A chord-wise foldable and quick deployable wing structure

Abstract

The application discloses a chord-wise folding and quick unfolding wing structure and relates to the technical field of aircraft design technology.The chord-wise folding and quick unfolding wing structure comprises chord-wise folding and unfolding wing sections, the chord-wise folding and unfolding wing sections are divided into a plurality of wing sections along the chord direction, the division surfaces of two adjacent wing sections are both planes, grooves are formed in the separation planes of the two adjacent wing ribs, buffer gaskets and strong magnets are arranged in the grooves, and the two adjacent wing sections are connected through a film hinge; and flow guides are arranged above the connecting gaps of the two adjacent wing ribs.The chord-wise folding and quick unfolding wing structure can be divided into a plurality of wing sections which can rotate around the lower surface division lines along the chord direction, so that the wing fully utilizes the circumferential storage size and can break through the limitation of the cylinder diameter on the chord length and area of the wing; the two adjacent wing sections are connected through the film hinge, so that the air resistance during flight is reduced; the automatic positioning and locking between the two adjacent wing sections are realized by using the suction force of the permanent magnet, and the structure is simple and has high reliability.

Description

TECHNICAL FIELD

[0001] The present application relates to the field of aircraft design, in particular to a chord-wise folding and quick-expanding wing structure. BACKGROUND

[0002] The folding wing unmanned aerial vehicle has foldable and unfoldable wings, which can be stored in a storage cylinder in a folded state, thereby facilitating reduction of transportation volume. At present, the wings of the folding wing unmanned aerial vehicle are generally fixed along the chord length, and the launch cylinder is generally cylindrical, so that the chord-wise size of the wing is strictly limited by the size of the launch cylinder, and the chord of the wing can generally only be less than the diameter of the cylinder, which brings two problems: first, the smaller chord length limits the wing Reynolds number, and the wing lift-drag ratio is low; second, the limited wing area affects the maximum take-off weight of the unmanned aerial vehicle, and the carrying capacity is weak. At present, most folding wing unmanned aerial vehicles adopt the span-wise folding mode to increase the wing area, but still cannot fully utilize the circumferential space of the launch cylinder. Seeking a new type of folding and unfolding wing structure that can break through the diameter limitation of the launch cylinder, fully utilize the circumferential space, and has a simple and reliable folding and unfolding process has become a difficult point in the current design of folding wing unmanned aerial vehicles. SUMMARY

[0003] The purpose of the present application is to provide a chord-wise folding and quick-expanding wing structure to solve the problems raised in the background technology and fully utilize the circumferential storage size to break through the limitation of the cylinder diameter on the chord length and area of the wing.

[0004] To achieve the above-mentioned purpose, the present application provides a chord-wise folding and quick-expanding wing structure, which comprises a chord-wise folding and unfolding wing segment, the chord-wise folding and unfolding wing segment is divided into a plurality of wing segments along the chord direction, the division surface of the adjacent two wing segments is a plane, a groove is formed in the separation plane on the adjacent two wing ribs, a buffer gasket and a strong magnet are arranged in the groove, and the adjacent two wing segments are connected through a thin film hinge.

[0005] A guide vane is arranged above the connecting gap of the adjacent two wing ribs.

[0006] Preferably, the wing segment near the one-third chord line in the plurality of wing segments is a main load-bearing wing segment, and the root of the main load-bearing wing segment is fixedly connected with the wing; the remaining wing segments are all V-shaped wing segments, and the root of the V-shaped wing segment is not fixedly connected with the wing.

[0007] Preferably, the total number of the main load-bearing wing segments and the V-shaped wing segments is 3-5.

[0008] Preferably, the groove comprises a groove one and a plurality of groove twos, the strong magnet is fixedly arranged in the groove two, the buffer gasket is fixedly arranged in the groove one, the inner surface of the buffer gasket is flush with the outer surface of the strong magnet, and the outer surface of the buffer gasket is flush with the division surface.

