an aircraft control system
A technology for aircraft manipulation and longitudinal manipulation, applied in the field of aircraft manipulation systems, to achieve the effects of long service life, low maintenance difficulty, and stable and reliable mechanism
Active Publication Date: 2018-04-13
XIAN AIRCRAFT DESIGN INST OF AVIATION IND OF CHINA
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Problems solved by technology
[0004] The object of the present invention is to provide an aircraft control system to solve or at least alleviate at least one of the problems in the background art
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[0023] In order to make the objectives, technical solutions and advantages of the present invention clearer, the technical solutions in the embodiments of the present invention will be described in more detail below in conjunction with the drawings in the embodiments of the present invention. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are some, but not all, embodiments of the invention. The embodiments described below by referring to the figures are exemplary and are intended to explain the present invention and should not be construed as limiting the present invention. Based on the embodiments of the present invention, all other embodiments obtained by persons of ordinary skill in the art without creative efforts fall within the protection scope of the present invention. Embodiments of the present invention will be described in detail below ...
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The invention discloses an aircraft control system and relates to the technical field of aircraft control system design. The aircraft control system comprises a first tail vane, a second tail vane, a first coupling rocker, a second coupling rocker, a driving connection rod, a decoupling rocker, a first decoupling connection rod, a second decoupling connection rod, a course control device and a longitudinal control device. The course control device is used for driving the first coupling rocker. The longitudinal control device is used for driving the second coupling rocker. The first coupling rocker is coupled to the second coupling rocker coaxially. The first coupling rocker is hinged to one end of the driving connection rod. The second coupling rocker is connected with a rotary shaft of the decoupling rocker. The decoupling rocker comprises an input end and two output ends. The input end of the decoupling rocker is hinged to the other end of the driving connection rod. The first decoupling connection rod is used for being connected with one output end of the decoupling rocker and the first tail vane. The second decoupling connection rod is used for being connected with the other output end of the decoupling rocker and the second tail vane. The aircraft control system has the beneficial effects that course control and longitudinal control can be achieved simultaneously, and structure is simple.
Description
technical field [0001] The invention relates to the technical field of aircraft control system design, in particular to an aircraft control system. Background technique [0002] In the field of current aircraft design, especially some small general-purpose aircraft with mechanical control mechanisms, many of them imitate the world's advanced V-shaped tail layout, that is, the two tails are inclined to both sides at an angle, and there are In addition, in the use of aircraft model aircraft, due to the reason of the shape and layout of the aircraft, the elevator and rudder should be combined in the conventional aircraft, and the functions of the elevator and rudder are combined in the V-shaped tail layout, that is, when the two When the side rudder surfaces are deflected in the same direction, the rudder surfaces play a role of yaw, that is, realize the function of rudder. To the pitch effect, that is to realize the function of the elevator. As a kind of experiential flying ...
Claims
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IPC IPC(8): B64C13/24
CPCB64C13/24
Inventor 王慧黑文静陈咸彤
Owner XIAN AIRCRAFT DESIGN INST OF AVIATION IND OF CHINA