EP0774104B1 - Systeme de projectile a stabilisation gyroscopique dirige contre des objets sous-marins - Google Patents

Systeme de projectile a stabilisation gyroscopique dirige contre des objets sous-marins Download PDF

Info

Publication number
EP0774104B1
EP0774104B1 EP96918101A EP96918101A EP0774104B1 EP 0774104 B1 EP0774104 B1 EP 0774104B1 EP 96918101 A EP96918101 A EP 96918101A EP 96918101 A EP96918101 A EP 96918101A EP 0774104 B1 EP0774104 B1 EP 0774104B1
Authority
EP
European Patent Office
Prior art keywords
projectile
stinger
nose
afterbody
water
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
EP96918101A
Other languages
German (de)
English (en)
Other versions
EP0774104A1 (fr
Inventor
Jeffrey A. Brown
Reed Copsey
Marshall Tulin
Roy Kline
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.)
Raytheon Co
Original Assignee
Raytheon Co
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 Raytheon Co filed Critical Raytheon Co
Publication of EP0774104A1 publication Critical patent/EP0774104A1/fr
Application granted granted Critical
Publication of EP0774104B1 publication Critical patent/EP0774104B1/fr
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

Links

Images

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
    • F42B10/42—Streamlined projectiles
    • F42B10/46—Streamlined nose cones; Windshields; Radomes
    • 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

