CN219790511U

CN219790511U - Connecting rod type folding wing tip and aircraft

Info

Publication number: CN219790511U
Application number: CN202321165472.3U
Authority: CN
Inventors: 刘铁让; 刘天奇; 奚晓波; 罗丹; 高丽敏; 陈晨忻
Original assignee: Commercial Aircraft Corp of China Ltd; Beijing Aeronautic Science and Technology Research Institute of COMAC
Current assignee: Commercial Aircraft Corp of China Ltd; Beijing Aeronautic Science and Technology Research Institute of COMAC
Priority date: 2023-05-15
Filing date: 2023-05-15
Publication date: 2023-10-03
Anticipated expiration: 2033-05-15

Abstract

The utility model relates to a connecting rod type folding wing tip and an airplane, which belong to the technical field of airplane body design, and overcome a plurality of defects in the prior art through a simple, efficient and unique folding mechanism, a locking mechanism and a protection mechanism; the folding wing tip comprises a wing tip fixing section, a wing tip movable section, a wing tip folding mechanism, a locking mechanism and a protection mechanism; the wing tip fixing section and the wing tip movable section are connected through the wing tip folding mechanism, and the wing tip movable section rotates relative to the wing tip fixing section under the action of the wing tip folding mechanism; the locking mechanism is connected with the wing tip folding mechanism and is used for locking the state of the wing tip folding mechanism after the wing tip folding mechanism finishes the action; the protection mechanism is connected with the wing tip movable section and is used for realizing the protection function.

Description

Connecting rod type folding wing tip and aircraft

Technical Field

The utility model relates to the technical field of aircraft body design, in particular to a connecting rod type folding wing tip and an aircraft.

Background

The use of high aspect ratio wings to increase the lift-drag ratio of an aircraft has become a major consideration in reducing fuel consumption in modern broadbody passenger aircraft designs. In order to overcome the problem of adaptability of aircraft to airports, i.e. the large wing span of the aircraft may exceed the requirements of the runway, taxiway and parking place for the width of the aircraft, the use of folded wing designs on large-format airliners has begun to receive increasing attention in recent years.

The use of folding wings on large, wide-body airliners has been a matter of recent years, but the use of folding wings on other types of aircraft has been a history of decades, particularly in the field of carrier-borne aircraft. From the prior disclosure, there are two main ways of folding wing design at present, one is based on the folding way driven by an electric rotary actuator, and the other is based on the folding way driven by a baseline type hydraulic actuator. In the two modes, although the latter is more traditional, the advantages of simple structural system design, high output power of an actuator, high reliability and the like are still an important driving mode selection in the current folding wing design.

In the folding approach based on linear drives, a folding design featuring a wing tip overhanging short beam is of great interest. The wing tip rotating part is provided with an overhanging short beam, namely one end of the short beam is fixed on the movable wing tip, one end of the short beam extends outwards, and then the overhanging end of the short beam is pushed by a linear actuator cylinder positioned on the wing tip fixing section and close to the lower wing surface to rotate around a hinge shaft arranged on the upper wing surface. However, this method, although simple in design and easy to implement, has the following disadvantages: one is that, when the folding wing tip is erected, the linear actuator needs to provide a sufficiently large push or pull force to counter the extreme moment caused by the severe side wind on the erected wing surface to the lower folding hinge shaft thereof under severe side wind conditions. Due to the limitation of the narrow space of the wing tip, the volume of the actuator cannot be quite large, and the high-power output is required, which obviously places quite high requirements on the performance of the actuator, and particularly when the wing is flat or the folded wing surface is quite high, the design is more challenging due to the limitation of the output power of the actuator; secondly, the arm of force that can be provided to the actuator against the external load torque in this design is relatively small, which means that the same external load torque requires a greater push or pull output from the actuator. The moment arm is increased, so that mutual interference between the overhanging end of the short beam and the lower airfoil surface of the fixed end is generated when the wing tip is erected, the lower airfoil surface is required to be opened, and a corresponding closing mechanism for opening when the wing tip is restored is designed, so that the complexity of a system is caused; thirdly, the design is that the most serious load working condition is the extreme crosswind working condition when the airfoil is erected, and the extreme crosswind working condition corresponds to the maximum elongation condition of the actuator, and when the actuator is pressed due to the crosswind direction, the extreme crosswind working condition is obviously unfavorable for the stability supported by the actuator cylinder; finally, this design has the disadvantage that after the wing is folded at the airport, the internal mechanisms and system equipment of the wing, including the extended actuators and the like, are exposed to the outside about the hinge axis, which obviously is disadvantageous for preventing the invasion of external environmental factors such as sun, dust, rain and snow when the aircraft is parked at various airports.

