Telescopic wing device and aircraft

Abstract

The invention provides a telescopic wing device and an aircraft, and relates to the technical field of aircraft telescopic wings, the telescopic wing device comprises: an outer wing, the inner part of the outer wing is provided with an accommodating groove with at least one open end; one end of the inner wing is in sliding fit with the outer wing, and the inner wing can be contained in the containing groove; the first elastic component is arranged in the accommodating groove and is connected with one end of the inner wing; the controllable limiting device and the elastic limiting mechanism are arranged in the outer wing, and the controllable limiting device and the elastic limiting mechanism can be matched with the inner wing in a limiting mode and keep the inner wing in a retracted state and an extended state respectively; the problems that a telescopic wing in the prior art has the defects of large size, large mass, high energy consumption, complex structure and the like and is not suitable for aircrafts with small wing sizes and small loads are solved.

Description

Technical Field

[0001] The present invention belongs to the technical field of retractable wings of aircraft, and more specifically, relates to a retractable wing device and an aircraft. Background Art

[0002] Currently, most retractable wings use hydraulic systems or electric servos as actuation systems and have relatively complex guidance and transmission systems. They have disadvantages such as large size, large mass, high energy consumption, and complex structure. They are not suitable for aircraft with smaller wings and less load. Summary of the invention

[0003] The purpose of the present invention is to provide a retractable wing device and an aircraft in view of the deficiencies in the prior art, so as to solve the problem that the retractable wings in the prior art have the disadvantages of large size, large mass, high energy consumption, complex structure, etc., and are not suitable for aircraft with smaller wing size and less load.

[0004] In order to achieve the above object, the present invention provides a telescopic wing device, comprising:

[0005] An outer wing, wherein a receiving groove with at least one end open is provided inside the outer wing;

[0006] An inner wing, one end of which is slidably matched with the outer wing, and the receiving groove is capable of receiving the inner wing;

[0007] a first elastic component, the first elastic component is arranged in the receiving groove and connected to one end of the inner wing;

[0008] A controllable limiter and an elastic limiter mechanism are provided inside the outer wing, and the controllable limiter and the elastic limiter mechanism can cooperate with the inner wing to limit and respectively keep the inner wing in a retracted state and an extended state.

[0009] Optionally, the accommodating groove is in the shape of a straight cylinder, one end of the inner wing is in the shape of a straight column that cooperates with the accommodating groove, and the leading edge of the other end of the inner wing is provided with a swept angle.

[0010] Optionally, a mounting hole is provided inside the inner wing, the first elastic component is partially located in the mounting hole, and the first elastic component is in a compressed state when the inner wing is in a retracted state and in an extended state.

[0011] Optionally, the controllable limiter is a pin puller for aircraft.

[0012] Optionally, the elastic limiting structure includes:

[0013] A sliding hole, the sliding hole is disposed in the outer wing and communicated with the receiving groove;

[0014] a second elastic component, the second elastic component being disposed in the sliding hole;

[0015] A limiting top cap, one end of which is slidably embedded in the sliding hole, and the other end of which extends into the containing groove;

[0016] A limiting hole is provided in the inner wing and is plugged and matched with the limiting top cap.

[0017] Optionally, the sliding hole is a through hole, and an internal thread is provided at one end of the sliding hole away from the accommodating groove. The elastic limiting structure also includes a screw, which cooperates with the internal thread and can be detachably installed in the sliding hole to limit the second elastic component.

[0018] Optionally, a guide structure is further included, and the guide structure includes:

[0019] A guide groove, wherein the guide groove is arranged on a groove wall of the accommodating groove;

[0020] A guide protrusion, wherein the guide protrusion is arranged on two side surfaces of one end of the inner wing, and the guide protrusion is slidably arranged in the guide groove. One end surface of the guide protrusion and a side groove wall of the guide groove form two positioning surfaces, and the two positioning surfaces are in contact when the inner wing is in an extended state.

