Folding wing of aircraft

Abstract

The utility model provides a folding wing of an aircraft, comprising: a seat plate for being fixed on the aircraft; the first wing and the second wing are respectively hinged to the seat plate; the driving device is arranged on the seat plate and is used for providing power; the first end of the transmission part is connected with the driving device, and the second end of the transmission part is hinged to one side of each wing; the locking pieces are arranged on the seat plate and the wings and are used for locking the wings; the cover plate is mounted on one side, deviating from the seat plate, of each wing, and the cover plate is connected with the seat plate. The driving device, the initial locking piece, the in-place locking piece and the like of the folding wing can be replaced, the wing and the seat plate are fixed firmly, meanwhile, the driving device and the locking pieces are simple, the reliability is relatively easy to control and guarantee, the structural function and performance can be guaranteed after quick-wear parts are disassembled and replaced many times, and the folding wing is suitable for being popularized and applied. And thus, the use cost of single wing unfolding can be reduced.

Description

Technical Field

[0001] The utility model belongs to the technical field of aircraft, and in particular relates to a folding wing of an aircraft. Background Art

[0002] After searching the prior art, it was found that the Chinese invention patent publication number CN116718080A discloses a large aspect ratio longitudinal folding wing locking and unlocking device, which integrates multiple functions such as initial locking and unlocking of the wing, driving movement and locking in place. However, this structure is not conducive to multiple uses. The initial folding lock, unfolding lock in place and buffer structure are not easy to replace and install, and the locking torque is small, and the aerodynamic force that the wing can bear is small. The piston device and the piston cylinder have the driving, locking and sealing functions at the same time. The structure is relatively complex, and the reliability control of the locking and sealing structure is a difficult point. Summary of the invention

[0003] In view of this, the purpose of the utility model is to provide a folding wing of an aircraft to solve the problems in the prior art that the wing is not easy to replace and install during initial folding and locking, unfolding and locking, and the buffer structure is not easy to replace and install, and the locking torque is small, and the aerodynamic force that the wing can bear is small. The piston device and the piston cylinder have the driving, locking and sealing functions at the same time, the structure is relatively complex, and the reliability of the locking and sealing structure is poor.

[0004] The present application provides a folding wing of an aircraft, comprising:

[0005] A seat plate, used for fixing on the aircraft;

[0006] a first wing and a second wing, each wing being hinged to the seat plate;

[0007] A driving device, which is arranged on the seat plate and is used to provide power;

[0008] A transmission member, a first end of which is connected to the driving device, and a second end of which is hinged to one side of each wing;

[0009] A locking member, which is arranged on the seat plate and each of the wings and is used to lock each of the wings;

[0010] A cover plate is mounted on a side of each wing away from the seat plate, and the cover plate is connected to the seat plate.

[0011] Furthermore, the driving device comprises:

[0012] A sleeve, which is arranged on the seat plate;

[0013] a spring coaxially disposed at a first end within the sleeve;

[0014] A piston is coaxially arranged in the sleeve, and the extended end of the piston is coaxially arranged in the spring and passes through the first end of the sleeve.

[0015] Furthermore, two mounting plates are arranged on the seat plate, and the driving device is installed between the two mounting plates.

[0016] Furthermore, the transmission member comprises:

[0017] A guide member, which is disposed on the seat plate, wherein a first end of the guide member is connected to the driving device;

[0018] Connecting rods, the first ends of the two connecting rods are hinged to the guide member, and the second end of each connecting rod is hinged to one of the wings.

[0019] Furthermore, the guide member comprises:

[0020] A mounting seat, which is arranged on the seat plate;

[0021] Guide rods, two of which are arranged in parallel on the mounting seat;

[0022] The sliding beam is slidably arranged on the two guide rods and is respectively hinged to the first end of each connecting rod.

[0023] Furthermore, each of the wings comprises:

[0024] A mounting portion, used for mounting between the seat plate and the cover plate;

[0025] The wingspan portion is an integral structure with the mounting portion, and the wingspan portion can rotate around a point of the mounting portion.

