Airplane filler cap opening mechanism
A technology of opening mechanism and flap, applied in the direction of aircraft accessories, etc., can solve the problems of unsuitable application of medium and low speed aircraft or small drones, high complexity of control system, high cost of use and maintenance, and achieve simple structure and high failure rate Low, the effect of improving the service life
Active Publication Date: 2016-12-14
JIANGXI HONGDU AVIATION IND GRP
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- Claims
- Application Information
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Problems solved by technology
The flap opening mechanism is widely used in current aircraft, especially the new generation of stealth fighters, which need a reliable flap opening mechanism when performing aerial refueling or combat missions, but the flap opening mechanism used in advanced fighters usually has a structural form Complexity, high complexity of the control system, high cost of use and maintenance, and cannot be properly applied to low-to-medium speed aircraft or small UAVs for some special tasks
Method used
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Embodiment
[0018] Example: see figure 1 — figure 2 .
[0019] An aircraft flap opening mechanism, which includes a push rod 3, a limit angle piece 4 connected with a fuselage frame 2 and a pre-tightening mechanism, the flap 1 is the object to be opened by the present invention, and the fuselage frame 2 is the object of the present invention In the installation position, the ejector rod 3 and the spring 7 are the main working components of the present invention. The ejector rod 3 can open the mouth cover stably and reliably under the action of the spring 7. The upper part of the ejector rod 3 is provided with a boss, and the upper end of the ejector rod 3 passes through Over the limit angle piece 4, and through the limit angle piece 4 upper limit, the limit angle piece 4 is connected with the fuselage frame 2 through the connecting piece 9,
[0020] The pre-tensioning mechanism includes a spring 7 and an adjusting sleeve 8 , the adjusting sleeve 8 is connected to the bottom plate of th...
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The invention discloses an airplane filler cap opening mechanism which comprises an ejector rod, a limiting corner plate connected with an airplane body frame, and a pre-tightening mechanism. The airplane filler cap opening mechanism is characterized in that a boss is arranged on the middle-upper portion of the ejector rod, the upper end of the ejector rod penetrates through the limiting corner plate, and the ejector rod is limited by the limiting corner plate. The pre-tightening mechanism comprises a spring and an adjusting sleeve, wherein the adjusting sleeve is connected with an airplane body bottom plate, and the portion between the boss of the ejector rod and the adjusting sleeve is sleeved with the spring. The airplane filler cap opening mechanism is simple in structure, low in failure rate and convenient to realize; the spring and the ejector rod are adopted as the main body of the opening mechanism, the opening torque of the ejector rod is adjusted through the adjusting sleeve, and with airplane filler cap restraint states as control conditions, work can be achieved without an extra complex control system.
Description
technical field [0001] The invention belongs to the field of aircraft structure design and relates to an aircraft flap opening mechanism. Background technique [0002] Covers are widely used in the aircraft field. For the equipment and accessories that need to be inspected, repaired, adjusted, filled, disassembled or replaced during the use and maintenance of the aircraft, the body structure is equipped with a cover. It is generally required that when the aircraft is stopped, all flaps should be able to open normally no matter what compression state the landing gear is in. A stable and reliable flap opening mechanism is needed to assist flap opening. The flap opening mechanism is widely used in current aircraft, especially the new generation of stealth fighters, which need a reliable flap opening mechanism when performing aerial refueling or combat missions, but the flap opening mechanism used in advanced fighters usually has a structural form Complexity, high complexity o...
Claims
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Patent Timeline
Login to View More IPC IPC(8): B64C1/14
CPCB64C1/14
Inventor 陈龙辉付杰斌张伟吉先武王强卢维富徐环宇胡定红李伟东王斌李灿山
Owner JIANGXI HONGDU AVIATION IND GRP