An out-of-hanger installation apparatus and method for a helicopter sliding cabin door

Abstract

The application provides a kind of outside mounting device and method of helicopter sliding cabin door, the device simulates the three-point support state of the front landing gear and main landing gear of the helicopter to the fuselage by simulating landing gear support module, door frame and cabin door sliding rail joint positioning module are used for positioning and installing door frame and cabin door sliding rail joint in sliding cabin door assembly, door frame and cabin door sliding rail joint positioning module are divided into left and right two groups, each group can slide and fix in Y direction, for adapting the deformation state of fuselage affected by counterweight;The application optimizes the positioning and support structure of fuselage, to restore the three-point support state and deformation state of fuselage more truly;Increase the adjusting function of door frame sliding rail positioning assembly along Y direction as a whole, to adapt to the deformation of fuselage and facilitate the product on and off the shelf;The assembly of door frame sliding rail assembly combines transmission platform counterweight module, to improve the deformation problem of sliding cabin door existing in the original assembly scheme.

Description

Technical Field

[0001] This invention belongs to the field of helicopter process equipment design technology, and particularly relates to an external mounting device and method for a helicopter sliding door. Background Technology

[0002] The helicopter sliding door assembly is located on the left and right sides of the front fuselage. The original positioning and assembly of the door frame and slide rail components were housed within the fuselage assembly jig. This assembly method failed to consider the structural deformation of the fuselage after the main reduction gear and other large components were subsequently installed on the fuselage transmission platform. This deformation directly led to deformation of the door frame and slide rail components within the sliding door assembly, thus affecting the normal operation of the sliding door. Furthermore, because the sliding door assembly involves the assembly of numerous components, and the available operating space on the fuselage assembly jig is limited, the positioning and assembly of the door frame and slide rail components is inconvenient.

[0003] Therefore, an external mounting device and method are needed to solve the assembly coordination problem of helicopter sliding doors. This would separate the positioning and assembly of the door frame and slide rail components from the final assembly jig, set up separate assembly fixtures, and combine them with the counterweight module on the transmission platform to optimize and improve the positioning and assembly scheme of the sliding door frame and slide rail components, thereby solving the assembly coordination problem of the sliding door. Summary of the Invention

[0004] The technical problem to be solved by this invention is the coordination problem of helicopter sliding door assembly. This invention proposes an external mounting device and method for helicopter sliding doors to replace the original assembly method of setting positioning structures on the general assembly frame. The sliding door components are assembled by simulating the actual deformation state of the fuselage.

[0005] The technical solution of this invention is: In a first aspect, an external mounting device for a helicopter sliding door is provided, comprising: a simulated landing gear support module 1 and a door frame and door rail joint positioning module 2. The simulated landing gear support module 1 simulates the three-point support state of the helicopter's nose landing gear and main landing gear on the fuselage. The door frame and door rail joint positioning module 2 is used for positioning and installing the door frame and door rail joint in the sliding door assembly. The door frame and door rail joint positioning module 2 is divided into two groups, left and right, each group being able to slide and be fixed in the Y direction to adapt to the state of the fuselage deformed by the counterweight.

[0006] Optionally, the simulated landing gear support module 1 includes a main frame 11, an adjustable support 12, a front landing gear positioning support structure 13, a main landing gear positioning support structure 14, and an elevation 15. The main frame 11 consists of a central main frame, front columns, and rear two-sided support frames and columns, all connected together by bolts; elevation 15 is set above the central main frame. The height of the adjustable support 12 is adjustable and it is distributed below the main frame 11 to support and level the device; The front start positioning support structure 13 includes a bottom support 131, a top positioning block 132, a pin 133, and a plate 134. The bottom support 131 and the top positioning block 132 are fitted together by square shaft holes, allowing for quick docking. The bottom support 131 is connected to the main frame 11 by screws, and the top positioning block 132 is connected to the front start connector of the fuselage by the pin 133 and the plate 134. There are two main landing gear positioning support structures 14, distributed on the left and right sides of the main frame 11. The main landing gear positioning support structure 14 includes a bottom support 141, a middle slider 142, and a top positioning shaft 143. The bottom support 141 is connected to the main frame 11 by screws. The bottom support 141 has a waist-shaped hole in the middle, and the middle slider 142 can slide back and forth on the bottom support 141. The middle slider 142 can quickly connect with the fuselage main landing gear connector through the shaft hole. The top positioning shaft 143 is used to simulate part of the landing gear and cooperates with the shaft hole of the middle slider 142.