In addition, U.S. patent No. 11440637B2 discloses a structure for folding a wing tip, but the structure still has the following disadvantages: firstly, the structure is complex, the stability is influenced, particularly, the load of the large-aspect-ratio wing is often larger, and the stability of the structure can not easily meet the requirement of the large-aspect-ratio wing; secondly, when the wing tip is folded, the wing tip cannot be folded at a large angle (such as 90 degrees or close to 90 degrees), and when the wing tip is applied to a wing with a large aspect ratio, the problem that the wing tip exceeds an airport runway, a taxiway and a parking place still exists possibly, so that the technical problem of the wing tip can not be effectively solved; thirdly, the structure can not be folded to 90 degrees, and the pressure of the crosswind direction to the relevant actuating devices still exists, which is not beneficial to stability.

Accordingly, there is a need to develop a connecting rod folding wing tip and aircraft to address the deficiencies of the prior art, to address or mitigate one or more of the problems described above.

Disclosure of Invention

In view of this, the present utility model provides a connecting rod type folding wing tip and an aircraft, which overcomes a plurality of disadvantages in the prior art by a simple, efficient and unique folding mechanism, locking mechanism and protection mechanism.

In one aspect, the present utility model provides a connecting rod folding wing tip comprising a wing tip fixed section, a wing tip movable section, a wing tip folding mechanism, a locking mechanism and a protection mechanism;

the wing tip fixing section and the wing tip movable section are connected through the wing tip folding mechanism, and the wing tip movable section rotates relative to the wing tip fixing section under the action of the wing tip folding mechanism;

the locking mechanism is connected with the wing tip folding mechanism and locks the wing tip folding mechanism after the wing tip folding mechanism finishes the action;

the protection mechanism is fixedly connected with the wing tip movable section and movably connected with the wing tip fixed section.

In accordance with aspects and any one of the possible implementations described above, there is further provided an implementation, the wing tip folding mechanism including a folding rotational hinge assembly, a folding link, a folding slide rail, and a folding actuator;

the upper airfoil surface of the wing tip fixing section and the upper airfoil surface of the wing tip movable section are hinged through the folding rotation hinging assembly;

the folding slide rail and the folding actuator are sequentially and fixedly arranged in the wing tip fixing section and near the bottom; the folding sliding rail and the folding actuator are coaxially arranged, and the folding sliding rail is positioned at the outer side of the folding actuator;

the outer end of the folding connecting rod is hinged with the wing tip movable section, and the inner end of the folding connecting rod is hinged with the actuating rod of the folding actuator; the bottom of the folding connecting rod is in sliding connection with the folding sliding rail.

In the aspect and any possible implementation manner described above, there is further provided an implementation manner, where the connection between the wing tip fixing section and the wing tip moving section is a chamfer structure, an included angle between the chamfer structure and an x-axis forward direction is 135 °, and the x-axis forward direction is a direction from the fuselage to the wing tip.

In aspects and any one of the possible implementations described above, there is further provided an implementation, the folding swivel hinge assembly including a swivel axis; in a top view state, the rotating shaft is perpendicular to the folding sliding rail, and the intersection point is positioned in the middle of the length direction of the folding sliding rail.

In the aspect and any possible implementation manner described above, there is further provided an implementation manner, where a length of the folding link is equal to a length of the folding slide rail.

In the aspect and any possible implementation manner described above, there is further provided an implementation manner, where the folding link is a Y-shaped rod body structure, and two ends of the folding link are connected to the folding actuator, and one end is connected to the wing tip movable section.

In aspects and any one of the possible implementations described above, there is further provided an implementation, the locking mechanism including a locking driver, a return lock bolt, a return stop, a cocking lock bolt, and a cocking stop;

the return stop block and the erection stop block are respectively and fixedly arranged below two ends of the folding slide rail of the wing tip folding mechanism, the return stop block is arranged at one end close to the airframe, and the erection stop block is arranged at one end far away from the airframe;

the recovery locking bolt is arranged on one side, close to the machine body, of the recovery stop block, and the erection locking bolt is arranged on one side, far away from the machine body, of the erection stop block;

the restoring locking bolt and the rising locking bolt are driven by the locking driver to achieve rising and lying, the corresponding locking bolt and the corresponding stop block are in contact connection during rising, and the corresponding locking bolt and the corresponding stop block have a certain distance in the longitudinal direction during lying, and the distance meets the space required by normal folding operation of the wing tip folding mechanism.

