A method of designing a locking mechanism

Abstract

The application provides a design method of a locking mechanism, and belongs to the technical field of aviation function structure design. The method comprises the following steps: step one, stress analysis of a locking point position is performed in combination with the stress load of a bottom fairing fixed on a bottom structure of an airframe and the working principle of a hook-type locking sleeve; step two, position setting of the locking point position on the bottom fairing is performed based on the stress analysis result; step three, setting of a hook-type locking sleeve reference and boundary in a locked state is performed, and a hook-type locking sleeve mounting interface in the locked state is obtained; step four, a bottom fairing locking point mounting platform is designed; and step five, a connecting piece of the hook-type locking sleeve and a locking mode of the connecting piece are designed. Through modeling design analysis, rapid disassembly and assembly of the hook-type locking mechanism of the bottom fairing under the bottom structure of the airframe in a non-hinge mode state are realized; the manufacturing process of the fairing is improved, and the aerodynamic environment of the fairing during flight is improved; and the method can be used for design of a bottom locking structure of a cockpit.

Description

TECHNICAL FIELD

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

[0002] In the optimization and improvement design of the bottom fairing of a helicopter, the original bottom fairing locking mechanism adopts a ring-shaped pull buckle locking device, which needs to be pulled by hand when being opened and closed, and a large force needs to be applied for operation. The operation is inconvenient and the fingers are easy to be hurt. In addition, in the design, not only the shape of the bottom of the fuselage will change, but also the structure of the left and right sides of the original body bottom will change, resulting in that the connection and installation surface of the new bottom fairing and the fuselage structure is different from before. The quick disassembly and installation cannot be realized.

[0003] Therefore, it is necessary to reconsider the design method of the locking mechanism, and the bottom fairing is arranged under the bottom structure of the fuselage, so as to realize the quick disassembly and installation. SUMMARY

[0004] In order to solve the technical problem that the bottom fairing cannot be simply and quickly disassembled and installed on the bottom structure of the fuselage in the prior art, the present application provides a design method of a locking mechanism, which arranges the bottom fairing under the bottom structure of the fuselage, realizes the quick disassembly and installation, and the technical scheme is as follows:

[0005] The present application provides a design method of a locking mechanism, which comprises the following steps:

[0006] Step one, force analysis of the locking point position is carried out in combination with the force load of the bottom fairing fixed on the bottom structure of the fuselage and the working principle of the hook-shaped locking sleeve.

[0007] Step two, the position of the locking point position is set on the bottom fairing based on the force analysis result.

[0008] Step three, the reference and boundary of the hook-shaped locking sleeve in the locking state are set, and the installation interface of the hook-shaped locking sleeve in the locking state is obtained.

[0009] Step four, in the full-machine assembly environment, the installation interface of the hook-shaped locking sleeve is placed in the position space of the locking point position based on the force analysis result, the locking point platform installation surface is obtained, and the bottom fairing locking point installation platform is designed.

[0010] Step five, the connecting piece of the hook-shaped locking sleeve and the stop mode of the connecting piece are designed.

[0011] In step one, the force state of the bottom fairing locking point position is determined in combination with the force load of the bottom fairing fixed on the bottom structure of the fuselage and the working principle of the hook-shaped locking sleeve in the flight state, and the force and position relationship of the locking point position and the connecting piece position in the locking state is preliminarily determined.

[0012] The locations of the locking point and the connector point are close to the edge of the bottom fairing.

[0013] In step two, based on the stress analysis result, three locking points, A1, A3 and A5, are set on one side of the bottom fairing from front to back, and three locking points, A2, A4 and A6, are set on the other side, and the locking points on the two sides are symmetrical.

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

[0015] First, the reference setting of the hook-type locking sleeve in the locked state is performed: the hook-type locking sleeve in the locked state is numerically modeled, the hook-type locking sleeve in the locked state is introduced into the assembly environment, and the key reference is set: when the hook of the hook-type locking sleeve is locked with the square ring buckle, the axis line L0 of the hook rotating around the cylindrical shaft of the square ring buckle coincides with the center line L1 of the cylindrical shaft of the square ring buckle; the bending hook rotating axis is L2, the seat is installed on the reference surface P1 of the machine body structure, the reference surface of the button platform is P2, the center line of the button platform on the reference surface P2 is L3, and the center axis of the square ring buckle tail shaft is L4.

[0016] Then, the boundary setting of the hook-type locking sleeve is performed: based on the hook-type locking sleeve numerical model, the first rectangle S1 is constructed with the center line L3 as the center on the reference surface P2, and the first rectangle S1 is the button installation surface boundary of the hook-type locking sleeve; the second rectangle S2 with an area smaller than that of the first rectangle S1 is constructed with the center line L3 as the center on the reference surface P2, and the second rectangle S2 is the button opening boundary of the hook-type locking sleeve, which is equidistant from the edge of the button platform, and the center point of the first rectangle S1 is set as O1 as the center point of the locking button reference surface.

[0017] The above-mentioned reference and boundary belong to the same assembly body coordinate system, and serve as the installation interface of the hook-type locking sleeve.

