Patent Grant
8056481
The present invention relates in general to a controlled deceleration projectile. In particular, the present invention provides a projectile, having a nose-mounted fuze thereon, which initiates an ignition charge via an ignition shaft disposed within the projectile body at a preset distance from target impact, resulting in inflation of the projectile body with propellant gases to a level sufficient to either expand same, rupture a rupture ring, or slide the hollow projectile body rearwards relative to the ignition shaft, so as to create an annular opening between the projectile body side wall and projectile body forward end. The payload, which is preferably non-lethal, is then ejected from this annular opening, the resulting forward velocity of the expelled payload and propellant gases producing a rearward thrust on the projectile, and a concomitant deceleration thereof.
Conventional non-lethal ammunition is launched with a kinetic energy sufficiently low to effect a non-lethal result upon target impact. To enable launching of ammunition at such reduced velocities (and hence with reduced kinetic energies), it is necessary to reduce the muzzle velocity. However, when utilizing non-lethal munitions, such as grenades, there is a danger that, even with reduced muzzle velocities, the projectile body itself may have sufficient kinetic energy to severely wound or damage a human target upon impact.
Further, when utilizing non-lethal munitions, such as non-lethal grenades, against inanimate targets, such as automotive windshields, etc., there is a danger that the projectile body will have sufficient kinetic energy upon impact to penetrate the target and harm surrounding human assets. Further, by reducing muzzle velocity, recoil impulse is also reduced, which frequently causes malfunctioning of the weapon operating system and fire control when firing the non-lethal ammunition from standard weapons. In addition, conventional non-lethal munitions are not range specific, i.e., they are meant to be used for targets within a wide range from the shooter, and are not tailored to targets within specific ranges.
Frequently, such conventional non-lethal munitions fail to reach reduced velocities (and thus reduced kinetic energies) before impacting the target, when the target is at a close proximity from the shooter, or are incapable of reaching targets at longer ranges, due to reduced velocities/kinetic energies at such longer ranges. Thus, many conventional non-lethal munitions are provided with detailed guidelines concerning target ranges, to minimize the occurrence of lethal impact or ineffectiveness. However, in combat situations, adherence to such guidelines is difficult and often overlooked.
Thus, it is an object of the present invention to provide a munition capable of providing recoil impulse sufficient to cycle standard weapons, while also providing optimized non-lethal effects at all target ranges. In particular, it is an object of the present invention to provide a munition capable of achieving sufficient recoil impulse and kinetic energy to reach desired targets, while also being able to reduce the velocity of the projectile body to a non-lethal level before impact with the target, or be capable of decelerating the projectile body before impact with the target to avoid impact of the projectile body with the target altogether.
In order to achieve the object of the present invention, the present inventors earnestly endeavored to provide a projectile having a projectile body capable of expelling a payload therein before impact, and decelerating the projectile body to a non-lethal velocity before impact with the target. Accordingly, the present inventors developed a controlled deceleration projectile having an expellable payload therein. In particular, in a first embodiment of the present invention, a controlled deceleration projectile is provided comprising:
(a) a hollow projectile body having a rear end, a circumferential portion adjacent the rear end defining an interior portion, and a front edge opposite the rear end defined by the circumferential portion;
(b) an interior portion of the hollow projectile body defined by the circumferential portion and rear end of the hollow projectile body, said interior portion capable of containing a payload;
(c) a hollow ignition shaft disposed within the interior portion of the hollow projectile body, the hollow ignition shaft having a first end with an angled exhaust surface formed contiguous there with adjacent the front edge of the hollow projectile body, a second end opposite the first end, a hollow middle portion there between having ignition ports disposed there through, and ignition propellant disposed within the hollow middle portion;
(d) ignition propellant disposed within the interior portion of the hollow projectile body, at least adjacent to the ignitions ports of the hollow ignition shaft;
(e) a payload disposed within the interior portion; and
(c) a nose-mounted fuze disposed adjacent the front edge of the hollow projectile body, and in communication with the ignition propellant disposed within the hollow ignition shaft, said nose-mounted fuze having a means for initiating the ignition propellant.
