Patent Application
20100251920
The present invention relates to a composite motor case and, more particularly, to a case munitions motor that is constructed to structurally degrade when exposed to an abnormally high temperature below the auto-ignition temperature of an encased propellant.
The destructive capability of explosive munitions is intended to be directed against an aggressor. However, this same lethal and/or damaging potential can result in the loss of manpower and capability of our own forces in the event that the munitions is mishandled, subject to fuel fire and/or cook-off conditions, or projectile and/or shock scenarios. Furthermore, the propagation of the damaging reaction from the initiating munitions to adjacent material and munitions can greatly enhance the severity of damage.
Various munitions motor cases provided with fire exposure safety features are known in the patented prior art.
U.S. Pat. No. 3,665,857 discloses a rocket motor case provided with a safety ejection plug which is sealed to the case by a sealant having a melting temperature lower than that of the auto-ignition temperature of the encased projectile charge, to enable the plug to be ejected from the case for pressure release when exposed to dangerously high temperature.
U.S. Pat. No. 4,494,373 discloses a rocket motor case having a cook-off safety feature, wherein selected portions of the case are structurally strengthened and thermally protected while other selected stress points in the case are left unprotected, thereby causing the case to rupture at the unprotected points for pressure venting if the case is exposed to abnormally high temperatures.
U.S. Pat. No. 5,170,007 discloses a roll-bonded, insensitive munitions motor case and method of production. The motor case comprises a sheet of fiber reinforced thermoplastic, thermoset or other suitable material rolled to form a case with a tubular configuration having at least one layer of material, and a coating of adhesive on at least part of the sheet for bonding the sheet to itself for maintaining the tubular configuration. The adhesive has a bond-strength breakdown temperature which is below the auto-ignition temperature of the housed propellant, thereby enabling the case to separate and un-roll when the breakdown temperature is reached to preclude dangerous propellant pressurization within the case. The method of production includes the steps of applying an adhesive to the sheet, rolling the sheet around a cylindrical tool to form a tubular case having at least one layer, and curing the case. Preferably the case is cured while on a tool which has a coefficient of thermal expansion which is greater than that of the sheet to ease removal of the case upon cooling. The casing sheet may be rolled such that there is a longitudinal section which has one less layer of material than the remainder of the case, whereby the case would fail along that longitudinal section if over-pressurization should occur.
U.S. Pat. No. 5,976,293 discloses a dimensionally stable Insensitive Munitions case for supporting and controllably combusting propellant and/or gas-generating combustion gases. The case is permeable to the combustion gases produced at temperatures above ambient temperature but below the auto-ignition temperature of the propellant and/or gas-generating supported therein. The case is dimensionally stable without the use of metals, alloys or the like that yield shrapnel upon explosion in the barrel section of the case.
U.S. Pat. No. 6,038,979 describes a process and material for forming a warhead casing. The material consists of tightly wound carbon fiber bonded by a room temperature curing resin. The process eases and speeds manufacturing and eliminates the need to do inside threading as the interior of the casing can be totally formed during winding of the carbon thread.
U.S. Pat. No. 6,386,110 provides a deforming charge assembly which has co-axially arranged inner and outer cylinders formed from carbon fiber. Each cylinder has a first layer of circumferentially wound carbon fiber, a second layer of unidirectional carbon fiber sheet and a plurality of layers of carbon fibers circumferentially wrapped around the second layer. Detonation barrier members are disposed between the inner and outer cylinders and bolted to the cylinders on the wrapping machine.
While the prior art motor cases enable some protection against dangerous propellant pressurization, they can be difficult and expensive to manufacture, and often do not provide adequate venting to insure safe release of the propellant energy.
Therefore, a need has been created for an economical, reliable and tailorable munitions case which provides the necessary structural integrity under normal conditions essential to its primary mission, while allowing structural degradation when the case reaches a predetermined, abnormal elevated temperature which is below the auto-ignition temperature of the encased propellant, thereby precluding dangerous propellant pressurization within the case. The motor case and method of production of the present invention meet this need.
Accordingly, a primary object of the present invention is to provide a tailored, economical and reliable insensitive munitions motor case that will lose its structural integrity upon reaching a predetermined temperature which is below the auto-ignition temperature of the housed propellant, thereby rendering the case incapable of sustaining sufficient internal pressure to destructively detonate the case.
Another object of the invention is to provide a method for manufacturing such an insensitive munitions motor case.
