Design method of locking mechanism

Abstract

The invention provides a design method of a locking mechanism, and belongs to the technical field of aviation functional structure design, the method comprises the following steps: 1, combining a stress load of a bottom fairing fixed on a fuselage bottom structure and a working principle of a hook-shaped locking sleeve to carry out stress analysis on a locking point part; 2, based on the stress analysis result, the position of a locking point part is set on the bottom fairing; step 3, setting a reference and a boundary of the hook-shaped locking kit in a locking state, and obtaining a hook-shaped locking kit mounting interface in the locking state; 4, designing a bottom fairing lock point mounting platform; and 5, designing a connecting piece of the hook-shaped locking kit and a locking mode of the connecting piece. Through modeling design analysis, the bottom fairing hook-shaped locking mechanism under the fuselage bottom structure can be quickly disassembled and assembled in a non-hinge mode state; the manufacturing process of the fairing is improved, and the aerodynamic environment of the fairing during flight is improved; the method can be used for design of a cabin bottom locking structure.

Description

Technical Field

[0001] The present invention belongs to the technical field of aviation functional structure design, and particularly relates to a design method for a locking mechanism. Background Art

[0002] In the optimization and improvement design of the bottom fairing of a helicopter, the original bottom fairing locking mechanism uses an annular buckle locking device. When opening and closing, it is necessary to hold the lifting ring by hand and apply a large force for operation. The operation is inconvenient and easy to hurt the fingers. In addition, during the design, not only the shape of the bottom of the fuselage changes, but also the structures on the left and right sides of the original fuselage bottom change, resulting in the connection and installation surfaces between the new bottom fairing and the fuselage structure being different from before. It is impossible to achieve quick disassembly and installation.

[0003] Therefore, it is necessary to reconsider the design method of the locking mechanism, place the bottom fairing under the bottom structure of the fuselage, and thus achieve quick disassembly and installation. Summary of the Invention

[0004] In order to solve the technical problem in the prior art that it is impossible to achieve simple and quick disassembly and assembly of the bottom fairing on the bottom structure of the fuselage, the present invention provides a design method for a locking mechanism, which places the bottom fairing under the bottom structure of the fuselage to achieve quick disassembly and installation. The technical solution is as follows:

[0005] Provide a design method for a locking mechanism, including:

[0006] Step 1: Combine the force load of the bottom fairing fixed to the bottom structure of the fuselage and the working principle of the hook-type locking tool to conduct a force analysis of the locking point part;

[0007] Step 2: Based on the force analysis result, set the position of the locking point part on the bottom fairing;

[0008] Step 3: Set the reference and boundary of the hook-type locking tool in the locked state, and obtain the installation interface of the hook-type locking tool in the locked state;

[0009] Step 4: In the full-aircraft assembly environment, in the position space of the locking point part, based on the force analysis result, place the installation interface of the hook-type locking tool to obtain the installation surface of the locking point platform, and design the locking point installation platform of the bottom fairing;

[0010] Step 5: Design the connecting piece of the hook-type locking tool and the stopping method of the connecting piece.

[0011] Among them, in Step 1, in the flight state, combine the force load of the bottom fairing fixed to the bottom structure of the fuselage and the working principle of the hook-type locking tool to determine the force state of the locking point part of the bottom fairing, and preliminarily determine the force and position relationship between the locking point part and the connecting piece part in the locked state.

[0012] The positions of the locking point part and the connecting part are close to the edge of the bottom fairing.

[0013] Among them, in step two, based on the force analysis results, on the bottom fairing, from front to back, 3 locking point parts are set on one side, namely A1, A3, and A5; 3 locking point parts are set on the other side, namely A2, A4, and A6, and the locking point parts on both sides are symmetrical left and right.

[0014] Among them, in step three, the process of obtaining the installation interface of the hook-type locking sleeve in the locked state includes:

[0015] First, set the benchmark of the hook-type locking sleeve in the locked state: digitalize the hook-type locking sleeve in the locked state, introduce the digital model of the hook-type locking sleeve in the assembly environment, and set the key benchmarks: when the hook of the hook-type locking sleeve locks the square loop, the axis L0 around which the hook rotates around the cylindrical axis of the square loop coincides with the center line L1 of the cylindrical axis of the square loop; the hook rotation axis is L2, the reference plane for installing the card seat on the body structure is P1, the reference plane of the button platform is P2, on the reference plane P2, the center line of the button platform is L3, and the central axis of the tail shaft of the square loop is L4;

[0016] Then, set the boundary of the hook-type locking sleeve: based on the digital model of the hook-type locking sleeve and in combination with the installation requirements, on the reference plane P2, with the center line L3 as the center, construct a first rectangle S1, and the first rectangle S1 is the boundary of the button installation surface of the hook-type locking sleeve; on the reference plane P2, with the center line L3 as the center, construct a second rectangle S2 with an area smaller than that of the first rectangle S1, and the second rectangle S2 is the button opening boundary of the hook-type locking sleeve, and the gap between this button opening boundary and the edge of the button platform is equidistant. Set the center point O1 of the first rectangle S1 as the center point of the locking button reference plane;

[0017] The above benchmarks and boundaries belong to the same assembly coordinate system and serve as the installation interface of the hook-type locking sleeve.