In a second embodiment of the present invention, the controlled deceleration projectile of the first embodiment is provided, wherein the projectile body is comprised of aluminum, copper, brass or steel.
In a third embodiment of the present invention, the controlled deceleration projectile of the first embodiment is provided, wherein the annular opening is from about 0.005 to 0.050 inches in diameter.
In a fourth embodiment of the present invention, the controlled deceleration projectile of the first embodiment is provided, wherein the circumferential portion of the hollow projectile body has a thickness of between about 0.030 and 0.125 inches.
In a fifth embodiment of the present invention, the controlled deceleration projectile of the first embodiment is provided, wherein the hollow projectile body expands from about 0.010 to about 0.100 inches in diameter at the front edge thereof after ignition of the expulsion propellant.
In a sixth embodiment, the controlled deceleration projectile of the first embodiment above is provided, wherein the nose-mounted fuze is a point-detonating fuze or a proximity fuze.
In a seventh embodiment of the present invention, the controlled deceleration projectile of the first embodiment above is provided, further comprising a ballast material disposed within the interior portion of the hollow projectile body.
In an eighth embodiment of the present invention, the controlled deceleration projectile of the seventh embodiment above is provided, wherein the ballast material is a dense powder, such as a metal powder. For example, tungsten or iron powder may be utilized.
In a ninth embodiment of the present invention, the controlled deceleration projectile of the first embodiment is provided, wherein the thickness of the circumferential portion of the hollow projectile body tapers towards to the front end thereof. This structural aspect enables the circumferential portion to deform (i.e., expand or “burp”) at the front edge thereof.
In a tenth embodiment of the present invention, the controlled deceleration projectile of the first embodiment above is provided, wherein the payload is a non-lethal payload. For example, the payload may be a ballast material, a pyrotechnic flash-bang composition, or a crowd control agent such as tear gas, etc.
In an eleventh embodiment of the present invention, the controlled deceleration projectile of the first embodiment above is provided, further comprising a rupture ring disposed between the front edge of the hollow projectile body and the nose mounted fuze or first end of the hollow ignition shaft. In such an embodiment, the rupture ring is provided as an alternative to a deformable hollow projectile body, wherein the rupture ring is designed to rupture at a predetermined pressure. Accordingly, the rupture ring may be formed of any material capable of failing at a set pressure, such as polymeric materials, plastics, thinly formed metals, etc.
In a twelfth embodiment of the present invention, the controlled deceleration projectile of the first embodiment of the present invention is provided, further comprising a check valve disposed between the nose mounted fuze and the first end of the hollow ignition shaft. This check valve allows the ignition of the ignition propellant within the hollow ignition shaft by the nose-mounted fuze, but prevents ignited propellant and gasses resulting therefrom from flowing towards the nose-mounted fuze. Rather, the propellant gases are directed rearwards, and through the ignition ports.
In a thirteenth embodiment of the present invention, the controlled deceleration projectile of the first embodiment above is provided, further comprising:
(i) expulsion propellant disposed within the interior portion of the hollow projectile body, adjacent the ignition ports of the hollow ignition shaft; and
(ii) one or more partitions disposed within the interior portion of the hollow projectile body,
wherein the partition(s) act to physically separate the expulsion propellant from the payload.
In a fourteenth embodiment of the present invention, the controlled deceleration projectile of the first embodiment above is provided, further comprising a tethering means having a first end in connection with the nose-mounted fuze, and a second end in connection with the hollow projectile body. This tethering means, which is preferably a string or line, allows the hollow projectile body and nose mounted fuze to directly detach from one another after firing, but remain connected so as to provide an additional means of deceleration.
