Rotorcraft cabin cover capable of bearing large load and design method of rotorcraft cabin cover

Abstract

The invention provides a rotorcraft cabin cover capable of bearing a large load and a design method thereof, the rotorcraft cabin cover is located on a cabin framework in the front of a rotorcraft and is a main force bearing component of the cabin cover, all the components are connected into a whole through riveting, and a ceiling is located on the upper portion of the cabin framework; the right door frame is located on the right of the cabin framework. The right door frame inner skin is positioned on the right side of the cabin framework; the left door frame is located on the left of the cabin framework. The left door frame inner skin is positioned on the left side of the cabin framework; when the cockpit cover is assembled, the cockpit framework is riveted with the left door frame and the right door frame through tool positioning, then the ceiling is riveted, and finally the left door frame inner skin and the right door frame inner skin are riveted. The cabin framework is a rectangular framework formed by combining a plurality of aluminum alloy I-shaped beams, and a middle framework with an I-shaped section is arranged in the center of the cabin framework; the cabin cover serves as a main force bearing structure, the rigidity of the cabin cover is improved by optimizing the section of the cabin framework, the cabin cover can participate in full-aircraft load transmission, the borne load is larger, the deformation amount is reduced, and the cabin door sealing effect is improved.

Description

Technical Field

[0001] The invention belongs to the technical field of the structural design of autogyros, and particularly relates to an autogyro cockpit cover capable of withstanding large loads and a design method thereof. Background Art

[0002] The cockpit cover is an important part of the autogyro cockpit, generally composed of components such as a windshield skeleton, a cabin door skeleton, and a ceiling, and is mainly used to support components such as cabin doors, skins, and transparent parts.

[0003] At present, the cockpit cover of an autogyro is generally designed as a secondary load-bearing structure, and mostly adopts lightweight composite material configurations such as carbon fiber. In order to improve the structural stiffness, the cockpit skeleton is mostly designed in the form of a square tubular structure. The loads borne by the cockpit cover of the autogyro are mainly aerodynamic loads, and there is not much participation in the force transmission of the whole aircraft. The loads borne are small, and the deformation amount is large. There will be a large gap between the cabin door and the skeleton due to the deformation of the skeleton, seriously affecting the sealing effect of the cabin door. Summary of the Invention

[0004] In order to solve the technical problems in the prior art that the cockpit cover participates less in the force transmission of the whole aircraft, bears small loads, has a large deformation amount, and affects the sealing effect of the cabin door, the invention provides an autogyro cockpit cover capable of withstanding large loads and a design method thereof. The cockpit cover serves as the main load-bearing structure. By optimizing the cross-section of the cockpit skeleton, the stiffness of the cockpit cover is improved, and it participates in the transmission of the loads of the whole aircraft (such as the landing loads of the landing gear and aerodynamic loads), bears greater loads, reduces the deformation amount, and improves the sealing effect of the cabin door; it is used for the design of the cockpit cover capable of withstanding large loads. The technical solutions are as follows:

[0005] In a first aspect, an autogyro cockpit cover capable of withstanding large loads is provided. The autogyro cockpit cover is located at the front of the autogyro and includes: a ceiling 5, a right door frame inner skin 6, a right door frame 7, a left door frame inner skin 8, a left door frame 9, and a cockpit skeleton 4. Among them, the cockpit skeleton is the main load-bearing component of the cockpit cover, and each component is connected to form an integral body through riveting. The ceiling 5 is located above the cockpit skeleton 4, adopts a honeycomb sandwich structure, and is riveted to the cockpit skeleton 4; the right door frame 7 is located on the right side of the cockpit skeleton 4 and is riveted to the outer surface of the cockpit skeleton 4; the right door frame inner skin 6 is located on the right side of the cockpit skeleton 4 and is riveted to the inner surface of the cockpit skeleton 4; the left door frame 9 is located on the left side of the cockpit skeleton 4 and is riveted to the outer surface of the cockpit skeleton 4; the left door frame inner skin 8 is located on the left side of the cockpit skeleton 4 and is riveted to the inner surface of the cockpit skeleton 4; when assembling the cockpit cover, the cockpit skeleton 4 uses a tooling for positioning and is respectively riveted to the left door frame 9 and the right door frame 7, then the ceiling 5 is riveted, and finally the left door frame inner skin 8 and the right door frame inner skin 6 are riveted; the cockpit skeleton 4 is composed of a plurality of aluminum alloy I-beams combined into a stable rectangular frame, and an intermediate skeleton with an I-shaped cross-section is arranged at its central position; the cockpit skeleton 4 is connected to the main load-bearing structure of the airframe structure.