In accordance with aspects and any one of the possible implementations described above, there is further provided an implementation in which the return lock bolt and the cocking lock bolt each comprise a straight section and a hooked section, and the straight section and the hooked section are integrally affixed.

In aspects and any one of the possible implementations described above, there is further provided an implementation, the guard mechanism including a guard plate and a guard plate strut;

the outer end of the protection plate is fixedly connected with the inner end of the wing tip movable section, and the fixedly connected point is close to the lower wing surface; the inner end of the protection plate is in a free state;

the upper end of the protection plate support rod is fixedly connected with the inner end of the wing tip movable section, and the fixedly connected point is close to the upper wing surface; the lower end of the protection plate supporting rod is fixedly connected with the upper surface of the protection plate, and the fixedly connected point is close to the inner end of the protection plate;

an opening for the free passage of the protection plate is formed in the lower wing surface of the wing tip fixing section.

In the aspect and any possible implementation manner described above, there is further provided an implementation manner, wherein one or more opening plugging plates are arranged on the lower airfoil surface of the wing tip fixing section, and a corresponding plugging track is arranged under each opening plugging plate; each opening plugging plate moves towards an opening formed in the lower wing surface along a corresponding plugging track under the driving of plugging power equipment, so that the opening is plugged.

In another aspect, the utility model provides an aircraft having a wing with a connecting rod folded wing tip as defined in any one of the preceding claims.

Compared with the prior art, one of the technical schemes has the following advantages or beneficial effects: according to the scheme, under the most serious load working condition, namely extreme side wind, the bearing of the actuator is reduced to zero from the maximum in the existing design, namely the original extreme load born by the actuator is completely transferred to the structure born by the wing tip fixing section, so that the requirement on the output power of the actuator is greatly reduced;

the other technical scheme has the following advantages or beneficial effects: according to the utility model, the folding connecting rod is introduced, so that the force arm of the external load moment of the actuator is relatively increased, and the use efficiency of the actuator is improved;

the other technical scheme has the following advantages or beneficial effects: according to the scheme, under the condition that an actuating mechanism is not added and the outer wing surface of the wing tip after being retracted is not influenced, the protection of internal equipment and systems after the wing tip is erected is provided by arranging a simple protection mechanism and a movable wing tip follow-up, so that the wing tip lifting device is simple, convenient and efficient, and is beneficial to popularization.

Of course, it is not necessary for any of the products embodying the utility model to achieve all of the technical effects described above at the same time.

Drawings

In order to more clearly illustrate the technical solutions of the embodiments of the present utility model, the drawings that are needed in the embodiments will be briefly described below, and it is obvious that the drawings in the following description are only some embodiments of the present utility model, and that other drawings can be obtained according to these drawings without inventive effort for a person skilled in the art.

FIG. 1 is a schematic illustration of a structure of a connecting rod type folding wing tip provided in one embodiment of the present utility model;

FIG. 2 illustrates the position of the connecting rod and actuating rod when the movable wing tip is cocked according to one embodiment of the present utility model

And a schematic diagram of a transmission mode of the device under a crosswind working condition;

FIG. 3 is a schematic view of the position of the connecting rod and the actuating rod and the load transmission pattern of the movable wing tip under the crosswind condition at any rotation angle according to an embodiment of the present utility model;

FIG. 4 is a schematic view of the positions of the connecting rod and the actuating rod when the movable wing tip returns to its original position according to one embodiment of the present utility model;

FIG. 5 is a schematic view of a movable wing tip retraction locking mechanism provided in accordance with one embodiment of the present utility model;

figure 6a is a schematic view of the structure of a follower wing tip with shield provided in accordance with one embodiment of the present utility model in a vertical cocked state;

figure 6b is a schematic view of the structure of a follower wing tip with built-in shield provided in one embodiment of the utility model in a 45 inclined condition;

FIG. 6c is a schematic view of a follower wing tip with built-in shield in a returned to its original position according to one embodiment of the present utility model;

FIG. 7a is a schematic top view of a wing tip in situ provided by an embodiment of the present utility model;

FIG. 7b is a schematic top view of a wing tip provided by an embodiment of the present utility model when folded 45;

FIG. 7c is a schematic top view of a wing tip provided in accordance with one embodiment of the present utility model when erected vertically;

fig. 8 is a schematic structural view of a locking mechanism according to an embodiment of the present utility model.