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

[0019] In the full machine assembly environment, in the position space of the locking point part A1, based on the stress analysis result of step one, the hook type locking sleeve installation interface is placed, the center line L3 of the button platform is perpendicular to the edge curve of the bottom fairing, the vertical projection through the center point O1 obtains the tangent plane P31 on the bottom fairing shape surface, the tangent plane P31 is offset to the inside of the fuselage, and the locking button installation surface P41 of the bottom fairing is obtained; the first rectangle S1 is projected onto the installation surface P41, and the first boundary S31 is obtained through the rounding treatment, and the area occupied by the first boundary S31 is the bottom fairing button platform area in the plane state; the first boundary S31 is projected into the bottom fairing shape surface, and the second boundary S41 is obtained by extending and offsetting, and the bottom fairing shape surface outside the second boundary S41 and the plane inside the first boundary S31 are connected, and finally a composite curved surface is obtained, the periphery of the composite curved surface is smoothly transitioned, and the inside is a plane sunk in the bottom fairing shape, which is a locking point platform installation surface; the second rectangle S2 is projected onto the locking point platform installation surface to obtain the button opening boundary S51;

[0020] The acquisition process of the locking point platform installation surface of the locking point parts A3, A5, A2, A4 and A6 is the same as that of the locking point platform installation surface of the locking point part A1.

[0021] Among them, the connecting piece of the hook type locking sleeve includes a machine body connecting piece and a bottom fairing connecting piece, and for the locking point part A1, in step five, the process of designing the connecting piece of the hook type locking sleeve includes:

[0022] Firstly, the machine body connecting piece is designed: in the position space of the locking point part A1 in step four, a machine angle box is designed between the clamping seat of the hook type locking sleeve and the bottom structure of the fuselage, the machine angle box is designed into a wedge shape with the clamping seat installation surface of the machine angle box abutting against the bottom structure of the fuselage and being connected by riveting; the clamping seat of the hook type locking sleeve abuts against the clamping seat installation surface of the machine angle box;

[0023] Then, the bottom fairing connecting piece is designed: in the position space of the locking point part A1 in step four, a machine angle box is designed between the locking sleeve button platform and the bottom fairing, the locking button installation surface P41 of the bottom fairing is taken as the positioning reference, and the reference surface P2 of the button platform coincides with the locking button installation surface P41; the machine angle box is designed into a U-shaped shape with the machine angle box installation surface abutting against the locking point platform installation surface of the bottom fairing and being connected by riveting, and the hook type locking sleeve button platform and the hook are hung in the middle of the machine angle box through a pin;

[0024] Finally, the stop mode of the body connecting piece and the bottom fairing connecting piece is designed: a boss is additionally arranged at the front end of the body connecting piece, the boss is perpendicular to the reference surface P1 of the clamping seat installation, and is parallel to the installation surface P41; a top plate is additionally arranged above the bottom fairing connecting piece, the top plate is perpendicular to the installation surface P41, and is parallel to the reference surface P1; after the two connecting pieces are installed, the boss and the top plate are perpendicular to each other and abut against each other in the locked state of the hook type locking mechanism.

[0025] The design process of the connecting piece of the hook type locking sleeve of the locking point positions A3, A5, A2, A4 and A6 is the same as that of the design process of the locking point position A1.

[0026] The beneficial effects of the present application are at least:

[0027] 1) A design method for installing a hook type locking sleeve locking mechanism is provided, and through modeling design analysis, the bottom fairing hook type locking mechanism under the bottom structure of the fuselage is quickly disassembled in a non-hinge mode state;

[0028] 2) Compared with the original bottom fairing, the present application makes the design of the bottom fairing simple and reliable, cancels the design of the locking point base filled with No. 17 filler (larger weight), cancels the design of the fairing edge notch (weakens the stiffness), improves the manufacturing process of the fairing (cancels the locking point base filling link and uses a mold to form once), 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 application can be applied to the design of the bottom locking structure of the cabin. At present, it has been implemented, and the actual effect is very good. BRIEF DESCRIPTION OF DRAWINGS

[0030] Figure 1 is a force diagram of the locking point position of the present application;

[0031] Figure 2 is a top view of the arrangement of the locking point position of the present application;

[0032] Figure 3 is a reference setting diagram of the hook type locking sleeve of the present application;

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

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

[0035] Figure 6 is a body connecting piece diagram of the present application;

[0036] Figure 7 is a bottom fairing connecting piece diagram of the present application;

[0037] Figure 8 is the schematic diagram of the locking mechanism connector of the present application;

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

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

[0040] Wherein, 1 - the bottom structure of the fuselage, 2 - the bottom fairing, 3 - the locking point position, 4 - the card seat, 5 - the square ring buckle, 6 - the hook, 7 - the button platform, 8 - the body connector, 9 - the bottom fairing connector, 10 - the boss, 11 - the top plate, 100 - the bottom fairing lock seat installation platform. DETAILED DESCRIPTION

[0041] The present application will be further described in detail by specific embodiments and drawings.

[0042] An embodiment of the present application provides a design method of a locking mechanism, specifically comprising the following steps:

[0043] Step one, stress analysis of the locking point position

[0044] Referring to Figure 1 , the bottom fairing 2 is taken as the research object, and the stress condition thereof is researched: in the flight state, the stress state of the locking point position 3 of the bottom fairing 2 is determined in combination with the stress load of the bottom fairing 2 fixed on the bottom structure of the fuselage 1 and the locking working principle of the hook type locking sleeve device, and the stress and position relationship of the locking point position 3 and the connector position in the locking state are preliminarily determined: the tension T is the acting force of the hook type locking sleeve device, the F is the aerodynamic load acting force, and the moment M is the acting moment of the fuselage structure. The position of the locking point position 3 and the connector position is close to the edge of the bottom fairing 2.

