Folding structure of wing
By designing the wing structure of the symmetrical folded part in the aircraft, combining positioning parts, limiting parts and elastic parts, the problems of complex and cost in the folding wing test structure in the prior art are solved, and the stability of static and dynamic experiments is achieved and reliability, simplifying operations and reducing costs.
Patent Information
- Application Number
- CN202421142051.3
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- Filing Date
- 2024-05-23
- Publication Date
- 2024-12-24
- Estimated Expiration
- 2034-05-23
AI Technical Summary
In the prior art, the deployment performance test method of the aircraft folding wing has complex structure, high cost and is difficult to meet the needs of static experiments and dynamic experiments at the same time, resulting in inconvenient experimental operation.
A wing structure including a symmetric folding part is designed, using a combination of positioning members, limiting members and elastic members to achieve stable folding and deployment of the wings through solenoid valves and bearings, simplifying the structure and reducing costs.
It realizes stability and reliability that can be met in both static and dynamic experiments, improves the reliability and operational convenience of the experiments, reduces costs, and has a wide range of applications.
Smart Images
Figure CN222224418U_ABST
Abstract
Description
Technical Field
[0001] The present application relates to the technical field of aircraft folding wing testing, and in particular to a folding structure of a wing. Background Art
[0002] The folding wings of an aircraft are one of the important factors to improve the performance and practicality of the aircraft. Therefore, it is very necessary to test its deployment performance. The folding wings of an aircraft need to meet certain requirements during the deployment process, including the deployment speed, deployment accuracy, deployment stability, deployment force, and deployment reliability. At the same time, the operation of the equipment during the deployment process also needs to have sufficient reliability and accuracy. In the design process of an aircraft with folding wings, the deployment performance of the folding wings should be fully considered, and it is necessary to verify through experiments whether it meets the design requirements.
[0003] The performance test of the folding wing of an aircraft usually includes two methods: static test and dynamic test. In the actual design and test of an aircraft, a combination of static test and dynamic test is generally used to test the performance of the folding wing.
[0004] Static experiments are mainly used to test the accuracy and stability of the folding wings of an aircraft. Using experimental equipment, the aircraft's wings are spread to a certain angle through manual or automatic control. The accuracy of the wings is tested by measuring the angle after the wings are spread, and even the tension of the wire rope, to test the accuracy and stability of the wings. In static tests, it is also necessary to record the status and position of each component after the wings are spread in detail and conduct structural analysis. This test method can test the static performance of the folding wings, but it has certain limitations for testing dynamic performance.
[0005] Dynamic experiments are mainly used to test the speed, strength and reliability of the folding wings of an aircraft. In dynamic experiments, common methods include using test aircraft or static test equipment to simulate the unfolding process of the folding wings during flight, and recording the unfolding speed, acceleration, angle and unfolding time. In practice, dynamic experiments focus on testing its operability and durability, which has a good guiding significance for the dynamic performance test of the folding wings. However, the current dynamic tests are also complex in structure and high in cost.
[0006] However, the folding structure in the prior art is complex and inconvenient to operate in order to meet the needs of both static and dynamic experiments. Utility Model Content
[0007] Based on this, it is necessary to provide a wing folding structure to address the above technical problems, which can meet the needs of both static and dynamic experiments and has a simple structure and is easy to operate.
[0008] A folding structure of a wing, comprising: two symmetrically arranged folding parts, wherein the folding parts comprise: a fuselage member connected to a fuselage, a wing member connected to a wing, a connecting member connected to the wing member, a power member connected to the connecting member, and two sets of positioning members;
[0009] The wing member is fixedly connected to the connecting member, and the connecting member is rotatably connected to the fuselage member, so that the connecting member rotates relative to the fuselage member under the drive of the power member, and the wing member and the connecting member are linked, so that the wing member has a folded state, a rotated state and an unfolded state;
[0010] One group of positioning members connects the fuselage member and the connecting member, and another group of positioning members connects the fuselage member and the wing member; the positioning points of the two groups of positioning members and the connection points between the wing member and the connecting member form a triangular structure.
