CN218317297U - Quick release device for anti-torsion arm of airplane - Google Patents
Quick release device for anti-torsion arm of airplane Download PDFInfo
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- CN218317297U CN218317297U CN202222694090.1U CN202222694090U CN218317297U CN 218317297 U CN218317297 U CN 218317297U CN 202222694090 U CN202222694090 U CN 202222694090U CN 218317297 U CN218317297 U CN 218317297U
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Abstract
The application belongs to the field of design of an aircraft undercarriage, and particularly relates to a quick release device for an aircraft torsion-proof arm, wherein the tail end of an upper torsion-proof arm of the undercarriage is of a double-lug structure, and the tail end of a lower torsion-proof arm of the undercarriage is of a single-lug structure; each ear hole of the double-ear structure is provided with a first bushing, one end of the first bushing, which is positioned at the outer side of the double-ear structure, is an outer end, and the outer end is connected with a protective cover; a cavity for accommodating a compression spring is formed between the protective cover and the first bushing, one end of the compression spring is propped against the protective cover, and the other end of the compression spring is propped against the quick-release shaft; the quick-release shaft is inserted into the holes of the first bushing and the protective cover, the first end of the quick-release shaft extends into the hole of the upper torsion-proof arm under the pretightening force of the compression spring, and the second end of the quick-release shaft is exposed outside the protective cover; the second end is provided with a quick-release handle which is propped against the outer end of the protective cover to limit the quick-release shaft to move upwards to prevent the torsion arm; the quick-release handle is pulled outwards to overcome the pretightening force of the compression spring, and the quick-release shaft is separated from the hole of the upper torsion-proof arm.
Description
Technical Field
The application belongs to the field of design of aircraft undercarriages, and particularly relates to a quick release device for an aircraft torsion arm.
Background
Install preventing turning round arm structure on the aircraft undercarriage, often through bolted connection, at buffer compression and extension in-process, upper and lower prevent turning round the arm pivoting, undertake ground load (subtract pendulum), turning moment transmission (turn) effect, the existence of preventing the turning round arm has restricted aircraft ground wide-angle and has pull, restriction aircraft ground operation, under some circumstances, need prevent the arm and prevent turning round the arm down and carry out quick dismantlement to last, and traditional bolted connection can't realize.
SUMMERY OF THE UTILITY MODEL
In order to solve the above problems, the present application provides a quick release for an aircraft anti-torsion arm, connected between an upper anti-torsion arm and a lower anti-torsion arm of a landing gear; the tail end of the upper anti-twist arm is of a double-lug structure, and the tail end of the lower anti-twist arm is of a single-lug structure;
each ear hole of the double-ear structure is provided with a first bushing, one end of the first bushing, which is positioned on the inner side of the double-ear structure, is an inner end, the inner end is provided with a flanging, and the flanging limits the first bushing to be disengaged outwards along the axial direction; one end of the first bushing outside the double-lug structure is an outer end, and the outer end is connected with a protective cover; a cavity for accommodating a compression spring is formed between the protective cover and the first bushing, one end of the compression spring is propped against the protective cover, and the other end of the compression spring is propped against the quick-release shaft; the quick-release shaft is inserted into the holes of the first bushing and the protective cover, the first end of the quick-release shaft extends into the hole of the upper torsion arm under the pretightening force of the compression spring, and the second end of the quick-release shaft is exposed outside the protective cover; the second end is provided with a quick-release handle which is propped against the outer end of the protective cover to limit the quick-release shaft to move upwards to prevent the torsion arm; overcoming the pretightening force of the compression spring, pulling the quick-release handle outwards, and enabling the quick-release shaft to be separated from the hole of the upper torsion-proof arm.
Preferably, the connection of the quick release shaft and the anti-torque arm has a second bushing.
Preferably, a third bushing is installed at the joint between the quick release shaft and the protective cover.
Preferably, the quick release handle is mounted on the quick release shaft by a self-locking nut.
Preferably, a spacer is provided between the end of the protective cover and the lower anti-twist arm.
Preferably, the protective cover is connected with the first bushing through threads.
