The invention relates to a decoy (3) for protecting a fast aircraft (1) against an incoming threat (2), wherein said decoy is non-driven. The decoy (3) has a squib (6) on one end and a molded body (11) on the opening side. If the decoy (3) has an active material container (8), the squib (6) can be attached to the end side thereof and the molded body (11) attached to the opening side thereof. The squib (6) contains a propellant, which is converted into a drive energy. The molded body (11) is heavier than the decoy (3) without the molded body (11) and has the task of preventing the separating of the molded body (3) to the rear. In addition, the molded body (11) should be at least 1.0-1.5 times heavier than the decoy itself. Advantageously, however, the molded body (11) is twice as heavy.

A thermal sleeve cover according to various embodiments can include a target layer material having emissivity and reflecting properties identifiable by a thermal sensor detecting device during firearm training. The thermal sleeve cover is fitted over a target backer in a taut manner to promote thermal contrast between the target layer material and its surrounding background. The tautness of the target layer material enhances the thermal identification when the target layer material is detected by the thermal sensor detecting device. The thermal cover is adjustable to snugly fit over a variety of target backers having different configurations and sizes.

A thermal sleeve cover according to various embodiments can include a target layer material having emissivity and reflecting properties identifiable by a thermal sensor detecting device during firearm training. The thermal sleeve cover is fitted over a target backer in a taut manner to promote thermal contrast between the target layer material and its surrounding background. The tautness of the target layer material enhances the thermal identification when the target layer material is detected by the thermal sensor detecting device. The thermal cover is adjustable to snugly fit over a variety of target backers having different configurations and sizes.

A non-pyrotechnic flare system and method includes at least one flare member that is configured to be deployed. The flare member(s) includes a head having a light-emitting diode (LED) that is configured to emit light when activated, and a wing-shaped appendage extending from the head. In at least one embodiment, a casing retains the flare member(s) in a stowed position. The flare member(s) is configured to be deployed from the casing.

A label comprising some figures that can be recognized by infrared vision devices. The main object is to put a figure surface on or near a reference surface and cooling one of these surfaces, in order to achieve cool surface and warm surface, enabling infrared vision devices to discriminate between the surfaces. The cooling of the surface is achieved by a Latent heat effect due to a evaporation of a liquid absorbed on said surface.

A label comprising some figures that can be recognized by infrared vision devices. The main object is to put a figure surface on or near a reference surface and cooling one of these surfaces, in order to achieve cool surface and warm surface, enabling infrared vision devices to discriminate between the surfaces. The cooling of the surface is achieved by a Latent heat effect due to a evaporation of a liquid absorbed on said surface.

An emitting structure for simulating an irradiance signature of a missile is provided. The emitting structure includes one or more radiation sources, each of which includes at least one ultraviolet radiation source and at least one infrared radiation source. The emitting structure also includes a spherical shell and a mechanism for positioning the radiation source(s) along a three dimensional boundary of the spherical shell. The emitting structure can locate and operate one of the radiation sources to simulate the irradiance signature of the missile.

An emitting structure for simulating an irradiance signature of a missile is provided. The emitting structure includes one or more radiation sources, each of which includes at least one ultraviolet radiation source and at least one infrared radiation source. The emitting structure also includes a spherical shell and a mechanism for positioning the radiation source(s) along a three dimensional boundary of the spherical shell. The emitting structure can locate and operate one of the radiation sources to simulate the irradiance signature of the missile.

A flare including: a casing; and a grain assembly, at least a portion of the grain assembly being slidably disposed in the casing, the grain assembly including: a shell structure; and a grain component at least partially disposed in the shell structure, the grain component including at least one combustible material and at least one reactive material positioned relative to the combustible material and configured to ignite combustion of the at least one combustible material; wherein the shell structure includes one or more fins at an aft end of the shell structure, the one or more fins being restrained into a first shape in the casing and configured to have a second shape, different from the first shape, when the restraint is removed.

A flare including: a casing; and a grain assembly, at least a portion of the grain assembly being slidably disposed in the casing, the grain assembly including: a shell structure; and a grain component at least partially disposed in the shell structure, the grain component including at least one combustible material and at least one reactive material positioned relative to the combustible material and configured to ignite combustion of the at least one combustible material; wherein the shell structure includes one or more fins at an aft end of the shell structure, the one or more fins being restrained into a first shape in the casing and configured to have a second shape, different from the first shape, when the restraint is removed.