Wherein, in the figure:

1. a wing tip fixing section; 2. a wing tip active section; 21. ear pieces; 3. a connecting rod; 31. a first pin; 32. a second pin; 4. a slide rail; 5. a linear actuator; 51. an actuating lever; 52. an actuator support; 6. folding and rotating the hinge shaft; 6': a projection of the folding rotary hinge shaft on the lower wing surface; 61. an airfoil hinge lug; 7. a locking mechanism; 71. restoring the locking bolt; 72. erecting a locking bolt; 73. restoring the stop block; 74. erecting a stop block; 75. a locking bolt link; 76. a locking bolt fixing fulcrum; 77. a lock driver; 78. a driver stop block; 79. a locking bolt hinge shaft; 100. a protection plate; 101. a protection plate strut; 11. spar webs.

Detailed Description

For a better understanding of the technical solution of the present utility model, the following detailed description of the embodiments of the present utility model refers to the accompanying drawings.

It should be understood that the described embodiments are merely some, but not all, embodiments of the utility model. All other embodiments, which can be made by those skilled in the art based on the embodiments of the utility model without making any inventive effort, are intended to be within the scope of the utility model.

To overcome the shortcomings of the prior designs described above, the present utility model proposes a new folding design that uses linear actuators to drive the wing tips. The main method is that a simple connecting rod is arranged at the movable end of the wing tip and the fixed section, one end of the simple connecting rod is connected with the movable part in a hinge supporting mode, and the other end of the simple connecting rod is supported on a linear sliding rail which is arranged in the wing tip fixed section and is close to the lower wing surface and is simultaneously connected with the output end of a linear actuating cylinder. The actuating cylinder is supported on the inner structure of the wing tip fixing section through two points, and the axis of the actuating cylinder is coincident with the central line of the sliding rail. The movable wing tip part is finally driven by the connecting rod, the sliding rail and the actuating cylinder. By the design, the defects of the prior method are completely overcome, and the special appearance is that: first, under the most severe load conditions, i.e. extreme crosswinds, the load bearing capacity of the actuator is reduced to zero by the maximum in the existing designs, in other words the extreme loads originally required to be borne by the actuator are all transferred to be borne by the wing tip fixing section structure. Obviously, such a design greatly reduces the requirements for the output power of the actuator; secondly, by introducing a connecting rod, the force arm of the external load moment of the actuator is relatively increased, so that the service efficiency of the actuator is improved; thirdly, the compression stability of the actuator in large elongation is improved by fixing two points of the actuator; fourth, the protection of internal equipment and systems after the wing tip is erected is provided by providing a simple guard plate with movable wing tip follower without adding any actuating mechanism and affecting the outer airfoil surface after the wing tip is retracted.

1. Design of a folding wing tip driving mode:

the content of the driving design method of the utility model comprises the following aspects:

a) In this method, as shown in fig. 1, the wing tip movable section 2 is connected to the wing tip fixed section 1 by a connecting rod 3 on the one hand, and is hinged to the upper end of the wing tip fixed section 1 by a folding rotation hinge shaft 6 on the other hand. One end of the connecting rod 3 is connected with the wing tip movable section through a hinge piece (a lug piece 21 connected with the wing tip movable section and the connecting rod), the other end of the connecting rod is connected with a sliding rail 4 and a linear actuator 5 which are fixed in the wing tip fixed section, the connecting rod is in sliding connection with the sliding rail 4, and the connecting rod is hinged with the end part of an actuating rod 51 to realize the movement of the actuating rod. The hinge is hinged.

b) The sliding rail 4 in the wing tip fixing section 1 is arranged straight, fixed and supported in the structure of the wing tip fixing section by the supporting piece; the sliding rail is arranged at the near outer end of the wing tip fixing section, wherein the outer end of the sliding rail is positioned at the outermost end of the wing tip fixing section, and the inner end of the sliding rail is positioned inside the wing tip fixing section.

c) The linear actuator 5 is also fixed inside the wing tip fixing section 1 in a manner or with a strength that the linear actuator does not deflect (which can be achieved by the actuator support 52 or other manners of fixing strength that are required), and the axis of the actuating rod 51 coincides with the central axis of the sliding rail 4; the linear actuator 5 is specifically located on the inside (the side remote from the wing tip active section) of the slide rail 4.