[0011] In one embodiment, each set of positioning members includes: positioning pins and positioning slots, wherein the positioning pins correspond to the positioning slots one by one; the positioning pins enter the corresponding positioning slots from the outside to form positioning points;
[0012] In a set of positioning members, the positioning pin is provided on the body member or the connecting member, and the positioning slot is provided on the connecting member or the body member;
[0013] In another set of positioning members, the positioning pins are arranged on the fuselage member or the wing member, and the positioning grooves are arranged on the wing member or the fuselage member.
[0014] In one embodiment, the positioning pin is a cylindrical structure, and the positioning groove is a semi-hole structure with an opening facing the moving direction of the cylindrical structure.
[0015] In one embodiment, the opening directions of the two positioning grooves are perpendicular.
[0016] In one embodiment, the positioning pin is a columnar structure, and the positioning groove is a hole-shaped structure whose cross section matches the columnar structure.
[0017] In one embodiment, the folding portion further comprises: a limiting member; the limiting member comprises: a limiting valve provided on the body member and two limiting grooves provided on the connecting member;
[0018] Before and after the connecting member rotates relative to the fuselage member, the limit valves respectively cooperate with different limit grooves to form limit points to correspond to the folding state or unfolding state of the wing member.
[0019] In one embodiment, the limit valve is a solenoid valve; the solenoid valve comprises a valve core and a valve body, the valve core is connected to the valve body and can pop out and retract relative to the valve body;
[0020] The valve body is fixedly connected to the fuselage member. When the valve core is aligned with the limiting groove, it is in a pop-up state, corresponding to the folding state or unfolding state of the wing member. Otherwise, the valve core is in a retracted state, corresponding to the rotation state of the wing member.
[0021] In one embodiment, when the wing is in a folded state, the connection point, the positioning point and the limit point of the wing member and the connecting member are collinear and parallel to the direction of the wing;
[0022] When the wing is in an unfolded state, the connection point, the positioning point and the limiting point of the wing member and the connecting member form a triangular structure.
[0023] In one embodiment, the folding portion further comprises: an elastic member; the elastic member comprises more than one spring;
[0024] One corresponding end of the spring is connected to the fuselage member, and the other corresponding end is connected to the wing member.
[0025] In one embodiment, the connecting member is rotatably connected to the fuselage member via a bearing.
[0026] The above-mentioned folding structure of a wing is provided with symmetrical folding parts, each folding part is provided with a connecting part connecting the fuselage part and the wing part, and two groups of positioning parts are provided. The positioning groove of the positioning part can select a semi-hole structure or a hole structure, and can also be combined with an electromagnetic valve. It can form a stable structure while meeting the needs of static experiments and dynamic experiments at the same time, improve the reliability of the experiment, further provide a limit part and an elastic part, increase the fixing points, further improve the reliability, and the structure is simple, easy to implement, low cost, and wide range of applications. BRIEF DESCRIPTION OF THE DRAWINGS
[0027] Figure 1 is a three-dimensional schematic diagram of a folding structure of a wing in one embodiment;
[0028] Figure 2 is a top view of a folding structure of a wing in one embodiment;
[0029] Figure 3 It is an enlarged view of the details of the folding structure of a wing in one embodiment.
[0030] Reference numerals:
[0031] Fuselage part 1;
[0032] Wing piece 2;
[0033] Connector 3;
[0034] Positioning member 4, positioning pin 41, positioning groove 42;
[0035] Limiting member 5, limiting valve 51, limiting groove 52;
[0036] Connection point A, positioning point B, limit point C. DETAILED DESCRIPTION
[0037] In order to make the purpose, technical solutions and advantages of the present application more clearly understood, the present application is further described in detail below in conjunction with the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are only used to explain the present application and are not intended to limit the present application. Based on the embodiments in the present application, all other embodiments obtained by ordinary technicians in the field without making creative work are within the scope of protection of the present application.
