Wing and aircraft
By designing a retractable wing consisting of four main arms, the problem that the existing fixed wing cannot shrink quickly in space-constrained scenarios is solved, and the wings are rapidly deployed and contracted, improving the scope of application and operational flexibility of the aircraft.
Patent Information
- Application Number
- CN202420504158.1
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- Filing Date
- 2024-03-15
- Publication Date
- 2025-03-04
- Estimated Expiration
- 2034-03-15
AI Technical Summary
The wings of existing aircraft are mostly fixed and cannot shrink rapidly in space-constrained scenarios and cannot meet special needs.
A retractable wing consisting of four main arms is designed, each two main arms are distributed on one side of the fuselage of the aircraft. The synchronous movement of the main arms is achieved through articulated connections and sliding connectors, forming a diamond shape for easy flight.
It realizes rapid contraction and deployment of the wings, which is suitable for space-constrained scenarios, and improves the scope of application and operational flexibility of the aircraft.
Smart Images
Figure CN222555141U_ABST
Abstract
Description
Technical Field
[0001] The present application relates to the technical field of aircraft, and more specifically, to a wing and an aircraft. Background Art
[0002] Currently, the wings of most aircraft are fixed. In some special scenarios, due to space limitations, a retractable wing is needed to meet the needs. Utility Model Content
[0003] The present application aims to at least partially solve the above-mentioned technical problems and provide a wing and an aircraft that can improve.
[0004] An embodiment of the present application provides a wing for use in an aircraft, wherein the wing is composed of four main arms, wherein every two main arms are distributed on one side of a fuselage of the aircraft, wherein the first ends of the two main arms located on the same side are hingedly connected, and the second ends of the main arms are movably arranged on the fuselage, and the second ends of the main arms located on both sides of the fuselage move synchronously on the fuselage.
[0005] Furthermore, the hinge point of the first end of the main arm is located at one end of its end surface.
[0006] Furthermore, the hinge point is arranged close to the fuselage.
[0007] Furthermore, two of the main arms are provided with hinged columns on their hinged points, and another two of the main arms are provided with hinged sleeves on their intersection points, and the hinged columns are matched with the hinged sleeves.
[0008] Furthermore, a connector is provided between the second ends of the main arms, and the connector is slidably disposed on the fuselage.
[0009] Furthermore, two ends of the connector are hingedly connected to two second ends of the main arm.
[0010] Furthermore, the outer end surface of the main arm is arranged in an arc shape.
[0011] Furthermore, the end surfaces at both ends of the main arm are arranged in a planar shape.
[0012] An embodiment of the present application also provides an aircraft, comprising the wing described above, and the aircraft also includes a tail wing and a propeller arranged at the tail end of the fuselage.
[0013] Furthermore, the aircraft includes a slide groove arranged at the upper end of the fuselage and a driving component arranged inside the slide groove, and the driving component drives the connector to slide inside the slide groove and drives the main arm to move.
[0014] The present application provides a wing and an aircraft. In the present device, the wing is composed of four main arms, and every two main arms are distributed on one side of the fuselage of the aircraft. The first ends of the two main arms located on the same side are hingedly connected, and the second ends of the main arms are movably arranged on the fuselage. The second ends of the main arms located on both sides of the fuselage move synchronously on the fuselage. A retractable aircraft wing with a simple structure, ingenious design and a wide range of applications is provided. BRIEF DESCRIPTION OF THE DRAWINGS
[0015] In order to more clearly illustrate the embodiments of the present application or the technical solutions in the prior art, the drawings required for use in the embodiments or the description of the prior art will be briefly introduced below. Obviously, the drawings described below are only embodiments of the present application. For ordinary technicians in this field, other drawings can be obtained based on the provided drawings without paying any creative work.
[0016] Figure 1 Schematic diagram of the overall structure of the aircraft in this embodiment;
[0017] Reference numerals:
[0018] 1-aircraft, 11-wing, 111-first main arm, 112-second main arm, 113-articulated column, 114-articulated sleeve, 12-fuselage, 121-carrying platform, 122-chute, 13-tail wing, 14-propeller. DETAILED DESCRIPTION
[0019] The following will be combined with the drawings in the embodiments of the present application to clearly and completely describe the technical solutions in the embodiments of the present application. Obviously, the described embodiments are only part of the embodiments of the present application, not all of the embodiments. Based on the embodiments in the present application, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of this application.
[0020] like Figure 1 As shown, an embodiment of the present application provides a wing 11 applied to an aircraft 1. The wing 11 is different from a conventional wing 11 in that it is retractable, has a clever design, and a simple structure. It can meet the needs of rapid retraction and unfolding of the wing 11 and is easy to promote and apply quickly.
[0021] In this embodiment, the wing 11 is mainly composed of four main arms, and the structures of the four main arms are basically the same. The difference lies in the connecting parts at both ends, which are arc-shaped in shape, which helps to reduce the wind resistance of the aircraft 1 during flight when the wing 11 is unfolded. The end faces at both ends of the main arms are flat, which is convenient for the two main arms to fit together when they are retracted; two main arms are arranged on one side of the fuselage 12 as a group, and the two main arms in a group are hinged together, and the non-hinged end is movably arranged on the upper part of the fuselage 12; when the wing 11 needs to be unfolded, the two main arms on the same side are moved toward the center of the fuselage 12 at one end connected to the fuselage 12 to form a diamond shape, which provides good stability and convenience for the flight of the aircraft 1.
[0022] Among them, a carrying platform 121 is horizontally arranged at the upper end of the fuselage 12, which is used to place the wings 11 when unfolded and retracted. The platform is formed by cutting off the upper part along the horizontal plane of the fuselage 12. The height of the platform accounts for about one-fifth of the height of the fuselage 12, and the remaining four-fifths of the space can meet the installation and operation of electrical equipment.