[0009] Preferably, the buffer pad is made of polystyrene foam, polyurethane foam or polyethylene foam.

[0010] Preferably, two groups of strong magnets are arranged between every two adjacent wing segments, and the two groups of strong magnets are fixed at opposite positions on the two separate planes and have opposite magnetic poles at the end close to each other.

[0011] Preferably, a plurality of film hinges are arranged on the lower surface of the adjacent wing segments along the span direction, and the main material of the film hinge is polypropylene, polyester film, nylon fabric and tensile fiber material along the chord direction.

[0012] Preferably, the shape of the flow guide plate is consistent with the geometric shape of the wing, and the length of the flow guide plate is the same as the span length of the wing segment, the width of the flow guide plate is 5mm-50mm, and the thickness of the flow guide plate is 0.2mm-1.0mm.

[0013] Preferably, along the width direction, the leading edge of the flow guide plate is bonded to the upper surface of the trailing edge of the wing segment, the trailing edge of the flow guide plate is suspended, and the leading edge and the trailing edge of the flow guide plate are both in a gentle slope structure.

[0014] Therefore, the wing structure with the above chord-wise folding and rapid unfolding has the following beneficial effects:

[0015] (1) The wing is divided into a plurality of wing segments that can rotate around the lower surface division line along the chord direction, so that when the wing is stored in the barrel, the chord line is divided into a plurality of lines around the center of the cross section, thereby fully utilizing the ring storage size, breaking through the limitation of the diameter of the launch barrel on the chord length of the wing, and effectively increasing the chord length and the wing area.

[0016] (2) The adjacent wing segments are connected by the film hinge, which can realize the rotation of the wing segment around the division line, and also saves the complex structure of the traditional mechanical hinge, saves the structure quality, and reduces the flight resistance.

[0017] (3) After the unmanned aerial vehicle is unfolded, the magnetic attraction of the permanent magnet is used to realize automatic positioning and locking, the spring and locking mechanism in the traditional folding structure are saved, the structure is simplified, the folding and unfolding difficulty is reduced, the buffer pad is used to protect the strong magnet, and the collision between the wing segments is avoided to damage the magnet structure.

[0018] (4) During flight, the moment brought by the aerodynamic force will make the wing segments press closer, preventing the wing segments from being separated under the action of the aerodynamic force, and improving the structural stability and reliability.

[0019] (5) The flow guide plate is used to cover the steps or gaps on the upper surface of the wing segment caused by process precision or docking error, thereby reducing the additional resistance caused by the segmentation of the wing segment.

[0020] The technical solutions of the present application are described in further detail below with reference to the accompanying drawings and examples. BRIEF DESCRIPTION OF DRAWINGS

[0021] Figure 1 Fig. 1 is a schematic diagram of the overall structure of an embodiment of the chord-wise folding and rapid unfolding wing structure of the present application.

[0022] Figure 2 Fig. 2 is a structural component diagram of the chord-wise folding and rapid unfolding wing structure of the present application.

[0023] Figure 3 Fig. 3 is a schematic diagram of the main load-bearing wing segment and the shape-maintaining wing segment of the chord-wise folding and rapid unfolding wing structure of the present application.

[0024] Figure 4 Fig. 4 is an assembly diagram of the wing segment-magnet-cushion piece of the chord-wise folding and rapid unfolding wing structure of the present application.

[0025] Figure 5 Fig. 5 is a schematic diagram of the thin film hinge of the chord-wise folding and rapid unfolding wing structure of the present application.

[0026] Figure 6 Fig. 6 is a schematic diagram of the guide vane in the folded state of the chord-wise folding and rapid unfolding wing structure of the present application.

[0027] Figure 7 Fig. 7 is a schematic diagram of the guide vane in the unfolded state of the chord-wise folding and rapid unfolding wing structure of the present application.

[0028] Figure 8 Fig. 8 is a schematic diagram of the unmanned aerial vehicle in the storage and transportation state in the cylinder of the chord-wise folding and rapid unfolding wing structure of the present application.

