A fixed-wing aircraft wing-body junction structure

Abstract

The application provides a fixed-wing aircraft wing-body butt joint structure, the bottom end front side of a central wing is symmetrically fixed with a first wing support and a third wing support, the bottom end rear side of the central wing is symmetrically fixed with a second wing support and a fourth wing support; further comprising a first fuselage joint and a second fuselage joint fixed on the top of a first side fuselage framework, the first fuselage joint and the second fuselage joint are connected through bolt fixing respectively with the first wing support and the second wing support; further comprising a third fuselage joint and a fourth fuselage joint fixed on the top of a second side fuselage framework, the third fuselage joint and the fourth fuselage joint are connected through bolt fixing respectively with the third wing support and the fourth wing support. The butt joint tool can realize the precise connection of the wing and the fuselage, improve the precision during butt joint, and reduce the damage of assembly stress concentration to the aircraft structure.

Description

Technical Field

[0001] This invention relates to the field of aviation equipment manufacturing, and in particular to a wing-body docking structure for fixed-wing aircraft. Background Technology

[0002] Wing-body docking is a crucial step in the assembly of major aircraft components. The attitude adjustment and alignment during docking play a decisive role in the overall assembly quality and efficiency of the aircraft. Furthermore, ensuring the coordination and interchangeability of the wing-body docking assembly is essential to guaranteeing the overall assembly quality of the aircraft. The precision of the wing-body docking has a significant impact on the safety, stability, and reliability of the aircraft.

[0003] The existing wing-body docking mainly uses a large number of tooling jigs and instruments such as horizontal theodolites to assist in wing-body assembly. This docking process has low precision and poor efficiency, and is prone to assembly inconsistencies. Summary of the Invention

[0004] The purpose of this invention is to overcome the above-mentioned shortcomings and provide a wing-body docking structure for fixed-wing aircraft. This docking structure can achieve precise connection between the wing and the fuselage, improve the accuracy during docking, reduce the damage to the airframe structure caused by assembly stress concentration, achieve stress-free installation, ensure the coordination and interchangeability of wing-body docking assembly, and meet the needs of repeated and rapid disassembly and installation of the wing and fuselage.

[0005] To achieve the above-mentioned technical features, the present invention aims to provide a fixed-wing aircraft wing-body docking structure, comprising a central wing, wherein a first wing support and a third wing support are symmetrically fixed to the front side of the bottom end of the central wing, and a second wing support and a fourth wing support are symmetrically fixed to the rear side of the bottom end of the central wing. It also includes a first fuselage joint and a second fuselage joint fixed to the top of the first fuselage frame, and the first fuselage joint and the second fuselage joint are respectively fixedly connected to the first wing support and the second wing support by bolts; It also includes a third fuselage joint and a fourth fuselage joint fixed to the top of the second fuselage frame, which are respectively fixed to the third wing support and the fourth wing support by bolts.

[0006] Preferably, the first wing support and the second wing support are located on the same side and are arranged symmetrically. The third and fourth wing supports are located on the same side and are arranged symmetrically.

[0007] Preferably, the first side fuselage frame and the second side fuselage frame are fixed to the top of the fuselage.

[0008] Preferably, a first wing bushing hole is machined on the first wing support, and a first wing bushing is installed inside the first wing bushing hole; The second wing support is machined with a second wing bushing hole, and the second wing bushing is installed inside the second wing bushing hole; The third wing support is machined with a third wing bushing hole, and the third wing bushing is installed inside the third wing bushing hole; The fourth wing support has a fourth wing bushing hole machined on it, and the fourth wing bushing is installed inside the fourth wing bushing hole.

[0009] Preferably, a first body bushing hole is machined on the first body joint, and a first body bushing is installed inside the first body bushing hole; The second fuselage joint is machined with a second fuselage bushing hole, and a second fuselage bushing is installed inside the second fuselage bushing hole; The third fuselage joint is machined with a third fuselage bushing hole, and a third fuselage bushing is installed inside the third fuselage bushing hole; The fourth fuselage joint has a fourth fuselage bushing hole, and the fourth fuselage bushing is installed inside the fourth fuselage bushing hole.