The slide rail 4 includes two parallel arrangement. The connecting rod 3 is arranged between the two sliding rails and is simultaneously in sliding connection with the two sliding rails.

d) The wing tip movable section rotates around a rotation shaft which is arranged on the fixed end and close to a wing surface under the drive of an actuator, namely the folding rotation hinge shaft 6, the wing surface of the fixed end and the wing surface of the movable end are always connected with each other along the axis through the hinge connection mode of the wing surface hinge lug 61 and the folding rotation hinge shaft 6, and the axes of the pin shafts of different connection positions are coincident with the axis of the folding rotation shaft of the whole wing surface.

e) The sliding rail 4, the actuator 5 and the connecting rod 3 are all positioned opposite to the rotation shaft at the mechanical supporting point of the movable end. The rotation axis o and the included angle alpha between the slide rail end points A and B are shown in the figure ₁ And alpha ₂ Length L of slide rail _AB Length L of connecting rod _CD Rotating the shaft to the lowerThe distance h of the airfoil and the distance e of the actuator axis from the lower airfoil can be adjusted to meet folding angle requirements, actuator power performance and structural design constraints and the like.

f) Analysis shows that when the included angle between the two end points of the sliding rail and the rotating shaft, the length of the sliding rail and the length of the connecting rod meet the following relation

α ₁ ＝α ₂ ＝45°

L _AB ＝L _CD ＝2(h-e)

L _CD ＝L _AB (1a,c)

At this point the wing tip fold angle Δθ is 90 ° and when the wing tip is cocked, as shown in fig. 2, under the most severe airfoil off-load conditions, i.e. extreme side winds, the loading F of the actuator _{Actuator device} Zero, in other words, the external load is now entirely borne by the fixed end structure. At the same time, the total elongation Δl of the actuator _{Actuator device} Equal to the length of the slide rail and the link, i.e.

Δθ＝90°

F _{Actuator device} ＝0

ΔL _{Actuator device} ＝L _AB ＝L _CD (2a,c)

In addition, at this time, the axial support reaction force F generated by the connecting rod 3 _CD Transverse and vertical supporting reaction forces F on the rotating shaft _OX F (F) _OY Respectively is

F _CD ＝M _O /(h-e)

F _OX ＝-M _O /d

F _Oy ＝-F _CD (3a,c)

M in the above _O ＝F _x d is the resultant force F of the crosswind load in the transverse direction _x The torque relative to the rotational axis, d, is the distance from the centre of pressure of the crosswind on the raised wing tip to the rotational axis.

g) The utility model also provides a design corresponding to the formulas (1 a, c) for loading the actuating rod F at any rotation angle theta (compared with the rotation angle in the fully unfolded state) _{Actuator device} Relationship to rotation angle. For simplicity, it is assumed here that the wing tip is rectangular, with lengths and widths a and b, respectively. Reference toAs shown in FIG. 3, the following relationship can be finally obtained

Wherein ρ is air density, V is crosswind speed, c _q The tie rod tilt angle beta is determined by the following equation for the aerodynamic coefficient

h) The slide rails are supported in a box girder structure in the form of a composite web or in the form of a metal bracket.

From the above, the design of the utility model thoroughly solves the high requirement on the output power of the actuator under the working condition of extreme side wind load in the existing design. And meanwhile, as the actuator is thoroughly fixed and does not allow deflection, the anti-compression instability capability of the actuator at the maximum extension is improved.

The realization of the folding wing tip driving mode is as follows:

on the basis of the above description of the basic design method, the utility model gives further details of the design by means of a plan view, as shown in fig. 7a, 7b, 7 c. The actuator and the slide rail are arranged on the axis of the wing tip. The slide rail comprises two rails which are arranged in parallel. The connecting rod is a Y-shaped rod body, two ends of the connecting rod are inner ends, and one end is an outer end. The two ends of the inner end of the connecting rod are respectively provided with a through hole, the first pin shaft 31 is arranged in the two through holes in a penetrating mode, the two ends of the first pin shaft 31 are respectively fixedly connected with a sliding block, and the sliding blocks are in sliding connection with the sliding rail. The two ends of the sliding rail are respectively provided with a locking structure, the sliding area of the sliding block is limited, the sliding block is locked, and meanwhile, the sliding block is prevented from being separated from the sliding rail. The outer end of the connecting rod is also provided with a through hole, the inner end face of the wing tip movable section is provided with two lugs, the lugs are respectively provided with a through hole, the outer end of the connecting rod is positioned between the two lugs, the second pin shaft 32 sequentially penetrates through the three through holes, the two ends of the second pin shaft 32 are provided with anti-falling pieces, and the second pin shaft 32 is prevented from falling out of the through holes, so that the connection between the connecting rod and the wing tip movable section is completed.

