Device and method for transporting, packaging and fixing aircraft fairing component

Abstract

The invention belongs to the technical field of aircraft body structure large component manufacturing, and particularly relates to an aircraft fairing component transporting, packaging and fixing device and method. A process covering cap with a mooring point is used for replacing a metal maintenance covering cap installed on a fairing structure to serve as a Z-direction main fixing point for mooring, the number of the mooring points of the fairing structure can be effectively increased, pre-tightening force in the X direction, the Y direction and the Z direction is increased, meanwhile, the tensile deformation amount of a tightening belt is reduced in advance, and the fairing structure is more stable. Movement of the fairing structure in the transportation process is reduced, and the situation that the whole packaging box bearing position possibly slides and a binding belt gets loose in the continuous vibration process, and consequently local instability is caused is avoided.

Description

Technical Field

[0001] This invention belongs to the field of aircraft airframe structural component manufacturing technology, specifically an aircraft fairing component transport packaging and fixing device and method. Background Technology

[0002] The aircraft fairing is a C-shaped semi-enclosed structure formed by riveting and threading together a machined frame, composite material panels, and metal maintenance access covers. This component employs a modular design, with the machined frame serving as the load-bearing structure, the composite material panels achieving aerodynamic requirements through mechanical connections, and the metal maintenance access covers for quick closure of equipment maintenance access. Its maximum dimensions exceed 3 meters, making it a typical large-size, thin-walled, complex structure with relatively poor overall rigidity and presenting the following technical challenges: 1. Vibration and shock risks In general road transport, under fixed conditions, the percentage of actual load to rated load has the greatest impact on the impact force on a specific vehicle. Road transport should be carried out at full load as much as possible to minimize impact force under the maximum permissible load, which is generally 1-2g. When the overall structure reaches the maximum overload, the current method of securing it with straps cannot completely fix it, causing the product to detach from the main body of the packaging box at a small distance, resulting in continuous impact. Riveted structures are prone to plastic deformation and structural damage under continuous impact.

[0003] 2. Challenges in Deformation Control The component's dimensions, with a single side length exceeding 3 meters, make it susceptible to bending moment deformation and local instability during transportation. The C-shaped semi-enclosed structure generates bending stress under lateral loads, requiring an internal support frame to raise the product's natural frequency to more than twice the transportation vibration frequency to prevent resonance and structural damage caused by transportation vibrations. Furthermore, the packaging box's support points may experience overall slippage and loosening of straps during continuous vibration, leading to localized instability. Summary of the Invention

[0004] The purpose of this invention is to address the problems and practical needs of the prior art by providing a transportation packaging and fixing device and method for aircraft fairing components. This method can effectively prevent plastic deformation and structural damage to the fairing riveted structure during transportation due to factors related to the fixing method, under continuous impact during vibration. It can meet the requirements for packaging fixing and transportation deformation control of similar weakly rigid fairing structures.

[0005] The technical solution for achieving the objective of this invention is as follows: According to a first aspect of this invention, a transport packaging and securing device for aircraft fairing components is provided for packaging and securing aircraft fairing components. The aircraft fairing component has an overall downward-clipping C-shaped semi-enclosed structure, including a machined frame beam skeleton, a composite material panel covering the machined frame beam skeleton, and a maintenance cover installed on the composite material panel; the transport packaging and securing device includes: The system comprises a bottom frame, a central support assembly, a first support clamping assembly, a second support clamping assembly, and a third support clamping assembly. The central support assembly is located at the center of the bottom frame and is used to support the central top machined frame beam of the aircraft fairing component. The first support clamping assembly is located in front of the central support assembly and is used for bottom support and top clamping of the front machined frame beam of the aircraft fairing component. The second and third support clamping assemblies are symmetrically arranged on the left and right sides of the central support assembly and are used for bottom support and top clamping of the machined frame beams on both sides of the aircraft fairing component.