[0006] The canopy of the present invention is composed of a canopy framework 4, a ceiling 5, an inner skin of the right doorframe 6, a right doorframe 7, an inner skin of the left doorframe 8, and a left doorframe 9. Among them, the canopy framework 4 is composed of high-strength aluminum alloy I-beams to form a stable load-bearing structure, and reinforcing ribs and reinforcing plates are provided at key positions. Compared with the composite material canopy framework, this structure has good strength and stiffness, can efficiently disperse the load to each component, improves the overall load-bearing capacity of the canopy, and reduces the deformation of the canopy. At the same time, the present invention plans the load transfer path so that the canopy and other structures of the airframe jointly bear large loads such as the landing gear landing load, ensures that the load can be transmitted along a reasonable path, and through the stiffness matching design of the canopy, ensures that the canopy can smoothly transfer the force from the acting point to other load-bearing structures.

[0007] Among them, the canopy framework 4 adopts an I-shaped structure.

[0008] In the prior art, in order to facilitate the installation of systems such as transparent parts, blind nuts are pre-riveted inside the tubular structure. However, after being disassembled many times, the nuts are likely to fall off into the enclosed space and are not easy to repair and replace.

[0009] In the present invention, in order to facilitate the installation of the windshield and solve the problem that the connecting parts are not easy to maintain after falling off, the cross-section of the canopy framework abandons the traditional square tube configuration and adopts an I-shaped structure, changing the local connection method of the transparent parts, which is convenient for repair and replacement.

[0010] Optionally, the canopy framework 4 includes: an upper-side framework 11, a right-side framework 12, a middle framework 13, a left-side framework 14, and a lower-side framework 17.

[0011] The upper-side framework 11, the right-side framework 12, the left-side framework 14, and the lower-side framework 17 are respectively located at the upper, right, left, and lower parts of the canopy framework, forming a square frame; the middle framework 13 is located at the center line position of the fuselage, dividing the square frame into two parts on the left and right; the square frame is used for installing the windshield.

[0012] Furthermore, the canopy framework 4 may further include: a right-rear support member 15, a middle-lower support member 16, and a left-rear support member 18.

[0013] The middle-lower support member 16 is located below and behind the middle framework 13 and is riveted to the middle framework, which is used to improve the stability of the middle framework 13 and transfer a part of the vertical load.

[0014] The right-rear support member 15 and the left-rear support member 18 are respectively located obliquely behind the right-side framework 12 and the left-side framework 14, and can support the right-side framework 12, the left-side framework 14, and the lower-side framework 17 at the same time.

[0015] Optionally, the middle framework 13 extends outwardly to the outer sides of the upper framework 11 and the lower framework 17 respectively; the upper part of the middle framework 13 is riveted to the ceiling 5, and the lower part is hinged to the airframe structure through a joint;

[0016] The middle framework 13 forms a cross structure with the upper framework 11 and the lower framework 17 respectively, and the various components are nested and lapped with each other.

[0017] Optionally, the right framework 12 and the left framework 14 extend outwardly to the outer sides of the lower framework 17 along the windshield boundary line direction, forming a strong support leg, which is connected to other airframe structures to form another load transfer route; the right framework 12 and the left framework 14 also extend outwardly a certain distance to the outer sides of the upper framework 11, and are connected to the ceiling 5 through connectors to avoid sudden changes in load.

