Unmanned helicopter rolling type undercarriage bearing structure and construction method thereof

Abstract

The invention provides an unmanned helicopter rolling type undercarriage bearing structure and a construction method thereof. The unmanned helicopter rolling type undercarriage bearing structure comprises a right buffering supporting column connector (1), a right longitudinal beam (2), a rear bulkhead (3), a front bulkhead (4), a left longitudinal beam (5), a left buffering supporting column connector (6), a left skin (7), a left rocker arm connector (9), a left horizontal plate (11), a bottom skin (12), a right rocker arm connector (13), a right horizontal plate (15), a right skin (16) and an upper floor (17). According to the rolling type undercarriage bearing structure, a plurality of box section type structures are constructed in the space of less than 200mm of the front and rear bulkheads, and the rolling type undercarriage bearing structure is direct in force transmission, small in deformation and high in weight efficiency. The buffer strut joint integrates a buffer strut mounting hole of a rolling undercarriage (10), an extension limiter mounting hole and a full-aircraft mooring mounting hole, and the design of mounting interfaces of multiple structures is realized on one plane.

Description

TECHNICAL FIELD

[0001] The application belongs to the field of aviation structure design, and particularly relates to a roll-pitch landing gear bearing structure of an unmanned helicopter and a construction method thereof. BACKGROUND

[0002] The roll-pitch landing gear is symmetrically distributed on both sides of the fuselage, can effectively increase the transverse span of the landing gear, and meets the stability requirement of the helicopter in parking.

[0003] Compared with the traditional strut type landing gear and the rocker arm type landing gear (pitch type), the roll-pitch landing gear has a more compact space requirement for the fuselage bearing structure, and the designer needs to complete the structure layout in a smaller space to realize load transmission, and also needs to consider other interface design requirements of the unmanned aerial vehicle. SUMMARY

[0004] The application provides a roll-pitch landing gear bearing structure of an unmanned helicopter and a construction method thereof, and mainly aims to construct a roll-pitch landing gear bearing structure in a smaller space, and meet the roll-pitch landing gear load transmission requirement, jack-up requirement and tethering requirement.

[0005] The application provides a roll-pitch landing gear bearing structure of an unmanned helicopter, which comprises a right buffer strut joint 1, a right longitudinal beam 2, a rear partition frame 3, a front partition frame 4, a left longitudinal beam 5, a left buffer strut joint 6, a left skin 7, a left rocker arm joint 9, a left horizontal plate 11, a bottom skin 12, a right rocker arm joint 13, a right horizontal plate 15, a right skin 16 and an upper floor 17.

[0006] The front partition frame 4, the rear partition frame 3, the upper floor 17, the left skin 7, the right skin 16 and the bottom skin 12 form a box-shaped structure and are arranged below the fuselage; the right longitudinal beam 2 and the left longitudinal beam 5 are located in the box-shaped structure and are symmetrically arranged on the left and right sides of the fuselage.

[0007] The left horizontal plate 11 and the right horizontal plate 15 are respectively located between the left skin 7 and the left longitudinal beam 5 and between the right skin 16 and the right longitudinal beam 2.

[0008] The left buffer strut joint 6 is arranged on the left horizontal plate 11, and a buffer strut mounting hole, an elongation limiter mounting hole and a whole-machine tethering mounting hole on the left buffer strut joint 6 extend out of the left skin 7.

[0009] The right buffer strut joint 1 is arranged on the right horizontal plate 15, and a buffer strut mounting hole, an elongation limiter mounting hole and a whole-machine tethering mounting hole on the right buffer strut joint 1 extend out of the right skin 16.

[0010] The left rocker arm joint 9 and the right rocker arm joint 13 are respectively located directly below the left longitudinal beam 5 and the right longitudinal beam 2 and are connected to the left longitudinal beam 5, the right longitudinal beam 2, the front partition frame 4 and the rear partition frame 3 through bolts.

[0011] Optionally, the right longitudinal beam 2, the rear bulkhead 3, the left longitudinal beam 5, the front bulkhead 4, the upper floor 17 and the bottom skin 12 are connected by riveting to form a load-bearing box section structure in the middle of the fuselage;

[0012] The front bulkhead 4, the rear bulkhead 3, the upper floor 17, the left skin 7 and the left horizontal plate 11 form a closed box section on the left side of the fuselage by riveting, and the left buffer strut joint 6 divides the closed box section into front and rear parts;

[0013] The front bulkhead 4, the rear bulkhead 3, the upper floor 17, the right skin 16 and the right horizontal plate 15 form a closed box section on the right side of the fuselage by riveting, and the right buffer strut joint 1 divides the closed box section into front and rear parts.

