CN110294102B

CN110294102B - Composite motion mechanism of integrated flap aileron

Info

Publication number: CN110294102B
Application number: CN201910344825.8A
Authority: CN
Inventors: 史佑民; 安刚; 康宁
Original assignee: Xian Jiaotong University; Qingan Group Co Ltd
Current assignee: Xian Jiaotong University; Qingan Group Co Ltd
Priority date: 2019-04-26
Filing date: 2019-04-26
Publication date: 2023-05-23
Anticipated expiration: 2039-04-26
Also published as: CN110294102A

Abstract

The invention belongs to the field of flight control mechanism design, and particularly relates to a composite motion mechanism of an integrated flap aileron. The invention provides a compound motion mechanism of an integrated flap aileron, which is an integral airfoil surface formed by combining an outer trailing edge flap and an aileron; the composite motion mechanism provides support for the front part of a pair of flap ailerons on a wing beam frame through a hinge four bar and a flap aileron support bar and can move under the action of a first driving force; the middle parts of two pairs of front ailerons on the wing beam frame are also supported by the tripod and the front aileron support rods and can move under the action of a second driving force. According to the motion mechanism, the actuator cylinder and the connecting rod mechanism are added on the original flap driving mechanism, the aileron wing surface of the existing aircraft is eliminated, the functions of the flap and the aileron are realized by utilizing the wing surface of the integrated flap, and the functions of lift-increasing and aileron roll control of the original trailing edge flap can be realized by the integrated flap.

Description

Composite motion mechanism of integrated flap aileron

Technical Field

The invention belongs to the field of flight control mechanism design, and particularly relates to a composite motion mechanism of an integrated flap aileron.

Background

As shown in FIG. 1, a modern large aircraft achieves the goal of increasing the wing area during take-off by extending

trailing edge flaps

101, 102 and leading edge slats 103 on the wing 100, the increase in the area of the wing 100 increasing the lift of the aircraft so that the aircraft takes off and lands at a lower speed. During the flight of the aircraft, the pilot achieves roll maneuver of the aircraft by manipulating the yaw angle of the left and right ailerons 104. The outboard trailing edge flap 102 and aileron 104 of an aircraft are typically two independent airfoils, and the

trailing edge flaps

101, 102 typically employ a recoil lower deflection mechanism, i.e., a fullerene-type motion mechanism; the aileron 104 adopts a movement mechanism for rotating and deflecting up and down, and the flap control computer and the main flight control computer respectively control the deflection angles of the

trailing edge flaps

101 and 102 and the aileron 104.

Disclosure of Invention

The invention provides a compound motion mechanism of an integrated flap aileron, wherein the integrated flap aileron is characterized in that an outer trailing edge flap and an aileron are combined into an airfoil surface, and the functions of lift augmentation and aileron roll manipulation of the original trailing edge flap can be realized through the integrated flap aileron by the compound motion mechanism.

The integrated flaperon is a composite motion mechanism of an integrated flaperon, and the integrated flaperon is an integral airfoil which synthesizes an outer trailing edge flap and an aileron; the composite motion mechanism provides support for the front part of a pair of flap ailerons on a wing beam frame through a hinge four bar and a flap aileron support bar and can move under the action of a first driving force; the middle parts of two pairs of front ailerons on the wing beam frame are also supported by the tripod and the front aileron support rods and can move under the action of a second driving force.

The hinge four-bar linkage comprises an upper bracket, a first connecting rod, a second connecting rod and a rotary actuator, wherein the main body of the rotary actuator is arranged on the upper bracket, the rocker arm of the rotary actuator is hinged with one end of the second connecting rod at the end part, the other end of the second connecting rod is hinged with one end of the first connecting rod, and the other end of the first connecting rod is hinged with the upper bracket.

The first flap support rod is hinged with the flap at one end and is hinged with the proximal connecting rod joint of the hinge four-bar at the other end.