[0018] Among them, in step four, the process of designing the locking point installation platform of the bottom fairing includes:

[0019] In the full-aircraft assembly environment, in the space at the A1 position of the locking point, based on the force analysis results of Step 1, insert the installation interface of the hook-type locking sleeve. The center line L3 of the button platform is perpendicular to the edge curve of the bottom fairing. Through the vertical projection of the center point O1, obtain the tangent plane P31 on the outer surface of the bottom fairing. Offset the tangent plane P31 inward into the fuselage to obtain the locking button installation surface P41 of the bottom fairing; project the first rectangle S1 onto the installation surface P41, and after rounding, obtain the first boundary S31. The area occupied by the first boundary S31 is the button platform area of the bottom fairing in the planar state; project the first boundary S31 into the outer surface of the bottom fairing and at the same time expand and offset it to obtain the second boundary S41. Connect the outer surface of the bottom fairing outside the second boundary S41 and the plane inside the first boundary S31 to finally obtain a composite surface. The four edges of the composite surface are smoothly transitioned, and the inside is a plane recessed into the outer surface of the bottom fairing. This plane is the locking point platform installation surface; project the second rectangle S2 onto this locking point platform installation surface to obtain the button opening boundary S51;

[0020] The process of obtaining the locking point platform installation surfaces of the locking points A3, A5, A2, A4, and A6 is the same as the process of obtaining the locking point platform installation surface of the locking point A1.

[0021] Among them, the connecting parts of the hook-type locking sleeve include the fuselage connecting part and the bottom fairing connecting part. For the locking point A1, in Step 5, the process of designing the connecting parts of the hook-type locking sleeve includes:

[0022] First, design the fuselage connecting part: In the space at the A1 position of the locking point in Step 4, design a machined angle box between the card seat of the hook-type locking sleeve and the bottom structure of the fuselage. Using the reference plane P1 for card seat installation and the reference plane P51 for the bottom structure installation of the fuselage as the positioning references, design the machined angle box in a wedge shape. The fuselage installation surface of the machined angle box abuts against the bottom structure of the fuselage, and use riveting for connection; the card seat of the hook-type locking sleeve abuts against the card seat installation surface of the machined angle box;

[0023] Then, design the bottom fairing connecting part: In the space at the A1 position of the locking point in Step 4, design a machined angle box between the locking sleeve button platform and the bottom fairing. Using the locking button installation surface P41 of the bottom fairing as the positioning reference, the reference plane P2 of the button platform coincides with the locking button installation surface P41; using the hook rotation axis L2 as the reference, design the machined angle box in a shape like the Chinese character 'ji'. The installation surface of the machined angle box abuts against the locking point platform installation surface of the bottom fairing, and use riveting for connection. The hook-type locking sleeve button platform and the hook are suspended in the middle of the machined angle box by pins;

[0024] Finally, design the stopping method for the fuselage connecting piece and the bottom fairing connecting piece: Add a boss at the front end of the fuselage connecting piece. This boss is perpendicular to the reference plane P1 for the installation of the clamping seat and is parallel to the installation surface P41. Add a top plate above the bottom fairing connecting piece. This top plate is perpendicular to the installation surface P41 and is parallel to the reference plane P1. After the two connecting pieces are installed, in the locked state of the hook-type locking mechanism, the boss and the top plate intersect vertically and are in contact with each other.

[0025] The design process of the connecting pieces of the hook-type locking sets at the locking points A3, A5, A2, A4, and A6 is the same as that of the locking point A1.

[0026] The beneficial effects of the present invention are at least as follows:

[0027] 1) Provide a design method for the locking mechanism of the hook-type locking set. Through modeling design analysis, the quick disassembly and assembly of the hook-type locking mechanism of the bottom fairing under the bottom structure of the fuselage in the non-hinge mode state are realized.

[0028] 2) Compared with the original bottom fairing, the present invention makes the design of the bottom fairing simple and reliable. It cancels the design of the locking point base filled with No. 17 packing (relatively large weight), cancels the design of the notch at the edge of the fairing (weakening of stiffness), improves the manufacturing process of the fairing (canceling the filling link of the locking point base and manufacturing it in one molding using a mold), and improves the aerodynamic environment of the fairing during flight (the hook-type locking button surface is flush with the outer surface of the fairing).

[0029] The method described in the present invention can be applied to the design of the locking structure at the bottom of the cockpit. It has been implemented and the actual effect is very good. Description of the Drawings

[0030] Figure 1 is the force diagram of the locking point part of the present invention;

[0031] Figure 2 is the top view of the layout of the locking point part of the present invention;

[0032] Figure 3 is the schematic diagram of the reference setting of the hook-type locking set of the present invention;

[0033] Figure 4 is the top view of the hook-type locking button platform of the present invention;

[0034] Figure 5 is the schematic diagram of the locking point installation surface of the bottom fairing of the present invention;

[0035] Figure 6 is the schematic diagram of the fuselage connecting piece of the present invention;

[0036] Figure 7 is the schematic diagram of the bottom fairing connecting piece of the present invention;

[0037] Figure 8 It is a schematic diagram of the connecting member of the locking mechanism of the present invention;

[0038] Figure 9 It is a schematic diagram of the final form obtained by using the method of the present invention;

[0039] Figure 10 It is a schematic diagram of a single set of the locking mechanism.

[0040] Among them, 1 - bottom structure of the fuselage, 2 - bottom fairing, 3 - locking point part, 4 - card seat, 5 - square ring buckle, 6 - hook, 7 - button platform, 8 - fuselage connecting member, 9 - bottom fairing connecting member, 10 - boss, 11 - top plate, 100 - installation platform for the bottom fairing lock seat. Specific embodiments

[0041] The present invention will be further described in detail below through specific embodiments and accompanying drawings.

