Fixing, quick-dismounting and vibration-reducing structure for equipment in aircraft cockpit

Abstract

The utility model belongs to the technical field of fixing design of equipment in an aircraft cockpit, and particularly relates to a quick-release vibration reduction structure for fixing the equipment in the aircraft cockpit, a mechanism composed of a quick-release sleeve, a lock catch, a reset spring, a vibration reduction steel wire and a force bearing frame is designed to fix the equipment, the reset spring 5 and the vibration reduction steel wire have flexibility and can isolate vibration to a certain degree, and the vibration reduction effect is good. The vibration reduction steel wire is arranged in the force bearing frame, so that the vibration of the force bearing frame can be effectively reduced, and the vibration of a machine body structure is prevented from being directly transmitted to equipment through the force bearing frame, so that the equipment bears a relatively large vibration load, the working performance of the equipment is seriously influenced, and even the equipment is damaged due to vibration; the device can be quickly switched between a pressing state and a loosening state, the device is disassembled and assembled, the position of the device is adjusted, and convenience and high efficiency are achieved.

Description

Technical Field

[0001] This application belongs to the technical field of aircraft cockpit equipment fixing design, and particularly relates to a quick-release shock-absorbing structure for fixing equipment in an aircraft cockpit. Background Art

[0002] There are many control and observation devices such as instruments and gauges in the aircraft cockpit. Currently, most of them are installed on the load-bearing frame set in the cockpit by screwing the installation edges of the equipment, so as to fix the equipment in the cockpit. This technical solution has the following defects:

[0003] 1) The vibration of the airframe structure will be directly transmitted to the equipment through the load-bearing frame, causing the equipment to bear a large vibration load, seriously affecting the working performance of the equipment, and even causing vibration damage to the equipment;

[0004] 2) For different tasks and different pilots, there are different control and observation requirements. Therefore, it is necessary to frequently disassemble and assemble the equipment in the cockpit and adjust the position of the equipment to ensure the comfort of the pilot's work and enable the efficient control of the aircraft. During the process, the disassembly and assembly of a large number of screws are involved, and the process is cumbersome, time-consuming and laborious.

[0005] In view of the existence of the above technical defects, this application is proposed. Summary of the Invention

[0006] The purpose of this application is to provide a quick-release shock-absorbing structure for fixing equipment in an aircraft cockpit to overcome or mitigate at least one aspect of the known technical defects.

[0007] The technical solution of this application is as follows:

[0008] A quick-release shock-absorbing structure for fixing equipment in an aircraft cockpit includes:

[0009] A load-bearing frame, connected in the aircraft cockpit, on which multiple rows of quick-release holes are provided;

[0010] Multiple shock-absorbing steel wires, connected to the load-bearing frame, built into the load-bearing frame, and arranged along the radial direction through each row of quick-release holes;

[0011] Multiple quick-release sleeves, in a stepped shape; one end with a smaller radial dimension of each quick-release sleeve passes through the installation hole opened on the equipment installation edge and extends into a quick-release hole;

[0012] Multiple latches, with an axial guide groove at the front end, two circumferential card slots communicating with the axial guide groove on the side wall, and a protruding part on the outer wall at the rear end; the front end of each latch passes through the quick-release sleeve and extends into the installation hole;

[0013] Multiple return springs, sleeved on the outer periphery of each latch, located between the stepped part of the quick-release sleeve and the protruding part of the latch;

[0014] Each latch has:

[0015] In the pressed state, press the latch to compress the protruding part against the return spring, rotate the latch to slide the damping wire into the axial guide groove, and then into the two circumferential card slots. Release the latch, and it will reset under the elastic force of the return spring, tighten the damping wire, press the return spring against the step part of the quick-release sleeve, and the quick-release sleeve presses against the equipment installation edge to fix the equipment on the load-bearing frame;

[0016] In the released state, rotate the latch to slide each damping wire out of the circumferential card slot, and then slide it out through the axial guide groove. At this time, the quick-release sleeve can be taken out from the quick-release hole to release the fixation of the equipment on the load-bearing frame.

[0017] According to at least one embodiment of the present application, in the above-mentioned quick-release damping structure for fixing equipment in the aircraft cockpit, the smaller-diameter end of each quick-release sleeve shrinks inward and is in inclined surface contact with the rear end of the latch.

