[Object] To provide a rotary wing aircraft capable of self-leveling and ensuring a stable landing state. [Solution] The rotary wing aircraft according to the present disclosure comprises a plurality of rotary blades, an arm part for supporting the plurality of rotary blades, a mounting part for mounting an object, and a connecting part for connecting the mounting part to the arm part in a state where the mounting part is movable within a predetermined range. The position of the connecting part of the rotary wing aircraft of the present disclosure is above the center of gravity of the arm part. Thereby, self-leveling is made possible and a stable landing state can be ensured.

A flying object (drone) has a propeller drive unit provided in a fuselage thereof, and flies through the air by being driven by the propeller drive unit. The drone has a gravitational center movement device which is provided in the upper section of the fuselage and is capable of moving the total gravitational center position of the entire drone. The drone is equipped with a movement controller which moves the total gravitational center position to a target position by acquiring the total gravitational center position and controlling operation of the gravitational center movement device.

A flight vehicle control and stabilization process detects and measures an orientation of a non-fixed portion relative to a fixed frame or portion of a flight vehicle, following a perturbation in the non-fixed portion from one or both of tilt and rotation thereof. A pilot or rider tilts or rotates the non-fixed portion, or both, to intentionally adjust the orientation and effect a change in the flight vehicle's direction. The flight vehicle control and stabilization process calculates a directional adjustment of the rest of the flight vehicle from this perturbation and induces the fixed portion to re-orient itself with the non-fixed portion to effect control and stability of the flight vehicle. The flight vehicle control and stabilization process also detects changes in speed and altitude, and includes stabilization components to adjust flight vehicle operation from unintentional payload movement on the non-fixed portion.

A flight vehicle control and stabilization process detects and measures an orientation of a non-fixed portion relative to a fixed frame or portion of a flight vehicle, following a perturbation in the non-fixed portion from one or both of tilt and rotation thereof. A pilot or rider tilts or rotates the non-fixed portion, or both, to intentionally adjust the orientation and effect a change in the flight vehicle's direction. The flight vehicle control and stabilization process calculates a directional adjustment of the rest of the flight vehicle from this perturbation and induces the fixed portion to re-orient itself with the non-fixed portion to effect control and stability of the flight vehicle. The flight vehicle control and stabilization process also detects changes in speed and altitude, and includes stabilization components to adjust flight vehicle operation from unintentional payload movement on the non-fixed portion.

Presented are weight distribution systems for aircraft center of gravity (CG) management, methods for making/operating such systems, and aircraft equipped with CG management systems. A method is presented for managing the CG of an aircraft. The aircraft includes first and second landing gears and an airframe that removably attaches thereto one or more payloads and/or hardware modules. The method includes supporting the aircraft on a support leg that operatively attaches to the airframe and, while supported on the support leg, determining if the aircraft pivots onto the first or second landing gear. If the aircraft pivots onto either landing gear, the method responsively identifies a new airframe position for the payload/hardware module that will shift the aircraft's CG to within a calibrated “acceptable” CG range; doing so should balance the aircraft on the support leg. The payload/hardware module is then relocated to the new airframe position.

Presented are weight distribution systems for aircraft center of gravity (CG) management, methods for making/operating such systems, and aircraft equipped with CG management systems. A method is presented for managing the CG of an aircraft. The aircraft includes first and second landing gears and an airframe that removably attaches thereto one or more payloads and/or hardware modules. The method includes supporting the aircraft on a support leg that operatively attaches to the airframe and, while supported on the support leg, determining if the aircraft pivots onto the first or second landing gear. If the aircraft pivots onto either landing gear, the method responsively identifies a new airframe position for the payload/hardware module that will shift the aircraft's CG to within a calibrated “acceptable” CG range; doing so should balance the aircraft on the support leg. The payload/hardware module is then relocated to the new airframe position.

A multiple hoist system is used with an unmanned aerial vehicle (UAV) for delivering parcels. An example of the multiple hoist system comprises two or more hoists that are independently operable, meaning that a first hoist can lower or raise a first line independently of using a second hoist to raise or lower a second line. The hoists can independently raise and lower their associated lines to allow the UAV to deliver multiple parcels to multiple delivery locations, or the hoists can synchronously raise and lower the associated lines together so that larger parcels can be delivered using the UAV. The hoists can be comprised within a body of the multiple hoist system. The body can further include a securing device for releasably securing the multiple hoist system to the UAV.

A multiple hoist system is used with an unmanned aerial vehicle (UAV) for delivering parcels. An example of the multiple hoist system comprises two or more hoists that are independently operable, meaning that a first hoist can lower or raise a first line independently of using a second hoist to raise or lower a second line. The hoists can independently raise and lower their associated lines to allow the UAV to deliver multiple parcels to multiple delivery locations, or the hoists can synchronously raise and lower the associated lines together so that larger parcels can be delivered using the UAV. The hoists can be comprised within a body of the multiple hoist system. The body can further include a securing device for releasably securing the multiple hoist system to the UAV.

An aircraft has a supporting structure and a shell that can be filled with a gas and which is tensioned by the supporting structure. The supporting structure includes a plurality of rod or tube-shaped sections which define a circular, oval or polygonal main clamping plane for the shell.

To provide a rotary wing aircraft capable of self-leveling and ensuring a stable landing state. The rotary wing aircraft according to the present disclosure comprises a plurality of rotary blades, an arm part for supporting the plurality of rotary blades, a mounting part for mounting an object, and a connecting part for connecting the mounting part to the arm part in a state where the mounting part is movable within a predetermined range. The position of the connecting part of the rotary wing aircraft of the present disclosure is above the center of gravity of the arm part. Thereby, self-leveling is made possible and a stable landing state can be ensured.