[0018] Optionally, the upper framework 11 extends rearward along the heading direction, which can not only play a role in the whole-aircraft load transfer, but also be used to support the hatch; the upper framework 11 is provided with a modified I-shaped cross-section, one side of which is connected to the windshield, and the other side is connected to the ceiling 5.

[0019] Optionally, in order to improve the support stiffness of the hatch and withstand the aerodynamic load, the left framework 14 and the left doorframe inner skin 8 and the left doorframe 9 form a modified cylindrical cross-section, and the right framework 12 and the right doorframe inner skin 6 and the right doorframe 7 form a modified cylindrical cross-section. Glass fitting surfaces and hatch sealing surfaces extend out on both sides of the modified cylindrical cross-section, meeting the requirements for glass installation, hatch sealing and structural load transfer.

[0020] Optionally, the middle framework 13 is composed of a middle right framework 21 and a middle left framework 22,

[0021] The middle right framework 21 and the middle left framework 22 are respectively located at the positions of two main load-bearing beams of the fuselage, and are hinged to the two main load-bearing beams of the fuselage through joints; the upper parts of the middle right framework 21 and the middle left framework 22 are riveted to the ceiling 5, and at the same time, an equipment installation plate is riveted below to form a top box section structure, which can also be used as a top console.

[0022] In a second aspect, a design method for a rotorcraft cockpit cover capable of withstanding large loads according to any one of the first aspect is provided, including:

[0023] Step 1, determine the large-load transfer path of the fuselage;

[0024] Step 2, determine the boundary lines and installation requirements of the hatch and the transparent parts;

[0025] Step 3, according to the requirements described in Step 1 and Step 2, determine the intersection positions of the cockpit framework and the fuselage structure;

[0026] Step 4: Determine the upper and lower boundary lines of the cockpit frame based on the upper and lower boundary lines of the cockpit frame and the transparent part in Step 2.

[0027] Step 5: Determine the cross-sectional forms of the left door frame and the right door frame according to the installation requirements of the cabin door.

[0028] Step 6: Complete the large load distribution based on the intersection points determined in Step 3 and Step 4, determine the loads of each component, and determine the cross-sectional shapes of each component of the cockpit frame according to the characteristics of the transmitted loads and the principle of minimum weight, and complete the determination of the dimensional parameters.

[0029] Step 7: Determine the connection form between the cockpit cover and the fuselage structure according to the assembly process and the component processing process, complete the determination of the process separation surfaces of each component, and complete the design of the cockpit cover.

[0030] The beneficial effects of the present invention are at least as follows:

[0031] (1) This cockpit cover is used to participate in the large load transmission of the whole aircraft, with direct force transmission, good structural stiffness, and high weight efficiency.

[0032] (2) The cross-section of the cockpit frame abandons the traditional square tube configuration and adopts an I-shaped structure, changing the local connection method of the transparent part, which is convenient for repair and replacement.

[0033] (3) This type of cockpit cover has a variant I-shaped cross-section and a variant cylindrical cross-section, which improves the structural stiffness and load transmission capacity and improves the connection processability of the glass.

[0034] (4) This cockpit cover has fewer parts and simple connection relationships, considers the assembly compensation with the fuselage structure, and has good installation processability. Description of the Drawings

[0035] Figure 1 It is a schematic diagram of the structure of the cockpit cover of the present invention;

[0036] Figure 2 It is a schematic diagram of the structure of cockpit frame configuration 1;

[0037] Figure 3 It is a schematic diagram of the structure of cockpit frame configuration 2;

[0038] Figure 4 It is a schematic diagram of the connection at the cross position of the frame;

[0039] Figure 5 It is a schematic cross-sectional diagram of the cabin door support structure;

[0040] Figure 6 It is a schematic cross-sectional diagram of the upper side frame structure;

[0041] Figure 7 It is a schematic diagram of the installation of the cockpit cover on the fuselage.