[0018] According to at least one embodiment of the present application, in the above-mentioned quick-release damping structure for fixing equipment in the aircraft cockpit, each latch has a slotted cross-head at its rear end.

[0019] According to at least one embodiment of the present application, in the above-mentioned quick-release damping structure for fixing equipment in the aircraft cockpit, the axial guide groove on each latch deviates from the center position of the latch.

[0020] According to at least one embodiment of the present application, in the above-mentioned quick-release damping structure for fixing equipment in the aircraft cockpit, the side walls of the axial guide groove and the circumferential card slot on each latch are arc-shaped, with a smooth transition between the axial guide groove and the circumferential card slot, and the end of the circumferential card slot facing away from the axial guide groove is inclined downward.

[0021] According to at least one embodiment of the present application, in the above-mentioned quick-release damping structure for fixing equipment in the aircraft cockpit, the angle of each circumferential card slot on the latch in the circumferential direction does not exceed 90°.

[0022] The present application has at least the following beneficial technical effects:

[0023] Provided is a quick-release vibration-damping structure for fixing equipment in an aircraft cabin. The design utilizes a mechanism consisting of a quick-release sleeve, a lock buckle, a return spring, a vibration-damping steel wire, and a load-bearing frame to fix the equipment. The return spring 5 and its vibration-damping steel wire are flexible and can isolate a certain degree of vibration. The vibration-damping steel wire is built into the load-bearing frame, which can effectively reduce the vibration of the load-bearing frame and avoid the vibration of the aircraft structure being directly transmitted to the equipment through the load-bearing frame, causing the equipment to bear a large vibration load, seriously affecting the working performance of the equipment, and even causing vibration damage to the equipment. In addition, by pressing and rotating the lock buckle, the equipment can be quickly switched between a tightened state and a loosened state, and the equipment can be disassembled and assembled, and the position of the equipment can be adjusted, which is convenient and efficient. BRIEF DESCRIPTION OF THE DRAWINGS

[0024] Figure 1 is a schematic diagram of a quick-release vibration reduction structure for fixing equipment in an aircraft cabin provided by an embodiment of the present application;

[0025] Figures 2 - 3 It is a partial schematic diagram of a quick-release vibration reduction structure for fixing equipment in an aircraft cabin provided by an embodiment of the present application;

[0026] Figure 4 is a partial cross-sectional view of a quick-release vibration reduction structure for fixing equipment in an aircraft cabin provided by an embodiment of the present application;

[0027] in:

[0028] 1- load-bearing frame; 2- vibration-damping steel wire; 3- quick-release sleeve; 4- lock buckle; 5- return spring;

[0029] A- axial guide groove; B- circumferential groove.

[0030] In order to better illustrate the present embodiment, some parts of the drawings may be omitted, enlarged or reduced, and do not represent the size of the actual product. In addition, the drawings are only used for illustrative purposes and should not be construed as limitations on the present application. DETAILED DESCRIPTION

[0031] In order to make the technical solution and advantages of the present application clearer, the technical solution of the present application will be described in further detail in detail and in detail with reference to the accompanying drawings. It can be understood that the specific embodiments described here are only partial embodiments of the present application, which are only used to explain the present application, not to limit the present application. It should be noted that, for the convenience of description, only the parts related to the present application are shown in the accompanying drawings, and other related parts can refer to the general design.

[0032] In addition, unless otherwise defined, the technical terms or scientific terms used in the description of this application should have the ordinary meanings understood by those of ordinary skill in the art to which this application belongs. The terms indicating directions used in the description of this application are only used to represent relative directions or positional relationships. When the absolute position of the object being described changes, its relative positional relationship may also change accordingly. The "including" used in the description of this application means that the elements or objects appearing before this word cover the elements or objects listed after this word and their equivalents, without excluding other elements or objects.

[0033] In addition, it should be noted that, unless otherwise clearly specified and limited, the terms such as "installation" and "connection" used in the description of this application should be understood in a broad sense. For example, connection can be a fixed connection or a detachable connection; it can be a mechanical connection or an electrical connection; it can be directly connected or indirectly connected through an intermediate medium. Those skilled in the art can understand their specific meanings in this application according to specific circumstances.

