US2426239A - Rocket shell - Google Patents

Rocket shell Download PDF

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Publication number
US2426239A
US2426239A US470378A US47037842A US2426239A US 2426239 A US2426239 A US 2426239A US 470378 A US470378 A US 470378A US 47037842 A US47037842 A US 47037842A US 2426239 A US2426239 A US 2426239A
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United States
Prior art keywords
projectile
segment
charge
rocket
tail
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Expired - Lifetime
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US470378A
Inventor
Henry M Renner
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Henry M Renner
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Priority to US470378A priority Critical patent/US2426239A/en
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Expired - Lifetime legal-status Critical Current

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    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42AMMUNITION; BLASTING
    • F42BEXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
    • F42B5/00Cartridge ammunition, e.g. separately-loaded propellant charges
    • F42B5/02Cartridges, i.e. cases with charge and missile
    • F42B5/10Cartridges, i.e. cases with charge and missile with self-propelled bullet
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42AMMUNITION; BLASTING
    • F42BEXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
    • F42B10/00Means 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
    • F42B10/02Stabilising arrangements
    • F42B10/26Stabilising arrangements using spin
    • F42B10/28Stabilising arrangements using spin induced by gas action
    • F42B10/30Stabilising arrangements using spin induced by gas action using rocket motor nozzles

