US2624281A - Projectile - Google Patents

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US2624281A
US2624281A US773283A US77328347A US2624281A US 2624281 A US2624281 A US 2624281A US 773283 A US773283 A US 773283A US 77328347 A US77328347 A US 77328347A US 2624281 A US2624281 A US 2624281A
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projectile
casing
velocity
conduit
fuel
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US773283A
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James A Mcnally
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James A Mcnally
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    • 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
    • F42B10/32Range-reducing or range-increasing arrangements; Fall-retarding means
    • F42B10/38Range-increasing arrangements
    • F42B10/40Range-increasing arrangements with combustion of a slow-burning charge, e.g. fumers, base-bleed projectiles
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02KJET-PROPULSION PLANTS
    • F02K7/00Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof
    • F02K7/08Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof the jet being continuous

Description

Jan. 6, 1953 J. A. M NALLY 2,624,281
PROJECTILE Filed Sept. 10, 1947 2 SHEETSSHEET l gvwc/wlm JAMES A. MC NALLY Jan. 6, 1953 J. A. M NALLY 2,624,281
PROJECTILE Filed Sept. 10, 1947 2 $HEETSSHEET 2 JAMES A. MC NALLY Patented Jan. 6, 1953 UNIT-ED sures PATENT OFFICE amaze-1 PRQJECTILE Ela'mes AfMcNaElly, United States Navy Application September 1o, 1947,:SerialNo.773,283 :2 (Cl. 102-49) Granted'under rifle 35.13. IS. code @1952, see. 266) This invention relates to projectiles and more particularly to proieetiles including novel means for increasing the range and accuracy thereof,
Heretofore, projectiles or missiles, such as rifle shells, bombs, rockets and projectiles carrying scientific instruments for determining physical conditions at remote locations, have been accelerated from zero velocity and projected to the desired target or location through application of externally applied forces thereto, -or upon operation of a self-contained power unit', such as a rocket mechanism. *-In all instances the projectile is accelerated to a maximum velocity-determined "by the characteristics of the propulsion means, and therefore, the range, accuracy and penetration force of such projectiles are limitedt'hereby.
It is therefore an object ofthe present invention to provide novel means for increasing range and accuracy of projectiles, missiles and the like.
Another object is to provide 'aprojecti-le enema ing novel propulsion means operaiile when (a predetermined velocity is imparted to the projectile for further "accelerating 'the projectile to extremely high velocities whereby an increase in rangeand accuracy thereof is obtained.
Another object is to provide in a projectile adapted to be accelerated to an initial velocity upon application of an externally applied force thereto, novel means operahlewhen the projectile attains said initial velocity to "further ac'c'eberate the projectile.
Another object is to provide in a projectile or the type adapted to lee-accelerated to an initial velocity upon application of an externally'applied force thereto, a hot motive fluid reaction means operable when the projectile "attains a predetermined velocity for further accelerating the projeotile to'apreviously unattainabiehi'gh velocity.
Still another object of the present invention is; to; provide a projectile "having self-contained motive means for accelerating the projectile from zero'velocity to 'a predetermined velocity and hot motive fluid reaction means ioriurtheraccelerating'the projectile after the self-contained motive means is dissipated.
Still another object is to provide novel means for improvingthe areodynamic characteristics or projectiles.
Other objects and features of thepresen't invention will appear more fully hereinafter upon consideration of the following detailed description in connection with the accompanying drawings which disclose several embodiments of the invention. It is to be expresslyunderstoodhowever, that the drawings are designed for purposes -2' of illustration only :and are not to 'be-con'strued' as a definition of the limits of the invention, reference for the latter purpose being had to the appended claims.
In the drawings, wherein similar reference haracters denote similar parts throughout the several views:
Fig. 1 is a diagrammaticshowing in section, oira projectile embodying the principles of "therpresent invention;
Fig. 2 is a profile View of the rear end of the proj ectileshown in Fig. '1;
Fig. 3 isa-pro'file view of the forward end of. the projectiledisclosed in Fig. 1-;
Fig. 4'is a diagrammatic illustration, insection, of :a projectile constructed .in accordance with another embodiment 'of'the presentinvention, and
5 is an illustration of a feature .of the-embodiment disclosed in Fig. 4.