[0014] Optionally, the left horizontal plate 11, the right horizontal plate 15, the corresponding left skin 7 and the right skin 16 below are provided with a left maintenance access cover 8 and a right maintenance access cover 14.

[0015] Optionally, the right buffer strut joint 1 and the left buffer strut joint 6 are aluminum alloy integral machined parts;

[0016] The buffer strut joint is provided with a tie-down mounting hole at the upper end and two ear pieces at the middle part, and the ear pieces are provided with an elongation limiter mounting hole and a buffer strut mounting hole;

[0017] A limiting boss is arranged on the ear piece on one side of the buffer strut mounting hole, which is used to limit the rotation of the connecting shaft of the landing gear buffer strut and plays a role of anti-loosening;

[0018] A bushing with internal and external threads is mounted in the tie-down mounting hole, the end of the bushing has a certain profile, the external thread of the bushing is smeared with anaerobic adhesive and then screwed into the tie-down mounting hole, the end is smeared with a sealant, and the end face of the bushing protrudes from the buffer strut joint by more than 5mm after installation.

[0019] Optionally, two openings larger than 80mm are arranged on the left and right sides of the front bulkhead 4 near the longitudinal beam, which are used for the installation of the left swing arm joint 9 and the right swing arm joint 13.

[0020] Optionally, the left swing arm joint 9 and the right swing arm joint 13 are titanium alloy machined parts, which include a connecting beam in a carrying pole structure, one side of the connecting beam is connected with the front bulkhead 4, the longitudinal beam and the rear bulkhead 3 through bolts, and the other side is provided with two ring structures at both ends, which are used for passing through the connecting shaft of the lateral swing landing gear swing arm;

[0021] A limiting boss is arranged at the position of one of the ring structures, which is used to limit the rotation of the connecting shaft of the lateral swing landing gear swing arm;

[0022] The bottom of the ring structure is provided with a jack support joint.

[0023] Optionally, the right longitudinal beam 2 and the left longitudinal beam 5 are made of machined aluminum alloy parts. The front end is a cross structure that integrates the partition frame, longitudinal beam, upper floor, horizontal plate, and skin connection structure, which is used to transmit the vertical load, lateral load and longitudinal load transmitted from the rocker arm joint to all directions.

[0024] A second aspect of the present invention provides a method for constructing a roll-type landing gear support structure for an unmanned helicopter as described in any one of the first aspects, comprising:

[0025] Step 1: Based on the roll-type landing gear configuration, determine the intersection point between the landing gear and the fuselage structure:

[0026] The roll-type landing gear includes a rocker arm assembly and a buffer strut assembly, and has at least three intersection points with the fuselage structure: rocker arm assembly intersection points A and B, and buffer strut assembly intersection point C.

[0027] Step 2, Load Analysis of Rolling Landing Gear

[0028] Determine the load type and direction at the intersection of the roll landing gear and the fuselage. The loads at the intersection of the rocker arm assembly are FAX, FAy, FAz, FBx, FBy, FBz, and the loads at the intersection of the buffer strut assembly are FCy, FCz.

[0029] Step 3: Based on the intersection points determined in Step 1 and the load types determined in Step 2, proceed with the arrangement of the load-bearing structure:

[0030] Based on the intersection point C of the buffer strut assembly and the loads at the intersection point being FCy and FCz, transverse planes S2 and S4 are arranged at this location to transfer the loads FCy and FCz. The rocker arm assembly load is divided into two application points A and B, and transverse planes S1 and S3 are arranged at these application points respectively to transfer FAy and FBy. A longitudinal plane L1 is arranged at the two application points A and B of the rocker arm assembly load, and a longitudinal plane L2 is arranged at a symmetrical position to transfer FAx and FBx. Two horizontal planes P1, P2, and P3 are arranged in the vertical direction to transfer the in-plane loads FAx, FAy, FBx, and FBy of the landing gear.