Description

Aug. 26, 1947. H. M. RENNER ROCKET SHELL Filed Dec. 28
2! Henry M.Renner Patented Aug. 26, 1947 ROCKET SHELL Henry M. Remier, Cedar-town, Ga.
Application December 28, 1942, Serial No. 470,378
(Granted under the act of March 3, 1883, as amended April 30, 1928; 370 0. G. 757) 12 Claims.
The invention described herein may be manufactured and used by or for the Government for governmental purposes, without the payment to me of any royalty thereon.
This invention relates to a shell and more particularly to a shell which is provided with rocket means to augment the action of the propellant charge in the gun.
It is an object of this invention to decrease the recoil force upon a gun and increase the efliciency with which the shell may be propelled along the trajectory.
The exact nature of the invention as well as other objects and advantage thereof will be apparent from the description of a preferred embodiment as shown in the accompanying drawing in which:
Fig. 1 is a longitudinal sectional view of a complete round including my invention.
Fig. 2 is a similar view of the projectile in the position it will occupy during flight conditions.
Fig. 3 is a rear end elevational view corresponding to Fig. 2.
Referring to the drawing by characters of reference there is shown in Fig. 1 a complete round of ammunition comprising a projectile body 1, preferably hollow for the reception of a suitable explosive charge, a cartridge case 2 and a disk 3 to receive and communicate the force of the explosion of the propellant B to the projectile I. The base of the projectile I is reduced in diameter and provided with external threads as at 5 while a cup like cavity 6 extends forward into the body of the projectile a. suflicient distance to house the aumliary propellant charge 1 of type suitable for propelling a rocket. A barrel segment 8 is provided with internal threads adapted to engage the threaded rear end of the projectile and provide a hollow extension thereof. The barrel segment 8 is provided with a cylindrical bore 9 the rear end of which is partially obstructed'by the flange in formed by reducing the diameter of the bore. Slidable in the bore 9 is a tube segment I l which is provided with a flange I2 engageable with th flange It to limit the rearward movement of the tube segment. Parallel with the axis of the tube segment and uniformly spaced about the circumference thereof are a plurality of tube receiving bores 13 which communicate with the interior of the barrel and are provided with rocket tubes 14. The tube segment II is provided with an internal bore l5 having a flange portion it of reduced diameter and slidable therein is the tail segment H which has a flanged portion l8 engageable with the flange It to limit rearward movement of the tail segment with relation to the tube segment. The tail segment is preferably tapered rearwardly and is provided at It with internal threads which receive the fuse tube 20. The fuse tube 20 extends forwardly through the 2 tall segment to communicate with the cavity 6. The fuse tube is provided with a rearward extension 2| to which a plurality of curved vanes 22 are secured by welding or other convenient means. Preferably the vanes are provided at their front ends with nlbs 23 which are designed to engage the tapered rear end of the barrel segment and assist in centering the vane assembly during the action of the propellant in the gun. Optionally a cylindrical tail member as may be secured to the outside of the curved vanes 22 by welding or other convenient means, and may conveniently be carried forward into engagement with an external flange 25 on the barrel segment 8.
A delay train 28 or other suitable time fuse means is provided in the fuse tube 20 to carry ignition from the propellant 4 to the front end of the tail segment. A priming charge 21 is preferably contained in the forward end of the tail segment and may be separated from the auxiliary propellant I by means of a powder gasket 28 or similar convenient means.
The operation of the device may be summarized as follows: Upon flring 0f the main propellant e the projectile assembly will be impelled through the barrel, the disk providing a, gas tight seal with the fuse tube by reason of the tapered joint therewith and by reason of the skirt providing a tight seal with the walls of the bore. At the same time the delay train 26 in the fuse tube will be ignited and, by the time the projectile assembly has cleared the gun muzzle a sufficient distance to insure safety to the un crew and avoid disclosing the gun position, will ignite the priming charge 21 which will in turn fire the auxiliary propellant l. The auxiliary charge I will extend the tube and tail segments, and the blast of gas escaping through the fuse tube 20 and the rocket tubes It will, by reaction, exert an additional propelling influence on the projectile assembly. The deflection of the blast from the rocket tubes by the curved surface of the vanes will tend to stabilize the assembly by maintaining it in rotation about the axis to some extent, although the bulk of the stabilizing influence will come from the flow of air through the vanes. It will be obvious that the sabot will probably be separated from its tapered engagement with the fuse tube by the force of air resistance and will be definitely separated by the initial blast from the rocket tubes. v
It is obvious that a projectile of this nature may be fired from either a rifle or smooth bore weapon although it is probable that higher accuracy may be obtained by initially rotating the assembly, as in firing from a rifled bore.
I claim:
1. A round of ammunition comprising a primary propellent charge, a projectile including a 3 rocket pro'pellent charge and racket tubes communicating with, said propellant charge, a fuse tube leading through said projectile to said rocket charge. a disk bearing on the rear end of said projectile to transmit the thrust from the primary propellent charge to the projectile, an aperture in said disk in substantially gas tight engagement with the exterior of said fuse tube, and a delay fuse passing through said fuse tube to transmit ignition from the primary propellant to the rocket propellant.
2. A projectile comprising a, hollow body having a boat-tailed rear end, a telescoping tail structure capable of being received in said hollow body, vanes on said tail structure bearing on the rear end of said body when the tail is telescoped, and forwardly extending nibs on said vanes bearing on the boat-tail portion of the body whereby the telescoped tail structure is positively centered in relation to the body.
3. A projectile comprising a hollow body portion, a tubular extension on the rear end of said hollow body having a tapered rear end, telescoping tail segments receivable in said tubular extension and capable of limited rearward extension therefrom, tail vanes on the rearmost tail segment engageable with the tapered rear end of v the extension when the tail segments are telescoped, a rearwardly facing flange on said tubular extension, and a cylindrical stabilizer secured to said tail vanes and bearing against the flange when the tail vanes engage the rear of the tubular extension.
4. A projectile as described in claim 3, a rocket charge in said hollow body portion, rocket orifices .in at least one of said tail segments, and fuse means to ignite said rocket charge.
5. A projectile as described in claim 3, said tail vanes being curved to maintain the assembly in rotation during flight.
6. A projectile as described in claim 3, forwardly extendingnibs on said tail vanes capable of engaging" the exterior of said tapered rear end portion. 7
7. A projectile as described in claim 3, a rocket charge in said hollow body, delay fuse means passing through the rearmost tail segment into communication with said charge. and rocket orifices in said segments for propulsion of said projectile.
8. A projectile comprising a hollow body having an auxiliary propellent charge in its forward portion, inner and outer telescoped tail segments normally within the body with their inner ends adjacent said charge, rocket tubes in the outer tail segment in communication with said auxiliary propellant charge, a delay fuse carried by the inner segment for igniting the auxilary charge, the telescoped segments being adapted to be extended with relation to each other and to the hollow body, means for limiting the rearward extension of the outer tail segment with relation to said body and means limiting the rearward movement of the inner segment with relation to the outer segment, and means fo igniting the delay fuse at the beginning of the projectile flight.
9. A projectile comprising a hollow body having an auxiliary propellent charge in its forward portion. inner and outer telescoped tail segments normally within the projectile body with inner front ends adjacent said charge, a delay fuse car-' 4 ried by the inner segment for igniting the charge. the telescoped segments being adapted to be extended with relation to each other and to the .projectile body, means for limiting the rearward extension of the outer segment with relation to the projectile body, and means for limiting the extension of the inner segment with relation to the outer segment, open end rocket tubes arranged around the periphery of the outer segment communicating with the gas chamber formed in the projectile body upon the extension of the outer tail segment, and means for igniting the delay fuse at the beginning of the projectile flight.
10. A round of ammunition comprising a primary propellant charge..a projectile comprising a hollow body portion defining a chamber, a rocket charge in said chamber, a rearward extension on said body, inner and outer tail segments normally telescoped within said extension, rocket orifices in at least one of said tail segments, and stabilizing vanes on the inner tail segment and normally spacing said rearward extension from the primary propellant charge.
11. A round of ammunition comprising a primary propellant charge, a projectile comprising a hollow body defining a chamber, a rocket charge in said chamber, a rearward extension on said body, inner and outer tail segments normally telescoped within said extension, rocket orifices in the outer segment, a fuse tube in the inner segment and communicating at its forward end with the rocket charge and its rear end with the propellant charge, a fuse in said tube for igniting the rocket charge, said fuse tube serving to augment said rocket orifices after the ignition of said rocket charge.
' i 12. The invention of claim 11 characterized in that the fuse tube is extended beyond the rear end of the innertail segment and stabilizing circularly spaced curved vanes are secured to said tube extension and normally space said rearward extension from said propellant charge, said vanes being positioned to receive the blasts from the said rocket orifices whereby said vanes are moved from normal to a position remote from the extension of the projectile'body during the flight of the projectile.
v HENRY M. RENNER. REFERENCES CITED The following references are of record in the file of this patent:
UNITED STATES PATENTS
US470378A 1942-12-28 1942-12-28 Rocket shell Expired - Lifetime US2426239A (en)