[0029] Figure 9 Fig. 9 is a schematic diagram of the unmanned aerial vehicle in the unfolded state after exiting the cylinder of the chord-wise folding and rapid unfolding wing structure of the present application.

[0030] Figure 10 Fig. 10 is a schematic diagram of the wing segment in the automatic compression state under aerodynamic load of the chord-wise folding and rapid unfolding wing structure of the present application.

[0031] Fig. 1 is a schematic diagram of the overall structure of an embodiment of the chord-wise folding and rapid unfolding wing structure of the present application. DETAILED DESCRIPTION

[0032] The technical solutions of the present application are described in further detail below with reference to the accompanying drawings and examples.

[0033] Unless otherwise defined, technical terms or scientific terms used in the present application shall have the meanings as commonly understood by one of ordinary skill in the art to which this application belongs. The terms "first", "second", and similar terms are used to distinguish one element from another, and are not necessarily used to describe a sequential or chronological order. The terms "comprises", "comprising", "includes", "including" and the like can be used in the sense of "including but not limited to". The terms "connected", "coupled", and "linked" and the like can be used to describe a physical or mechanical connection, electrical connection, whether direct or indirect, or logical or other connection between or among two or more elements. The terms "upper", "lower", "left", "right", and the like are used to describe relative positions for ease of description and are not necessarily used to describe absolute positions.

[0034] Embodiment

[0035] Referring to Figures 1-10 , the present application provides a chord-wise folding and rapid unfolding wing structure, which comprises a chord-wise folding and unfolding wing section 1. The chord-wise folding and unfolding wing section 1 is divided into a plurality of wing sections along the chord direction. The wing section near the one-third chord line among the plurality of wing sections is a main load-bearing wing section 101, which has relatively high strength and rigidity. The root of the main load-bearing wing section 101 is fixedly connected with the wing, and can transmit the wing shear force and bending and torsional moments to the fuselage. The remaining wing sections are all shape-maintaining wing sections 102, which have relatively low strength and rigidity, and are mainly used to maintain the shape of the wing. The roots of the shape-maintaining wing sections 102 are not fixedly connected with the wing, and have relatively weak load-carrying capacity. As shown in Figure 3 , the total number of the main load-bearing wing sections 101 and the shape-maintaining wing sections 102 is set to 3-5 sections, and the specific number is determined according to the specific conditions of the unmanned aerial vehicle.

[0036] The division surfaces of the adjacent two wing sections are all planes. As shown in Figure 4 , grooves 103 are formed in the separation planes on the adjacent two wing flanges. The grooves 103 are provided with buffer gaskets 4 and strong magnets 3. The grooves 103 include grooves one 1032 and a plurality of grooves two 1031. The grooves two 1031 have a relatively deep depth, and are used to fix the strong magnets. The grooves one 1032 have a relatively shallow depth, and are used to fix the buffer gaskets 4. The material of the buffer gaskets 4 is polystyrene foam, or polyurethane foam, or polyethylene foam. The inner surface of the buffer gasket 4 is flush with the outer surface of the strong magnet 3, and the outer surface of the buffer gasket 4 is flush with the division surface. The buffer gasket 4 can effectively buffer the impact force when the wing sections are docked, and protect the magnet structure.

[0037] Two groups of strong magnets 3 are arranged between every two adjacent wing segments, and the two groups of strong magnets 3 are fixed in consistent positions on the two separated planes by adhesion, so that the positioning accuracy of the butt joint of the wing segments is improved, and the end portions of the two groups of strong magnets 3 close to each other are opposite in magnetism.

[0038] As shown in Figure 5 , two adjacent wing segments are connected by a plurality of film hinges 2 which are distributed along the spanwise direction, and the front and rear portions of the film hinges 2 are adhesively connected to the lower surfaces of the adjacent wing segments, and the upper surfaces are not connected, so that the wing segments can freely rotate within a range of 180° around the lower surface division line. The main material of the film hinge 2 is polypropylene, polyester film, nylon cloth, etc., and the inside is added with tensile reinforcing fiber material along the chordwise direction, so that the film hinge 2 has flexibility and strength, and has the advantages of high toughness, good durability and light weight.