[0038] It should be noted that all directional indications in the embodiments of the present application (such as up, down, left, right, front, back, etc.) are only used to explain the relative position relationship, movement status, etc. between the components under a certain specific posture (as shown in the accompanying drawings). If the specific posture changes, the directional indication will also change accordingly.
[0039] In addition, the descriptions of "first", "second", etc. in this application are only for descriptive purposes and cannot be understood as indicating or implying their relative importance or implicitly indicating the number of the indicated technical features. Therefore, the features defined as "first" or "second" may explicitly or implicitly include at least one of the features. In the description of this application, "multiple groups" means at least two groups, such as two groups, three groups, etc., unless otherwise clearly and specifically defined.
[0040] In this application, unless otherwise clearly specified and limited, the terms "connection", "fixation", etc. should be understood in a broad sense. For example, "fixation" can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection, an electrical connection, a physical connection, or a wireless communication connection; it can be a direct connection, or an indirect connection through an intermediate medium, or it can be the internal connection of two elements or the interaction relationship between two elements, unless otherwise clearly defined. For ordinary technicians in this field, the specific meanings of the above terms in this application can be understood according to specific circumstances.
[0041] In addition, the technical solutions between the various embodiments of the present application can be combined with each other, but it must be based on the fact that ordinary technicians in the field can implement it. When the combination of technical solutions is contradictory or cannot be implemented, it should be deemed that such combination of technical solutions does not exist and is not within the scope of protection required by this application.
[0042] The present application provides a folding structure of a wing, such as Figures 1 to 3As shown, in one embodiment, it includes: two folding parts, and the two folding parts are axially symmetrically distributed about the center line of the aircraft. That is to say, the structures of the two folding parts are the same, and the following description takes one folding part as an example.
[0043] Each folding part comprises: a fuselage part, a wing part, a connecting part, a power part and a positioning part.
[0044] The fuselage piece is connected to the fuselage and has a plate-like structure.
[0045] The wing piece is connected to the wing and is a plate-like structure.
[0046] The connecting member is connected to the fuselage member, the wing member and the power member at the same time, wherein the connecting member is rotationally connected to the fuselage member (for example, through a bearing), fixedly connected to the wing member, and rotationally connected to the power member. The connecting member rotates relative to the fuselage member under the drive of the power member, and the wing member and the connecting member are linked, so that the wing member has a folded state, a rotated state and an unfolded state.
[0047] The power member is connected to the fuselage member and the connecting member at the same time, wherein the power member is fixedly connected to the fuselage member and is rotationally connected to the connecting member.
[0048] There are two groups of positioning parts, one group of positioning parts connects the fuselage parts and the connecting parts, and the other group of positioning parts connects the fuselage parts and the wing parts; the positioning points of the two groups of positioning parts and the connection points between the wing parts and the connecting parts form a triangular structure to form a stable state.
[0049] Among them, each group of positioning parts includes: positioning pins and positioning slots, the positioning pins and the positioning slots correspond one to one; the positioning pins enter the corresponding positioning slots from the outside to form positioning points (the positioning points are the positions where the positioning pins and the positioning slots cooperate, and there are two positioning points in total); in one group of positioning parts, the positioning pins are arranged on the fuselage parts or the connecting parts, and the positioning slots are arranged on the connecting parts or the fuselage parts, that is, if the positioning pins are arranged on the fuselage parts, then the positioning slots are arranged on the connecting parts, and if the positioning pins are arranged on the connecting parts, then the positioning slots are arranged on the fuselage parts; in another group of positioning parts, the positioning pins are arranged on the fuselage parts or the wing parts, and the positioning slots are arranged on the wing parts or the fuselage parts, that is, if the positioning pins are arranged on the fuselage parts, then the positioning slots are arranged on the wing parts, and if the positioning pins are arranged on the wing parts, then the positioning slots are arranged on the fuselage parts.
[0050] In one embodiment, the positioning pin is a cylindrical structure, the positioning groove is a semi-hole structure with an opening facing the moving direction of the cylindrical structure, and the positioning pin is parallel to the axial direction of the positioning groove.