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Cited By (30)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2630066A (en) * 1945-02-08 1953-03-03 Speers G Ponder Incendiary bomb
US2644364A (en) * 1950-05-24 1953-07-07 Us Army Cartridge case containing propelling rocket igniting charge and rocket projectile
US2671398A (en) * 1951-05-11 1954-03-09 Allen S Peck Metal pop-out stabilizing tail for small bombs
US2694364A (en) * 1949-01-18 1954-11-16 Lyle K Liljegren Streamlined mortar shell
US2876678A (en) * 1952-04-05 1959-03-10 Lyon George Albert Rocket gun
US2879955A (en) * 1951-08-02 1959-03-31 Zborowski Helmut P G A R Von Airborne bodies and in particular self propelled missiles
DE1168293B (en) * 1960-10-25 1964-04-16 Energa Shaped charge projectile with tail unit, guide ring and cartridge case
US3151412A (en) * 1962-01-02 1964-10-06 Jack Spencer Firearm barrel with grooves and projectile with fins fitting in said grooves
US3267854A (en) * 1963-12-17 1966-08-23 Gunnar P Michelson Missile
US3283721A (en) * 1964-11-09 1966-11-08 Kruzell George Ralph Reaction type missile
US3292879A (en) * 1965-06-25 1966-12-20 Canrad Prec Ind Inc Projectile with stabilizing surfaces
US3323457A (en) * 1965-04-02 1967-06-06 Arthur T Biehl Underwater weapon
US3390850A (en) * 1967-08-04 1968-07-02 Army Usa Fin for inducing spin in rotating rockets
US3494284A (en) * 1968-03-19 1970-02-10 Bernard A Gross Projectile with expandable body
US3507220A (en) * 1969-01-02 1970-04-21 Clifton M Mcclure Ammunition round
US3720169A (en) * 1971-03-30 1973-03-13 Us Army Incendiary projectile for smooth bore special purpose individual weapon
US3724377A (en) * 1969-05-07 1973-04-03 Brevets Aero Mecaniques Shell cartridges
US3853288A (en) * 1967-07-17 1974-12-10 H Bode Encasement for the tail section of a rocket with a central nozzle and extendible control vanes
US3886841A (en) * 1973-05-29 1975-06-03 Matthew S Smith Rocket powered round
US3915091A (en) * 1973-05-29 1975-10-28 Matthew S Smith Rocket powered round
US4104969A (en) * 1976-02-13 1978-08-08 Rheinmetall Gmbh Arrangement for improving the burning efficiency of a rocket-borne solid propellant charge cartridge
US4497460A (en) * 1983-03-25 1985-02-05 The United States Of America As Represented By The Secretary Of The Navy Erodale spin turbine for tube-launched missiles
US4944226A (en) * 1988-08-19 1990-07-31 General Dynamics Corp., Pomona Div. Expandable telescoped missile airframe
US5450795A (en) * 1993-08-19 1995-09-19 Adelman Associates Projectile for small firearms
US20040069173A1 (en) * 2002-10-15 2004-04-15 Mark Key Projectile for rapid fire gun
US20040094661A1 (en) * 2000-07-03 2004-05-20 Stig Johnsson Method and arrangement for artillery missiles
US20110162247A1 (en) * 2009-12-22 2011-07-07 Diehl Bgt Defence Gmbh & Co. Kg Grenade and grenade launching apparatus
EP2735838A1 (en) * 2012-11-23 2014-05-28 Tda Armements S.A.S. Artillery ammunition with sliding structure
US10677574B2 (en) 2016-05-03 2020-06-09 Dimosthenis Panousakis Self contained internal chamber for a projectile
WO2020141290A1 (en) * 2019-01-04 2020-07-09 The Secretary Of State For Defence Captive piston projectile and method of manufacture

