CN118289202A - Flap retraction system based on flexible flap - Google Patents

Abstract

The invention discloses a flap retraction system based on flexible flaps, which belongs to the technical field of aircraft flaps and comprises: the flexible flap comprises a wing, a retraction mechanism connected with the wing through a connecting base, and a flexible flap main structure connected with the retraction mechanism; the flexible flap main structure comprises a flap front end, the flap front end is connected with a retracting mechanism through a connecting piece, one side of the flap front end is integrally formed with a flap tail end, two bases are arranged on the outer portion of the flap front end, a worm is rotatably arranged in the bases through a bearing, a turbine is connected with the worm in an externally meshed mode, a threaded shaft is connected with the turbine in an internally connected mode, one end of the threaded shaft, far away from the turbine, penetrates through the inner portion of the flap front end and is connected with a movable plate through the bearing, and a rocker arm assembly is arranged on the movable plate.

Description

Flap retraction system based on flexible flap

Technical Field

The invention relates to the technical field of aircraft flaps, in particular to a flap retraction system based on flexible flaps.

Background

Aircraft flaps are a type of retractable device on the wings of an aircraft, commonly used to increase wing area and lift, thereby improving the take-off and landing performance of the aircraft. In flight, in order to reduce drag and increase the speed of flight, the flaps need to be stowed, at which point the retraction of the flaps needs to be accomplished using a flap retraction mechanism. Thus, the aircraft flap retraction mechanism acts as an important component on the aircraft wing.

Currently, flap retraction mechanisms have become an important component of modern aircraft, and common retraction mechanisms include chain drives, screw drives, hydraulic drives, electric drives, and the like, as well as flexible flap-based retraction mechanisms and the like.

The traditional flap retraction system of the aircraft is complex in structure, various in parts and huge in volume, and the aerodynamic performance of the assault part is optimized by the fairing, so that the flap retraction system based on the flexible flap is provided.

Disclosure of Invention

The present invention aims to solve at least one of the technical problems existing in the prior art. To this end, an object of the invention is to propose a flap retraction system based on flexible flaps.

In order to achieve the above purpose, the present invention provides the following technical solutions:

A flexible flap-based flap retraction system comprising: the flexible flap comprises a wing, a retraction mechanism connected with the wing through a connecting base, and a flexible flap main structure connected with the retraction mechanism;

The flexible flap main structure comprises a flap front end, wherein the flap front end is connected with a retracting mechanism through a connecting piece, one side of the flap front end is integrally formed with a flap tail end, two bases are arranged outside the flap front end, a worm is rotatably arranged inside the bases through a bearing, a turbine is connected with the outside of the worm in a meshed manner, a threaded shaft is connected with the inside of the turbine, one end of the threaded shaft, far away from the turbine, penetrates through the inside of the flap front end and is connected with a movable plate through the bearing, and a rocker arm assembly is arranged on the movable plate;

As a further optimization scheme of the invention, the outer part of the front end of the flap, which is close to the tail end of the flap, is connected with a fixed base, one side of the fixed base is integrally formed with a fixed plate, the fixed base and the fixed plate are provided with second sliding grooves, and the movable plate slides in the second sliding grooves.

As a further optimization scheme of the invention, the rocker arm assembly comprises a main arm, the main arm is rotatably connected to a movable plate, a connecting arm is connected to the movable plate through a rotating shaft, the other end of the connecting arm is connected to a fixed plate, the outer part of the main arm is connected with a first connecting rod, a second connecting rod and a third connecting rod through rotating shafts, and one ends of the first connecting rod, the second connecting rod and the third connecting rod, which are far away from the main arm, are attached to the tail end of the flap.

As a further optimization scheme of the invention, a plurality of sliding blocks are connected to the wing, a plurality of first sliding grooves are formed in the outer portion of the front end of the flap, and the sliding blocks are connected to the inner portion of the first sliding grooves in a sliding mode.

Compared with the prior art, the invention has the beneficial effects that:

in the invention, the retraction mechanism is two sets of mutually independent control systems, the originally complex retraction motion of the flap is split into two independent transmissions, each motion is independently controlled more flexibly, and the operation is simpler and more direct. The respective functional requirements may be realized alone or in combination.

According to the invention, the reliability of the system can be effectively improved by a simple mechanical structure, and the anti-interference capability of the system is improved by the array type hydraulic system. Meanwhile, the protruding part is omitted, so that the fairing is omitted, and the aerodynamic performance of the aircraft is optimized.

