Positioning structure for hook lock and adjusting method thereof
Through the embedded hook lock structure, combined with the hook lock support, lock ring support and stop pin assembly, the hook lock protrusion is solved, and the hook lock protrusion is insufficient, achieving three-dimensional adjustment and stable hook state, which is suitable for reliable connection of aircraft head fairing.
Patent Information
- Application Number
- CN202510537226.3
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- Filing Date
- 2025-04-27
- Publication Date
- 2025-07-18
AI Technical Summary
The existing hook lock structure protrudes the shape of the head, increases aerodynamic resistance, lacks limit and guidance functions, and lacks three-dimensional adjustment capabilities. The lock hook shakes and is unstable during flight.
It adopts an embedded hook lock structure, including a hook and lock support assembly, a lock ring support assembly and a stop pin assembly, and has three-dimensional adjustment function. The spring blade is used to ensure that the lock hook automatically pops up in the open state. The stop pin provides limiting and guiding functions to ensure that the lock hook is stable in the closed state.
It realizes the embedded installation of the hook lock, reduces aerodynamic resistance, and has three-dimensional adjustment capabilities, ensuring that the lock hook is stable during flight and simple to operate, and is suitable for reliable connection between the nose fairing and the fuselage structure.
Smart Images
Figure CN120327768A_ABST
Abstract
Description
Technical Field
[0001] The present invention belongs to the technical field of airframe structure design, and particularly relates to a positioning structure for a hook lock and an adjustment method thereof. Background Art
[0002] Since various electronic devices such as radomes are often arranged inside the nose fairing of an aircraft, and the devices need maintenance, the nose fairing needs to be opened to facilitate maintenance operations by maintenance personnel; the nose fairing and the airframe structure are often connected by screwing or hinges to meet different maintenance requirements. Screwing is applicable to occasions with low maintenance frequency. At this time, maintenance personnel need to lift the entire nose fairing to perform maintenance operations; hinge connection is applicable to occasions with high maintenance frequency. At this time, maintenance personnel rotate and open the nose fairing to perform maintenance operations. When using a hinge connection, the nose fairing of an aircraft often uses a hook lock to meet the locking requirement.
[0003] Most of the existing hook lock structures protrude and are fixed outside the nose shape, increasing the aerodynamic drag; when the hook lock is connected to the nose fairing and the airframe structure, it lacks limiting and guiding functions, and often only has the adjustment ability in a single direction; when the hook lock is in the open state, its locking hook cannot automatically pop out, and when the hook lock is in the locked state, its locking hook is not stable and shakes during the flight of the aircraft. In order to keep the nose shape smooth and meet the shaping requirements, the hook lock should use an embedded installation structure form; to compensate for the errors caused by the assembly of the airframe structure, the hook lock should have a three-dimensional adjustment function in addition to reliable limiting and guiding functions; to ensure the correct state of the hook lock in the open state of the hook lock, the hook lock needs to have an automatic pop-out function; the hook lock needs to ensure a stable state and cannot shake in the closed state of the hook lock.
[0004] Therefore, a positioning structure for a hook lock is needed. Summary of the Invention
[0005] In order to solve the technical problems in the prior art that the hook lock protrudes from the shape, the connection structure between the hook lock and the nose fairing and the airframe structure has poor limiting and guiding effects, poor three-dimensional adjustment ability, the locking hook of the hook lock cannot automatically pop out, and it cannot remain stable during flight, the present invention provides a positioning structure for a hook lock and an adjustment method thereof, which realizes the shaping requirements of the nose and can realize the guiding, limiting and three-dimensional adjustment functions of the hook lock, ensuring the safe, reliable and convenient assembly of the hook lock. The technical solutions are as follows:
[0006] In a first aspect, a positioning structure for a hook lock is provided, including: a hook lock support assembly 3, a lock ring support assembly 4, and a stop pin assembly 5.