[0051] Preferably, the opening directions of the two positioning grooves are perpendicular to each other so as to form positioning in different directions.
[0052] In one embodiment, the positioning pin is a columnar structure, and the positioning groove is a hole-shaped structure whose cross section matches the columnar structure.
[0053] Preferably, the positioning pin can be selected as a solenoid valve, and the specific structure belongs to the prior art and will not be described in detail here.
[0054] In one embodiment, the folding part further includes: a limit member, which includes: a limit valve and two limit slots; the limit valve is arranged on the fuselage member, and the limit slot is arranged on the connecting member. Before and after the connecting member rotates relative to the fuselage member, the limit valve cooperates with different limit slots to form a limit point (the limit point is the position where the limit pin cooperates with the limit slot, and there is a total of one limit point) to correspond to the folding state or unfolding state of the wing member. The setting of the limit member can further limit the degree of freedom of the wing member on the basis of the positioning member, thereby preventing the folding state or unfolding state of the wing member from failing, and ensuring the stability and reliability of the state.
[0055] Preferably, the limit valve is a solenoid valve; the solenoid valve includes a valve core and a valve body, the valve core is connected to the valve body and can pop out and retract relative to the valve body; the valve body is fixedly connected to the fuselage part, and the valve core is in a pop-up state when it is aligned with the limit groove, and the pop-up state of the valve core corresponds to the folding state or unfolding state of the wing part, otherwise the valve core is in a retracted state, and the retracted state of the valve core corresponds to the rotation state of the wing part.
[0056] Further preferably, when the wing is in a folded state, the connection points, positioning points and limit points between the wing member and the connecting member are collinear and parallel to the direction of the wing; when the wing is in an unfolded state, the connection points, positioning points and limit points between the wing member and the connecting member form a triangular structure; this arrangement can ensure the stability of the wing in the folded state and the unfolded state, and is not prone to retraction resulting in a change in state.
[0057] In one embodiment, the folding portion further includes: an elastic member, the elastic member includes more than one spring; one corresponding end of the spring is connected to the fuselage member, and the other corresponding end is connected to the connecting member or the wing member. The specific number, position and size of the spring can be specifically set according to actual conditions to provide different forces and match different wings. Specifically, the fuselage member is provided with a first row of holes in an array, the connecting member or the wing member is provided with a second row of holes in an array, and fixing bolts are provided in more than one first row of holes and more than one second row of holes to fix the springs. The specific fixing method belongs to the prior art.
[0058] Preferably, in one group of positioning parts, the positioning pin is arranged on the connecting part, and the positioning slot is arranged on the fuselage part; in another group of positioning parts, the positioning pin is arranged on the wing part, and the positioning slot is arranged on the fuselage part; at the same time, a locking part is arranged in the positioning slot to automatically lock the positioning pin entering the positioning slot, and the wing part is in a folded state. When an experiment is required, the locking part is turned to make the wing part automatically unfold under the elastic force of the elastic part, and the wing part is in an unfolded state; in the above arrangement, the elastic part plays the role of a power part, which can replace the motor and other structures in the prior art as the power part of the folding part, thereby simplifying the composition of the folding structure, increasing the convenience of operation, and reducing costs. It should be noted that the locking part is a prior art and will not be described in detail here.
[0059] In a specific embodiment, the folding portion includes: a fuselage member, a wing member, a connecting member, a power member, a positioning member, a limiting member and an elastic member.
[0060] The fuselage piece is a rectangular plate-shaped structure, and the two folding parts share one fuselage piece.
[0061] The wing member is a rectangular plate-shaped structure, and two wing members are symmetrically arranged on both sides of the fuselage member. When the length direction of the wing member is perpendicular to the length direction of the fuselage member and the two wing members are parallel, the wing member is in a folded state, and when the length direction of the wing member is parallel to the length direction of the fuselage member and the two wing members are collinear, the wing member is in an unfolded state.