[0007] Optionally, the door frame and hatch slide rail joint positioning module 2 includes a bottom frame 21, a side frame 22, a screw mechanism 23, a slide rail mechanism 24, a side frame theoretical position positioning structure 25, an adjustable support 26, and a door frame and hatch slide rail joint positioning structure 27. The bottom frame 21 is connected to the main frame 11 by screws and pins, and is supported and leveled to the ground by adjustable supports 26. A slide rail mechanism 24 is provided on the bottom frame 21, and the side frame 22 is connected to the bottom frame 21 by the slide rail mechanism 24. The side frame 22 can slide left and right along the slide rail mechanism 24. One end of the screw mechanism 23 is fixed to the bottom frame 21, and the other end is connected to the side frame 22. It is used to realize the left and right sliding and position locking of the side frame 22. The door frame and hatch slide rail joint positioning structure 27 is divided into multiple sets of different positioning and clamping structures, which are set on the inside of the side frame 22 for clamping the door frame and hatch slide rail joint. The side frame theoretical position positioning structure 25 is located between the bottom frame 21 and the side frame 22, and is divided into front and rear sets. It positions and fixes the side frame 22 and is used for the installation and verification of the door frame and hatch slide rail joint positioning module 2.

[0008] Optionally, the side frame theoretical position positioning structure 25 includes a lower support 251, an upper support 252, a pin 253, and an indicator plate 254. The lower support 251 is mounted on the bottom frame 21, and the upper support 252 is mounted on the side frame 22. The lower support 251 and the upper support 252 are connected by a pin 253. The indicator plate 254 is mounted on the upper support 252, and its lower tip points to the engraving line on the lower support 251.

[0009] Furthermore, the device also includes: a fuselage mounting and dismounting auxiliary module 3. The upper and lower frame auxiliary module 3 includes: tray 1 31, tray 2 32, tray 3 33, tray 4 34, screw mechanism 1 35, and screw mechanism 2 36. Pallets 1 (31), 2 (32), 3 (33), and 4 (34) are each connected to the main frame 11 via two screw mechanisms (35). Screw mechanism 1 (35) is used to adjust the pallets up and down. Screw mechanism 2 (36) is located below the pallets and is used to adjust the pallets left and right. Screw mechanism 1 (35) and screw mechanism 2 (36) are used together to facilitate the adjustment of the machine body posture. During product riveting and assembly, the upper and lower frame auxiliary module 3 is completely separated from the machine body and does not provide support.

[0010] Furthermore, the device also includes: a transmission platform counterweight module 4, used to simulate the weight and center of gravity of a large mass component on the helicopter transmission platform. The fuselage structure is deformed by the force applied by the transmission platform counterweight module 4, thereby restoring the fuselage deformation in the overall state of the helicopter.

[0011] Optionally, the heavy components include the main reducer, engine, and propeller.

[0012] In a second aspect, a method for external mounting of a helicopter sliding door is provided, for use with any of the external mounting devices for helicopter sliding doors described in the first aspect, the method comprising: Slide the door frame and hatch slide rail joint positioning module 2 to the left and right sides to make room in the middle. Connect the fuselage to the simulated landing gear support module 1, and clamp the door frame and cabin door slide rail joint onto the door frame and cabin door slide rail joint positioning module 2; Slide the door frame and door slide rail joint positioning module 2 toward the middle until the door frame and door slide rail joint on it are fixed against the side of the fuselage. At this time, perform the corresponding riveting operation.

[0013] Optionally, when docking the fuselage with the simulated landing gear support module 1, the fuselage attitude is adjusted using the fuselage upper and lower frame auxiliary module 3 to facilitate docking. After the fuselage is docked with this device, the fuselage upper and lower frame auxiliary module 3 is separated from the fuselage and does not interfere with the deformation of the fuselage.

