Flexible wing surface folding wing under complex space constraint
By designing crests and troughs on the flexible wing surface and controlling their geometric relationship, the motion uncertainty problem of the flexible wing surface and the four-bar linkage mechanism was solved, and a folding wing design with minimum folding space and maximum unfolding ratio was achieved.
Patent Information
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- BEIJING LINJIN SPACE AIRCRAFT SYST ENG INST
- Filing Date
- 2025-03-24
- Publication Date
- 2026-06-23
AI Technical Summary
In the existing technology, the combination of flexible composite material wing surface and four-bar deformation mechanism restricts its folding method, making it impossible to achieve minimum folding envelope, and the motion uncertainty is large, which cannot meet the folding and unfolding requirements of wings under complex spatial constraints.
The design incorporates crest and trough creases on the flexible wing surface. By controlling the geometric relationship between these creases, the wing can coordinate with a four-bar linkage to achieve orderly folding and unfolding, thereby reducing the space occupied after folding.
It achieves coordinated movement between the flexible wing surface and the four-bar linkage, maximizes the expansion-retraction ratio, ensures minimal space after folding, and meets the folding and expansion requirements under complex spatial constraints.
Smart Images
Figure CN224392938U_ABST
Abstract
Description
Technical Field
[0001] This utility model belongs to the field of aerospace deformable wing design, specifically relating to a flexible wing with folding and unfolding surfaces under complex spatial constraints. Background Technology
[0002] A certain aircraft employs a folding wing technology. This wing consists of a four-bar linkage and a flexible composite material airfoil. To maximize the spread-out area ratio of the folding wing, its volume envelope in the folded state needs to be minimized. However, due to the inherent stiffness of the flexible composite material airfoil, it cannot be folded as freely as ordinary fabric. Therefore, a specific folding method is required to achieve the minimum folded envelope. Furthermore, the flexible composite material airfoil is connected to each edge of the four-bar linkage. The folding motion of the four-bar linkage constantly restricts the edge position of the flexible airfoil, and its folding method must satisfy certain geometric relationships to accommodate the movement of the four-bar linkage. Given these unique flexible airfoil folding requirements, a folding wing that meets all these requirements currently does not exist. Summary of the Invention
[0003] The purpose of this invention is to solve the problems existing in the prior art and provide a flexible folding wing under complex spatial constraints, which is composed of a four-bar deformation mechanism and a flexible composite material wing surface. The flexible wing surface has the smallest volume after folding and closing, and meets the complex spatial constraints brought about by the deformation process of the four-bar mechanism.
[0004] This invention provides a flexible folding wing under complex spatial constraints. All four sides of the flexible wing are fixed to links of a four-bar linkage mechanism, and the wing is fully flattened when fully deployed. The drive link rotates around its joints after being driven by an external power source. The linkage mechanism, constrained by the configuration, performs deployment or retraction actions, and the linkage movement drives the wing to deploy synchronously. Creases are designed on the flexible wing surface, divided into crest creases and trough creases. By controlling the geometric relationship between each crease, the orderly folding and deployment of the flexible wing surface is achieved, minimizing the space occupied after folding.
[0005] The beneficial effects of this utility model are as follows:
[0006] This invention designs crest and trough creases on a flexible wing surface, enabling it to fold and unfold in an orderly manner, and coordinating the deformation motion of the flexible wing surface with that of the four-bar linkage. This avoids the motion uncertainties during the folding and unfolding process caused by the low stiffness of the flexible wing surface, minimizing the space occupied by the folded flexible wing surface and maximizing the expansion-to-retraction ratio of the folding wing. This method has high versatility and practicality, meeting the design requirements for wing surface folding methods of this type of deformable wing. Attached Figure Description
[0007] The accompanying drawings, which form part of this application, are used to provide a further understanding of the present invention. The illustrative embodiments of the present invention and their descriptions are used to explain the present invention and do not constitute an improper limitation of the present invention.