Definitions

  • This invention relates to munitions, and, more particularly, to a projectile system that can be fired from air against underwater objects located at moderate underwater ranges.
  • Projectiles are widely used against targets in air.
  • the projectile is placed into a gun, together with a propellant.
  • the propellant is ignited, driving the projectile out of the barrel of the gun and toward the target.
  • Projectiles have extremely limited capability to be fired from air against targets in water, primarily for three reasons.
  • the projectile may not enter the water at all, and instead may skip away.
  • the projectile may enter the water but its path is altered. This problem is always a consideration, but it is of particular concern to the accuracy of the projectile when the surface of the water exhibits a constantly varying state due to wave motion.
  • Second, the drag produced by the water rapidly slows the projectile and drastically limits its range.
  • the range of conventional projectiles in water varies according to the weight and initial velocity of the projectile, but is typically at most no more than about 0.91m (3 feet) under optimal conditions for a conventional 20 millimeter projectile.
  • the lateral hydrodynamic forces on the projectile can cause it to tumble, further limiting its range and effectiveness.
  • the present invention fulfills this need, and further provides related advantages.
  • DE-4022462A discloses a solid air-launched underwater projectile formed from a modified sub-calibre solid shot.
  • the core of the solid shot has a shortened front portion projected by a ballistic cap. It is relieved to form an annular step, clear of which is a cylindrical portion smaller than the core and with a flat end face at right angles to the core axis.
  • the present invention provides a projectile system, as claimed in claim 1, and a method, as claimed in claim 11, for its use.
  • the projectile system is fired from air against submerged underwater objects, passing through the air/water interface on its way to the target.
  • the demonstrated range of the projectile is about 4.6m (15 feet) under water in a 0.50 caliber size.
  • the projectile can pass through the air/water interface with little or no deflection, regardless of the angle of incidence of the projectile.
  • the projectile is relatively inexpensive, and can be produced for a variety of both conventional and unconventional weapons of various bores.
  • a projectile system comprises a projectile having a generally cylindrically symmetric projectile body with a projectile body forward end and a projectile body rearward end.
  • the projectile includes means for forming a cavitation void around the projectile body when the projectile body is passed through water located at the projectile body forward end.
  • the cavitation void is a substantially liquid-free volume extending radially outwardly and rearwardly from the wetted forward end of the projectile.
  • This volume filled only with air and water vapor, exerts little drag and/or lateral force on the body of the projectile. Consequently, the projectile can travel for moderately large distances through water. If, as the projectile enters or travels through water, it experiences lateral instability so that the cylindrical axis of the projectile does not coincide with its trajectory (flight path), the stabilizing means interacts with the surface of the cavitation void and exerts a restoring force that tends to bring the cylindrical axis of the projectile back into coincidence with the trajectory. Absent such a restoring force, the projectile would quickly deviate from its trajectory and begin tumbling.
  • a projectile system comprises a generally cylindrically symmetric projectile with a projectile forward end and a projectile rearward end.
  • the projectile has a stinger head at the projectile forward end.
  • the stinger head includes a stinger nose having a nose maximum diameter and a stinger body having a stinger body forward end joined to a rearward end of the stinger nose.
  • the stinger body includes a stinger nose support having a nose support diameter, and a flow separation groove between the stinger nose support and the stinger nose.
  • the flow separation groove has a groove diameter less than the nose maximum diameter.
  • the projectile further includes a generally cylindrically symmetric projectile body joined to the stinger head.
  • the projectile body has a projectile afterbody having a projectile afterbody diameter greater than the nose support maximum diameter, and a projectile forebody joined to the stinger nose support at a forward end and to the projectile afterbody at a rearward end. There is means for stabilizing the projectile against lateral instability joined to the projectile body.
  • a projectile is an object that is propelled by an external force, and which has no capacity for self propulsion.
  • a bullet mounted to a canister of propellant that remains in a gun after the bullet is fired is a projectile because the bullet itself has no self-propulsion capability.
  • aircraft, rockets, and torpedoes that have a built-in engine and carry their own fuel are not projectiles.
  • the present invention relates to a projectile and a system for its utilization, not to a self-propelled device.
