Removable fairing for helicopter

Abstract

The present invention belongs to the design technology of helicopter fairings, and relates to a detachable fairing for helicopters. It comprises: a left detachable fairing, a right detachable fairing, a middle quick-release fairing, and a guide limit device. The present invention adopts a block-type design, dividing the fairing into two functional fairings: general disassembly and quick disassembly, which respectively correspond to the two usage requirements of "aircraft overhaul or engine troubleshooting" and "regular inspection, maintenance and troubleshooting of airborne equipment". The middle quick-release fairing adopts a composite sandwich structure, which can reduce the weight of the fairing structure by about 20% and shorten the fairing manufacturing cycle by nearly 50%. The quick-release design using a quick-release cloud-shaped lock and a guide limit device can effectively improve the efficiency of fairing disassembly and installation by nearly 10 times compared with ordinary bolt connection methods while ensuring the safety of aircraft flight, and effectively extend the service life of fasteners, ensure the aircraft attendance rate, and improve the economic benefits and civil market competitiveness of this type of aircraft.

Description

Technical Field

[0001] The invention belongs to helicopter fairing design technology and relates to a detachable helicopter fairing. Background Art

[0002] Currently, helicopters' rear firewall fairings often use one-piece bolted fairings, segmented bolted fairings, integral sliding fairings, or fixed-wrap fairings with localized inspection and maintenance access panels. None of these types effectively address the daily maintenance of onboard equipment, quick assembly and disassembly of the fairing, or lightweight design. Furthermore, when aircraft are modified and their onboard equipment is readjusted, significant time and cost are required to redesign the rear firewall fairing, significantly impacting the competitiveness of civil aircraft in the market. Summary of the Invention

[0003] Purpose of the invention: To invent a helicopter fairing that can be quickly disassembled and installed, so as to improve the maintainability of onboard equipment and achieve the goal of lightweight and low-cost design of the fairing.

[0004] Technical solution:

[0005] A detachable fairing for a helicopter comprises a left detachable fairing, a right detachable fairing, a middle quick-detachable fairing, and a guide limiting device.

[0006] Furthermore, the left detachable fairing includes a left fairing skin, a left reinforcing angle bar, and a left locking frame, wherein the left detachable fairing is fixedly connected to the helicopter firewall and the airborne equipment mounting platform by ordinary bolts.

[0007] Furthermore, the left fairing skin is an aluminum alloy part, which reduces the weight of the fairing structure while playing a role in aerodynamic rectification and protection of airborne equipment.

[0008] Furthermore, the left side reinforcing angle material is an aluminum alloy part, which is fixedly connected to the left side fairing skin by ordinary riveting connection, thereby improving the overall stiffness and stability of the left side fairing skin.

[0009] Furthermore, the left lock frame is an aluminum alloy part, which is fixedly connected to the left fairing skin and the left reinforcing angle material by ordinary riveting connection, providing an installation position for the quick-release cloud-shaped lock fixed connection.

[0010] Furthermore, the right detachable fairing includes a right fairing skin, a right reinforcing angle bar, and a right locking frame, wherein the right detachable fairing is fixedly connected to the helicopter firewall and the airborne equipment mounting platform by ordinary bolts.

[0011] Furthermore, the right fairing skin is an aluminum alloy part, which reduces the weight of the fairing structure while playing a role in aerodynamic rectification and protection of airborne equipment.

[0012] Furthermore, the right side reinforcing angle material is an aluminum alloy part, which is fixedly connected to the right side fairing skin by ordinary riveting connection method, thereby improving the overall stiffness and stability of the right side fairing skin.

[0013] Furthermore, the right lock frame is an aluminum alloy part, which is fixedly connected to the right fairing skin and the right reinforcing angle material by ordinary riveting connection, providing an installation position for the quick-release cloud-shaped lock fixed connection.

[0014] Furthermore, the middle quick-release fairing includes a middle fairing skin, an insert, and a quick-release cloud-shaped lock, wherein the middle quick-release fairing is fixedly connected to the left detachable fairing, the right detachable fairing and the airborne equipment mounting platform through the quick-release cloud-shaped lock.

[0015] Furthermore, the central fairing skin adopts a lightweight design in the form of a composite honeycomb sandwich structure, which not only reduces the weight of the fairing structure but also plays a role in aerodynamic straightening and protection of airborne equipment.

[0016] Furthermore, the insert is a finished fastening connector, which is embedded in the middle fairing skin by conventional adhesive connection method and is used for fixed connection of the guide limit device.