[0006] In one possible embodiment, the transport packaging securing device further includes a process port cover, a cross-shaped lug fixed to the surface of the process port cover near the bottom frame, and a binding strap; the process port cover replaces the maintenance port cover located on top of the aircraft fairing component, one end of the binding strap is connected to the cross-shaped lug, and the other end is fixedly connected to the lug on the bottom frame for pulling and securing the top of the aircraft fairing component.

[0007] In one possible embodiment, the central support assembly includes a central support bracket and a central slide plate; the bottom end of the central support bracket is fixedly connected to the bottom frame, the central slide plate is fixed to the top end of the central support bracket, and the central slide plate has a central slot that is consistent with the distribution direction of the top machined frame beam skeleton of the aircraft fairing component, which is used to support the product while restricting the longitudinal and lateral movement of the product.

[0008] In one possible embodiment, the first support and clamping assembly includes a first support unit and a first clamping unit. The bottom end of the first support unit is fixedly connected to the bottom frame, and the bottom end of the first clamping unit is slidably connected to the bottom frame. The top of the first support unit provides internal fixed support to the front end of the aircraft fairing component, and the top of the first clamping unit engages with the first support unit at the same position to externally clamp the front end of the aircraft fairing component. The first support unit includes a first support bracket and a first support slide. The bottom end of the first support bracket is fixedly connected to the bottom frame, and the first support slide is fixedly connected to the bottom frame. The first support bracket is fixed at the top of the first support plate. The first support plate has a first slot that is consistent with the distribution direction of the machined frame beam corresponding to the aircraft fairing component. The first clamping unit includes a first clamping bracket and a first clamping pressure plate. The bottom end of the first clamping bracket is slidably connected to the bottom frame to realize sliding opening and closing relative to the first support unit, and is positioned and locked by a first positioning pin and an auxiliary bolt. The first clamping pressure plate is fixed at the top of the first clamping bracket. The side of the first clamping pressure plate that contacts the front end of the aircraft fairing component has a pressure surface that conforms to the shape of the front end of the aircraft fairing component.

[0009] In one possible embodiment, the second support and clamping assembly includes multiple sets of second support units and second clamping units of different heights. The bottom end of the second support unit is fixedly connected to the bottom frame, and the bottom end of the second clamping unit is slidably connected to the bottom frame. The tops of the multiple sets of second support units internally support one side of the aircraft fairing component, and the tops of the multiple sets of second clamping units cooperate with the second support unit at the same position to externally press and clamp the aircraft fairing component. The second support unit includes a second support bracket and a second support slide. The bottom end of the second support bracket is connected to... The bottom frame is fixedly connected, and the second supporting slide is fixed to the top of the second supporting bracket. The second supporting slide has a second slot that is consistent with the distribution direction of the machined frame beam skeleton at the corresponding position of the aircraft fairing component. The second clamping unit includes a second clamping bracket and a second clamping pressure plate. The bottom end of the second clamping bracket is slidably connected to the bottom frame to achieve sliding relative to the second supporting unit and to achieve positioning and locking by a second positioning pin. The second clamping pressure plate is fixed to the top of the second clamping bracket, and the side of the second clamping pressure plate that contacts the aircraft fairing component has a pressure surface that conforms to the shape of the corresponding position.

[0010] In one possible embodiment, the third support and clamping assembly includes multiple sets of third support units and third clamping units of different heights. The bottom end of the third support unit is fixedly connected to the bottom frame, and the bottom end of the third clamping unit is slidably connected to the bottom frame. The tops of the multiple sets of third support units provide internal fixed support to one side of the aircraft fairing component, and the tops of the multiple sets of third clamping units cooperate with the third support unit at the same position to externally press and clamp the aircraft fairing component. The third support unit includes a third support bracket and a third support slide. The bottom end of the third support bracket is fixed to the bottom frame. The connection is as follows: the third supporting slide is fixed to the top of the third supporting bracket; the third supporting slide has a third slot that is consistent with the distribution direction of the machined frame beam skeleton at the corresponding position of the aircraft fairing component; the third clamping unit includes a third clamping bracket and a third clamping pressure plate; the bottom end of the third clamping bracket is slidably connected to the bottom frame to achieve sliding relative to the third supporting unit, and is positioned and locked by a third positioning pin; the third clamping pressure plate is fixed to the top of the third clamping bracket, and the side of the third clamping pressure plate that contacts the aircraft fairing component has a pressure surface that conforms to the shape of the corresponding position.