  • the projectile system can further include a discardable sabot that initially fits around the projectile and creates a uniform diameter that fits smoothly in the bore of a firing weapon. After the projectile system is fired, the sabot falls away and the projectile travels along its trajectory to the target.
  • the present invention provides an important advance in the art of projectile systems.
  • the projectile of the invention can be fired from air effectively against an underwater target. In the air, the projectile is spin stabilized along a straight trajectory. The projectile passes through the air/water interface with little deflection, for a wide range of angles of incidence. In water, the trajectory is maintained and there is a moderate underwater range.
  • Figure 1 depicts a series 20 of projectiles being propelled from a barrel of a gun 22, which is located in air, toward a target 24, which is immersed in water.
  • the first-fired projectile 26 has passed through an air/water interface 28 and is surrounded by water. However, the first-fired projectile 26 resides within a cavitation void 30, so that the surrounding water does not actually touch the first-fired projectile 26, except at its wetted forwardmost end.
  • a second-fired projectile 32 is still travelling along its trajectory in air. Pieces 34 of an optional sabot have separated from the second-fired projectile 32 shortly after the second-fired projectile 32 has left the gun 22.
  • a third-fired projectile 36 has a sabot 38 still positioned around the projectile, prior to its separation. The projectile 36 and sabot 38 together constitute one form of a projectile system 40.
  • Figure 2 illustrates one embodiment of a projectile 50 in side elevation
  • Figure 3 shows the front elevation of the same projectile.
  • the projectile 50 is generally cylindrically symmetric with a forward end 52 and a rearward end 54.
  • "generally cylindrically symmetric" means that the body is cylindrically symmetric about a cylindrical axis 56, except that there may be discrete features such as fragmentation grooves, fins, or flares which are spaced around the circumference of the body.
  • the projectile body 58 includes a generally cylindrically symmetric projectile afterbody 60 that occupies approximately the rearmost half of the projectile body 58.
  • the projectile body 58 also includes a generally cylindrically symmetric projectile forebody 62 whose rearward end 64 is contiguous with the projectile afterbody 60.
  • the projectile forebody 62 is in the shape of a frustum of a cone.
  • the projectile body 58 is preferably formed of a dense penetrator material such as tungsten.
  • the projectile body 58 may optionally be hollow to contain a payload cavity 66, shown in Figure 4.
  • the payload cavity 66 contains a reactive chemical such as lithium perchlorate oxidizer or an explosive.
  • a pattern of fragmentation grooves 68 is desirably formed on an outer surface of the projectile body 58, as shown in Figure 5.
  • the fragmentation grooves 68 include longitudinal grooves 70 extending parallel to the cylindrical axis 56 and one or more circumferential grooves 72 extending around the circumference of the payload body 58.
  • a structure that induces the creation of the cavitation void 30 around the projectile 50 when the projectile 50 travels rapidly through water is located at the forward end 52 of the projectile 50.
  • This structure passes through the water such that the water does not flow along the projectile body 58. Instead, the water is forced in a transverse direction so that it does not contact and wet the sides of the projectile body 58. Only the cavitation-producing structure contacts and is wetted by the water.
  • the cavitation void 30 is a partial vacuum that may contain some air and water vapor.
  • Figure 6 illustrates one form of the cavitation-producing structure, a stinger head 74.
  • the stinger head 74 is cylindrically symmetric about the cylindrical axis 56 and is affixed to a projectile body forward end 76.
  • the stinger head 74 includes a forwardmost stinger nose 78.
  • the stinger nose 78 includes a flat, blunt forward face 80 with a nose maximum diameter D N .
  • This forward face 80 is preferably very smooth, with a surface roughness of no more than about 406 ⁇ m (16 microinches).
  • the stinger nose 78 tapers radially inwardly at an angle A, which is preferably about 80°, relative to the forward face 80.
  • the stinger nose 78 is supported on a stinger body 82, which in turn is affixed to the projectile body forward end 76.
  • the stinger body 82 includes a cylindrical stinger nose support 84 and a circumferential flow separation groove 86 between the stinger nose support 84 and the stinger nose 78.
  • the flow separation groove 86 may alternatively be viewed as a forwardly facing shoulder between the stinger nose support 84 and the stinger nose 78.
  • a diameter D G of the flow separation groove 86 is less than the diameter D N of the forward face 80 of the stinger nose 78.
  • the stinger head 74 is preferably made of a hard material such as high speed steel, tungsten carbide, or tungsten alloy to resist impact with the water.
