CN111003142B

CN111003142B - Flexible connecting device for wing body

Info

Publication number: CN111003142B
Application number: CN201911359110.6A
Authority: CN
Inventors: 付强; 蔡栋材
Original assignee: AVIC First Aircraft Institute
Current assignee: AVIC First Aircraft Institute
Priority date: 2019-12-25
Filing date: 2019-12-25
Publication date: 2022-08-19
Anticipated expiration: 2039-12-25
Also published as: CN111003142A

Abstract

The present application provides a flexible connection device for a wing body, the flexible connection device 300 for a wing body 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 stopper 314, the flexible connection device 300 is used for connecting the wing body 100 and the wing 200, wherein: the left side and the right side of the wing 200 are respectively provided with a front rail 311 and a rear rail 312 in the vertical direction, the front rail 311 and the rear rail 312 are both in a strip structure, and the top ends of the front rail 311 and the rear rail 312 are respectively arranged on the lower surfaces of the left side and the right side of the wing 200; the trolley 313 is two sliding block components used for sliding on the front track 311 and the rear track 312, two sliding trolleys 313 are arranged on the front track 311, two sliding trolleys 313 are arranged on the rear track 312, and the trolleys 313 are fixedly arranged on the side surface of the body 100; the front rail 311 is provided at upper and lower ends thereof with stoppers 314, respectively, and the rear rail 312 is provided at upper and lower ends thereof with stoppers 314, respectively.

Description

Flexible wing body connecting device

Technical Field

The application relates to the aircraft structure design technology, in particular to a flexible connecting device for a wing body.

Background

The wings and the fuselage of the existing fixed wing aircraft are rigidly connected, namely the fuselage and reinforcing points on the wings are connected into a rigid whole through connecting pieces such as bolts, bolts and the like. There is an inherent problem with this arrangement: when the wings are disturbed by gusts, the movement of the wings can be directly transmitted to the fuselage, so that personnel or equipment in the fuselage and the whole fuselage structure bear large overload, the comfort is poor, and the fatigue life of the structure is influenced.

Disclosure of Invention

The invention is primarily aimed at improving the comfort of the passengers inside the fuselage and the loads to which the aircraft structure is subjected in gusty conditions.

The present application provides a flexible connection device for a wing body, the flexible connection device 300 for a wing body 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 stopper 314, the flexible connection device 300 is used for connecting the wing body 100 and the wing 200, wherein:

the left side and the right side of the wing 200 are respectively provided with a front rail 311 and a rear rail 312 in the vertical direction, the front rail 311 and the rear rail 312 are both in a strip structure, and the top ends of the front rail 311 and the rear rail 312 are respectively arranged on the lower surfaces of the left side and the right side of the wing 200; the pulleys 313 are two sliding block assemblies used for sliding on the front rail 311 and the rear rail 312, two slidable pulleys 313 are arranged on the front rail 311, two slidable pulleys 313 are arranged on the rear rail 312, and the pulleys 313 are fixedly arranged on the side face of the machine body 100; the upper end and the lower end of the front rail 311 are respectively provided with a stopper 314, and the upper end and the lower end of the rear rail 312 are respectively provided with a stopper 314; one end of the damper 320 is connected to the wing connection joint 202 and the other end of the damper 320 is connected to the fuselage connection joint 328.

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

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

Preferably, the wing connection joint 202 is of a double-lug structure, the fuselage connection joint 328 is of a double-lug structure, and both ends of the bumper 320 are of a single-lug structure.

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

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

Preferably, the fuselage attachment joints 328 are disposed on fuselage sidewall structures 329.

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

Compared with the existing connection structure of the airplane wing and the airplane body, the connection structure of the airplane body and the airplane wing has better load transfer characteristic, can improve the movement characteristic of the airplane body and the comfort of passengers, simultaneously reduces the acting force at the connection part of the airplane wing and the airplane body, and is beneficial to improving the fatigue life of the airplane structure. On the other hand, the weight of the structure where the force is concentrated by the aircraft can be reduced.