[0007] The hook lock 1 of the hook lock is fixed on the nose cowl assembly 6 through the hook lock support assembly 3, and the adjustable lock ring 2 of the hook lock is fixed on the cockpit cover assembly 7 through the lock ring support assembly 4; the stop pin assembly 5 connects the hook lock support assembly 3 and the lock ring support assembly 4;
[0008] The hook lock support assembly 3 includes: a hook lock support 8 and a spring plate 13, and the spring plate 13 is riveted to the hook lock support 8;
[0009] The stop pin assembly 5 includes: a plurality of adjusting washers 29, a fixed washer 31, and a stop pin 32; the plurality of adjusting washers 29 and the fixed washer 31 form a stop plate, and the plurality of adjusting washers 29 and the fixed washer 31 are provided with guiding and limiting holes for the stop pin 32; the plurality of adjusting washers 29 and the fixed washer 31 are fixed on the cockpit cover assembly 7; one end of the stop pin 32 is fixed on the nose cowl assembly 6, and the other end is provided with a tapered head 42, and the tapered head 42 makes it easier for the stop pin 32 to be inserted into the guiding and limiting holes of the plurality of adjusting washers 29 and the fixed washer 31 at the moment of its contact with the fixed washer 31; the stop pin 32 is provided with a retaining tooth 43 for limiting the nose cowl assembly 6, and the retaining tooth 43 limits the nose cowl assembly 6 to a certain position by contacting the fixed washer 31 and the lock ring support 18.
[0010] The hook lock protruding from the nose shape not only increases the aerodynamic drag but also is not aesthetically pleasing. In order to keep the nose shape smooth and meet the shaping requirements, the hook lock should use an embedded installation structure form; to compensate for the errors caused by the assembly of the airframe structure, the hook lock should have a three-dimensional adjustment function in addition to having a reliable limiting function and guiding function; to ensure the correct hook lock state when the hook lock is in the open state, the hook lock needs to have an automatic pop-up function; when the hook lock is in the closed state, the hook lock needs to ensure a stable state without shaking.
[0011] Among them, the hook lock support 8 is provided with a groove for embedding the hook lock 1;
[0012] After the hook lock is closed, the lock hook does not shake under the reaction force of the spring plate 13, and after the hook lock is opened, the lock hook of the hook lock can automatically pop open under the reaction force of the spring plate 13;
[0013] The plurality of adjusting washers 29 and the fixed washer 31 are fixed on the cockpit cover assembly 7 through bolts 33, and a part of the adjusting washers 29 is located outside the cockpit cover assembly 7, and another part of the adjusting washers 29 is located inside the cockpit cover assembly 7.
[0014] Furthermore, the hook lock support assembly 3 further includes: a hook lock pin shaft 9; the hook lock 1 is connected to the hook lock support 8 through the hook lock pin shaft 9; the hook lock pin shaft 9 is fixed on the hook lock support 8 to prevent the hook lock 1 of the hook lock from falling off.
[0015] Among them, the hook lock support 8 is provided with a first mounting plane 15 and a second mounting plane 16 for the stop pin assembly 5. The first mounting plane 15 and the second mounting plane 16 are perpendicular to the mounting direction of the stop pin assembly 5. To improve the stiffness and bending resistance of the structure near the first mounting plane 15 and the second mounting plane 16, the hook lock support 8 is provided with vertical ribs 17 to bear the acting force brought by the stop pin assembly 5.
[0016] Among them, the material of the spring piece 13 is 65Mn, the thickness is 0.8 mm, and the Rockwell hardness after heat treatment is 40 - 45 HRC.
[0017] Among them, the lock ring support assembly 4 includes: a lock ring support 18 and a toothed plate 19; the guide block 23 in the adjustable lock ring 2 is screwed to the toothed plate 19 and the lock ring support 18 through bolts 20. The bolts 20 are provided with mounting holes for lock wires 30; the toothed plate 19 is riveted to the lock ring support 18 and the cockpit cover assembly 7.