The first flap support rod is hinged with the flap at a first flap rotation point and a second flap rotation point respectively.

The three vertex angles of the tripod are respectively hinged with the upper bracket, one end of the second front flap supporting rod and the actuating end of the actuating cylinder, the other end of the actuating cylinder is hinged and fixed, and the other end of the second front flap supporting rod is hinged with the front flap.

A lower bracket extends from the upper bracket and is hinged with one vertex angle of the tripod, and the actuator cylinder is hinged and fixed on the lower bracket.

When the flap is manipulated to retract as a flap, the drive at the front of the flap is in the retracted position and the drive at the middle of the flap is in the extended position.

When the flap is maneuvered to extend as a flap, the drive means in the front of the flap is in the extended position and the drive means in the middle of the flap is in the extended position.

When the flap is manipulated to deflect downward as a flap, the drive at the front of the flap is in the stowed position and the drive at the middle of the flap is in the extended position.

When the flap is manipulated to deflect upward as an flap, the drive at the front of the flap is in the stowed position and the drive at the middle of the flap is in the stowed position.

The motion mechanism adds the actuator cylinder and the connecting rod mechanism on the original flap driving mechanism, cancels the aileron airfoil surface of the existing aircraft, and realizes the functions of flaps and ailerons by utilizing the airfoil surface of the integrated flap aileron.

Drawings

FIG. 1 is a block diagram of a flap and aileron on a wing of a conventional aircraft;

FIG. 2 is a state diagram of the composite motion mechanism of the present invention for achieving flap stow functionality;

FIG. 3 is a state diagram of the compound motion mechanism of the present invention for achieving a flap extend function;

FIG. 4 is a state diagram of the compound motion mechanism of the present invention for implementing aileron downward deflection;

fig. 5 is a state diagram of the composite motion mechanism of the present invention for realizing the aileron upward deflection function.

1. An upper bracket; 2. a first rotating point of the soft connecting rod; 3. a first connecting rod; 4. a first flap aileron support rod; 5. a first flap rotation point; 6. a second flap rotating point; 7. a third flap rotation point; 8. a flap; 9. a second flap supporting rod; 10. a tripod rotation point I; 11. tripod rotation point two; 12. a tripod; 13. a first rotation point of the lower bracket; 14. an actuator cylinder; 15. a second rotation point of the lower bracket; 16. a lower bracket; 17. a lower rotation point of the connecting rod; 18. a second connecting rod; 19. a second rotation point of the connecting rod; 20. a rotary actuator; 21. wing beam frame

Detailed Description

The invention relates to a composite motion mechanism of an integrated flap wing, the three-dimensional wing beam comprises an upper bracket 1, a first upper rotating point 2 of a connecting rod, a first connecting rod 3, a first flap supporting rod 4, a first flap rotating point 5, a second flap rotating point 6, a third flap rotating point 7, a third flap 8, a second flap supporting rod 9, a first tripod rotating point 10, a second tripod rotating point 11, a tripod 12, a first lower bracket rotating point 13, an actuator cylinder 14, a second lower bracket rotating point 15, a lower bracket 16, a lower connecting rod rotating point 17, a second connecting rod 18, a second connecting rod rotating point 19, a rotary actuator 20 and a wing beam frame 21.

The upper bracket 1 is fixedly connected to the wing beam frame 21, the connecting rod I3 is hinged with the upper bracket 1 at the upper rotating point 2 of the connecting rod I, the lower end of the flap aileron supporting rod I4 is hinged with the connecting rod I3 at the lower rotating point 17 of the connecting rod I, the upper end of the flap aileron supporting rod I4 is hinged with the flap aileron 8 at the flap aileron rotating point I5 and the flap aileron rotating point II 6 respectively, the upper end of the flap aileron supporting rod II 9 is hinged with the flap aileron 8 at the flap aileron rotating point III 7,