2. Locking design after folding wing tip is received and released

The utility model also provides a locking mode design after the wing tip is retracted and released for the driving design corresponding to the formulas (1 a, c). Figure 2 shows the situation in which the wing tip needs to be locked after being stowed or rotated 90 deg. at the airport under this design. Figure 4 shows the situation when the wing tip is replaced when the aircraft leaves the airport, with the slide rail coincident with the link, in this design.

The boundary between the wing tip movable section and the wing tip fixed section according to the present utility model is in the form of a chamfer, and the direction of the chamfer is the combination direction from the lower airfoil surface to the upper airfoil surface and from the outside to the inside (the outside is the side far from the fuselage), preferably, the angle of the chamfer is 45 ° compared with the vertical direction.

The locking design of the present utility model is shown in fig. 5 and includes the following aspects:

a) The lock mechanism 7 includes a lock driver 77, a return lock bolt 71, a return stopper 73, a rise lock bolt 72, a rise stopper 74, and a lock bolt link 75. The number of the return lock pins 71 and the return stopper 73 is two, and the number of the rise lock pins 72 and the rise stopper 74 is two. The return lock bolt 71 and the return stop block 73 are provided at one end of the slide rail near the actuator, and the rise lock bolt 72 and the rise stop block 73 are provided at one end of the slide rail far from the actuator.

b) Both locking bolts are optimally designed as bending bolts according to the requirements and are hinged inside the wing tip fixing section.

c) The restoring stop block and the erection stop block are fixed at the upper edge and the lower edge of the end part of the sliding rail, and the shape of the restoring stop block and the erection stop block is matched with the locking bolt.

d) The return locking bolt and the cocking locking bolt are connected by a locking bolt connecting rod and then driven by the same locking driver, or can be driven separately by different locking drivers.

e) After the wing tip returns to the original position, the wing tip is locked by restraining the end of the connecting rod to slide through an end return locking bolt and a return stop block, wherein the end of the end close to the actuator, of the sliding rail, and the end return locking bolt is used for locking. The wing tip is locked after being erected, and the end head of the connecting rod is restrained to slide through an end head erection locking bolt and an erection stopping block at the other side of the sliding rail to be locked.

f) The locking driver pulls up the locking bolt connecting rod in the wing tip retracting process, and pushes down the locking bolt connecting rod after the wing tip retracting process is completed. The locking actuator performs the same action regardless of the wing tip being the retraction process.

g) The present utility model provides a driver stop 78 to limit the extension range of the locking actuator. The stop block is fixedly arranged below the locking bolt when the locking bolt is restored to the locking state, and the locking bolt is blocked by the stop block in the lying process, so that the stop is realized.

Realization of locking after folding wing tip is received and released:

on the basis of the above description of the basic design method, further details of implementation on the design are given below by means of a simple 3-dimensional schematic, as shown in fig. 8. The figure, in combination with figures 5 and 7a-c, illustrates the main details of the implementation of the locking design of the present utility model. The return locking bolt 71 and the rising locking bolt 73 have the same structure and comprise a straight line section and a hook section, the straight line section faces upwards in a locking state, the hook section is positioned below the straight line section and is of an integrated fixedly connected structure, the tail end of the hook section is in contact connection with a corresponding stop block, the locking bolt cannot move continuously, and the locking bolt stops the movement of a sliding block on a sliding rail at the moment to play a limiting role. The return stop and the locking stop may be disposed below the slide rail. In the locked state, the hook section of the return locking bolt 71 is located on the side of the return stop block 73 near the actuator, the hook section of the erection locking bolt 72 is located on the side of the erection stop block 74 far away from the actuator, i.e. the hook sections of any locking bolt are all located on the outer sides of the corresponding stop blocks, and the structure is arranged so that the wing tip is in the unfolded state, the wing tip movable section 2 cannot continuously rotate downwards again, and the wing tip is in the erected state, the wing tip movable section cannot continuously rotate upwards again, so that the locking function is realized. When the wing tip is required to be released, the return locking bolt and the erection locking bolt are both moved to a lying state, so that the locking bolt is separated from the stop block, and meanwhile, the locking bolt is separated from the sliding rail and the sliding block on the sliding rail, so that the sliding block is not blocked any more, and the wing tip movable section can be unfolded or erected by sliding. As shown in fig. 8, the two restoring locking bolts are arranged in parallel and fixedly connected with each other, the two rising locking bolts are also arranged in parallel and fixedly connected with each other, the two restoring locking bolts and the two rising locking bolts are fixedly connected by adopting a locking bolt connecting rod, the locking bolt connecting rod is fixedly connected with a locking driver at the same time, under the action of the locking driver, the four locking bolts synchronously move at the same time, and the locking bolts are converted between rising locking and lying and releasing in the moving state.

