The present invention relates to the field of heavier-than-air aircraft, such as airplanes and unmanned aerial vehicles (UAV) and, in particular, to emergency rescue systems. The technical objective is accomplished by providing an aircraft, such as a drone, including a powerplant, a parachute, and a body. In particular, the parachute has a fixed shape, it is permanently in an opened state and is connected to the body by rigid braces, while the aircraft center of gravity is located below the aircraft aerodynamic center.

Systems and methods are disclosed for implanting a dual-kite aerial vehicle including a first kite apparatus, a second kite apparatus, and a tether extending between the first and second kite apparatuses. In particular, the disclosed systems include a first kite apparatus including a first flight controller that maintains flight at a first altitude. The disclosed system further includes a second kite apparatus including a second flight controller that maintains flight at a second altitude. The flight controllers can cooperatively maintain a gradient air movement between the first and second altitudes by extending or retracting the tether to modify a difference in the air movements between the first and second kite apparatuses. The systems described herein additionally include components for generating electrical energy from the gradient air movement to extend a flight time of the dual-kite aerial vehicle.

A paradrone includes a canopy having a parafoil, a transverse canopy frame coupled to the parafoil to support the parafoil, a longitudinal canopy frame that is coupled to the parafoil while having a bent structure such that the parafoil generates a lift, and at least one parafoil connecting portion for connecting at least one canopy frame among the transverse canopy frame and the longitudinal canopy frame to the parafoil. The paradrone also includes a servomotor portion having a servomotor body and a servomotor arm for coupling and fixing intersecting parts of the transverse canopy frame and the longitudinal canopy frame. The servomotor arm is connected to a servomotor body and rotated in a predetermined direction by driving of the servomotor body to change the angle between the travelling direction of the paradrone fuselage and the transverse and longitudinal canopy frames, thereby changing the angle of attack.

Various embodiments of the present disclosure provide a parasail-assisted system for launching a fixed-wing aircraft into free flight and for retrieving a fixed-wing aircraft from free flight.

Provided herein is a canopy control system comprising a yoke, configured to be pivotably securable to a vehicle and securable to a line system of a canopy in use, such that the yoke pivots with respect to the vehicle in a first direction when the canopy is subjected to a wind force; and a control mechanism configured to apply a control force to the canopy line system to cause the canopy to oppose the wind force, such that yoke pivots with respect to the vehicle in a second direction which is opposite to the first direction.

The present invention relates to the field of heavier-than-air aircraft, such as airplanes and unmanned aerial vehicles (UAV) and, in particular, to emergency rescue systems. The technical objective is accomplished by providing an aircraft, such as a drone, including a powerplant, a parachute, and a body. In particular, the parachute has a fixed shape, it is permanently in an opened state and is connected to the body by rigid braces, while the aircraft center of gravity is located below the aircraft aerodynamic center.

An aerial vehicle safety apparatus includes an expandable object, an ejection apparatus, a bag-shaped member, and a gas generator. The expandable object is wound or folded in a non-expanded state and generates at least any of lift and buoyancy in an expanded state. The ejection apparatus is coupled to the expandable object by a coupling member and ejects the non-expanded expandable object into air. The bag-shaped member is provided in the expandable object and wound or folded together with or separately from the non-expanded expandable object, and expands the non-expanded expandable object by at least partially being inflated like a tube. The gas generator is provided in the expandable object and inflates the bag-shaped member by causing gas generated at the time of activation to flow into the bag-shaped member.

A system and a method for suppressing a deterioration of communication quality due to frequent occurrence of handovers at cell boundaries of a plurality of cells formed by a plurality of radio relay apparatuses that can move in an upper airspace, are provided. In the system, each of the plurality of radio relay apparatuses for performing a radio communication with a terminal apparatus comprises a radio relay station which is movably provided by flying in an upper airspace, forms a cell toward the ground or the sea, and performs a radio communication with a terminal apparatus located in the cell. Each of the plurality of radio relay apparatuses flies in cooperation with each other so as to maintain a positional relationship between the radio relay apparatuses by an autonomous control or external control.

A parachute device for drone includes a container, a power source, a base, a parachute body and an open-assist member. A top of the container has an opening. The power source is disposed on a bottom of the container. The base is disposed on the power source. The parachute body, disposed on the base, is in a folded status. The open-assist member is disposed in the parachute body. The open-assist member contacts the base and the center of the inner surface of the parachute body.

A method and apparatus for an unmanned aerial system is described herein. An unmanned aerial system capable of being launched from a grenade launcher includes a tubular body that encloses a compartment for a payload and a battery, a motor coupled to the tubular body, a propeller coupled to the motor, and a parachute disposed within the tubular body when the unmanned aerial system is in a stowed configuration and disposed outside of the tubular body when the unmanned aerial system is in a powered flight configuration.