[0045] Step two, position setting of the locking point position

[0046] The stress analysis result of the locking position obtained in step one is obtained, and based on the consideration of safety redundancy, three locking point positions are set on the bottom fairing 2 from front to back on one side, which are A1, A3 and A5, and three locking point positions are set on the other side, which are A2, A4 and A6. The locking point positions on both sides are symmetrical, as shown in Figure 2 The position of the selected locking point position does not affect the surrounding structure and system.

[0047] Step three, obtaining the installation interface of the hook type locking sleeve device (locking state)

[0048] 1. The datum setting of the hook type locking sleeve device is performed,

[0049] Referring to Figure 3 The hook type locking sleeve in the locked state is modeled. In the assembly environment, the hook type locking sleeve in the locked state is introduced, and the key datum is set: when the hook 6 of the hook type locking sleeve locks the square ring buckle 5, the axis L0 of the rotation of the hook 6 around the cylindrical shaft of the square ring buckle 5 coincides with the center line L1 of the cylindrical shaft of the square ring buckle 5. The rotation axis of the hook 6 is L2. The reference surface of the mounting of the cartridge 4 on the machine body structure is P1. The reference surface of the button platform 7 is P2. On the reference surface P2, the center line of the button platform 7 is L3. The center axis of the tail shaft of the square ring buckle 5 is L4.

[0050] 2. Boundary setting of the hook type locking sleeve is performed,

[0051] Referring to Figure 4 , referring to the hook type locking sleeve model, combined with the installation requirements, a rectangle S1 is built on the reference surface P2 with the center line L3 as the center. The rectangle S1 is the button mounting surface boundary of the hook type locking sleeve. Similarly, another rectangle S2 is built on the reference surface P2 with the center line L3 as the center. The area of the rectangle S2 is smaller than that of the rectangle S1. The rectangle S2 is the button opening boundary of the hook type locking sleeve, which is equidistant from the edge of the button platform 7. The center point of the rectangle S1 is set as O1, which is taken as the center point of the locking button reference surface.

[0052] The above datum and boundary belong to the same assembly coordinate system, which serves as the installation interface of the hook type locking sleeve.

[0053] Step four, design the bottom fairing lock point mounting platform

[0054] In the full machine assembly environment, in the position space of the lock point part A1, based on the stress analysis results of step one, the hook type 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, the vertical projection of the center point O1 is obtained, and the tangent plane P31 on the outer surface of the bottom fairing 2 is obtained. The tangent plane P31 is offset to the inside of the fuselage, and the locking button mounting surface P41 of the bottom fairing 2 is obtained; the rectangle S1 is projected onto the mounting surface P41, and after rounding treatment, the boundary S31 is obtained. The area occupied by the boundary S31 is the button platform area of the bottom fairing 2 in the flat state; the boundary S31 is projected into the outer surface of the bottom fairing 2, and the boundary S41 is obtained by expanding and offsetting; after cutting, bridging and combining, etc. Surface processing, the outer surface of the bottom fairing 2 outside the boundary S41 and the plane inside the boundary S31 are connected, and finally a synthetic surface is obtained. The four edges of the synthetic surface are smoothly transitioned, and the inside is a plane that is sunken in the shape of the bottom fairing. The plane is the lock point platform mounting surface. The rectangle S2 is projected onto the lock point platform mounting surface to obtain the button opening boundary S51. Referring to Figure 5 . Figure 5In the present embodiment, i is equal to 1, 2, 3, 4, 5 or 6. When the locking point position is A1, i is 1; when the locking point position is A2, i is 2; when the locking point position is A3, i is 3; when the locking point position is A4, i is 4; when the locking point position is A5, i is 5; and when the locking point position is A6, i is 6.

[0055] The locking point platform installation surface of the remaining five locking point positions A3, A5, A2, A4 and A6 is obtained in sequence according to the above operation, and the specific operation is as follows:

[0056] In the locking point position A3 position space, based on the stress analysis result of step one, the hook type 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, the vertical projection through the center point O1 is obtained, the tangent plane P33 on the outer surface of the bottom fairing 2 is obtained, the tangent plane P33 is offset to the inside of the fuselage, and the locking button installation surface P43 of the bottom fairing 2 is obtained; the rectangular S1 is projected onto the installation surface P43, and after rounding treatment, the boundary S33 is obtained, and the area occupied by the boundary S33 is the button platform area of the bottom fairing 2 in the plane state; the boundary S33 is projected into the outer surface of the bottom fairing 2, and at the same time, the boundary S43 is obtained by expanding and offsetting; after cutting, bridging and combining and other surface processing, the outer surface of the bottom fairing 2 outside the boundary S43 and the plane inside the boundary S33 are connected, and finally a synthetic surface is obtained, the edges of the synthetic surface are smoothly transitioned, the inside is a plane sunk in the bottom fairing shape, and the plane is the locking point platform installation surface. The rectangular S2 is projected onto the locking point platform installation surface to obtain the button opening boundary S53.