3. Protection design of the actuation area after the folding wing tip is erected:

in order to prevent the influence of external environmental factors such as sun, dust, rain and snow on the mechanism and system equipment in the opening area around the wing tip rotating shaft after the wing tip is erected, the utility model proposes a built-in follow-up protection plate scheme, as shown in fig. 6a, 6b and 6 c.

The protection design comprises:

a) The protection device comprises a protection plate and a protection plate support rod.

b) In order to minimize interference, the web girder structure inside the wing tip fixing section must be excessively perpendicular to the rotation axis direction. And then eliminating the interference area of the protection plate by forming a strip-shaped opening.

c) The length of the shield cannot exceed the intersection point of the shield with the line connecting the outer end points of the rotating shaft and the sliding rail shown in fig. 6 a. Preferably the same length as the connecting rod.

d) The protection plate and the support rod are fixed on the wing tip fixing section.

By adopting the follow-up protection plate design, the influence of the external environment on the mechanism and equipment in the wing tip can be effectively reduced, and an additional actuating mechanism can not be introduced.

According to the design thought, the specific implementation content of the protection structure comprises:

in the vertical erection state of the wing tip movable section, as shown in fig. 6a, the protection plate is also in the vertical erection state, the top end of the protection plate is fixedly connected with the lower end and the near outer side of the wing tip movable section, the protection plate support rod is in an oblique arrangement state, the top end of the protection plate support rod is fixedly connected with the lower end and the near inner side of the wing tip movable section, the bottom end of the protection plate support rod is fixedly connected with the near bottom end of the protection plate, and the inclined sections of the protection plate, the protection plate support rod and the wing tip movable section form a triangle to play a role in stabilizing. The chamfer here refers to the connection surface of the wing tip movable section and the wing tip fixed section in the unfolded state.

In the horizontal recovery state of the wing tip active section, as shown in fig. 6c, the guard plate 100 is also in a horizontal state because of the fixed connection relationship of the guard plate 100, the guard plate strut 101 and the wing tip active section, the guard plate 100 acts with the action of the wing tip active section. At this time, the protection plate 100 is horizontally positioned inside the wing tip fixing section, specifically, above the wing tip lower wing surface and below the sliding rail.

In the state that the wing tip movable section is in a 45-degree standing state, as shown in fig. 6b, the protection plate moves along with the action of the wing tip movable section due to the fixedly connected relation of the protection plate, the protection plate support rod and the wing tip movable section, so that in the state, the protection plate and the protection plate support rod extend out of the lower wing surface of the wing tip (in order to play an effective protection role, the length of the protection plate is required to be the same as that of the connecting rod, namely, the connecting rod is a Y-shaped connecting rod for supporting the rotation of the wing tip movable section). In the scheme of the utility model, the vertical erection and horizontal extension (return to the original position) of the wing tip movable section belong to target states, and the state between the two target states is a transitional state, so that the protection scheme of the utility model can well solve the protection effect under the two target states, namely the protection of the connecting rod and related parts thereof is realized under the vertical erection state, and under the horizontal extension state, the good protection effect can be also realized due to the matching state between the protection plate and the opening of the lower airfoil surface. Meanwhile, in the two target states, the horizontal extension is in a normalized state, the vertical erection is generally applicable to runway sections with widths which cannot meet the requirements of the aircraft, and belongs to a short-time state.

As a further protection scheme, one or more opening plugging plates can be arranged beside the opening of the lower wing surface, plugging tracks are arranged under each opening plugging plate, and each opening plugging plate moves to the opening of the lower wing surface along the plugging tracks under the driving of power equipment so as to realize plugging of the opening, thereby solving the problem that the opening of the lower wing surface of the wing tip fixing section is not protected in place under the vertical erection state.