[0021] Optionally, the guide groove comprises a guide portion and a positioning portion which are connected in sequence, the guide portion is clearance-fitted with the guide protrusion, and the positioning portion is transitionally fit with the guide protrusion.

[0022] Optionally, the guiding portion and the positioning portion are connected via a tapered transition portion.

[0023] The present invention also provides an aircraft, comprising the above-mentioned telescopic wing device.

[0024] The present invention provides a telescopic wing device and an aircraft, which have the following beneficial effects: the telescopic wing device can accommodate an inner wing in an accommodating groove inside an outer wing to achieve the retraction of the inner wing, and in the retracted state of the inner wing, energy is stored by a first elastic component, and a through-hole controllable limiter is used to lock the inner wing to keep the inner wing in a retracted state; when the inner wing is extended, it is only necessary to release the limit on the inner wing by the controllable limiter, and the inner wing can be automatically extended under the action of the first elastic component, and at the same time, it is limited in the extended position by an elastic limit mechanism to maintain the telescopic state of the inner wing; the telescopic wing device adopts a controllable limiter to lock the inner wing in the retracted state, and adopts an elastic limit mechanism to limit the inner wing in the extended state by utilizing elasticity, the structure is simple and compact, the degree of lightweight is high, and it can be suitable for aircraft with small wing size and load.

[0025] Other features and advantages of the present invention will be described in detail in the following detailed description. BRIEF DESCRIPTION OF THE DRAWINGS

[0026] The above and other objects, features and advantages of the present invention will become more apparent through a more detailed description of exemplary embodiments of the present invention in conjunction with the accompanying drawings, wherein like reference numerals generally represent like components throughout the exemplary embodiments of the present invention.

[0027] Figure 1 A three-dimensional structural schematic diagram of a telescopic wing device according to an embodiment of the present invention is shown.

[0028] Figure 2 A schematic structural diagram of an inner wing of a telescopic wing device according to an embodiment of the present invention is shown in a retracted state.

[0029] Figure 3 A schematic structural diagram of an inner wing of a telescopic wing device according to an embodiment of the present invention is shown in the process of extending.

[0030] Figure 4 A schematic structural diagram of an inner wing of a telescopic wing device according to an embodiment of the present invention is shown in an extended state.

[0031] Figure 5 Shows Figure 4 An enlarged schematic diagram of point A.

[0032] Figure 6 Shows Figure 4 An enlarged schematic diagram of point B.

[0033] Figure 7 A schematic diagram of the exploded structure of a guide structure of a telescopic wing device according to an embodiment of the present invention is shown.

[0034] Figure 8 A schematic diagram of a state in which the telescopic wings of an aircraft are retracted is shown.

[0035] Fig. 9 A schematic diagram of a state in which the retractable wings of an aircraft are extended is shown.

[0036] Description of reference numerals:

[0037] 1. Aircraft body; 2. Telescopic wing; 3. Outer wing; 4. Elastic limiting mechanism; 5. Inner wing; 6. First elastic component; 7. Aircraft pin puller; 3-1. First limiting step; 3-2. Positioning part; 3-3. Transition part; 3-4. Guide part; 4-1. Cylindrical screw; 4-2. Second elastic component; 4-3. Limiting top cap; 5-1. Limiting hole; 5-2. Mounting hole; 5-3. Straight columnar structure; 5-4 Second limiting step; 5-5. Guide protrusion. DETAILED DESCRIPTION

[0038] The preferred embodiments of the present invention will be described in more detail below. Although the preferred embodiments of the present invention are described below, it should be understood that the present invention can be implemented in various forms and should not be limited by the embodiments set forth herein. On the contrary, these embodiments are provided to make the present invention more thorough and complete, and to fully convey the scope of the present invention to those skilled in the art.

