A cover for an intake of an air-breathing engine in a missile is disclosed. The cover comprises a motive arrangement operable to move from a first configuration in which the cover is lockable to a missile, to a second configuration in which the cover is pushed outwardly from the missile. In the first configuration, the surface of the cover is flush with the surface of the missile and the motive arrangement is located inwardly of the cover surface. A missile provided with such a cover is also disclosed.

A cover for an intake of an air-breathing engine in a missile is disclosed. The cover comprises a motive arrangement operable to move from a first configuration in which the cover is lockable to a missile, to a second configuration in which the cover is pushed outwardly from the missile. In the first configuration, the surface of the cover is flush with the surface of the missile and the motive arrangement is located inwardly of the cover surface. A missile provided with such a cover is also disclosed.

Provided is a rocket for artificial rainfall using an ejection hygroscopic flare, the rocket including: a rocket body configured to descend with a parachute after flight by thrust, and having a hygroscopic flare discharge outlet; a communication module installed in the rocket body, and configured to transmit and receive a launch command and an ejection command with a ground station; an ejection hygroscopic flare installed in the rocket body and filled with cloud seeds and a burning material therein; and a hygroscopic flare ejection device configured to separate and eject the ejection hygroscopic flare from an inside of the rocket body to an outside thereof.

Provided is a rocket for artificial rainfall using an ejection hygroscopic flare, the rocket including: a rocket body configured to descend with a parachute after flight by thrust, and having a hygroscopic flare discharge outlet; a communication module installed in the rocket body, and configured to transmit and receive a launch command and an ejection command with a ground station; an ejection hygroscopic flare installed in the rocket body and filled with cloud seeds and a burning material therein; and a hygroscopic flare ejection device configured to separate and eject the ejection hygroscopic flare from an inside of the rocket body to an outside thereof.

A powered projectile having a nose portion, a body portion, a tail portion, and a central axis. In various embodiments a collar is rotatably mounted to a control support portion with a plurality of aerodynamic surfaces thereon for despinning the collar. An alternator configured as an axial flux machine with a stator arranged can be axially adjacent to one or more rotors, the stator including a plurality of windings and the one or more rotors each including a plurality of permanent magnets arranged about the face of the respective one or more rotor. In various embodiments the projectile includes an assembly of projectile control circuitry. In one or more embodiments, upon relative motion of the rotor with respect to the stator, magnetic flux from the magnets interacts with the windings of the stator and passes through an air gap between the one or more rotors and stator.

The present invention relates to a glide bomb and methods of use thereof for use with an unmanned or manned aerial vehicle or for operative deployment. In one form, the glide bomb is configured to be carried and released by an unmanned aerial vehicle (“UAV”) for flight towards a selected target. The glide bomb includes an elongate body having a nose and an opposed tail aligned along a longitudinal axis; a payload; a pair of wings extendable from opposed sides of the body for producing lift, said wings configured to be selectively moveable between a retracted position and an extended position; and two or more tail control surfaces operatively associated with the tail of the body for at least pitch and yaw control.

A method of forming a solid fuel. The method comprises passivating a fuel material comprising a metalloid. Passivating the fuel material comprises combining the fuel material, a solvent, and an isocyanate passivation agent to form a solution, and passivating exposed surfaces of the fuel material with the isocyanate passivation agent to form a passivated fuel material. The method further comprises combining the passivated fuel material with at least one binder to form a mixture, and combining a curing agent with the mixture to form a solid fuel. Related solid fuels, solid fuel ramjet engines, and methods of passivating boron and forming a solid fuel ramjet engine are also disclosed.

A method of reducing low-energy flow in a flight vehicle engine includes an isolator of the engine having a swept-back wedge to improve flow mixing. The wedge includes forward shock-anchoring locations, such as edges or rapidly-curved portions, that anchor oblique shocks in situations where the isolator has sufficient back pressure. The swept-back wedge may also create swept oblique shocks along its length. Boundary layer flow streamlines are diverted running parallel to or parallel but moving outward conically to the swept-wedge leading edge moving outboard and upward. The non-viscous flow outside the boundary layer is processed through the swept-back ramp shock and diverted outboard and upward as well. The outboard aft portion of the wedge at the sidewall intersection may also induce shocks and divert flow near the walls closer toward the walls and upward, and/or improve flow mixing.

A method of reducing low-energy flow in a flight vehicle engine includes an isolator of the engine having a swept-back wedge to improve flow mixing. The wedge includes forward shock-anchoring locations, such as edges or rapidly-curved portions, that anchor oblique shocks in situations where the isolator has sufficient back pressure. The swept-back wedge may also create swept oblique shocks along its length. Boundary layer flow streamlines are diverted running parallel to or parallel but moving outward conically to the swept-wedge leading edge moving outboard and upward. The non-viscous flow outside the boundary layer is processed through the swept-back ramp shock and diverted outboard and upward as well. The outboard aft portion of the wedge at the sidewall intersection may also induce shocks and divert flow near the walls closer toward the walls and upward, and/or improve flow mixing.

According to a first aspect of the present invention, there is provided a reconnaissance and communication assembly, adapted to be launched from a gun barrel into the air. The assembly comprises a carrier (with a cavity) and a payload (within the cavity). The payload is arranged to be controllably expelled from the carrier and once expelled from the carrier, the payload transmits a signal.