[0010] Preferably, the first wing bushing hole, the second wing bushing hole, the third wing bushing hole, the fourth wing bushing hole, the first fuselage bushing hole, the second fuselage bushing hole, the third fuselage bushing hole, and the fourth fuselage bushing hole are parallel to the flight direction of the aircraft.

[0011] Preferably, the first wing bushing hole and the first wing bushing form an interference fit; The second wing bushing hole and the second wing bushing form an interference fit; The third wing bushing hole and the third wing bushing form an interference fit; The fourth wing bushing hole and the fourth wing bushing form an interference fit.

[0012] Preferably, the first fuselage bushing hole and the first fuselage bushing form an interference fit; The second fuselage bushing hole and the second fuselage bushing form an interference fit; The third fuselage bushing hole and the third fuselage bushing form an interference fit; The fourth fuselage bushing hole and the fourth fuselage bushing form an interference fit.

[0013] Preferably, the first fuselage connector, the second fuselage connector, the third fuselage connector and the fourth fuselage connector each adopt a double-fork lug connector structure.

[0014] The present invention has the following beneficial effects: 1. The docking fixture of the present invention can achieve precise connection between the wing and the fuselage, improve the accuracy during docking, reduce the damage to the airframe structure caused by assembly stress concentration, achieve the purpose of stress-free installation, ensure the coordination and interchangeability of wing-fuselage docking assembly, and meet the needs of repeated rapid disassembly and rapid installation of the wing and fuselage.

[0015] 2. By using an interference fit between the bushing and the inner diameter of the mounting hole, the reliability of the bushing installation and fixing is ensured. At the same time, the bushing enhances the structural strength of the mounting hole and ensures the subsequent installation accuracy. Attached Figure Description

[0016] The present invention will be further described below with reference to the accompanying drawings and embodiments.

[0017] Figure 1 This is a first-view 3D diagram of the overall structure of the present invention.

[0018] Figure 2 For the present invention Figure 1 Enlarged view of a section of the central wing.

[0019] Figure 3 This is a structural diagram of the docking structure between the first wing support and the first fuselage joint of the present invention.

[0020] Figure 4 This is a second-view three-dimensional diagram of the overall structure of the present invention.

[0021] Figure 5 This is a three-dimensional view of the four fuselage joints on the body of the present invention.

[0022] Figure 6 This is a three-dimensional view of the four wing supports on the central wing of the present invention.

[0023] Figure 7 For the present invention Figure 6 Enlarged view of the four wing supports on the center wing.

[0024] In the diagram: First wing support 1, Second wing support 2, Third wing support 3, Fourth wing support 4, Center wing 5, Side wing 6, Second side fuselage frame 7, Third fuselage joint 8, Fourth fuselage joint 9, First side fuselage frame 10, First fuselage joint 11, Second fuselage joint 12; First wing bushing 101, first wing bushing hole 102; Second wing bushing 201, second wing bushing hole 202; Third wing bushing 301, third wing bushing hole 302; Fourth wing bushing 401, fourth wing bushing hole 402; Third fuselage bushing 801, third fuselage bushing hole 802; Fourth fuselage bushing 901, fourth fuselage bushing hole 902; First fuselage bushing 1101, first fuselage bushing hole 1102; Second fuselage bushing 1201, second fuselage bushing hole 1202. Detailed Implementation

[0025] The embodiments of the present invention will be further described below with reference to the accompanying drawings.

[0026] See Figure 1-7 A fixed-wing aircraft wing-fuselage docking structure is characterized by comprising a central wing 5, wherein a first wing support 1 and a third wing support 3 are symmetrically fixed to the front side of the bottom end of the central wing 5, and a second wing support 2 and a fourth wing support 4 are symmetrically fixed to the rear side of the bottom end of the central wing 5; it also includes a first fuselage joint 11 and a second fuselage joint 12 fixed to the top of a first side fuselage frame 10, the first fuselage joint 11 and the second fuselage joint 12 being bolted to the first wing support 1 and the second wing support 2 respectively; and a third fuselage joint 8 and a fourth fuselage joint 9 fixed to the top of a second side fuselage frame 7, the third fuselage joint 8 and the fourth fuselage joint 9 being bolted to the third wing support 3 and the fourth wing support 4 respectively. This docking fixture enables precise connection between the wing and the fuselage, improves the accuracy during docking, reduces stress concentration during assembly and damage to the airframe structure, achieves stress-free installation, ensures the coordination and interchangeability of the wing-fuselage docking assembly, and meets the needs of repeated rapid disassembly and assembly of the wing and fuselage.