[0042] An embodiment of the present invention provides a design method for a locking mechanism, which specifically includes the following steps:

[0043] Step 1: Conduct a force analysis of the locking point part

[0044] Refer to Figure 1 , taking the bottom fairing 2 as the research object to study its force condition: In the flight state, combining the force load of the bottom fairing 2 fixed to the bottom structure 1 of the fuselage and the locking working principle of the hook - type locking set, determine the force state of the locking point part 3 of the bottom fairing 2, and preliminarily determine the force and position relationship between the locking point part 3 and the connecting member part in the locked state: The tension T is the acting force of the hook - type locking set, the force F is the acting force of the aerodynamic load, and the moment M is the acting moment of the fuselage structure. The positions of the locking point part 3 and the connecting member part are close to the edge of the bottom fairing 2.

[0045] Step 2: Set the position of the locking point part

[0046] Obtain the force analysis result of the locking part in Step 1, and considering the safety redundancy, on the bottom fairing 2, set 3 locking point parts from front to back on one side, namely A1, A3, and A5, and set 3 locking point parts on the other side, namely A2, A4, and A6. The locking point parts on both sides are symmetrical left and right, as shown in Figure 2 . The positions of the selected locking point parts do not affect the surrounding structures and systems.

[0047] Step 3: Obtain the installation interface of the hook - type locking set (locked state)

[0048] 1. Conduct a reference setting for the hook - type locking set,

[0049] See Figure 3 , digitalize the hook - type locking sleeve in the locked state. In the assembly environment, introduce the digital model of the hook - type locking sleeve in the locked state, and set the key benchmarks: when the hook 6 of the hook - type locking sleeve locks the square loop 5, the axis L0 around which the hook 6 rotates about the cylindrical axis of the square loop 5 coincides with the center line L1 of the cylindrical axis of the square loop 5. The rotation axis of the hook 6 is L2. The reference plane for installing the card seat 4 on the body structure is P1. The reference plane of the button platform 7 is P2. On the reference plane P2, the center line of the button platform 7 is L3. The central axis of the tail shaft of the square loop 5 is L4.

[0050] 2. Set the boundaries of the hook - type locking sleeve,

[0051] See Figure 4 , referring to the digital model of the hook - type locking sleeve and combining the installation requirements, on the reference plane P2, with the center line L3 as the center, build a rectangle S1. The rectangle S1 is the boundary of the button installation surface of the hook - type locking sleeve. Similarly, on the reference plane P2, with the center line L3 as the center, build another rectangle S2. The area of the rectangle S2 is smaller than the area of the rectangle S1. The rectangle S2 is the boundary of the button opening of the hook - type locking sleeve, and the gap between this boundary and the edge of the button platform 7 is equidistant. Set the center point of the rectangle S1 as O1, and use O1 as the center point of the reference plane of the locking button.

[0052] The above - mentioned benchmarks and boundaries belong to the same assembly coordinate system and serve as the installation interface of the hook - type locking sleeve.

[0053] Step Four: Design the installation platform for the bottom fairing lock point

[0054] In the full - machine assembly environment, in the space at the A1 position of the lock point part, based on the force - analysis results of Step One, place the installation interface of the hook - type locking sleeve. The center line L3 of the button platform 7 is perpendicular to the edge curve of the bottom fairing 2. Through the vertical projection of the center point O1, obtain the tangent plane P31 on the outer surface of the bottom fairing 2. The tangent plane P31 is offset inward towards the fuselage to obtain the locking - button installation surface P41 of the bottom fairing 2; project the rectangle S1 onto the installation surface P41, and after filleting, obtain the boundary S31. The area occupied by the boundary S31 is the button - platform area of the bottom fairing 2 in the planar state; project the boundary S31 into the outer surface of the bottom fairing 2 and at the same time expand and offset to obtain the boundary S41; then through surface treatments such as trimming, bridging, and combining, connect the outer surface of the bottom fairing 2 outside the boundary S41 and the plane inside the boundary S31. Finally, obtain a composite surface. The four - week edges of this composite surface are smoothly transitioned, and the inside is a plane recessed into the bottom - fairing shape. This plane is the lock - point platform installation surface. Project the rectangle S2 onto this lock - point platform installation surface to obtain the button - opening boundary S51. See Figure 5 . Figure 5Among them, i is equal to 1, 2, 3, 4, 5 or 6. When the locking point part is A1, i is 1; when the locking point part is A2, i is 2; when the locking point part is A3, i is 3; when the locking point part is A4, i is 4; when the locking point part is A5, i is 5; when the locking point part is A6, i is 6.

[0055] According to the above operations, the locking point platform installation surfaces of the remaining 5 locking point parts A3, A5, A2, A4 and A6 are obtained in sequence as follows:

[0056] In the spatial position of the locking point part A3, based on the force analysis result of step one, place the hook-shaped locking sleeve installation interface. The center line L3 of the button platform 7 is perpendicular to the edge curve of the bottom fairing 2. Through the vertical projection of the center point O1, obtain the tangent plane P33 on the outer surface of the bottom fairing 2. The tangent plane P33 is offset towards the fuselage interior to obtain the locking button installation surface P43 of the bottom fairing 2; project the rectangle S1 onto the installation surface P43, and after rounding, obtain the boundary S33. The area occupied by the boundary S33 is the button platform area of the bottom fairing 2 in the planar state; project the boundary S33 into the outer surface of the bottom fairing 2 and simultaneously expand and offset to obtain the boundary S43; then through surface treatments such as trimming, bridging and combining, connect the outer surface of the bottom fairing 2 outside the boundary S43 and the plane inside the boundary S33. Finally, obtain a composite surface. The four peripheries of this composite surface are smoothly transitioned, and the interior is a plane recessed in the bottom fairing shape. This plane is the locking point platform installation surface. Project the rectangle S2 onto this locking point platform installation surface to obtain the button opening boundary S53.