  • the stinger head 74 impacts the water at velocities as high as 914-1219 m/s (3000-4000 feet per second), which imposes a loading of about 5GPa (50 kilobars) on the stinger head in a period of about 0.1 microsecond.
  • the stinger nose 78 portion of the stinger head 74 should be very smooth to promote a thin boundary layer dimension. Testing has shown that the stinger nose 78 should have a surface roughness of no greater than about 406 ⁇ m (16 microinches) in order to achieve the desired boundary layer dimension during the travel of the projectile through the water.
  • a water flow boundary layer is produced at the stinger nose 78.
  • the water flow boundary layer adheres to the surface of the stinger nose 78.
  • the inwardly tapered shape of the stinger nose 78 cooperates with the flow separation groove 86 to cause an intended flow separation of the water from the projectile 50 as the projectile 50 passes through the water. As shown in Figure 7, this flow separation creates the cavitation void 30.
  • the forwardly facing surface 80 of the stinger nose 78 portion of the projectile 50 contacts the water, and the remainder of the projectile 50 is not wetted.
  • the pressure and skin drag on the projectile 50 is therefore minimal, resulting in greatly extended underwater range of the projectile as compared with conventional projectiles. Hydrodynamic effects on the projectile that potentially cause trajectory deviations are also reduced.
  • the stinger nose 78 is not optimally streamlined for passage through the air, but because of its small diameter the added air resistance is not significant and the projectile 50 is capable of supersonic flight through air.
  • the projectile 50 includes a forwardly facing stabilization shoulder 90 positioned between the projectile afterbody 60 and the projectile forebody 62, as seen in Figures 2, 5, 7, and 8.
  • This stabilization shoulder 90 is formed by making the diameter of the projectile afterbody 60 larger than that of the projectile forebody 62 at their point of joining.
  • the shoulder 90 may be at 90° to the cylindrical axis 56, or rearwardly tapered.
  • the stabilization shoulder 90 functions in the manner shown in Figure 8. If the projectile 50 yaws into the wall of the cavity 30, the stabilization shoulder 90 is brought into contact with the envelope of the cavitation void 30. Water pressure against the stabilization shoulder 90 creates a restoring force that pushes the cylindrical axis 56 of the projectile 50 back toward coincidence with the trajectory 88.
  • the stabilization shoulder 90 also plays a role in fragmentation of the projectile 50 by imposing a fragmentation force on the projectile body 58 that is unique to the event of impact with the target 24 and is not experienced as the projectile enters the water or elsewhere. After the stinger head 74 and projectile forebody 62 have penetrated the target, the target contacts the stabilization shoulder 90 to push it and thence the outer casing of the projectile afterbody 60 rearwardly toward the fragmentation grooves 68. This relative movement leads to a fragmentation of the outer casing of the projectile afterbody 60 and exposure and dispersal of the contents of the payload cavity 66.
  • the projectile 50 is desirably manufactured in three pieces shown in Figure 2: the stinger head 74, a forebody unit 92, and an afterbody unit 94, which are thereafter assembled as the final projectile 50.
  • This approach allows the stinger head 74 to be made of a hard, erosion-resistant, and impact-resistant material such as high speed steel, tungsten carbide, or tungsten alloy.
  • the stinger head 74 can be machined to an extremely smooth finish.
  • the projectile forebody unit 92 is made of a dense material such as tungsten, to provide mass and to reduce wear on the inside of the gun barrel.
  • the projectile afterbody unit 94 is made of a soft, less dense material such as copper or brass, to reduce the mass at the rear of the projectile.
  • the projectile 50 is initially furnished encased within the sabot 38, as shown in Figure 9.
  • the sabot 38 is a sectional housing formed of a plurality of the pieces 34 that fit over the projectile body 58, permitting the projectile forebody 62 and the stinger head 74 to extend therefrom.
  • the sabot 38 is made of a relatively soft material such as nylon 612, which, unlike the metallic and hard materials that comprise the projectile body 58, does not unduly wear the interior walls of the barrel of the gun 22 as the projectile system 40 is fired therefrom.
  • the projectile system 40 is loaded into a cartridge (not shown) that also contains gunpowder and a primer behind the sabot, in the manner of a conventional bullet.
  • This assembly is loaded into the gun 22, the charge of powder is ignited, and the projectile system travels the length of the barrel and out of the gun.
  • the rifling of the barrel of the gun acting against the exterior surface of the sabot 34 induces a spinning of the projectile system 40 about the cylindrical axis 56.
  • This spinning comparable to the spinning induced in conventional bullets, gyroscopically stabilizes the trajectory of the projectile as it travels through the air.
  • the sabot 38 remains in contact with the projectile 50, see projectile 36 of Figure 1.