[0062] The connecting member is arranged between the fuselage member and the wing member. Specifically, the connecting member is arranged at the top of the fuselage member and is rotatably connected to the fuselage member through bearings and flanges in sequence. The connecting member is arranged at the bottom of the wing member and is fixedly connected to the wing member.
[0063] The power member is arranged at the bottom of the fuselage member and is fixedly connected to the fuselage member. The shaft of the power member passes through the fuselage member and is rotatably connected to the connecting member through flanges and bearings in sequence to drive the connecting member to rotate.
[0064] There are two groups of positioning parts; both positioning pins are cylindrical structures, one of which is arranged on the connecting part, and the other is arranged on the wing part; both positioning grooves are arranged on the fuselage part, and both are semi-hole structures that penetrate the straight quadrangular prism structure and are formed by the inward depression of one side of the straight quadrangular prism structure. The two straight quadrangular prism structures are arranged alternately, and one straight quadrangular prism structure is arranged above the other straight quadrangular prism structure. The opening direction of one of the positioning grooves is the same as the length direction of the fuselage part, and the opening direction of the other positioning groove is perpendicular to the length direction of the fuselage part.
[0065] The limit valve of the limit part is a solenoid valve, the valve body of the solenoid valve is connected to the fuselage part, when the wing part is in the folded state, the valve core is in the pop-up state (the solenoid valve is closed and not powered) and matches with a limit groove on the connecting part, when the wing part is in the rotating state, the valve core is in the retracted state (the solenoid valve is open and powered) and abuts against the connecting part, when the wing part is in the unfolded state, the valve core is in the pop-up state and matches with another limit groove on the connecting part. It should be noted that the solenoid valve and the specific connection method are prior art and will not be described in detail here.
[0066] The elastic member comprises a spring; one end of the spring is connected to the fuselage member, and the other end of the spring is connected to the wing member.
[0067] In this embodiment, the two positioning points are staggered in the three axial directions to form a stable positioning effect in the three directions, thereby ensuring the stability and reliability of the wing in the folded state and the unfolded state.
[0068] The working process of this application is:
[0069] The positioning pin provided on the connecting member matches with the corresponding positioning groove to form a positioning point, and the other set of positioning members is in an unmatched state; the valve core of the solenoid valve is in a pop-up state and matches with a limit groove to form a limit point; at this time, the wing member is in a folded state;
[0070] The valve core of the solenoid valve is in a retracted state and abuts against the connecting piece; the motor rotates forward, driving the connecting piece to rotate clockwise, and the wing piece and the connecting piece are linked; the positioning pin provided on the connecting piece is rotated out of the corresponding matching positioning groove and becomes an unmatched state, and the positioning pin provided on the wing piece matches the corresponding positioning groove to form another positioning point; the motor stops, and the connecting piece and the linked wing piece rotate into place; the valve core of the solenoid valve is in a pop-up state and matches with another limit groove to form a limit point; at this time, the wing piece is in an unfolded state;
[0071] The valve core of the solenoid valve is in a retracted state and abuts against the connecting piece; the motor reverses, driving the connecting piece to rotate counterclockwise, and the wing piece and the connecting piece are linked; the locating pin on the wing piece is screwed out of the corresponding matching locating groove and becomes an unmatched state, and the locating pin on the connecting piece matches the corresponding locating groove to form another locating point; the motor stops, and the connecting piece and the linked wing piece rotate into place; the valve core of the solenoid valve is in a pop-up state and matches a limit groove to form a limit point; at this time, the wing piece is restored to a folded state.
[0072] The above-mentioned folding structure of a wing is provided with symmetrical folding parts, each folding part is provided with a connecting part connecting the fuselage part and the wing part, and two groups of positioning parts are provided. The positioning groove of the positioning part can select a semi-hole structure or a hole structure, and can also be combined with an electromagnetic valve. It can form a stable structure while meeting the needs of static experiments and dynamic experiments at the same time, improve the reliability of the experiment, further provide a limit part and an elastic part, increase the fixing points, further improve the reliability, and the structure is simple, easy to implement, low cost, and wide range of applications.