[0057] In the locking point position A5 position space, based on the stress analysis result of step one, the hook type 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, the vertical projection through the center point O1 is obtained, the tangent plane P35 on the outer surface of the bottom fairing 2 is obtained, the tangent plane P35 is offset to the inside of the fuselage, and the locking button installation surface P45 of the bottom fairing 2 is obtained; the rectangular S1 is projected onto the installation surface P45, and after rounding treatment, the boundary S35 is obtained, and the area occupied by the boundary S35 is the button platform area of the bottom fairing 2 in the plane state; the boundary S35 is projected into the outer surface of the bottom fairing 2, and at the same time, the boundary S45 is obtained by expanding and offsetting; after cutting, bridging and combining and other surface processing, the outer surface of the bottom fairing 2 outside the boundary S45 and the plane inside the boundary S35 are connected, and finally a synthetic surface is obtained, the edges of the synthetic surface are smoothly transitioned, the inside is a plane sunk in the bottom fairing shape, and the plane is the locking point platform installation surface. The rectangular S2 is projected onto the locking point platform installation surface to obtain the button opening boundary S55.

[0058] In the position space of the lock point part A2, based on the stress analysis result of step one, the hook type locking sleeve installation interface is put in, the center line L3 of the button platform 7 is perpendicular to the edge curve of the bottom fairing 2, the vertical projection through the center point O1 obtains the tangent plane P32 on the surface of the bottom fairing 2, the tangent plane P32 is biased towards the inside of the fuselage, and the locking button installation surface P42 of the bottom fairing 2 is obtained; the rectangle S1 is projected onto the installation surface P42, and after rounding treatment, the boundary S32 is obtained, and the area occupied by the boundary S32 is the button platform area of the bottom fairing 2 in the plane state; the boundary S32 is projected into the surface of the bottom fairing 2, and at the same time, the boundary S42 is obtained by expanding and offsetting; after cutting, bridging and combining and other surface processing, the surface of the bottom fairing 2 outside the boundary S42 and the plane inside the boundary S32 are connected, and finally a synthetic surface is obtained, the edges of the synthetic surface are smoothly transitioned, the inside is a plane sunk in the bottom fairing surface, and the plane is the lock point platform installation surface. The rectangle S2 is projected onto the lock point platform installation surface to obtain the button opening boundary S52.

[0059] In the position space of the lock point part A4, based on the stress analysis result of step one, the hook type locking sleeve installation interface is put in, the center line L3 of the button platform 7 is perpendicular to the edge curve of the bottom fairing 2, the vertical projection through the center point O1 obtains the tangent plane P34 on the surface of the bottom fairing 2, the tangent plane P34 is biased towards the inside of the fuselage, and the locking button installation surface P44 of the bottom fairing 2 is obtained; the rectangle S1 is projected onto the installation surface P44, and after rounding treatment, the boundary S34 is obtained, and the area occupied by the boundary S34 is the button platform area of the bottom fairing 2 in the plane state; the boundary S34 is projected into the surface of the bottom fairing 2, and at the same time, the boundary S44 is obtained by expanding and offsetting; after cutting, bridging and combining and other surface processing, the surface of the bottom fairing 2 outside the boundary S44 and the plane inside the boundary S34 are connected, and finally a synthetic surface is obtained, the edges of the synthetic surface are smoothly transitioned, the inside is a plane sunk in the bottom fairing surface, and the plane is the lock point platform installation surface. The rectangle S2 is projected onto the lock point platform installation surface to obtain the button opening boundary S54.

[0060] In the position space of the locking point A6, based on the stress analysis result of step one, a hook type 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, the vertical projection through the center point O1 obtains the tangent plane P36 on the profile surface of the bottom fairing 2, the tangent plane P36 is offset to the inside of the fuselage, and the locking button installation surface P46 of the bottom fairing 2 is obtained; the rectangle S1 is projected onto the installation surface P46, and after rounding treatment, the boundary S36 is obtained, and the area occupied by the boundary S36 is the button platform area of the bottom fairing 2 in the plane state; the boundary S36 is projected into the profile surface of the bottom fairing 2, and the boundary S46 is obtained by extending and offsetting; after surface processing such as cutting, bridging and combining, the profile surface of the bottom fairing 2 outside the boundary S46 and the plane inside the boundary S36 are connected, and finally a synthetic surface is obtained, the periphery of the synthetic surface is smoothly transitioned, and the inside is a plane sunk in the profile of the bottom fairing, which is the locking point platform installation surface. The rectangle S2 is projected onto the locking point platform installation surface to obtain the button opening boundary S56.

[0061] Step five, design the connecting piece of the hook type locking sleeve

[0062] For the locking point A1,

[0063] Firstly, the machine body connecting piece 8 is designed, specifically: in the position space of the locking point A1 in step four, a machine angle box is designed between the hook type locking sleeve holder 4 and the bottom structure 1 of the fuselage, taking the reference surface P1 of the holder 4 and the installation reference surface P51 of the bottom structure of the fuselage as the positioning reference, the machine angle box is designed in the shape of a wedge, as shown in Figure 6 . Figure 6 In the formula, i is equal to 1, 2, 3, 4, 5 or 6. When the locking point is A1, i is 1; when the locking point is A2, i is 2; when the locking point is A3, i is 3; when the locking point is A4, i is 4; when the locking point is A5, i is 5; and when the locking point is A6, i is 6. In an embodiment, 7075 high-strength hard aluminum material can be selected. The machine angle box machine installation surface is attached to the bottom structure 1 of the fuselage, and is connected by riveting. The holder 4 of the hook type locking sleeve is attached to the holder installation surface of the angle box. There are four through holes on the angle box installation surface, which can be screwed with the angle box;

