Abstract: An energetic material comprises an energetic crystalline material substantially coated in an energetic plasticiser material.

Abstract: A retaining clip for the retention of a fin-stabilised projectile in a desired position in a barrel at the rear breech end of a launcher, the clip comprising a generally cylindrical body portion having: engagement means for engaging with the launcher at the said rear breech end, said engagement means extending at least part of the way around the said cylindrical body portion and adapted to prevent forward movement of the clip when positioned in the launcher, a substantially central axial aperture for allowing access for firing the projectile a plurality of radially and axially extending grooves for engaging the fins of the projectile when the clip is fitted to the projectile, each of said grooves having facing walls defining the groove therebetween, and the grooves adapted to divide the cylindrical body portion into a plurality of connected segments locating means positioned on at least one of said walls of at least one of said grooves and intruding into or above the groove, said locating means adapted to

Abstract: An apparatus for the initiation of a propellant comprises a combustion chamber such as barrel 6, a charge of propellant 5 in the chamber and means for igniting the propellant of the charge by microwave heating comprising a source of microwave radiation 11, a microwave transparent window 9 in a wall of the said chamber and, means for applying microwaves from the said source into the said chamber via the said window. The apparatus may be used in a gun as shown or in a rocket motor.

Abstract: A safety and arming unit for a round of ammunition, comprising one or more acceleration sensors for detecting when the acceleration of the ammunition reaches at least two different predetermined linear acceleration values; timer means for measuring the time interval between the detection of two of the predetermined linear acceleration values, means for electronically comparing the said measured time interval with a range of predetermined and pre-set time intervals representing satisfactory firing for the round of ammunition, and means for producing an electronic signal when the said measured time interval falls within the range of predetermined and pre-set time intervals, which signal operates to arm the ammunition ready for detonation.

Abstract: An aircraft cargo container adapted to provide blast attenuation in the event of an explosion within the container comprises panels (2,3) of blast resistant material joined together by joint means (4,5) which are adapted to provide a relatively rigid joint udner normal handling conditions, but which provide a relatively flexible hinged joint capable of transmitting tensile loads between the panels under blast conditions. Additional reinforcement may be provided by a lattice of high tensile strength straps 6 substantially surrounding the container.

Abstract: A pipe and method of manufacture of the pipe are described. The pipe comprises a core of helically wound steel strip embedded in a plastics material matrix and lined with inner and outer linings of filament wound fiber reinforced plastics material.

Abstract: A rubbery polymer is produced in situ in a cast double base propellant composition.

Abstract: A fragmentation grenade comprises a quantity of high explosive (11) contained within a casing (12, 13) and means (29) for detonating the high explosive (11) so as to cause the casing (12, 13) to disintegrate into a plurality of high velocity fragments (13). The high explosive (11) and the casing (12, 13) are so configured that the fragments (13) are preferentially projected in one or more particular directions relative to the axis (X--X) of the casing (12, 13), and the grenade is provided with a self-righting mechanism (22), whereby the axis can automatically be placed in a desired orientation.

Abstract: Solid propellant combustion apparatus such as a rocket motor, incorporating a combustion termination valve for providing two combustion phases from a single propellant charge system, the valve comprising a valve body (50) surrounding an opening (52) in the pressure vessel of the combustion apparatus, a valve member (60), retaining means (65) for releasably retaining said valve member in sealing engagement with the valve body whereby to hold the valve closed during a first combustion phase, valve opening means (68) operable on command for releasing said retaining means whereby to cause the valve member (61) to disengage from the valve body thereby opening the valve to terminate said first combustion phase by rapid de-pressurisation of the combustion gases through said opening, and valve closure means (72) operable on command to move the valve member (61) into sealing engagement with the valve body whereby to close the valve prior to re-ignition of the propellant charge for a second combustion phase.

Abstract: A recoil system for field-type guns automatically adjusts the recoil distance of the barrel according to the angle of elevation of the gun barrel relative to the ground. The system includes a recoil cylinder in fixed relationship to the gun barrel and a piston rod operably connected to a two-art piston valve within the cylinder. The rotational position of one of the valve parts is controlled by the angular position of the piston rod about its axis and the rotation position of the second valve part is controlled by its axial piston within the recoil cylinder bore. Fluid flow orifi are defined between the first and second valve part, the area of the orifi being determined by the rotational positions of the two valve parts relative to each other. As barrel elevation is increased, the piston rod is rotated via a camming device which is itself moved by a tooth riding in a non-axial and non-linear slot in the camming device.