[0034] A quick-release shock-absorbing structure for fixing equipment in an aircraft cockpit, comprising:

[0035] A load-bearing frame 1, connected inside the aircraft cockpit, on which multiple rows of quick-release holes are provided; the load-bearing frame 1 can be specifically designed as a frame structure, and the number and distribution positions of the quick-release holes on it can be designed according to the needs of equipment fixation;

[0036] Multiple shock-absorbing steel wires 2, connected to the load-bearing frame 1, built inside the load-bearing frame 1, and arranged along the radial direction through each row of quick-release holes; both ends of the shock-absorbing steel wires 2 can be welded to the load-bearing frame 1 or connected to the load-bearing frame 1 through nuts;

[0037] Multiple quick-release sleeves 3, in a stepped shape; one end with a smaller radial dimension of each quick-release sleeve 3 passes through the installation hole opened on the equipment installation side and extends into a quick-release hole. Specifically, which quick-release hole to choose can be determined according to the equipment fixation position;

[0038] Multiple latches 4, with an axial guide groove A at the front end and two circumferential card slots B communicating with the axial guide groove on the side wall, and a protruding part on the outer wall at the rear end; the front ends of each latch 4 pass through the quick-release sleeve 3 and extend into the installation hole;

[0039] Multiple return springs 5, sleeved on the outer periphery of each latch 4, located between the stepped part of the quick-release sleeve 3 and the protruding part of the latch 4;

[0040] Each latch 4 has:

[0041] In the pressed state, press the latch 4 to compress the protruding part against the return spring 5, rotate the latch 4 clockwise, so that the damping wire 2 slides into the axial guide groove A, and then into the two circumferential clamping grooves B. Release the latch 4, and it will reset under the elastic force of the return spring 5, tighten the damping wire 2, so that the return spring 5 is pressed against the step part of the quick-release sleeve 3, and the quick-release sleeve 3 is pressed against the equipment installation edge, thereby fixing the equipment on the load-bearing frame 1;

[0042] In the released state, rotate the latch 4 counterclockwise to slide each damping wire 2 out of the circumferential clamping groove B, and then slide out through the axial guide groove A. At this time, the quick-release sleeve 3 can be taken out from the quick-release hole, releasing the fixation of the equipment on the load-bearing frame 1. During this process, the latch 4 can be pressed to compress the protruding part against the return spring 5. After releasing the latch 4, it can automatically reset under the elastic force of the return spring 5.

[0043] The aircraft cockpit equipment fixing and quick-release damping structure disclosed in the above embodiment is designed to fix the equipment by using the mechanism composed of the quick-release sleeve 3, the latch 4, the return spring 5, the damping wire 2 and the load-bearing frame 1. The return spring 5 and its damping wire 2 are flexible, which can isolate a certain degree of vibration, and the damping wire 2 is built into the load-bearing frame 1, which can effectively reduce the vibration of the load-bearing frame 1 and avoid the vibration of the airframe structure being directly transmitted to the equipment through the load-bearing frame 1, causing the equipment to bear a large vibration load, seriously affecting the working performance of the equipment, and even causing vibration damage to the equipment.

[0044] In addition, by pressing and rotating the latch 4, it can be quickly switched between the pressed state and the released state, disassembling and assembling the equipment, and adjusting the position of the equipment, which is convenient and efficient.

[0045] In some alternative embodiments, in the above aircraft cockpit equipment fixing and quick-release damping structure, the smaller-diameter end of each quick-release sleeve 3 shrinks inward and is in inclined surface contact with the rear end of the latch 4 to be able to limit the position of the latch 4.

[0046] In some alternative embodiments, in the above aircraft cockpit equipment fixing and quick-release damping structure, each latch 4 has a slotted crosshead at its rear end, so that a flat-blade screwdriver can be used to conveniently press and rotate the latch 4.

[0047] In some alternative embodiments, in the above aircraft cockpit equipment fixing and quick-release damping structure, the axial guide groove A on each latch 4 deviates from the center position of the latch 4.