[0064] Then, the bottom fairing connecting piece 9 is designed, specifically: in the position space of the locking point A1 in step four, a machine angle box is designed between the hook type locking sleeve button platform 7 and the bottom fairing 2, taking the installation surface P41 of the bottom fairing as the positioning reference, and the reference surface P2 of the button platform 7 coincides with the installation surface P41. Taking the hook rotating axis L2 as the reference, the machine angle box is designed in the shape of a U, as shown in Figure 7 . Figure 7In the example, i is 1, 2, 3, 4, 5, or 6. When the locking point is A1, i is 1; when the locking point is A2, i is 2; when the locking point is A3, i is 3; when the locking point is A4, i is 4; when the locking point is A5, i is 5; and when the locking point is A6, i is 6. In one embodiment, 7075 high-strength duralumin can be used. The mounting surface of the machined corner box is in contact with the mounting surface of the bottom fairing locking point platform and riveted together. The button platform 7 and hook 6 of the hook-type locking set are suspended in the middle of the machined corner box by pins.

[0065] Finally, the stopping method of the body connector 8 and the bottom fairing connector 9 is designed, specifically: Figure 1 As shown, the bottom fairing locking point 3 needs to have a torque M, that is, the stopping effect of the hook type locking mechanism. Figure 8 A square boss 10 is added to the front end of the body connector 8. Boss 10 is perpendicular to the base mounting datum plane P1 and parallel to the mounting surface P41. A top plate 11 is added above the bottom fairing connector 9. Top plate 11 is perpendicular to the mounting surface P41 and parallel to the datum plane P1. After the two connectors are installed, when the hook-type locking mechanism is locked, boss 10 and top plate 11 intersect perpendicularly and abut against each other.

[0066] Follow the above steps to obtain the connectors of the hook-type locking sets at the remaining five locking points A3, A5, A2, A4, and A6. The details are as follows:

[0067] For the locking point A3,

[0068] First, design the fuselage connector 8. Specifically, in the locking point position A3 of step 4, design a machine-made corner box between the hook-type locking set's base 4 and the fuselage bottom structure 1. Use the base installation reference plane P1 and the fuselage bottom plate structure installation reference plane P53 as positioning references, and design the machine-made corner box into a wedge shape, such as Figure 6 As shown, 7075 high-strength duralumin can be used. The machined corner box fuselage mounting surface is abutted against the fuselage bottom structure 1 and riveted together. The hook-type locking set's holder 4 is abutted against the machined corner box's holder mounting surface. The corner box mounting surface has four through-holes that can be screwed to the corner box.

[0069] Next, design the bottom fairing connector 9. Specifically, in the locking point A3 space in step 4, design a machined angle box between the button platform 7 of the hook-type locking set and the bottom fairing 2. Use the bottom fairing mounting surface P43 as the positioning reference, and the button platform's reference surface P2 coincides with the mounting surface P43. Using the hook's rotation axis L2 as the reference, design the machined angle box into a "J" shape, as shown in the following example.Figure 7 The 7075 high-strength hard aluminum material is selected, the machine corner box mounting surface is attached to the bottom fairing locking point platform mounting surface, and the riveting mode is used for connection. The button platform 7 and the hook 6 of the hook type locking mechanism are suspended in the middle of the machine corner box through a pin.

[0070] Finally, the locking mode of the machine body connecting piece 8 and the bottom fairing connecting piece 9 is designed. Specifically, as shown in Figure 1 The bottom fairing locking point part 3 needs the torque M, that is, the locking action of the hook type locking mechanism. The machine body connecting piece 8 and the bottom fairing connecting piece 9 are continuously optimized, as shown in Figure 8 A boss 10 is additionally arranged at the front end of the machine body connecting piece 8. The boss 10 is perpendicular to the reference surface P1 of the clamping seat mounting surface and parallel to the mounting surface P43. A top plate 11 is additionally arranged above the bottom fairing connecting piece 9. The top plate 11 is perpendicular to the mounting surface P43 and parallel to the reference surface P1. After the two connecting pieces are mounted, the boss 10 and the top plate 11 are perpendicular to each other and abut against each other in the locking state of the hook type locking mechanism.

[0071] For the locking point part A5,

[0072] Firstly, the machine body connecting piece 8 is designed. Specifically, in the position space of the locking point part A5 in step four, a machine corner box is designed between the clamping seat 4 of the hook type locking mechanism and the bottom structure 1 of the machine body. The reference surface P1 of the clamping seat mounting surface and the mounting reference surface P55 of the bottom structure of the machine body are used as positioning references. The machine corner box is designed in a wedge shape, as shown in Figure 6 The 7075 high-strength hard aluminum material is selected. The machine corner box mounting surface is attached to the bottom structure 1 of the machine body, and the riveting mode is used for connection. The clamping seat 4 of the hook type locking mechanism is attached to the clamping seat mounting surface of the machine corner box. Four through holes are arranged on the corner box mounting surface, and screws can be used for screwing with the corner box;

[0073] Then, the bottom fairing connecting piece 9 is designed. Specifically, in the position space of the locking point part A5 in step four, a machine corner box is designed between the button platform 7 of the hook type locking mechanism and the bottom fairing 2. The mounting surface P45 of the bottom fairing is used as a positioning reference. The reference surface P2 of the button platform is coincident with the mounting surface P45. The machine corner box is designed in a few character shapes with the hook rotating axis L2 as a reference, as shown in Figure 7 The 7075 high-strength hard aluminum material is selected. The machine corner box mounting surface is attached to the bottom fairing locking point platform mounting surface, and the riveting mode is used for connection. The button platform 7 and the hook 6 of the hook type locking mechanism are suspended in the middle of the machine corner box through a pin.