[0018] The toothed plate 19 is provided with countersunk head rivet counterbore holes 25, bolt through holes 28, relief grooves 27 for CHC screws 26, and adjusting teeth 24 arranged in the U direction. At the countersunk head rivet counterbore holes 25, the toothed plate 19, the lock ring support 18 and the cockpit cover assembly 7 are riveted together with countersunk head rivets, and the countersunk head rivets do not protrude from the surface of the toothed plate 19, so as not to affect the assembly of the guide block 23 in the adjustable lock ring 2 and the toothed plate 19; the bolt through holes 28 are circular holes. The guide block 23 in the adjustable lock ring 2, the toothed plate 19, the lock ring support 18 and the cockpit cover assembly 7 are connected through the bolt through holes 28. At this time, the adjustable lock ring 2 is fixed to the cockpit cover assembly 7; the guide block 23 is provided with adjusting teeth arranged in the U direction, and the bolt through holes 28 are waist-shaped holes along the W direction; the lock ring support assembly 4 has the functions of adjusting along the U direction and along the W direction; the adjustment step of the adjusting teeth on the toothed plate 19 and the adjusting teeth on the guide block 23 is 0.75 mm, and the adjustment range is -3 mm to +3 mm.
[0019] Among them, both sides of the stop pin 32 are provided with operation planes 40 to facilitate operation tools such as wrenches to clamp the operation planes 40 on both sides, so as to turn the stop pin 32 or the slotted nut 37 to adjust the tightening torque. One end of the stop pin 32 is provided with a thread 41 for fixing to the nose cover assembly 6.
[0020] Among them, the fitting relationship between the stop pin 32 and the hole on the hook lock support 8 is H7 / g6.
[0021] Among them, the thickness of each adjusting shim 29 is 0.5 mm.
[0022] In a second aspect, a method for adjusting a positioning structure for a hook lock is provided, including:
[0023] When the nose cowl assembly 6 is closed, the stop pin 32 contacts the cockpit canopy assembly 7. At the same time, the number of shims 29 on the outer and inner sides of the cockpit canopy assembly 7 is adjusted to regulate the gap between the cockpit canopy assembly 7 and the nose cowl assembly 6 until the design requirements are met, while the length of the bolt 33 remains unchanged.
[0024] The beneficial effects of the present invention are at least as follows:
[0025] 1) Aerodynamic shape: The embedded hook lock installation structure does not protrude from the outer shape and has an aerodynamic shape function, reducing the aerodynamic drag.
[0026] 2) Convenient assembly: The embedded hook lock installation structure has a three-dimensional adjustment function after comprehensive use, can compensate for the assembly error of the airframe structure, ensure reliable installation of the nose cowl, uniform step difference, and uniform compression of the sealing strip.
[0027] 3) Safe and reliable: By means of the spring plate, lock wire, and controlling the state of the hook lock axis, ensure the safe and reliable use of the hook lock.
[0028] 4) Simple to use and maintain: The embedded hook lock installation structure is simple to use, adjust, and install, with accessible space and convenient operation.
[0029] 5) Wide application range: The configuration in the present invention or a similar configuration derived from the present invention can be used in the structural design of the nose fairing, nose radome, or other part covers.