[0027] Furthermore, the first wing support 1 and the second wing support 2 are located on the same side and arranged symmetrically; the third wing support 3 and the fourth wing support 4 are located on the same side and arranged symmetrically. This arrangement ensures reliable connection between the subsequent wing supports and the fuselage joint.

[0028] Furthermore, the first side fuselage frame 10 and the second side fuselage frame 7 are fixed to the top of the fuselage.

[0029] Furthermore, a first wing bushing hole 102 is machined on the first wing support 1, and a first wing bushing 101 is installed inside the first wing bushing hole 102; by using the first wing bushing 101, the structural strength of the hole is enhanced and its service life is extended.

[0030] The second wing support 2 has a second wing bushing hole 202 machined on it, and a second wing bushing 201 is installed inside the second wing bushing hole 202; by using the second wing bushing 201, the structural strength of the hole is enhanced and its service life is extended.

[0031] The third wing support 3 has a third wing bushing hole 302 machined on it, and a third wing bushing 301 is installed inside the third wing bushing hole 302; by using the third wing bushing 301, the structural strength of the hole is enhanced and its service life is extended.

[0032] The fourth wing support 4 has a fourth wing bushing hole 402 machined on its upper surface, and a fourth wing bushing 401 is installed inside the fourth wing bushing hole 402. The use of the fourth wing bushing 401 enhances the structural strength of the hole and extends its service life.

[0033] Furthermore, a first body bushing hole 1102 is machined on the first body connector 11, and a first body bushing 1101 is installed inside the first body bushing hole 1102; by using the first body bushing 1101, the structural strength of the hole is enhanced and its service life is extended.

[0034] The second body connector 12 has a second body bushing hole 1202 machined on it, and a second body bushing 1201 is installed inside the second body bushing hole 1202; by using the second body bushing 1201, the structural strength of the hole is enhanced and its service life is extended.

[0035] The third body connector 8 has a third body bushing hole 802 machined on it, and a third body bushing 801 is installed inside the third body bushing hole 802; the third body bushing 801 enhances the structural strength of the hole and extends its service life.

[0036] The fourth body connector 9 has a fourth body bushing hole 902 machined on it, and a fourth body bushing 901 is installed inside the fourth body bushing hole 902. The fourth body bushing 901 enhances the structural strength of the hole and extends its service life.

[0037] Furthermore, the first wing bushing hole 102, the second wing bushing hole 202, the third wing bushing hole 302, the fourth wing bushing hole 402, the first fuselage bushing hole 1102, the second fuselage bushing hole 1202, the third fuselage bushing hole 802, and the fourth fuselage bushing hole 902 are all parallel to the flight direction of the aircraft.

[0038] Furthermore, the first wing bushing hole 102 and the first wing bushing 101 form an interference fit; the second wing bushing hole 202 and the second wing bushing 201 form an interference fit; the third wing bushing hole 302 and the third wing bushing 301 form an interference fit; and the fourth wing bushing hole 402 and the fourth wing bushing 401 form an interference fit. These interference fits ensure coaxiality and installation accuracy.

[0039] Furthermore, the first fuselage bushing hole 1102 and the first fuselage bushing 1101 form an interference fit; the second fuselage bushing hole 1202 and the second fuselage bushing 1201 form an interference fit; the third fuselage bushing hole 802 and the third fuselage bushing 801 form an interference fit; and the fourth fuselage bushing hole 902 and the fourth fuselage bushing 901 form an interference fit. These interference fits ensure coaxiality and installation accuracy.

[0040] Furthermore, the first fuselage connector 11, the second fuselage connector 12, the third fuselage connector 8, and the fourth fuselage connector 9 all adopt a double-fork lug connector structure. The double-fork lug connector structure ensures reliable docking with the wing support.