the lower bracket 16 is fixedly connected to the wing beam frame 21, the lower bracket 16 is hinged with the tripod 12 at a first lower bracket rotating point 13, the tripod 12 is hinged with the lower end of a second flap supporting rod 9 at a first tripod rotating point 10, the left end of the actuator cylinder 14 is hinged with the lower bracket 16 at a second lower bracket rotating point 15, the right end of the actuator cylinder 14 is hinged with the tripod 12 at a second tripod rotating point 11, the rotary actuator 20 is fixedly connected to the wing beam frame 21, the lower end of a second connecting rod 18 is hinged with the rotary actuator 20 at a second connecting rod rotating point 19, and the upper end of the second connecting rod 18 is hinged with the first connecting rod 3 and the first flap supporting rod 4 at a lower connecting rod rotating point 17.

When the flap function is extended, the rotary actuator 20 rotates anticlockwise, and drives the flap 8 to extend through the first connecting rod 3, the second connecting rod 18, the first flap supporting rod 4 and the second flap supporting rod 9, so that the flap extending function is realized.

When the flap aileron realizes the aileron downward deflection function: the actuator cylinder 14 extends out and drives the flap 8 to deflect downwards through the tripod 12, the flap support rod I4 and the flap support rod II 9, so that the downward deflection function of the flap is realized.

Claims

1. The utility model provides a compound motion of integral type front of a garment aileron, its characterized in that: the integrated flap aileron is an integral airfoil formed by combining an outer trailing edge flap and an aileron; the composite motion mechanism provides support for the front part of the flap (8) on the wing beam frame (21) through a hinge four-bar and a flap support bar I (4) and can move under the action of a first driving force; the middle part of the flap aileron (8) is supported on the wing beam frame (21) through a tripod (12) and a flap aileron supporting rod II (9) and can move under the action of a second driving force;

the hinge four-bar linkage comprises an upper bracket (1), a first connecting rod (3), a second connecting rod (18) and a rotary actuator (20), wherein the main body of the rotary actuator (20) is arranged on the upper bracket (1), the rocker arm of the rotary actuator is hinged with one end of the second connecting rod (18) at the end part, the other end of the second connecting rod (18) is hinged with one end of the first connecting rod (3), and the other end of the first connecting rod (3) is hinged with the upper bracket (1); the first flap aileron support rod (4) is hinged with the flap aileron (8) at one end and is hinged with a near-end connecting rod joint of the hinge four-bar at the other end;

a lower bracket (16) extending from the upper bracket (1), wherein the lower bracket (16) is hinged with one vertex angle of the tripod (12), and the actuating cylinder (14) is hinged and fixed on the lower bracket (16); the other two vertex angles of the tripod (12) are respectively hinged with one end of a second flap supporting rod (9) and the actuating end of an actuating cylinder (14), and the other end of the second flap supporting rod (9) is hinged with a flap (8).

2. The compound motion mechanism of claim 1, wherein: the first flap supporting rod (4) is hinged with the flap (8) at a first flap rotating point (5) and a second flap rotating point (6) respectively.

3. The compound motion mechanism according to any one of claims 1-2, wherein: when the flap (8) is operated to be retracted, the drive means in the front of the flap (8) is in the retracted position and the drive means in the middle of the flap (8) is in the extended position.

4. The compound motion mechanism according to any one of claims 1-2, wherein: when the flap 8 is manoeuvred out as a flap, the drive means in front of the flap 8 is in the extended position and the drive means in the middle of the flap 8 is in the extended position.

5. The compound motion mechanism according to any one of claims 1-2, wherein: when the flap (8) is manoeuvred as a flap-down bias, the drive means in front of the flap (8) is in the stowed position and the drive means in the middle of the flap (8) is in the extended position.

6. The compound motion mechanism according to any one of claims 1-2, wherein: when the flap (8) is operated to deflect upwards as an aileron, the drive means in front of the flap (8) is in a stowed position and the drive means in the middle of the flap (8) is in a stowed position.