CN111003142B - Flexible connecting device for wing body - Google Patents

Abstract

The present application provides a wing body flexible connection device. The wing body flexible connection device 300 includes a motion mechanism 310 and a buffer 320. The motion mechanism 310 includes a front rail 311, a rear rail 312, a pulley 313 and a stop device 314. The flexible connecting device 300 is used to connect the fuselage 100 and the wing 200, wherein: the left and right sides of the wing 200 are respectively provided with a vertical front rail 311 and a rear rail 312, and the front rail 311 and the rear rail 312 are both long Strip-shaped structure, the top ends of the front rail 311 and the rear rail 312 are respectively arranged on the lower surfaces of the left and right sides of the wing 200; Two slidable pulleys 313 are arranged on the upper, and two slidable pulleys 313 are arranged on the rear track 312, and the pulleys 313 are fixedly arranged on the side of the fuselage 100; the upper and lower ends of the front track 311 are respectively provided with stop devices 314 , the upper end and the lower end of the rear rail 312 are respectively provided with stop devices 314 .

Description

A wing body flexible connection device

technical field

The present application relates to aircraft structure design technology, in particular to a wing body flexible connection device.

Background technique

A rigid connection is adopted between the wings and the fuselage of the existing fixed-wing aircraft, that is, the fuselage and the reinforcement points on the wings are connected into a relatively rigid whole by connecting parts such as bolts and pins. This structure has an inherent problem: when the wing is disturbed by a gust of wind, the movement of the wing will be directly transmitted to the fuselage, causing the personnel or equipment inside the fuselage and the entire structure to bear a large overload, resulting in poor comfort. , and affect the structural fatigue life.

SUMMARY OF THE INVENTION

The purpose of the present invention is mainly to improve the comfort of the occupants inside the fuselage and the loads that the aircraft structure bears under gust conditions.

The present application provides a wing body flexible connection device. The wing body flexible connection device 300 includes a motion mechanism 310 and a buffer 320. The motion mechanism 310 includes a front rail 311, a rear rail 312, a pulley 313, and a stop device 314. The flexible connecting device 300 is used for connecting the fuselage 100 and the wing 200, wherein:

The left and right sides of the wing 200 are respectively provided with a front track 311 and a rear track 312 in a vertical direction. The front track 311 and the rear track 312 are both elongated structures, and the tops of the front track 311 and the rear track 312 are respectively arranged on the wing 200 The lower surfaces of the left and right sides; the pulley 313 is two slider assemblies for sliding on the front rail 311 and the rear rail 312, two slidable pulleys 313 are set on the front rail 311, and two slidable pulleys 313 are set on the rear rail 312 The pulley 313 is fixedly arranged on the side of the fuselage 100; the upper and lower ends of the front rail 311 are respectively provided with stop devices 314, and the upper and lower ends of the rear rail 312 are respectively provided with stop devices 314; the buffer 320 One end of the bumper 320 is connected to the wing connecting joint 202 , and the other end of the buffer 320 is connected to the fuselage connecting joint 328 .

Preferably, the buffer 320 includes a spring device and a damping device.

Preferably, the buffer 320 includes a bolt 321 , a nut 322 , a joint bearing 323 , an upper buffer joint 324 , an inner buffer cylinder 325 , an outer buffer cylinder 326 and a lower buffer joint 327 .

Preferably, the wing connecting joint 202 is a binaural structure, the fuselage connecting joint 328 is a binaural structure, and both ends of the buffer 320 are a single-ear structure.

Preferably, the axial direction of the buffer 320 is parallel to the axial direction of the front rail 311 and the axial direction of the rear rail 312 .

Preferably, the spring coefficient and damping coefficient of the buffer 320 are set according to the wing weight, the fuselage weight and the gust frequency.

Preferably, the fuselage connecting joint 328 is arranged on the side wall structure 329 of the fuselage.

Preferably, the wing connecting joint 202 is provided on the wing surface 201 .

Compared with the existing aircraft wing-to-fuselage connection structure, this fuselage-to-wing connection structure has better load transfer characteristics, which can improve the motion characteristics of the fuselage and the comfort of the occupants, while reducing the wing The force at the connection with the fuselage is beneficial to improve the fatigue life of the aircraft structure. On the other hand, it is possible to reduce the structural weight of the aircraft where the force is concentrated.

