Abstract: A parafoil recovery system capable of autonomously controlling the descent profile of a payload to a recovery area and maneuvering the parafoil to execute a soft landing in the recovery area is disclosed. A descent profile management system determines wind speed and direction, altitude, heading, and position of the payload based on sensor input. The descent profile management system also determines a gliding flight path profile from the launch point to the desired recovery area. A flare and stall maneuver is executed at the end of the landing sequence by braking the parafoil to slow the vertical descent speed and groundspeed for a soft landing. The pitch attitude of the payload can be adjusted by the descent profile management system to prevent nose-first impact with the ground. The parafoil canopy is released from the payload upon touchdown to prevent the canopy from dragging the payload on the ground after landing.

Abstract: A parafoil system for autonomously controlling the gliding descent of a payload/UAV from a launch point to a predetermined recovery area and manipulating the parafoil to execute a soft landing in the recovery area, a sensing means associated with the system for determining wind speed and direction, as well as altitude, heading and position of the system, a means housed within the system for processing information received from the sensing means to determine the gliding flight path from the launch point to a predetermined recovery area and the execution of a flare maneuver to achieve a soft landing, control surface means on the parafoil canopy, mechanical means coupling the information processing means with the control surface means for adjusting the control surface means to accomplish the steering to the recovery area during gliding flight and the flare maneuver during landing, and a power source in the payload/UAV.

Abstract: An anti-submarine warfare system includes an unmanned “sea-sitting” aircraft housing submarine detecting equipment, the aircraft including a body portion having a catamaran configuration adapted for stably supporting the body portion when sitting in water, the body portion including a fuselage and laterally disposed sponsons connected to the fuselage via platforms, and submarine detecting equipment housed within the fuselage and adapted to be electronically linked to sonobuoys disposed in adjacent water locations.

Abstract: An anti-submarine warfare system includes an unmanned “sea-sitting” aircraft housing submarine detecting equipment, the aircraft including a body portion having a catamaran configuration adapted for stably supporting the body portion when sitting in water, the body portion including a fuselage and laterally disposed sponsons connected to the fuselage via platforms, and submarine detecting equipment housed within the fuselage and adapted to be electronically linked to sonobuoys disposed in adjacent water locations.

Abstract: A system for servicing unmanned aircraft includes an aircraft service area located adjacent a landing strip, a track and follower mechanism, and a plurality of stations disposed along the track and follower mechanism including a first station having apparatus for connecting the aircraft to the track and follower mechanism, a second station for reading information from and to a computer located onboard the aircraft, a third station for removing old weapons from and securing new weapons to the aircraft, and a fourth station for refueling the aircraft. The aircraft is able to move under its own power from the runway to the aircraft service area following landing on the runway, and from the aircraft service area to the runway for takeoff following servicing of the aircraft.

Abstract: The invention is a cargo compartment for a lighter-than-air vehicle, the vehicle having a longitudinal, vertical and lateral axis. In detail, the cargo compartment includes a cargo carrying structure mounted to the bottom of the vehicle, the structure extending along at least a portion of the longitudinal axis of the vehicle and having a plurality of passageways extending along the longitudinal axis of the vehicle. Each of the passageways is aligned with the lateral axis of the vehicle and extend completely through the structure, and is adapted to simultaneously unload cargo from one end and load cargo from the opposite end. A cargo moving system is mounted in the floor of each passageway for moving the cargo in one end and out the opposite end of the passageway and intermediate positions therebetween. A cargo securing system is mounted on the floor of the passageway for releasable securing the cargo within the passageway at the intermediate positions.

Abstract: The invention is a propulsion system for powering an aircraft in both vertical and horizontal flight modes. In detail, the invention includes a pair of ducted lift fans mounted in the aircraft for providing thrust in the vertical flight mode. A pair of ducted cruise fans are mounted in the aircraft for providing thrust in the horizontal flight mode. Two sets of turboshaft engines are mounted in the aircraft with each of the sets comprising a plurality of the turboshaft engines, each turboshaft engine including an output shaft and having an optimal power output sufficient for powering one of the pair of ducted cruise fans in the horizontal flight mode. Each of the sets includes a sufficient number of the turboshaft engines to provide an optimal power output for powering one of the pair of ducted lift fans and one of the pairs of ducted cruise fans the vertical flight mode. A shafting system is mounted in the aircraft for coupling all of the turboshaft engines to the pairs of ducted fans.

Abstract: The invention is a propulsion system for powering an aircraft in both vertical and horizontal flight modes. In detail, the invention includes first and second gas-driven ducted lift fans mounted in the aircraft for providing thrust in the vertical flight mode. First and second shaft-driven ducted cruise fans that have inlet ducts and bypass air ducts that are mounted in the aircraft for providing thrust in the horizontal flight mode and supercharged air for the engines in all flight modes. First and second gas transfer ducts couple the bypass air ducts of the first and second ducted cruise fans to the first and second turbo compressors, respectively. First and second shaft-driven turbo compressors are mounted in the first and second gas transfer ducts, respectively. First and second high-pressure feed ducts couple the first and second shaft-driven turbo compressors to the first and second ducted lift fans, respectively.

Abstract: The invention is a propulsion system for powering an aircraft in both vertical and horizontal flight modes. In detail, the invention comprises a gas-driven ducted lift fan mounted in the aircraft for providing thrust in the vertical flight mode. A turbofan engine is mounted in the aircraft that comprises a fan section for providing thrust in the horizontal flight mode and a turboshaft engine having an output drive shaft coupled to the fan section for driving same. A gas transfer duct is mounted in the aircraft having a first end adapted to receive exhaust air from the fan section and a second end coupled to the lift fan. A turbocompressor is mounted in the transfer duct and a combustor is mounted in the transfer duct between the turbocompressor and the lift fan, the combustor for receiving and burning fuel and providing combustion gases for driving the ducted left fan. A shafting system couples the turbocompressor to the output shaft of the turboshaft engine.