CN-122009473-A - Large-angle folding mechanism and method for aircraft wings

CN122009473ACN 122009473 ACN122009473 ACN 122009473ACN-122009473-A

Abstract

The invention relates to the technical field of folding of wings of aircrafts, in particular to a large-angle folding mechanism and a large-angle folding method for wings of aircrafts, comprising a fixed wing section connected with a fuselage, a movable wing section connected with the fixed wing section in a folding way and a folding drive for connecting the fixed wing section with the movable wing section, wherein the bottom of the folding end of the fixed wing section is rotationally connected with the bottom of the folding end of the movable wing section, the folding drive is used for driving the movable wing section to downwards overturn and fold to be close to the lower surface of the fixed wing section, the folding drive is used for driving the movable wing section to downwards overturn to be close to the lower surface of the fixed wing section around a rotating connection position, so that the downwards folding of the movable wing section is realized, the space below the fixed wing section is fully utilized, the space utilization rate is improved, the fuselage width is reduced, the occupied space of the aircrafts is reduced, the whole structure is simple, the cost is low, and the operation is simple and convenient.

Inventors

ZHANG CHAO
SUN JIGEN
HAN YUXIN
LIU YILUN

Assignees

西安交通大学

Dates

Publication Date: 20260512
Application Date: 20260331

Claims (10)

1. The large-angle folding mechanism for the aircraft wing is characterized by comprising a fixed wing section (2) connected with the fuselage (1), a movable wing section (3) connected with the fixed wing section (2) in a folding way, and a folding drive for connecting the fixed wing section (2) with the movable wing section (3); The bottom of the folding end of the fixed wing section (2) is rotationally connected with the bottom of the folding end of the movable wing section (3); The folding drive is used for driving the movable wing section (3) to turn downwards and fold to be close to the lower surface of the fixed wing section (2).
2. The aircraft wing high angle folding mechanism according to claim 1, characterized in that the length of the stationary wing section (2) is greater than or equal to the length of the movable wing section (3).
3. The high angle folding mechanism of an aircraft wing according to claim 2, wherein the folding drive is configured to control an angle between a folding end of the fixed wing section (2) and a folding end of the movable wing section (3) to be 0 ° to 180 °.
4. An aircraft wing wide angle folding mechanism according to claim 3, wherein the folding drive comprises a fixed wing end actuator (21), a movable wing end actuator (31) and a triangular rocker arm (4), and the bottom of the folding end of the fixed wing section (2) is rotatably connected with the bottom of the folding end of the movable wing section (3) through a rotating shaft; Fixed wing actuating groove has been seted up in fixed wing section (2), movable wing actuating groove has been seted up in movable wing section (3), the stiff end of fixed wing end actuator (21) extends to in the fixed wing actuating groove and is articulated with the fixed wing actuating groove, the stiff end of movable wing end actuator (31) extends to in the movable wing actuating groove and is articulated with the movable wing actuating groove, the apex angle connecting hole of triangle-shaped rocking arm (4) with the pivot rotates to be connected, the flexible end of fixed wing end actuator (21) and the flexible end of movable wing end actuator (31) rotate with the base angle connecting hole that triangle-shaped rocking arm (4) corresponds respectively to be connected, fixed wing actuating groove and movable wing actuating groove all are relative with triangle-shaped rocking arm (4).
5. The aircraft wing high angle folding mechanism according to claim 4, characterized in that the triangular rocker arm (4) is isosceles triangle.
6. The aircraft wing wide angle folding mechanism of claim 1, wherein the folding drive further comprises a locking unit disposed between the folding end of the fixed wing section (2) and the folding end of the movable wing section (3), the locking unit being configured to connect the fixed wing section (2) and the movable wing section (3) when the movable wing section (3) is unfolded, and to unlock when the movable wing section (3) is folded.
7. The aircraft wing wide angle folding mechanism of claim 6, wherein the locking unit comprises a mechanical lock catch (23) and a locking groove (33), the mechanical lock catch (23) is arranged at the folding end of the fixed wing section (2), and the locking groove (33) is arranged at the folding end of the movable wing section (3).
8. The high-angle folding mechanism for an aircraft wing according to claim 4, wherein when the included angle between the folding end of the fixed wing section (2) and the folding end of the movable wing section (3) is 0 °, the lengths of the fixed wing end actuator (21) and the movable wing end actuator (31) are equal and are both When the included angle between the folding end of the fixed wing section (2) and the folding end of the movable wing section (3) is 180 degrees, the lengths of the fixed wing end actuator (21) and the movable wing end actuator (31) are equal and are all ; Wherein, the The distance between the apex angle connecting hole and the base angle connecting hole of the triangular rocker arm (4); Is half of the distance between the two bottom corner connecting holes; in order to realize the horizontal distance between the vertex angle connecting hole of the triangular rocker arm (4) and the fixed end of the fixed wing end actuator (21) or the fixed end of the movable wing end actuator (31) when the included angle between the folding end of the fixed wing section (2) and the folding end of the movable wing section (3) is 0 degrees, Is the longitudinal distance between the vertex angle connecting hole of the triangular rocker arm (4) and the fixed end of the fixed wing end actuator (21) or the fixed end of the movable wing end actuator (31).
9. The aircraft wing high angle folding mechanism of claim 4, wherein the limit output force of the movable wing end actuator (31) is not less than F: Wherein, the When the included angle between the folding end of the fixed wing section (2) and the folding end of the movable wing section (3) is 180 degrees, the horizontal distance between the gravity center of the movable wing section (3) and the vertex angle connecting hole of the triangular rocker arm (4); Is the dead weight of the movable wing section (3).
10. An aircraft wing wide angle folding method, characterized in that based on the aircraft wing wide angle folding mechanism of any one of claims 3-9, comprising the following steps: the aircraft sends a folding instruction; Judging whether an included angle between the folding end of the fixed wing section (2) and the folding end of the movable wing section (3) is 180 degrees or not according to the extension distance of the fixed wing end actuator (21) and/or the movable wing end actuator (31); the telescopic ends of the fixed wing end actuator (21) and the movable wing end actuator (31) are synchronously stretched until the included angle between the folding end of the fixed wing section (2) and the folding end of the movable wing section (3) is 180 degrees; the aircraft sends a deployment instruction; judging whether an included angle between the folding end of the fixed wing section (2) and the folding end of the movable wing section (3) is 0 degree or not according to the extension distance of the fixed wing end actuator (21) and/or the movable wing end actuator (31); The telescopic ends of the fixed wing end actuator (21) and the movable wing end actuator (31) synchronously shrink until the included angle between the folding end of the fixed wing section (2) and the folding end of the movable wing section (3) is 0 degrees.