[0041] Example 2: A method for wing-body docking of a fixed-wing aircraft, the docking method employing the aforementioned wing-body docking structure, includes the following steps: Step 1: Connect the first wing support 1, the third wing support 3, the second wing support 2 and the fourth wing support 4 to the center wing 5 first, leaving installation slack in the mounting holes that mate with the fuselage; Step 2: Use a crane to lift the assembled center wing 5, and connect and fix the first wing support 1, the second wing support 2 and the third wing support 3 to the first fuselage joint 11, the second fuselage joint 12 and the third fuselage joint 8 with process bolts. Use a reaming tool to enlarge the diameter of the mounting holes at the location of the fourth wing support 4 and the fourth fuselage joint 9 to be smaller than the outer diameter of the bushing, and then use process bolts to connect the fourth wing support 4 and the fourth fuselage joint 9. Step 3: Following the steps in Step 2, enlarge the diameter of the mounting holes at the connection positions of the first wing support 1 and the first fuselage joint 11, the second wing support 2 and the second fuselage joint 12, and the third wing support 3 and the third fuselage joint 8 to a size smaller than the outer diameter of the bushing. Finally, remove all the process bolts. Step 4: After the center wing 5 is separated from the fuselage, install the bushings in the bushing holes at all the wing supports and fuselage joints in sequence. Based on the characteristic that the bushing mounting hole is smaller than the outer diameter of the bushing, soak the bushing in liquid nitrogen for 5-8 minutes. After it has cooled completely and the outer diameter has shrunk, press it into the bushing hole. After returning to room temperature, the bushing forms an interference fit with the wing support and fuselage joint. Step 5: Lift the center wing 5 again, adjust its attitude, and after the bushing holes of the four wing supports are aligned with those of the fuselage joint, first insert the connecting bolts at the corresponding positions of the second wing support 2 and the fourth wing support 4, and then insert the bolts at the positions of the first wing support 1 and the third wing support 3 to complete the connection between the center wing 5 and the fuselage.

[0042] Example 3: A method for wing-body docking of a fixed-wing aircraft, the docking method employing the aforementioned wing-body docking structure, includes the following steps: Step 1: Connect the first wing support 1, the third wing support 3, the second wing support 2 and the fourth wing support 4 to the center wing 5 first, leaving installation slack in the mounting holes that mate with the fuselage; Step 2: Use a crane to lift the assembled center wing 5, and connect and fix the first wing support 1, the second wing support 2 and the third wing support 3 to the first fuselage joint 11, the second fuselage joint 12 and the third fuselage joint 8 with process bolts. Use a reaming tool to enlarge the diameter of the mounting holes at the location of the fourth wing support 4 and the fourth fuselage joint 9 to be 10 microns smaller than the outer diameter of the bushing, and then use process bolts to connect the fourth wing support 4 and the fourth fuselage joint 9. Step 3: Following the steps in Step 2, enlarge the diameter of the mounting holes at the connection positions of the first wing support 1 and the first fuselage joint 11, the second wing support 2 and the second fuselage joint 12, and the third wing support 3 and the third fuselage joint 8 to 10 microns smaller than the outer diameter of the bushing. Finally, remove all the process bolts. Step 4: After the center wing 5 is separated from the fuselage, install the bushings in the bushing holes at all the wing supports and fuselage joints in sequence. Based on the characteristic that the bushing mounting hole is smaller than the outer diameter of the bushing, soak the bushing in liquid nitrogen for 5-8 minutes. After it has cooled completely and the outer diameter has shrunk, press it into the bushing hole. After returning to room temperature, the bushing forms an interference fit with the wing support and fuselage joint. Step 5: Lift the center wing 5 again, adjust its attitude, and after the bushing holes of the four wing supports are aligned with those of the fuselage joint, first insert the connecting bolts at the corresponding positions of the second wing support 2 and the fourth wing support 4, and then insert the bolts at the positions of the first wing support 1 and the third wing support 3 to complete the connection between the center wing 5 and the fuselage.

