Abstract: An aircraft includes a fuselage extending along a first x-axis and a wing assembly including a first wing an a second wing. A first power assembly of the aircraft includes a first propulsion element and a first electric motor while a second power assembly includes a second propulsion element and a second electric motor. The aircraft further includes a third power assembly positioned aft of the first power assembly and the second power assembly. The third power assembly includes a third propulsion element and an internal combustion engine.

Abstract: A hybrid aircraft system uses a combination of direct propeller driven gas engine and electric motor power to provide vertical thrust and control for hover of the aircraft. Furthermore, a portable launch/recovery system is configured for use with an aircraft such as a Vertical Takeoff and Landing (VTOL) Unmanned Air Vehicle (UAV). The system is configured to enable ships with limited available deck space to become UAV-compatible.

Abstract: A range extension unit extends the range of a guided mortar bomb. The range extension unit includes a housing interface defining an internal cup that receives a rear portion of a guided mortar bomb, wherein the housing interface covers a rear portion of the mortar bomb. The housing interface, when coupled to the mortar bomb, collectively forms an aerodynamically shaped body with the mortar bomb. At least two deployable wings are attached to the housing interface, wherein the wings transition between a retracted state and a deployed state.

Abstract: A hybrid aircraft system uses a combination of direct propeller driven gas engine and electric motor power to provide vertical thrust and control for hover of the aircraft. Furthermore, a portable launch/recovery system is configured for use with an aircraft such as a Vertical Takeoff and Landing (VTOL) Unmanned Air Vehicle (UAV). The system is configured to enable ships with limited available deck space to become UAV-compatible.

Abstract: A guidance unit system is configured to be used for a ground-launched projectile. The system includes a housing configured to be attached to a ground-launched projectile. The housing is coupled to an attachment region that attaches to the projectile, wherein the housing is configure to rotate relative to the attachment region. A motor is contained within the housing and a bearing surrounding the motor. The bearing is rigidly attached to the housing such that the motor rotates with the housing and shields the motor from inertial loads experienced by the housing.

Abstract: A guidance unit system is configured to be used for a ground-launched projectile. The system includes a housing configured to be attached to a ground-launched projectile. The housing is coupled to an attachment region that attaches to the projectile, wherein the housing is configure to rotate relative to the attachment region. A motor is contained within the housing and a bearing surrounding the motor. The bearing is rigidly attached to the housing such that the motor rotates with the housing and shields the motor from inertial loads experienced by the housing.

Abstract: A Projectile Continuous Power Module (PCMP) is configured to take incoming or oncoming airflow of an inflight projectile and direct the airflow to a turbine for converting the airflow into electrical power. The PCMP is mounted within or otherwise coupled to an airframe of the projectile. The PCMP is coupled to the projectile in a manner such that an air inlet of the projectile is positioned to capture incoming or oncoming boundary layer airflow as the projectile travels.

Abstract: A guidance unit system is configured to be used for a ground-launched projectile. The system includes a housing configured to be attached to a ground-launched projectile. The housing is coupled to an attachment region that attaches to the projectile, wherein the housing is configure to rotate relative to the attachment region. A motor is contained within the housing and a bearing surrounding the motor. The bearing is rigidly attached to the housing such that the motor rotates with the housing and shields the motor from inertial loads experienced by the housing.

Abstract: A range extension unit extends the range of a guided mortar bomb. The range extension unit includes a housing interface defining an internal cup that receives a rear portion of a guided mortar bomb, wherein the housing interface covers a rear portion of the mortar bomb. The housing interface, when coupled to the mortar bomb, collectively forms an aerodynamically shaped body with the mortar bomb. At least two deployable wings are attached to the housing interface, wherein the wings transition between a retracted state and a deployed state.

Abstract: A Projectile Continuous Power Module (PCMP) is configured to take incoming or oncoming airflow of an inflight projectile and direct the airflow to a turbine for converting the airflow into electrical power. The PCMP is mounted within or otherwise coupled to an airframe of the projectile. The PCMP is coupled to the projectile in a manner such that an air inlet of the projectile is positioned to capture incoming or oncoming boundary layer airflow as the projectile travels.

Abstract: A guidance unit system is configured to be used for a ground-launched projectile. The system includes a housing configured to be attached to a ground-launched projectile. The housing is coupled to an attachment region that attaches to the projectile, wherein the housing is configure to rotate relative to the attachment region. A motor is contained within the housing and a bearing surrounding the motor. The bearing is rigidly attached to the housing such that the motor rotates with the housing and shields the motor from inertial loads experienced by the housing.

Abstract: A guidance unit system is configured to be used for a ground-launched projectile. The system includes a housing configured to be attached to a ground-launched projectile. The housing is coupled to an attachment region that attaches to the projectile, wherein the housing is configure to rotate relative to the attachment region. A motor is contained within the housing and a bearing surrounding the motor. The bearing is rigidly attached to the housing such that the motor rotates with the housing and shields the motor from inertial loads experienced by the housing.

Abstract: A guided bomb is provided with a central hardback section having a pair of extensible wings pivotally attached thereto. The hardback section is attached to the bomb by a saddle member. After launch of the bomb from the aircraft, the wings are extended by means of an electric motor and gear train to provide the lift necessary for gliding flight. One or more ailerons are provided on the trailing edges of the wings to enable control of the flight, these ailerons being controlled by the bomb's resident guidance system. The geometry of the wings, the hardback section and saddle member are designed so that the guided bomb units can be fitted within a restricted space on bomber aircraft rotary launchers.

Abstract: A microcomputer with a modem is programmed with information for controlling a flight control computer on a missile. The microcomputer is carried on an aircraft from which the missile is controlled. The pilot of the aircraft has a keypad for setting the target coordinates in the microcomputer. The audio signals from the microcomputer modem are fed to the voice communications system of the aircraft so as to modulate the carrier of the transmitted signal. This signal is received by the receiver on the missile and demodulated and employed to control signals for the missile in the missile flight control computer. The pilot of the aircraft sets in target coordinates for the missile on a keypad connected to the microcomputer.

Abstract: An unpowered air vehicle, i.e. a glider, which is air-launched from appreciable range, is densely packed with a large area, explosive net. At a pre-determined location, the net is extracted from the glider by a parachute and expanded completely before landing on the surface of the water or land that contains a large field of mines. The explosive material in the net is then detonated, destroying the mines covered by the net. The longitudinal ends of the net are attached to a folding, multi-arm framework designed to expand and thereby spread the net after separation from the glider. The spreading action is initiated by an extraction parachute which pulls the first frame from the air vehicle. The spreading action is completed by the second frame which is coupled to a brake mechanism in the glider that maintains tension throughout the net to complete the spreading of the net.

Abstract: A device having pop-out wings and a guidance and control system is detachably mounted on a munition such as a bomb and is used to extend the range capability of the munition. Prior to launch, the wings are folded together. The control system is contained within a saddle portion of the device, and when the munition is released from the aircraft, the wings are caused to pop out to their flying position. The saddle is secured to the munition through a single bolt. Controllable flaps are installed along the trailing edges of the wings, such flaps being operated to control the pitch and roll angle of the munition. When the target area is reached, the device is jettisoned by detonating a charge which shears the securing bolt, thereby permitting the device to pivot rearwardly and separate from the munition.