[0014] Furthermore, after clamping the door frame and door slide rail joint onto the door frame and door slide rail joint positioning module 2, the transmission platform counterweight module 4 is installed at the corresponding position on the fuselage; After the riveting operation is completed, slide the door frame and door slide rail joint positioning module 2 to the left and right sides to avoid the fuselage, remove the transmission platform counterweight module 4 on the fuselage, and then use the fuselage mounting and dismounting auxiliary module 3 to assist in the dismounting of the fuselage.

[0015] The beneficial effects of this application are as follows: This invention provides an external mounting device and method for solving the assembly coordination problem of helicopter sliding doors. It optimizes the fuselage's positioning support structure to more realistically reproduce the fuselage's three-point support and deformation states; it adds an overall Y-axis adjustment function to the door frame slide rail positioning assembly to adapt to fuselage deformation and facilitate product loading and unloading; the assembly of the door frame slide rail assembly incorporates a transmission platform counterweight module, improving the sliding door deformation problem present in the original assembly scheme; thus effectively solving the sliding door assembly coordination problem. Attached Figure Description

[0016] Figure 1 A schematic diagram of the external mounting device for solving the assembly coordination problem of helicopter sliding door; Figure 2 A schematic diagram simulating a landing gear support module; Figure 3 This is a schematic diagram of the front positioning support structure; Figure 4 A schematic diagram of the main positioning support structure; Figure 5 A schematic diagram of the positioning module for the door frame and hatch slide rail joint; Figure 6 A schematic diagram of the theoretical location of the side frame structure; Figure 7 This is a schematic diagram of the auxiliary modules mounted on the fuselage. Figure 8 This is a side view of an example of the use of the present invention; Figure 9 This is a top view of an example of the use of the present invention.

[0017] The components are: 1-Simulated landing gear support module, 2-Door frame and cabin door slide rail joint positioning module, 3-Fuselage upper and lower frame auxiliary module, 11-Main frame, 12-Adjustable support, 13-Trail landing gear positioning support structure, 14-Main landing gear positioning support structure, 15-Elevation, 131-Bottom support, 132-Top positioning block, 133-Pin, 134-Insert, 141-Bottom support, 142-Center slider, 143-Top positioning shaft. 21-Bottom frame, 22-Side frame, 23-Screw mechanism, 24-Slide rail mechanism, 25-Theoretical position positioning structure of side frame, 26-Adjustable support, 27-Positioning structure of door frame and hatch slide rail joint, 251-Lower support, 252-Upper support, 253-Pin, 254-Indicator plate, 31-Pattern 1, 32-Pattern 2, 33-Pattern 3, 34-Pattern 4, 35-Screw mechanism 1, 36-Screw mechanism 2. Detailed Implementation

[0018] To make the objectives, technical solutions, and advantages of the embodiments of the present invention clearer, the technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0019] The features and illustrative embodiments of various aspects of the present invention will now be described in detail. Numerous specific details are set forth in the following detailed description to provide a thorough understanding of the invention. However, it will be apparent to those skilled in the art that the invention may be practiced without requiring some of these specific details. The following description of embodiments is merely intended to provide a better understanding of the invention by illustrating examples of the invention. The invention is by no means limited to any specific setups and methods set forth below, but covers any improvements, substitutions, and modifications to structures, methods, and devices without departing from the spirit of the invention. Well-known structures and techniques are not shown in the drawings and the following description to avoid unnecessarily obscuring the invention.

[0020] It should be noted that, unless otherwise specified, the embodiments of the present invention and the features thereof can be combined with each other, and the various embodiments can be referenced and cited from each other.

[0021] The present invention will now be described in detail with reference to the accompanying drawings and specific embodiments.

[0022] This invention provides an external mounting device and method for solving the assembly coordination problem of helicopter sliding door, such as... Figure 1 As shown, the device mainly includes a simulated landing gear support module 1, a door frame and cabin door slide rail joint positioning module 2, and a fuselage overmount and undermount auxiliary module 3.

[0023] The simulated landing gear support module 1 is used to simulate the three-point support state of the helicopter's nose landing gear and main landing gear on the fuselage.

[0024] See Figure 2 The main structure of the simulated landing gear support module 1 includes a main frame 11, an adjustable support 12, a front landing gear positioning support structure 13, a main landing gear positioning support structure 14, and an elevation 15.

[0025] The main frame 11 consists of a central main frame, front columns, and rear two side support frames and columns, which are connected to each other as a whole by screws and pins.