[0011] In one possible embodiment, the contact surfaces of the central support assembly, the first support clamping assembly, the second support clamping assembly, the third support clamping assembly, and the aircraft fairing component are isolated and damped using EVA material with flexible and impact-resistant properties. Vibration energy is absorbed through the elastic deformation of the soft material, forming a unified whole between the packaging box and the fairing product.

[0012] In one possible embodiment, the transport packaging securing device further includes an upper frame structure disposed above the aircraft fairing component for overall protection of the outer surface of the aircraft fairing component, and its bottom end is connected to the bottom frame.

[0013] According to a second aspect of the present invention, a method for securing aircraft fairing components in transport packaging is provided, employing the aforementioned aircraft fairing component transport packaging securing device, comprising the following steps: The aircraft fairing components are hoisted onto the bottom frame and aligned with the corresponding positions of the center support assembly, the first support clamping assembly, the second support clamping assembly, and the third support clamping assembly. The aircraft fairing components are placed and snapped onto the central support assembly; The first support clamping assembly, the second support clamping assembly, and the third support clamping assembly are used to clamp and press the aircraft fairing components.

[0014] In one possible embodiment, by performing stress analysis on the aircraft fairing components, at least three maintenance access covers are selected on the front two sides and the middle of the aircraft fairing components to be replaced with process access covers. The cross lugs are pulled to the bottom frame and fixed in four mutually orthogonal directions using the binding straps, serving as the main fixing points in the Z direction for tethering.

[0015] Compared with the prior art, the significant advantages of this invention are: This invention uses a process port cover with its own tethering point instead of the metal maintenance port cover installed on the fairing structure as the main fixing point in the Z direction for tethering. This can effectively increase the number of tethering points on the fairing structure itself. By using distributed binding and universal fasteners to tighten, the pre-tightening force in the X, Y, and Z directions is increased, while the tensile deformation of the fastening straps is reduced in advance. This reduces the movement of the fairing structure during transportation and avoids the possibility of overall slippage and loosening of the binding straps during continuous vibration of the packaging box support position, which could lead to local instability. Attached Figure Description

[0016] Figure 1 This is a schematic diagram of the aircraft fairing transport packaging fixing device according to a preferred embodiment of the present invention; Figure 2 A schematic diagram of the bottom frame, central support assembly, first support clamping assembly, second support clamping assembly, and third support clamping assembly of the aircraft fairing transport packaging fixing device according to a preferred embodiment of the present invention. Figure 3 This is a schematic diagram of the side loading and unloading structure of the aircraft fairing transport packaging fixing device according to a preferred embodiment of the present invention; Figure 4 This is a schematic diagram of the support structure of the aircraft fairing transport packaging fixing device according to a preferred embodiment of the present invention; Figure 5 This is a schematic diagram of the connection between the aircraft fairing support module and the product according to a preferred embodiment of the present invention; Figure 6 Schematic diagram of the end tray module of the aircraft fairing transport packaging fixing device; Figure 7 Schematic diagram of the fastening structure for the aircraft fairing packaging box; Figure 8 A schematic diagram of the side panel structure of an aircraft fairing packaging box; Figure 9 Diagram showing the pre-installed fastening connectors for the aircraft fairing packaging box; Figure 10 Schematic diagram of the upper protective structure of the aircraft fairing packaging box; Figure 11 A schematic diagram of the connection of the aircraft fairing fastening straps; Figure 12 A schematic diagram of the connector on the process port cover of an aircraft fairing; 1 is the lifting point, 2 is the quick-release assembly of the upper cover, 3 is the connector, 4 is the forklift opening, 5 is the pallet module, 6 is the product frame, 7 is the EVA material, 8 is the wooden pallet module, 9 is the fastening strap, 10 is the pressure plate module, 11 is the movable baffle, 12 is the wooden baffle, and 13 is the connector. Detailed Implementation

[0017] 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.