  • the sabot pieces 34 separate from the projectile under the influence of the imposed aerodynamic forces, as seen for the projectile 32 of Figure 1. The sabot pieces 34 are thus discarded, and the projectile travels along its trajectory toward the target.
  • the projectile 50 preferably has a length-to-diameter ratio (L/D) of greater than 4:1, and is preferably from about 4:1 to about 8:1.
  • L/D length-to-diameter ratio
  • the restoring force moment arm is insufficient to counteract lateral instability and there is insufficient mass in the projectile for satisfactory penetration.
  • L/D the projectile becomes difficult to stabilize gyroscopically and cannot be accommodated in conventional gun mechanisms.
  • conventional fired projectiles have L/D ratios of about 2-3.
  • Figure 10 illustrates a projectile 100 having a radially flared enlargement 102 of a projectile afterbody 104 at the rearmost end of the projectile afterbody 104.
  • This radially flared enlargement 102 also serves a stabilization function, like the stabilization shoulder 90. If the radially flared enlargement 102 contacts the sides of the cavitation void 30 as a result of a lateral instability, it produces a restoring force in the manner discussed previously for the stabilization shoulder 90.
  • the use of the radially flared enlargement 102 has the advantage that its moment arm to the center of gravity of the projectile 100 is larger than the moment arm of the stabilization shoulder 90 to the center of gravity of the projectile 100, so that the restoring torque is greater. It has the disadvantage of increasing the outer diameter of the projectile 100 and adding mass at the rear of the projectile 100 rather than further forward as is desirable.
  • FIG. 10 Another embodiment of a stinger head 106 is also shown in Figure 10 and in greater detail in Figure 11.
  • the stinger head 106 is like the stinger head 74, except that a conical forward face 108 is substituted for the flat forward face 80 of Figure 6.
  • An included conical angle B of the conical nose 108 can be as large as about 130° while still permitting the stinger head 106 to cooperate with the flow separation groove 86 to induce the flow separation that leads to the formation of the cavitation void 30 as the projectile 100 travels through the water.
  • the flat forward face 80 of Figure 6 is preferred to induce the flow separation, but the use of the conical forward face 108 has the advantage that it reduces the shock loading on the projectile 100 as it enters the water at the air/water interface 28. For designs utilizing a high mass of the projectile and a propellant creating a high muzzle velocity, it may be necessary to reduce such shock loading so that the projectile does not fragment when it enters the water.
  • Figure 12 also shows another embodiment of a projectile forebody 118.
  • the projectile forebody 62 of Figure 2 is generally conical.
  • the projectile forebody 118 of Figure 12 is ogival in shape.
  • An ogive having a shape generally describable as comprising a portion of an ellipse, is convexly curved outwardly as compared with a conical shape.
  • the ogive permits additional mass of the projectile 110 to be concentrated toward the forward end of the projectile 110, as desired, rather than toward its rear.
  • Ogival shapes are used in some other contexts such as some conventional bullets, missiles, and rockets for another reason, reducing aerodynamic drag.
  • the ogival projectile forebody 118 has little effect on aerodynamic drag as compared with the conical projectile forebody 62. Instead, as noted, its function is to increase the mass of the projectile 110, with the mass positioned near the forward end. Other shapes of the projectile forebody can also be used.
  • Figure 13 illustrates a preferred method for utilizing any of the projectiles and projectile systems made according to the present invention to damage an underwater object.
  • a projectile system is provided, numeral 130.
  • the projectile system is as previously described, or has a combination of the features previously described.
  • the projectile system is propelled toward an underwater target from a location in the air, numeral 132, as illustrated in Figure 1.
  • the projectile travels through the air initially, passes through the air/water interface, and then travels through the water toward the target.
  • Embodiments of the present invention have been prepared for 20 millimeter and .50 caliber projectile systems and fired from air against underwater targets. Water penetration without skipping was obtained at angles of incidence from vertical (90°) to as shallow as about 20° in both cases. Conventional projectiles skip at angles of incidence less than about 30°, while the present projectile can enter the water at shallower angles.
  • the 20 millimeter projectile had an underwater range of about 30.5m (100 feet), as compared with an underwater range of about 0.91m (3 feet) for a conventional 20 millimeter projectile.
  • the .50 caliber projectile had an underwater range of about 4.6m (15 feet), as compared with an underwater range of about 0.91m (3 feet) for a conventional .50 caliber projectile. (Range here is defined as the distance of penetration through water to strike the target at a velocity of about 305 m/s (1000 feet per second).)