The device is positioned between the upper and lower anti-torsion arms of the nose landing gear of the airplane, the quick-release shaft is connected with the upper and lower anti-torsion arms, the requirement on roughness precision is high, and the quick-release and installation can be flexibly carried out by matching with good lubrication; the compression spring is arranged, and the pressing force ensures that the upper anti-torsion arm and the lower anti-torsion arm are reliably connected; the quick-release handle is fixed at two ends of the device through the locking nuts, so that the integrated movement of the quick-release shaft and the quick-release handle can be ensured, and the quick release and the installation are realized. The disengaging device is novel in design, simple in structure and high in safety, and achieves quick disengaging of the anti-torsion arm and large-angle traction of the ground of the airplane.
Drawings
FIG. 1 is a front elevational view of a preferred embodiment of the quick release device of the present application;
fig. 2 is a cross-sectional view of a preferred embodiment of the quick release mechanism of the present application.
Detailed Description
In order to make the implementation objects, technical solutions and advantages of the present application clearer, the technical solutions in the embodiments of the present application will be described in more detail below with reference to the drawings in the embodiments of the present application. 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 present application. The embodiments described below with reference to the accompanying drawings are exemplary and intended to be used for explaining the present application and should not be construed as limiting the present application. All other embodiments obtained by a person of ordinary skill in the art without any inventive work based on the embodiments in the present application are within the scope of protection of the present application. Embodiments of the present application will be described in detail below with reference to the drawings.
As shown in fig. 1-2, the present application provides a quick disconnect for an aircraft torsion arm, connected between an upper torsion arm 6 and a lower torsion arm 7 of a landing gear; the tail end of the upper anti-torsion arm 6 is of a double-lug structure, and the tail end of the lower anti-torsion arm 7 is of a single-lug structure;
each ear hole of the double-lug structure is provided with a first bushing 11, one end of the first bushing 11 on the inner side of the double-lug structure is an inner end, the inner end is provided with a flanging, and the flanging limits the first bushing 11 to be disengaged outwards along the axial direction; one end of the first bushing 11 outside the double-lug structure is an outer end, and the outer end is connected with the protective cover 3; a cavity for accommodating a compression spring 9 is formed between the protective cover 3 and the first bush 11, one end of the compression spring 9 is propped against the protective cover 3, and the other end of the compression spring is propped against the quick-release shaft 8; the quick-release shaft 8 is inserted into the first bush 11 and the hole of the protective cover 3, the first end of the quick-release shaft 8 extends into the hole of the upper torsion-proof arm 6 under the pretightening force of the compression spring 9, and the second end of the quick-release shaft 8 is exposed out of the protective cover 3; the second end is provided with a quick-release handle 2, the quick-release handle 2 props against the outer end of the protective cover 3 to limit the displacement of the quick-release shaft 8 upwards to the anti-torsion arm 6; overcoming the pretightening force of the compression spring, pulling the quick-release handle 2 outwards, and enabling the quick-release shaft 8 to be separated from the hole of the upper anti-twist arm 6. The connection of the quick release shaft 8 and the anti-torque arm 6 is provided with a second bushing 12. A third bushing 10 is arranged at the joint between the quick release shaft 8 and the protective cover 3. The quick-release handle 2 is arranged on the quick-release shaft 8 through the self-locking nut 1. A spacer 4 is provided between the end of the protective cover 3 and the lower anti-twist arm 7. The protective cover 3 is screwed to the first bush 11.
The action mechanism of the application is as follows: 1. in the conventional working states of retraction, extension and the like of the landing gear, the quick release device plays a role in connecting the upper anti-torsion arm and the lower anti-torsion arm, the protective cover 3 is fixed, the compression spring 9 compresses the quick-release shaft 8, the upper anti-torsion arm 6 and the lower anti-torsion arm 7 are connected through the quick-release shaft, and the anti-torsion arms rotate around the shafts in the process of compression and extension of the buffer, so that the ground load transmission and torque transmission functions of the anti-torsion arms are realized.
2. When the disengaging function is realized, the quick-release handle 2 is pulled outwards along two lateral sides, and the protective cover 10 is fixed, and the quick-release shaft 8 compresses the compression spring 9, so that the upper anti-torque arm 6 and the lower anti-torque arm 7 are separated from each other and are pulled out to the outer side of the shoulder of the second bushing 12, the upper anti-torque arm and the lower anti-torque arm are disengaged, the lower anti-torque arm is reversed downwards under the action of gravity torque, the upper anti-torque arm is turned upwards under the action of an upper device, and at the moment, the airplane can realize large-angle ground traction operation.