[0018] 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.

[0019] 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 in each other. The present invention will now be described in detail with reference to the accompanying drawings and embodiments.

[0020] To address the transportation protection requirements of the riveted structure of the weakly rigid fairing, the following packaging and fixing scheme is adopted: through technical analysis, some metal maintenance covers are selected as mooring points. By combining multi-point flexible constraints with the internal buffer support structure of the fairing, a three-dimensional support and fixing system is constructed to achieve energy dispersion and impact absorption during transportation vibration, thereby effectively suppressing the risk of plastic deformation of the riveted structure.

[0021] The detailed technical solution mainly includes the following two aspects: 1. Structural support and mechanical reinforcement Determination of process tethering points Based on the stress analysis of the fairing structure, three metal maintenance covers were selected as the main Z-axis fixing points in areas where binding was difficult on the main support surfaces. Process covers with built-in tethering points were used instead of the metal maintenance covers installed on the aircraft fairing structure. Twelve tethering straps were used to connect the joints on the process covers to the joints on the base assembly beam. Fasteners were used to tighten the tethering straps, reducing tensile deformation and limiting the product's upward, forward, backward, and left-right movement.

[0022] Modular support The packaging box base assembly mainly consists of a bottom mounting plate and an upper modular support. The base is welded from steel profiles and plates. A wooden pallet module is mounted on the upper part of the support, and the floor is made of 3mm thick patterned steel plate. Quick-release components, rain cover hooks, lifting points, and transport vehicle connection joints are installed around the base frame. A fixed support frame is installed above the base plate for mounting the pallet and pressure plate modules. A machined frame beam inside the fairing is selected as the main support for the product. Corresponding L-shaped pallet modules are installed on the modular support to support the product while restricting its longitudinal and lateral movement. The entire fairing is secured to the modular support using straps and clamping devices, completing the fairing packaging and securing.

[0023] 2. Selection of cushioning materials At the contact points with the fairing structure, EVA material with flexible and impact-resistant properties is used for isolation and shock absorption. Vibration energy is absorbed through the elastic deformation of the soft material, forming a unified whole between the packaging box and the fairing product.

[0024] Example 1 The front aircraft fairing (behind frame 26) is located above the main fuselage structure, situated between frame 26 and frame 32A. Its design weight is approximately 260 kg, with external dimensions of approximately 3500 mm long, 5500 mm wide, and 2200 mm high. The packaging box measures 6300 mm × 3740 mm × 2840 mm and weighs approximately 3.2 tons. The overall frame of the packaging box is reusable. The front aircraft fairing (behind frame 26) packaging box consists of several main parts, including a Q235 steel welded base, a steel support frame, a steel upper cover, pine wood pallet modules, pressure plate modules, and baffles. The base and upper support frame are welded into a modular unit. A wooden pallet module is mounted on the upper end of the support frame. After the product is placed inside, the pressure plate module and baffle are connected to the support frame on the base using bolts. The wooden pallet module, pressure plate module, and baffle are wrapped with 20 mm thick EVA material in the areas in contact with the product, providing isolation and cushioning. (1) Front aircraft fairing (26 frames rear) packaging box base assembly structure The front aircraft fairing (26-frame rear) packaging box base assembly includes a base and an upper welded bracket. The overall structure is welded from steel profiles and steel plates. A wooden pallet module is mounted on the upper end of the bracket, and the floor is made of 3mm thick patterned steel plate, which also serves as a work platform during packaging. The base frame is equipped with quick-release components, rain cover hooks, lifting points, and transport vehicle connection joints. A fixed support frame is installed above the base plate for mounting the pallet module and pressure plate module. The base assembly structure is as follows: Figure 2 As shown.