Landscapes

  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Toys (AREA)
  • Control Of Position, Course, Altitude, Or Attitude Of Moving Bodies (AREA)
  • Traffic Control Systems (AREA)
  • Confectionery (AREA)
  • Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)

Claims (11)

  1. Système de projectile comprenant un projectile (50) ayant de façon générale une symétrie de révolution, avec une extrémité avant de projectile (52) et une extrémité arrière de projectile (54), le projectile ayant :
    une tête de dard (74) à l'extrémité avant de projectile (76), la tête de dard (74) comprenant
    un nez de dard (78) ayant un diamètre de nez maximal,
    un corps de dard (82) ayant une extrémité avant de corps de dard jointe à une extrémité arrière du nez de dard (78), le corps de dard comprenant
    un support de nez de dard (84) ayant un diamètre de support de nez, et
    une gorge de séparation d'écoulement (86) entre le support de nez de dard (84) et le nez de dard (78), la gorge de séparation d'écoulement (86) ayant un diamètre de gorge inférieur au diamètre de nez maximal;
    un corps de projectile (58) ayant de façon générale une symétrie de révolution, joint à la tête de dard, le corps de projectile (58) ayant
    un arrière-corps de projectile (60) ayant un diamètre d'arrière-corps de projectile supérieur au diamètre de nez maximal, et
    un avant-corps de projectile (62) joint au support de nez de dard à une extrémité avant et à l'arrière-corps de projectile à une extrémité arrière (64); et
    des moyens (90) pour stabiliser le projectile contre une instabilité latérale, les moyens de stabilisation étant joints au corps de projectile (58)
       caractérisé en ce que
    l'arrière-corps de projectile comprend en outre
    une cavité de charge utile (66), et
    une charge utile contenue à l'intérieur de la cavité de charge utile (66).
  2. Système de projectile selon la revendication 1, dans lequel le nez de dard (78) comprend une face avant mousse (80) ou une face avant conique.
  3. Système de projectile selon la revendication 1, dans lequel le nez de dard (78) comprend
    une région avant de nez de dard ayant un diamètre maximal de région avant de nez de dard,
    une région arrière de nez de dard adjacente à la gorge de séparation d'écoulement (86), la région arrière de nez de dard ayant un diamètre de région arrière de nez de dard inférieur au diamètre maximal de région avant de nez de dard.
  4. Système de projectile selon la revendication 1, dans lequel la gorge de séparation d'écoulement (86) comprend
       un épaulement de gorge de séparation faisant face vers l'avant, entre le nez de dard (78) et le support de nez de dard (84).
  5. Système de projectile selon la revendication 1, dans lequel l'arrière-corps de projectile comprend
    une région centrale cylindrique, et
    une pluralité de gorges (68) dans la région centrale.
  6. Système de projectile selon la revendication 1, dans lequel les moyens de stabilisation comprennent
       un épaulement de stabilisation (90) faisant face vers l'avant, placé entre l'arrière-corps de projectile (60) et la région d'avant-corps de projectile (62).
  7. Système de projectile selon la revendication 6, dans lequel les moyens de stabilisation (90) comprennent en outre
       un agrandissement évasé radialement sur l'arrière-corps de projectile (60), à l'extrémité arrière (64) du projectile.
  8. Système de projectile selon la revendication 1, dans lequel le riez de dard (78) a une finition de surface correspondant à une rugosité ne dépassant pas environ 406 µm (16 micro-pouces).
  9. Système de projectile selon la revendication 1, dans lequel la tête de dard (74) est constituée par un matériau sélectionné dans le groupe comprenant l'acier et le carbure de tungstène.
  10. Système de projectile selon la revendication 1, comprenant en outre
       un sabot largable (34) fixé autour du projectile (50).
  11. Procédé pour endommager une cible sous-marine (24), comprenant les étapes suivantes :
    on fournit un système de projectile incluant un projectile (50) comprenant
    un corps de projectile (58) présentant de façon générale une symétrie de révolution, avec une extrémité avant de corps de projectile (62) et une extrémité arrière de corps de projectile (60),
    des moyens pour former un vide de cavitation (30) autour du corps de projectile (58) lorsque le corps de projectile (58) passe dans l'eau, les moyens de formation étant placés à l'extrémité avant de corps de projectile (62), et
    des moyens (90) pour stabiliser le corps de projectile (58) contre une instabilité latérale, les moyens de stabilisation (90) étant joints au corps de projectile (58); et
    on propulse le projectile (50) vers une cible sous-marine (24) à partir d'un emplacement dans l'air, à travers une interface air/eau, et en le faisant entrer dans l'eau,
       caractérisé en ce que
       le projectile comprend en outre un avant-corps de projectile (62) et un arrière-corps de projectile (60), cet arrière-corps (60) comprenant une cavité de charge utile (66) et une charge utile contenue à l'intérieur de la cavité de charge utile (66).
EP96918101A 1995-06-07 1996-06-04 Systeme de projectile a stabilisation gyroscopique dirige contre des objets sous-marins Expired - Lifetime EP0774104B1 (fr)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
US47442795A 1995-06-07 1995-06-07
US474427 1995-06-07
PCT/US1996/008926 WO1996041114A1 (fr) 1995-06-07 1996-06-04 Systeme de projectile a stabilisation gyroscopique dirige contre des objets sous-marins