Claims

1. A wing-body docking structure for a fixed-wing aircraft, characterized in that, The central wing (5) is symmetrically fixed with a first wing support (1) and a third wing support (3) on the front side of the bottom end of the central wing (5), and with a second wing support (2) and a fourth wing support (4) symmetrically fixed on the rear side of the bottom end of the central wing (5). It also includes a first fuselage joint (11) and a second fuselage joint (12) fixed to the top of the first side fuselage frame (10), and the first fuselage joint (11) and the second fuselage joint (12) are respectively fixedly connected to the first wing support (1) and the second wing support (2) by bolts; It also includes a third fuselage joint (8) and a fourth fuselage joint (9) fixed to the top of the second fuselage frame (7), and the third fuselage joint (8) and the fourth fuselage joint (9) are respectively fixedly connected to the third wing support (3) and the fourth wing support (4) by bolts.

2. The wing-body docking structure for a fixed-wing aircraft according to claim 1, characterized in that: The first wing support (1) and the second wing support (2) are located on the same side and are arranged symmetrically. The third wing support (3) and the fourth wing support (4) are located on the same side and are arranged symmetrically.

3. The wing-body docking structure for a fixed-wing aircraft according to claim 1, characterized in that: The first side fuselage frame (10) and the second side fuselage frame (7) are fixed to the top of the fuselage.

4. The wing-body docking structure for a fixed-wing aircraft according to claim 1, characterized in that: The first wing support (1) has a first wing bushing hole (102) machined on it, and a first wing bushing (101) is installed inside the first wing bushing hole (102). The second wing support (2) has a second wing bushing hole (202) machined on it, and the second wing bushing (201) is installed inside the second wing bushing hole (202). The third wing support (3) has a third wing bushing hole (302) machined on it, and the third wing bushing (301) is installed inside the third wing bushing hole (302). The fourth wing support (4) has a fourth wing bushing hole (402) machined on its upper part, and the fourth wing bushing (401) is installed inside the fourth wing bushing hole (402).

5. The wing-body docking structure for a fixed-wing aircraft according to claim 4, characterized in that: The first body connector (11) has a first body bushing hole (1102) machined on it, and a first body bushing (1101) is installed inside the first body bushing hole (1102). The second body connector (12) has a second body bushing hole (1202) machined on it, and the second body bushing (1201) is installed inside the second body bushing hole (1202). The third fuselage connector (8) has a third fuselage bushing hole (802) machined on it, and the third fuselage bushing (801) is installed inside the third fuselage bushing hole (802). The fourth fuselage bushing hole (902) is machined on the fourth fuselage joint (9), and the fourth fuselage bushing (901) is installed inside the fourth fuselage bushing hole (902).

6. The wing-body docking structure for a fixed-wing aircraft according to claim 4, characterized in that: The first wing bushing hole (102), the second wing bushing hole (202), the third wing bushing hole (302), the fourth wing bushing hole (402), the first fuselage bushing hole (1102), the second fuselage bushing hole (1202), the third fuselage bushing hole (802), and the fourth fuselage bushing hole (902) are all parallel to the flight direction of the aircraft.

7. The wing-body docking structure for a fixed-wing aircraft according to claim 4, characterized in that: The first wing bushing hole (102) and the first wing bushing (101) form an interference fit; The second wing bushing hole (202) and the second wing bushing (201) form an interference fit; The third wing bushing hole (302) and the third wing bushing (301) form an interference fit; The fourth wing bushing hole (402) and the fourth wing bushing (401) form an interference fit.

8. The wing-body docking structure for a fixed-wing aircraft according to claim 5, characterized in that: The first fuselage bushing hole (1102) and the first fuselage bushing (1101) form an interference fit; The second fuselage bushing hole (1202) and the second fuselage bushing (1201) form an interference fit; The third fuselage bushing hole (802) and the third fuselage bushing (801) form an interference fit; The fourth fuselage bushing hole (902) and the fourth fuselage bushing (901) form an interference fit.

9. The wing-body docking structure for a fixed-wing aircraft according to claim 4, characterized in that: The first fuselage connector (11), the second fuselage connector (12), the third fuselage connector (8) and the fourth fuselage connector (9) all adopt a double-fork lug connector structure.

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