3. When the quick-release handle 2 is pulled outwards during installation, the quick-release shaft 8 is pulled outwards along with the quick-release handle until the end part is submerged or flush with the convex shoulder of the first bush 11, the second bush 12 in the lug holes of the upper anti-torsion arm 6 and the lower anti-torsion arm 7 is aligned with the inner hole of the first bush 11, the quick-release shaft is pressed into the lug hole of the upper anti-torsion arm under the action of the compression spring, and the upper anti-torsion arm and the lower anti-torsion arm are connected
The device breaks through the functional limitation of bolt connection torque arm on the premise of ensuring the conventional function, provides the quick-release function and realizes the large-angle turning operation of the airplane ground. The outer circle of the quick-release shaft 8 is in clearance fit with the inner hole of the second bush 12, and the quick-release function is guaranteed to be achieved through a lubricating measure and high roughness precision. The device is simple and reliable, has better universality and can be applied to the design of a large number of airplanes.
The above description is only for the specific embodiments of the present application, but the scope of the present application is not limited thereto, and any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope of the present application should be covered within the scope of the present application. Therefore, the protection scope of the present application shall be subject to the protection scope of the claims.
Claims (6)
1. A quick release device for anti-torsion arms of an aircraft, characterized in that it is connected between an upper anti-torsion arm (6) and a lower anti-torsion arm (7) of the undercarriage; the tail end of the upper anti-twist arm (6) is of a double-lug structure, and the tail end of the lower anti-twist arm (7) is of a single-lug structure;
each ear hole of the double-ear structure is internally provided with a first bushing (11), one end of the first bushing (11) at the inner side of the double-ear structure is an inner end, the inner end is provided with a flanging, and the flanging limits the first bushing (11) to be disengaged outwards along the axial direction; one end of the first bushing (11) on the outer side of the double-lug structure is an outer end, and the outer end is connected with a protective cover (3); a cavity for accommodating a compression spring (9) is formed between the protective cover (3) and the first bushing (11), one end of the compression spring (9) is propped against the protective cover (3), and the other end of the compression spring is propped against the quick-release shaft (8); the quick-release shaft (8) is inserted into the holes of the first bushing (11) and the protective cover (3), the first end of the quick-release shaft (8) extends into the hole of the upper anti-torsion arm (6) under the pretightening force of the compression spring (9), and the second end of the quick-release shaft (8) is exposed outside the protective cover (3); the second end is provided with a quick-release handle (2), the quick-release handle (2) props against the outer end of the protective cover (3) to limit the displacement of the quick-release shaft (8) upwards to the anti-torsion arm (6); the quick-release handle (2) is pulled outwards to overcome the pretightening force of the compression spring, and the quick-release shaft (8) is separated from the hole of the upper anti-twist arm (6).
2. Quick release device for anti-torsion arms of aircraft according to claim 1, characterized in that the junction of the quick-release shaft (8) and the anti-torsion arm (6) has a second bush (12).
3. Quick release device for anti-torsion arms of aircraft, according to claim 1, characterized in that the junction between the quick release shaft (8) and the protective cover (3) is fitted with a third bush (10).
4. Quick release device for anti-torsion arms of aircraft according to claim 1, characterized in that the quick release handle (2) is mounted on the quick release shaft (8) by means of a self-locking nut (1).
5. Quick release device for anti-torsion arms of aircraft, according to claim 1, characterized in that between the end of the protective shield (3) and the lower anti-torsion arm (7) there is a spacer (4).
6. Quick release device for anti-torsion arms of aircraft according to claim 1, characterized in that the connection between the protective cap (3) and the first bushing (11) is by means of a screw thread.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202222694090.1U CN218317297U (en) | 2022-10-12 | 2022-10-12 | Quick release device for anti-torsion arm of airplane |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202222694090.1U CN218317297U (en) | 2022-10-12 | 2022-10-12 | Quick release device for anti-torsion arm of airplane |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN218317297U true CN218317297U (en) | 2023-01-17 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202222694090.1U Active CN218317297U (en) | 2022-10-12 | 2022-10-12 | Quick release device for anti-torsion arm of airplane |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN218317297U (en) |
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2022
- 2022-10-12 CN CN202222694090.1U patent/CN218317297U/en active Active
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