[0042] Among them, 4 - cockpit framework, 5 - ceiling, 6 - inner skin of right doorframe, 7 - right doorframe, 8 - inner skin of left doorframe, 9 - left doorframe, 11 - upper side framework, 12 - right side framework, 13 - middle framework, 14 - left side framework, 15 - right rear support, 16 - middle lower support, 17 - lower side framework, 18 - left rear support, 21 - middle right side framework, 22 - middle left side framework, 23 - belt plate, 24 - corner box. Specific embodiments

[0043] To make the objectives, technical solutions, and advantages of the embodiments of the present invention clearer, the technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are some, but not all, of the embodiments of the present invention. All other embodiments obtained by those of ordinary skill in the art based on the embodiments of the present invention without creative efforts fall within the scope of protection of the present invention.

[0044] The features and illustrative embodiments of various aspects of the present invention will be described in detail below. In the following detailed description, many specific details are set forth to provide a comprehensive understanding of the present invention. However, it is obvious to those skilled in the art that the present invention can be practiced without some of these specific details. The following description of the embodiments is only to provide a better understanding of the present invention by showing examples of the present invention. The present invention is in no way limited to any specific arrangements and methods set forth below, but covers any improvements, substitutions, and modifications of structures, methods, and devices without departing from the spirit of the present invention. Well-known structures and technologies are not shown in the drawings and the following description to avoid unnecessarily obscuring the present invention.

[0045] It should be noted that, without conflict, the embodiments of the present invention and the features in the embodiments can be combined with each other, and the various embodiments can refer to and cite each other.

[0046] The present invention will be described in detail below with reference to the accompanying drawings and specific embodiments.

[0047] Please refer to Figure 1 and Figure 7 , the cockpit cover of the autogyro of the present invention is located at the front of the autogyro and is mainly composed of a ceiling 5, an inner skin 6 of the right doorframe, a right doorframe 7, an inner skin 8 of the left doorframe, a left doorframe 9, and a cockpit framework 4. The cockpit framework 4 is divided into two configurations according to different load transfer routes, as shown in Figure 2 and Figure 3。The cockpit framework is the main load-bearing component of the cockpit canopy. Each component is connected to each other by riveting to form an integral whole. The ceiling 5 is located above the cockpit framework 4 and usually adopts a honeycomb sandwich structure, which is riveted to the cockpit framework 4; the right door frame 7 is located on the right side of the cockpit framework 4 and is riveted to the outer surface of the cockpit framework 4; the right door frame inner skin 6 is located on the right side of the cockpit framework 4 and is riveted to the inner surface of the cockpit framework 4; the left door frame 9 is located on the left side of the cockpit framework 4 and is riveted to the outer surface of the cockpit framework 4; the left door frame inner skin 8 is located on the left side of the cockpit framework 4 and is riveted to the inner surface of the cockpit framework 4. When assembling the cockpit canopy, the cockpit framework 4 uses tooling for positioning and rivets the left door frame 9 and the right door frame 7 respectively, then rivets the ceiling 5, and finally rivets the left door frame inner skin 8 and the right door frame inner skin 6.

[0048] See Figure 2 , the cockpit framework configuration 1 is mainly composed of an upper side framework 11, a right side framework 12, a middle framework 13, a left side framework 14, a right rear support member 15, a middle lower support member 16, a lower side framework 17 and a left rear support member 18.

[0049] The upper side framework 11, the right side framework 12, the left side framework 14 and the lower side framework 17 are respectively located at the upper, right, left and lower parts of the cockpit framework, forming a square frame. The middle framework 13 is located at the center line position of the fuselage, dividing the above-mentioned square frame into two parts on the left and right; the square frame is used to install the windshield. In order to facilitate the installation of the windshield and solve the problem that it is not easy to maintain when the connecting piece falls off, the cross-section of the cockpit framework abandons the traditional square tube configuration and adopts an I-shaped structure, and a vertical rib perpendicular to the outer surface is added at intervals, which has good maintainability while improving the stiffness.