[0074] Finally, the locking mode of the machine body connecting piece 8 and the bottom fairing connecting piece 9 is designed. Specifically, as shown in Figure 1As shown, the bottom fairing locking point 3 needs torque M, that is, the stop action of the hook type locking mechanism. The body connector 8 and the bottom fairing connector 9 are continuously optimized, as shown in Figure 8 A boss 10 is added at the front end of the body connector 8, which is perpendicular to the reference surface P1 of the card seat installation and parallel to the installation surface P45. A top plate 11 is added above the bottom fairing connector 9, which is perpendicular to the installation surface P45 and parallel to the reference surface P1. After the installation of the two connectors, the boss 10 and the top plate 11 intersect perpendicularly and abut against each other in the locked state of the hook type locking mechanism.

[0075] For the locking point A2,

[0076] First, the body connector 8 is designed, specifically: in the step four locking point A2 position space, a machining angle box is designed between the card seat 4 of the hook type locking sleeve and the bottom structure 1 of the fuselage, taking the reference surface P1 of the card seat installation and the installation reference surface P52 of the bottom structure of the fuselage as the positioning reference, the machining angle box is designed into a wedge shape, as shown in Figure 6 7075 high-strength hard aluminum material can be selected, the fuselage installation surface of the machining angle box abuts against the bottom structure 1 of the fuselage, and is connected by riveting. The card seat 4 of the hook type locking sleeve abuts against the card seat installation surface of the machining angle box. There are four through holes on the angle box installation surface, which can be screwed with the angle box;

[0077] Then, the bottom fairing connector 9 is designed, specifically: in the step four locking point A2 position space, a machining angle box is designed between the button platform 7 of the hook type locking sleeve and the bottom fairing 2, taking the installation surface P42 of the bottom fairing as the positioning reference, the reference surface P2 of the button platform coincides with the installation surface P42. Taking the hook rotating axis L2 as the reference, the machining angle box is designed into a few character shape, as shown in Figure 7 7075 high-strength hard aluminum material can be selected, the installation surface of the machining angle box abuts against the installation surface of the bottom fairing locking point platform, and is connected by riveting, the button platform 7 of the hook type locking sleeve and the hook 6 are hung in the middle of the machining angle box through the pin;

[0078] Finally, the stop mode of the body connector 8 and the bottom fairing connector 9 is designed, specifically: as shown in Figure 1 The bottom fairing locking point 3 needs torque M, that is, the stop action of the hook type locking mechanism. The body connector 8 and the bottom fairing connector 9 are continuously optimized, as shown in Figure 8A boss 10 is added to the front end of the body connector 8, which is perpendicular to the reference plane P1 of the card seat installation and parallel to the installation plane P42. A top plate 11 is added above the bottom fairing connector 9, which is perpendicular to the installation plane P42 and parallel to the reference plane P1. After the two connectors are installed, the boss 10 and the top plate 11 intersect perpendicularly and abut each other under the locking state of the hook type locking mechanism.

[0079] For the locking point A4,

[0080] First, design the body connector 8, specifically: in the step four locking point A4 position space, between the card seat 4 of the hook type locking sleeve and the bottom structure 1 of the fuselage, design a machining angle box, take the reference plane P1 of the card seat installation and the installation reference plane P54 of the bottom structure of the fuselage as the positioning reference, design the machining angle box into a wedge shape, as shown in Figure 6 Optionally use 7075 high-strength hard aluminum material, the installation surface of the machining angle box is abutted with the bottom structure 1 of the fuselage, and is connected by riveting. The card seat 4 of the hook type locking sleeve is abutted on the card seat installation surface of the machining angle box. There are four through holes on the installation surface of the angle box, which can be screwed with the angle box;

[0081] Then, design the bottom fairing connector 9, specifically: in the step four locking point A4 position space, between the button platform 7 of the hook type locking sleeve and the bottom fairing 2, design a machining angle box, take the installation plane P44 of the bottom fairing as the positioning reference, and the reference plane P2 of the button platform coincides with the installation plane P44. Take the hook rotating axis L2 as the reference, design the machining angle box into a few character shape, as shown in Figure 7 Optionally use 7075 high-strength hard aluminum material, the installation surface of the machining angle box is abutted with the bottom fairing locking point platform installation surface, and is connected by riveting, the button platform 7 of the hook type locking sleeve and the hook 6 are hung in the middle of the machining angle box through the pin;

[0082] Finally, design the stop mode of the body connector 8 and the bottom fairing connector 9, specifically: as shown in Figure 1 The bottom fairing locking point 3 needs torque M, that is, the stop action of the hook type locking mechanism. Continue to optimize the design on the body connector 8 and the bottom fairing connector 9, refer to Figure 8 A boss 10 is added to the front end of the body connector 8, which is perpendicular to the reference plane P1 of the card seat installation and parallel to the installation plane P44. A top plate 11 is added above the bottom fairing connector 9, which is perpendicular to the installation plane P44 and parallel to the reference plane P1. After the two connectors are installed, the boss 10 and the top plate 11 intersect perpendicularly and abut each other under the locking state of the hook type locking mechanism.

