An aircraft control system (100) including an aircraft control module (110), a trained classifier module (120), and an aircraft control processing engine (13). The aircraft control module (110) generates first control outputs (104a to 104c) based on received aircraft operating inputs (102a to 102d). The trained classifier module receives the aircraft operating inputs (102a to 102d) and generates second control outputs (104d to 104f). The aircraft control processing engine (130) receives the first control outputs (104a to 104c) and the second control outputs (104d to 104f) and generates operating control outputs (106a to 106c), based on the received first control outputs and second control outputs. The aircraft control processing engine (130) then controls the aircraft using the operating control outputs (106a to 106c).

The present invention discloses a high-speed take-off and landing anti-falling airplane. The airplane includes an fuselage, wing mechanisms are provided on the fuselage, each wing mechanism includes a main wing, an invisible wing, a slow descent wing, a layer wing, an empennage, a slow descent wing adjusting mechanism, an invisible wing adjusting mechanism and a layer wing adjusting mechanism, the layer wings are provided on the upper side and the lower side of each main wing respectively, and the layer wing adjusting mechanisms are provided on the inner sides of the layer wings; the front end of the layer wing adjusting mechanism is fixedly connected with the inner side of the layer wing; according to the high-speed take-off and landing anti-falling airplane, the take-off speed and safety are improved, and fuel consumption is reduced.

The present invention discloses a high-speed take-off and landing anti-falling airplane. The airplane includes an fuselage, wing mechanisms are provided on the fuselage, each wing mechanism includes a main wing, an invisible wing, a slow descent wing, a layer wing, an empennage, a slow descent wing adjusting mechanism, an invisible wing adjusting mechanism and a layer wing adjusting mechanism, the layer wings are provided on the upper side and the lower side of each main wing respectively, and the layer wing adjusting mechanisms are provided on the inner sides of the layer wings; the front end of the layer wing adjusting mechanism is fixedly connected with the inner side of the layer wing; according to the high-speed take-off and landing anti-falling airplane, the take-off speed and safety are improved, and fuel consumption is reduced.

A control device is provided which forms a communication area on a ground to control an aircraft having an antenna for providing a radio communication service to a user terminal in the communication area. The control device includes a control unit that makes a plurality of aircrafts fly in formation, and controls the plurality of aircrafts such that the communication area of each of the plurality of aircrafts moves while covering a part of a preset target area and the entire target area is covered by a plurality of the communication areas of the plurality of aircrafts.

A first moving body has: a first control information generation unit for generating first control information for causing the first moving body to operate by itself; a state acquisition unit for acquiring states of the first moving body and a second moving body; a second control information generation unit for generating, on the basis of the acquired states, second control information for causing the first moving body and the second moving body to operate in a coordinated manner; a third control information generation unit for generating third control information from the first control information and the second control information; and an operation control unit for controlling operation of the first moving body in accordance with the third control information.

A first moving body has: a first control information generation unit for generating first control information for causing the first moving body to operate by itself; a state acquisition unit for acquiring states of the first moving body and a second moving body; a second control information generation unit for generating, on the basis of the acquired states, second control information for causing the first moving body and the second moving body to operate in a coordinated manner; a third control information generation unit for generating third control information from the first control information and the second control information; and an operation control unit for controlling operation of the first moving body in accordance with the third control information.

To provide an aircraft of which flight efficiency can be improved. An image capturing method according to this embodiment is a method for capturing an image of an object to be photographed by using a plurality of aircrafts including an image capturing part. The image capturing method includes a ranking step of setting up a predetermined ranking for each of the aircrafts, a control step of performing control on the basis of the ranking, and an image capturing step of moving the aircraft and using the image capturing part to capture an image of the object. According to this configuration, a plurality of aircrafts can be used to capture images of a plurality of objects to be photographed simultaneously from different angles.

An aerial vehicle control system includes an aerial vehicle and a computing device. The aerial vehicle includes an altitude controller and a lateral propulsion controller. The computing device includes a processor and a memory. The memory stores instructions that, when executed by the processor, cause the computing device to obtain location data corresponding to a location of the aerial vehicle; obtain wind data; determine an altitude command, a latitude command, and a longitude command based on at least one of the location data or the wind data; cause the altitude controller to implement at least one of the altitude command, the latitude command, or the longitude command; and cause the lateral propulsion controller to implement at least one of the altitude command, the latitude command, or the longitude command.

An aerial vehicle control system includes an aerial vehicle and a computing device. The aerial vehicle includes an altitude controller and a lateral propulsion controller. The computing device includes a processor and a memory. The memory stores instructions that, when executed by the processor, cause the computing device to obtain location data corresponding to a location of the aerial vehicle; obtain wind data; determine an altitude command, a latitude command, and a longitude command based on at least one of the location data or the wind data; cause the altitude controller to implement at least one of the altitude command, the latitude command, or the longitude command; and cause the lateral propulsion controller to implement at least one of the altitude command, the latitude command, or the longitude command.

Systems and methods for controlling a fixed-wing aircraft during flight are disclosed. The aircraft comprises first and second flight control surfaces of different types. The method comprises determining that a pilot command of the first flight control surface will excite a structural flexible mode of the aircraft and then executing the pilot command of the first flight control surface in conjunction with a command of the second flight control surface to mitigate the effect of the excitation of the structural flexible mode of the aircraft.