[0057] In the spatial position of the locking point part A5, based on the force analysis result of step one, place the hook-shaped locking sleeve installation interface. The center line L3 of the button platform 7 is perpendicular to the edge curve of the bottom fairing 2. Through the vertical projection of the center point O1, obtain the tangent plane P35 on the outer surface of the bottom fairing 2. The tangent plane P35 is offset towards the fuselage interior to obtain the locking button installation surface P45 of the bottom fairing 2; project the rectangle S1 onto the installation surface P45, and after rounding, obtain the boundary S35. The area occupied by the boundary S35 is the button platform area of the bottom fairing 2 in the planar state; project the boundary S35 into the outer surface of the bottom fairing 2 and simultaneously expand and offset to obtain the boundary S45; then through surface treatments such as trimming, bridging and combining, connect the outer surface of the bottom fairing 2 outside the boundary S45 and the plane inside the boundary S35. Finally, obtain a composite surface. The four peripheries of this composite surface are smoothly transitioned, and the interior is a plane recessed in the bottom fairing shape. This plane is the locking point platform installation surface. Project the rectangle S2 onto this locking point platform installation surface to obtain the button opening boundary S55.

[0058] In the spatial position of the locking point part A2, based on the force analysis result of Step 1, insert the installation interface of the hook-type locking sleeve. The center line L3 of the button platform 7 is perpendicular to the edge curve of the bottom fairing 2. Through the vertical projection of the center point O1, obtain the tangent plane P32 on the outer surface of the bottom fairing 2. Offset the tangent plane P32 inward towards the fuselage to obtain the locking button installation surface P42 of the bottom fairing 2. Project the rectangle S1 onto the installation surface P42, and after rounding, obtain the boundary S32. The area occupied by the boundary S32 is the button platform area of the bottom fairing 2 in the planar state. Project the boundary S32 into the outer surface of the bottom fairing 2 and expand and offset it simultaneously to obtain the boundary S42. Then, through surface treatments such as trimming, bridging, and combining, connect the outer surface of the bottom fairing 2 outside the boundary S42 and the plane inside the boundary S32. Finally, obtain a composite surface. The four peripheries of this composite surface are smoothly transitioned, and the interior is a plane recessed in the shape of the bottom fairing. This plane is the locking point platform installation surface. Project the rectangle S2 onto this locking point platform installation surface to obtain the button opening boundary S52.

[0059] In the spatial position of the locking point part A4, based on the force analysis result of Step 1, insert the installation interface of the hook-type locking sleeve. The center line L3 of the button platform 7 is perpendicular to the edge curve of the bottom fairing 2. Through the vertical projection of the center point O1, obtain the tangent plane P34 on the outer surface of the bottom fairing 2. Offset the tangent plane P34 inward towards the fuselage to obtain the locking button installation surface P44 of the bottom fairing 2. Project the rectangle S1 onto the installation surface P44, and after rounding, obtain the boundary S34. The area occupied by the boundary S34 is the button platform area of the bottom fairing 2 in the planar state. Project the boundary S34 into the outer surface of the bottom fairing 2 and expand and offset it simultaneously to obtain the boundary S44. Then, through surface treatments such as trimming, bridging, and combining, connect the outer surface of the bottom fairing 2 outside the boundary S44 and the plane inside the boundary S34. Finally, obtain a composite surface. The four peripheries of this composite surface are smoothly transitioned, and the interior is a plane recessed in the shape of the bottom fairing. This plane is the locking point platform installation surface. Project the rectangle S2 onto this locking point platform installation surface to obtain the button opening boundary S54.

[0060] In the space of the locking point part at position A6, based on the force analysis result of Step 1, a hook-shaped locking sleeve installation interface is placed. The center line L3 of the button platform 7 is perpendicular to the edge curve of the bottom fairing 2. Through the vertical projection of the center point O1, the tangent plane P36 on the outer surface of the bottom fairing 2 is obtained. The tangent plane P36 is offset inward into the fuselage to obtain the locking button installation surface P46 of the bottom fairing 2. The rectangle S1 is projected onto the installation surface P46, and after filleting, the boundary S36 is obtained. The area occupied by the boundary S36 is the button platform area of the bottom fairing 2 in the planar state. The boundary S36 is projected into the outer surface of the bottom fairing 2 and simultaneously extended and offset to obtain the boundary S46. Through surface treatments such as trimming, bridging, and combining, the outer surface of the bottom fairing 2 outside the boundary S46 and the plane inside the boundary S36 are connected. Finally, a composite surface is obtained. The four peripheral edges of the composite surface are smoothly transitioned, and the inside is a plane recessed into the shape of the bottom fairing. This plane is the locking point platform installation surface. The rectangle S2 is projected onto this locking point platform installation surface to obtain the button opening boundary S56.