[0030] The embedded hook lock structure has been implemented on the aircraft, and the actual effect is good. BRIEF DESCRIPTION OF THE DRAWINGS
[0031] Figure 1 It is a schematic diagram of the hook lock assembly structure;
[0032] Figure 2-1 It is a side view of the hook lock assembly installation structure;
[0033] Figure 2-2 It is a top view of the hook lock assembly installation structure;
[0034] Figure 3 It is a schematic diagram of the hook lock support assembly structure;
[0035] Figure 4 It is a schematic diagram of the hook lock support structure;
[0036] Figure 5 It is a schematic diagram of the spring plate structure;
[0037] Figure 6-1 It is an overall schematic diagram of the lock ring support assembly structure;
[0038] Figure 6-2 It is an internal schematic diagram of the lock ring support assembly structure;
[0039] Figure 7 Schematic cross-sectional view of the cockpit cover sealing support
[0040] Figure 8 Side view of the structure of the stop pin assembly
[0041] Figure 9 Cross-sectional view of the structure of the stop pin assembly
[0042] Figure 10 Schematic view of the structure of the stop pin
[0043] Figure 11 Schematic view of the installation axis of the hook lock assembly
[0044] Figure 12 Schematic view of the installation method of the adjusting nut lock wire
[0045] Among them, 1 - hook lock, 2 - adjustable lock ring, 3 - hook lock support assembly, 4 - lock ring support assembly, 5 - stop pin assembly, 6 - nose cover assembly, 7 - cockpit cover assembly, 8 - hook lock support, 9 - hook lock pin shaft, 10 - washer, 11 - slotted nut, 12 - split pin, 13 - spring plate, 14 - rivet, 15 - installation plane, 16 - installation plane, 17 - vertical rib, 18 - lock ring support, 19 - toothed plate, 20 - adjusting bolt, 21 - gasket, 22 - self-locking nut, 23 - guide block, 24 - adjusting tooth, 25 - countersunk hole for countersunk head screw, 26 - CHC screw, 27 - avoidance groove, 28 - bolt through hole, 29 - adjusting gasket, 30 - lock wire, 31 - fixed gasket, 32 - stop pin, 33 - bolt, 34 - washer, 35 - nut, 36 - nut, 37 - slotted nut, 38 - washer, 39 - split pin, 40 - operating plane, 41 - thread, 42 - conical head, 43 - stop tooth, 44 - limit guiding hole. Specific implementation mode
[0046] To make the objectives, technical solutions and advantages of the embodiments of the present invention clearer, the technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are some, but not all, of the embodiments of the present invention. All other embodiments obtained by those of ordinary skill in the art based on the embodiments of the present invention without creative efforts shall fall within the protection scope of the present invention.
[0047] The features and exemplary embodiments of various aspects of the present invention will be described in detail below. In the following detailed description, numerous specific details are set forth in order to provide a thorough understanding of the present invention. However, it will be apparent to those skilled in the art that the present invention may be practiced without some of these specific details. The following description of the embodiments is only intended to provide a better understanding of the present invention by showing examples of the present invention. The present invention is in no way limited to any specific arrangements and methods set forth below, but covers any improvements, substitutions, and modifications of structures, methods, and devices without departing from the spirit of the present invention. In the drawings and the following description, well-known structures and techniques are not shown to avoid unnecessarily obscuring the present invention.
[0048] It should be noted that, without conflict, the embodiments of the present invention and the features in the embodiments may be combined with each other, and the various embodiments may be referred to and cited with each other.
[0049] The present invention will be described in detail below in conjunction with the accompanying drawings and specific embodiments.
[0050] An embodiment of the present invention provides a positioning structure for a hook lock, as Figure 1 shown, including: a hook lock 1, an adjustable lock ring 2, a hook lock support assembly 3, a lock ring support assembly 4, and a stop pin assembly 5; wherein, the adjustable lock ring 2 has a non-step adjustment amount of L thread length, and the others are structural design parts.
[0051] The axes of the hook lock 1 and the adjustable lock ring 2 should be in a straight line, and the angular deviation range is -10° to +10°;
[0052] As Figure 2-1 , Figure 2-2 shown, the hook lock 1 is fixed on the nose hood assembly 6 through the hook lock support assembly 3, and the adjustable lock ring 2 is fixed on the cockpit hood assembly 7 through the lock ring support assembly 4; the stop pin assembly 5 connects the hook lock support assembly 3 and the lock ring support assembly 4.
[0053] As Figure 3 shown, the hook lock support assembly 3 includes: a hook lock support 8, a hook lock pin 9, a washer 10, a castle nut 11, a split pin 12, and a spring plate 13; wherein, the hook lock 1 is connected to the hook lock support 8 through the hook lock pin 9, and the end of the hook lock pin 9 (material: alloy structural steel 35NiCr16) is fixed on the hook lock support 8 through the washer 10, the castle nut 11, and the split pin 12 to prevent it from falling off; the spring plate 13 is riveted to the hook lock support 8 through two rivets 14, and the function of the spring plate is that after the hook lock is closed, its lock hook does not shake under the reaction force of the spring plate, and after the hook lock is opened, the lock hook of the hook lock can automatically spring open under the reaction force of the spring plate.