Abstract: The method of joining a coupling member to a pipe end is described. The method is particularly concerned with providing a coupling member on the end of a pipe of composite construction formed from a plurality of helically wound reinforcement strips of steel. The method comprises the steps of forming at least one generally circumferentially directed groove in the outer surface of the pipe wall adjacent the end of the pipe to a depth extending into the reinforcement core, providing a coupling member adapted to fit the end of the pipe overlapping the region of the groove or groove, providing key means to extend between said sleeve and said groove in said pipe, providing a curable resin in the joint area between said pipe and said sleeve and curing said resin to bond said coupling member to said pipe end. The resultant coupling is of increased efficiency in providing both an adhesively bonded and mechanically coupled joint.

Abstract: A pipe and method of manufacture of the pipe are described. The pipe comprises a core of helically wound steel strip embedded in a plastics material matrix and lined with inner and outer linings of filament wound fiber reinforced plastics material.

Abstract: A clip for the retention of a round of ammunition in a desired position in a barrel is described, the clip being manufactured from a plastics material and comprising a generally cylindrical body portion; the body portion having a plurality of generally radially and axially directed grooves therein, said grooves being adapted to engage the tail fins of an associated round of ammunition; engagement means extending at least part of the way around said body portion, said engagement means having a greater diameter than that of the body portion and being adapted to engage with a recess at the breech-end of an associated gun barrel to prevent forward movement; and a substantially central aperture to allow access to the propellant charge of the associated round of ammunition.

Abstract: An energetic composition comprising the following components in the following relative proportions:Component A: from 5% to 25% by weight of a polymeric binder;Component B: from 65% to 90% by weight of a highly energetic filler comprising at least one heteroalicyclic nitramine compound; andComponent C: from 1% to 15% by weight of a plasticiser which comprises at least one nitroaromatic compound; the percentages by weight of Components A, B and C adding to 100%.

Abstract: Nitrocellulose propellant compositions are provided comprising as ballistic modifier a copper II complex of a C.sub.6 -C.sub.12 chain aliphatic carboxylic acid, advantageously in conjunction with one or more conventional ballistic modifiers for example, lead or copper compounds such as lead stearate, lead acetophthalate, lead .beta.-resorcylate and basic copper salicylate. The preferred complex is copper II caproate. The propellant compositions exhibit good quality plateau or mesa burning over a useful pressure range for a wide range of energy and burning rates. The copper II complexes are especially advantageous in cast double base propellants particularly because their solubility in the organic solvents used facilitates their incorporation into these compositions.

Abstract: A cargo or luggage container adapted for use on an aircraft which container has strengthened faces made from and/or reinforced by blast resistant material and at least one weakened Face made from a material relatively unresistant to blast, the strengthened faces forming in use at least the top and bottom faces of the container whereby blast From a detonating or exploding device within the container is directed out of the container preferentially by failure of the weakened face or faces. There may be one weakened face which in use is arranged to be the face nearest to an adjacent region of the aircraft hull. Alternatively, or in addition there may be two weakened faces on opposite sides of the container which in use are arranged to be the sides facing fore and aft with respect to the longitudinal axis of the aircraft.

Abstract: Nitrocellulose propellant compositions are provided comprising zinc oxide as ballistic modifier, advantageously in conjunction with one or more conventional ballistic modifiers for example, lead or copper compounds such as lead stearate, lead acetophthalate, lead B-resorcylate and basic copper salicylate. The propellant compositions exhibit good quality plateau burning over a useful pressure range for a wide range of burning rates.

Abstract: In the event of sudden depressurization caused by an explosion in an aircraft cargo compartment, a blast attenuation valve is provided in the aircraft's air channels to form a barrier to the passage of air between the cargo compartment and passenger cabin. The valve contains a mixture of compressible bodies through which air can normally permeate. After an explosion, the bodies block and blast wave by compressing together due to the substantial increase in pressure.

Abstract: A thermal insulator for a rocket motor body comprises a member adapted to be fitted as a sleeve on the outer surface of the body the member comprising a composite of cork having on its outer surface a layer of fibre reinforced polymeric material wherein a substantial proportion of the fibre reinforcement comprises fibres of low-conducting material.

Abstract: A sabot for use with a spin stabilized projectile comprises a closed front end portion having lines or strips of weakness running along sides of the sabot which meet at a front end surface of the sabot, thereby providing a continuously extending line or region of weakness across the front end surface.Preferably, the sabot front end portion has at least three, desirably four or more, lines or strips of weakness running along the length of the front end portion. These lines or strips may meet at an intersection of lines or strips at the front end surface, but they preferably meet at a front end membrane region.Discarding sabots according to the present invention are especially suitable for use with tubular projectiles. These projectiles may for example be used in training ammunition rounds which are suitable for firing from the UK 30 mm RARDEN (UK Registered Trade Mark) Gun.