[0025] The lower end of the base assembly is designed with two 200×100mm rectangular tubes, 1600mm center-to-center, arranged along the width to serve as forklift openings, according to standard forklift interface dimensions. The surrounding area is welded with a quick-release cover assembly, rain cover hooks, lifting points, and connectors for connection to the transport vehicle. Figure 3 Show.

[0026] Eight pallet modules, evenly distributed inside the product at frames 26, 29, and 32A, serve as the main load-bearing structure supporting the product and also limit the product's position when placed in the packaging box. Figure 2 As shown.

[0027] The pallet modules at frames 26 and 29 are L-shaped, used for lateral positioning when the product is placed in the packaging box. The contact area between the pallet module and the product is bonded with 20mm thick EVA material and covered with canvas. The specific connection method between the pallet module and the product is as follows... Figure 5 As shown.

[0028] The groove in the pallet module at frame 32A is used to limit the forward and backward movement of the product when it is placed into the packaging box. The contact area between the pallet module and the product is bonded with 20mm thick EVA material and covered with canvas. The end pallet module is as follows... Figure 6 As shown.

[0029] The four pressure plate modules arranged on the outside of the product at frames 26 and 32A, and the one fastening strap arranged on the outer surface of the product at frame 29, are all used to restrict the upward movement of the product. Figure 7 As shown.

[0030] The base assembly features three sets of wooden baffles and two sets of movable baffles on each side (the movable baffles are filled with PER foam to clamp the product after it is placed inside). These baffles are designed to prevent vibration at the bottom of the product during transportation. Figure 8 As shown (left side only).

[0031] The structural beam at the upper end of the support is equipped with a fastening strap connector, which connects to the connector on the process port cover via a fastening strap to restrict the product's upward, forward, backward, left, and right movement. The connector is as follows: Figure 9 As shown.

[0032] (2) Front aircraft fairing (26 frames rear) packaging box upper cover structure The outer cover of the packaging box mainly serves to provide support and rain protection, as well as to protect the internal products and the main structure of the box from impacts. It is welded from 40×40mm square tubing with a thickness of 3mm. Figure 10 As shown, a 5mm thick connecting strip is added to the joint of the square tubes on the upper cover as a structural reinforcement at the intersection point, and a 10mm thick mounting plate with an opening is welded to the lower end for connection with the quick-release assembly on the base assembly.

[0033] (3) Connection and fixation between the front aircraft fairing (behind frame 26) and the packaging box Three of the product's outer caps were replaced with process caps. The process caps maintained the same structure as the product, and metal connectors were installed inside for localized reinforcement. Twelve tension straps were used to bind the connectors on the process caps to the tension strap connections on the base assembly beam. The tension straps were then tightened with fasteners to reduce tensile deformation and limit the product's upward, backward, left, and right movement. The connection of the tension straps (the crosshairs on the process caps) is as follows: Figure 11 As shown, the connector on the process port cover is as follows Figure 12 As shown. After the product is secured, reinstall the upper cover structure of the packaging box and connect it to the base of the packaging box using the quick-release assembly.

[0034] Example 2 Front aircraft fairing packaging process a. Place the front aircraft fairing product into the base of the packaging box by hoisting it in place, and adjust the position of all wooden pallet modules and inner baffles in the packaging box; b. First, install the four outer pressure plate modules, six wooden baffles, and six movable baffles (the movable baffles are filled with protective foam to clamp the product after it is placed in) to prevent the front aircraft fairing product from moving upwards and vibrating at the bottom during transportation; c. Use 12 fastening straps to bind the joints on the process port cover and the fastening strap connection joints on the base assembly beam, and use fasteners to tighten and straighten the fastening straps to reduce the amount of tensile deformation of the fastening straps and prevent the product from moving upward, backward, left and right during transportation. d. Install a fastening strap at frame 29 on the outside of the product to limit the upward movement of the middle part of the product; and add fastening straps on the outside of the aircraft fairing product as needed for binding. e. The corner pieces extending from the lower frame edge on the lower surface of the aircraft fairing are wrapped with protective foam and then secured with protective tape; f. Hoist the cover onto the base of the packaging box, ensuring the fixing pins between the cover and the main body of the packaging box are aligned, and complete the base connection and fixation, connecting the quick-release components and bolts; Use a rainproof cover to completely cover the packaging box to prevent rain, snow, and debris from causing surface damage to the aircraft fairing during transportation.