[0054] As Figure 3 ,Figure 4 As shown, the hook lock support 8 is designed with installation planes 15 and 16 of the stop pin assembly 5, and the planes are perpendicular to the installation direction of the stop pin assembly 5; in order to improve the rigidity and bending resistance of the structure near the installation planes 15 and 16 of the stop pin assembly 5, the hook lock support 8 is designed with vertical ribs 17 to bear the force brought by the stop pin assembly 5.
[0055] like Figure 5 As shown, the material of the spring sheet 13 is 65Mn-cold rolled + annealed-δ0.8, and the Rockwell hardness after heat treatment is 40-45HRC. The thickness value and the hardness value after heat treatment of the spring sheet should be adaptively adjusted as the size of the spring sheet changes, and the use effect during the opening and closing process of the hook lock should be used as the adjustment basis.
[0056] like Figure 6-1 , Figure 6-2 As shown, the lock ring support assembly 4 includes: a lock ring support 18, an adjusting bolt 20, a gasket 21, a self-locking nut 22, and a toothed plate 19; wherein the screw 20, the gasket 21, and the self-locking nut 22 are used to fix the guide block 23 in the adjustable lock ring 2 to the toothed plate 19 and the lock ring support 18;
[0057] like Figure 12 As shown, the lock wire 30 is installed on the adjusting nut 20 in a prescribed manner to prevent the adjusting nut 20 from loosening. This can prevent the impact of vibration during the flight of the aircraft, so that the hook lock structure needs to have an anti-loosening function.
[0058] like Figure 7 As shown, the toothed plate 19 is provided with U-direction arrangement adjustment teeth 24, countersunk holes 25, bolt through holes 28, and CHC screw 26 avoidance grooves 27; wherein the CHC screw is a screw provided with the adjustable lock ring 2 of the product; the bolt through hole 28 is a circular hole opening, the guide block 23 is provided with U-direction arrangement adjustment teeth, and the screw through hole is a waist-shaped hole along the W direction; the lock ring support assembly 4 has adjustment functions along the U direction and along the W direction; the toothed plate 19 and the toothed plate on the guide block 23 are adjusted by a step length of 0.75mm + / -3mm; the toothed plate 19 is riveted to the hook lock support 8 and the cabin cover assembly 7 through countersunk nails.
[0059] like Figure 8 , Figure 9 As shown, the stop pin assembly 5 includes: a stop pin 32, multiple adjustment washers 29, a fixed washers 31 and a connecting piece; multiple adjustment washers 29 and fixed washers 31 form a stop plate; wherein multiple adjustment washers 29 and fixed washers 31 are fixed to the cockpit cover assembly 7 by bolts 33, washers 34, nuts 35 and locking wires 36; the stop pin 32 is fixed to the nose cover assembly 6 by a slot nut 37, a washer 38 and a cotter pin 39.
[0060] like Figure 9 ,Figure 10 As shown in the figure, operating planes 40 are designed on both sides of the stop pin 32 to facilitate the clamping of the operating planes 40 on both sides by operating tools such as wrenches, so as to turn the stop pin 32 or the grooved nut 37 to adjust the tightening torque; the clearance fit relationship between the stop pin 32 and the limiting and guiding hole 44 of the lock ring support 18 is a clearance fit H7 / g6, which can ensure that the stop pin 32 can rotate freely in the limiting and guiding hole 44 of the lock ring support 18; one end of the stop pin 32 is designed with a thread 41, and the side of the thread 41 is inserted into the limiting and guiding hole 44 of the lock ring support 18, and the grooved nut 37 is screwed into the thread 41 to fix the stop pin 32 on the lock ring support 18. The other end is designed with a tapered head 42 to facilitate guiding and inserting into the limiting and guiding hole 45 on the hook lock support 8; the stop pin 32 is designed with a retaining tooth 43 for limiting. The retaining tooth 43 contacts the fixed gasket 31 and the lock ring support 18, so that the nose cowl assembly 6 is limited to a certain position.