[0031] Step 4: Based on the load-bearing structure layout determined in Step 3, complete the load-bearing structure design scheme.

[0032] Step 5: Set buffer support mounting holes, elongation limiter mounting holes, and full-machine tie-down mounting holes on the buffer support joint;

[0033] Step 6: Install the jack support joint on the rocker arm joint;

[0034] Step 7: Based on the roll landing gear load data and jacking and mooring loads determined in Step 2, determine the dimensions of the fuselage load-bearing structure;

[0035] Step 8: Based on the dimensions, environmental adaptability requirements, and assembly process requirements determined in Step 7, complete the detailed design of the load-bearing structure.

[0036] In summary, the beneficial effects of the present invention are as follows:

[0037] (1) A support structure for a roll-type landing gear was constructed, which integrates a mooring interface, an extension limiter interface and a jack joint while satisfying the load transfer of the landing gear. It has high space utilization and high structural efficiency.

[0038] (2) The support structure has direct load transfer, small deformation, and high weight efficiency;

[0039] (3) The proposed design method for the load-bearing structure of the roll landing gear is applicable to the construction of the installation structure of multiple models of roll landing gear;

[0040] (4) This type of load-bearing structure has been applied to a certain type of unmanned helicopter with good results. Attached Figure Description

[0041] Figure 1 Schematic diagram of a roll-type landing gear installation;

[0042] Figure 2 3D schematic diagram of the support structure for a roll-type landing gear;

[0043] Figure 3 3D schematic diagram of the buffer support joint;

[0044] Figure 4 Schematic diagram of buffer support connection;

[0045] Figure 5 Schematic diagram of tethering interface bushing installation;

[0046] Figure 6a Rocker arm installation diagram Figure 1 ;

[0047] Figure 6b Rocker arm installation diagram Figure 2 ;

[0048] Figure 7 3D schematic diagram of the cross-shaped longitudinal beam structure;

[0049] Figure 8 Schematic diagram of the load on a roll-type landing gear;

[0050] Figure 9 Schematic diagram of the load-bearing structure of the roll-type landing gear;

[0051] Explanation of reference numerals in the attached figures:

[0052] 100. Roller Landing Gear 200. Support Structure 1. Right Buffer Strut Joint 2. Right Longitudinal Beam 3. Rear Bulkhead 4. Front Bulkhead 5. Left Longitudinal Beam 6. Left Buffer Strut Joint 7. Left Skin 8. Left Maintenance Port Cover 9. Left Rocker Arm Joint 11. Left Horizontal Plate 12. Bottom Skin 13. Right Rocker Arm Joint 14. Right Maintenance Port Cover 15. Right Horizontal Plate 16. Right Skin 17. Upper Floor 18. Shim 19. Movable Bushing 20. Buffer Strut 21. Fixed Bushing 22. Connecting Shaft 23. Slotted Nut 24. Tie Bushing 25. Rocker Arm Connecting Shaft 26. Adjusting Shim 27. Tie Mounting Hole 28. Extension Limiter Mounting Hole 29. Buffer Strut Mounting Hole 30. Limiting Boss 31. Jack Support Joint. Detailed Implementation

[0053] The following explanation, in conjunction with the accompanying drawings, details the roll-type landing gear support structure and its construction method for unmanned helicopters provided by this invention.

[0054] like Figures 1-9 As shown, the present invention provides a roll-type landing gear support structure for unmanned helicopters and its construction method.

[0055] The unmanned helicopter roll-type landing gear support structure of the present invention is as follows: Figure 1 As shown, it mainly consists of two parts: a roll landing gear 100 and a load-bearing structure 200. The roll landing gear 100 is hinged to both sides of the load-bearing structure 200 via rocker arms and buffer struts.

[0056] The load-bearing structure of the roll-type landing gear is 200. Figure 2 As shown, it mainly consists of the right buffer support joint 1, right longitudinal beam 2, rear partition 3, front partition 4, left longitudinal beam 5, left buffer support joint 6, left skin 7, left maintenance cover 8, left rocker arm joint 9, left horizontal plate 11, bottom skin 12, right rocker arm joint 13, right maintenance cover 14, right horizontal plate 15, right skin 16 and upper floor 17.