*With reference "more particularly to Fig. 1 of the drawings, "a projectile of the type adapted'to be accelerated to an initial velocity upon application of an external 'forcetheret'o, is disclosed therein constructed in accordance with the principles of the present invention. The projectile includes a cylindrical casing "[10 of streamlined form for motion'to the-left as viewed in thecdrawing. The diameter-of the casing 1-0 is constant at'therear portion thereof'while the forwardpoh tion possesses a. gradually decreasing diameter extending toward the forward end and terminating inn cylindrical opening I I. The rear end 'of the casing do is terminated by a wall l2 having an opening F3 therein for the purpose that will.
input of a high pressure or combustion ichamber' i=5, A high velocity discharge nozzle 16 is provid'ed between the output of the chamber 15 and the opening 1-3. The nozzle 4 6 extends, with.
gradually hicreasing diameter, from the output of the chamber 1 5, in symmetrical relation with the'longitudi nal' axisof the easing nan, tothe-openin'g" annular fuel reservoir 1 of. icyline dri'cal' oross section, is positioned. within the easing' to, in symmetrical relation with respect to the longitudinal axis thereof, and in :close prox imity with the chamber '15. Fuel conduit 18 is connected fluid communication with the reservoir-"l l' at'a point on'the peripherythereof. The conduit 1-8 is connected through electrically operated valve I9 to annular fuel manifold 20 associated with the combustion chamber I5. A plurality of fuel injection nozzles 2| are radially positioned in the wall of the chamber I to form communications between the manifold and the combustion chamber I5. The valve I9 is normally biased in a closed pOsition and means are provided to move the valve I9 to an open position to form a fuel communication between the reservoir I1 and the chamber I5 when a predetermined pressure exists within the conduit I4. Such means includes a pressure responsive contr l device 22 mounted in the conduit I4. The device 22 functions in response-to a predetermined pressure within the conduit I4 to apply, through conductor 22 a signal to energize the valve I9 in manner described heretofore. A suitable igniter means 23, which may take the form of a spark plug or a chemically treated metallic wire for producing a glow discharge when fluid at high velocity passes thereover, is provided in the combustion chamber I5 to ignite the combustive mixture therein.
When the projectile is accelerated to an initial velocity due to the application of an external force thereto, such as for example, the forces applied upon firing the projectile from a rifle, or the force of gravity when the projectile is utilized as an aerial bomb, air at high velocities is injected or rammed into the opening II, and, due to the gradually decreasing diameter of the conduit I4, the air is injected into the combustion chamber I5 at extremely high pressures. Due to the centrifugal forces created by the rotating projectile, fuel within the reservoir I1 is forced against the outer peripheral wall thereof to apply fuel to the conduit I8. The reservoir I! may be pressurized in conventional manner to force the fuel through conduit I8 against valve I9. When the pressure within the conduit I4 attains a predetermined value to operate the device 22, the valve I9 is moved to open position thereby supplying fuel under pressure to the manifold and into the combustion chamber I5 through injection nozzles 2I. The injected fuel is mixed with the compressed air to form a highly combustive mixture within the chamber I5 which is exploded by the igniting means 23, automatically or in response to operation of the device 22. When combustion occurs a source of hot motive fluid is generated in the chamber I5. The hot motive fluid is exhausted at high velocities through discharge nozzle I6 applying a force to the projectile to increase the forward motion thereof.
In order to impart further rotation to the projectile to thereby increase the accuracy thereof, a plurality of reaction vanes 24 are mounted in the exhaust nozzle I6 extending inwardly toward the longitudinal axis of the casing Ill. As shown more clearly in Fig. 2 of the drawing, the vanes 24 are angularly mounted with respect to the longitudinal axis of the casing ID to provide reaction members responsive to the hot motive fluid passing thereover for imparting rotation to the projectile about the longitudinal axis thereof.