Claims

1. An aircraft cowling component shipping package securing device, comprising: The application relates to a packaging fixing device for an aircraft fairing component, and the aircraft fairing component is in a lower-coupling type C-shaped semi-enclosing structure, and comprises a machined frame beam skeleton, a composite material panel covering the machined frame beam skeleton and a maintenance door cover installed on the composite material panel. The bottom frame, the center supporting assembly, the first supporting and clamping assembly, the second supporting and clamping assembly and the third supporting and clamping assembly are arranged in the center of the bottom frame, and are used for supporting the center top machined frame beam skeleton of the aircraft fairing component; the first supporting and clamping assembly is arranged in front of the center supporting assembly, and is used for supporting the bottom and clamping the top of the front end machined frame beam skeleton of the aircraft fairing component; the second supporting and clamping assembly and the third supporting and clamping assembly are symmetrically arranged on the left and right sides of the center supporting assembly, and are used for supporting the bottom and clamping the top of the machined frame beam skeletons on the two sides of the aircraft fairing component.

2. An aircraft whole body enclosure component shipping package securing device as defined in claim 1, wherein, The transportation packaging fixing device further comprises a process door cover, cross ear pieces fixed to the surface of the process door cover near the bottom frame and a binding belt; the process door cover replaces the maintenance door cover on the top of the aircraft fairing component, one end of the binding belt is connected with the cross ear pieces, and the other end is fixedly connected with the ear pieces on the bottom frame, and is used for pulling and fixing the top of the aircraft fairing component.

3. An aircraft whole body enclosure component shipping package securing device as defined in claim 1, wherein, The center supporting assembly comprises a center supporting bracket and a center drag plate; the bottom end of the center supporting bracket is fixedly connected with the bottom frame, the center drag plate is fixed to the top end of the center supporting bracket, and the center drag plate is provided with a center clamping groove which is consistent with the distribution direction of the top machined frame beam skeleton of the aircraft fairing component, and is used for supporting the product and limiting the longitudinal and transverse movement of the product.

4. An aircraft whole body enclosure component shipping package securing device as defined in claim 1, wherein, The first supporting and clamping assembly comprises a first supporting unit and a first clamping unit; the bottom end of the first supporting unit is fixedly connected with the bottom frame, the bottom end of the first clamping unit is slidingly connected with the bottom frame, the top of the first supporting unit internally fixes and supports the front end of the aircraft fairing component, and the top of the first clamping unit externally presses and clamps the front end of the aircraft fairing component in the same position as the first supporting unit; the first supporting unit comprises a first supporting bracket and a first supporting drag plate; the bottom end of the first supporting bracket is fixedly connected with the bottom frame, and the first supporting drag plate is fixed to the top end of the first supporting bracket; the first supporting drag plate is provided with a first clamping groove which is consistent with the distribution direction of the machined frame beam skeleton corresponding to the position of the aircraft fairing component; the first clamping unit comprises a first clamping bracket and a first clamping pressing plate; the bottom end of the first clamping bracket is slidingly connected with the bottom frame, realizes the sliding of approaching and moving away relative to the first supporting unit, and is positioned and locked through a first positioning pin; the first clamping pressing plate is fixed to the top end of the first clamping bracket, and the side of the first clamping pressing plate in contact with the front end of the aircraft fairing component has a pressing surface which is co-molded with the outer shape of the front end of the aircraft fairing component.

