CN-224225284-U - Switching structure of airplane wing spar and metal joint

Abstract

The utility model discloses an airplane wing spar and metal joint switching structure in the technical field of airplane connecting structures, which comprises a connecting piece, wherein the connecting piece is in a triangle-like arrangement, a wing spar connecting area, a middle beam connecting area and a rear beam connecting area are arranged on the connecting piece, a weight reducing groove is formed between the middle beam connecting area and the rear beam connecting area, weight reducing holes are formed in the connecting piece, and the wing spar joint, the middle beam joint and the rear beam joint are distributed in a triangle shape as a whole. The utility model combines the double metal joints of the middle beam and the rear beam with one spar joint by adopting the form of the switching structure, ensures that the structure has higher rigidity and strength when bearing bending moment, shearing force and torsion while ensuring high-efficiency load transmission, and secondly, the triangular layout of the middle beam, the rear beam and the spar can expand the inner space of the wing and the tail wing, thereby being convenient for the arrangement of a fuel system, a pipeline or a cable and improving the flexibility and the functionality of the inner space.

Inventors

• LI JUN
• XU XINYU
• Che Zhixuan
• GONG JUN
• LI XUN
• LAN BIN
• HE YUANQING
• MA TINGTING
• HAN XU
• JIANG TAO
• CHEN HAO
• MA YAO

Assignees

• 江苏新扬新材料股份有限公司

Dates

Publication Date

20260512

Application Date

20250530

Claims (6)

1. 1. The switching structure of the airplane wing spar and the metal joint comprises a connecting piece (1) and is characterized in that the connecting piece (1) is arranged in a triangle-like shape, a wing spar connecting area (100), a middle beam connecting area (200) and a rear beam connecting area (300) are arranged on the connecting piece (1), a weight reduction groove (400) is formed between the middle beam connecting area (200) and the rear beam connecting area (300), a weight reduction hole (500) is formed in the connecting piece (1), wing spar joints (600) are nested on the outer side of the wing spar connecting area (100), middle beam joints (700) are inserted in the middle beam connecting area (200), rear beam joints (800) are inserted in the rear beam connecting area (300), and the wing spar joints (600), the middle beam joints (700) and the rear beam joints (800) are distributed in a triangle shape integrally.
2. 2. An aircraft spar and metal joint transition structure according to claim 1, wherein the spar connection zone (100) comprises a spar first web (101) and a spar second web (102), the spar first web (101) and the spar second web (102) being arranged in a C-shape, the spar connection zone (100) being arranged in correspondence with the spar joint (600).
3. 3. An aircraft spar and metal joint transition structure according to claim 1, wherein the spar comprises a spar web (601) and a spar cap (602), the spar web (601) is attached to a first spar web (101), the spar cap (602) is attached to a second spar web (102), the joint between the spar cap (602) and the second spar web (102) is thinned, and the total thickness of the joint region is consistent with the joint thickness and the spar joint (600) thickness.
4. 4. An aircraft spar and metal joint transition structure according to claim 3, wherein the spar caps (602) are flush with the ends of the spar second webs (102) with glass cloth gaps and assembly gaps between the webs.
5. 5. An aircraft spar and metal joint transfer structure according to claim 1, wherein the spar connection zone (200) comprises a first spar connection plate (201) and a second spar connection plate (202), the spar joint (700) comprises a spar web (701) and a spar cap (702), and the spar joint (700) is arranged in correspondence with the spar connection zone (200).
6. 6. An aircraft spar and metal joint transfer structure according to claim 1, wherein the back beam connection zone (300) comprises a back beam first connection plate (301) and a back beam second connection plate (302), and the back beam joint (800) is arranged corresponding to the back beam connection zone (300).

Description

Switching structure of airplane wing spar and metal joint Technical Field The utility model relates to the technical field of aircraft connection structures, in particular to an adapter structure of an aircraft wing spar and a metal joint. Background Aircraft wings and tails are important components of an aircraft. The main function of the wing is to generate aerodynamic lift force, so that the flight performance and maneuvering performance of the aircraft in all flight states specified by technical requirements are ensured. The tail fin is positioned behind the wing, and the function of the tail fin is to ensure the pitching stability and the maneuverability of the airplane. The structural forms of aircraft wings and tails are generally divided into beam, monolithic, multi-wall and hybrid types. The wing spar is a longitudinal member in the aircraft airfoil that is subjected primarily to bending moments and shear forces, which are critical to ensuring the strength and stiffness of the wing structure. The bending moment load is borne by the upper edge strip, the lower edge strip and the web plate in a tension and compression mode, and the tangential load is transmitted by the web plate in a shearing mode. Wherein, the bending moment is transmitted to the joint of the frame by the spar cap in the form of couple, and the web plate transmits shearing force to the joint of the frame. In spar designs, the greatest load is placed at the spar joint and the higher the structural strength requirements, the less load is placed from the spar joint toward the tip. Modern aircraft typically employ web-type or monolithic spars, typically having at least two or more spars on the wing structure. The spar is mainly formed by integrally processing metal materials such as aluminum alloy, steel or titanium alloy, so that the spar has good structural performance, but the overall weight, the production cost and the electrochemical corrosion problem of the aircraft are increased. Meanwhile, in some large-sized airplanes with larger loading, more than two wing beams are needed for the wing structure, and the multi-beam structure can bear larger pneumatic load, but easily causes too high safety margin of wing tips, greatly improves the structural weight, increases the manufacturing cost and reduces the internal volumes of wings and tail wings. The double-joint type integral spar has a complex structure, extremely high processing difficulty and inconvenient disassembly, assembly and maintenance. We therefore propose a transition structure for an aircraft spar and a metal joint. Disclosure of utility model Aiming at the defects in the prior art, the utility model provides a switching structure of an airplane wing spar and a metal joint. The airplane wing spar and metal joint switching structure comprises a connecting piece, wherein the connecting piece is arranged like a triangle, a wing spar connecting area, a middle beam connecting area and a rear beam connecting area are arranged on the connecting piece, a weight reducing groove is formed between the middle beam connecting area and the rear beam connecting area, a weight reducing hole is formed in the connecting piece, wing spar joints are nested at the outer side of the wing spar connecting area, middle beam joints are inserted into the middle beam connecting area, rear beam joints are inserted into the rear beam connecting area, and the wing spar joints, the middle beam joints and the rear beam joints are distributed in a triangle integrally. Optionally, the spar connection zone includes a spar first connection plate and a spar second connection plate, the spar first connection plate and the spar second connection plate are arranged in a C shape, and the spar connection zone is arranged corresponding to the spar joint. Optionally, the spar comprises a spar web and a spar cap, the spar web is jointed with a first spar connecting plate, the spar cap is jointed with a second spar connecting plate, the lap joint of the spar cap and the second spar connecting plate is thinned, and the total thickness of the lap joint area is consistent with the joint thickness and the joint thickness of the spar. Optionally, the spar cap is flush with an end of the spar second webs, and a glass cloth gap and an assembly gap are provided between the webs. Optionally, the middle beam connecting region comprises a middle beam first connecting plate and a middle beam second connecting plate, the middle beam joint comprises a middle beam web plate and a middle beam edge strip, and the middle beam joint and the middle beam connecting region are correspondingly arranged. Optionally, the back beam connection area includes back beam first connecting plate and back beam second connecting plate, back beam joint corresponds the setting with back beam connection area. Compared with the prior art, the utility model has the beneficial effects that: 1. The middle beam and rear beam bimetal joint is combined with one