As previously mentioned, means are also provided by the present invention for improving the aerodynamic characteristics of projectiles to further increase the range and accuracy thereof. Such means functions to discharge a high velocity hot motive fluid jet along the outer surface of the casing I0, throughout the entire diameter thereof, from a point adjacent the opening II, rearwardly toward the wall I2. The presence of a high velocity fluid jet along the outer surface of the casing I0 effectively energizes the boundary layer formed thereon, to reduce friction, to prevent separation and to increase the overall aerodynamic characteristics of the projectile. As shown in Figs. 1 and 3, the foregoing means comprises a circumferential discharge nozzle 25 located in the forward end of the casing I0, adjacent and rearwardly of the opening II. The nozzle 25 is positioned to discharge a high velocity fluid jet rearwardly along the outer surface of the casing I0 throughout the entire area thereof. The nozzle 25 extends inwardly toward the longitudinal axis of the casing I0 and terminates in a circumferential manifold 26. A plurality of conduits 21 form a fluid communication between the manifold 26 and the combustion chamber I5 in such a manner to transfer a portion of the hot motive fluid generated in the combustion chamber I5 to the manifold 26 for energizing the nozzle 25. In order to produce a high velocity fluid jet from the nozzle 25 the number of conduits 21, the dimensions of the nozzle 25, the manifold 26 and the conduits 21 are properly proportioned to maintain the required pressure relationships.
In Fig. 4 of the drawings a projectile having primary propulsion means, such as a rocket motor for accelerating the projectile to an initial velocity, is disclosed including novel features of the present invention. This embodiment includes certain features of the invention disclosed in Fig. l, and similar elements are designated by corresponding reference numerals. The primary pro pulsion means comprises a rocket mechanism of conventional construction carried by a casing '39 including a plurality of rocket exhaust ports 3| in the rear end thereof. The casing 30 is designed for insertion in an exhaust nozzle 32 which also functions to form a discharge passage for the hot motive fluid generated in the combustion chamber I5, in a manner similar to the exhaust nozzle I6 of Fig. 1. Upon ignition of the primary propulsion means the projectile is accelerated thereby to a velocity determined by the characteristics thereof. As the energy of the primary propulsion means dissipates the forces applied to the forward end of the casing 30 by the pressures in the chamber I5 eject the casing 30 from the exhaust nozzle 32. After ejection of the casing 30, generated hot motive fluid exhausts through the nozzle 32 applying forces to further accelerate the projectile in a manner similar to operation of the Fig. 1 system.
In this embodiment means are provided for supplying fluid under pressure to the combustion chamber I5 independently of axial rotation of the casing II]. A resilient diaphragm 33, constructed of hydrocarbon resistant plastic material, is provided for separating the reservoir I? into a fuel chamber 34 and an air chamber 35. The fuel chamber 34 communicates with the fuel conduit I8, while the air chamber 35 is initially supplied with air under suitable pressure to maintain the supplied fuel above a predetermined pressure throughout the period of operation.
Since the type of projectile disclosed in Fig. 4 is discharged from a smooth tube means are provided for imparting axial rotation thereto. The rocket mechanism exhaust ports 3| are angularly positioned with respect to the longitudinal axis of the projectile to impart rotation thereto during operation of the primary propulsion means. As shown in Fig. 5, the means for imparting rotation to the projectile after the casing 36 is discharged therefrom includes a plurality of reaction vanes 36 pivotally mounted in slots 37 angularly positioned in the casing I0 with respect to the longitudinal axis thereof. The vanes 36 are urged inwardly toward the longitudinal axis of the projectile to extend within the nozzle 32 by the action of spring numbers 38. When the easing 30 is inserted into the exhaust conduit 32 the vanes 36 are forced into respective slots 37. The flow of hot motive fluid through the nozzle 32 reacts against the vanes 36 to impart rotation to the projectile in a manner similar to the arrangement shown in Fig. 1.
There is thus provided by the present invention novel means for increasing the range and accuracy of projectiles. The novel means is so characterized to be readily utilized in connection with rifle shells, rockets fired from smooth tubes and aerial bombs. Moreover, the novel means are constructed in such a manner as to operate automatically when the projectile attains a predetermined velocity to generate a source of energy for imparting further acceleration thereto. Furthermore, novel means are provided by the present invention for energizing the boundary layer formed on the outer surface of the projectile to improve the aerodynamic characteristics thereof.