[0026] Furthermore, the installation portion includes:

[0027] A first through hole, which is used to be sleeved on the mounting shaft so that the wing can rotate around the mounting shaft;

[0028] A second through hole, which is used to install an initial locking member, wherein the initial locking member is used to lock the wing in an initial folding state;

[0029] A third through hole is used to install a locking member in place, wherein the locking member in place is used to adjust the wing to an unfolded or folded state;

[0030] An ear seat is arranged on one side of the mounting portion, and the ear seat is hinged to the second end of the transmission member.

[0031] Further, the first wing and the second wing are respectively hinged to the seat plate via a mounting shaft;

[0032] Both ends of the mounting shaft are fixed on the seat plate and the cover plate.

[0033] Furthermore, the first end of the mounting shaft is provided with a first end cover, and the second end thereof is provided with a threaded hole along its axial direction, the threaded hole is used to install an adapted bolt, and the tail end of the bolt is provided with a second end cover consistent with the first end cover;

[0034] Each of the end covers is fixed to the seat plate and the cover plate via a pressure ring, and the inner diameter of each of the pressure rings is smaller than the outer diameter of each of the end covers.

[0035] Further, the locking member includes an initial locking member and an in-position locking member;

[0036] The initial locking member connects each of the wings and the seat plate, the initial locking member is a wearing part, and each of the initial locking members is disconnected under the action of the driving device;

[0037] The locking member in place includes a threaded member, a spring and a fixing pin connected in sequence. The locking member in place is installed on each wing via the threaded member. Each wing moves to the position of the limiting hole on the seat plate corresponding to the fixing pin under the driving device. The fixing pin extends into the limiting hole under the action of the spring to lock the wing.

[0038] The beneficial effects of this application are:

[0039] The present application provides a folding wing for an aircraft, wherein the wing drive device, initial locking member, in-position locking member, etc. can all be replaced, thus solving the problem that the initial folding, unfolding in-position locking, and buffer structure of the wing are difficult to replace. The wing is fixed to the seat plate more firmly, and the in-position locking member has a large locking torque, thus solving the problem that the wing has a small in-position locking torque and the wing is difficult to withstand large aerodynamic loads during flight. At the same time, the drive device and the locking member have simple structures, the spring buffers the piston, and the reliability is relatively easy to control and ensure, especially after multiple disassembly and replacement of wearing parts, the structural function and performance can be guaranteed, thereby reducing the cost of a single wing deployment. BRIEF DESCRIPTION OF THE DRAWINGS

[0040] The above and other objects, features and advantages of the present invention will become more apparent through the following description of the embodiments of the present invention with reference to the accompanying drawings.

[0041] Figure 1 It is a schematic diagram of the axial structure of the wing in a folded state provided according to an embodiment of the utility model;

[0042] Figure 2 According to the embodiment of the present utility model Figure 1 Bottom view of

[0043] Figure 3It is a partial structural schematic diagram of a wing in an unfolded state provided according to an embodiment of the utility model;

[0044] Figure 4 It is a schematic diagram of a partial structure from another perspective in a wing-expanded state according to an embodiment of the utility model;

[0045] Figure 5 It is a partial cross-sectional view of a wing in a folded state according to an embodiment of the utility model;

[0046] Figure 6 A partial cross-sectional view of a wing in an unfolded state according to an embodiment of the utility model.

[0047] Among them, 1-seat plate, 2-driving device, 3-cover plate, 4-first wing, 5-second wing, 6-transmission member, 7-mounting plate, 8-mounting seat, 9-guide rod, 10-sliding beam, 11-connecting rod, 12-mounting shaft, 13-in-place locking member, 14-ear seat, 15-pressure ring, 16-initial locking member;

[0048] 21-sleeve, 22-piston, 23-spring. DETAILED DESCRIPTION

[0049] Various embodiments of the present invention will be described in more detail below with reference to the accompanying drawings. In each of the accompanying drawings, the same elements are represented by the same or similar reference numerals. For the sake of clarity, the various parts in the accompanying drawings are not drawn to scale.