Citations (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US46490A (en) * 1865-02-21 Improvement in projectiles
US229499A (en) * 1880-06-29 Explosive shell
US263407A (en) * 1882-08-29 Submarine torpedo
GB191210325A (en) * 1912-05-01 1912-12-05 Boris Svistounoff Improvements in or relating to Projectiles.
US1257126A (en) * 1917-12-24 1918-02-19 Eugene Schneider Explosive projectile.
GB191512036A (en) * 1915-08-20 1919-03-13 Eugene Schneider An Improved Explosive Projectile.
US1347125A (en) * 1919-02-28 1920-07-20 Schneider & Cie Projectile for bomb-throwers
US1817377A (en) * 1928-08-15 1931-08-04 James Roy Walter Projectile
FR711464A (en) * 1930-05-22 1931-09-10 Refinements to fletched projectiles
US1994490A (en) * 1934-09-11 1935-03-19 Leslie A Skinner Rocket projectile
FR820266A (en) * 1936-04-10 1937-11-08 Bomb and Projectile Improvements

Patent Citations (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US46490A (en) * 1865-02-21 Improvement in projectiles
US229499A (en) * 1880-06-29 Explosive shell
US263407A (en) * 1882-08-29 Submarine torpedo
GB191210325A (en) * 1912-05-01 1912-12-05 Boris Svistounoff Improvements in or relating to Projectiles.
GB191512036A (en) * 1915-08-20 1919-03-13 Eugene Schneider An Improved Explosive Projectile.
US1257126A (en) * 1917-12-24 1918-02-19 Eugene Schneider Explosive projectile.
US1347125A (en) * 1919-02-28 1920-07-20 Schneider & Cie Projectile for bomb-throwers
US1817377A (en) * 1928-08-15 1931-08-04 James Roy Walter Projectile
FR711464A (en) * 1930-05-22 1931-09-10 Refinements to fletched projectiles
US1879840A (en) * 1930-05-22 1932-09-27 Brandt Edgar William Bladed projectile
US1994490A (en) * 1934-09-11 1935-03-19 Leslie A Skinner Rocket projectile
FR820266A (en) * 1936-04-10 1937-11-08 Bomb and Projectile Improvements

