuzes are regulated so as to bring the reaction charges operation at the desired moment, during the trajectory or on departure of the shot.
  • ll denotes a driving banddisposed on the base of the casing 2, and I8 a discardable centering band mounted on the nozzle-carrier ring 3.
  • the projectile ends at the front in a tapered point IS, the outer surface of which prolongs the inflected curve of the portion 6 of the casing.
  • Fig. 2 shows a modification of the projectile shown in Fig. 1, from which it differs in that the internal shell I, instead of itself having a screwthread coming into engagement with a thread on the nozzle-carrier member 3, is in contact with the latter only through shoulders 51 engaging assembly screws 58.
  • the external side walls of the shell I stand a slight distance away from the internal walls of the member 3, in order to permit the gases free access to the nozzles l, 5 placed near the centre of gravity G.
  • a projectile comprising an outer casing of streamline/shape, a nozzle carrying member disposed on the casing in the vicinity of the center of gravity of the' projectile and being provided with nozzles, an inner casing separate from said outer casing and centered in said nozzle carrying member and completely enclosed within said outer casing and spaced therefrom, said inner. casin'g having an oifensive charge therein and forming an internal shell, and a propulsive rocket charge in the space provided between said outer casing and said inner casing and in discharge communication with said nozzles.
  • a projectile comprising a casing having the greatest part of .its longitudinal exterior profile in the form of a tip decreasing from the portion of maximum diameter of the casing to the front end thereof, a nozzle carrying member disposed on the casing in the vicinity'of the center of gravity of the projectile, said nozzle carrying memher being provided with nozzles, a shell centered in said nozzle carrying member and completely enclosed within said casing, a bursting charge in said shell, and a propulsive rocket charge in said casing and in discharge communication with said nozzles.
  • a projectile comprising a casing having the greatest part of its longitudinal exterior profile in the'form of a tip decreasing from the portion of maximum diameter of the casing to the front end thereof, a nozzle carrying member fixed in said casing in the vicinity of the center of gravity of the projectile, said nozzle carrying member being formed with a front and rear series of nozzles, a shell centered in said nozzle carrying member and completely enclosed within said casing, a bursting charge in said shell, a front rocket charge in said casing in front of said shell, 2. rear rocket charge in said casing in rear of said shell, said front and rear rocket charges being in discharge communication with said front and rear series of nozzles respectively.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Combustion & Propulsion (AREA)
  • General Engineering & Computer Science (AREA)
  • Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
US216406A 1937-06-28 1938-06-28 Projectile Expired - Lifetime US2206809A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
LU2206809X 1937-06-28

Publications (1)

Publication Number Publication Date
US2206809A true US2206809A (en) 1940-07-02

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Family Applications (1)

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US216406A Expired - Lifetime US2206809A (en) 1937-06-28 1938-06-28 Projectile

Country Status (2)

Country Link
US (1) US2206809A (enrdf_load_stackoverflow)
NL (1) NL56750C (enrdf_load_stackoverflow)

Cited By (15)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2421552A (en) * 1943-12-27 1947-06-03 Usa Casing and nozzle construction for rocket motors
US2504648A (en) * 1941-10-25 1950-04-18 Edward F Chandler Projectile
US2633702A (en) * 1946-02-28 1953-04-07 Clarence N Hickman Multiple nozzle rocket
US2683415A (en) * 1945-08-13 1954-07-13 Untied States Of America As Re Rocket motor
US2690314A (en) * 1949-12-15 1954-09-28 Us Navy Long-range guided athodyd
US2773448A (en) * 1954-01-21 1956-12-11 Brandt Soc Nouv Ets Rocket projectile
US2816721A (en) * 1953-09-15 1957-12-17 Taylor Richard John Rocket powered aerial vehicle
US2941469A (en) * 1955-11-15 1960-06-21 George E Barnhart Projectile construction
US2972859A (en) * 1958-11-25 1961-02-28 Ici Ltd Rocket motors
US3044255A (en) * 1954-05-14 1962-07-17 Soc Tech De Rech Ind Powder propulsive for rockets or other self-propelled projectiles
US3088273A (en) * 1960-01-18 1963-05-07 United Aircraft Corp Solid propellant rocket
DE1168803B (de) * 1961-03-06 1964-04-23 Baronin Ilyana Von Thyssen Bor Rotationsstabilisierte Granate mit zusaetzlichem Raketenantrieb
US3326128A (en) * 1964-09-09 1967-06-20 Norris Industries Rockets and combinations of rockets and cases
US3439613A (en) * 1964-11-26 1969-04-22 Bolkow Gmbh Self-propelled hollow charge having concave liner with propellant contained therein
US4643098A (en) * 1983-10-20 1987-02-17 A/S Raufoss Ammunisjonsfabrikker Rocket with tracer charge and gunpowder rods

Cited By (15)

* 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
US2421552A (en) * 1943-12-27 1947-06-03 Usa Casing and nozzle construction for rocket motors
US2683415A (en) * 1945-08-13 1954-07-13 Untied States Of America As Re Rocket motor
US2633702A (en) * 1946-02-28 1953-04-07 Clarence N Hickman Multiple nozzle rocket
US2690314A (en) * 1949-12-15 1954-09-28 Us Navy Long-range guided athodyd
US2816721A (en) * 1953-09-15 1957-12-17 Taylor Richard John Rocket powered aerial vehicle
US2773448A (en) * 1954-01-21 1956-12-11 Brandt Soc Nouv Ets Rocket projectile
US3044255A (en) * 1954-05-14 1962-07-17 Soc Tech De Rech Ind Powder propulsive for rockets or other self-propelled projectiles
US2941469A (en) * 1955-11-15 1960-06-21 George E Barnhart Projectile construction
US2972859A (en) * 1958-11-25 1961-02-28 Ici Ltd Rocket motors
US3088273A (en) * 1960-01-18 1963-05-07 United Aircraft Corp Solid propellant rocket
DE1168803B (de) * 1961-03-06 1964-04-23 Baronin Ilyana Von Thyssen Bor Rotationsstabilisierte Granate mit zusaetzlichem Raketenantrieb
US3326128A (en) * 1964-09-09 1967-06-20 Norris Industries Rockets and combinations of rockets and cases
US3439613A (en) * 1964-11-26 1969-04-22 Bolkow Gmbh Self-propelled hollow charge having concave liner with propellant contained therein
US4643098A (en) * 1983-10-20 1987-02-17 A/S Raufoss Ammunisjonsfabrikker Rocket with tracer charge and gunpowder rods

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Publication number Publication date
NL56750C (enrdf_load_stackoverflow)

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