[0026] The adjustable support 12 is height-adjustable and is located below the main frame 11 to support and level the device.

[0027] See Figure 3 The front starting positioning support structure 13 is divided into a bottom support 131, a top positioning block 132, a pin 133, and a plate 134. The bottom support 131 and the top positioning block 132 are fitted by square shaft holes, which can be quickly connected. The bottom support 131 is connected to the main frame 11 by screws, and the top positioning block 132 is connected to the front starting connector of the fuselage by pins 133 and plates 134.

[0028] See Figure 4 The main landing gear positioning support structure 14 consists of a bottom support 141, a middle slider 142, and a top positioning shaft 143. The bottom support 141 is connected to the main frame 11 by screws. The bottom support 141 has a waist-shaped hole in the middle, allowing the middle slider 142 to slide back and forth on the bottom support 141. The middle slider 142 can quickly connect with the fuselage main landing gear connector through a shaft hole. The top positioning shaft 143 simulates part of the landing gear and engages with the shaft hole of the middle slider 142. There are two main landing gear positioning support structures 14, distributed on the left and right sides of the main frame 11.

[0029] Elevation 15 is set above the main frame in the middle, and three can be set symmetrically on the left and right sides respectively.

[0030] The door frame and door slide rail joint positioning module 2 is used for positioning and installing the door frame and door slide rail joint in the sliding door assembly. This module is divided into left and right groups, each group can slide and be fixed in the Y direction, which is used to adapt to the deformation of the fuselage due to the influence of counterweight, and to avoid interference between the deformed fuselage structure and the positioning device.

[0031] See Figure 5 The main structure of the door frame and hatch slide rail joint positioning module 2 includes a base frame 21, a side frame 22, a screw mechanism 23, a slide rail mechanism 24, a side frame theoretical position positioning structure 25, an adjustable support 26, and a door frame and hatch slide rail joint positioning structure 27. The base frame 21 is directly connected to the main frame 11 by screws and pins, and is supported and leveled to the ground by the adjustable support 26. The slide rail mechanism 24 is installed on the base frame 21, and the side frame 22 is connected to the base frame 21 by the slide rail mechanism 24. The side frame 22 can slide left and right along the slide rail mechanism 24. One end of the screw mechanism 23 is fixed to the base frame 21, and the other end is connected to the side frame 22, which is used to realize the left and right sliding and position locking of the side frame 22. The door frame and hatch slide rail joint positioning structure 27 is divided into multiple sets of different positioning and clamping structures, which are set on the inside of the side frame 22 for clamping the door frame and hatch slide rail joint. The side frame theoretical position positioning structure 25 is located between the bottom frame 21 and the side frame 22, and is divided into front and rear groups. It can position and fix the side frame 22 and is used for the installation and verification of the door frame and hatch slide rail joint positioning module 2.

[0032] See Figure 6The main structure of the side frame theoretical position positioning structure 25 includes a lower support 251, an upper support 252, a pin 253, and an indicator plate 254. The lower support 251 is installed on the bottom frame 21, and the upper support 252 is installed on the side frame 22. The lower support 251 and the upper support 252 are connected by the pin 253. The indicator plate 254 is installed on the upper support 252, and its lower tip points to the engraved line on the lower support 251 to visually reflect the impact of fuselage deformation.

[0033] The fuselage mounting and dismounting auxiliary module 3 is used to assist in mounting and dismounting the fuselage. See [link / reference]. Figure 7 The main structure includes pallet 1 (31), pallet 2 (32), pallet 3 (33), pallet 4 (34), screw mechanism 1 (35), and screw mechanism 2 (36). Pallets 1 (31), 2 (32), 3 (33), and 4 (34) are each connected to the main frame 11 via two screw mechanisms 1 (35). Screw mechanism 1 (35) is used for vertical adjustment of the pallets. Screw mechanism 2 (36) is located below the pallets and is used for horizontal adjustment of the pallets. Screw mechanisms 1 (35) and 2 (36) are used together to facilitate machine body posture adjustment. During product riveting and assembly, the upper and lower frame auxiliary module 3 is completely separated from the machine body and does not provide support.