Cited By (40)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2630066A (en) * 1945-02-08 1953-03-03 Speers G Ponder Incendiary bomb
US2694364A (en) * 1949-01-18 1954-11-16 Lyle K Liljegren Streamlined mortar shell
US2644364A (en) * 1950-05-24 1953-07-07 Us Army Cartridge case containing propelling rocket igniting charge and rocket projectile
US2671398A (en) * 1951-05-11 1954-03-09 Allen S Peck Metal pop-out stabilizing tail for small bombs
US2879955A (en) * 1951-08-02 1959-03-31 Zborowski Helmut P G A R Von Airborne bodies and in particular self propelled missiles
US2876678A (en) * 1952-04-05 1959-03-10 Lyon George Albert Rocket gun
DE1168293B (en) * 1960-10-25 1964-04-16 Energa Shaped charge projectile with tail unit, guide ring and cartridge case
US3151412A (en) * 1962-01-02 1964-10-06 Jack Spencer Firearm barrel with grooves and projectile with fins fitting in said grooves
US3267854A (en) * 1963-12-17 1966-08-23 Gunnar P Michelson Missile
US3283721A (en) * 1964-11-09 1966-11-08 Kruzell George Ralph Reaction type missile
US3323457A (en) * 1965-04-02 1967-06-06 Arthur T Biehl Underwater weapon
US3292879A (en) * 1965-06-25 1966-12-20 Canrad Prec Ind Inc Projectile with stabilizing surfaces
US3853288A (en) * 1967-07-17 1974-12-10 H Bode Encasement for the tail section of a rocket with a central nozzle and extendible control vanes
US3390850A (en) * 1967-08-04 1968-07-02 Army Usa Fin for inducing spin in rotating rockets
US3494284A (en) * 1968-03-19 1970-02-10 Bernard A Gross Projectile with expandable body
US3507220A (en) * 1969-01-02 1970-04-21 Clifton M Mcclure Ammunition round
US3724377A (en) * 1969-05-07 1973-04-03 Brevets Aero Mecaniques Shell cartridges
US3720169A (en) * 1971-03-30 1973-03-13 Us Army Incendiary projectile for smooth bore special purpose individual weapon
US3886841A (en) * 1973-05-29 1975-06-03 Matthew S Smith Rocket powered round
US3915091A (en) * 1973-05-29 1975-10-28 Matthew S Smith Rocket powered round
US4104969A (en) * 1976-02-13 1978-08-08 Rheinmetall Gmbh Arrangement for improving the burning efficiency of a rocket-borne solid propellant charge cartridge
US4497460A (en) * 1983-03-25 1985-02-05 The United States Of America As Represented By The Secretary Of The Navy Erodale spin turbine for tube-launched missiles
US4944226A (en) * 1988-08-19 1990-07-31 General Dynamics Corp., Pomona Div. Expandable telescoped missile airframe
US5450795A (en) * 1993-08-19 1995-09-19 Adelman Associates Projectile for small firearms
US20040094661A1 (en) * 2000-07-03 2004-05-20 Stig Johnsson Method and arrangement for artillery missiles
US7226016B2 (en) 2000-07-03 2007-06-05 Bae Systems Bofors Ab Method and arrangement for low or non-rotating artillery shells
US20070084961A1 (en) * 2000-07-03 2007-04-19 Bofors Defence Ab Method and arrangement for low or non-rotating artillery shells
AU2003273289B2 (en) * 2002-10-15 2009-01-22 Mark Key Projectile for rapid fire gun
US6862996B2 (en) * 2002-10-15 2005-03-08 Mark Key Projectile for rapid fire gun
US20060011088A1 (en) * 2002-10-15 2006-01-19 Key Mark B Projectile for rapid fire gun
WO2004036139A2 (en) * 2002-10-15 2004-04-29 Mark Key Projectile for rapid fire gun
US20040069173A1 (en) * 2002-10-15 2004-04-15 Mark Key Projectile for rapid fire gun
US7395762B2 (en) 2002-10-15 2008-07-08 Key Mark B Projectile for rapid fire gun
WO2004036139A3 (en) * 2002-10-15 2004-06-03 Mark Key Projectile for rapid fire gun
US20110162247A1 (en) * 2009-12-22 2011-07-07 Diehl Bgt Defence Gmbh & Co. Kg Grenade and grenade launching apparatus
US9488422B2 (en) * 2009-12-22 2016-11-08 Diehl Bgt Defence Gmbh & Co. Kg Grenade and grenade launching apparatus
EP2735838A1 (en) * 2012-11-23 2014-05-28 Tda Armements S.A.S. Artillery ammunition with sliding structure
FR2998660A1 (en) * 2012-11-23 2014-05-30 Tda Armements Sas MUNITION OF ARTILLERY WITH SLIDING STRUCTURE
US10677574B2 (en) 2016-05-03 2020-06-09 Dimosthenis Panousakis Self contained internal chamber for a projectile
WO2020141290A1 (en) * 2019-01-04 2020-07-09 The Secretary Of State For Defence Captive piston projectile and method of manufacture

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