EP0774104B1

EP0774104B1 - Gyroscopically stabilized projectile system for use against underwater objects

Info

Publication number: EP0774104B1
Application number: EP96918101A
Authority: EP
Inventors: Jeffrey A. Brown; Reed Copsey; Marshall Tulin; Roy Kline
Original assignee: Raytheon Co
Current assignee: Raytheon Co
Priority date: 1995-06-07
Filing date: 1996-06-04
Publication date: 2000-11-15
Anticipated expiration: 2016-06-04
Also published as: NO970554D0; AU685027B2; NO970554L; CA2196970A1; WO1996041114A1; IL120160A0; EP0774104A1; DE69610968D1; DE69610968T2; AU6044796A; KR970705001A; JPH10501881A

Description

BACKGROUND OF THE INVENTION

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. In the most common approach, 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. First, the trajectory of the projectile can be radically altered when it encounters the interface between the air and the water (i.e., the surface of the water). At a shallow angle of incidence to the water, the projectile may not enter the water at all, and instead may skip away. At a higher angle of incidence to the water, 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. Third, the lateral hydrodynamic forces on the projectile can cause it to tumble, further limiting its range and effectiveness.

For these reasons, projectiles are seldom fired from air against targets submerged in water. If conventional projectiles are fired from air toward a target submerged in water, they are largely ineffective. Instead, self-propelled devices such as torpedoes are used, and even in this case the torpedo is usually dropped into the water before its propulsion is started.

There are applications where a projectile that can be fired against underwater targets from the air would be useful. For example, a standard defense against amphibious military operations is underwater mines placed at moderate depths in near-shore landing areas. Such mines are now removed by specially trained swimmers at considerable risk or robotic devices which have significant constraints in their operation. An alternative approach would be to fire a projectile at the underwater mine from the air, as from a helicopter. Projectiles are far less costly than self-propelled devices in such applications, and could be made of different sizes and types for firing from a range of weapons of both small and large bores.

Thus, there is a need for a projectile that can be fired from air against underwater targets. 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.

SUMMARY OF THE INVENTION

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.

In accordance with the invention, 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. There is also a means for stabilizing the projectile body against lateral instability joined to the projectile body.

With this projectile, 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.

In a preferred embodiment, 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.

As used herein, a "projectile" is an object that is propelled by an external force, and which has no capacity for self propulsion. Thus, in this use, 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. For example, 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.

Because of its varying diameters along the length of the projectile, 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. Other features and advantages of the present invention will be apparent from the following more detailed description of the preferred embodiment, taken in conjunction with the accompanying drawings, which illustrate, by way of example, the principles of the invention.

BRIEF DESCRIPTION OF THE DRAWINGS

Figure 1 is a schematic drawing of a series of projectiles being fired from air toward a target submerged in the water;

Figure 2 is a side elevational view of one embodiment of the projectile;

Figure 3 is a forward-end elevational view of the projectile of Figure 2;

Figure 4 is a sectional view of the projectile of Figures 2 and 3, taken generally along line 4-4 of Figure 3;

Figure 5 is a schematic detail of Figure 2, illustrating the projectile afterbody;

Figure 6 is a detail of Figure 2, illustrating the stinger head;

Figure 7 is a schematic view of the projectile as it travels on a straight trajectory through water;

Figure 8 is a schematic view similar to that of Figure 7, except that the projectile has experienced a lateral instability;

Figure 9 is a schematic view of a projectile with a sabot;

Figure 10 is a side elevational view of a second embodiment of the projectile;

Figure 11 is a detail of Figure 10, illustrating an alternative embodiment of the stinger head;

Figure 12 is a side elevational view of a third embodiment of the projectile; and

Figure 13 is a block flow diagram of a method for damaging underwater targets.

DETAILED DESCRIPTION OF THE INVENTION

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, and 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. As used herein, "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 majority of the length of the projectile 50 is a projectile body 58. 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. In the projectile body 58, 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. To promote fragmentation of the projectile body 58 upon impact with the target 24 and subsequent dispersal of the contents of the payload cavity 66, 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. In this embodiment, 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 µm (16 microinches). Rearwardly of the forward face 80, 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. In the illustrated preferred embodiment, 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 µm (16 microinches) in order to achieve the desired boundary layer dimension during the travel of the projectile through the water.

As the projectile 50 passes through the water at a high velocity, 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. Along the sides 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. Thus, only 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.