[0017] Furthermore, the quick-release cloud-shaped lock is a finished fastening connector, which is fixedly connected to the left detachable fairing, the right detachable fairing, the middle fairing skin and the airborne equipment installation platform through ordinary riveting connection. It can realize the rapid disassembly of the middle quick-release fairing, effectively improving the maintainability of the helicopter's airborne equipment.

[0018] Furthermore, the guide limit device includes a connecting joint, a connecting support, an adjustable gasket, a bushing, and a guide pin, wherein the connecting joint is fixedly connected to the middle quick-release fairing through a common bolt connection method, and the connecting support is fixedly connected to the airborne equipment mounting platform through common bolts.

[0019] Furthermore, the connecting joint is an aluminum alloy part, which is fixedly connected to the central quick-release fairing by ordinary bolt connection.

[0020] Furthermore, the connecting support is an aluminum alloy part, which is fixedly connected to the airborne equipment installation platform by ordinary bolt connection.

[0021] Furthermore, the adjustable gasket is a part made of multiple layers of 0.2mm thick aluminum alloy sheets fixed together by ordinary gluing, and is mainly used to adjust the gap between the connection support and the airborne equipment installation platform.

[0022] Furthermore, the bushing is a stainless steel part, which is embedded in the connecting joint through a temperature difference method and is used for inserting and fixing the guide pin.

[0023] Furthermore, a layer of sealant is applied around the fitting area between the bushing and the connection joint to prevent electrochemical corrosion between the bushing and the connection joint.

[0024] Furthermore, the guide pin is a stainless steel part, which is fixedly connected to the connecting support by ordinary bolt connection, and is used for guiding the installation and fixation of the middle quick-release fairing.

[0025] Furthermore, a layer of sealant is applied to the contact surface between the guide pin and the connecting support to prevent electrochemical corrosion between the guide pin and the connecting support.

[0026] Beneficial effects:

[0027] This invention relates to helicopter fairing design technology, specifically a removable helicopter fairing. It comprises a left-side removable fairing, a right-side removable fairing, a central quick-release fairing, and a guide and stop device. The present invention utilizes a segmented design, dividing the fairing into two functional types: general disassembly and quick-release, tailored to the actual aircraft's operational needs. These functions correspond to "aircraft overhaul or engine troubleshooting" and "regular maintenance and troubleshooting of onboard equipment," respectively. Furthermore, the present invention utilizes a lightweight, quick-release design. The central quick-release fairing utilizes a composite sandwich structure, reducing fairing weight by approximately 20% and shortening the fairing manufacturing cycle by nearly 50%. The quick-release design, which utilizes a quick-release cloud-shaped lock and a guide and stop device, effectively improves fairing removal and installation efficiency by nearly 10 times compared to conventional bolted connections, while ensuring flight safety. This design also effectively extends the service life of fasteners, ensuring aircraft availability and enhancing the economic benefits and competitiveness of this aircraft type in the civilian market. BRIEF DESCRIPTION OF THE DRAWINGS

[0028] Figure 1 Schematic diagram of the position of the entire aircraft with a detachable fairing according to an embodiment of the present invention;

[0029] Figure 2 A schematic diagram of the composition of a left detachable fairing according to an embodiment of the present invention;

[0030] Figure 3 A schematic diagram of the right detachable fairing according to an embodiment of the present invention;

[0031] Figure 4 A schematic diagram of the composition of a middle quick-release fairing according to an embodiment of the present invention;

[0032] Figure 5 Schematic diagram of the connection of a quick-release cloud-shaped lock according to an embodiment of the present invention;

[0033] Figure 6 A schematic diagram of an installation of an embedded component according to an embodiment of the present invention;

[0034] Figure 7 Schematic diagram of a guide and limiting device according to an embodiment of the present invention;

[0035] Figure 8 Schematic diagram of the left side guide limit device according to an embodiment of the present invention;

[0036] Figure 9 Schematic diagram of the right guide limit device according to an embodiment of the present invention;

[0037] Figure 10 This is a schematic diagram of the installation of a limiting device according to an embodiment of the present invention (only the left side is shown);

[0038] Figure 11 This is a schematic diagram of the installation of a central quick-release fairing according to an embodiment of the present invention (only the guide and limit device is shown).