[0057] The right longitudinal beam 2 and left longitudinal beam 5 are symmetrically arranged on the left and right sides of the fuselage. A front bulkhead 4 and a rear bulkhead 3 are respectively arranged at the front and rear of the longitudinal beams. The upper part of the right longitudinal beam 2, rear bulkhead 3, left longitudinal beam 5, and front bulkhead 4 are covered by an upper floor 17, and the lower part is covered by a bottom skin 12. The right longitudinal beam 2, rear bulkhead 3, left longitudinal beam 5, front bulkhead 4, upper floor 17, and bottom skin 12 are connected by riveting, forming a load-bearing box-section structure in the middle of the fuselage. The left and right sides of the front bulkhead 4, rear bulkhead 3, and upper floor 17 are covered by left skin 7 and right skin 16. The left horizontal plate 11 and right horizontal plate 15 are located on the left skin 7 and left longitudinal beam 5, respectively. Between the skin 16 and the right longitudinal beam 2; the front bulkhead 4, rear bulkhead 3, upper floor 17, left skin 7, and left horizontal plate 11 are riveted to the left side of the fuselage to form a closed box section, and the left buffer support joint 6 divides this closed box section into front and rear parts; the front bulkhead 4, rear bulkhead 3, upper floor 17, right skin 16, and right horizontal plate 15 are riveted to the right side of the fuselage to form a closed box section, and the right buffer support joint 1 divides the closed box section into front and rear parts; the left rocker arm joint 9 and the right rocker arm joint 13 are located directly below the left longitudinal beam 5 and the right longitudinal beam 2, respectively, and are connected to the left longitudinal beam 5, the right longitudinal beam 2, the front bulkhead 4, and the rear bulkhead 3 by bolts. In order to facilitate the operation of the rocker arm joint connection bolts, the left maintenance cover 8 and the right maintenance cover 14 are provided below the left horizontal plate 11 and the right horizontal plate 15. The roll-type landing gear load-bearing structure is designed in the form of multiple box segments, which can transfer the load between the box segments. It has good overall rigidity and forms multiple force transmission paths. Even if one component is damaged, the load can still be transferred from other paths, which can improve safety.

[0058] The right buffer support joint 1 and the left buffer support joint 6 are integral machined aluminum alloy parts, such as... Figure 3 As shown, it integrates the landing gear 100 buffer strut mounting hole 28, the extension limiter mounting hole 29, and the aircraft mooring mounting hole 27. The load of the landing gear buffer strut, the load of the extension limiter when the aircraft is stopped, and the aircraft mooring load can all be transferred through this structure, resulting in high load transfer efficiency. Two bushings are installed inside the buffer strut mounting hole, such as... Figure 4As shown, one is a fixed bushing and the other is a movable bushing. When the slotted nut is tightened, the movable bushing moves inward to press against the buffer strut, ensuring that the buffer strut is clamped. A limiting boss 30 is designed on the lug on one side of the buffer strut mounting hole to limit the rotation of the landing gear buffer strut connecting shaft and prevent loosening. A bushing with both internal and external threads is installed inside the whole-aircraft mooring interface. The end of this bushing has a certain profile, and both the inner and outer sides of the bushing are threaded. It is usually made of high-strength structural steel. After applying anaerobic adhesive, it is screwed into the buffer strut joint. The end is then coated with sealant to protect the buffer strut joint from wear by the mooring joint. Applying anaerobic adhesive and sealant provides good corrosion protection. After installation, the end face of this bushing must protrude more than 5mm from the buffer strut joint for easy clamping. Two shoulder bushings are installed on both sides of the extension limiter mounting hole, usually made of stainless steel, to prevent wear on the mounting hole.

[0059] On both sides of the front bulkhead 4, near the longitudinal beam, there are two openings larger than 80mm, mainly for the installation of the left rocker arm joint 9 and the right rocker arm joint 13.

[0060] The left rocker arm joint 9 and the right rocker arm joint 13 are machined titanium alloy parts, including: a connecting beam with a flat pole structure, one side of the connecting beam is connected to the front bulkhead 4, the longitudinal beam and the rear bulkhead 3 by bolts, and the other side has two ring structures at both ends for passing through the connecting shaft of the rocker arm of the roll-over landing gear.

[0061] A limit boss is provided at a ring structure location to limit the rotation of the connecting shaft of the rocker arm of the roll-type landing gear;

[0062] The bottom of the ring structure is equipped with a jack support joint 31.