[0083] For the locking point A6,

[0084] First, the body connector 8 is designed, specifically: in the step four lock point position A6 position space, between the hook type locking sleeve set of card seat 4 and the bottom structure 1 of the fuselage, a machining angle box is designed, taking the reference surface P1 of the card seat installation and the reference surface P56 of the bottom plate structure installation as the positioning reference, the machining angle box is designed into a wedge shape, as shown in Figure 6 . Optionally, 7075 high-strength hard aluminum material can be used, the body installation surface of the machining angle box is attached to the bottom structure 1 of the fuselage, and is connected by riveting. The card seat 4 of the hook type locking sleeve set is attached to the card seat installation surface of the machining angle box. There are four through holes on the installation surface of the angle box, which can be screwed with the angle box;

[0085] Then, the bottom fairing connector 9 is designed, specifically: in the step four lock point position A6 position space, between the button platform 7 of the hook type locking sleeve set and the bottom fairing 2, a machining angle box is designed, taking the installation surface P46 of the bottom fairing as the positioning reference, the reference surface P2 of the button platform coincides with the installation surface P46. Taking the hook rotating axis L2 as the reference, the machining angle box is designed into a few character shape, as shown in Figure 7 . Optionally, 7075 high-strength hard aluminum material can be used, the installation surface of the machining angle box is attached to the bottom fairing lock point platform installation surface, and is connected by riveting, the button platform 7 of the hook type locking sleeve set and the hook 6 are suspended in the middle of the machining angle box by a pin;

[0086] Finally, the stop mode of the body connector 8 and the bottom fairing connector 9 is designed, as shown in Figure 1 , the bottom fairing lock point position 3 needs torque M, that is, the stop action of the hook type locking mechanism. The body connector 8 and the bottom fairing connector 9 are continuously optimized, as shown in Figure 8 , a boss 10 is added at the front end of the body connector 8, the boss 10 is perpendicular to the reference surface P1 of the card seat installation, and is parallel to the installation surface P46. A top plate 11 is added above the bottom fairing connector 9, the top plate 11 is perpendicular to the installation surface P46, and is parallel to the reference surface P1. After the two connectors are installed, the boss 10 and the top plate 11 intersect perpendicularly and abut against each other in the locked state of the hook type locking mechanism.

[0087] Figure 9 The final form diagram of the design method of the locking mechanism provided by the present application is shown. According to the design method of the present application, a standard locking sleeve set is used, and a locking mechanism system of the bottom fairing is finally designed. The locking mechanism system is provided with six sets of hook type locking mechanisms L on the bottom fairing. Through the locking mechanism system, the bottom fairing can be locked under the bottom structure of the fuselage, and it is convenient to remove the bottom fairing from the fuselage structure, so that the maintenance and protection of the bottom of the fuselage by the ground crew is facilitated.

[0088] The locking mechanism single set device as shown in Figure 10 The body connecting member 8 and the bottom fairing connecting member 9 are made of high-strength aluminum alloy. The body connecting member 8 is arranged under the body bottom structure by riveting. The bottom fairing connecting member 9 is arranged on the lock seat mounting platform 100 of the bottom fairing by riveting. The lock of the hook-shaped locking sleeve in the hook-shaped locking sleeve is mounted on the bottom fairing connecting member by a pin. The lock seat of the square ring buckle 5 in the hook-shaped locking sleeve is bolted on the body connecting member 8. By adjusting the length of the square ring buckle, the boss 10 of the body connecting member 8 and the top plate 11 of the bottom fairing connecting member 9 are in close contact. When the hook-shaped locking sleeve is used, the hook 6 is hung on the square ring buckle 5, and by pressing the button platform 7, the hook-shaped locking sleeve with the hook is tightened by its own elasticity, pulling the square ring buckle 5, achieving locking, thereby achieving the locking of the bottom fairing at this lock point. By locking the 6 lock points, the entire fairing is locked on the body bottom structure.

[0089] The above only expresses the embodiments of the present application, which are described in detail and in detail, but cannot be understood as a limitation on the scope of the patent. It should be noted that for ordinary skilled in the art, without departing from the concept of the present application, a number of modifications and improvements can be made, which are within the scope of the present application. In addition, the non-exhaustive part of the present application is a conventional technology.