[0061] The embodiment of the present invention also provides an adjustment method for the positioning structure of the hook lock, including:
[0062] A total of + / - 5 mm adjustment amount is available for multiple adjusting gaskets 29 with an adjustment step of 0.5 mm per file; when the nose cowl assembly 6 is closed, the stop pin 32 contacts the cockpit cover assembly 7. By adjusting the number of multiple adjusting gaskets 29 on the outer side of the cockpit cover assembly 7, the gap between the cockpit cover assembly 7 and the nose cowl assembly 6 changes; in order to keep the length of the bolt 33 unchanged, the gaskets on one side need to be subtracted and placed on the other side, and the total number of gaskets on both sides always remains unchanged; during the adjustment process, the stop pin 32 contacts the end face of the stop plate and does not contact the hole of the stop plate;
[0063] When the nose cowl assembly 6 is in the closed state, the nose fairing contacts the stop plate, and the hook lock is hooked and tightened. Figure 11 It is a schematic diagram of the installation axis of the hook lock assembly.
[0064] The key points of the present invention are:
[0065] 1) Provide an embedded installation structure for the hook lock, including a hook lock support assembly, a lock ring support assembly and a stop pin assembly;
[0066] 2) Provide a connection structure between the hook lock and the hook lock support assembly, which can ensure the reliable installation of the hook lock on the nose cowl assembly;
[0067] 3) Provide a connection structure between the adjustable lock ring and the hook ring support assembly, which can ensure the reliable installation of the adjustable lock ring on the cockpit cover assembly and has a two-dimensional adjustment function;
[0068] 4) Provide a hook lock fixing spring piece, which can ensure the stable position of the hook lock without shaking in the locked state and the automatic ejection of the hook lock in the opened state;
[0069] 5) A stop pin assembly structure is provided, which has the functions of adjusting the gap between the nose cowl and the cockpit canopy, guiding, and limiting, and is convenient to operate;
[0070] 6) A hook lock installation state is provided, which can ensure that the hook does not come out of the lock ring during the flight of the aircraft;
[0071] 7) A regulating nut wire locking installation state is provided, which can ensure that the nut does not loosen during the flight of the aircraft.
[0072] The above only expresses the implementation modes of the present invention, and the description is relatively specific and detailed, but it cannot be understood as a limitation on the scope of the patent. It should be noted that for those of ordinary skill in the art, without departing from the concept of the present invention, several deformations and improvements can still be made, and these all belong to the protection scope of the present invention. In addition, the parts not elaborated in the present invention are all conventional technologies.
Claims
1. A positioning structure for a hook lock, characterized in that, Comprising: A latch support assembly (3), a lock ring support assembly (4), and a stop pin assembly (5), The latch (1) of the hook lock is fixed to the nose hood assembly (6) through the latch support assembly (3), and the adjustable lock ring (2) of the hook lock is fixed to the cockpit hood assembly (7) through the lock ring support assembly (4); The stop pin assembly (5) connects the latch support assembly (3) and the lock ring support assembly (4); The latch support assembly (3) includes: a latch support (8) and a spring plate (13), and the spring plate (13) is riveted to the latch support (8); The stop pin assembly (5) includes: a plurality of adjusting washers (29), a fixed washer (31), and a stop pin (32); The plurality of adjusting washers (29) and the fixed washer (31) form a stop plate, and the plurality of adjusting washers (29) and the fixed washer (31) are provided with guiding and limiting holes for the stop pin (32); The plurality of adjusting washers (29) and the fixed washer (31) are fixed to the cockpit hood assembly (7); One end of the stop pin (32) is fixed to the nose hood assembly (6), and the other end is provided with a tapered head (42); The stop pin (32) is provided with a retaining tooth (43) for limiting the nose hood assembly (6), and the retaining tooth (43) limits the nose hood assembly (6) to a certain position by contacting the fixed washer (31) and the lock ring support (18).
