A system for autonomously replacing batteries or fuel cells on small aerial vehicles such as Unmanned Aerial Vehicles (UAVs) or radio-controlled aircraft (RC) is described. At the core of this system is a “universal battery receptacle” that can be added to a variety of unmanned aircraft platforms and provides a uniform interface for battery or fuel cell replacement in the form of a commensurately designed “universal fuel cell”.

Additionally, a system is described through which an aerial vehicle can be accepted, manipulated, the batteries replaced, and the vehicle re-launched, all without direct user intervention. Such systems can be deployed across a geographic area to increase the range of aerial vehicles without extensive ground support personnel.

The present disclosure relates to a launch system and method. The launch system and method can include at least a preliminary accelerator tube system (PAT) that can be combined with a main accelerator tube system (MAT). The PAT alone or combined with the MAT can be used for launch of a vehicle for testing and/or for delivery of a payload.

The present disclosure relates to a launch system and method. The launch system and method can include at least a preliminary accelerator tube system (PAT) that can be combined with a main accelerator tube system (MAT). The PAT alone or combined with the MAT can be used for launch of a vehicle for testing and/or for delivery of a payload.

Provided is a balloon-launching apparatus capable of reducing an increase in the size of the apparatus when a large number of housing sections for housing observation balloons are provided. A balloon-launching apparatus 1 includes a plurality of housing sections 41 each formed in a box shape having an opening 321 that opens in an upper part thereof and configured to house a balloon 21, the housing section 41 launching the balloon 21 from the opening 321. The plurality of housing sections 41 are arranged in a matrix shape. Due to the matrix arrangement of the housing sections 41, the balloon-launching apparatus 1 can reduce the creation of dead space even when a large number of the housing sections 41 are disposed and can thus reduce an increase in the size of the balloon-launching apparatus 1.

The present invention is a canister-launched pyrotechnically actuated folding wing UAV. The invention features a method for reliable and irreversible locking of a foldable wing, while enabling compact storage, cost reduction, ease of deployment and aerodynamic performance unattainable in current folding-wing designs. In a specific embodiment, the UAV is pre-packaged in a deployment canister for single-button deployment. The UAV can be offered in a rental system in which part or the entirety of the device can be returned for refurbishing. Additionally, the device can be provided as a fully expendable unit.

The present invention is a canister-launched pyrotechnically actuated folding wing UAV. The invention features a method for reliable and irreversible locking of a foldable wing, while enabling compact storage, cost reduction, ease of deployment and aerodynamic performance unattainable in current folding-wing designs. In a specific embodiment, the UAV is pre-packaged in a deployment canister for single-button deployment. The UAV can be offered in a rental system in which part or the entirety of the device can be returned for refurbishing. Additionally, the device can be provided as a fully expendable unit.

The disclosed invention is a passive flow control device, mounted vertically forward of the helicopter launch and recovery area on a ship flight deck. The vertical flow control device reduces the airwake effect on the ship flight deck for safer operation of helicopters during launch and recovery missions from ships. The device is retractable to reduce the ships topside signature and increase the ship's military effectiveness. It can also be modified for maximum effectiveness based on a combination of the ship's topside features, the ship's operation speeds, helicopter operations, and environmental conditions.

The disclosed invention is a passive flow control device, mounted vertically forward of the helicopter launch and recovery area on a ship flight deck. The vertical flow control device reduces the airwake effect on the ship flight deck for safer operation of helicopters during launch and recovery missions from ships. The device is retractable to reduce the ships topside signature and increase the ship's military effectiveness. It can also be modified for maximum effectiveness based on a combination of the ship's topside features, the ship's operation speeds, helicopter operations, and environmental conditions.

Off-board gyrocopter take-off systems and associated methods are disclosed. A representative method includes restraining a gyrocopter from vertical and lateral movement, pre-rotating a fixed-pitch lift rotor of the gyrocopter via a power source located off the gyrocopter, and releasing the gyrocopter for vertical movement to allow the gyrocopter to lift under a force provided by the lift rotor. Optionally, the method can further include interrupting or reducing power from the power source to the gyrocopter as a way to release the gyrocopter for vertical movement.

Off-board gyrocopter take-off systems and associated methods are disclosed. A representative method includes restraining a gyrocopter from vertical and lateral movement, pre-rotating a fixed-pitch lift rotor of the gyrocopter via a power source located off the gyrocopter, and releasing the gyrocopter for vertical movement to allow the gyrocopter to lift under a force provided by the lift rotor. Optionally, the method can further include interrupting or reducing power from the power source to the gyrocopter as a way to release the gyrocopter for vertical movement.