[0061] Step Five: Design the connecting piece of the hook-shaped locking sleeve

[0062] For the locking point part A1

[0063] First, design the fuselage connecting piece 8, specifically: In the space of the locking point part A1 in Step Four, a machined angle box is designed between the clamping seat 4 of the hook-shaped locking sleeve and the bottom structure 1 of the fuselage. Taking the reference plane P1 for the installation of the clamping seat 4 and the reference plane P51 for the installation of the fuselage bottom structure as the positioning references, the machined angle box is designed in a wedge shape, as Figure 6 shown. Figure 6 In the figure, i is equal to 1, 2, 3, 4, 5, or 6. When the locking point part is A1, i is 1; when the locking point part is A2, i is 2; when the locking point part is A3, i is 3; when the locking point part is A4, i is 4; when the locking point part is A5, i is 5; when the locking point part is A6, i is 6. In one embodiment, 7075 high-strength hard aluminum material can be selected. The fuselage installation surface of the machined angle box abuts against the bottom structure 1 of the fuselage and is connected by riveting. The clamping seat 4 of the hook-shaped locking sleeve abuts against the clamping seat installation surface of the machined angle box. There are 4 through holes on the angle box installation surface, and screws can be used to screw the angle box;

[0064] Then, design the bottom fairing connecting piece 9, specifically: In the space of the locking point part A1 in Step Four, a machined angle box is designed between the button platform 7 of the hook-shaped locking sleeve and the bottom fairing 2. Taking the installation surface P41 of the bottom fairing as the positioning reference, the reference plane P2 of the button platform 7 coincides with the installation surface P41. Taking the bending axis L2 of the hook as the reference, the machined angle box is designed in a U shape, as Figure 7 shown. Figure 7Among them, i is equal to 1, 2, 3, 4, 5 or 6. When the locking point part is A1, i is 1; when the locking point part is A2, i is 2; when the locking point part is A3, i is 3; when the locking point part is A4, i is 4; when the locking point part is A5, i is 5; when the locking point part is A6, i is 6. In an embodiment, 7075 high-strength hard aluminum material can be selected. The machined angle box installation surface abuts against the bottom fairing locking point platform installation surface, and riveting is used for connection. The button platform 7 and the hook 6 of the hook-type locking tool are suspended in the middle of the machined angle box through pins;

[0065] Finally, design the stopping method of the airframe connecting piece 8 and the bottom fairing connecting piece 9, specifically: as Figure 1 shown, a moment M needs to act on the bottom fairing locking point part 3, that is, the stopping action of the hook-type locking mechanism. Continue to optimize the design on the airframe connecting piece 8 and the bottom fairing connecting piece 9, see Figure 8 , add a boss 10 at the front end of the airframe connecting piece 8. The boss 10 is a square boss. The boss 10 is perpendicular to the reference plane P1 for the installation of the card seat and is parallel to the installation surface P41. Add a top plate 11 above the bottom fairing connecting piece 9. The top plate 11 is perpendicular to the installation surface P41 and is parallel to the reference plane P1. After the two connecting pieces are installed, in the locked state of the hook-type locking mechanism, the boss 10 and the top plate 11 are vertically intersecting and abut against each other.

[0066] Obtain the connecting pieces of the hook-type locking tools for the remaining 5 locking point parts A3, A5, A2, A4, and A6 in sequence according to the above operations. Specifically as follows:

[0067] For the locking point part A3,

[0068] First, design the airframe connecting piece 8, specifically: in the space of the locking point part A3 in step four, design a machined angle box between the card seat 4 of the hook-type locking tool and the airframe bottom structure 1. Taking the reference plane P1 for the installation of the card seat and the reference plane P53 for the installation of the airframe bottom plate structure as the positioning reference, design the machined angle box into a wedge shape, as Figure 6 shown. 7075 high-strength hard aluminum material can be selected. The machined angle box airframe installation surface abuts against the airframe bottom structure 1, and riveting is used for connection. The card seat 4 of the hook-type locking tool abuts against the card seat installation surface of the machined angle box. There are 4 through holes on the angle box installation surface, and screws can be used to screw the angle box;

[0069] Then, design the bottom fairing connecting piece 9, specifically: in the space of the locking point part A3 in step four, design a machined angle box between the button platform 7 of the hook-type locking tool and the bottom fairing 2. Taking the installation surface P43 of the bottom fairing as the positioning reference, the reference plane P2 of the button platform coincides with the installation surface P43. Taking the hook rotation axis L2 as the reference, design the machined angle box into a shape like the Chinese character 'ji', asFigure 7 As shown. 7075 high-strength hard aluminum material can be selected. The machined angle box installation surface abuts against the installation surface of the locking point platform at the bottom fairing, and is connected by riveting. The button platform 7 and the hook 6 of the hook-type locking sleeve are suspended in the middle of the machined angle box through pins;

[0070] Finally, design the stopping method of the fuselage connecting piece 8 and the bottom fairing connecting piece 9. Specifically: as Figure 1 shown, a moment M needs to act on the locking point part 3 of the bottom fairing, that is, the stopping action of the hook-type locking mechanism. Continue to optimize the design on the fuselage connecting piece 8 and the bottom fairing connecting piece 9. Refer to Figure 8 . Add a boss 10 at the front end of the fuselage connecting piece 8. The boss 10 is perpendicular to the reference plane P1 for the installation of the card seat and parallel to the installation surface P43. Add a top plate 11 above the bottom fairing connecting piece 9. The top plate 11 is perpendicular to the installation surface P43 and parallel to the reference plane P1. After the two connecting pieces are installed, in the locked state of the hook-type locking mechanism, the boss 10 and the top plate 11 intersect vertically and abut against each other.