In a fourteenth embodiment of the present invention, the controlled deceleration projectile of the thirteenth embodiment above is provided, wherein the nose-mounted fuze is tethered to the hollow projectile body via a string or line in connection at a first end thereof with the hollow projectile body, and at a second end thereof with the nose-mounted fuze.
In a fifteenth embodiment of the present invention, the controlled deceleration projectile of the eleventh embodiment above is provided, further comprising:
(i) a rear chamber disposed within the hollow projectile body between the rear end of the hollow projectile body and the second end of the hollow ignition shaft;
(ii) a rear chamber port disposed within the hollow projectile body between the rear chamber and the second end of the hollow ignition shaft, so as to connect the hollow ignition shaft to the rear chamber;
(iii) two or more rear chamber exhaust ports, each of said exhaust ports being hollow, and extending from the rear chamber to the circumferential portion of the projectile, thereby providing a means of egress from the rear chamber to the exterior of the projectile.
In a sixteenth embodiment of the present invention, the controlled deceleration projectile of the fifteenth embodiment above is provided, further comprising:
(i) a check valve disposed within or adjacent to the rear chamber port.
In a seventeenth embodiment of the present invention, the controlled deceleration projectile of the fifteenth embodiment above is provided, further comprising:
(i) ballast propellant disposed within the rear chamber;
(ii) rear ballast disposed in each of said rear chamber exhaust ports; and
(ii) a rear piston disposed in each of said rear chamber exhaust ports, between the rear ballast and the rear chamber.
In an eighteenth embodiment of the present invention, the controlled deceleration projectile of the fifteenth embodiment above is provided, further comprising:
(i) solid rocket propellant disposed within the rear chamber.
In a nineteenth embodiment of the present invention, a controlled deceleration projectile is provided comprising:
(a) a hollow projectile body having a rear end, a circumferential portion adjacent the rear end defining an interior portion, and a front edge opposite the rear end defined by the circumferential portion;
(b) an interior portion of the hollow projectile body defined by the circumferential portion and rear end of the hollow projectile body, said interior portion capable of containing a payload;
(c) a hollow ignition shaft disposed within the interior portion of the hollow projectile body, the hollow ignition shaft having a first end with an angled exhaust surface formed contiguous there with adjacent the front edge of the hollow projectile body, a second end opposite the first end having a body stop (i.e., a projection extending therefrom) formed therein, a hollow middle portion there between having ignition ports disposed there through, and ignition propellant disposed within the hollow middle portion;
(d) a shear ring disposed between the hollow projectile body and hollow ignition shaft, so as to rigidly secure the hollow projectile body to the hollow ignition shaft;
(e) a payload disposed within the interior portion; and
(c) a nose-mounted fuze disposed adjacent the front edge of the hollow projectile body, and in communication with the ignition propellant disposed within the hollow ignition shaft, said nose-mounted fuze having a means for initiating the ignition propellant.
In the above embodiment, the shear ring is formed of a material designed to fail (i.e., break, crack, etc.) at a certain pressure or force. Upon failure of the shear ring, the hollow projectile body is free to slide rearward relative to the hollow ignition shaft, until reaching the body stop. Accordingly, there is no need to deform the hollow projectile body to provide an expulsion point for the payload.
When the controlled deceleration projectile of the present invention is fired, the nose-mounted fuze ignites the ignition propellant when the projectile travels to within a preset distance from a target, causing the ignition propellant to form propellant gases within the interior portion thereof. These propellant gases thereby create high pressure within the interior portion of the hollow projectile body. In one embodiment, this high pressure causes expansion of the hollow projectile body at least at and adjacent to the front edge thereof sufficient to create an annular opening between the front edge of the projectile body and the nose-mounted fuze.