Claims

1. A method of designing a locking mechanism, characterized by, The application comprises the following steps: Step one, stress analysis of the locking point part based on the stress load of the bottom fairing fixed on the bottom structure of the fuselage and the working principle of the hook-type locking sleeve; Step two, position setting of the locking point part on the bottom fairing based on the stress analysis result; Step three, setting of the reference and boundary of the hook-type locking sleeve in the locked state and obtaining of the mounting interface of the hook-type locking sleeve in the locked state: firstly, setting of the reference of the hook-type locking sleeve in the locked state: numerical modeling of the hook-type locking sleeve in the locked state, introduction of the numerical model of the hook-type locking sleeve in the locked state in the assembly environment, setting of the key reference: when the hook of the hook-type locking sleeve is locked with the square ring buckle, the axis L0 of the rotation of the hook around the cylindrical shaft of the square ring buckle coincides with the center line L1 of the cylindrical shaft of the square ring buckle; the rotation axis of the hook is L2, the mounting of the clamping seat on the reference surface P1 of the machine body structure, the reference surface P2 of the button platform, the center line L3 of the button platform on the reference surface P2, and the center axis L4 of the tail shaft of the square ring buckle; then, boundary setting of the hook-type locking sleeve: based on the numerical model of the hook-type locking sleeve, the first rectangle S1 is constructed on the reference surface P2 with the center line L3 as the center, and the first rectangle S1 is the boundary of the button mounting surface of the hook-type locking sleeve; the second rectangle S2 with an area smaller than that of the first rectangle S1 is constructed on the reference surface P2 with the center line L3 as the center, and the second rectangle S2 is the button opening boundary of the hook-type locking sleeve, which is equidistant from the edge of the button platform, and the center point of the first rectangle S1 is set as O1 as the center point of the locking button reference surface; the above-mentioned reference and boundary belong to the same assembly body coordinate system and serve as the mounting interface of the hook-type locking sleeve; Step four, in the full-machine assembly environment, the mounting interface of the hook-type locking sleeve is placed in the position space of the locking point part based on the stress analysis result, and the locking point platform mounting surface is obtained to design the locking point mounting platform of the bottom fairing; Step five, design of the connecting piece of the hook-type locking sleeve and the stop mode of the connecting piece.

2. The method of claim 1, wherein, In step one, the stress state of the locking point part of the bottom fairing is determined based on the stress load of the bottom fairing fixed on the bottom structure of the fuselage and the working principle of the hook-type locking sleeve in the flight state, and the stress and position relationship of the locking point part and the connecting piece part in the locked state are preliminarily determined.

3. The method of 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 of claim 3, wherein, In step two, based on the stress analysis result, three locking point parts, A1, A3 and A5, are set on one side of the bottom fairing from front to back, and three locking point parts, A2, A4 and A6, are set on the other side, and the locking point parts on the two sides are symmetrical.

5. The method of claim 4, wherein, In step four, the process of designing the locking point mounting platform of the bottom fairing comprises: In the full machine assembly environment, in the position space of the locking point part A1, based on the stress analysis result of step one, the hook type locking sleeve installation interface is put in, the center line L3 of the button platform is perpendicular to the edge curve of the bottom fairing, the vertical projection through the center point O1 is obtained, the tangent plane P31 on the bottom fairing profile surface is obtained, the tangent plane P31 is offset to the inside of the fuselage, and the locking button installation surface P41 of the bottom fairing is obtained; Project the first rectangle S1 onto the installation surface P41, and obtain the first boundary S31 after rounding treatment, the area occupied by the first boundary S31 is the bottom fairing button platform area in the plane state; Project the first boundary S31 into the bottom fairing profile surface, and expand the offset to obtain the second boundary S41, connect the bottom fairing profile surface outside the second boundary S41 and the plane inside the first boundary S31, and finally obtain a composite curved surface, the periphery of the composite curved surface is smoothly transitioned, and the inside is a plane sunk in the bottom fairing profile, which is a locking point platform installation surface; Project the second rectangle S2 onto the locking point platform installation surface to obtain the button opening boundary S51; The acquisition process of the locking point platform installation surface of the locking point parts A3, A5, A2, A4 and A6 is the same as that of the locking point platform installation surface of the locking point part A1.

6. The method of claim 5, wherein, The connecting piece of the hook type locking sleeve includes a machine body connecting piece and a bottom fairing connecting piece. For the locking point part A1, in step five, the process of designing the connecting piece of the hook type locking sleeve includes: Firstly, the machine body connecting piece is designed: in the position space of the locking point part A1 in step four, a machine angle box is designed between the clamping seat of the hook type locking sleeve and the bottom structure of the fuselage, the machine angle box is designed in a wedge shape with the clamping seat installation reference surface P1 and the bottom structure installation reference surface P51 as the positioning reference, the machine angle box fuselage installation surface is in close contact with the bottom structure of the fuselage and is connected by riveting; the clamping seat of the hook type locking sleeve is in close contact with the clamping seat installation surface of the machine angle box; Then, the bottom fairing connecting piece is designed: in the position space of the locking point part A1 in step four, a machine angle box is designed between the locking sleeve button platform and the bottom fairing, the locking button installation surface P41 of the bottom fairing is used as the positioning reference, and the reference surface P2 of the button platform is coincident with the locking button installation surface P41; the machine angle box is designed in a U shape with the hook rotating axis L2 as the reference, the machine angle box installation surface is in close contact with 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 machine angle box through a pin; Finally, the stop mode of the machine body connecting piece and the bottom fairing connecting piece is designed: a boss is added at the front end of the machine body connecting piece, the boss is perpendicular to the clamping seat installation reference surface P1 and parallel to the installation surface P41; a top plate is added above the bottom fairing connecting piece, the top plate is perpendicular to the installation surface P41 and parallel to the reference surface P1; after the installation of the two connecting pieces, the boss and the top plate are perpendicular to each other and in close contact with each other under the locking state of the hook type locking mechanism. The design process of the connecting member of the hook type locking sleeve of the locking point sites A3, A5, A2, A4 and A6 is the same as that of the locking point site A1.

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