[0039] 1. Left detachable fairing 2. Right detachable fairing 3. Middle quick-release fairing 4. Guide limiter 5. Firewall 6. Airborne equipment mounting platform 7. Engine exhaust pipe 101. Left fairing skin 102. Left reinforced angle bar 103. Lock frame 201. Right fairing skin 202. Right reinforced angle bar 301. Middle fairing skin 302. Quick-release cloud lock 303. Insert 401. Left guide limiter Position 402. Right guide limit device 3021. Spring sheet 3022. Quick-release screw 3023. Adjustment pad 3024. Cloud-shaped lock seat 4000. Sealant 4011. Left connecting joint 4012. Left connecting support 4013. Adjustable gasket 4014. Bushing 4015. Short guide pin 4016. Nut 4017. Washer 4021. Right connecting joint 4022. Right connecting support 4023. Long guide pin. DETAILED DESCRIPTION

[0040] The fairing is fixed to the firewall and the onboard equipment mounting platform using conventional bolt connections. This invention utilizes a block-type, quick-release fastener design and a guide limiter. This design effectively reduces the difficulty of fairing removal and installation, while ensuring flight safety, and improves the maintainability of the aircraft's onboard equipment.

[0041] A detachable fairing for a helicopter according to an embodiment of the present invention includes: a left detachable fairing, a right detachable fairing, a middle quick-release fairing, and a guide and limiting device.

[0042] Furthermore, the left detachable fairing is fixedly connected to the firewall and the airborne equipment mounting platform by ordinary bolt connection.

[0043] Furthermore, the left detachable fairing includes a left fairing skin, a left reinforcing angle bar, and a locking frame, wherein the left reinforcing angle bar and the locking frame are fixedly connected to the left fairing skin by ordinary riveting connection.

[0044] Furthermore, the right detachable fairing is fixedly connected to the firewall and the airborne equipment mounting platform by ordinary bolt connection.

[0045] Furthermore, the right detachable fairing includes a right fairing skin, a right reinforcing angle bar, and a locking frame, wherein the right reinforcing angle bar and the locking frame are fixedly connected to the right fairing skin by ordinary riveting connection.

[0046] Furthermore, the middle quick-release fairing includes a middle fairing skin, an insert, and a quick-release cloud-shaped lock, wherein the middle quick-release fairing is fixedly connected to the firewall, the left detachable fairing, the right detachable fairing and the airborne equipment mounting platform through the quick-release cloud-shaped lock.

[0047] Furthermore, the insert is embedded in the interior of the middle fairing skin by conventional adhesive connection, providing a fixed installation point for the guide limit device.

[0048] Furthermore, the quick-release cloud-shaped lock is fixedly connected to the left detachable fairing, the right detachable fairing, the middle fairing skin, and the airborne equipment installation platform through ordinary riveting connection methods.

[0049] Furthermore, the guide and limit device includes a connecting joint, a connecting support, an adjustable spacer, a bushing, a guide pin, a fastening nut, and a nut washer, which are used to guide the installation and fixed connection of the central quick-release fairing. The connecting joint and the connecting support are fixed to the central quick-release fairing and the airborne equipment mounting platform respectively using ordinary bolt connections.

[0050] Furthermore, the adjustable gasket is a part made of multiple layers of 0.2mm thick aluminum alloy sheets fixed together by ordinary gluing, and is mainly used for adjusting the gap between the connection support and the airborne equipment installation platform.

[0051] Furthermore, the bushing is embedded in the connecting joint through the temperature difference method, and the guide pin is fixedly connected to the connecting support through a fastening nut. The bushing, guide pin, and nut washer are all stainless steel parts, and ordinary sealant is used to fill the surrounding protection method to avoid electrochemical corrosion between the stainless steel material and the aluminum alloy material.

[0052] The following is a detailed description with reference to the accompanying drawings.

[0053] The present invention comprises a left detachable fairing 1, a right detachable fairing 2, a middle quick-release fairing 3, and a guide limiter 4. Figure 1 shown.

[0054] The left detachable fairing 1 is composed of a left fairing skin 101, a left reinforcing angle 102, and a locking frame 103. The left detachable fairing 1 is fixedly connected to the firewall 5 and the airborne equipment installation platform 6 by ordinary bolt connection. Figure 1 、 Figure 2 shown.

[0055] The left fairing skin 101 is an aluminum alloy part, and the forming method is common sheet metal forming, such as Figure 2 shown.

[0056] The left side reinforcement angle 102 and the lock frame 103 are fixedly connected to the left side fairing skin 101 by ordinary riveting connection. Figure 2 shown.

[0057] The right detachable fairing 2 is composed of a right fairing skin 201, a right reinforcing angle bar 202, and a locking frame 103. The right detachable fairing 2 is fixedly connected to the firewall 5 and the airborne equipment installation platform 6 by ordinary bolt connection. Figure 1 、 Figure 3 shown.

[0058] The right fairing skin 201 is an aluminum alloy part, and the forming method is common sheet metal forming, such as Figure 3 shown.

