Self-adaptive bolt lock support structure

Abstract

The invention belongs to the field of aircraft structure design, and particularly relates to a self-adaptive bolt lock support structure. According to the structure, a movable support is fixedly installed on a cabin door, a first connector is arranged on the movable support, an installation hole is formed in the first connector, and a joint bearing is installed in the installation hole; the limiting stop piece is fixedly connected with the movable support and is provided with a first limiting part and a second limiting part, the deflection angle of the inner ring of the knuckle bearing is limited through the first limiting part, and the outer ring of the knuckle bearing is limited through the second limiting part; the fixed support is fixedly installed on the machine body, a second connector is arranged on the fixed support, a plug pin hole is formed in the second connector, and when the cabin door is closed, the plug pin hole is aligned to the bearing hole of the knuckle bearing; and the bolt penetrates through the bearing hole of the knuckle bearing and the bolt hole to finish locking. The limiting blocking pieces are installed on the two sides of the movable support, the knuckle bearing can be prevented from being disengaged when the plug pin is inserted, and the situation that the deflection angle of the knuckle bearing is too large to block the plug pin hole is prevented.

Description

Technical Field

[0001] The present application belongs to the field of aircraft structure design, and in particular relates to an adaptive latch lock support structure. Background Art

[0002] A transport aircraft has an oversized cargo door. The door moves in a fixed-axis rotation form, and some locking points are far away from the door's rotation axis. The door is locked to the fuselage structure through multiple latch locks. The support is installed on the door structure and rotates around the rotation axis with the door, and the latch lock is fixedly installed on the fuselage end frame. In the theoretical closed position of the door, the latch hole on the support should be coaxial with the latch lock pin, but the door will be affected by gust loads, gravity, drive loads, etc. during the closing process. Limited by its own stiffness, manufacturing, assembly errors and other factors, there will be a certain deviation between the latch hole on the support and the latch lock axis. And due to the uncertainty of the direction and size of the gust load and the difference in stiffness at each position of the door. The direction and size of each latch deviation are also uncertain. This affects the locking of the latch lock.

[0003] Currently, most existing aircraft use a method where a large tapered guide structure is set on the latch part, and a copper bushing is pressed into the latch hole of the support part. However, this method cannot make the latch coaxial with the latch hole on the support, and can only be inserted by force. The non-coaxiality leads to a large friction between the bushing and the latch during the insertion of a single locking point, which causes serious wear of the bushing and makes it difficult to insert the latch. Locking multiple locking points at the same time may even tear the structures from each other, which has a great impact on the cabin door structure.

[0004] Therefore, it is desired to have a technical solution to overcome or at least alleviate at least one of the above-mentioned defects of the prior art. Summary of the invention

[0005] The purpose of the present application is to provide an adaptive latch lock support structure to solve at least one problem existing in the prior art.

[0006] The technical solution of this application is:

[0007] An adaptive latch lock support structure, comprising:

[0008] A movable support, the movable support is fixedly mounted on the hatch, the movable support is provided with a first joint, the first joint is provided with a mounting hole, and a spherical bearing is installed in the mounting hole;

[0009] A limit stopper, the limit stopper is fixedly connected to the movable support, the limit stopper has a first limit portion and a second limit portion, the first limit portion is used to limit the deflection angle of the inner ring of the spherical bearing, and the second limit portion is used to limit the outer ring of the spherical bearing;

[0010] A fixed support, the fixed support is fixedly mounted on the fuselage, the fixed support is provided with a second joint, the second joint is provided with a latch hole, and when the cabin door is closed, the latch hole is aligned with the bearing hole of the joint bearing;

[0011] A latch pin is passed through the bearing hole of the spherical bearing and the latch pin hole to complete the locking.

[0012] In at least one embodiment of the present application, the movable support is a 7050 aluminum alloy machined part.

[0013] In at least one embodiment of the present application, the first connector is a single-ear connector.

[0014] In at least one embodiment of the present application, the spherical bearing is a standard part.

[0015] In at least one embodiment of the present application, the limit stopper is triangular in shape, and two limit stoppers are symmetrically fixed on two sides of the first joint by bolt groups.

[0016] In at least one embodiment of the present application, the first limiting portion has a first limiting surface close to the inner ring of the spherical bearing, and the second limiting portion has a second limiting surface close to the outer ring of the spherical bearing. The thickness of the first limiting portion is less than the thickness of the second limiting portion. By designing the thickness difference of the two limiting portions, a deflection space of the inner ring of the spherical bearing is formed between the first limiting surface and the second limiting surface.

[0017] In at least one embodiment of the present application, the deflection space of the inner ring of the spherical plain bearing is designed according to the maximum deviation of each position.

[0018] In at least one embodiment of the present application, the limit stopper is a stainless steel machined part.

[0019] In at least one embodiment of the present application, the fixed support is a 7050 aluminum alloy machined part.

[0020] In at least one embodiment of the present application, the second connector is a double-ear connector.

[0021] In at least one embodiment of the present application, the latch is a stainless steel machined part.

[0022] In at least one embodiment of the present application, a tapered guide structure is designed at the front end of the latch.