[0071] For the locking point part A5,

[0072] First, design the fuselage connecting piece 8. Specifically: in the space at the position of the locking point part A5 in step four, design a machined angle box between the card seat 4 of the hook-type locking sleeve and the fuselage bottom structure 1. Taking the reference plane P1 for the installation of the card seat and the reference plane P55 for the installation of the fuselage bottom plate structure as the positioning reference, design the machined angle box into a wedge shape, as Figure 6 shown. 7075 high-strength hard aluminum material can be selected. The installation surface of the machined angle box on the fuselage abuts against the fuselage bottom structure 1 and is connected by riveting. The card seat 4 of the hook-type locking sleeve abuts against the card seat installation surface of the machined angle box. There are 4 through holes on the angle box installation surface, and screws can be used to screw the angle box;

[0073] Then, design the bottom fairing connecting piece 9. Specifically: in the space at the position of the locking point part A5 in step four, design a machined angle box between the button platform 7 of the hook-type locking sleeve and the bottom fairing 2. Taking the installation surface P45 of the bottom fairing as the positioning reference, the reference plane P2 of the button platform coincides with the installation surface P45. Taking the hook rotation axis L2 as the reference, design the machined angle box into a shape like the Chinese character 'ji', as Figure 7 shown. 7075 high-strength hard aluminum material can be selected. The installation surface of the machined angle box abuts against the installation surface of the locking point platform at the bottom fairing and is connected by riveting. The button platform 7 and the hook 6 of the hook-type locking sleeve are suspended in the middle of the machined angle box through pins;

[0074] Finally, design the stopping method of the fuselage connecting piece 8 and the bottom fairing connecting piece 9. Specifically: as Figure 1As shown, a moment M needs to act on the bottom fairing locking point part 3, that is, the stopping action of the hook-type locking mechanism. Continue to optimize the design on the airframe connecting piece 8 and the bottom fairing connecting piece 9. Refer to Figure 8 , add a boss 10 at the front end of the airframe connecting piece 8. The boss 10 is perpendicular to the reference plane P1 for the installation of the clamping seat and is parallel to the installation surface P45. Add a top plate 11 above the bottom fairing connecting piece 9. The top plate 11 is perpendicular to the installation surface P45 and is parallel to the reference plane P1. After the two connecting pieces are installed, in the locked state of the hook-type locking mechanism, the boss 10 and the top plate 11 intersect vertically and are in contact with each other.

[0075] For the locking point part A2,

[0076] First, design the airframe connecting piece 8. Specifically: in the space at the position of the locking point part A2 in step four, design a machined angle box between the clamping seat 4 of the hook-type locking tool and the airframe bottom structure 1. With the reference plane P1 for the installation of the clamping seat and the reference plane P52 for the installation of the airframe bottom plate structure as the positioning references, design the machined angle box into a wedge shape, as Figure 6 shown. 7075 high-strength hard aluminum material can be selected. The installation surface of the machined angle box on the airframe is in contact with the airframe bottom structure 1 and is connected by riveting. The clamping seat 4 of the hook-type locking tool is in contact with the clamping seat installation surface of the machined angle box. There are 4 through holes on the angle box installation surface, and screws can be used to screw the angle box;

[0077] Then, design the bottom fairing connecting piece 9. Specifically: in the space at the position of the locking point part A2 in step four, design a machined angle box between the button platform 7 of the hook-type locking tool and the bottom fairing 2. With the installation surface P42 of the bottom fairing as the positioning reference, the reference plane P2 of the button platform coincides with the installation surface P42. With the bending hook rotation axis L2 as the reference, design the machined angle box into a shape like Figure 7 shown. 7075 high-strength hard aluminum material can be selected. The installation surface of the machined angle box is in contact with the installation surface of the bottom fairing locking point platform and is connected by riveting. The button platform 7 and the bending hook 6 of the hook-type locking tool are suspended in the middle of the machined angle box through pins;

[0078] Finally, design the stopping method of the airframe connecting piece 8 and the bottom fairing connecting piece 9. Specifically: as Figure 1 shown, a moment M needs to act on the bottom fairing locking point part 3, that is, the stopping action of the hook-type locking mechanism. Continue to optimize the design on the airframe connecting piece 8 and the bottom fairing connecting piece 9. Refer to Figure 8, a boss 10 is added to the front end of the body connecting member 8. The boss 10 is perpendicular to the reference plane P1 for the installation of the clamping seat and is parallel to the installation surface P42. A top plate 11 is added above the bottom fairing connecting member 9. The top plate 11 is perpendicular to the installation surface P42 and is parallel to the reference plane P1. After the two connecting members are installed, in the locked state of the hook-type locking mechanism, the boss 10 and the top plate 11 intersect perpendicularly and abut against each other.

[0079] For the locking point part A4,

[0080] First, design the body connecting member 8. Specifically: in the space at the locking point part A4 in step four, a machined angle box is designed between the clamping seat 4 of the hook-type locking set and the bottom structure 1 of the fuselage. With the reference plane P1 for the installation of the clamping seat and the reference plane P54 for the installation of the fuselage bottom structure as the positioning references, the machined angle box is designed in a wedge shape, as Figure 6 shown. 7075 high-strength hard aluminum material can be selected. The installation surface of the machined angle box on the fuselage abuts against the bottom structure 1 of the fuselage, and they are connected by riveting. The clamping seat 4 of the hook-type locking set abuts against the installation surface of the machined angle box. There are 4 through holes on the installation surface of the angle box, and screws can be used to screw-connect with the angle box;

[0081] Then, design the bottom fairing connecting member 9. Specifically: in the space at the locking point part A4 in step four, a machined angle box is designed between the button platform 7 of the hook-type locking set and the bottom fairing 2. With the installation surface P44 of the bottom fairing as the positioning reference, the reference plane P2 of the button platform coincides with the installation surface P44. With the bending hook rotation axis L2 as the reference, the machined angle box is designed in a shape like Figure 7 shown. 7075 high-strength hard aluminum material can be selected. The installation surface of the machined angle box abuts against the installation surface of the locking point platform of the bottom fairing, and they are connected by riveting. The button platform 7 and the bending hook 6 of the hook-type locking set are suspended in the middle of the machined angle box through pins;

[0082] Finally, design the stopping method for the body connecting member 8 and the bottom fairing connecting member 9. Specifically: as Figure 1 shown, a moment M needs to act on the locking point part 3 of the bottom fairing, that is, the stopping effect of the hook-type locking mechanism. Continue to optimize the design on the body connecting member 8 and the bottom fairing connecting member 9. Refer to Figure 8 , a boss 10 is added to the front end of the body connecting member 8. The boss 10 is perpendicular to the reference plane P1 for the installation of the clamping seat and is parallel to the installation surface P44. A top plate 11 is added above the bottom fairing connecting member 9. The top plate 11 is perpendicular to the installation surface P44 and is parallel to the reference plane P1. After the two connecting members are installed, in the locked state of the hook-type locking mechanism, the boss 10 and the top plate 11 intersect perpendicularly and abut against each other.