Although several embodiments of the present invention have been disclosed and described herein it is to be expressly understood that various changes and substitutions may be made therein without departing from the spirit of the invention as well understood by those skilled in the art. For example, automatic pressure responsive valvular means may be employed at the input and output ports of the combustion chamber to provide intermittent operation if desired. Furthermore, it is to be expressly understood that the unused volume within the casing ID is provided for carrying elements commensurate with the desired use of the projectile, such as explosive charges for example when the projectile is employed as a destructive missile. Reference therefore will be had to the appended claims for the definition of the limits of the invention.
The invention described herein may be manufactured and used by or for the Government of the United States of .America for governmental purposes without the payment of any royalties thereon or therefor.
What is claimed is:
1. In a projectile adapted to be discharged from a smooth bore means including a casing, means forming a longitudinal opening through said casing, said opening including an input portion extending from the forward end of said casing with gradually decreasing cross-sectional area, a high pressure area of reduced cross-sectional area communicating with said input portion and an exhaust portion extending with gradually increasing cross-sectional area from said high pressure area to the rear end of said projectile, conduit means leading from said high pressure area, a nozzle exhausting at the forward outer surface of the projectile and connected to said conduit means to discharge a high velocity fiuid jet rearwardly along the outer surface of said casing throughout the entire area thereof, said exhaust portion including a plurality of movable reaction vanes pivotably mounted in slots annularly positioned in said casing with respect to the longitudinal axis thereof, said reaction vanes imparting rotation to said projectile, propulsion means mounted in said exhaust portion operable to accelerate said projectile to a certain velocity, means including an annular fuel reservoir surrounding said high pressure area and a fuel conduit, means in said fuel conduit to control the amount of fuel from said annular reservoir to said high pressure area for generating a source of hot motive fluid in said pressure area for discharge through said exhaust conduit to further accelerate said projectile after discharge of said propulsion means.
2. In a projectile adapted to be discharged from a smooth bore means including a casing, means forming a longitudinal opening through said casing, said opening including an input portion extending from the forward end of said casing with gradually decreasing cross-sectional area, a high pressure area of reduced cross-sectional area communicating with said input portion and an exhaust portion extending with gradually increasing cross-sectional area from said high pressure area to the rear end of said projectile, conduit means leading from said high pressure area, a nozzle exhausting at the forward outer surface of the projectile and connected to said conduit means to discharge a high velocity fluid jet rear- Wardly along the outer surface of said casing throughout the entire area thereof, said exhaust portion including a plurality of movable reaction vanes pivotably mounted in slots annularly positioned in said casing with respect to the longitudinal axis thereof, said reaction vanes imparting rotation to said projectile, propulsion means mounted in said exhaust portion operable to accelerate said projectile to a certain velocity, said propulsion means mounted for discharge from said exhaust portion by the pressure in said pressure area after dissipation of the energy thereof, means including an annular fuel reservoir surrounding said high pressure area and a fuel conduit, means in said fuel conduit to control the amount of fuel from said annular reservoir to said high pressure area for generating a source of hot motive fluid in said pressure area for discharge through said exhaust conduit to further accelerate said projectile after discharge of said propulsion means.
JAMES A. MCNALLY.
