A system and method for conducting electronic warfare on a target site includes the use of a small unmanned aircraft system (SUAS) having a fuselage and a Prandtl wing, wherein at least two electric ducted fans are positioned on the fuselage. A power system of the SUAS has a plurality of hydrogen fuel cells positioned within the Prandtl wing. An electronic warfare payload is carried by the fuselage, wherein the electronic warfare payload and the at least two electric ducted fans are powered by at least a portion of the plurality of hydrogen fuel cells. During an operation, the SUAS may launch near an IAD site and initiate an electronic warfare effect on an integrated air defense site with electronic warfare payload carried by the SUAS to interfere with at least one surface-to-air missile (SAM) system.

Typical composite panels are brittle and unable to support transverse pressure loads that might be imposed on the panels. For example, the use of typical panels around fuel tanks of a vehicle are unable to support transverse pressure loads that might be imposed on the fuel tanks during a crash of the vehicle or a ballistic impact to the fuel tanks. In the embodiments described herein, panels include face sheets that are bonded to a foam core. The foam core includes a corrugated core sheet that is formed from a highly ductile material, such as Polyethylene or Aluminum. When a transverse pressure load is imposed on the panel, core crush of the foam occurs as the core sheet elongates from its original corrugated shape to a curve shape during deformation. This allows the panel to dissipate the energy of the transverse pressure load applied to the panel.

The present disclosure pertains to self-piloted, electric vertical takeoff and landing (VTOL) aircraft that are safe, low-noise, and cost-effective to operate for cargo-carrying and passenger-carrying applications over relatively long ranges. A VTOL aircraft has a tandem-wing configuration with one or more propellers mounted on each wing to provide propeller redundancy, allowing sufficient propulsion and control to be maintained in the event of a failure of any of the propellers or other flight control devices. The arrangement also allows the propellers to be electrically-powered, yet capable of providing sufficient thrust with a relatively low blade speed, which helps to reduce noise. In addition, the aircraft is aerodynamically designed for efficient flight dynamics with redundant controls for yaw, pitch, and roll.

The present disclosure pertains to self-piloted, electric vertical takeoff and landing (VTOL) aircraft that are safe, low-noise, and cost-effective to operate for cargo-carrying and passenger-carrying applications over relatively long ranges. A VTOL aircraft has a tandem-wing configuration with one or more propellers mounted on each wing to provide propeller redundancy, allowing sufficient propulsion and control to be maintained in the event of a failure of any of the propellers or other flight control devices. The arrangement also allows the propellers to be electrically-powered, yet capable of providing sufficient thrust with a relatively low blade speed, which helps to reduce noise. In addition, each wing is designed to tilt, thereby rotating the propellers, as the aircraft transitions between forward flight and hover flight. While in the hover flight, the propellers may be offset from vertical so that horizontal thrust components of the propellers may be used to provide efficient yaw control.

A system, method, apparatus, and software for an uncrewed aerial freighter technology is provided. The technology includes an aircraft designed to carry only cargo, and operates either remotely or autonomously. The technology includes a software system to control the flight as well as refueling, landing, takeoff, and disposing and receiving of materials and containers. The technology includes a tracking system, using blockchain technology, of the materials, aircraft, and other features.

Embodiments of unmanned, rotary wing drones are described herein that include an insect trap for luring and capturing mosquitoes or other insects. The drone can include a set of propulsion units, each having a motor and propeller, and that collectively provide sufficient lift when operating to allow the drone to fly. A flight controller can be used to send and receive information and control a flight of the drone according to a flight plan stored on the drone. The insect trap includes a funnel or other mechanism to allow only for one-way movement of an insect into a container. To lure the insect into the trap, ultraviolet light can be shone on high-surface titanium dioxide powder that is stored within a mesh bag. A battery or other power source can be used to power the various components, and solar panels can be used to charge the battery when the drone has landed.

Systems, devices, and methods including: a latching mechanism comprising: a first latch configured to attach to a door of an unmanned aerial vehicle (UAV); a second latch configured to attach to a portion of the UAV distal from the first latch; a string connected between the first and second latch, where the string secures the door shut; at least two radio modules in communication with a ground control station; and at least two burn wires in contact with a portion of the string between the first latch and the second latch; where current from a backup battery passes to at least one burn wire when the burn signal is received, where the burn wire causes the connection between the first latch and the second latch to be broken and the door of the UAV is separated from the UAV, and where the parachute is deployed when the door of the UAV is separated from a rest of the UAV.

A shield system for an unmanned arial vehicle (AUV) is provided. The shield system includes inner shield members rigidly mounted to at least the rotor arms of the AUV and outer shield members shock mounted to the inner shield members. The shield system defines opening for sensors, payload or mechanical portions of the UAV.

A composite panel assembly including a first panel with a first skin, a second skin, a core, and an assembly flange. A second panel includes a first skin, a second skin, a core, and an assembly flange. A fastening device is adapted to fasten the assembly flange of the first panel to the assembly flange of the second panel, wherein the core of one of the first panel or the second panel includes reinforcing pins and a high-density portion placed along the assembly flange.

In one aspect, an unmanned aerial system for crowd control, includes a chassis for attaching components of the unmanned aerial system and one or more rotary wings, each of the one or more rotary wings drivable by a respective motor. A container stores a pressurized source of a crowd control agent and a nozzle is provided for dispersing the crowd control agent into the air. An electronically controlled valve selectively places the nozzle into fluid communication with the container. In a further aspect, a modular unmanned aerial system for crowd control is provided.