[0023] The invention has at least the following beneficial technical effects:

[0024] The adaptive latch lock support structure of the present application installs a joint bearing on the movable support so that the inner ring of the joint bearing will be coaxial with the latch under the action of the guide structure at the front end of the latch during the insertion of the latch into the movable support, thereby successfully locking the latch; limit stops are installed on both sides of the movable support, which can prevent the joint bearing from falling out when the latch is inserted, and control the adaptation angle of the joint bearing on the other hand to prevent the joint bearing from deflecting too much and blocking the latch hole. BRIEF DESCRIPTION OF THE DRAWINGS

[0025] Figure 1 It is a schematic diagram of the retraction of the latch of the adaptive latch lock support structure according to one embodiment of the present application;

[0026] Figure 2 It is a schematic diagram of a latch extension of an adaptive latch lock support structure according to an embodiment of the present application;

[0027] Figure 3 is a schematic diagram of a limit stopper in one embodiment of the present application;

[0028] Figure 4 It is a schematic diagram of a latch according to one embodiment of the present application.

[0029] in:

[0030] 1- movable support; 2- limit stopper; 3- fixed support; 4- latch; 5- joint bearing. DETAILED DESCRIPTION

[0031] In order to make the purpose, technical scheme and advantages of the implementation of this application clearer, the technical scheme in the embodiment of this application will be described in more detail below in conjunction with the drawings in the embodiment of this application. In the drawings, the same or similar reference numerals throughout represent the same or similar elements or elements with the same or similar functions. The described embodiments are part of the embodiments of this application, not all of them. The embodiments described below with reference to the drawings are exemplary and are intended to be used to explain this application, and should not be construed as limitations on this application. Based on the embodiments in this application, all other embodiments obtained by ordinary technicians in this field without making creative work are within the scope of protection of this application. The embodiments of this application are described in detail below in conjunction with the drawings.

[0032] In the description of the present application, it should be understood that the terms "center", "longitudinal", "lateral", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside", etc., indicating orientations or positional relationships, are based on the orientations or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the present application and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore should not be understood as limiting the scope of protection of the present application.

[0033] The following is combined with Figure 1 to Figure 2 This application is described in further detail.

[0034] The present application provides an adaptive latch lock support structure, comprising: a movable support 1, a limit stopper 2, a fixed support 3 and a latch 4.

[0035] Specifically, Figure 1-2 As shown, the movable support 1 is fixedly mounted on the cabin door, a first joint is provided on the movable support 1, a mounting hole is opened on the first joint, and a spherical bearing 5 is installed in the mounting hole.

[0036] In the preferred embodiment of the present application, the first joint is a single-ear joint. The spherical bearing 5 is a standard part, and the spherical bearing 5 includes a spherical bearing outer ring, a spherical bearing inner ring and a bearing hole. The spherical bearing inner ring can not only rotate around the axis, but also deflect relative to the spherical bearing outer ring.

[0037] The limit stopper 2 is fixedly connected to the movable support 1, and the limit stopper 2 has a first limit part and a second limit part. The deflection angle of the inner ring of the joint bearing 5 is limited by the first limit part, and the outer ring of the joint bearing 5 is limited by the second limit part; the fixed support 3 is fixedly installed on the fuselage, and a second joint is provided on the fixed support 3. The second joint is provided with a latch hole. When the cabin door is closed, the latch hole is aligned with the bearing hole of the joint bearing 5; the latch 4 passes through the bearing hole of the joint bearing 5 and the latch hole to complete the locking.

[0038] In a preferred embodiment of the present application, the limit stopper 2 is triangular, and two limit stoppers 2 are symmetrically fixedly installed on both sides of the first joint by bolt groups. Figure 3 As shown, the first limiting portion of the limiting stopper 2 has a first limiting surface a close to the inner ring of the spherical bearing 5, and the second limiting portion has a second limiting surface b close to the outer ring of the spherical bearing 5. The thickness of the first limiting portion is less than the thickness of the second limiting portion. By designing the thickness difference of the two limiting portions, a deflection space for the inner ring of the spherical bearing 5 is formed between the first limiting surface a and the second limiting surface b.

[0039] In this embodiment, the second joint on the fixed support 3 is a double-ear joint. Advantageously, Figure 4As shown, the front end of the latch pin 4 is designed with a conical guide structure.

[0040] The adaptive latch lock support structure of the present application has a movable support 1 that is a 7050 aluminum alloy machined part, a limit stopper 2 that is a stainless steel machined part, a fixed support 3 that is a 7050 aluminum alloy machined part, a latch 4 that is a stainless steel machined part, and a spherical bearing 5 that is a standard part. The processing technology is mature, the processing reliability is high, the cost is controllable, and the size and tolerance of the parts are easily guaranteed.

[0041] The adaptive latch lock support structure of the present application, the movable support 1 is fixedly installed on the cabin door structure, and moves with the opening / closing of the cabin door. The limit stopper 2 is fixedly connected to the movable support 1 through two bolt groups. On the one hand, the first limit profile a of the first limit part limits the deflection angle of the inner ring of the joint bearing 5 to prevent excessive deflection of the inner ring. On the other hand, the second limit profile b of the second limit part limits the outer ring of the joint bearing 5 to prevent the joint bearing 5 from slipping out. The latch 4 is installed on the fuselage mechanism side through the fixed support 3. After the cabin door is closed, the latch 4 extends out and passes through the bearing hole of the joint bearing installed on the movable support 1 to complete the locking. When the cabin door needs to be opened, the latch 4 retracts and the cabin door opens.