[0063] The left rocker arm connector 9 and the right rocker arm connector 13 are machined titanium alloy parts, such as Figure 6a and Figure 6b As shown, similar to a carrying pole structure, each end of the carrying pole has a connector with a Φ45mm through hole for the rocker arm connecting shaft of the roll landing gear to pass through. The middle of the carrying pole is an I-beam structure, which can improve the rigidity of the connector. A limiting boss is designed on the front end of the connector to restrict the rotation of the rocker arm connecting shaft. The front end of the connector is connected to the front bulkhead 4 by four bolts, the rear end is connected to the rear bulkhead 3 by four bolts, and the middle is connected to the longitudinal beam by four bolts. The load of the roll landing gear is directly transmitted to the frame beam structure, resulting in direct force transmission. At the same time, the front ends of the left rocker arm connector 9 and the right rocker arm connector 13 are respectively designed with jack support connectors. The jack connectors are integrated with the rocker arm connectors, resulting in direct force transmission and light weight.

[0064] The right longitudinal beam 2 and the left longitudinal beam 5 are made of machined aluminum alloy parts, such as Figure 5As shown, the front end is a cross-shaped structure that integrates the frame, longitudinal beams, floor, and horizontal plate connection structure. It can transmit the vertical, lateral, and longitudinal loads from the rocker arm joint in all directions, resulting in high joint weight efficiency.

[0065] Installation and adjustment method of load-bearing structure: (1) Position the buffer strut joint and rocker arm joint using the roll-type landing gear tooling dummy; (2) With the buffer strut joint as the center, complete the riveting of other load-bearing structures to the buffer strut joint; (3) According to the actual value of the gap between the rocker arm joint and the skin, add an adjustment shim between the rocker arm joint and the skin (the shim thickness is between 0.5-1.2mm), prepare the rocker arm joint bolt mounting holes, and use bolts to complete the installation of the rocker arm joint.

[0066] The present invention also provides a method for constructing a roll-type landing gear load-bearing structure, comprising the following steps:

[0067] Step 1: Based on the roll-type landing gear configuration, determine the intersection point between the landing gear and the structure:

[0068] The roll-type landing gear includes a rocker arm assembly and a buffer strut assembly, and has at least three intersection points with the fuselage structure: rocker arm assembly intersection points A and B, and buffer strut assembly intersection point C.

[0069] Step 2, Load Analysis of Rolling Landing Gear

[0070] Taking the roll landing gear as the research object, the load type and direction at the intersection of the roll landing gear and the fuselage are determined. The main loads at the intersection of the rocker arm assembly are FAX, FAy, FAz, FBx, FBy, FBz, and the loads at the intersection of the buffer strut assembly are FCy and FCz.

[0071] Step 3: Based on the intersection points determined in Step 1 and the load types determined in Step 2, proceed with the arrangement of the load-bearing structure:

[0072] Based on the intersection point C of the buffer strut assembly and the loads at the intersection point being FCy and FCz, transverse planes S2 and S4 are arranged at this location to transfer the loads FCy and FCz. The rocker arm assembly load is divided into two application points A and B, and transverse planes S1 and S3 are arranged at these application points to transfer FAy and FBy. A longitudinal plane L1 is arranged at the two application points A and B of the rocker arm assembly load, and a longitudinal plane L2 is arranged at a symmetrical location to transfer FAx and FBx. Two horizontal planes P1, P2, and P3 are arranged in the vertical direction to transfer the in-plane loads FAx, FAy, FBx, and FBy of the landing gear. All of the above planes are included within the theoretical outer surface of the helicopter and are covered by skin. Multiple planes, floor, and skin are combined to form multiple box-section structures, which can be used to transfer the torque generated by loads in various directions.

[0073] Step 4: Based on the load-bearing structure layout determined in Step 3, complete the load-bearing structure design scheme.

[0074] Step 5: Complete the design and connection of the buffer strut joint and rocker arm joint on the fuselage according to the interface form of the roll-type landing gear;

[0075] Step 6: Complete the design of the lifting and mooring interfaces according to the requirements of the jack lifting and mooring interfaces;

[0076] Step 7: Based on the roll landing gear load data and jacking and mooring loads determined in Step 2, determine the dimensional definition of the fuselage load-bearing structure;

[0077] Step 8: Based on the dimensional definitions, environmental adaptability requirements, and assembly process requirements determined in Step 7, complete the detailed design of the load-bearing structure.

