A flame effect system for an unmanned aerial vehicle (UAV) includes a hopper configured to store a powdered fuel, a propellant tank configured to store a propellant, and a nozzle configured to expel the powdered fuel into an atmosphere. Furthermore, the flame effect system includes a fluid path extending from the propellant tank to the nozzle. The hopper is fluidly coupled to the fluid path at an intersection between the propellant tank and the nozzle, the hopper is configured to enable the powdered fuel to flow into the fluid path, and the propellant tank is configured to expel the propellant through the fluid path to fluidize the powdered fuel within the fluid path and to drive the fluidized powdered fuel through the nozzle.

The present invention provides a system and method including a master drone equipped with a target guidance system (TGM), and slave drones releasably attached to the master drone by a smart cable system. The slave drone carries and delivers non-guided ammunition directly to targets. The TGM identifies the enemy targets, their coordinates, and releases at least one slave drones to destroy the enemy targets.

Unmanned systems, and primarily vehicles, and in most embodiments unmanned aerial systems (UAS), as well as novel guided and unguided munitions are presented herein. to the two combine to present unmanned weaponized systems that not only carry weapons functionality, but allow for advanced observation and reconnaissance. These unmanned systems are largely directed toward military applications where the weaponized unmanned system may be forward deployed to allow human warfighters to remain at long range distances from the potential targets, and to provide surveillance, target identification and tracking, general reconnaissance information, and the like, while also providing weaponized attack capabilities. The unmanned systems may, in some embodiments, include advanced command and control capabilities for communication between the system and the remote, rear-positioned warfighter, and between separate elements of the unmanned system. Many embodiments also include weapons systems, munitions, or rounds with guidance and real-time maneuverability capabilities as well.

A tactically deployable rotorcraft for targeted delivery of effects and/or sensors includes a body housing an energy subsystem, a control and communications subsystem, and a modular payload compartment for holding an effect or sensor payload, the body having a generally cylindrical outline and a plurality of arm-rotor niches therein. Arm-rotor assemblies are pivotably mounted to the body, each including an articulating arm and a rotor at a distal end, and each being pivotable between (1) a closed position in a corresponding arm-rotor niche within the outline of the body, and (2) an open position extending from the body with the rotor facing in a flight direction. The rotors are powered by the energy subsystem and controlled by the control and communications subsystem to provide powered flight to a target location for delivery of the effect or sensor payload.

Embodiments of a payload attachment system secure a missile, a suicide drone, or other ordinance to a wing or fuselage of a combat drone (or another type of aircraft) using one or more vacuum mounting modules, wherein each vacuum mounting module comprises at least one vacuum pump controllably coupled to a microcontroller, a vacuum cup fluidly coupled to the at least one vacuum pump, and a transceiver that receives an instruction corresponding to one of a vacuum cup actuation signal or a vacuum cup release signal.

Apparatus and associated methods relate to an Aerial Munitions Loading and Delivery System (LBDS) configured to be mounted on an unmanned aerial platform, the LBDS having a munition holding unit including: a lever engaging frame configured to engage a interlock engagement frame of a fused munition, and a spring-loaded pin coupled to a top end of the munition configured to vertically support the munition, wherein, when the munition is loaded into the LBDS, the lever engaging frame includes an aperture configured to allow access to a safety pin of the munition. The lever engaging frame and the spring-loaded pin may, for example, exert a force in opposite directions along a horizontal axis to deactivate the munition, such that the safety pin can be removed without activating the munition.

[Subject] To provide a power feeder that harvests and supplies energy from the natural world.

[SOLUTION] The power feeder 81 comprises a first electrode 8112 formed by a conductor and placed in the earth or in water in a body of water in contact with the earth's crust at the tip where the conductor is exposed, a second electrode 8113 formed by a conductor and placed in the earth's atmosphere at the tip where the conductor is exposed, a The power collection unit 811, which converts the AC current input from the first electrode 8112 into DC current; the superposition unit 812, which boosts the DC power output by the power collection unit 811 by series connection; and the DC-AC conversion unit 813, which converts the DC power output by the superposition unit 812 into AC power.

A system for delivering and activating a two-part explosive may include an unmanned vehicle and/or an elevated structure, and a two-part explosive device. The device may include a container that is attached to, and releasable from, the unmanned vehicle or elevated structure. The container may contain an unsensitized explosive enclosed in a casing and and a sensitizing agent adjacent to the casing. The device may include an opening mechanism positioned at least partially within the container and adjacent to the casing. The opening mechanism may open the casing and expose the unsensitized explosive to the sensitizing agent, forming the two-part explosive in response to the container being released from the unmanned vehicle or elevated structure. The device may include a detonator inside or attached to the container. The detonator may trigger ignition of the two-part explosive after the unsensitized explosive is exposed to the sensitizing agent.

A system and method are provided for safe arming a flying machine that carries an explosive device. Once armed, the flying machine can provide air defense against a target (e.g., an unwanted aircraft) by using the explosive device to kinetically intercept the unwanted aircraft. The flying machine can include an explosive device, an arming device, and one or more sensors (e.g., a 9-axis inertial measurement unit). By processing the sensor data, the flying machine determines whether arming criteria have been satisfied (e.g., the flying machine has attained a desired altitude or undergone a specified pattern of accelerations), and when the arming criteria are satisfied the flying machine arms the explosive device by completing a detonation path. If the explosive device is not detonated, the system returns to a safe state before the flying machine back to its origin.

Systems and methods include an unmanned aerial vehicle (UAV) having a body and a plurality of propulsion systems, a gimbal system having a plurality of targeting sensors and a warhead mount configured to carry and deploy a warhead, and a logic device. The logic device is configured to detect a target along a UAV flight path, track the target using sensed data from the targeting sensors, calculate an attack vector for the UAV to intercept the target, calculate a detonation angle for the warhead with respect to the attack vector and a selected location on the target, and instruct the gimbal system to orient the warhead at the detonation angle.