[0039] like Figures 1 to 4 As shown, the present invention provides a telescopic wing device, comprising:

[0040] The outer wing 3 has a receiving groove with at least one end open inside;

[0041] An inner wing 5, one end of the inner wing 5 is slidably matched with the outer wing 3, and the receiving groove can receive the inner wing 5;

[0042] A first elastic component 6, which is disposed in the receiving groove and connected to one end of the inner wing 5;

[0043] The controllable limiter and the elastic limiter mechanism 4 are arranged inside the outer wing 3, and the controllable limiter and the elastic limiter mechanism 4 can cooperate with the inner wing 5 to limit and keep the inner wing 5 in a retracted state and an extended state respectively.

[0044] Specifically, in order to solve the problem that the telescopic wing in the prior art has the disadvantages of large size, large mass, high energy consumption, and complex structure, and is not suitable for aircraft with small wing size and small load; the telescopic wing device provided by the present invention can accommodate the inner wing 5 in the accommodating groove inside the outer wing 3 to achieve the retraction of the inner wing 5, and store energy through the first elastic component 6 in the retracted state of the inner wing 5, and lock the inner wing 5 through the through-hole controllable limiter to keep the inner wing 5 in the retracted state. When the inner wing 5 is extended, it only needs to release the limit of the inner wing 5 through the controllable limiter, and the inner wing 5 can be automatically extended under the action of the first elastic component 6, and at the same time, it is limited in the extended position by the elastic limiting mechanism 4 to maintain the telescopic state of the inner wing 5; the telescopic wing device adopts a controllable limiter to lock the inner wing 5 in the retracted state, and adopts an elastic limiting mechanism 4 to realize the limit of the inner wing 5 in the extended state by elasticity. It has a simple and compact structure and a high degree of lightweight, and can be suitable for aircraft with small wing size and load.

[0045] Optionally, the accommodating groove is in the shape of a straight cylinder, one end of the inner wing 5 is in the shape of a straight column that matches the accommodating groove, and the leading edge of the other end of the inner wing 5 is provided with a swept angle.

[0046] Specifically, the inner wing 5 cooperates with the groove wall of the straight cylindrical accommodating groove through the straight columnar structure 5 - 3 at one end thereof, thereby providing a certain guiding effect for the extension and retraction of the inner wing 5 .

[0047] Optionally, a mounting hole 5 - 2 is provided inside the inner wing 5 , and a portion of the first elastic component 6 is located in the mounting hole 5 - 2 . When the inner wing 5 is in the retracted state and in the extended state, the first elastic component 6 is in a compressed state.

[0048] Specifically, the first elastic component 6 is compressed to store energy when the inner wing 5 is in the retracted state, so as to provide thrust for the inner wing 5 when it is extended. The first elastic component 6 is still in a compressed state when the inner wing 5 is in the extended state, which can play a certain positioning and stabilizing role for the inner wing and prevent it from shaking in the spanwise direction after it is extended.

[0049] In this embodiment, both ends of the accommodating groove are open, and one end of the first elastic component 6 is in limiting contact with the aircraft.

[0050] In this embodiment, the first elastic component 6 is a spring.

[0051] Optionally, the controllable limiter is a pin puller 7 for an aircraft.

[0052] Specifically, the aircraft pin puller 7 is a pyrotechnic device that receives electrical commands to be actuated. It is initially in an extended state, with its pin portion inserted in a blind hole on the inner wing 5. It receives electrical commands to actuate the pin portion to retract, thereby releasing the lock on the inner wing 5. The aircraft pin puller 7 is used as a controllable limiter, which has a simple and compact structure, is conducive to lightweight design, and is simple and convenient to operate.

[0053] Optionally, the elastic limiting structure includes:

[0054] A sliding hole, which is provided in the outer wing 3 and communicates with the receiving groove;

[0055] A second elastic component 4-2, the second elastic component 4-2 is arranged in the sliding hole;

[0056] A limiting top cap 4-3, one end of which is slidably embedded in the sliding hole, and the other end of which extends into the receiving groove;

[0057] The limiting hole 5-1 is opened in the inner wing 5 and is plugged and matched with the limiting top cap 4-3.

