Control device, vertical take-off and landing aircraft and control method
A control device, a vertical take-off and landing technology, which is applied in the field of flight control and can solve the problems of the control device pilot's manipulation error, the pilot's high physical strength, and the complex structure of the vertical take-off and landing aircraft.
Pending Publication Date: 2021-05-18
BEIJING AERONAUTIC SCI & TECH RES INST OF COMAC +1
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Problems solved by technology
[0003] The object of the present invention is to provide a control device, a vertical take-off and landing aircraft and a control method, to solve the problems that the vertical take-off and landing aircraft is complex in structure, inconvenient to operate, the pilot's physical strength is exhausted, and the control device easily leads to the pilot's misoperation
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[0041] The present invention will be further described in detail below in conjunction with the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are only used to explain the present invention, but not to limit the present invention. In addition, it should be noted that, for the convenience of description, the drawings only show some but not all structures related to the present invention.
[0042] In the description of the present invention, unless otherwise expressly specified and limited, the terms "connected", "connected" and "fixed" should be understood in a broad sense, for example, it may be a fixed connection, a detachable connection, or an integrated ; It can be a mechanical connection or an electrical connection; it can be a direct connection or an indirect connection through an intermediate medium, and it can be the internal connection of two elements or the interaction relationship between the two elements....
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The invention belongs to the technical field of flight control, and discloses a control device, a vertical take-off and landing aircraft and a control method. According to the control device, a lifting control mechanism is rotationally connected to a handle to control the aircraft to ascend and descend; the first rotating shaft and the lifting control mechanism are located at the two ends of the handle respectively, and the handle rotates relative to the first rotating shaft to control the aircraft to horizontally move left and right; the transverse control mechanism rotates relative to the second rotating shaft to control the aircraft to adjust the course; the first frame box is slidably located on the sliding rail to control the aircraft to horizontally move front and back, in the rotor wing mode, the axial centering mechanism can drive the first frame box to slide and center in the set direction of the sliding rail, and in the fixed wing mode, the damping mechanism can prevent the first frame box from sliding in the set direction of the sliding rail. The control device can control the aircraft in a rotor wing mode and a fixed wing mode, is simple in structure, can effectively avoid control errors of a pilot, and can save physical power of the pilot.
Description
technical field [0001] The invention relates to the technical field of flight control, in particular to a control device, a vertical take-off and landing aircraft and a control method. Background technique [0002] The vertical take-off and landing aircraft has the characteristics of both the rotorcraft and the fixed-wing aircraft, and its control method needs to be able to adapt to the operating characteristics of the rotor mode and the fixed-wing mode. The design purpose of the control device of the vertical take-off and landing aircraft is to meet the control concept and control logic of the two modes, reduce the control device to reduce the control load, and avoid human errors caused by mode switching. However, the existing vertical take-off and landing aircraft has a complex structure, is inconvenient to operate, and consumes a large amount of the pilot's physical strength. SUMMARY OF THE INVENTION [0003] The purpose of the present invention is to provide a control...
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IPC IPC(8): B64C13/04
CPCB64C13/0421
Inventor 杨勇鱼润汐郭玮张驰崔赫夫王利剑杨志刚
Owner BEIJING AERONAUTIC SCI & TECH RES INST OF COMAC