[0050] According to the need of load transfer, the middle framework 13 extends outward to the upper side framework 11 and the lower side framework 17 respectively; the upper part of the middle framework 13 is riveted to the cockpit ceiling 5, and the lower part is hinged to the airframe structure through a joint; the middle lower support member 16 is located behind and below the middle framework 13 and is riveted to the middle framework, which is used to improve the stability of the middle framework 13 and transfer a part of the vertical load. The middle framework 13 forms a cross structure with the upper side framework 11 and the lower side framework 17 respectively. Each component is nested and overlapped with each other, and the positions that cannot be overlapped are connected by a strap 23 and an angle box 24. See Figure 4 。

[0051] The right-side frame 12 and the left-side frame 14 respectively extend downward and outward along the windshield boundary line direction to the outside of the lower-side frame 17, forming a strong support leg, which is connected to other structures of the airframe to form another load transmission path; the right rear support member 15 and the left rear support member 18 are respectively located obliquely behind the right-side frame 12 and the left-side frame 14, and can support the right-side frame 12, the left-side frame 14 and the lower-side frame 17 at the same time. The right-side frame 12 and the left-side frame 14 need to extend a certain distance upward and outward along the outside of the upper-side frame 11 and maintain a certain number of connecting pins with the cockpit ceiling 5, so as to avoid sudden changes in load.

[0052] The upper-side frame 11 extends backward along the course direction, which can not only play the role of the whole-aircraft load transmission, but also be used to support the hatch. The upper-side frame 11 needs to have a Figure 6 mutated I-shaped section as shown, with one side connected to the windshield and the other side connected to the ceiling 5.

[0053] In order to improve the support stiffness of the hatch and withstand the aerodynamic load, a mutated cylindrical section as shown in Figure 5 needs to be formed between the cockpit frame and the hatch. On the basis of the cylindrical section, a glass fitting surface and a hatch sealing surface are extended, meeting the requirements of glass installation, hatch sealing and structural load transmission.

[0054] See Figure 3 , the difference between the cockpit frame configuration 2 and the cockpit frame configuration 1 is that the middle frame is split into a middle right-side frame 21 and a middle left-side frame 22. The middle right-side frame 21 and the middle left-side frame 22 are respectively located at the positions of the two main load-bearing beams of the fuselage and are directly hinged to the two support beams of the fuselage through joints; the upper parts of the middle right-side frame 21 and the middle left-side frame 22 are riveted to the cockpit ceiling 5, and at the same time, an equipment installation plate is riveted below to form a top box section structure, which can also be used as a top console, and the structural weight efficiency is relatively high.

[0055] The design method of the cockpit cover that bears large loads in the embodiment of the present invention includes the following steps:

[0056] Step 1, determine the large-load transmission path of the fuselage;

[0057] Step 2, determine the boundary lines and installation requirements of the hatch and the transparent parts;

[0058] Step 3, according to the requirements described in Step 1 and Step 2, determine the intersection positions of the left-side frame, the right-side frame, the middle frame and the fuselage structure;

[0059] Step 4, according to the upper and lower boundary lines of the cockpit frame and the transparent parts in Step 2, determine the upper and lower boundary lines of the cockpit frame;

[0060] Step 5, according to the hatch installation requirements, determine the cross-sectional forms of the left door frame and the right door frame;

[0061] Step 6: Based on the intersection points determined in Step 3 and Step 4, complete the large load distribution, determine the loads on each component, and based on the characteristics of the transmitted loads and the principle of minimum weight, determine the cross-sectional shapes of each component of the cockpit frame, and complete the determination of the dimensional parameters;

[0062] Step 7: Based on the assembly and component processing technologies, determine the connection form between the cockpit cover and the fuselage structure, complete the determination of the technological separation surfaces of each component, and complete the design of the cockpit cover.

