The application relates to an aircraft, a method, an apparatus and a computer readable storage medium for controlling the aircraft with at least one sensor arranged thereon, the method including detecting a motor state of the aircraft, acquiring at least one sensing data of the at least one sensor, and controlling the aircraft to perform a startup operation or a shutdown operation according to the motor state and the at least one sensing data, so that the aircraft can be autonomously controlled to perform the startup operation or the shutdown operation, and the user experience is improved.

A wing for use in a flapping wing aircraft, having a strut assembly including a main strut and a plurality of support struts each oriented at an angular interval between 30 degrees and 90 degrees with respect to the support strut, at least a section of the support struts having a front section, a connecting section adjacent thereto, and a rear section adjacent thereto, and wherein each of said support struts is secured to said main strut by said connecting section, and further having a group of planking members made of a resilient and dimensionally stable sheet material and connected to said strut assembly.

A thrust generator comprising: a motor (17), and a wing mounting (10), comprising a base (11) and a wing (2, 20), the base connected to the motor and configured to rotate the wing mounting about a stroke axis (13) within an angular stroke range, wherein the wing comprises a wing panel (24) having a first longitudinal edge (5) and a second longitudinal edge (6), the wing panel defining a wing surface (4) between the first and second longitudinal edges, and wherein the wing panel is configurable between: a first configuration in which the first longitudinal edge of the wing panel defines a leading edge and the second longitudinal edge of the wing panel defines a trailing edge; and a second configuration in which the second longitudinal edge of the wing panel defines a leading edge and the first longitudinal edge of the wing panel defines a trailing edge, the thrust generator being configured to rotate the wing mounting about the stroke axis in a first direction when the wing panel is in the first configuration and to rotate the base about the stroke axis in a second direction when the wing panel is in the second configuration.

An ornithopter aircraft has a main body. A first wing frame mount and a second wing frame mount are mounted to the main body. A first wing frame is rotably mounted to a first wing frame axle on the first wing frame mount. The first wing frame is configured to rotate relative to the main body and the rotation can be powered. The first wing frame feathers are rotably mounted to the first wing frame at first feather axles and the first wing frame feather rotation can be powered. The first wing frame feathers are configured to rotate relative to the first wing frame and the first wing frame feather rotation can be powered. A second wing frame is configured to be rotably mounted to a second wing frame axle on the second wing frame mount.

The invention relates to a flight system having at least two actuated flapping wings (2), an actuated tail unit (9), a control device and an exoskeleton (1) for at least one person. The exoskeleton (1) is movable independently of the flapping wings (2). The control device is configured to receive motion sensor signals from the exoskeleton (1) and to use the motion sensor signals to define specified movement signals and to control the flapping wings (2) and/or the tail unit (9) by way of the specified movement signals. The specified movement signals can be defined such that the movements of the flapping wings (2) and/or of the tail unit (9) follow those of the exoskeleton (1).

A method for realizing a vertical take-off and landing aircraft that does not use a mechanism dedicated for take-off and landing, which cannot be achieved on the basis of an existing concept of aircraft flight control, by introducing a new concept of a shoulder rotational axis and an arm rotational axis into aircraft flight control and controlling vertical take-off and landing and ordinary flight with the same mechanism. This instruction eliminates a necessity of a tail and ailerons from an airframe of the aircraft, enables reduction of manufacturing, maintenance, and running costs thereof, and makes it possible to avoid problems of maneuverability and cruising distance performance of airframes of vertical take-off and landing aircrafts.

A ferromagnetic actuator is disposed between first and second semiconductor devices that include first and second inductors. Each inductor is disposed on top of a multilevel wiring structure. Current flows through the first inductor to generate a first magnetic field that attracts the ferromagnetic actuator towards the first inductor causing the ferromagnetic actuator to transition from a first state to a second state. In the second state, a portion of the ferromagnetic actuator is disposed closer to the first inductor than it is in the first state. Current flows through the second inductor to generate a second magnetic field that attracts the ferromagnetic actuator towards the second inductor causing the ferromagnetic actuator to transition from the first or second state to a third state. In the third state, a portion of the ferromagnetic actuator is disposed closer to the first inductor than it is in the first state.

The present disclosure provides an aircraft (10) for flying in a forward direction (F). The aircraft (10) comprises an aircraft body (20), and a wing comprising a first wing portion (30A) and a second wing portion (30B). The first wing portion (30A) and the second wing portion (30B) extend away from the aircraft body (20). The first wing portion (30A) and the second wing portion (30B) are configured to generate a first lift value during level flight of the aircraft (10) in the forward direction (F) when the first wing portion (30A) and the second wing portion (30B) are in an equilibrium position. Each of the first wing portion (30A) and the second wing portion (30B) is flexibly mounted relative to the aircraft body (20) such that when a lift force generated by the first wing portion (30A) changes from the first lift value to a second lift value, the first wing portion (30A) is deflected substantially vertically away from an equilibrium position. The aircraft (10) is configured to provide a further force to the first wing portion (30A) to substantially prevent further deflection of the first wing portion (30A) away from the equilibrium position.

A dragonfly-like miniature four-winged ornithopter includes: a fuselage (101), two front flapping wings (102), two front wing connectors (103) with first connecting rods, two rear flapping wings (104), two rear wing connectors (105) with second connecting rods, a driving gear (106), a shaft gear (107), a first-stage gear (108), two second-stage gears (109) with third connecting rods, two third-stage gears (114) with fourth connecting rods, two front ball joint connecting rods (110), two rear ball joint connecting rods (111), two steering engine connecting rods (112), two steer engines (113), and a brushless direct current motor.

A method for realizing a vertical take-off and landing aircraft that does not use a mechanism dedicated for take-off and landing, which cannot be achieved on the basis of an existing concept of aircraft flight control, by introducing a new concept of a shoulder rotational axis and an arm rotational axis into aircraft flight control and controlling vertical take-off and landing and ordinary flight with the same mechanism. This instruction eliminates a necessity of a tail and ailerons from an airframe of the aircraft, enables reduction of manufacturing, maintenance, and running costs thereof, and makes it possible to avoid problems of maneuverability and cruising distance performance of airframes of vertical take-off and landing aircrafts.