[0059] The right side reinforcement angle bar 202 and the lock frame 103 are fixedly connected to the right side fairing skin 201 by ordinary riveting connection. Figure 3 shown.

[0060] The middle quick-release fairing 3 is composed of a middle fairing skin 301, a quick-release cloud-shaped lock 302, and an insert 303. The middle quick-release fairing 3 is fixedly connected to the firewall 5, the left detachable fairing 1, the right detachable fairing 2, and the airborne equipment installation platform 6 through the quick-release cloud-shaped lock 302. Figure 1 、 Figure 4 shown.

[0061] The quick-release cloud-shaped lock 302 is composed of a spring sheet 3021, a quick-release screw 3022, an adjustment pad 3023, and a cloud-shaped lock seat 3024. The quick-release cloud-shaped lock 302 is a finished fastening connector, wherein the spring sheet 3021 is fixedly connected to the middle fairing skin 301 by a common riveting method, the adjustment pad 3023 and the cloud-shaped lock seat 3024 are fixedly connected to the lock frame 103 or the firewall 5 or the airborne equipment installation platform 6 by a common riveting method, and the quick-release screw 3022 and the cloud-shaped lock seat 3024 are locked by a mechanical connection to achieve a fixed connection of the middle quick-release fairing 3, as shown in FIG. Figure 5 shown.

[0062] The insert 303 is fixed to the interior of the middle fairing skin 301 by conventional adhesive connection method, providing a fixed installation point for the guide limit device 4, such as Figure 6 shown.

[0063] The guide and limit device 4 is composed of a left guide and limit device 401 and a right guide and limit device 402. Figure 7 shown.

[0064] The left guide limit device 401 is composed of a left connecting joint 4011, a left connecting support 4012, an adjustable gasket 4013, a bushing 4014, a short guide pin 4015, a nut 4016, and a washer 4017. Figure 7 、 Figure 8 shown.

[0065] The right guide limit device 401 is composed of a right connecting joint 4021, a right connecting support 4022, a long guide pin 4025, an adjustable spacer 4013, a bushing 4014, a nut 4016, and a washer 4017. Figure 7 、 Figure 9 shown.

[0066] The left connecting joint 4011 and the left connecting support 4012 are fixedly connected to the middle quick-release fairing 3 and the airborne equipment installation platform 6 respectively by ordinary bolt connection. Figure 1 、 Figure 6 、 Figure 7 、 Figure 8 、 Figure 9 shown.

[0067] The adjustable gasket 4013 is used to adjust the gap between the left connecting support 4012, the right connecting support 4022 and the airborne equipment installation platform 6, which can effectively reduce the difficulty of positioning and installing the guide limit device 4 and increase the difficulty of disassembling and installing the central quick-release fairing 3. Figure 1 、 Figure 6 、 Figure 7 、 Figure 8 、 Figure 9 、 Figure 11 shown.

[0068] The bushing 4014 is assembled into the left connecting joint 4011 and the right connecting joint 4021 by the temperature difference method, and the sealant 4000 is applied around the circumference to prevent electrochemical corrosion between the stainless steel parts and the aluminum alloy parts. Figure 8 、 Figure 9 、 Figure 10 shown.

[0069] The short guide pin 4015 and the long guide pin 4023 are fixedly connected to the left connecting support 4012 and the right connecting support 4022 through nuts 4016 and washers 4017, and sealant 4000 is applied around them to prevent electrochemical corrosion between stainless steel parts and aluminum alloy parts. Figure 8 、 Figure 9 、 Figure 10 shown.

[0070] The short guide pin 4015 and the long guide pin 4023 are designed in a long and short combination. When installing the middle quick-release fairing 3, the long guide pin 4023 is used to perform preliminary positioning of the middle quick-release fairing 3. Then, the angle and position of the middle quick-release fairing 3 are adjusted by swinging to force the short guide pin 4015 to align with the bushing 4014, and finally the positioning of the middle quick-release fairing 3 is completed. Figure 1 、 Figure 7 、 Figure 8 、 Figure 9 、 Figure 10 、 Figure 11 shown.

[0071] The present invention solves and realizes the following functions:

[0072] According to the maintenance and installation position of the airborne equipment and the inspection and maintenance needs, the present invention adopts a block design, dividing the detachable fairing into three modular units: the left detachable fairing, the right detachable fairing and the middle quick-release fairing. The left detachable fairing and the right detachable fairing are connected with ordinary bolts and are only disassembled during aircraft overhaul or engine troubleshooting. The middle quick-release fairing is mainly used during regular inspection and maintenance and troubleshooting of airborne equipment, and is disassembled more frequently.