[0078] In this invention, the roll-type landing gear load-bearing structure constructs multiple box-section structures within a space of less than 200mm between the front and rear bulkheads. This results in direct force transmission, minimal deformation, and high weight efficiency. The buffer strut joint integrates the roll-type landing gear buffer strut mounting holes, elongation limiter mounting holes, and aircraft-wide mooring mounting holes, achieving a multi-structure mounting interface design on a single plane. A limiting boss is designed on the side of the buffer strut joint lug to prevent the buffer strut mounting bolts from rotating, forming a single kinematic pair. Two bushings are installed in the buffer strut mounting hole, one fixed and one movable. When the slotted nut is tightened, the movable bushing moves inward, pressing against the buffer strut to ensure it is clamped. A bushing with both internal and external threads is installed inside the mooring mounting interface. This bushing has a certain profile at its end and protrudes more than 5mm from the buffer strut joint after installation, preventing wear on the buffer strut joint. The rocker arm joint adopts a flat-pole structure, with a connector at each end featuring a Φ45mm through hole. A limiting boss is designed on the front face, integrating a jack connector. The longitudinal beams have a cross-shaped structure, allowing connection to structures in multiple directions (front, rear, left, right, up, and down), resulting in high integration. An adjusting shim is designed between the rocker arm joint and the skin structure, with a thickness between 0.5 and 1.2 mm, ensuring adjustable longitudinal, lateral, and vertical positions for both the buffer support joint and the rocker arm joint.

Claims

1. A roll-type landing gear support structure for an unmanned helicopter, characterized in that, include: Right buffer strut joint (1), right longitudinal beam (2), rear bulkhead (3), front bulkhead (4), left longitudinal beam (5), left buffer strut joint (6), left skin (7), left rocker arm joint (9), left horizontal plate (11), bottom skin (12), right rocker arm joint (13), right horizontal plate (15), right skin (16) and upper floor (17); The front bulkhead (4), rear bulkhead (3), upper floor (17), left skin (7), right skin (16) and bottom skin (12) form a box-shaped structure and are located under the fuselage; the right longitudinal beam (2) and left longitudinal beam (5) are located inside the box section structure and are symmetrically arranged on the left and right sides of the fuselage. The left horizontal plate (11) and the right horizontal plate (15) are located between the left skin (7) and the left longitudinal beam (5), and between the right skin (16) and the right longitudinal beam (2), respectively. The left buffer strut joint (6) is set on the left horizontal plate (11), and the buffer strut mounting hole, elongation limiter mounting hole and whole machine tie-down mounting hole on the left buffer strut joint (6) extend out of the left skin (7); The right buffer strut joint (1) is set on the right horizontal plate (15), and the buffer strut mounting hole, elongation limiter mounting hole and whole machine tie-down mounting hole on the right buffer strut joint (1) extend out of the right skin (16); The left rocker arm joint (9) and the right rocker arm joint (13) are located directly below the left longitudinal beam (5) and the right longitudinal beam (2), respectively, and are connected to the left longitudinal beam (5), the right longitudinal beam (2), the front partition (4), and the rear partition (3) respectively by bolts.

2. The unmanned helicopter roll-type landing gear support structure according to claim 1, characterized in that, The right longitudinal beam (2), rear bulkhead (3), left longitudinal beam (5), front bulkhead (4), upper floor (17) and bottom skin (12) are connected by riveting to form a load-bearing box section structure in the middle of the fuselage; The front bulkhead (4), rear bulkhead (3), upper floor (17), left skin (7) and left horizontal plate (11) are riveted to the left side of the fuselage to form a closed box section, and the left buffer support joint (6) divides the closed box section into front and rear parts; The front bulkhead (4), rear bulkhead (3), upper floor (17), right skin (16) and right horizontal plate (15) are riveted to the right side of the fuselage to form a closed box section. The right buffer support joint (1) divides the closed box section into front and rear parts.

3. The unmanned helicopter roll-type landing gear support structure according to claim 1, characterized in that, Left maintenance cover (8) and right maintenance cover (14) are provided on the left skin (7) and right skin (16) below the left horizontal plate (11) and right horizontal plate (15).