The scheme of the utility model is an innovation of a method for locking the folding wing tip of the large-span civil aircraft, can be used for designing the folding wing tip of a large-scale wide passenger plane in the future, is beneficial to greatly reducing the high power output requirement of an actuator at present, and overcomes the technical challenges brought by arranging the high-power actuator in a narrow space of a wing to drive the folding wing tip in the current design. Meanwhile, the scheme of the utility model is also convenient for the protection design of the actuating system of the aircraft in the off-flight state.

The connecting rod type folding wing tip provided by the embodiment of the utility model is described in detail. The above description of embodiments is only for aiding in the understanding of the method of the present utility model and its core ideas; meanwhile, as those skilled in the art will have variations in the specific embodiments and application scope in accordance with the ideas of the present utility model, the present description should not be construed as limiting the present utility model in view of the above.

It should also be noted that the terms "comprises," "comprising," or any other variation thereof, are intended to cover a non-exclusive inclusion, such that a product or system that comprises a list of elements does not include only those elements but may include other elements not expressly listed or inherent to such product or system. Without further limitation, an element defined by the phrase "comprising one … …" does not exclude the presence of other like elements in a commodity or system comprising such elements. By "substantially" is meant that within an acceptable error range, a person skilled in the art is able to solve the technical problem within a certain error range, substantially achieving the technical effect.

The terminology used in the embodiments of the utility model is for the purpose of describing particular embodiments only and is not intended to be limiting of the utility model. As used in this application and the appended claims, the singular forms "a," "an," and "the" are intended to include the plural forms as well, unless the context clearly indicates otherwise. In the present utility model, the terms "upper", "lower", "left", "right", "inner", "outer", "middle", "lateral", "vertical", and the like indicate an azimuth or a positional relationship based on that shown in the drawings. In addition to the above terms may be used to denote orientation or positional relationships, other meanings may be used, such as the term "upper" may also be used in some cases to denote some sort of attachment or connection. The specific meaning of these terms in the present utility model will be understood by those of ordinary skill in the art according to the specific circumstances. The term "and/or" as used herein is merely one association relationship describing the associated object, meaning that there may be three relationships, e.g., a and/or B, may represent: a exists alone, A and B exist together, and B exists alone. In addition, the character "/" herein generally indicates that the front and rear associated objects are an "or" relationship.

Claims

1. A connecting rod type folding wing tip, which is characterized by comprising a wing tip fixing section, a wing tip moving section, a wing tip folding mechanism, a locking mechanism and a protection mechanism;

2. The connecting rod folding wing tip of claim 1, wherein the wing tip folding mechanism comprises a folding rotational hinge assembly, a folding connecting rod, a folding slide rail, and a folding actuator;

3. A connecting rod type folding wing tip according to claim 1, wherein the connection of the wing tip fixing section and the wing tip moving section is in a bevel structure, the included angle between the bevel structure and the positive direction of the x-axis is 135 degrees, and the positive direction of the x-axis is the direction from the fuselage to the wing tip.

4. The connecting rod folding wing tip of claim 2, wherein the folding swivel hinge assembly includes a swivel axis; in a top view state, the rotating shaft is perpendicular to the folding sliding rail, and the intersection point is positioned in the middle of the length direction of the folding sliding rail.

5. The connecting rod type folding wing tip according to claim 2, wherein the folding connecting rod is of a Y-shaped rod body structure, two ends of the folding connecting rod are connected with the folding actuator, and one end is connected with the wing tip movable section.

6. The connecting rod folding wing tip of claim 1, wherein the locking mechanism includes a locking driver, a return lock bolt, a return stop, a cocking lock bolt, and a cocking stop;

7. The connecting rod folding wing tip of claim 6, wherein the return lock pin and the cocking lock pin each comprise a straight section and a hooked section, and the straight section and the hooked section are integrally affixed.

8. The connecting rod folded wing tip of claim 1, wherein the guard mechanism includes a guard plate and a guard plate strut;

9. The connecting rod type folding wing tip according to claim 8, wherein one or more opening plugging plates are arranged on the lower wing surface of the wing tip fixing section, and corresponding plugging tracks are arranged below each opening plugging plate; each opening plugging plate moves towards an opening formed in the lower wing surface along a corresponding plugging track under the driving of plugging power equipment, so that the opening is plugged.

10. An aircraft, wherein the wing of the aircraft has a connecting rod folded wing tip according to any one of claims 1 to 9.