[0058] Specifically, Figure 5 As shown, under the elastic force of the second elastic component 4-2, the limiting top cap 4-3 is in an extended state, and during the extension process of the inner wing 5, the inclined structure formed at the leading edge of the wing by the forward sweep angle of the inner wing 5 is utilized, and the limiting top cap 4-3 and the second elastic component 4-2 are gradually pressed through the extension of the inner wing 5, so that the limiting top cap 4-3 enters the sliding hole, and when the inner wing 5 is extended into place, the limiting top cap 4-3 is aligned with the limiting hole 5-1, and under the action of the second elastic component 4-2, the limiting top cap 4-3 is inserted into the limiting hole 5-1, thereby limiting the leading edge position of the inner wing 5.

[0059] In this embodiment, the second elastic component 4 - 2 is a spring.

[0060] Optionally, the sliding hole is a through hole, and an internal thread is provided at one end of the sliding hole away from the accommodating groove. The elastic limiting structure also includes a screw, which cooperates with the internal thread and can be detachably installed in the sliding hole to limit the second elastic component 4-2.

[0061] Specifically, one end of the sliding hole away from the accommodating groove is blocked by a screw and serves as a limit for one end of the second elastic component 4-2. Such a configuration allows the second elastic component 4-2 to be detachable and reused. For example, when conducting a ground test verification, the screw is unscrewed, the second elastic component 4-2 and the limiting top cap 4-3 are taken out, and the inner wing can be pressed into the accommodating cavity to restore its retracted state.

[0062] In this embodiment, the screw is a cylindrical screw 4-1.

[0063] Optionally, a guiding structure is further included, and the guiding structure includes:

[0064] A guide groove, which is arranged on the groove wall of the receiving groove;

[0065] The guide protrusion 5-5 is arranged on two side surfaces of one end of the inner wing 5, and the guide protrusion 5-5 is slidably arranged in the guide groove. One end surface of the guide protrusion 5-5 and one side groove wall of the guide groove form two positioning surfaces. When the inner wing 5 is in the extended state, the two positioning surfaces are in contact.

[0066] Specifically, Figure 6 As shown, through the sliding cooperation between the guide protrusions 5-5 on both sides of the inner wing 5 and the guide groove, the extension and retraction of the inner wing 5 can be guided at the rear edge of the inner wing 5. At the same time, a first limiting step 3-1 is formed at the groove wall on one side of the guide groove, and a second limiting step 5-4 is formed at one end surface of the guide protrusion 5-5, so as to limit the extended state of the inner wing 5 at the rear edge of the inner wing 5.

[0067] In this embodiment, the guide protrusion 5 - 5 is in the shape of a strip extending along the extending direction of the inner wing 5 .

[0068] Optionally, the guide groove includes a guide portion 3-4 and a positioning portion 3-2 connected in sequence, the guide portion 3-4 is clearance-fitted with the guide protrusion 5-5, and the positioning portion 3-2 is transitionally fit with the guide protrusion 5-5.

[0069] Specifically, Figure 7 As shown, the guide portion 3-4 provides a normal guiding function for the sliding of the inner wing 5 in the accommodating groove. The guide portion 3-4 and the guide protrusion 5-5 on the inner wing 5 are not tightly matched, and a clearance fit is adopted; the positioning portion 3-2 is arranged at the end of the outer wing 3 away from the aircraft. During the extension of the inner wing 5, when the inner wing 5 is about to be extended into place, the guide protrusion 5-5 enters the positioning portion 3-2 which is smaller than the guide portion 3-4, and the positioning portion 3-2 and the guide protrusion 5-5 are more tightly matched, and a transition fit is adopted to reduce the shaking of the inner wing in the extended state.

[0070] Optionally, the guide portion 3 - 4 and the positioning portion 3 - 2 are connected via a tapered transition portion 3 - 3 .

[0071] Specifically, the transition portion 3-3 adopts a tapered structure to provide guidance for the guide protrusion 5-5 to enter the positioning portion 3-2, allowing it to run smoothly.