[0073] In addition, to improve the maintainability of airborne equipment and reduce the difficulty of fairing disassembly and installation, the present invention also adopts a lightweight, quick-release design. The central quick-release fairing adopts a composite sandwich structure, which can reduce the fairing structure weight by approximately 20% and shorten the fairing manufacturing cycle by nearly 50%. The quick-release design, which uses a quick-release cloud-shaped lock and a guide limiter, effectively improves the efficiency of fairing disassembly and installation by nearly 10 times compared to ordinary bolt connections while ensuring aircraft flight safety. It also effectively extends the service life of fasteners, ensures aircraft attendance, and improves the economic benefits and civil market competitiveness of this type of aircraft.

Claims

1. A detachable fairing for a helicopter, characterized in that: include: Left detachable fairing, right detachable fairing, middle quick-release fairing, guide limit device; The left detachable fairing includes a left fairing skin, a left reinforcing angle bar, and a left locking frame, wherein the left detachable fairing is fixedly connected to the helicopter firewall and the airborne equipment mounting platform by ordinary bolts; The right detachable fairing includes a right fairing skin, a right reinforcing angle bar, and a right locking frame, wherein the right detachable fairing is fixedly connected to the helicopter firewall and the airborne equipment mounting platform by ordinary bolts; The middle quick-release fairing includes a middle fairing skin, an insert, and a quick-release cloud-shaped lock, wherein the middle quick-release fairing is fixedly connected to the left detachable fairing, the right detachable fairing, and the airborne equipment installation platform through the quick-release cloud-shaped lock; The guide limit device includes a connecting joint, a connecting support, an adjustable gasket, a bushing, and a guide pin, wherein the connecting joint is fixedly connected to the middle quick-release fairing through ordinary bolt connection, and the connecting support is fixedly connected to the airborne equipment mounting platform through ordinary bolts.

2. The helicopter detachable fairing according to claim 1, characterized in that: The left fairing skin is an aluminum alloy part; the right fairing skin is an aluminum alloy part.

3. The helicopter detachable fairing according to claim 1, characterized in that: The left side reinforcing angle material is an aluminum alloy part, which is fixedly connected to the left side fairing skin by ordinary riveting connection method; the right side reinforcing angle material is an aluminum alloy part, which is fixedly connected to the right side fairing skin by ordinary riveting connection method.

4. The helicopter detachable fairing according to claim 1, characterized in that: The left lock frame is an aluminum alloy part, which is fixed to the left fairing skin and the left reinforcing angle material by ordinary riveting connection, providing an installation position for the quick-release cloud-shaped lock fixed connection; the right lock frame is an aluminum alloy part, which is fixed to the right fairing skin and the right reinforcing angle material by ordinary riveting connection, providing an installation position for the quick-release cloud-shaped lock fixed connection.

5. The detachable fairing of a helicopter according to claim 1, characterized in that: The middle fairing skin adopts a composite honeycomb sandwich structure.

6. The detachable fairing of a helicopter according to claim 1, characterized in that: The insert is a finished fastening connector, which is embedded in the middle fairing skin by conventional gluing and is used for fixed connection of the guide limit device.

7. The detachable fairing of a helicopter according to claim 1, characterized in that: The quick-release cloud-shaped lock is a finished fastening connector, which is fixedly connected to the left detachable fairing, the right detachable fairing, the middle fairing skin and the airborne equipment installation platform through ordinary riveting connection method, and is used for the rapid disassembly of the middle quick-release fairing.

8. The helicopter detachable fairing according to claim 1, characterized in that: The connecting joint is an aluminum alloy part, which is fixed to the middle quick-release fairing by ordinary bolt connection; The connecting support is an aluminum alloy part and is fixedly connected to the airborne equipment mounting platform by ordinary bolt connection.

9. The detachable fairing of a helicopter according to claim 1, characterized in that: The adjustable gasket is a part made of multiple layers of 0.2mm thick aluminum alloy sheets fixed together by ordinary gluing, and is used to adjust the gap between the connection support and the airborne equipment installation platform.

10. The helicopter detachable fairing according to claim 1, characterized in that: The bushing is a stainless steel part that is embedded in the connection joint through the temperature difference method and is used for inserting and fixing the guide pin. A layer of sealant is applied around the bushing and the connection joint to prevent electrochemical corrosion between the bushing and the connection joint. The guide pin is a stainless steel part, which is fixed to the connecting support by ordinary bolt connection and is used for guiding, installing and fixing the middle quick-release fairing. A layer of sealant is applied to the fitting surface of the guide pin and the connecting support to prevent electrochemical corrosion between the guide pin and the connecting support.

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