Nevertheless, there may be lateral forces applied to the projectile 50 as it enters the water at the air-water interface 28 or as it travels through the water. In normal movement of the projectile 50, its cylindrical axis 56 rotates about its trajectory 88 to gyroscopically stabilize the projectile on that trajectory. When lateral instability occurs in the absence of a lateral stabilizing means such as discussed next, the rearward end 54 moves laterally relative to the forward end 52. The side of the projectile would contact the wall of the cavitation void 30, wetting the side of the projectile. In this event, a tumbling motion of the projectile 50 would be induced, leading to increased water drag, collapse of the cavitation void 30, and a rapid slowing of the projectile 50.

To counteract lateral instability, a means for stabilizing the projectile against lateral instability is provided on the projectile body 58. As its stabilization means, 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. Initially upon leaving the gun 22, the sabot 38 remains in contact with the projectile 50, see projectile 36 of Figure 1. After a brief time, 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. For smaller values of L/D, the restoring force moment arm is insufficient to counteract lateral instability and there is insufficient mass in the projectile for satisfactory penetration. For larger values of L/D, the projectile becomes difficult to stabilize gyroscopically and cannot be accommodated in conventional gun mechanisms. By comparison, conventional fired projectiles have L/D ratios of about 2-3.

Various modifications may be made to the projectile, as shown in Figures 10-12. The features of projectiles having these modifications are otherwise the same as those previously described for the projectile 50, and those descriptions are incorporated here. The features may be used in various combinations as may be appropriate.

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.

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).)

Although a particular embodiment of the invention has been described in detail for purposes of illustration, various modifications and enhancements may be made without departing from the scope of the invention as defined by the appended claims.

Claims

A projectile system comprising a generally cylindrically symmetric projectile (50) with a projectile forward end (52) and a projectile rearward end (54), the projectile having:

a stinger head (74) at the projectile forward end (76), the stinger head (74) including

a stinger nose (78) having a nose maximum diameter,

a stinger body (82) having a stinger body forward end joined to a rearward end of the stinger nose (78), the stinger body including

a stinger nose support (84) having a nose support diameter, and

a flow separation groove (86) between the stinger nose support (84) and the stinger nose (78), the flow separation groove (86) having a groove diameter less than the nose maximum diameter;

a generally cylindrically symmetric projectile body (58) joined to the stinger head, the projectile body (58) having

a projectile afterbody (60) having a projectile afterbody diameter greater than the nose maximum diameter, and

a projectile forebody (62) joined to the stinger nose support at a forward end and to the projectile afterbody at a rearward end (64); and

means (90) for stabilizing the projectile against lateral instability, the means for stabilizing being joined to the projectile body (58)

characterised in that

said projectile afterbody further comprises

a payload cavity (66), and

a payload contained within the payload cavity (66).
The projectile system of claim 1, wherein the stinger nose (78) comprises a blunt forward face (80) or a conical forward face.
The projectile system of claim 1, wherein the stinger nose (78) comprises

a stinger nose forward region having a stinger nose forward region maximum diameter,

a stinger nose rearward region adjacent to the flow separation groove (86), the stinger nose rearward region having a stinger nose rearward region diameter less than the stinger nose forward region maximum diameter.
The projectile system of claim 1, wherein the flow separation groove (86) comprises
a forwardly facing separation groove shoulder between the stinger nose (78) and the stinger nose support (84).
The projectile system of claim 1, wherein the projectile afterbody comprises

a cylindrical central region, and

a plurality of grooves (68) in the central region.
The projectile system of claim 1, wherein the means for stabilizing comprises
a forwardly facing stabilization shoulder (90) positioned between the projectile afterbody (60) and the projectile forebody (62) region.
The projectile system of claim 6, wherein the means (90) for stabilizing further comprises
a radially flared enlargement on the projectile afterbody (60) at the projectile rearward end (64).
The projectile system of claim 1, wherein the stinger nose (78) has a surface finish of no greater than about 406 µm (16 microinches).
The projectile system of claim 1, wherein the stinger head (74) is made from a material selected from the group consisting of steel and tungsten carbide.
The projectile system of claim 1, further comprising
a discardable sabot (34) affixed around the projectile (50).
A method for damaging an underwater target (24), comprising the steps of

providing a projectile system including a projectile (50) comprising

a generally cylindrically symmetric projectile body (58) with a projectile body forward end (62) and a projectile body rearward end (60),

means for forming a cavitation void (30) around the projectile body (58) when the projectile body (58) is passed through water, the means for forming being located at the projectile body forward end (62), and

means (90) for stabilizing the projectile body (58) against lateral instability, the means (90) for stabilizing being joined to the projectile body (58); and

propelling the projectile (50) toward an underwater target (24) from a location in air, through an air/water interface, and into water,

characterised in that
the projectile further comprises a projectile forebody (62) and a projectile afterbody (60), wherein said afterbody (60) comprises a payload cavity (66) and a payload contained within the payload cavity (66).