[0048] In some alternative embodiments, in the above-described fixed quick-release vibration damping structure for in-aircraft cockpit equipment, the side walls of the axial guiding grooves A and the circumferential clamping grooves B on each latch 4 are arc-shaped, and there is a smooth transition between the axial guiding grooves A and the circumferential clamping grooves B, so as to facilitate the smooth sliding of the vibration damping wire 2 between the axial guiding grooves A and the circumferential clamping grooves B. Moreover, one end of the circumferential clamping groove B facing away from the axial guiding groove A is inclined downward. In this way, when the latch 4 is in the pressed state, the vibration damping wire 2 can be effectively clamped, and the latch 4 can be limited in the pressed state.

[0049] In some alternative embodiments, in the above-described fixed quick-release vibration damping structure for in-aircraft cockpit equipment, the angle of each circumferential clamping groove B on the latch 4 in the circumferential direction does not exceed 90°. In this way, through a relatively small rotation, the transformation between the pressed state and the released state of the latch 4 can be realized, and the equipment can be disassembled and assembled quickly.

[0050] So far, the technical solutions of the present application have been described in conjunction with the preferred embodiments shown in the drawings. Those skilled in the art should understand that the protection scope of the present application is obviously not limited to these specific embodiments. Without departing from the principle of the present application, those skilled in the art can make equivalent changes or substitutions to the relevant technical features, and the technical solutions after these changes or substitutions will fall within the protection scope of the present application.

Claims

1. An aircraft cockpit equipment fixed quick-release vibration damping structure, characterized in that, Comprising: A load-bearing frame (1), connected inside the aircraft cockpit, on which multiple rows of quick-release holes are provided; Multiple damping steel wires (2), connected to the load-bearing frame (1), built inside the load-bearing frame (1), and arranged along the radial direction through each row of quick-release holes; Multiple quick-release sleeves (3), in a stepped shape; one end with a smaller radial dimension of each quick-release sleeve (3) passes through the mounting hole opened on the equipment mounting edge and extends into a quick-release hole; Multiple latches (4), with an axial guide groove (A) at the front end and two circumferential card slots (B) communicating with the axial guide groove on the side wall, and a protruding part on the outer wall at the rear end; the front end of each latch (4) passes through the quick-release sleeve (3) and extends into the mounting hole; Multiple return springs (5), sleeved on the outer circumference of each latch (4), located between the stepped part of the quick-release sleeve (3) and the protruding part of the latch (4); Each latch (4) has: A compressed state, pressing the latch (4) to compress the protruding part against the return spring (5), rotating the latch (4) to make the damping steel wire (2) slide into the axial guide groove (A), and then slide into the two circumferential card slots (B), releasing the latch (4), and resetting under the elastic force of the return spring (5) to tighten the damping steel wire (2), pressing the return spring (5) against the stepped part of the quick-release sleeve (3), and the quick-release sleeve (3) pressing against the equipment mounting edge, thereby fixing the equipment on the load-bearing frame (1); A released state, rotating the latch (4) to make each damping steel wire (2) slide out of the circumferential card slot (B), and then slide out through the axial guide groove (A). At this time, the quick-release sleeve (3) can be taken out from the quick-release hole to release the fixation of the equipment on the load-bearing frame (1).

2. The quick-release damping structure for fixing equipment inside the aircraft cockpit according to claim 1, wherein One end with a smaller radial dimension of each quick-release sleeve (3) contracts inward and is in inclined surface contact with the rear end of the latch (4).

3. The quick-release damping structure for fixing equipment inside the aircraft cockpit according to claim 1, wherein Each latch (4) has a slotted head at the rear end.

4. The quick-release damping structure for fixing equipment inside the aircraft cockpit according to claim 1, wherein The axial guide groove (A) on each latch (4) deviates from the center position of the latch (4).

5. The quick-release damping structure for fixing equipment inside the aircraft cockpit according to claim 1, wherein The side walls of the axial guide groove (A) and the circumferential card slot (B) on each latch (4) are arc-shaped, with a smooth transition between the axial guide groove (A) and the circumferential card slot (B), and one end of the circumferential card slot (B) facing away from the axial guide groove (A) is inclined downward.

6. The quick-release damping structure for fixing equipment inside the aircraft cockpit according to claim 1, wherein The angle of the circumferential card slot (B) on each latch (4) in the circumferential direction does not exceed 90°.

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