5. An aircraft whole body enclosure component shipping package securing device as defined in claim 1, wherein, The second support and clamping assembly includes multiple sets of second support units and second clamping units of different heights. The bottom end of the second support unit is fixedly connected to the bottom frame, and the bottom end of the second clamping unit is slidably connected to the bottom frame. The tops of the multiple sets of second support units provide internal support to one side of the aircraft fairing component, and the tops of the multiple sets of second clamping units cooperate with the second support unit at the same position to externally press and clamp the aircraft fairing component. The second support unit includes a second support bracket and a second support slide. The bottom end of the second support bracket is fixedly connected to the bottom frame. The second support slide is fixed to the top of the second support bracket. The second support slide has a second slot that is consistent with the distribution direction of the machined frame beam corresponding to the aircraft fairing component. The second clamping unit includes a second clamping bracket and a second clamping pressure plate. The bottom end of the second clamping bracket is slidably connected to the bottom frame to achieve sliding relative to the second support unit and to achieve positioning and locking by a second positioning pin. The second clamping pressure plate is fixed to the top of the second clamping bracket. The side of the second clamping pressure plate that contacts the aircraft fairing component has a pressure surface that conforms to the shape of the corresponding position.

6. An aircraft whole body enclosure component shipping package securing device as defined in claim 1, wherein, The third support and clamping assembly includes multiple sets of third support units and third clamping units of different heights. The bottom end of the third support unit is fixedly connected to the bottom frame, and the bottom end of the third clamping unit is slidably connected to the bottom frame. The tops of the multiple sets of third support units provide internal fixed support to one side of the aircraft fairing component, and the tops of the multiple sets of third clamping units cooperate with the third support unit in the same position to externally press and clamp the aircraft fairing component. The third support unit includes a third support bracket and a third support slide. The bottom end of the third support bracket is fixedly connected to the bottom frame. The third support slide is fixed to the top of the third support bracket. The third support slide has a third slot that is consistent with the distribution direction of the machined frame beam skeleton at the corresponding position of the aircraft fairing component. The third clamping unit includes a third clamping bracket and a third clamping pressure plate. The bottom end of the third clamping bracket is slidably connected to the bottom frame to achieve sliding relative to the third support unit, and is positioned and locked by a third positioning pin. The third clamping pressure plate is fixed to the top of the third clamping bracket. The side of the third clamping pressure plate that contacts the aircraft fairing component has a pressure surface that conforms to the shape of the corresponding position.

7. An aircraft whole body enclosure component shipping package securing device as defined in claim 1, wherein, The contact surfaces of the central support assembly, the first support clamping assembly, the second support clamping assembly, the third support clamping assembly, and the aircraft fairing components are isolated and damped using EVA material with flexible and impact-resistant properties. Vibration energy is absorbed through the elastic deformation of the soft material, forming a unified whole between the packaging box and the fairing product.

8. An aircraft whole body enclosure component shipping package securing device as defined in claim 1, wherein, The transport packaging securing device also includes an upper frame structure, which is located above the aircraft fairing component and is used for overall protection of the outer surface of the aircraft fairing component. Its bottom end is connected to the bottom frame.

9. An aircraft nacelle component transport packaging securing method using the aircraft nacelle component transport packaging securing device according to any one of claims 1 to 8, characterized in that Includes the following steps: The aircraft fairing components are hoisted onto the bottom frame and aligned with the corresponding positions of the center support assembly, the first support clamping assembly, the second support clamping assembly, and the third support clamping assembly. The aircraft fairing components are placed and snapped onto the central support assembly; The first support clamping assembly, the second support clamping assembly, and the third support clamping assembly are used to clamp and press the aircraft fairing components.

10. A method of packaging and securing an aircraft whole-mould component for transport according to claim 9, wherein, By performing stress analysis on the aircraft fairing components, at least three maintenance access covers were selected on the front two sides and the middle of the aircraft fairing components to be replaced with process access covers. The cross lugs were pulled to the bottom frame and fixed in four mutually orthogonal directions using the binding straps, serving as the main fixing points in the Z direction for tethering.

Images