Azimuth controller applicable to aircraft

Abstract

The invention provides an azimuth controller applicable to an aircraft. The azimuth controller is composed of a main body and an integrated control chip, wherein a kinetic energy display signal lamp and a plurality of control buttons are arranged on a panel; the control buttons include a mode conversion switch, a positive and negative direction control button, a retarded regulator and a maximum stroke regulator; and the various control buttons are electrically connected to the integrated control chip. According to the azimuth controller applicable to the aircraft, an inductor is integrally combined with the controller and the modes of a steering engine are switched and selected by virtue of the mode conversion switch; therefore, the azimuth controller is not only applicable to a digital steering engine but also suitable for an analog steering engine.

Description

technical field [0001] The invention relates to an aircraft model product, in particular to an azimuth controller applicable to a model aircraft. Background technique [0002] When the molded aircraft is hovering in the air, sometimes it will be blown by the side wind. At this time, the tail rudder of the helicopter will deviate in the horizontal direction. In order to correct this deviation, the applicable The azimuth controller of the aircraft will send a control signal to the tail rudder servo to resist the deviation of the tail rudder in the opposite direction. When the tail rudder stops drifting, the control signal applicable to the azimuth controller of the aircraft also disappears thereupon. If the crosswind continuously hits the helicopter, it will cause the tail rudder to shift continuously. At this time, the azimuth controller of the applicable aircraft will resist the deviation of the tail rudder until the tail rudder moves to the leeward position. This is the we...

AI Technical Summary

Problems solved by technology

If the crosswind continuously hits the helicopter, it will cause the tail rudder to shift continuously. At this time, the azimuth controller of the applicable aircraft will resist the deviation of the tail rudder until the tail rudder moves to the leeward position. This is the weather vane effect. As a result, the tail rudder is offset, and the original position cannot be maintained; secondly, the traditional azimuth controller for aeronautical vehicles only sends a control signal to the tail rudder servo when the tail rudder of the helicopter moves, and when the tail rudder stops moving , the control signal also returns to zero, which causes the azimuth controller of the applicable aeronautical aircraft to be unable to control the tail rudder servo in time; in addition, the traditional azimuth controller applicable to the aeronautical aircraft is large in size and heavy in weight, which will consume energy when the aircraft is flying. energy, thereby reducing the flight time of the aircraft

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