[0073] The technical features of the above embodiments may be combined arbitrarily. To make the description concise, not all possible combinations of the technical features in the above embodiments are described. However, as long as there is no contradiction in the combination of these technical features, they should be considered to be within the scope of this specification.
[0074] The above-mentioned embodiments only express several implementation methods of the present application, and the descriptions thereof are relatively specific and detailed, but they cannot be understood as limiting the scope of the present application. It should be pointed out that, for a person of ordinary skill in the art, several variations and improvements can be made without departing from the concept of the present application, and these all belong to the protection scope of the present application. Therefore, the protection scope of the present application shall be subject to the attached claims.
Claims
1. A folding structure of a wing, characterized in that: include: Two symmetrically arranged folding parts, the folding parts comprising: a fuselage part connected to the fuselage, a wing part connected to the wing, a connecting part connected to the wing part, a power part connected to the connecting part, and two sets of positioning parts; The wing member is fixedly connected to the connecting member, and the connecting member is rotatably connected to the fuselage member, so that the connecting member rotates relative to the fuselage member under the drive of the power member, and the wing member and the connecting member are linked, so that the wing member has a folded state, a rotated state and an unfolded state; One group of positioning members connects the fuselage member and the connecting member, and another group of positioning members connects the fuselage member and the wing member; the positioning points of the two groups of positioning members and the connection points between the wing member and the connecting member form a triangular structure.
2. A wing folding structure according to claim 1, characterized in that: Each set of positioning members includes: positioning pins and positioning grooves, the positioning pins correspond to the positioning grooves one by one; the positioning pins enter the corresponding positioning grooves from the outside to form positioning points; In a set of positioning members, the positioning pin is provided on the body member or the connecting member, and the positioning slot is provided on the connecting member or the body member; In another set of positioning members, the positioning pins are arranged on the fuselage member or the wing member, and the positioning grooves are arranged on the wing member or the fuselage member.
3. A wing folding structure according to claim 2, characterized in that: The positioning pin is a cylindrical structure, and the positioning groove is a semi-hole structure with an opening facing the moving direction of the cylindrical structure.
4. The folding structure of a wing according to claim 3, characterized in that: The opening directions of the two positioning grooves are perpendicular.
5. The folding structure of a wing according to claim 2, characterized in that: The positioning pin is a columnar structure, and the positioning groove is a hole-shaped structure whose cross section matches the columnar structure.
6. The folding structure of a wing according to claim 2, characterized in that: The folding part further comprises: a limiting member; the limiting member comprises: a limiting valve provided on the body member and two limiting grooves provided on the connecting member; Before and after the connecting member rotates relative to the fuselage member, the limit valves respectively cooperate with different limit grooves to form limit points to correspond to the folding state or unfolding state of the wing member.
7. The folding structure of a wing according to claim 6, characterized in that: The limit valve is a solenoid valve; the solenoid valve comprises a valve core and a valve body, the valve core is connected to the valve body and can pop out and retract relative to the valve body; The valve body is fixedly connected to the fuselage member. When the valve core is aligned with the limiting groove, it is in a pop-up state, corresponding to the folding state or unfolding state of the wing member. Otherwise, the valve core is in a retracted state, corresponding to the rotation state of the wing member.
8. The folding structure of a wing according to claim 7, characterized in that: When the wing is in a folded state, the connection point, the positioning point and the limit point of the wing member and the connecting member are collinear and parallel to the direction of the wing; When the wing is in an unfolded state, the connection point, the positioning point and the limiting point of the wing member and the connecting member form a triangular structure.
9. A folding structure of a wing according to any one of claims 1 to 8, characterized in that: The folding portion further comprises: an elastic member; the elastic member comprises more than one spring; One corresponding end of the spring is connected to the fuselage member, and the other corresponding end is connected to the wing member.
10. A folding structure of a wing according to any one of claims 1 to 8, characterized in that: The connecting member is rotatably connected to the fuselage member via a bearing.