2. The positioning structure for a hook lock according to claim 1, characterized in that, The latch support (8) is provided with a groove for embedding the latch (1); After the hook lock is closed, the lock hook does not shake under the reaction force of the spring plate (13), and after the hook lock is opened, the lock hook of the hook lock can automatically spring open under the reaction force of the spring plate (13); The plurality of adjusting washers (29) and the fixed washer (31) are fixed to the cockpit hood assembly (7) through bolts (33), and a part of the adjusting washers (29) is located outside the cockpit hood assembly (7), and another part of the adjusting washers (29) is located inside the cockpit hood assembly (7).
3. The positioning structure for a hook lock according to claim 1, characterized in that, The latch support assembly (3) further includes: a latch pin (9); The latch (1) is connected to the latch support (8) through the latch pin (9); The latch pin (9) is fixed to the latch support (8) to prevent the latch (1) of the hook lock from falling off.
4. The positioning structure for a hook lock according to claim 1, characterized in that, The latch support (8) is provided with a first mounting plane (15) and a second mounting plane (16) for the stop pin assembly (5), The first mounting plane (15) and the second mounting plane (16) are perpendicular to the mounting direction of the stop pin assembly (5); The latch support (8) is provided with a rib (17) to bear the acting force brought by the stop pin assembly (5).
5. The positioning structure for a hook lock according to claim 1, wherein The material of the spring plate (13) is 65Mn, the thickness is 0.8 mm, and the Rockwell hardness after heat treatment is 40 - 45 HRC.
6. The positioning structure for a hook lock according to claim 1, characterized in that, The lock ring support assembly (4) includes: a lock ring support (18), a toothed plate (19); The guiding block (23) in the adjustable lock ring (2) is screwed to the toothed plate (19) and the lock ring support (18) through bolts (20), and the bolts (20) are provided with mounting holes for lock wires (30); The toothed plate (19) is riveted to the lock ring support (18) and the cockpit hood assembly (7); The toothed plate (19) is provided with countersunk head rivet holes (25), bolt through holes (28), relief grooves (27) for CHC screws (26), and adjusting teeth (24) arranged in the U direction. At the countersunk head rivet holes (25), the toothed plate (19), the lock ring support (18), and the cockpit cover assembly (7) are riveted together using countersunk head rivets, and the countersunk head rivets do not protrude from the surface of the toothed plate (19), so as not to affect the assembly of the guide block (23) in the adjustable lock ring (2) and the toothed plate (19); the bolt through holes (28) are circular holes. The guide block (23) in the adjustable lock ring (2), the toothed plate (19), the lock ring support (18), and the cockpit cover assembly (7) are connected through the bolt through holes (28). At this time, the adjustable lock ring (2) is fixed to the cockpit cover assembly (7); the guide block (23) is provided with adjusting teeth arranged in the U direction, and the bolt through holes (28) are waist-shaped holes along the W direction; the lock ring support assembly (4) has adjustment functions along the U direction and the W direction; the adjustment step of the adjusting teeth on the toothed plate (19) and the adjusting teeth on the guide block (23) is 0.75 mm, and the adjustment range is -3 mm to +3 mm.
7. The positioning structure for a hook lock according to claim 1, characterized in that Operating planes (40) are provided on both sides of the stop pin (32), and a thread (41) for fixing to the nose hood assembly (6) is provided at one end of the stop pin (32).
8. The positioning structure for a hook lock according to claim 1, characterized in that, The mating relationship between the stop pin (32) and the hole in the hook lock support (8) is H7 / g6.
9. The positioning structure for a hook lock according to claim 1, characterized in that The thickness of each adjusting shim (29) is 0.5 mm.
10. A method for adjusting a positioning structure of the hook lock according to any one of claims 1 to 9, characterized in that, Comprising: When the nose hood assembly (6) is closed, the stop pin (32) contacts the cockpit cover assembly (7). At the same time, the number of adjusting shims (29) on the outside and inside of the cockpit cover assembly (7) is adjusted, and the gap between the cockpit cover assembly (7) and the nose hood assembly (6) is adjusted until the design requirements are met, while the length of the bolt (33) remains unchanged.