[0050] refer to Figures 1 to 6 The present application provides a folding wing of an aircraft, comprising: a seat plate 1, used to be fixed on the aircraft; a first wing 4 and a second wing 5, each of which is hinged on the seat plate 1; a driving device 2, which is arranged on the seat plate 1 and is used to provide power; a transmission member 6, a first end of which is connected to the driving device 2, and a second end of which is respectively hinged to one side of each wing; a locking member, which is arranged on the seat plate 1 and each of the wings and is used to lock each of the wings; a cover plate 3, which is installed on a side of each of the wings away from the seat plate 1, and the cover plate 3 is connected to the seat plate 1.

[0051] In this embodiment, the seat plate 1 is used to be fixed on the aircraft, the cover plate 3 is connected to the seat plate 1, the first wing 4 and the second wing 5 are both arranged between the seat plate 1 and the cover plate 3, and a mounting shaft 12 is connected between the seat plate 1 and the cover plate 3, and both ends of the mounting shaft 12 are respectively installed on the seat plate 1 and the cover plate 3.

[0052] The driving device 2 and the transmission member 6 are both installed between the cover plate 3 and the seat plate 1. The driving device 2 is connected to the aircraft driving source, so that the driving device 2 drives the transmission member 6, and the transmission member 6 drives the wing to move, so that the wing is unfolded, and is locked by the locking member to ensure that the wing is in an unfolded state. As those skilled in the art should understand, the wing is initially in a folded state, and the wing is in an unfolded state through the action of the driving device 2. The initial folded state in this embodiment is locked by the locking member, thereby ensuring that the wing is in a folded state.

[0053] In this embodiment, reference Figure 2 , Figure 3 and Figure 5 The driving device 2 includes: a sleeve 21, which is arranged on the seat plate 1; a spring 23, which is coaxially arranged at the first end of the sleeve 21; a piston 22, which is coaxially arranged in the sleeve 21, and the extended end of the piston 22 is coaxially arranged in the spring 23 and passes through the first end of the sleeve 21.

[0054] Two mounting plates 7 are provided on the base plate 1, and the driving device 2 is installed between the two mounting plates 7. The driving device 2 is fixed by the two mounting plates 7. Under the action of the driving source, the piston 22 in the driving device 2 moves toward the first end of the sleeve 21 with the spring 23, and the spring 23 can play a role of shock absorption and buffering for the piston 22.

[0055] The transmission member 6 includes: a guide member, which is arranged on the seat plate 1, and the first end of the guide member is connected to the driving device 2; a connecting rod 11, the first ends of two connecting rods 11 are hinged to the guide member, and the second end of each connecting rod 11 is hinged to one of the wings.

[0056] refer to Figure 3 and Figure 4 The guide member includes: a mounting seat 8, which is arranged on the seat plate 1; a guide rod 9, two guide rods 9 are arranged in parallel on the mounting seat 8; a sliding beam 10, which can be slidably arranged on the two guide rods 9 and is respectively hinged to the first end of each connecting rod 11.

[0057] The mounting seat 8 is fixed on the seat plate 1, and the guide rod 9 guides the sliding beam 10. The extended end of the piston 22 of the driving device 2 causes the sliding beam 10 to slide along the guide rod 9, and the sliding beam 10 pushes each connecting rod 11, and each connecting rod 11 further pushes each wing.

[0058] In this embodiment, each wing includes: a mounting portion for mounting between the seat plate 1 and the cover plate 3; and a wing span portion which is an integral structure with the mounting portion, and the wing span portion can rotate around a point of the mounting portion.

[0059] The mounting portion includes: a first through hole, which is used to be sleeved on the mounting shaft 12 so that the wing can rotate around the mounting shaft 12; a second through hole, which is used to install an initial locking member 16, and the initial locking member 16 is used to lock the initial folding state of the wing; a third through hole, which is used to install a position locking member 13, and the position locking member 13 is used to adjust the wing to the unfolded and folded state; an ear seat 14, which is arranged on one side of the mounting portion, and the ear seat 14 is hinged to the second end of the transmission member 6.