[0083] For the locking point part A6,

[0084] First, design the airframe connecting piece 8, specifically: in the space at the locking point part A6 in Step 4, design a machined angle box between the clamping seat 4 of the hook-type locking sleeve and the airframe bottom structure 1. Taking the reference plane P1 for the installation of the clamping seat and the reference plane P56 for the installation of the airframe bottom plate structure as the positioning references, design the machined angle box in a wedge shape, as Figure 6 shown. 7075 high-strength hard aluminum material can be selected. The airframe installation surface of the machined angle box abuts against the airframe bottom structure 1, and is connected by riveting. The clamping seat 4 of the hook-type locking sleeve abuts against the clamping seat installation surface of the machined angle box. There are 4 through holes on the angle box installation surface, and screws can be used to screw-connect with the angle box;

[0085] Then, design the bottom fairing connecting piece 9, specifically: in the space at the locking point part A6 in Step 4, design a machined angle box between the button platform 7 of the hook-type locking sleeve and the bottom fairing 2. Taking the installation surface P46 of the bottom fairing as the positioning reference, the reference plane P2 of the button platform coincides with the installation surface P46. Taking the bending hook rotation axis L2 as the reference, design the machined angle box in a shape like a capital "J", as Figure 7 shown. 7075 high-strength hard aluminum material can be selected. The installation surface of the machined angle box abuts against the locking point platform installation surface of the bottom fairing, and is connected by riveting. The button platform 7 and the bending hook 6 of the hook-type locking sleeve are suspended in the middle of the machined angle box by pins;

[0086] Finally, design the stopping method for the airframe connecting piece 8 and the bottom fairing connecting piece 9, specifically: as Figure 1 shown, a moment M needs to act on the locking point part 3 of the bottom fairing, that is, the stopping effect of the hook-type locking mechanism. Continue to optimize the design on the airframe connecting piece 8 and the bottom fairing connecting piece 9. Refer to Figure 8 . Add a boss 10 at the front end of the airframe connecting piece 8. The boss 10 is perpendicular to the reference plane P1 for the installation of the clamping seat and is parallel to the installation surface P46. Add a top plate 11 above the bottom fairing connecting piece 9. The top plate 11 is perpendicular to the installation surface P46 and is parallel to the reference plane P1. After the two connecting pieces are installed, in the locked state of the hook-type locking mechanism, the boss 10 and the top plate 11 intersect vertically and abut against each other.

[0087] Figure 9 FIG. is the schematic diagram of the final form obtained by using the design method of the locking mechanism provided by the present invention. According to the design method of the present invention, by applying a standard locking sleeve, the locking mechanism system of the bottom fairing is finally designed. This locking mechanism system is provided with 6 sets of hook-type locking mechanisms L on the bottom fairing. Through this locking mechanism system, the bottom fairing can be locked under the airframe bottom structure, and can be easily removed to move the bottom fairing out of the airframe structure, facilitating the maintenance and support of the airframe bottom by the ground crew.

[0088] As shown in the figure, a single set of the locking mechanism is as follows Figure 10 shown. The body connecting piece 8 and the bottom fairing connecting piece 9 are made of high-strength aluminum alloy. Among them, the body connecting piece 8 is arranged under the bottom structure of the body by riveting. The bottom fairing connecting piece 9 is arranged on the lock seat installation platform 100 of the bottom fairing by riveting. The lock of the hook 6 in the hook-type locking kit is installed on the bottom fairing connecting piece through a pin. The lock seat of the square ring buckle 5 in the hook-type locking kit is installed on the body connecting piece 8 through a bolt. By adjusting the length of the square ring buckle, the boss 10 of the body connecting piece 8 and the top plate 11 of the bottom fairing connecting piece 9 are made to abut. When the hook-type locking kit is enabled, first hang the hook 6 on the square ring buckle 5, and by pressing the button platform 7, the hook-type locking kit with the hook tightens itself through its own elastic force, pulls the square ring buckle 5, and realizes locking, so as to realize the locking of the lock point here of the bottom fairing. Through the locking of 6 lock points, the locking of the entire fairing on the bottom structure of the body is realized.

[0089] 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 design method of a locking mechanism, characterized in that, Including: Step 1: Combine the force loads of the bottom fairing fixed to the bottom structure of the fuselage and the working principle of the hook-type locking kit to conduct a force analysis of the locking point part; Step 2: Based on the force analysis results, set the position of the locking point part on the bottom fairing; Step 3: Set the reference and boundary of the hook-type locking kit in the locked state to obtain the installation interface of the hook-type locking kit in the locked state; Step 4: In the full-aircraft assembly environment, in the position space of the locking point part, based on the force analysis results, place the installation interface of the hook-type locking kit to obtain the installation surface of the locking point platform and design the locking point installation platform of the bottom fairing; Step 5: Design the connecting piece of the hook-type locking kit and the stopping method of the connecting piece.