4. The unmanned helicopter roll-type landing gear support structure according to claim 1, characterized in that, The right buffer support joint (1) and the left buffer support joint (6) are integral machined aluminum alloy parts; The upper end of the buffer support joint is provided with a mooring mounting hole, and the middle part is provided with two lugs. The lugs are provided with elongation limiter mounting holes and buffer support mounting holes. A limiting boss is provided on the lug on one side of the buffer strut mounting hole to limit the rotation of the connecting shaft of the landing gear buffer strut and play a role in preventing loosening. A bushing with both internal and external threads is installed inside the mooring mounting hole. The end of the bushing has a certain profile. Anaerobic adhesive is applied to the outer thread of the bushing before it is screwed into the mooring mounting hole. Sealant is applied to the end. The rear end face of the bushing protrudes more than 5mm from the buffer support joint.

5. The unmanned helicopter roll-type landing gear support structure according to claim 1, characterized in that, On the left and right sides of the front partition (4), near the longitudinal beam, there are two openings larger than 80mm, which are used for the installation of the left rocker arm joint (9) and the right rocker arm joint (13).

6. The unmanned helicopter roll-type landing gear support structure according to claim 1, characterized in that, The left rocker arm joint (9) and the right rocker arm joint (13) are machined titanium alloy parts, including: a connecting beam with a flat pole structure, one side of the connecting beam is connected to the front bulkhead (4), the longitudinal beam and the rear bulkhead (3) by bolts, and the other side has two ring structures at both ends for passing through the connecting shaft of the rocker arm of the roll-over landing gear; A limit boss is provided at a ring structure location to limit the rotation of the connecting shaft of the rocker arm of the roll-type landing gear; The bottom of the ring structure is equipped with a jack support joint.

7. The unmanned helicopter roll-type landing gear support structure according to claim 1, characterized in that, The right longitudinal beam (2) and the left longitudinal beam (5) are made of aluminum alloy machined parts. The front end is a cross structure that integrates the partition frame, longitudinal beam, upper floor, horizontal plate and skin connection structure, which is used to transmit the vertical load, lateral load and longitudinal load transmitted from the rocker arm joint to all directions.

8. A method for constructing a roll-type landing gear support structure for an unmanned helicopter as described in any one of claims 1-7, comprising: Step 1: Based on the roll-type landing gear configuration, determine the intersection point between the landing gear and the fuselage structure: The roll-type landing gear includes a rocker arm assembly and a buffer strut assembly, and has at least three intersection points with the fuselage structure: rocker arm assembly intersection points A and B, and buffer strut assembly intersection point C. Step 2, Load Analysis of Rolling Landing Gear Determine the load type and direction at the intersection of the roll landing gear and the fuselage. The loads at the intersection of the rocker arm assembly are FAX, FAy, FAz, FBx, FBy, FBz, and the loads at the intersection of the buffer strut assembly are Fcy and Fcz. Step 3: Based on the intersection points determined in Step 1 and the load types determined in Step 2, proceed with the arrangement of the load-bearing structure: Based on the intersection point C of the buffer strut assembly and the loads at that intersection point being Fcy and Fcz, transverse planes S2 and S4 are arranged at this location to transfer the loads Fcy and Fcz. The rocker arm assembly load is divided into two application points A and B, and transverse planes S1 and S3 are arranged at these application points to transfer FAy and FBy. A longitudinal plane L1 is arranged at the two application points A and B of the rocker arm assembly load, and a longitudinal plane L2 is arranged at a symmetrical location to transfer FAx and FBx. Two horizontal planes P1, P2, and P3 are arranged in the vertical direction to transfer the in-plane loads FAx, FAy, FBx, and FBy of the landing gear. Step 4: Based on the load-bearing structure layout determined in Step 3, complete the load-bearing structure design scheme. Step 5: Set buffer support mounting holes, elongation limiter mounting holes, and full-machine tie-down mounting holes on the buffer support joint; Step 6: Install the jack support joint on the rocker arm joint; Step 7: Determine the dimensions of the fuselage load-bearing structure based on the roll landing gear load data and jacking and mooring loads determined in Step 2. Step 8: Based on the dimensions, environmental adaptability requirements, and assembly process requirements determined in Step 7, complete the detailed design of the load-bearing structure.

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