Description

Large-angle folding mechanism and method for aircraft wings Technical Field The invention relates to the technical field of folding of aircraft wings, in particular to a large-angle folding mechanism and method of an aircraft wing. Background The aircraft wing fold design is a core means of balancing the aerodynamic requirements of flight with the parking space limitations. However, the conventional folding scheme generally has the problem that the storage volume is not optimized thoroughly, most of the folded wings are still perpendicular to the machine body, for example, the Chinese patent application with publication number of CN1192821A provides a fully-sealed linkage folding mechanism for double-folded wings, the double-folded wings are kept in a vertical state after folding, so that the occupied space in the height direction is not obviously reduced, the linear spiral mechanism of a part of the rotatable folding structure can only realize small-angle rotation of 3-60 degrees, the wings cannot be completely parallel to the machine body, external driving parts are needed, the structural volume is further increased, and the Z-shaped folding wings can realize multi-section folding (for example, a 'pond goose' ship-borne early warning/anti-diving machine in the United kingdom), but the folded wings still protrude out of the outline of the machine body, and the space utilization rate is lower. Therefore, the existing wing folding mechanism is difficult to meet the requirement of an aircraft for a compact parking space. Disclosure of Invention The invention aims to provide a large-angle folding mechanism and method for an aircraft wing, which solve the technical problem that the existing wing folding structure occupies a large shutdown space after being folded. The invention solves the technical problems as follows: a large-angle folding mechanism for an aircraft wing comprises a fixed wing section connected with a fuselage, a movable wing section connected with the fixed wing section in a folding manner, and a folding drive for connecting the fixed wing section and the movable wing section; the bottom of the folding end of the fixed wing section is rotationally connected with the bottom of the folding end of the movable wing section; the folding drive is used for driving the movable wing section to fold downwards and close to the lower surface of the fixed wing section. Further defined, the length of the stationary wing panel is greater than or equal to the length of the movable wing panel. Further limited, the folding drive is used for controlling the included angle between the folding end of the fixed wing section and the folding end of the movable wing section to be 0-180 degrees. The folding drive comprises a fixed wing end actuator, a movable wing end actuator and a triangular rocker arm, wherein the bottom of the folding end of the fixed wing section is rotationally connected with the bottom of the folding end of the movable wing section through a rotating shaft; The fixed wing section is internally provided with a fixed wing driving groove, the movable wing section is internally provided with a movable wing driving groove, the fixed end of the fixed wing end actuator extends into the fixed wing driving groove and is hinged with the fixed wing driving groove, the fixed end of the movable wing end actuator extends into the movable wing driving groove and is hinged with the movable wing driving groove, the vertex angle connecting hole of the triangular rocker arm is rotationally connected with the rotating shaft, the telescopic end of the fixed wing end actuator and the telescopic end of the movable wing end actuator are respectively rotationally connected with the base angle connecting hole corresponding to the triangular rocker arm, and the fixed wing driving groove and the movable wing driving groove are opposite to each other with the triangular rocker arm. Further defined, the triangular rocker arm is isosceles triangle. Further defined, the folding drive further comprises a locking unit disposed between the fixed wing folding end and the movable wing folding end, the locking unit being configured to connect the fixed wing to the movable wing when the movable wing is unfolded and to unlock when the movable wing is folded. Further defined, the locking unit comprises a mechanical lock catch and a locking groove, wherein the mechanical lock catch is arranged at the folding end of the fixed wing section, and the locking groove is arranged at the folding end of the movable wing section. Further defined, when the included angle between the folding end of the fixed wing section and the folding end of the movable wing section is 0 DEG, the lengths of the fixed wing end actuator and the movable wing end actuator are equal and are bothWhen the included angle between the folding end of the fixed wing section and the folding end of the movable wing section is 180 degrees, the lengths of the fixed wing end actu