REFERENCES CITED The following references are of record in the file of this patent:
UNITED STATES PATENTS Number Name Date 1,376,316 Chilowsky Apr. 26, 1921 1,994,490 Skinner Mar. 19, 1935 2,246,429 Brandt June 17, 1941 2,410,538 Walton Nov. 5, 1946 2,419,866 Wilson Apr. 29, 1947 FOREIGN PATENTS Number Country Date 1,734 Great Britain 1876 14,000 Great Britain 1896 126,325 Great Britain May 15, 1919 637,043 Germany Oct. 19, 1936 866,598 France May 26, 1941
US773283A 1947-09-10 1947-09-10 Projectile Expired - Lifetime US2624281A (en)

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Cited By (24)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2940213A (en) * 1955-05-04 1960-06-14 Hans A Mauch Jet propelled balloon
US2941469A (en) * 1955-11-15 1960-06-21 George E Barnhart Projectile construction
US2972950A (en) * 1952-08-22 1961-02-28 Ludolph F Welanetz Rod type explosive warhead
US2989922A (en) * 1953-02-17 1961-06-27 Marvin H Greenwood Ramjet propulsion device
US2995317A (en) * 1955-09-14 1961-08-08 Metallbau Semler G M B H External combustion stato-jet engine
US3002716A (en) * 1956-03-01 1961-10-03 Power Jets Res & Dev Ltd Aircraft
US3008413A (en) * 1956-05-24 1961-11-14 Georg E Knausenberger High speed missile
DE1147144B (en) * 1958-09-08 1963-04-11 Ferdinand Metzler Jet propelled missile
US3095163A (en) * 1959-10-13 1963-06-25 Petroleum Res Corp Ionized boundary layer fluid pumping system
US3556443A (en) * 1968-07-23 1971-01-19 Robert P Kidwell Boundary layer control of airborne vehicles
US3635404A (en) * 1970-06-18 1972-01-18 Us Navy Spin stabilizing rocket nozzle
US3713157A (en) * 1964-07-31 1973-01-23 North American Aviation Inc Energy absorption by a radioisotope produced plasma
FR2192699A5 (en) * 1971-01-06 1974-02-08 Flatau Abraham
FR2496868A1 (en) * 1980-12-19 1982-06-25 United Technologies Corp VARIABLE PUSH-STATOREACTOR PROJECTILE LAUNCHED BY CANON
US4502649A (en) * 1980-12-19 1985-03-05 United Technologies Corporation Gun-launched variable thrust ramjet projectile
US4537371A (en) * 1982-08-30 1985-08-27 Ltv Aerospace And Defense Company Small caliber guided projectile
FR2663113A1 (en) * 1990-06-08 1991-12-13 Rheinmetall Gmbh PROJECTILE WITH UNDER-CALIBER KINETIC EFFECT FOR SHOOTING EXERCISES.
US5485975A (en) * 1994-07-19 1996-01-23 Northrop Grumman Corporation Slotted cowl inlet lip for introducing high pressure air
US5934611A (en) * 1997-10-20 1999-08-10 Northrop Grumman Corporation Low drag inlet design using injected duct flow
US6464171B2 (en) * 1997-04-04 2002-10-15 Georgia Tech Research Corp. Leading edge channel for enhancement of lift/drag ratio and reduction of sonic boom
US7861977B1 (en) * 2006-03-13 2011-01-04 The United States Of America As Represented By The Secretary Of The Navy Adaptive material actuators for Coanda effect circulation control slots
US9297625B2 (en) * 2013-06-24 2016-03-29 Charl E. Janeke Apparatus and methods for hypersonic nosecone
US10094644B2 (en) * 2013-07-31 2018-10-09 Alpha Velorum Ag Method for increasing the range of spin-stabilized projectiles, and projectile of said type
US10139207B2 (en) * 2016-02-04 2018-11-27 Richard D Adams Projectile having increased velocity and aerodynamic performance

Citations (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB189614000A (en) * 1896-06-24 1897-05-29 Alfred Vincent Newton Improvements in War Rockets.
GB126325A (en) * 1916-08-21 1919-05-15 Procedes Westinghouse Leblanc Improvements in War Rockets.
US1376316A (en) * 1918-10-24 1921-04-26 Chilowsky Constantin Projectile
US1994490A (en) * 1934-09-11 1935-03-19 Leslie A Skinner Rocket projectile
DE637043C (en) * 1934-05-25 1936-10-19 E H Gustav De Grahl Dr Ing Missile with air ducts surrounding the combustion chamber
US2246429A (en) * 1936-03-30 1941-06-17 Sageb Sa Projectile
FR866598A (en) * 1940-04-24 1941-08-20 Improvements to self-propelling projectiles
US2410538A (en) * 1939-11-22 1946-11-05 Walton George William Prime mover
US2419866A (en) * 1941-02-11 1947-04-29 Wilson Walter Gordon Aerial torpedo

Patent Citations (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB189614000A (en) * 1896-06-24 1897-05-29 Alfred Vincent Newton Improvements in War Rockets.
GB126325A (en) * 1916-08-21 1919-05-15 Procedes Westinghouse Leblanc Improvements in War Rockets.