Drawings

FIG. 1 is a schematic view of an external perspective structure of the present invention;

FIG. 2 is a schematic view of a partially exploded construction of the present invention;

FIG. 3 is a schematic perspective view of a rocker arm assembly of the present invention;

FIG. 4 is a schematic view of the structure of the threaded shaft and the forward end of the flap of the present invention;

FIG. 5 is a schematic view of the retracting mechanism and the front end of the flap of the present invention

FIG. 6 is a schematic view of the structure of the airfoil and slider of the present invention.

In the figure:

10. A wing; 11. A slide block;

20. A flap front end; 21. A flap end; 22. A first chute;

30. a worm; 31. A turbine; 32. A threaded shaft;

40. A retracting mechanism;

50. A fixed base; 51. a second chute; 52. a moving plate; 53. a main arm; 54. a fixing plate; 55. a first connecting rod; 56. a second connecting rod; 57. a connecting arm; 58. and a connecting rod III.

Detailed Description

The following description of the embodiments of the present invention will be made clearly and completely with reference to the accompanying drawings, in which it is apparent that the embodiments described are only some embodiments of the present invention, but not all embodiments. All other embodiments, which can be made by those skilled in the art based on the embodiments of the invention without making any inventive effort, are intended to be within the scope of the invention.

Referring to fig. 1-6, the present invention provides a technical solution:

A flexible flap-based flap retraction system comprising: the wing 10 and a retraction mechanism 40 connected with the wing 10 through a connecting base;

The retracting mechanism 40 is two sets of transmission mechanisms which do not interfere with each other, and can be one or a combination of a plurality of any mechanical transmission modes such as hydraulic transmission, pneumatic transmission, gear transmission, hinge transmission, belt transmission, worm transmission and the like.

The flexible flap main structure is connected with the retracting mechanism 40 and comprises a flap front end 20, the flap front end 20 is connected with the retracting mechanism 40 through a connecting piece, a flap tail end 21 is integrally formed on one side of the flap front end 20, two bases are arranged outside the flap front end 20, a worm 30 is rotatably arranged inside the bases through a bearing, a turbine 31 is connected with the outside of the worm 30 in a meshed manner, a threaded shaft 32 is connected with the inside of the turbine 31, one end of the threaded shaft 32, far away from the turbine 31, penetrates through the inside of the flap front end 20 and is connected with a movable plate 52 through the bearing, and a rocker arm assembly is arranged on the movable plate 52;

wherein the flap tip 21 and the flap nose 20 are flexible skins.

The outer portion of the front end 20 of the flap, which is close to the tail end 21 of the flap, is connected with a fixed base 50, one side of the fixed base 50 is integrally formed with a fixed plate 54, the fixed base 50 and the fixed plate 54 are provided with a second sliding groove 51, and the moving plate 52 slides in the second sliding groove 51.

The rocker arm assembly comprises a main arm 53, the main arm 53 is rotatably connected to a moving plate 52, a connecting arm 57 is connected to the moving plate 52 through a rotating shaft, the other end of the connecting arm 57 is connected to a fixed plate 54, a connecting rod I55, a connecting rod II 56 and a connecting rod III 58 are connected to the outside of the main arm 53 through rotating shafts, and one ends, far away from the main arm 53, of the connecting rod I55, the connecting rod II 56 and the connecting rod III 58 are attached to a flap tail end 21.

The wing 10 is connected with a plurality of sliding blocks 11, a plurality of first sliding grooves 22 are formed in the outer portion of the front end 20 of the wing, and the sliding blocks 11 are connected to the inner portion of the first sliding grooves 22 in a sliding mode.

The working principle of the embodiment is as follows:

When the flap is required to be folded and unfolded, the folding and unfolding mechanisms 40 are started, two sets of mutually independent control systems are respectively used for the two sets of folding and unfolding mechanisms 40, one set of control folding and unfolding mechanisms 40 drives the pushing out and the folding out of the flap front end 20 through a hydraulic push rod, and in the pushing process, the sliding block 11 slides in the first sliding groove 22 to provide a limiting effect for the flap front end 20;

The other set of control retraction mechanism 40 controls the downward bending and restoration of the front end 20 of the flap, namely drives the front end 20 of the flap to rotate at the front end of the wing 10, splits the originally complex retraction motion of the flap into two independent transmissions, independently controls each motion, is more flexible, has simpler and more direct motion, and can singly or in combination realize corresponding functional requirements.

The main structure of the flexible flap is controlled to bend through the rocker arm assembly, the rocker arm assembly consists of a main arm 53, a first connecting rod 55, a second connecting rod 56, a connecting arm 57 and a third connecting rod 58, power generated by an aircraft engine drives the worm 30 to rotate, then the worm 30 drives the turbine 31 to rotate, and the turbine 31 drives the threaded shaft 32 to link, so that the moving plate 52 moves forwards on the fixed base 50 horizontally.