Publications (2)

Publication Number Publication Date
EP0774104A1 EP0774104A1 (fr) 1997-05-21
EP0774104B1 true EP0774104B1 (fr) 2000-11-15

Family

ID=23883489

Family Applications (1)

Application Number Title Priority Date Filing Date
EP96918101A Expired - Lifetime EP0774104B1 (fr) 1995-06-07 1996-06-04 Systeme de projectile a stabilisation gyroscopique dirige contre des objets sous-marins

Country Status (9)

Country Link
EP (1) EP0774104B1 (fr)
JP (1) JPH10501881A (fr)
KR (1) KR970705001A (fr)
AU (1) AU685027B2 (fr)
CA (1) CA2196970A1 (fr)
DE (1) DE69610968T2 (fr)
IL (1) IL120160A0 (fr)
NO (1) NO970554L (fr)
WO (1) WO1996041114A1 (fr)

Family Cites Families (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB777324A (en) * 1952-02-04 1957-06-19 Hugo Abramson Improvements in and relating to projectiles
US3282216A (en) * 1962-01-30 1966-11-01 Clifford T Calfee Nose cone and tail structures for an air vehicle
US3434425A (en) * 1967-06-30 1969-03-25 Aai Corp Underwater projectile
US4405100A (en) * 1981-02-20 1983-09-20 The United States Of America As Represented By The Secretary Of The Navy Turbulence generator for maximizing configuration tolerances of free flight ordnance
SE444983B (sv) * 1981-09-09 1986-05-20 Bofors Ab For ovningsendamal utskjutbar fenstabiliserad ammunitionsenhet
DE3314750A1 (de) * 1983-04-23 1984-10-25 L'Etat Français représenté par le Délégué Général pour l'Armement, Paris Mittel zum verbessern des abloeseverhaltens von treibkaefigsegmenten von einem wuchtgeschoss fuer die rohrwaffe
GB2251220B (en) * 1983-05-18 1993-01-27 Diehl Gmbh & Co A sea mine
DE4022462A1 (de) * 1990-07-14 1992-01-16 Diehl Gmbh & Co Luftverbringbares unterwasser-projektil

Also Published As

Publication number Publication date
AU685027B2 (en) 1998-01-08
NO970554D0 (no) 1997-02-06
EP0774104A1 (fr) 1997-05-21
DE69610968D1 (de) 2000-12-21
JPH10501881A (ja) 1998-02-17
NO970554L (no) 1997-04-01
AU6044796A (en) 1996-12-30
KR970705001A (ko) 1997-09-06
IL120160A0 (en) 1997-06-10
WO1996041114A1 (fr) 1996-12-19
CA2196970A1 (fr) 1996-12-19
DE69610968T2 (de) 2001-03-15

