Abstract: The invention is directed to a solid, pyrotechnic composition as a base-bleed composition for reducing the base-drag of non-self-propelled projectiles. The composition comprises a oxygenated hydrocarbon component and an oxidizing agent component.

Abstract: An extendible probe projectile and an extendible probe assembly therefor, in which the extendible probe reduces drag on the projectile in its extended position and is moved to its extended locked drag-reducing position by ram air action which is converted into a forwardly acting force on the probe during forward motion of the projectile.

Abstract: A projectile includes a propellant charge and a nozzle opening provided in a rear projectile part and serving as an exit for propellant charge gases during flight of the projectile; a resilient rupturnable rubber or plastic sealing disc closing the nozzle opening for protection against environmental influences.

Abstract: A device for the impervious sealing of a structure, for example a munitions compartment of a rocket, is disclosed. This device comprises an elastic shaped section inside which the edge of the structure and rim of a lid are imperviously embedded. This device further has means for thrusting the lid outwards from the structure. This thrust pushes the rim and/or the edge out of the shaped section through the deformation of this elastic shaped section, and causes the total expulsion of lid. When the device is fitted into a rocket, the moving away of the rim modifies the aerodynamic drag coefficient (Cx) of the rocket. This difference in Cx causes the total expulsion of the lid and thus causes the structure to be opened.

Abstract: Atmospheric drag and heating of the forwardmost portions of high speed transatmospheric vehicles and projectiles are reduced by lowering the atmospheric mass density immediately forward of a moving body. A fine high speed stream or jet of a material containing a chemically interactive component is ejected forwardly of such a body moving at high speed with respect to the atmosphere and, in a preferred embodiment of this invention ignites by interaction with the oncoming atmosphere and forms a sustained zone of combustion that, in effect, acts as a maintained "fireball" that explodes away ambient atmosphere transversely of the moving body so that there is generated a zone of low atmospheric density immediately in front of the forwardmost portion of the body. A supply of ejectable material and equipment for forcibly driving the same through a nozzle are carried with the body. The ejected material is preferably pressurized to render it flowable before ejection.

Abstract: A supporting cupola is provided for the propellant of a base-bleed gas generator for a projectile, shell or the like. The supporting cupola is arranged in the discharge aperture of the gas generator and provides a reduced gas outlet area from the base-bleed combustion chamber during launch of the projectile. The supporting cupola is made of a material which is easily eroded by the hot combustion gases, such as magnesium. The reduced outlet area increases the pressure in the combustion chamber during the acceleration stage of the projectile so that an improved ignition of the propellant and reduced risk of extinguishment is obtained. Due to erosion of the cupola material the outlet opening area increases with time providing a regressive burning rate of the propellant which means an increased base-bleed effect with respect to the firing range of the projectiles.

Abstract: A base bleed unit arranged to increase the range of fire or to reduce the time of flight for shells and projectiles includes a housing (1) surrounding a fuel charge (6) and associated igniter (4), extending from the rear portion of a projectile body (2) and including at least one outlet nozzle (5,5',5") for combustion gases, which by means of a mass flow, and possibly combustion adjacent to the base plane, reduce existing base drag. According to an embodiment of the invention, the housing (1) comprises a caseshaped member 1 attachable against a projectile body (2), having at least one igniter (4) arranged adjacent to an internal plane of a restricting wall surface at the housing (1), located in an opposed relationship to the portion of the housing (1) attachable against a projectile body (2). The combustion flame of the igniter (4) is hereby maintained directed towards the fuel charge (6) and away from the outlet nozzle/nozzles (5, 5',5").

Abstract: A device for reducing drag of a round of ammunition or projectile (1) comprises a gas-producing compound (3) such as a propergol, the combustion of which generates gases at a pressure of at least sufficient value to fill the low-pressure region which is formed at the rear end of a projectile and causes drag. The device comprises a gas-tight casing (2) containing the explosive compound (3) and an igniter (6) for initiating combustion of the compound. The casing comprises fasteners which cooperate with complementary fasteners (11) arranged at the rear end of the round of ammunition so as to permit gas-tight fitting of the casing at the rear end of the projectile, at any moment and in particular at the firing location, in order to reduce drag and to increase the range of the projectile.