[0063] Among them, the intersection points of the left and right side frames and the fuselage structure in Step 3 are located at the positions of the main load-bearing frames;

[0064] If the transparent part is divided into two pieces, the middle frame in Step 3 is located at the axis of symmetry of the autogyro, and the intersection point is located on the front support frame; if the transparent part is divided into three pieces of left, middle and right, the middle frame in Step 3 is split into a middle right frame and a middle left frame, and the intersection points of the middle left and right frames with the fuselage are respectively located on the left and right main load-bearing beams, and are symmetrically arranged;

[0065] The upper and lower side frames determined in Step 4 need to extend obliquely downward to both sides for a certain distance and intersect with the main load-bearing frame of the fuselage to form another support leg of the cockpit cover for bearing the bending moment;

[0066] In Step 5, the left and right door frames and the left and right side frames form a variant cylindrical cross-section to improve the support stiffness of the cabin door;

[0067] In Step 6, each cross-section of the cockpit frame forms a variant I-shaped cross-section to improve the installation processability of the transparent part.

[0068] Exemplarily, adjustment gaskets are added at the connection positions between the cockpit cover and the fuselage, and the thickness of the gaskets is preferably 1-1.5 mm. It is used for compensating the structural assembly error.

[0069] The above only expresses the implementation modes of the present invention, and its description is relatively specific and detailed, but it cannot be understood as a limitation to the scope of the patent. It should be noted that for those of ordinary skill in the art, without departing from the concept of the present invention, several deformations and improvements can still be made, and these all belong to the protection scope of the present invention. In addition, the parts not elaborated in the present invention are all conventional technologies.

Claims

1. A rotorcraft cockpit canopy capable of withstanding large loads, characterized in that, The rotorcraft cockpit fairing is located at the front of the rotorcraft and includes: a roof (5), a right doorframe inner skin (6), a right doorframe (7), a left doorframe inner skin (8), a left doorframe (9), and a cockpit framework (4). Among them, the cockpit framework is the main load-bearing component of the cockpit fairing, and each component is connected to form a whole by riveting. The roof (5) is located above the cockpit framework (4), adopts a honeycomb sandwich structure, and is riveted to the cockpit framework (4); the right doorframe (7) is located on the right side of the cockpit framework (4) and is riveted to the outer surface of the cockpit framework (4); the right doorframe inner skin (6) is located on the right side of the cockpit framework (4) and is riveted to the inner surface of the cockpit framework (4); the left doorframe (9) is located on the left side of the cockpit framework (4) and is riveted to the outer surface of the cockpit framework (4); the left doorframe inner skin (8) is located on the left side of the cockpit framework (4) and is riveted to the inner surface of the cockpit framework (4); when assembling the cockpit fairing, the cockpit framework (4) uses a tooling for positioning and is respectively riveted to the left doorframe (9) and the right doorframe (7), then the roof (5) is riveted, and finally the left doorframe inner skin (8) and the right doorframe inner skin (6) are riveted; the cockpit framework (4) is composed of multiple aluminum alloy I-beams to form a stable rectangular frame, and an intermediate framework with an I-shaped cross-section is arranged at its central position; the cockpit framework (4) is connected to the main load-bearing structure of the airframe structure.

2. The rotorcraft cockpit fairing capable of withstanding large loads according to claim 1, characterized in that, The cockpit framework (4) adopts an I-shaped structure.

3. The rotorcraft cockpit fairing capable of withstanding large loads according to claim 2, characterized in that, The cockpit framework (4) includes: an upper side framework (11), a right side framework (12), an intermediate framework (13), a left side framework (14), and a lower side framework (17). The upper side framework (11), the right side framework (12), the left side framework (14), and the lower side framework (17) are respectively located at the upper, right, left, and lower parts of the cockpit framework, forming a square frame; the intermediate framework (13) is located at the center line position of the fuselage, dividing the square frame into two parts on the left and right; the square frame is used for installing the windshield.