US1376316A (en) * 1918-10-24 1921-04-26 Chilowsky Constantin Projectile
DE637043C (en) * 1934-05-25 1936-10-19 E H Gustav De Grahl Dr Ing Missile with air ducts surrounding the combustion chamber
US1994490A (en) * 1934-09-11 1935-03-19 Leslie A Skinner Rocket projectile
US2246429A (en) * 1936-03-30 1941-06-17 Sageb Sa Projectile
US2410538A (en) * 1939-11-22 1946-11-05 Walton George William Prime mover
FR866598A (en) * 1940-04-24 1941-08-20 Improvements to self-propelling projectiles
US2419866A (en) * 1941-02-11 1947-04-29 Wilson Walter Gordon Aerial torpedo

Cited By (26)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2972950A (en) * 1952-08-22 1961-02-28 Ludolph F Welanetz Rod type explosive warhead
US2989922A (en) * 1953-02-17 1961-06-27 Marvin H Greenwood Ramjet propulsion device
US2940213A (en) * 1955-05-04 1960-06-14 Hans A Mauch Jet propelled balloon
US2995317A (en) * 1955-09-14 1961-08-08 Metallbau Semler G M B H External combustion stato-jet engine
US2941469A (en) * 1955-11-15 1960-06-21 George E Barnhart Projectile construction
US3002716A (en) * 1956-03-01 1961-10-03 Power Jets Res & Dev Ltd Aircraft
US3008413A (en) * 1956-05-24 1961-11-14 Georg E Knausenberger High speed missile
DE1147144B (en) * 1958-09-08 1963-04-11 Ferdinand Metzler Jet propelled missile
US3095163A (en) * 1959-10-13 1963-06-25 Petroleum Res Corp Ionized boundary layer fluid pumping system
US3713157A (en) * 1964-07-31 1973-01-23 North American Aviation Inc Energy absorption by a radioisotope produced plasma
US3556443A (en) * 1968-07-23 1971-01-19 Robert P Kidwell Boundary layer control of airborne vehicles
US3635404A (en) * 1970-06-18 1972-01-18 Us Navy Spin stabilizing rocket nozzle
FR2192699A5 (en) * 1971-01-06 1974-02-08 Flatau Abraham
US3877383A (en) * 1971-01-06 1975-04-15 Abraham Flatau Munition
FR2496868A1 (en) * 1980-12-19 1982-06-25 United Technologies Corp VARIABLE PUSH-STATOREACTOR PROJECTILE LAUNCHED BY CANON
DE3149735A1 (en) * 1980-12-19 1982-08-12 United Technologies Corp STRAINJET ENGINE BULLET AND METHOD THAT FOLLOWS A BALLISTIC FLIGHT TRACK
US4502649A (en) * 1980-12-19 1985-03-05 United Technologies Corporation Gun-launched variable thrust ramjet projectile
US4537371A (en) * 1982-08-30 1985-08-27 Ltv Aerospace And Defense Company Small caliber guided projectile
FR2663113A1 (en) * 1990-06-08 1991-12-13 Rheinmetall Gmbh PROJECTILE WITH UNDER-CALIBER KINETIC EFFECT FOR SHOOTING EXERCISES.
US5485975A (en) * 1994-07-19 1996-01-23 Northrop Grumman Corporation Slotted cowl inlet lip for introducing high pressure air
US6464171B2 (en) * 1997-04-04 2002-10-15 Georgia Tech Research Corp. Leading edge channel for enhancement of lift/drag ratio and reduction of sonic boom
US5934611A (en) * 1997-10-20 1999-08-10 Northrop Grumman Corporation Low drag inlet design using injected duct flow
US7861977B1 (en) * 2006-03-13 2011-01-04 The United States Of America As Represented By The Secretary Of The Navy Adaptive material actuators for Coanda effect circulation control slots
US9297625B2 (en) * 2013-06-24 2016-03-29 Charl E. Janeke Apparatus and methods for hypersonic nosecone
US10094644B2 (en) * 2013-07-31 2018-10-09 Alpha Velorum Ag Method for increasing the range of spin-stabilized projectiles, and projectile of said type
US10139207B2 (en) * 2016-02-04 2018-11-27 Richard D Adams Projectile having increased velocity and aerodynamic performance

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