[0008] Figure 1 This is a schematic diagram of the folded state of a flexible wing structure according to an embodiment of the present utility model;
[0009] Figure 2 This is a schematic diagram of the unfolded state of a flexible wing structure according to an embodiment of the present utility model;
[0010] Figure 3 This is a geometric schematic diagram of a flexible wing folding method according to an embodiment of the present invention.
[0011] Wherein: 1-Active rod; 2-Driven rod; 3-Semi-flexible airfoil; 4-Wing leading edge; 5-Frame; A-Connection end between active rod and frame; D-Connection end between active rod and driven rod; B-Connection end between driven rod and wing leading edge; C-Connection end between frame and wing leading edge; F-Incenter point of triangle ABC. Detailed Implementation
[0012] To enable those skilled in the art to better understand the present invention, the technical solutions of the present invention will be clearly and completely described below with reference to the accompanying drawings of the embodiments. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort should fall within the protection scope of the present invention.
[0013] This embodiment provides a flexible folding wing under complex spatial constraints, and its schematic diagram is shown below. Figure 1-2 As shown, the folding wing consists of a four-bar linkage and a semi-flexible airfoil 3. The four-bar linkage includes a driving link 1, a driven link 2, a leading edge 4, and a frame 5. When the folding wing is fully deployed, the four-bar linkage unfolds into a right-angled triangle, with the driving link 1 and the driven link 2 collinear. The edge of the flexible airfoil 3 is completely fixed to the linkage mechanism, and the airfoil unfolds or folds along with the linkage mechanism during deformation.
[0014] like Figure 3 As shown, the flexible wing surface 3 is designed with creases that satisfy certain geometric relationships. Solid lines represent crest creases, and dashed lines represent trough creases. Straight lines AF, BF, and CF are the angle bisectors of ∠BAC, ∠ABC, and ∠ACB, respectively. The distance between each crease is equal, ensuring that the width of each folded unit is the same. The number of creases is even, and the distance between creases is determined by the folding envelope. When the folded wing retracts, crease lines are drawn on the actual wing surface to control the orderly retraction of the flexible wing surface.
[0015] The above description of the disclosed embodiments enables those skilled in the art to make or use the invention. Various modifications to these embodiments will be readily apparent to those skilled in the art, and the general principles defined herein may be implemented in other embodiments without departing from the scope of the invention. Therefore, the invention is not to be limited to the embodiments shown herein, but is to be accorded the widest scope consistent with the principles and novel features disclosed herein.
Claims
1. A flexible folding wing under complex spatial constraints, characterized in that, The folding wing comprises: a four-bar linkage deformation mechanism and a semi-flexible airfoil; wherein the four-bar linkage deformation mechanism includes a driving link, a driven link, a leading edge of the wing, and a frame; The active and driven rods are collinear; the edge of the semi-flexible wing surface is fixedly connected to the linkage mechanism; the active rod rotates around the joint after being driven by an external power source, and the four-bar linkage deformable mechanism is constrained by the configuration relationship to form an unfolding or retracting action; during the deformation process of the four-bar linkage deformable mechanism, the wing surface unfolds or folds accordingly; When the folding wing is fully extended, the four-bar linkage deformable mechanism unfolds into a right-angled triangle state.
2. The flexible folding wing under complex spatial constraints according to claim 1, characterized in that, The semi-flexible wing surface is designed with creases that satisfy geometric relationships.
3. The flexible folding wing under complex spatial constraints according to claim 2, characterized in that, The creases form n right triangles, where n is a natural number; the incenters of the n right triangles formed by the creases coincide with the incenters of the right triangles formed by the four-bar linkage.
4. The flexible folding wing under complex spatial constraints according to claim 2, characterized in that, The distance between the creases is equal, and the width of each folded unit is the same.
5. A flexible folding wing under complex spatial constraints according to claim 2, characterized in that, The number of creases is even, and the distance between creases is determined by the convergence envelope.