[0042] In the adaptive latch lock support structure of the present application, the first limiting profile a of the first limiting portion of the limiting stopper 2 needs to be designed in accordance with the deflection angle of the inner ring of the spherical bearing 5, and the deflection angle of the inner ring of the spherical bearing 5 needs to be designed according to the maximum deviation of each position. A conical guide structure is designed at the front end of the latch 4, and the conical guide structure can be inserted when the inner ring of the spherical bearing 5 reaches the maximum deflection angle. After the hatch is closed, the latch 4 extends out, and under the action of the conical guide structure at the front end of the latch 4, the bearing hole of the spherical bearing 5 is coaxial with the latch 4, and the latch 4 passes through the bearing hole of the spherical bearing on the movable support 1 to complete the locking.

[0043] The adaptive latch lock support structure of the present application has the following beneficial effects:

[0044] 1. By installing the spherical bearing 5 on the movable support 1, when the latch 4 is inserted into the movable support 1, the inner ring of the spherical bearing 5 will be coaxial with the latch 4 under the action of the guide structure at the front end of the latch 4, thereby locking the latch smoothly.

[0045] 2. Limit stops 2 are installed on both sides of the movable support 1. On the one hand, they can prevent the joint bearing 5 from falling out when the pin 4 is inserted. On the other hand, they can control the adaptation angle of the joint bearing 5 to prevent the joint bearing 5 from deflecting too much and blocking the pin hole.

[0046] The adaptive latch lock support structure of the present application has been subjected to detailed design analysis, which shows that it fully meets the functional requirements, has a small number of parts, strong adaptability, good economy and assembly performance, and is applicable to lock supports that cooperate with latches for both civil and military aircraft cabin doors.

[0047] The above is only a specific implementation of the present application, but the protection scope of the present application is not limited thereto. Any changes or substitutions that can be easily thought of by a person skilled in the art within the technical scope disclosed in the present application should be included in the protection scope of the present application. Therefore, the protection scope of the present application shall be based on the protection scope of the claims.

Claims

1. An adaptive latch lock support structure, characterized in that: include: A movable support (1), the movable support (1) being fixedly mounted on the cabin door, the movable support (1) being provided with a first joint, the first joint being provided with a mounting hole, and a spherical bearing (5) being mounted in the mounting hole; a limit stopper (2), the limit stopper (2) being fixedly connected to the movable support (1), the limit stopper (2) comprising a first limit portion and a second limit portion, the first limit portion being used to limit the deflection angle of the inner ring of the spherical bearing (5), and the second limit portion being used to limit the outer ring of the spherical bearing (5); A fixed support (3), the fixed support (3) being fixedly mounted on the fuselage, the fixed support (3) being provided with a second joint, the second joint being provided with a latch hole, and when the cabin door is closed, the latch hole is aligned with the bearing hole of the joint bearing (5); The latch pin (4) passes through the bearing hole of the joint bearing (5) and the latch pin hole to complete the locking.

2. The adaptive latch lock support structure according to claim 1, characterized in that: The movable support (1) is a 7050 aluminum alloy machined part.

3. The adaptive latch lock support structure according to claim 2, characterized in that: The first connector is a single-ear connector.

4. The adaptive latch lock support structure according to claim 3, characterized in that: The spherical bearing (5) is a standard part.

5. The adaptive latch lock support structure according to claim 4, characterized in that: The limit stopper (2) is triangular in shape, and two limit stoppers (2) are symmetrically fixedly mounted on two sides of the first joint by means of bolt groups.

6. The adaptive latch lock support structure according to claim 5, characterized in that: The first limiting portion has a first limiting surface close to the inner ring of the spherical bearing (5), and the second limiting portion has a second limiting surface close to the outer ring of the spherical bearing (5). The thickness of the first limiting portion is less than the thickness of the second limiting portion. By designing the thickness difference of the two limiting portions, a deflection space for the inner ring of the spherical bearing (5) is formed between the first limiting surface and the second limiting surface.

7. The adaptive latch lock support structure according to claim 6, characterized in that: The deflection space of the inner ring of the spherical bearing (5) is designed according to the maximum deviation amount at each position.

8. The adaptive latch lock support structure according to claim 7, characterized in that: The position limiting stopper (2) is a stainless steel machined part.

9. The adaptive latch lock support structure according to claim 8, characterized in that: The fixed support (3) is a 7050 aluminum alloy machined part.

10. The adaptive latch lock support structure according to claim 9, characterized in that: The second connector is a double-ear connector.

11. The adaptive latch lock support structure according to claim 10, characterized in that: The latch (4) is a stainless steel machined part.

12. The adaptive latch lock support structure according to claim 11, characterized in that: The front end of the latch pin (4) is designed with a tapered guide structure.

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