The rocker arm assembly takes the connection part of the root part of the rocker arm assembly and the fixed base 50 as the center of a circle and takes the connecting rod I55, the connecting rod II 56 and the connecting rod III 58 as the constraint radius to carry out circular arc-shaped movement, and the connecting rod III 58 drives the flap tail end 21 to deform downwards and plays a role in supporting the flap tail end 21 not to collapse after the deformation is completed.

Similarly, a flexible flap main structure should be driven synchronously by a plurality of rocker arm assemblies which are communicated with each other and transmit power through the same turbine 31.

Under the condition that the main structure of the flexible flap can meet the requirement of downward bending of the tail end of the flap, the integral retracting mechanism of the flap is simplified into linear hydraulic actuation, the parallel array formed by a plurality of retracting mechanisms 40 is only used for forming, and the retracting structure of the connecting rod rocker arm screw rod which is originally protruded from the lower part of the wing is simplified and completely retracted into the wing. The simple mechanical structure can effectively improve the reliability of the system, and the array type hydraulic system improves the anti-interference capability of the system. Meanwhile, the protruding part is omitted, so that the fairing is omitted, and the aerodynamic performance of the aircraft is optimized.

In the description of the present invention, the terms "first," "second," and the like are used for descriptive purposes only and are not to be construed as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defining "a first" or "a second" may explicitly or implicitly include one or more such feature. The meaning of "a plurality of" is two or more, unless specifically defined otherwise.

In the present invention, unless explicitly specified and limited otherwise, the terms "mounted," "connected," "secured," and the like are to be construed broadly, and may be, for example, fixedly connected, detachably connected, or integrally formed; can be mechanically or electrically connected; can be directly connected or indirectly connected through an intermediate medium, and can be communicated with the inside of two elements or the interaction relationship of the two elements. The specific meaning of the above terms in the present invention can be understood by those of ordinary skill in the art according to the specific circumstances.

None of the inventions are related to the same or are capable of being practiced in the prior art. Although embodiments of the present invention have been shown and described, it will be understood by those skilled in the art that various changes, modifications, substitutions and alterations can be made therein without departing from the principles and spirit of the invention, the scope of which is defined in the appended claims and their equivalents.

Claims (4)

1. A flexible flap-based flap retraction system, comprising: the wing (10), a retracting mechanism (40) connected with the wing (10) through a connecting base, and a flexible flap main structure connected with the retracting mechanism (40).

The flexible flap main structure comprises a flap front end (20), the flap front end (20) is connected with a retracting mechanism (40) through a connecting piece, one side integrated into one piece of the flap front end (20) is provided with a flap tail end (21), two bases are arranged on the outer portion of the flap front end (20), a worm (30) is rotatably arranged in the base through a bearing, a turbine (31) is connected with the worm (30) in an externally meshed mode, a threaded shaft (32) is connected with the turbine (31) in an internally connected mode, one end of the threaded shaft (32) away from the turbine (31) penetrates through the inside of the flap front end (20) and is connected with a movable plate (52) through the bearing, and a rocker arm assembly is arranged on the movable plate (52).

2. The flexible flap-based flap retraction system of claim 1 wherein: the outside that is close to flap end (21) of flap front end (20) is connected with unable adjustment base (50), one side integrated into one piece of unable adjustment base (50) has fixed plate (54), second spout (51) have all been seted up on unable adjustment base (50) and fixed plate (54), remove plate (52) and slide in the inside of second spout (51).

3. The flexible flap-based flap retraction system of claim 1 wherein: the rocker arm assembly comprises a main arm (53), the main arm (53) is rotationally connected to a moving plate (52), a connecting arm (57) is connected to the main arm (53) through a rotating shaft, the other end of the connecting arm (57) is connected to a fixed plate (54), a connecting rod I (55), a connecting rod II (56) and a connecting rod III (58) are connected to the outer portion of the main arm (53) through rotating shafts, and one end, far away from the main arm (53), of the connecting rod I (55) and the connecting rod II (56) and one end, far away from the connecting rod III (58), of the connecting rod III (58) are attached to a flap tail end (21).

4. The flexible flap-based flap retraction system of claim 1 wherein: the wing (10) is connected with a plurality of sliding blocks (11), a plurality of first sliding grooves (22) are formed in the outer portion of the front end (20) of the wing flap, and the sliding blocks (11) are connected to the inner portion of the first sliding grooves (22) in a sliding mode.