[0023] The two main arms located on the same side, namely the first main arm 111 and the second main arm 112, have first ends that are connected by a hinged manner, and second ends of the two main arms are movably arranged on the upper part of the fuselage 12. It can be understood that the first end is one end at which the two main arms are hinged to each other, and the second end is one end at which the two main arms are respectively connected to the fuselage 12.
[0024] Among them, a hinge column 113 is provided at the first end of the first main arm 111, and a hinge sleeve 114 is provided at the first end of the second main arm 112. The hinge column 113 is fixed to the outside of the first main arm 111 and leaves a partial gap. The hinge sleeve 114 is fixed to the outside of the second main arm 112 and sleeved on the hinge column 113. With this arrangement, the first main arm 111 and the second main arm 112 can rotate with each other to achieve an angle change between the two, wherein the angle change range is 45°-180°.
[0025] Specifically, the hinge point of the first end of the first main arm 111 is disposed on an end of its end surface close to the fuselage 12. Correspondingly, the hinge point of the second main arm 112 is also located on an end of its end surface close to the fuselage 12.
[0026] The second ends of the two main arms are movably arranged on a support platform 121 horizontally arranged on the upper part of the fuselage 12, and a slide groove 122 is opened on the support platform 121. An electric slider currently available on the market (not shown) is arranged on the inner side of the slide groove 122, and a connector is arranged at the upper end of the slide groove 122. The connector is slidably connected to the electric slider through a connecting piece, and the connecting piece can be a rod-shaped casting with high strength; in addition, the connector connects the second ends of the two main arms, and the rotational connection between the connector and the main arm can be achieved by setting a rotating shaft between the two.
[0027] Another aircraft 1 provided according to an embodiment of the present application includes the wing 11 described above, and also includes a tail 13 and a propeller 14 arranged at the tail end of the fuselage 12 of the aircraft 1.
[0028] In this embodiment, the aircraft 1 also includes a slide groove 122 arranged at the upper end of the fuselage 12 and a driving component arranged on the inner side of the slide groove 122, wherein the driving component drives the connector to slide in the slide groove 122 and drives the main arm to move, wherein the driving component is the electric slider described above.
[0029] The working principle of the wing 11 of the aircraft 1 in this embodiment is as follows:
[0030] The retractable wing 11 is used for the aircraft 1 that takes off by catapult.
[0031] When the aircraft 1 is in a grounded state, its wings 11 are retracted, the four main arms are retracted on the supporting platform, the two groups of main arms are in a parallel state, and the two electric sliders inside the slide groove 122 are respectively located at the two ends of the slide groove 122. At this time, the distance between the two electric sliders is the farthest.
[0032] When the aircraft 1 is flying, before being ejected by the ejection device, the wing 11 is always in a retracted state. After being ejected by the ejection device, the controller in the aircraft 1 controls the electric slider to slide, and the two electric sliders move toward each other, and drive the indirectly connected main arms to move. A group of main arms on the same side can also rotate with each other. When the electric slider moves a preset distance and stops, the four main arms are enclosed to form a diamond shape. With its arc-shaped shape, it can better assist the flight of the aircraft 1.
[0033] 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. It should also be noted that the terms "include", "comprise" or any other variants thereof are intended to cover non-exclusive inclusion, so that a process, method, commodity 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, commodity or device. In the absence of further restrictions, the elements defined by the sentence "comprise a ..." do not exclude the existence of other identical elements in the process, method, commodity or device including the elements.
[0034] Each embodiment in this specification is described in a related manner, and the same or similar parts between the embodiments can be referred to each other, and each embodiment focuses on the differences from other embodiments. In particular, for the device embodiment, since it is based on a similar method embodiment, the description is relatively simple, and the relevant parts can be referred to the partial description of the method embodiment.
[0035] The above are only embodiments of the present application and are not intended to limit the present application. For those skilled in the art, the present application may have various changes and variations. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present application should be included within the scope of the claims of the present application.
Claims
1. A wing, applied to an aircraft, characterized in that: The wing is composed of four main arms, and every two main arms are distributed on one side of the fuselage of the aircraft. The first ends of the two main arms located on the same side are hingedly connected, and the second ends of the main arms are movably arranged on the fuselage. The second ends of the main arms located on both sides of the fuselage move synchronously on the fuselage.
2. The wing according to claim 1, characterized in that The hinge point of the first end of the main arm is located at one end of its end surface.
3. The wing according to claim 2, characterized in that The hinge point is arranged close to the fuselage.
4. The wing according to claim 2, characterized in that Two of the main arms are provided with hinged columns at their hinged points, and the other two main arms are provided with hinged sleeves at their intersection points. The hinged columns are matched with the hinged sleeves.
5. The wing according to claim 1, characterized in that A connector is arranged between the second ends of the main arms, and the connector is slidably arranged on the fuselage.
6. The wing according to claim 5, characterized in that The two ends of the connector are hingedly connected to the two second ends of the main arm.
7. The wing according to claim 1, characterized in that The outer end surface of the main arm is arranged in an arc shape.
8. The wing according to claim 1, characterized in that The end surfaces at both ends of the main arm are arranged in a planar shape.
9. An aircraft, comprising the wing according to any one of claims 1 to 8, characterized in that: The aircraft also includes a tail wing and a propeller arranged at the tail end of the fuselage.
10. The aircraft according to claim 9, characterized in that The aircraft comprises a slide groove arranged at the upper end of the fuselage and a driving component arranged inside the slide groove, and the driving component drives the connector to slide inside the slide groove and drives the main arm to move.