Abstract: A propellant charge for the reduction of base eddying or drag of a shell 12 with a centrally disposed ignition conduit and an ignition device for the charge disposed in the conduit. To improve the ignition readiness of the propellant charge, the inner surface of the propellant charge, which surrounds the ignition conduit, is formed so that it conically narrows in the aft direction. Additionally, the inner surface of the propellant charge may be provided with stepped sections. Finally, the ignition conduits disposed in the housing of the ignition device may be disposed at an angle relative to the longitudinal axis of the propellant charge so that they face the inner surface thereof.

Abstract: An arrangement for reducing the base drag in projectiles constructed pursuant to the high-low pressure system including a gas-generating charge, a chamber with a pressure-reducing component, and a discharge aperture provided in the base wall. In the arrangement for the reduction of the base drag in projectiles, the charge is annularly shaped, the pressure-reducing component is formed as a tube axially extending through the charge and possesses a multiplicity of nozzles. Through the provision of the large number or multiplicity of nozzles, the tube, which separates the high-pressure space from the low-pressure space, a relatively gentle gas jet exits from the bottom of the projectile. For this purpose, of significance is the swirling of the individual gas jets in the low-pressure space in accordance with the principle of the countercurrent process. The vacuum in the region of the projectile base is reduced to a minimum due to the gentle jet.

Abstract: Arrangement for a terminally guided projectile provided with a target seeking arrangement and path correction arrangement. The arrangement includes a preferably fin-stabilized, slowly-rotating artillery shell which is provided with an elongated cavity into which the terminally guided projectile, which comprises a fin-stabilized mortar projectile, is introduced. The mortar projectile is arranged so that it is ejected rearwards from the artillery shell by means of a separation charge in the vicinity of a selected target, after which the mortar projectile is terminally guided towards the target in a manner known per se.

Abstract: A ballistic propulsion system of the type used to launch grenades from a rifle. The system includes a housing having a propulsion tail protion with a ballistic cartridge mounted inside and a nozzle with a rear opening having a diameter d.sub.1. This opening is surrounded by an annular seating surface having an outside diameter d.sub.2, which is larger than d.sub.1. A diaphragm is mounted in engagement with the seating surface, and the diaphragm is designed to remain intact when pressures generated by a ballistic cartridge are asserted on a surface area of diameter d.sub.1 or less, but to break away from the propulsion tail when the gas pressure is applied to a surface area having a diameter d.sub.2 or greater. As a result, the diaphragm remains intact when the projectile is first launched by gas pressure generated by a ballistic cartridge within the rifle, but the diaphragm breaks away when the ballistic cartridge inside the propulsion tail builds up sufficient pressure.

Abstract: A solid fuel rocket in which the rocket casing acts as a warhead. Solid propellant rocket motors require relatively heavy cases to contain the 1000-2000 psi combustion pressure needed for efficient performance. This casing can be used as a fragmentation warhead by forming longitudinal grooves in the elongated rocket casing, causing the casing to fracture along the grooves and allowing the pressure within the casing to disperse the fragments. The resulting strip-like fragments are particularly useful against "soft" equipment targets, such as anti-vehicle and anti-radar applications. Several different methods for rupturing the case along spaced, parallel longitudinal lines are disclosed. This system eliminates the need for a separate warhead including case and explosive at the cost of a slight increase in propellant case thickness and weight.

Abstract: A rocket motor is disclosed which employs a Class 1.1 detonatable composition which is both a propellant and explosive. One grain design is configured to give a high boost acceleration during the burning phase of a perforated portion of the grain. The internally burning grain subsequently changes to an end-burning grain which provides a sustaining thrust burning period. The rocket motor flies to target with the burning surface progressing towards the head end. The rocket burns to target, but the design always provides some remaining propellant which serves as the warhead explosive on impact with the target. Detonator means cause the remaining unburned propellant to denonate at target impact or prior to target impact. This rocket motor design does not provide for separation between the warhead and the motor case. Therefore, the complete rocket motor travels to the target area.