[0060] It should be understood that through holes or limit holes corresponding to the first through hole, the second through hole and the third through hole are opened on the seat plate 1, and a through hole corresponding to the first through hole is opened on the cover plate 3. The seat plate 1 and the cover plate 3 are also connected by a number of bolts to achieve fixation of the two.

[0061] The two ends of the installation shaft 12 are fixed on the seat plate 1 and the cover plate 3. The first end of the installation shaft 12 is provided with a first end cover, and the second end thereof is provided with a threaded hole along its axial direction, the threaded hole is used to install an adapted bolt, and the tail end of the bolt is provided with a second end cover consistent with the first end cover; each of the end covers is respectively fixed to the seat plate 1 and the cover plate 3 via a pressure ring 15, and the inner diameter of each pressure ring 15 is smaller than the outer diameter of each end cover. The pressure ring 15 is fixed to the seat plate 1 and the cover plate 3 via bolts, and each end cover is connected to the pressure ring 15 via a plurality of bolts.

[0062] refer to Figure 3 and Figure 4 The locking member includes an initial locking member 16 and an in-position locking member 13; the initial locking member 16 connects each wing with the seat plate 1, and the initial locking member 16 is a wearing member. Each initial locking member 16 is disconnected under the action of the driving device 2. After the initial locking member 16 is disconnected, each wing rotates around its own mounting shaft 12 under the action of the transmission member 6. The in-position locking member 13 includes a threaded member, a spring and a fixing pin connected in sequence. The in-position locking member 13 is installed on each wing through the threaded member. Each wing moves to the position of the limiting hole on the seat plate 1 corresponding to the fixing pin under the driving device 2. The fixing pin extends into the limiting hole under the action of the spring to lock the wing.

[0063] The threaded part is provided with an external thread corresponding to the third through hole, and a flat or cross groove is provided at the end of the threaded part, which is convenient for installation and removal with a practical screwdriver. After the threaded part is installed in the third through hole, it should be flush with the wing surface, the fixing pin is in the third through hole, and the spring is in a compressed state. When the wing rotates, the fixing pin rotates to the position of the limit hole opened on the seat plate 1, and the spring releases energy to tighten the fixing pin into the limit hole. The fixing pin fixes each wing relative to the seat plate 1.

[0064] In an optional embodiment, a limiting member is provided on the seat plate 1. When the wing is unfolded, the limiting member limits the unfolding of the wing so that the wing is fully unfolded. Correspondingly, the fixing pin is opposite to the limiting hole, and the fixing pin extends into the limiting hole of the seat plate 1 to fix the wing.

[0065] In an optional embodiment, a guiding arc groove is provided on the seat plate 1 on the path corresponding to the rotation of the fixing pin, and the arc groove is connected to the limit hole. During the rotation and unfolding of the wing, the fixing pin slides in the arc groove and finally extends into the limit hole, thereby fixing the wing to the seat plate 1.

[0066] It is understandable that the strength of the fixing pin should be sufficient to lock the wing when it is in the unfolded state.

[0067] The present application provides a folding wing of an aircraft, wherein the wing drive device 2, initial locking member 16, in-position locking member 13, etc. can all be replaced, solving the problem that the initial and in-position locking and buffering structures of the wing deployment are difficult to replace. The wing is fixed to the seat plate 1 more firmly, and the in-position locking member 13 has a large locking torque, solving the problem that the wing has a small in-position locking torque and the wing is difficult to withstand a large aerodynamic load during flight. At the same time, the drive device 2 and the locking member are simple, and the spring 23 has a buffering effect on the piston. The reliability is relatively easy to control and ensure, especially after multiple disassembly and replacement of wearing parts, the structural function and performance can be guaranteed, thereby reducing the use cost of a single wing deployment.

[0068] It should be noted that, in this article, relational terms such as first and second, etc. are only used to distinguish one entity or operation from another entity or operation, and do not necessarily require or imply any such actual relationship or order between these entities or operations. Moreover, the terms "include", "comprise" or any other variants thereof are intended to cover non-exclusive inclusion, so that a process, method, article or device including a series of elements includes not only those elements, but also other elements not explicitly listed, or also includes elements inherent to such process, method, article or device. In the absence of further restrictions, the elements defined by the statement "comprise a ..." do not exclude the presence of other identical elements in the process, method, article or device including the elements.

