Aircraft flap mechanism based on linear execution control
A linear execution, flap technology, applied in aircraft transmission, aircraft power transmission, aircraft power devices, etc., can solve the problems of flap drive control and flap position indication failure, limit switch positioning and fixing difficulties, etc. Achieve the effect of reducing the number of limit switches, light weight and novel structure
Pending Publication Date: 2020-11-03
九成通用飞机设计制造(大连)有限公司
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Problems solved by technology
This installation method, on the one hand, makes the positioning and fixing of the limit switch more difficult; on the other hand, the limit switch is also used as the feedback of the flap action angle and flap position indication. Once a mechanical or electrical failure occurs, it may cause the flap to drive. Both controls and flap position indications fail
Method used
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Embodiment 1
[0032] There are three positions for the flaps to be retracted. When the aircraft is in level flight, the flaps need to be fully retracted. When the aircraft takes off, the flaps need to be lowered to a certain angle. When the aircraft is landing, the flaps need to be fully lowered. like Figure 1-3 As shown, this embodiment provides an aircraft flap mechanism based on linear execution control, including an integrated support frame, a limit switch a, a limit switch b, and a flap motor. There are multiple sets of copper sleeves between the cover and the backing plate, and a pull rod is slidably connected between each set of copper sleeves. One end of the pull rod is connected with the push rod of the flap motor, and the flap motor is connected with Backing plate, the two sides of the backing plate are respectively provided with a limit switch a and a limit switch b for the middle angle limit of the flap, and the pull bar moves synchronously with the push rod of the flap motor, ...
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The invention discloses an aircraft flap mechanism based on linear execution control, and the mechanism comprises an integrated supporting frame, a limiting switch a, a limiting switch b and a flap motor; the integrated supporting frame comprises a cover located on a base plate, wherein a plurality of sets of copper sleeves are arranged between the cover and the base plate, and a pull rod is slidably connected between each set of copper sleeves; one end of the pull rod is connected with a push rod of a flap motor, a base plate is connected to the flap motor, and a limiting switch a and a limiting switch b are arranged on the two sides of the base plate respectively; a push rod of the flap motor is connected with a right driving rod through a rocker arm, the rocker arm is located on a rightdriving rotary disc, the right driving rotary disc is connected with a left driving rotary disc through a steel cable, the left driving rotary disc is connected with a rocker arm type connecting rod,and the rocker arm type connecting rod is connected with a potentiometer. The device is novel in structure, is light in weight, is low in cost, is high in reliability, and is simple in installation and debugging.
Description
technical field [0001] The invention belongs to the technical field of aircraft components, in particular to an aircraft flap mechanism based on linear execution control. Background technique [0002] Flap refers to an airfoil-shaped movable device on the edge of the modern wing. It can be installed on the trailing edge and leading edge of the wing, and can be deflected downward or slide backward. Its basic effect is to increase the area of the wing. Increased lift in flight. However, during the operation of the flaps, the cockpit cannot accurately read the position of the flaps, which will affect the flying attitude of the aircraft and make it difficult for the driver to control the aircraft. [0003] In the prior art, there are several implementation schemes for flap drive and flap position indication as follows: [0004] Option 1: Only use mechanical linkages to control the flaps of the aircraft, such as the Cubs; the mechanical flap control system is heavy and the te...
Claims
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IPC IPC(8): B64C13/50
CPCB64C13/50
Inventor 孙樵舒启明邓静尹戈戈
Owner 九成通用飞机设计制造(大连)有限公司