A position restriction device for a suspension member that can improve the position accuracy of a flight body by a simple mechanism. The present disclosure is a position restriction device for a suspension member suspended from a flight body, comprising a restriction part for restricting the movement of the position of the suspension member, and a guide part for guiding the suspension member to a position where the movement of the suspension member can be restricted by the restriction part at least.

A position restriction device for a suspension member that can improve the position accuracy of a flight body by a simple mechanism. The present disclosure is a position restriction device for a suspension member suspended from a flight body, comprising a restriction part for restricting the movement of the position of the suspension member, and a guide part for guiding the suspension member to a position where the movement of the suspension member can be restricted by the restriction part at least.

In some embodiments, methods and systems are provided that for transporting and deploying unmanned aerial vehicles. The unmanned aerial vehicles may be deployed from mobile stations that include receptacles each configured to retain an unmanned aerial vehicle. The receptacles may be independently movable into relative positions that permit multiple unmanned aerial vehicles to be deployed simultaneously from the mobile stations.

An unmanned aerial vehicle (UAV) (200, 300, 400, 700, 800, 1000, 1200, 1500) can include a central body (202, 302, 402, 702, 802, 1002, 1202, 1502), a plurality of rotors, and a plurality of arms (204, 306, 406, 706, 806, 1006, 1206, 1506) extending from the central body (202, 302, 402, 702, 802, 1002, 1202, 1502), where each arm of the plurality of arms (204, 306, 406, 706, 806, 1006, 1206, 1506) is configured to support one or more of the plurality of rotors. The UAV may include at least one sensor (208, 318, 418, 718, 818, 822, 1022, 1218, 1222, 1518) located on the UAV (200, 300, 400, 700, 800, 1000, 1200, 1500) outside of a keep-out zone, where the keep-out zone is defined at least in part by (1) a plurality of rotor disks, a rotor disk of the plurality of rotor disks for each of the plurality of rotors, each rotor disk corresponding to an area that is swept by one or more rotor blades (206, 308, 408, 708, 808, 1008, 1208, 1508) of a corresponding rotor when the rotor blades (206, 308, 408, 708, 808, 1008, 1208, 1508) are spun, and (2) a shape that is formed by adjoining respective centers of adjacent rotor disks.

An automated pilotless air ambulance system. The system includes an air vehicle (AV) having a fuselage coupled to a stretcher for carrying a patient. The system is configured to fly the patient from a point of injury to a medical treatment facility. The system also has a plurality of air lift motors for vertically lifting the air vehicle. The system further includes a plurality of air-lift motors coupled to the fuselage forming a low profile. The air lift motors are centralized motors or de-centralized motors for vertically lifting the AV. The system also has an automated life support and monitoring patient suite having a plurality of life support and monitoring devices, including medical supplies. The system additionally has a bidirectional datalink coupled to the air vehicle for executing various functions such as communicating with a patient's or a first responder's mobile device.

An aerial vehicle having a low radar signature includes a first side on which turbine openings, and payload bays or landing gear bays are disposed. A second side of the aerial vehicle is designed to have a smaller radar signature than the first side.

An undercarriage for an aircraft, an aircraft and an aircraft landing method are disclosed. The undercarriage includes: at least three bendable mechanical arms, wherein each mechanical arm includes a mount, a first link and a second link located in a same plane, the mount is connected with the aircraft, the mount is rotatable about an axis perpendicular to a bottom surface of the aircraft, the other end of the first link is pivotably connected with one end of the second link, and the other end of the second link is connected with a rotating wheel; a force feedback device configured to detect whether or not the mechanical arms receive forces, respectively; and drive mechanisms configured to respectively drive the mechanical arms to move such that in an outspreading process of the undercarriage, the drive mechanisms drive any one of the mechanism arms to be maintained in a current state when the force feedback device detects that the one of the mechanism arms receives a force.

The zero carbon emission vehicle as disclosed herein may include a condenser for extracting fluid water from the atmosphere, an electrolyzer for generating hydrogen from the fluid water, and one or more deformable fluid-retaining chambers that couple thereto for selectively adjusting the buoyancy and altitude of the zero carbon emission vehicle in real-time, to maintain the air vehicle in flight substantially without needing to land and refuel the air vehicle. Solar panels provide the energy for the described systems, and the energy from the solar panels can be stored in the form of hydrogen gas which gives buoyancy to the air vehicle.

An automated and versatile autonomously climbing undercarriage with flight capability that automatically reaches a suitable area for cleaning purposes, repair purposes, and monitoring purposes without being constantly connected to a supply station or base station in the process, and that independently goes to the surface of the facade and independently moves along the surface and away from the surface. The automated and versatile autonomously climbing undercarriage with vacuum suction units as per the invention involves a multicopter with two, three or more rotors or propellers attached to the autonomously climbing undercarriage.

A multi-mode mobility micro air vehicle (MAV) accomplishes ground locomotion by hopping on a retractable leg. The hopping is translated into forward locomotion when aided by the forward thrust of propellers, and the orientation of locomotion is directed by aerodynamic controls like ailerons, rudders, stabilators, or plasma actuators. The foot of the leg is convexly curved so as to produce hopping that is statically and passively dynamically stable. The MAV is also equipped for vertical takeoff so that it may conduct multiple idling missions in sequence and may return home for recovery and reuse. Structural integration of power storage and photovoltaic generation systems into the aerodynamic surface of the MAV lightens the weight of the MAV while also providing a strong structure and permitting the MAV to harvest its own energy. The MAV may autonomously conduct surveillance missions and/or serve as a flying platform for self-healing sensor or communications networks, especially when multiple MAVs are used in concert.