2. The method according to claim 1, characterized in that, In Step 1, in the flight state, combine the force loads of the bottom fairing fixed to the bottom structure of the fuselage and the working principle of the hook-type locking kit to determine the force state of the locking point part of the bottom fairing, and preliminarily determine the force and position relationship between the locking point part and the connecting piece part in the locked state.

3. The method according to claim 1, wherein The positions of the locking point part and the connecting piece part are close to the edge of the bottom fairing.

4. The method according to claim 3, characterized in that, In Step 2, based on the force analysis results, on the bottom fairing, from front to back, set 3 locking point parts on one side, namely A1, A3, and A5; set 3 locking point parts on the other side, namely A2, A4, and A6. The locking point parts on both sides are symmetric left and right.

5. The method according to claim 4, characterized in that In Step 3, the process of obtaining the installation interface of the hook-type locking kit in the locked state includes: First, conduct the reference setting of the hook-type locking kit in the locked state: digitalize the hook-type locking kit in the locked state, introduce the digital model of the hook-type locking kit in the assembly environment, and set the key reference: when the hook of the hook-type locking kit locks the square loop, the axis L0 of the hook rotating around the cylindrical axis of the square loop coincides with the center line L1 of the cylindrical axis of the square loop; the hook rotation axis is L2, the reference plane for installing the card seat on the airframe structure is P1, the reference plane of the button platform is P2, on the reference plane P2, the center line of the button platform is L3, and the central axis of the tail shaft of the square loop is L4; Then, conduct the boundary setting of the hook-type locking kit: Based on the digital model of the hook-type locking kit, combined with the installation requirements, on the reference plane P2, with the center line L3 as the center, construct a first rectangle S1, and the first rectangle S1 is the boundary of the button installation surface of the hook-type locking kit; on the reference plane P2, with the center line L3 as the center, construct a second rectangle S2 with an area smaller than that of the first rectangle S1. The second rectangle S2 is the button opening boundary of the hook-type locking kit, and the gap between the button opening boundary and the edge of the button platform is equidistant. Set the center point O1 of the first rectangle S1 as the center point of the locked button reference plane; The above reference and boundary belong to the same assembly coordinate system and serve as the installation interface of the hook-type locking kit.

6. The method according to claim 5, characterized in that In Step 4, the process of designing the locking point installation platform of the bottom fairing includes: In the full-aircraft assembly environment, in the space at the A1 position of the locking point, based on the force analysis results of Step 1, insert the installation interface of the hook-type locking sleeve. The center line L3 of the button platform is perpendicular to the edge curve of the bottom fairing. Through the vertical projection of the center point O1, obtain the tangent plane P31 on the outer surface of the bottom fairing. Offset the tangent plane P31 inward towards the fuselage to obtain the locking button installation surface P41 of the bottom fairing; project the first rectangle S1 onto the installation surface P41, and after rounding, obtain the first boundary S31. The area occupied by the first boundary S31 is the button platform area of the bottom fairing in the planar state; project the first boundary S31 onto the outer surface of the bottom fairing and simultaneously expand and offset it to obtain the second boundary S41. Connect the outer surface of the bottom fairing outside the second boundary S41 and the plane inside the first boundary S31 to finally obtain a composite surface. The four edges of the composite surface are smoothly transitioned, and the interior is a plane recessed in the outer surface of the bottom fairing, and this plane is the locking point platform installation surface; project the second rectangle S2 onto this locking point platform installation surface to obtain the button opening boundary S51; The process of obtaining the locking point platform installation surfaces of the locking points A3, A5, A2, A4, and A6 is the same as the process of obtaining the locking point platform installation surface of the locking point A1.

7. The method according to claim 6, characterized in that, The connecting parts of the hook-type locking sleeve include a fuselage connecting part and a bottom fairing connecting part. For the locking point A1, in Step 5, the process of designing the connecting parts of the hook-type locking sleeve includes: First, design the fuselage connecting part: In the space at the A1 position of the locking point in Step 4, design a machined angle box between the card seat of the hook-type locking sleeve and the bottom structure of the fuselage. Using the reference plane P1 for card seat installation and the reference plane P51 for the bottom structure installation of the fuselage as the positioning references, design the machined angle box in a wedge shape. The fuselage installation surface of the machined angle box abuts against the bottom structure of the fuselage, and is connected by riveting; the card seat of the hook-type locking sleeve abuts against the card seat installation surface of the machined angle box; Then, design the bottom fairing connecting part: In the space at the A1 position of the locking point in Step 4, design a machined angle box between the locking sleeve button platform and the bottom fairing. Using the locking button installation surface P41 of the bottom fairing as the positioning reference, the reference plane P2 of the button platform coincides with the locking button installation surface P41; with the hook rotation axis L2 as the reference, design the machined angle box in a shape like the Chinese character "ji". The installation surface of the machined angle box abuts against the locking point platform installation surface of the bottom fairing, and is connected by riveting. The hook-type locking sleeve button platform and the hook are suspended in the middle of the machined angle box by pins; Finally, design the stopping method for the fuselage connecting part and the bottom fairing connecting part: Add a boss at the front end of the fuselage connecting part. This boss is perpendicular to the reference plane P1 for card seat installation and is parallel to the installation surface P41; add a top plate above the bottom fairing connecting part. This top plate is perpendicular to the installation surface P41 and is parallel to the reference plane P1; after the two connecting parts are installed, in the locked state of the hook-type locking mechanism, the boss and the top plate intersect perpendicularly and abut against each other; The design process of the connecting piece of the hook-type locking kit at the locking points A3, A5, A2, A4 and A6 is the same as that of the locking point A1.

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