Disclosed are the thermal protection and drag reduction method and system for an ultra high-speed aircraft. A cold source is and a cold source driving device are arranged inside a cavity of the ultra high-speed aircraft. A plurality of micropores are arranged on a wall surface of the cavity. The cold source driving device comprises an air pump, a cold source reservoir and a buffer. The air pump supplies compressed air to a cold source reservoir during operation. The cold source enters the buffer and is vaporized under the action of air pressure. High-pressure gas is ejected from the micropores to form a gas film on the outer surface of the cavity. The gas film not only can perform thermal protection on the ultra high-speed aircraft, but also can effectively reduce viscous drag between the aircraft and the external gas, by virtue of which the thermal barrier phenomenon is alleviated or eliminated. Therefore, security of the ultra high-speed aircraft is improved and service life is prolonged.

A device is provided. The device includes at least one SMM component fabricated from an SMM. The SMM component is configured to change shape in response to receiving a stimulus. The SMM component is also configured to deploy from a device body of the device allowing the device to change shape in an advantageous way. A method implemented by a device is also provided. The method includes changing a shape of an SMM component of the device in response to receiving a stimulus. The SMM component is fabricated from an SMM. The method also includes deploying the SMM component from a device body of the device allowing the device to change shape in an advantageous way.

A bullet system (1) for use with a weapon upon firing, the bullet system (1) including a main body (3) acting as a projectile, as well as a first, second and third drag-reducing assemblies (5a, 5b, 5c) for providing the bullet system (1) with reductions of base drag, frontal drag and skin drag, during flight trajectory, the drag-reducing assemblies (5a, 5b, 5c) being fluidly connectable to one another via a common longitudinal channel (11), and the most frontward (5b) of said drag-reducing assemblies (5a, 5b, 5c) being provided with a material capable of being converted into an operative vapor discharge to be released from an orifice located at the bullet tip for covering the outer surface of the main body (3) of the bullet system (1) with said operative vapor discharge during flight, and thus, reducing the skin and frontal drag of the bullet system (1) during flight; wherein the first drag-reducing assembly (5a) is being provided about a rearward portion of the main body (3) for providing the bullet (1) with a reduction of base drag during flight trajectory.

A bullet system (1) for use with a weapon upon firing, the bullet system (1) including a main body (3) acting as a projectile, as well as a first, second and third drag-reducing assemblies (5a, 5b, 5c) for providing the bullet system (1) with reductions of base drag, frontal drag and skin drag, during flight trajectory, the drag-reducing assemblies (5a, 5b, 5c) being fluidly connectable to one another via a common longitudinal channel (11), and the most frontward (5b) of said drag-reducing assemblies (5a, 5b, 5c) being provided with a material capable of being converted into an operative vapor discharge to be released from an orifice located at the bullet tip for covering the outer surface of the main body (3) of the bullet system (1) with said operative vapor discharge during flight, and thus, reducing the skin and frontal drag of the bullet system (1) during flight; wherein the first drag-reducing assembly (5a) is being provided about a rearward portion of the main body (3) for providing the bullet (1) with a reduction of base drag during flight trajectory.

There is provided a reversible range extension device, capable in use, of being reversibly engaged to a body of an artillery shell, said range extension device comprising at least one energetic material, and an igniter, wherein the range extension device comprises a first end with an aperture, and second closed end, wherein the range extension device, in use, is selectively arranged to be in an active orientation or inert orientation, wherein in the active orientation the range extension device is arranged such that the aperture faces rearwardly away from the shell to allow the range extension device to function, and in the inert orientation the range extension device is arranged such that the aperture faces inwardly towards the shell.

There is provided a reversible range extension device, capable in use, of being reversibly engaged to a body of an artillery shell, said range extension device comprising at least one energetic material, and an igniter, wherein the range extension device comprises a first end with an aperture, and second closed end, wherein the range extension device, in use, is selectively arranged to be in an active orientation or inert orientation, wherein in the active orientation the range extension device is arranged such that the aperture faces rearwardly away from the shell to allow the range extension device to function, and in the inert orientation the range extension device is arranged such that the aperture faces inwardly towards the shell.

A projectile including a jacket, a core and a stabilizer part, the stabilizer part including a shaft and a fin part fastened to the shaft at the first end of the stabilizer part, whereby in the core of the projectile is a cylindrical cavity, which is closed at least partly with a shutoff part in which shutoff part is an aperture for the shaft of the stabilizer part, whereby a piston is fastened to the second end of the shaft of the stabilizer part, which piston is disposed in a cavity for forming a space at the front end of the piston and through the shaft of the stabilizer part a channel passes into the space and in the front part of the cavity is a solid fuel, which is made to ignite by means of the powder pressure produced in conjunction with firing of the projectile.

The present invention relates to a range extension device, particularly to a reversible range extension device, especially reversible base bleed device. There is provided a reversible range extension device, capable in use, of being reversibly engaged to a body of an artillery shell, said range extension device comprising at least one energetic material, and an igniter, wherein the range extension device comprises a first end with an aperture, and second closed end, wherein the range extension device, in use, is selectively arranged to be in an active orientation or inert orientation, wherein in the active orientation the range extension device is arranged such that the aperture faces rearwardly away from the shell to allow the range extension device to function, and in the inert orientation the range extension device is arranged such that the aperture faces inwardly towards the shell.

The present invention relates to a range extension device, particularly to a reversible range extension device, especially reversible base bleed device. There is provided a reversible range extension device, capable in use, of being reversibly engaged to a body of an artillery shell, said range extension device comprising at least one energetic material, and an igniter, wherein the range extension device comprises a first end with an aperture, and second closed end, wherein the range extension device, in use, is selectively arranged to be in an active orientation or inert orientation, wherein in the active orientation the range extension device is arranged such that the aperture faces rearwardly away from the shell to allow the range extension device to function, and in the inert orientation the range extension device is arranged such that the aperture faces inwardly towards the shell.