Description of drawings

1 is an axonometric view of a fixed-wing aircraft provided by the application;

2 is a left side view of a fixed-wing aircraft provided by the application;

3 is a front view of a fixed-wing aircraft provided by the application;

4 is a schematic diagram of the connection between a buffer and a wing provided by the application;

5 is a schematic structural diagram of a wing body flexible connection device provided by the application;

6 is a schematic diagram of the connection between a buffer and a fuselage provided by the application;

Among them: 100-fuselage, 200-wing, 300-flexible connecting device, 310-movement mechanism, 320-buffer, 201-wing lower surface, 202-wing connecting joint, 311-front track, 312-rear track , 313- pulley, 314-stop device, 321-bolt, 322-nut, 323-joint bearing, 324-buffer upper joint, 325-buffer inner cylinder, 326-buffer outer cylinder, 327-buffer lower Joint, 328-fuselage connection joint, 329-fuselage side wall structure.

Detailed ways

The comfort of the occupants and the overloads to which the aircraft structure is subjected are primarily related to the motion of the fuselage. The wing is the main aerodynamic surface of the aircraft and is most affected by gusts. When encountering a gust, the aerodynamic force on the wing changes rapidly, and the force is transmitted to the fuselage through the joint between the wing and the fuselage, causing the fuselage and the wing to vibrate and undulate. These are bad for both comfort and structural loads. In order to avoid the direct transfer of motion and load between the wing and the fuselage, the present invention adds a link between the wing and the fuselage that can make the two move relatively, that is, the two are connected through a motion mechanism. In order to restrain the two from colliding together or completely disengaging, a stop structure needs to be provided at the end of the movement stroke. In addition, in order for the movement to be transmitted smoothly, it is necessary to provide buffers between the wings and the fuselage. The buffer consists of a spring device and a damping device. By choosing the elastic coefficient and damping coefficient reasonably, a significant shock absorption and load reduction effect can be produced for gusts within a certain frequency range.

Claims (8)

1. A wing body flexible connection device, characterized in that the wing body flexible connection device (300) comprises a motion mechanism (310) and a buffer (320), and the motion mechanism (310) comprises a front rail (311) , a rear rail (312), a pulley (313) and a stop device (314), the flexible connection device (300) is used to connect the fuselage (100) and the wing (200), wherein: The left and right sides of the wing (200) are respectively provided with a front rail (311) and a rear rail (312) in a vertical direction. The front rail (311) and the rear rail (312) are both elongated structures, and the front rail (311) and the top ends of the rear track (312) are respectively arranged on the lower surfaces of the left and right sides of the wing (200); the pulley (313) is two slider assemblies for sliding on the front track (311) and the rear track (312), Two slidable pulleys (313) are arranged on the front rail (311), and two slidable pulleys (313) are arranged on the rear track (312), and the pulleys (313) are fixedly arranged on the side surface of the fuselage (100). The upper end and the lower end of the front track (311) are respectively provided with a stop device (314), and the upper end and the lower end of the rear track (312) are respectively provided with a stop device (314); One end of the buffer (320) is connected to the wing On the connecting joint (202), the other end of the buffer (320) is connected to the connecting joint (328) of the fuselage. 2. The wing body flexible connection device according to claim 1, wherein the buffer (320) comprises a spring device and a damping device. 3. The flexible connection device of the wing body according to claim 1, wherein the buffer (320) comprises a bolt (321), a nut (322), a joint bearing (323), and a buffer upper joint (324) , the buffer inner cylinder (325), the buffer outer cylinder (326) and the buffer lower joint (327). 4. The wing body flexible connection device according to claim 1, wherein the wing connection joint (202) is a binaural structure, the fuselage connection joint (328) is a binaural structure, and the buffer (320) Both ends of the monaural structure. 5 . The flexible connection device of the wing body according to claim 1 , wherein the axial direction of the buffer ( 320 ) is parallel to the axial direction of the front rail ( 311 ) and the axial direction of the rear rail ( 312 ). 6 . . 6 . The flexible connection device of the wing body according to claim 1 , wherein the elastic coefficient and damping coefficient of the buffer ( 320 ) are set according to the wing weight, the fuselage weight and the gust frequency. 7 . 7. The wing body flexible connection device according to claim 1, wherein the fuselage connection joint (328) is provided on the fuselage side wall structure (329). 8. The wing body flexible connection device according to claim 1, wherein the wing connection joint (202) is provided on the wing surface (201).

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