[0072] like Figure 8 and Fig. 9 As shown, the present invention also provides an aircraft, comprising the above-mentioned retractable wing device.

[0073] Specifically, the aircraft has the above-mentioned retractable wing device, which can effectively reduce the size of the aircraft envelope space. It uses a spring as power and controls its deployment timing through the aircraft pin puller 7. It has the characteristics of simple and reliable structure, small size, and light weight. It is suitable for aircraft with small wing size and light load.

[0074] In this embodiment, the above-mentioned telescopic wing device can adopt a modular design, the inner wing 5 and the outer wing 3 form a telescopic wing 2, and an ear structure is set at the root of the outer wing 3, which is directly installed on the surface of the aircraft body 1 through the ear structure. It is easy to disassemble and assemble and has a wide range of application scenarios.

[0075] The embodiments of the present invention have been described above, and the above description is exemplary, not exhaustive, and is not limited to the disclosed embodiments. Many modifications and changes will be apparent to those skilled in the art without departing from the scope and spirit of the described embodiments.

Claims

1. A telescopic wing device, characterized in that: include: An outer wing, wherein a receiving groove with at least one end open is provided inside the outer wing; An inner wing, one end of which is slidably matched with the outer wing, and the receiving groove is capable of receiving the inner wing; a first elastic component, the first elastic component is arranged in the receiving groove and connected to one end of the inner wing; A controllable limiter and an elastic limiter mechanism are provided inside the outer wing, and the controllable limiter and the elastic limiter mechanism can cooperate with the inner wing to limit and respectively keep the inner wing in a retracted state and an extended state.

2. The telescopic wing device according to claim 1, characterized in that: The receiving groove is in the shape of a straight cylinder, one end of the inner wing is in the shape of a straight column matched with the receiving groove, and the leading edge of the other end of the inner wing is provided with a swept angle.

3. The telescopic wing device according to claim 1, characterized in that: A mounting hole is provided inside the inner wing, and a portion of the first elastic component is located in the mounting hole. When the inner wing is in a retracted state or in an extended state, the first elastic component is in a compressed state.

4. The telescopic wing device according to claim 1, characterized in that: The controllable limiter is a pin puller for an aircraft.

5. The telescopic wing device according to claim 1, characterized in that: The elastic limiting structure comprises: A sliding hole, the sliding hole is disposed in the outer wing and communicated with the receiving groove; a second elastic component, the second elastic component being disposed in the sliding hole; A limiting top cap, one end of which is slidably embedded in the sliding hole, and the other end of which extends into the containing groove; A limiting hole is provided in the inner wing and is plugged and matched with the limiting top cap.

6. The telescopic wing device according to claim 5, characterized in that: The sliding hole is a through hole, and an internal thread is provided at one end of the sliding hole away from the accommodating groove. The elastic limiting structure also includes a screw, which cooperates with the internal thread and can be detachably installed in the sliding hole to limit the second elastic component.

7. The telescopic wing device according to claim 1, characterized in that: Also included is a guide structure, the guide structure comprising: A guide groove, wherein the guide groove is arranged on a groove wall of the accommodating groove; A guide protrusion, wherein the guide protrusion is arranged on two side surfaces of one end of the inner wing, and the guide protrusion is slidably arranged in the guide groove. One end surface of the guide protrusion and a side groove wall of the guide groove form two positioning surfaces, and the two positioning surfaces are in contact when the inner wing is in an extended state.

8. The telescopic wing device according to claim 7, characterized in that: The guide groove comprises a guide portion and a positioning portion which are connected in sequence, the guide portion is clearance-matched with the guide protrusion, and the positioning portion is transitionally matched with the guide protrusion.

9. The telescopic wing device according to claim 8, characterized in that: The guide portion and the positioning portion are connected via a tapered transition portion.

10. An aircraft, characterized in that: The telescopic wing device comprises the telescopic wing device according to any one of claims 1 and 9.

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