4. The rotorcraft cockpit fairing capable of withstanding large loads according to claim 3, characterized in that The cockpit framework (4) further includes: a right rear support member (15), an intermediate lower support member (16), and a left rear support member (18). The intermediate lower support member (16) is located below and behind the intermediate framework (13) and is riveted to the intermediate framework, which is used to improve the stability of the intermediate framework (13) and transfer a part of the vertical load. The right rear support member (15) and the left rear support member (18) are respectively located obliquely behind the right side framework (12) and the left side framework (14), and can support the right side framework (12), the left side framework (14), and the lower side framework (17) simultaneously.

5. The rotorcraft cockpit fairing capable of withstanding large loads according to claim 3, characterized in that The intermediate framework (13) extends outward to the upper side framework (11) and the lower side framework (17) respectively; the upper part of the intermediate framework (13) is riveted to the roof (5), and the lower part is hinged to the airframe structure through a joint. The intermediate framework (13) forms a cross-shaped structure with the upper side framework (11) and the lower side framework (17) respectively, and the components are nested and overlapped with each other.

6. The rotorcraft cockpit fairing capable of withstanding large loads according to claim 3, characterized in that The right-side frame (12) and the left-side frame (14) respectively extend downward and outward along the windshield boundary line towards the lower-side frame (17), forming a strong support leg, which is connected to other structures of the fuselage to form another load transfer path; the right-side frame (12) and the left-side frame (14) simultaneously extend a certain distance upward and outward along the upper-side frame (11), and are connected to the ceiling (5) through connecting parts.

7. The rotorcraft cockpit fairing capable of withstanding large loads according to claim 3, wherein the upper-side frame (11) extends rearward along the heading direction; the upper-side frame (11) is provided with a modified I-shaped cross-section, one side of which is connected to the windshield, and the other side is connected to the ceiling (5).

8. The rotorcraft cockpit fairing capable of withstanding large loads according to claim 3, wherein the left-side frame (14) and the left doorframe inner skin (8), the left doorframe (9) form a modified cylindrical cross-section, and the right-side frame (12) and the right doorframe inner skin (6), the right doorframe (7) form a modified cylindrical cross-section. Glass fitting surfaces and cabin door sealing surfaces extend from both sides of the modified cylindrical cross-section.

9. The rotorcraft cockpit fairing capable of withstanding large loads according to claim 3, characterized in that The middle frame (13) is composed of a middle right-side frame (21) and a middle left-side frame (22), the middle right-side frame (21) and the middle left-side frame (22) are respectively located at the positions of two main load-bearing beams of the fuselage, and are hinged to the two main load-bearing beams of the fuselage through joints; the upper parts of the middle right-side frame (21) and the middle left-side frame (22) are riveted to the ceiling (5), and at the same time, an equipment mounting plate is riveted below to form a top box-section structure.

10. A design method for a rotorcraft cockpit cover capable of withstanding large loads according to any one of claims 1 to 9, characterized in that, including: Step 1, determine the large-load transfer path of the fuselage; Step 2, determine the boundary lines and installation requirements of the cabin door and transparent components; Step 3, according to the requirements described in Step 1 and Step 2, determine the intersection positions of the cockpit frame and the fuselage structure; Step 4, according to the upper and lower boundary lines of the cockpit frame and the transparent component in Step 2, determine the upper and lower boundary lines of the cockpit frame; Step 5, according to the installation requirements of the cabin door, determine the cross-section forms of the left doorframe and the right doorframe; Step 6, according to the intersections determined in Step 3 and Step 4, complete the large-load distribution, determine the loads of each component, and according to the characteristics of the transmitted loads and the principle of minimum weight, determine the cross-section shapes of each component of the cockpit frame, and complete the determination of the dimensional parameters; Step 7, according to the assembly process and the component processing process, determine the connection form between the cockpit fairing and the fuselage structure, complete the determination of the process separation surfaces of each component, and complete the design of the cockpit fairing.

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