[0034] See Figure 8 and Figure 9 The device also includes a transmission platform counterweight module 4, which is used to simulate the weight and center of gravity of large components such as the main reducer, engine, and rotor blades on the helicopter transmission platform. The fuselage structure is deformed by the force applied by the transmission platform counterweight module 4, thereby approximately restoring the fuselage deformation under the whole state of the helicopter.

[0035] like Figure 5 and Figure 6 As shown. When using this device, first slide the door frame and door rail joint positioning module 2 to the left and right sides to create space in the middle. Then, assemble the fuselage with the simulated landing gear support module 1, and clamp the door frame and door rail joint onto the door frame and door rail joint positioning module 2. When assembling the fuselage with the simulated landing gear support module 1, use the fuselage mounting and dismounting auxiliary module 3 to adjust the fuselage attitude for easy assembly. After the fuselage is assembled with this device, the fuselage mounting and dismounting auxiliary module 3 separates from the fuselage and does not interfere with the fuselage's deformation. Next, install the transmission platform counterweight module 4 at the corresponding position on the fuselage. Then, slide the door frame and door rail joint positioning module 2 towards the middle until the door frame and door rail joint on it are against the side of the fuselage and fixed in place. At this point, the corresponding riveting operation can be performed. After the riveting operation is completed, slide the door frame and door rail joint positioning module 2 to the left and right sides to avoid the fuselage, remove the transmission platform counterweight module 4 from the fuselage, and then use the fuselage mounting and dismounting auxiliary module 3 to assist in the lowering of the fuselage.

[0036] When using the simulated landing gear support module 1, the front landing gear positioning support structure 13 is connected to the fuselage front landing gear connector through the top positioning block 132, pin 133 and insert 134, and the main landing gear positioning support structure 14 is connected to the fuselage main landing gear connector through the middle slider 142 and the shaft hole of the top positioning shaft 143, so as to realize the positioning and fixation of the fuselage and this device.

[0037] When using the door frame and hatch slide rail joint positioning module 2, first operate the screw mechanism 23 to move the side frame 22 outward, and use the door frame and hatch slide rail joint positioning structure 27 on it to clamp the door frame and hatch slide rail joint. After the fuselage is positioned and fixed, operate the screw mechanism 23 again to move the side frame 22 inward until the door frame and hatch slide rail joint is close to the fuselage.

[0038] For the fuselage mounting and unmounting auxiliary module 3, when in use, the first screw mechanism 35 is operated to adjust the tray up and down, and the second screw mechanism 36 is operated to adjust the tray left and right. This module is only used for the fuselage mounting and unmounting. When riveting the door frame and cabin door slide rail joints to the fuselage, it completely avoids the fuselage.

[0039] The above description merely illustrates embodiments of the present invention and is quite specific and detailed; however, it should not be construed as limiting the scope of the patent. It should be noted that those skilled in the art can make various modifications and improvements without departing from the concept of the present invention, and these all fall within the scope of protection of the present invention. Furthermore, any parts of the present invention not described in detail are conventional techniques.

Claims

1. An external mounting device for a helicopter sliding door, characterized in that, include: The simulated landing gear support module, door frame and door slide rail joint positioning module are used to position and install the door frame and door slide rail joint in the sliding door assembly. The simulated landing gear support module simulates the three-point support state of the helicopter's nose landing gear and main landing gear on the fuselage. The door frame and door slide rail joint positioning module is divided into left and right groups. Each group can slide and be fixed in the Y direction to adapt to the state of the fuselage deformed by the counterweight. The simulated landing gear support module includes a main frame, adjustable supports, a front landing gear positioning support structure, a main landing gear positioning support structure, and an elevation. The main frame consists of a central main frame, front columns, and rear side support frames and columns, all connected together by bolts; the elevation is set above the central main frame. The height of the adjustable supports is adjustable, and they are distributed below the main frame to support and level the device. The front start positioning support structure includes a bottom support, a top positioning block, a pin, and a plate; the bottom support and the top positioning block are fitted together by square shaft holes for quick connection; the bottom support is connected to the main frame by screws, and the top positioning block is connected to the front start connector of the fuselage by pins and plates. There are two main landing gear positioning support structures, distributed on the left and right sides of the main frame. The main landing gear positioning support structure includes a bottom support, a middle slider, and a top positioning shaft. The bottom support is connected to the main frame by screws. The bottom support has an oblong hole in the middle, and the middle slider can slide back and forth on the bottom support. The middle slider and the fuselage main landing gear connector can be quickly connected through the shaft hole. The top positioning shaft is used to simulate part of the landing gear and cooperates with the shaft hole of the middle slider.