[0069] Finally, it should be noted that: Obviously, the above embodiments are only examples for clearly explaining the present invention, and are not intended to limit the implementation methods. For ordinary technicians in the relevant field, other different forms of changes or modifications can be made based on the above description. It is not necessary and impossible to list all the implementation methods here. The obvious changes or modifications derived from this are still within the scope of protection of the present invention.

Claims

1. A folding wing of an aircraft, characterized in that: include: A seat plate, used for fixing on the aircraft; a first wing and a second wing, each wing being hinged to the seat plate; A driving device, which is arranged on the seat plate and is used to provide power; A transmission member, a first end of which is connected to the driving device, and a second end of which is hinged to one side of each wing; A locking member, which is arranged on the seat plate and each of the wings and is used to lock each of the wings; A cover plate, which is mounted on a side of each wing away from the seat plate, and the cover plate is connected to the seat plate; Wherein, the transmission member comprises: A guide member, which is disposed on the seat plate, wherein a first end of the guide member is connected to the driving device; Connecting rods, the first ends of the two connecting rods are hinged to the guide member, and the second end of each connecting rod is hinged to one of the wings.

2. The folding wing of an aircraft according to claim 1, characterized in that: The driving device comprises: A sleeve, which is arranged on the seat plate; a spring coaxially disposed at a first end within the sleeve; A piston is coaxially arranged in the sleeve, and the extended end of the piston is coaxially arranged in the spring and passes through the first end of the sleeve.

3. The folding wing of an aircraft according to claim 1, characterized in that: The seat plate is provided with two mounting plates, and the driving device is mounted between the two mounting plates.

4. The folding wing of an aircraft according to claim 1, characterized in that: The guide member comprises: A mounting seat, which is arranged on the seat plate; Guide rods, two of which are arranged in parallel on the mounting seat; The sliding beam is slidably arranged on the two guide rods and is respectively hinged to the first end of each connecting rod.

5. The folding wing of an aircraft according to claim 1, characterized in that: Each of the wings comprises: A mounting portion, used for mounting between the seat plate and the cover plate; The wingspan portion is an integral structure with the mounting portion, and the wingspan portion can rotate around a point of the mounting portion.

6. The folding wing of an aircraft according to claim 5, characterized in that: The installation part comprises: A first through hole, which is used to be sleeved on the mounting shaft so that the wing can rotate around the mounting shaft; A second through hole, which is used to install an initial locking member, wherein the initial locking member is used to lock the wing in an initial folding state; A third through hole is used to install a locking member in place, wherein the locking member in place is used to adjust the wing to an unfolded or folded state; An ear seat is arranged on one side of the mounting portion, and the ear seat is hinged to the second end of the transmission member.

7. The folding wing of an aircraft according to claim 1, characterized in that: The first wing and the second wing are respectively hinged to the seat plate via a mounting shaft; Both ends of the mounting shaft are fixed on the seat plate and the cover plate.

8. The folding wing of an aircraft according to claim 7, characterized in that: The first end of the mounting shaft is provided with a first end cover, and the second end thereof is provided with a threaded hole along its axial direction, the threaded hole is used to install an adapted bolt, and the tail end of the bolt is provided with a second end cover consistent with the first end cover; Each of the end covers is fixed to the seat plate and the cover plate via a pressure ring, and the inner diameter of each of the pressure rings is smaller than the outer diameter of each of the end covers.

9. The folding wing of an aircraft according to claim 1, characterized in that: The locking member comprises an initial locking member and an in-position locking member; The initial locking member connects each of the wings and the seat plate, the initial locking member is a wearing part, and each of the initial locking members is disconnected under the action of the driving device; The locking member in place includes a threaded member, a spring and a fixing pin connected in sequence. The locking member in place is installed on each wing via the threaded member. Each wing moves to the position of the limiting hole on the seat plate corresponding to the fixing pin under the driving device. The fixing pin extends into the limiting hole under the action of the spring to lock the wing.

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