The present disclosure provides a propulsion system with a retardant set between two sections of propellant for delaying the combustion and reducing the generated smoke or heat while launching the propulsion system.

The present disclosure provides a propulsion system with a retardant set between two sections of propellant for delaying the combustion and reducing the generated smoke or heat while launching the propulsion system.

An ordnance for air-borne delivery to a target under remotely controlled in-flight navigation. In one embodiment, self-powered aerial ordnance includes upper and lower cases. A plurality of co-axial, deployable blades is powered by a motor positioned in the upper case. When deployed, the blades are rotatable about the upper case to impart thrust and bring the vehicle to a first altitude above a target position. An explosive material and a camera are positioned in a lower case which is attached to the upper case. The camera generates a view along the ground plane and above the target when the ordinance is in flight. When the vehicle is deployed it is remotely controllable to deliver the vehicle to the target to detonate the explosive at the target. The ordnance may drop directly on a target as a bomb does.

An ordnance for air-borne delivery to a target under remotely controlled in-flight navigation. In one embodiment, self-powered aerial ordnance includes upper and lower cases. A plurality of co-axial, deployable blades is powered by a motor positioned in the upper case. When deployed, the blades are rotatable about the upper case to impart thrust and bring the vehicle to a first altitude above a target position. An explosive material and a camera are positioned in a lower case which is attached to the upper case. The camera generates a view along the ground plane and above the target when the ordinance is in flight. When the vehicle is deployed it is remotely controllable to deliver the vehicle to the target to detonate the explosive at the target. The ordnance may drop directly on a target as a bomb does.

A winged external guidance frame placed on the muzzle that can couple with a projectile while exiting the barrel utilizing the kinetic energy of the projectile to travel to the target while the accuracy is provided by on board electronics and corrected using the wings. Alternately a reusable unmanned aerial system that travels in the speed and direction of the projectile and couples with the projectile as it exits the barrel.

A winged external guidance frame placed on the muzzle that can couple with a projectile while exiting the barrel utilizing the kinetic energy of the projectile to travel to the target while the accuracy is provided by on board electronics and corrected using the wings. Alternately a reusable unmanned aerial system that travels in the speed and direction of the projectile and couples with the projectile as it exits the barrel.

An integrated propulsion and warhead system for an artillery round includes a propulsion, such as a solid rocket motor and/or an air-breathing jet engine, and an annular explosive concentrically arranged around at least a portion of the propulsion system. The integrated propulsion and warhead system is included in a propulsion section of the artillery round so that space in an adjacent guidance section is increased and the space allocation for the propulsion system and annular explosive is optimized.

Embodiments include active protection systems and methods for an aerial platform. An onboard system includes radar modules, detects aerial vehicles within a threat range of the aerial platform, and determines if any of the aerial vehicles are an aerial threat. The onboard system also determines an intercept vector to the aerial threat, communicates the intercept vector to an eject vehicle, and causes the eject vehicle to be ejected from the aerial platform to intercept the aerial threat. The eject vehicle includes alignment thrusters to rotate a longitudinal axis of the eject vehicle to substantially align with the intercept vector, a rocket motor to accelerate the eject vehicle along an intercept vector, divert thrusters to divert the eject vehicle in a direction substantially perpendicular to the intercept vector, and attitude control thrusters to make adjustments to the attitude of the eject vehicle.

An aero vehicle with a dual mode propulsion system that can operate in a first mode below a ramjet speed and a second mode at a ramjet speed. The first mode is operated using a compressor driven by an electric motor supplied with electrical power from a power pack. When the vehicle has reached a speed where the ramjet engine can operate, the power pack is dropped from the vehicle to decrease the weight of the vehicle.

A guided missile with a sleeve-shaped missile body, at least one engine for producing forward thrust, at least one flight direction control device, and at least one aerodynamic extension. The least one flight direction control device is rotatably mounted to a top area and/or a bottom area of the sleeve-shaped missile body for adjusting a flight direction of the guided missile. The least one aerodynamic extension comprises an aerodynamic cross-sectional shape that is arranged on a left-hand side and/or a right-hand side of the sleeve-shaped missile body.