2. The apparatus as claimed in claim 1, characterized in that, The door frame and hatch slide rail joint positioning module includes a bottom frame, side frame, screw mechanism, slide rail mechanism, side frame theoretical position positioning structure, adjustable support, and door frame and hatch slide rail joint positioning structure; The bottom frame is connected to the main frame by bolts and is supported and leveled to the ground by adjustable supports. A slide rail mechanism is installed on the bottom frame, and the side frame is connected to the bottom frame by the slide rail mechanism, allowing the side frame to slide left and right along the slide rail mechanism. One end of the screw mechanism is fixed to the bottom frame, and the other end is connected to the side frame, used to realize the left and right sliding and position locking of the side frame. The positioning structure of the door frame and hatch slide rail joint consists of multiple sets of different positioning and clamping structures, which are set on the inside of the side frame for clamping the door frame and hatch slide rail joint. The side frame theoretical position positioning structure is located between the bottom frame and the side frame, divided into front and rear sets, for positioning and fixing the side frame, and is used for the installation and verification of the door frame and hatch slide rail joint positioning module.

3. The apparatus as described in claim 2, characterized in that, The side frame theoretical positioning structure includes a lower support, an upper support, a pin, and an indicator plate; The lower support is mounted on the bottom frame, and the upper support is mounted on the side frame. The lower support and the upper support are connected by a pin. The indicator plate is mounted on the upper support, and its pointed end points to the engraving line on the lower support.

4. The apparatus as claimed in claim 1, characterized in that, The device also includes: an auxiliary module for mounting and dismounting the fuselage. The machine body mounting auxiliary module includes: tray one, tray two, tray three, tray four, screw mechanism one, and screw mechanism two. Pallets 1, 2, 3, and 4 are each connected to the main frame via two screw mechanisms. Screw mechanism 1 is used to adjust the pallets up and down. Screw mechanism 2 is located below the pallets and is used to adjust the pallets left and right. Screw mechanism 1 and screw mechanism 2 are used together to facilitate the adjustment of the machine body posture. During product riveting and assembly, the upper and lower frame auxiliary modules are completely separated from the machine body and do not provide support.

5. The apparatus as described in claim 4, characterized in that, The device also includes a transmission platform counterweight module, which is used to simulate the weight and center of gravity of large mass components on the helicopter transmission platform. The fuselage structure is deformed by the force applied by the transmission platform counterweight module, thereby restoring the fuselage deformation in the overall state of the helicopter.

6. The apparatus as claimed in claim 5, characterized in that, The major components include the main reducer, engine, and propeller.

7. A method for external mounting of a helicopter sliding door, characterized in that, External mounting device for a helicopter sliding door according to any one of claims 1 to 6, the method comprising: Slide the door frame and hatch slide rail joint positioning module to the left and right sides to make room in the middle. Connect the fuselage to the simulated landing gear support module, and clamp the door frame and cabin door slide rail joint onto the door frame and cabin door slide rail joint positioning module; Slide the door frame and door slide rail joint positioning module toward the middle until the door frame and door slide rail joint on it are fixed against the side of the fuselage. At this point, perform the corresponding riveting operation.

8. The method as described in claim 7, characterized in that, When docking the fuselage with the simulated landing gear support module, the fuselage attitude is adjusted using the fuselage upper and lower frame auxiliary module to facilitate docking. After the fuselage is docked with this device, the fuselage upper and lower frame auxiliary module is separated from the fuselage and does not interfere with the deformation of the fuselage.

9. The method as described in claim 8, characterized in that, After clamping the door frame and door slide rail joint onto the door frame and door slide rail joint positioning module, install the transmission platform counterweight module at the corresponding position on the fuselage. After the riveting operation is completed, slide the door frame and door slide rail joint positioning module to the left and right sides to avoid the fuselage, remove the transmission platform counterweight module on the fuselage, and then use the fuselage mounting and dismounting auxiliary module to assist in the dismounting of the fuselage.

Images