In one alternative embodiment, the high pressure within the interior portion causes rupturing of a rupture ring, thereby forming an annular opening at the point of the rupture ring. In another alternative embodiment, the high pressure induced by the propellant gases causes shearing of a shear ring holding the hollow projectile body to the hollow ignition shaft, allowing the projectile body to slide rearwards, thereby creating an annular opening adjacent the front edge of the projectile body. In each embodiment, the payload, as well as the propellant gases, is then expelled through the annular opening, causing deceleration of the hollow projectile body by the reverse thrust created by the propellant gases and payload.
In a further alternative embodiment, as described above in the sixteenth through eighteenth embodiments above, further means of reverse thrust are provided. In particular, in one embodiment, ballast is expelled from rear chamber exhaust ports by the ignition of ballast propellant disposed within a rear chamber. This ballast propellant is initiated by the ignition propellant, thereby eliminating the need for an additional source of initiation. In an alternative embodiment, rather than expelling ballast, solid rocket propellant is disposed within the rear chamber, and when initiated by the ignition propellant disposed within the hollow ignition shaft, a reverse thrust is provided via the rear chamber exhaust ports by the expulsion of hot solid rocket propellant gases there from.
As illustrated in
It has been found that the optimum thickness of the circumferential portion 7 of the hollow projectile body 3, when formed of aluminum, for enabling proper expansion thereof during firing, is between about 0.030 and 0.125 inches. This circumferential portion 7 thickness allows the hollow projectile body 3 to expand from about 0.010 to about 0.40 inches in diameter at the front edge 11 thereof after ignition of the expulsion propellant 38. In an alternative embodiment, the thickness of the circumferential portion 7 may be tapered toward the front edge 11 of the hollow projectile body 3, which may be desired in some applications to tailor the size of the annular opening 45 created between the front edge 11 and nose-mounted fuze 41 upon ignition of the expulsion propellant 38, as illustrated in
The hollow ignition shaft 27, which contains ignition propellant 29, is disposed within the interior portion 9, and has a first end 31 adjacent the ignition shaft port 25. A second end 33 of the hollow ignition shaft 27 is disposed opposite the first end 31, and a hollow middle portion 35 is disposed there between. Ignition ports 37 are disposed through said hollow middle portion 35. As illustrated in
During testing, it was found that the payload 39 was frequently expelled in an uneven and uncontrolled manner, causing the projectile to decelerate in unexpected ways. For example, the majority of the payload 39 was sometimes expelled from one side of the projectile 1, causing the projectile to be forced in a direction relatively perpendicular to its flight path. In other instances, the payload 39 was observed to shoot straight outwards from the annular opening 45, rather than towards the target as desired. The present inventors unexpectedly discovered that integrating an angled exhaust surface 24 into to the hollow ignition shaft 27 directed the payload 39 towards the target upon expulsion from the projectile as desired. Further, this directed expulsion of the payload 39 was found to contribute to a more controlled expulsion, and hence a more controlled deceleration of the projectile 1.
In certain embodiments, such as illustrated in
A nose-mounted fuze 41, which may be a proximity fuze or point-detonation fuze, is disposed adjacent the front edge 11 of the hollow projectile body 3, and is in communication with the ignition propellant 29 disposed within the hollow ignition shaft 27, so as to be able to ignite/initiate same. Thus, the nose-mounted fuze 41 has a conventional means for initiating the ignition propellant 29, such as a primer assembly, electrical initiation means, etc.
Further, as mentioned above, also contained within the interior payload cup cavity 19 is the payload 39, which generally is a powder or aggregate material, or a pyrotechnic, but is not limited thereto. Preferably, the payload is a non-lethal payload, including for example a dense powder, such as a metal powder, but may be any powder that is non-lethal upon impact with the target. Alternatively, the non-lethal payload may be comprised of a pyrotechnic flash-bang material, a riot control agent, or a marking dye. In addition, the interior payload cup cavity 19 may further comprise a ballast material, such as a dense powder, or the payload 39 may act itself as the ballast material.