Drawings

FIG. 1 is an isometric view of a fixed-wing aircraft provided herein;

FIG. 2 is a left side view of a fixed wing aircraft as provided herein;

FIG. 3 is a front view of a fixed-wing aircraft provided herein;

FIG. 4 is a schematic view of a bumper attached to a wing according to the present disclosure;

FIG. 5 is a schematic view of a flexible connection device for a wing body according to the present application;

FIG. 6 is a schematic view of a bumper attached to a fuselage according to the present disclosure;

wherein: 100-fuselage, 200-wing, 300-flexible connecting device, 310-moving mechanism, 320-buffer, 201-lower surface of wing, 202-connecting joint of wing, 311-front rail, 312-rear rail, 313-pulley, 314-stopping device, 321-bolt, 322-nut, 323-knuckle bearing, 324-upper joint of buffer, 325-inner cylinder of buffer, 326-outer cylinder of buffer, 327-lower joint of buffer, 328-connecting joint of fuselage and 329-side wall structure of fuselage.

Detailed Description

The comfort of the passengers and the overloads to which the aircraft structure is subjected are mainly related to the movements of the fuselage. The wings are the major aerodynamic surfaces of the aircraft and are most affected by gusts. When exposed to gusts, the aerodynamic forces on the wings change rapidly and the forces are transferred to the fuselage through the joint between the wings and the fuselage, causing the fuselage to vibrate and heave together with the wings. These are detrimental to comfort and structural loading. In order to avoid the direct transmission of motion and load in the wing and the fuselage, the invention adds a link which can enable the wing and the fuselage to generate relative motion between the wing and the fuselage, namely, the wing and the fuselage are connected through a motion mechanism. In order to restrain the two from colliding together or completely separating, a stop structure is required at the end of the movement stroke. In addition, in order to enable smooth transfer of motion, a damper needs to be provided between the wing and the fuselage. The buffer is composed of a spring device and a damping device. By reasonably selecting the elastic coefficient and the damping coefficient, the damping and load-reducing effect can be remarkably generated aiming at the gust in a certain frequency range.

Claims

1. A flexible connection device for a wing body (300), characterized in that the flexible connection device (300) comprises a movement mechanism (310) and a damper (320), the movement mechanism (310) comprises a front rail (311), a rear rail (312), a trolley (313) and a stopper device (314), the flexible connection device (300) is used for connecting a fuselage (100) and a wing (200), wherein:

the left side and the right side of the wing (200) are respectively provided with a front rail (311) and a rear rail (312) in the vertical direction, the front rail (311) and the rear rail (312) are both in a long strip structure, and the top ends of the front rail (311) and the rear rail (312) are respectively arranged on the lower surfaces of the left side and the right side of the wing (200); the pulleys (313) are two sliding block assemblies which are used for sliding on a front track (311) and a rear track (312), two slidable pulleys (313) are arranged on the front track (311), two slidable pulleys (313) are arranged on the rear track (312), and the pulleys (313) are fixedly arranged on the side face of the machine body (100); the upper end and the lower end of the front rail (311) are respectively provided with a stop device (314), and the upper end and the lower end of the rear rail (312) are respectively provided with a stop device (314); one end of the buffer (320) is connected to the wing connection joint (202), and the other end of the buffer (320) is connected to the fuselage connection joint (328).

2. The flexible wing body attachment of claim 1, wherein the damper (320) comprises a spring means and a damping means.

3. The wing body flexible connection device of claim 1, wherein the damper (320) comprises a bolt (321), a nut (322), a knuckle bearing (323), a damper upper joint (324), a damper inner cylinder (325), a damper outer cylinder (326), and a damper lower joint (327).

4. The wing body flexible connecting device of claim 1, characterized in that the wing connecting joint (202) is of a double-lug structure, the fuselage connecting joint (328) is of a double-lug structure, and both ends of the buffer (320) are of a single-lug structure.

5. The flexible wing body connection device according to claim 1, characterized in that the axial direction of the bumper (320) is parallel to both the axial direction of the front rail (311) and the axial direction of the rear rail (312).

6. The flexible connection device of wing body according to claim 1, characterized in that the elastic coefficient and damping coefficient of the damper (320) are set according to wing weight, fuselage weight and gust frequency.

7. The wing body flexible attachment of claim 1, characterized in that the fuselage attachment joint (328) is provided on a fuselage sidewall structure (329).

8. The wing body flexible connection device of claim 1, characterized in that the wing connection joint (202) is provided on a wing surface (201).