In accordance with the present invention there is provided an insensitive munitions (IM) casing, such as a motor case, for housing a propellant charge, said casing comprising,
a reinforcing fiber, tape or sheet of composite material wound, wrapped or rolled respectively, to form a case having a number of composite layers,
said reinforcing fiber, tape or sheet composite material being coated with adhesive bonding material for bonding the reinforcing fiber, tape or sheet to itself for constructing and maintaining the configuration of the composite case,
said adhesive having a bond-strength breakdown temperature which is below the auto-ignition temperature of the housed propellant,
characterized in that at least some of the wound, wrapped or rolled composite layers are discontinuous, thereby enabling the discontinuous sections to lose their strength and separate once the bond strength breakdown temperature of the adhesive is reached causing the case to fail at the discontinuous interface thereby releasing internal pressure in the case and preventing dangerous propellant pressurization within the case.
Another aspect of the present invention there is provided an insensitive munitions (IM) casing wherein the at least some of the reinforcing fiber, tape or sheet composite layer that is discontinuous overlaps, thereby bonding the composite layer to itself and prevent separation of the discontinuous layers below the bond strength breakdown temperature of the adhesive due to the overlap.
Yet another aspect of the present invention is to provide an insensitive munitions (IM) casing wherein the interface of the discontinuous sections is covered with a patch of adhesive coated reinforcing material, said adhesive having a bond strength breakdown temperature below the auto-ignition temperature of the housed propellant, said patch bonds the discontinuous sections and prevents separation of the discontinuous layers below the bond strength breakdown temperature of the adhesive.
A still further aspect of the invention is to provide an efficient and economical method of manufacturing a composite IM motor case from reinforcing fiber, tape or sheet material, coated with an adhesive having a bond strength breakdown temperature below the auto-ignition temperature of a housed propellant, comprising, winding, wrapping or rolling the adhesive coated reinforcing fiber, tape or sheet material around a mandrel to form at least one layer of material, making at least part of some of the layers discontinuous, and curing the case.
Yet another object of the invention is to provide a method of manufacturing a composite IM motor case as described above, where the discontinuous layers either overlap or are covered with an adhesive coated composite patch material.
The method may include providing a gap between the mandrel and the case after cool-down to facilitate easy removal of the case from the mandrel. The term fiber in the specification and claims is used to denote a fiber which itself comprises one or more filaments and may have various forms, such as braided fibers or woven fibers. The term tape in the specification and claims is used to denote a flat strip of made from fibers as is understood in the art.
Examples of appropriate reinforcing material from which the fiber, tape or sheet can be produced include, but are not limited to, graphite, fiberglass, silica, polyaramide, quartz and the like. Preferably, the fibers are pre-preg fibers of thermoplastic or thermosetting adhesives.
The present invention has some of the following advantages:
1. By virtue of the pre-selected discontinuity of the composite layered material it readily enables venting of a munitions casing to release excessive internal pressure prior to any contained propellant reaching the auto-ignition temperature.
2. by using filament winding, the casing can be easily made in a variety of forms—i.e. not limited to only a tubular form, as when making the casings from sheets; and
3. The level and location of the discontinuity can be controlled to meet different requirements for casings. This is accomplished by varying the length and place of the overlap or the size of the patch which will depend on the tensile strength of the fiber.
The invention may be more clearly understood upon reading of the following detailed description of non-limiting exemplary embodiments thereof, with reference to the following drawings, in which:
Referring first to
After the casing is completely wound it is cured to harden the reinforcing tapes, overlaps and patches. It is understood that not all the windings have to be cut and made discontinuous, just enough of them so that when the adhesive of the overlap portion or patch softens or melts at their breakdown temperature below the auto-ignition temperature of a housed propellant the loss of adhesion between tapes and overlap or patch allows the tape sections to separate and enable release of the pressure in the case before reaching the auto-ignition temperature.
Preferably, a suitable length of overlap and suitable adhesive is chosen so that the overlapping portion has strength close to that of the uncut filament.
Thus, the casing is as strong under normal conditions as it would otherwise be without the discontinuities. The munitions can be put in the casing prior or after curing.
The shape of the casing is defined by a shaped body or mandrel upon which the filament or tape is wound. This shape may be cylindrical, conical or any variety of shapes.
In prior art casings, the fibers, tapes or sheets are typically continuous, with only the terminal end overlapping. In contrast, because the IM casing of the present invention has multiple discontinuities it allows much greater flexibility in design and control of the parameters of the IM.
It should be understood that the above description is merely exemplary and that there are various embodiments of the present invention that may be devised.
| Number | Date | Country | Kind |
|---|---|---|---|
| 186966 | Oct 2007 | IL | national |
| Filing Document | Filing Date | Country | Kind | 371c Date |
|---|---|---|---|---|
| PCT/IL2008/001400 | 10/23/2008 | WO | 00 | 4/28/2010 |