It is preferable that the nose-mounted fuze 41 not impact the target during firing, as the nose-mounted fuze 41 may itself be lethal upon impact. Thus, the nose-mounted fuze 41 is preferably affixed to the hollow projectile body 3, to allow the deceleration process to act upon the nose-mounted fuze 41, as well as the hollow projectile body 3. As an alternative to direct affixation, the nose-mounted fuze 41 may be in connection with the hollow projectile body 3 via a tethering means. For example, as illustrated in
As illustrated in
The high internal pressure built up within the internal portion 9 causes the propellant gases to expel the payload 39 through the annular opening 45. This expulsion of pressurized gases, payload 39 and, alternatively, ballast material, creates a reverse thrust on the hollow projectile body 3. This reverse thrust decelerates the hollow projectile body 3, thereby slowing the velocity of the hollow projectile body 3 to a non-lethal velocity upon impact with the target, or more desirable, avoids impact of the hollow projectile body 3 with the target altogether.
During testing, it was found that different materials used to fabricate the hollow projectile body require different amounts of internal pressure to “burp” the projectile. In particular, the pressure needed to adequately expand the hollow projectile body to create a desirable annular opening varies based on material used, and dimensions (such as thickness) of the material. Importantly, after expansion and expulsion of the propellant gases and the non-lethal payload, the internal pressure is rapidly reduced. Thus, undesirable fragmentation of the hollow projectile body is avoided.
In an alternative embodiment, as illustrated in
In a further preferred embodiment of the present invention, as illustrated in
In a further preferred embodiment, instead of providing a deformable hollow projectile body 3 (which can “burp”) as illustrated in
As illustrated in
The present inventors have found through experimental testing that some payloads do not have sufficient mass to provide a counterthrust strong enough to reduce velocity of the projectile to a non-lethal level. To address this issue, in a preferred embodiment of the present invention, as illustrated in
In such an embodiment, two or more rear chamber exhaust ports 65 are disposed within the projectile 1, extending from the rear chamber 63 to the circumferential portion 7 of the projectile body 3, so as to provide an opening from the rear chamber 63 to the exterior of the projectile. The rear ballast 67 is disposed within each of the chamber exhaust ports 65. This rear ballast 67 can be comprised of any suitable material to provide a rearward force upon being expelled. For example, metallic powder, such as tungsten or iron powder, may be used.
A rear piston 69 is disposed adjacent the rear ballast 67, so as to physically separate the rear ballast 67 from propellant 71 or 73, and provide an interface between expanding propellant gases and the ballast 67. As shown in
As illustrated in
In the embodiments of the present invention illustrated in
Although specific embodiments of the present invention have been disclosed herein, those having ordinary skill in the art will understand that changes can be made to the specific embodiments without departing from the spirit and scope of the invention. The scope of the invention is not to be restricted, therefore, to the specific embodiments. Furthermore, it is intended that the appended claims cover any and all such applications, modifications, and embodiments within the scope of the present invention.
This application is a continuation-in-part application of pending U.S. patent application Ser. No. 11/717,964, filed Mar. 14, 2007, the contents of which are incorporated herein by reference.
| Number | Name | Date | Kind |
|---|---|---|---|
| 1042176 | Voeller | Oct 1912 | A |
| 4294172 | Rauschert et al. | Oct 1981 | A |
| 4333402 | Landstrom et al. | Jun 1982 | A |
| 4446794 | Simmons | May 1984 | A |
| 4892038 | Lubbers | Jan 1990 | A |
| 6523478 | Gonzalez et al. | Feb 2003 | B1 |
| 6688032 | Gonzalez et al. | Feb 2004 | B1 |
| Number | Date | Country | |
|---|---|---|---|
| 20110252995 A1 | Oct 2011 | US |
| Number | Date | Country | |
|---|---|---|---|
| Parent | 11717964 | Mar 2007 | US |
| Child | 12434793 | US |