Similar Documents

Publication Publication Date Title
AU683799B2 (en) Aerodynamically stabilized projectile system for use against underwater objects
USH1938H1 (en) Supercavitating water-entry projectile
US8196514B2 (en) Warhead
US20070006766A1 (en) Munition device
US4597333A (en) Two-part armor-piercing projectile
US4712465A (en) Dual purpose gun barrel for spin stabilized or fin stabilized projectiles and gun launched rockets
US4612860A (en) Projectile
US5804759A (en) Hunting bullet having a telescoping flechette and comprising a sub-projectile connected to a launcher
US5092246A (en) Small arms ammunition
KR100331776B1 (ko) 소구경발사체를위한부품들이조절분리되는탄환발사장치
EP0774104B1 (fr) Systeme de projectile a stabilisation gyroscopique dirige contre des objets sous-marins
AU686954B2 (en) Full caliber projectile for use against underwater objects
US20060124021A1 (en) High velocity projectiles
US11085745B1 (en) Two stage projectile for armor piercing
JP7178419B2 (ja) 水平分散パターンを提供するための装置および方法
WO2024200907A1 (fr) Projectile sous pression
RU2415374C1 (ru) Сверхзвуковой реактивный снаряд с отделяемой головной частью
CA2495869A1 (fr) Projectiles a vitesse elevee
AU2002339235A1 (en) High velocity projectiles

Legal Events

Date Code Title Description
PUAI Public reference made under article 153(3) epc to a published international application that has entered the european phase

Free format text: ORIGINAL CODE: 0009012

AK Designated contracting states

Kind code of ref document: A1

Designated state(s): DE FR GB IT NL SE

17P Request for examination filed

Effective date: 19970528

RAP1 Party data changed (applicant data changed or rights of an application transferred)

Owner name: RAYTHEON COMPANY

RAP1 Party data changed (applicant data changed or rights of an application transferred)

Owner name: RAYTHEON COMPANY

17Q First examination report despatched

Effective date: 19990518

GRAG Despatch of communication of intention to grant

Free format text: ORIGINAL CODE: EPIDOS AGRA

GRAG Despatch of communication of intention to grant

Free format text: ORIGINAL CODE: EPIDOS AGRA

GRAH Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOS IGRA

GRAH Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOS IGRA

GRAA (expected) grant

Free format text: ORIGINAL CODE: 0009210

AK Designated contracting states

Kind code of ref document: B1

Designated state(s): DE FR GB IT NL SE

ITF It: translation for a ep patent filed
REF Corresponds to:

Ref document number: 69610968

Country of ref document: DE

Date of ref document: 20001221

ET Fr: translation filed
PLBE No opposition filed within time limit

Free format text: ORIGINAL CODE: 0009261

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: NO OPPOSITION FILED WITHIN TIME LIMIT

26N No opposition filed
REG Reference to a national code

Ref country code: GB

Ref legal event code: IF02

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: SE

Payment date: 20110613

Year of fee payment: 16

Ref country code: FR

Payment date: 20110621

Year of fee payment: 16

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: NL

Payment date: 20110621

Year of fee payment: 16

Ref country code: GB

Payment date: 20110601

Year of fee payment: 16

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: DE

Payment date: 20110601

Year of fee payment: 16

Ref country code: IT

Payment date: 20110615

Year of fee payment: 16

REG Reference to a national code

Ref country code: NL

Ref legal event code: V1

Effective date: 20130101

REG Reference to a national code

Ref country code: SE

Ref legal event code: EUG

GBPC Gb: european patent ceased through non-payment of renewal fee

Effective date: 20120604

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: SE

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20120605

Ref country code: IT

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20120604

REG Reference to a national code

Ref country code: FR

Ref legal event code: ST

Effective date: 20130228

REG Reference to a national code

Ref country code: DE

Ref legal event code: R119

Ref document number: 69610968

Country of ref document: DE

Effective date: 20130101

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: GB

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20120604

Ref country code: DE

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20130101

Ref country code: NL

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20130101

Ref country code: FR

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20120702