[0039] As shown in Figure 6 and Figure 7 , a guide vane 5 is arranged above the connecting gap of two adjacent wing flanges, and the guide vane 5 is mainly used for maintaining the shape of the wing after the butt joint of the wing segments, and the material of the guide vane 5 is carbon fiber, metal, polyurethane film, etc. The shape of the guide vane 5 is consistent with the geometric shape of the wing, the length of the guide vane 5 is the same as the span length of the wing segment, the width of the guide vane 5 is set to 5mm-50mm, the thickness of the guide vane 5 is set to 0.2mm-1.0mm, and the specific width and thickness are determined according to the scale of the unmanned aerial vehicle. Along the width direction, the leading edge of the guide vane 5 is adhesively connected to the upper surface of the trailing edge of the wing segment, the trailing edge of the guide vane 5 is suspended, and the leading edge and the trailing edge of the guide vane 5 are both polished to be of a gentle slope structure, so as to avoid airflow separation and reduce the wind resistance.

[0040] The specific working mode of the present application is as follows:

[0041] (1) As shown in Figure 8 , when the unmanned aerial vehicle is stored in the cylinder, the wings are in a scattered state, the upper surfaces of the chordwise folding and unfolding wing segments 1 are separated, and the lower surfaces are adhesively connected by the film hinges 2. This storage form makes the chord length of the wing no longer strictly limited by the diameter of the launching cylinder, and the circumferential space in the launching cylinder can be fully utilized.

[0042] (2) As shown in Figure 9 , after the unmanned aerial vehicle is launched from the cylinder, the chordwise folding and unfolding wing segments 1 are attracted by the strong magnets 3, and the adjacent wing segments rotate around the lower surface film hinges 2 to complete the butt joint and fixation. During the butt joint process, the buffer gaskets 4 can effectively buffer the impact force between the wing segments during the butt joint, and protect the wing segments and the strong magnets 3 from being damaged.

[0043] (3) As shown in Figure 10As shown, during flight, the aerodynamic force on each wing segment is upward, the non-main load-bearing wing segment 101 transmits the aerodynamic force to the main load-bearing wing segment 101 through the separation surface between the wing segments, at this time, the diaphragm hinge 2 is in tension, and the adjacent wing segments are in a compact state.

[0044] (4) Affected by the machining process and the positioning accuracy of the magnet, a gap and a step may exist after the butt joint of the adjacent wing segments, the guide vane 5 can cover the gap and the step, avoid local separation of the airflow, and reduce the aerodynamic loss.

[0045] (5) After completing the flight, when the wing is stored, the wing segments only need to be bent downward to overcome the magnetic attraction, so that the adjacent wing segments are separated, and the operation is simple and reliable.

[0046] Therefore, the wing structure adopting the above string-wise folding and rapid unfolding can be divided into multiple wing segments that can rotate around the lower surface division line in the string direction, so that the wing fully utilizes the circumferential storage size, and the limitation of the cylinder diameter on the chord length and the area of the wing can be broken; the adjacent wing segments are connected through the diaphragm hinge, the complex hinge structure can be omitted, and the resistance during flight is reduced; the permanent magnet is used to realize the automatic positioning and locking between the adjacent wing segments, the wing segments are pressed tightly by the moment brought by the aerodynamic force, the spring and the locking mechanism are omitted, the structure is simple, and the reliability is high; the guide vane is used to cover the step or the gap on the upper surface of the adjacent wing segments, so that the aerodynamic performance loss caused by the division of the wing segments is reduced.

[0047] Finally, it should be noted that: the above examples are only used to illustrate the technical solutions of the present application but not to limit it, although the present application has been described in detail with reference to the preferred embodiments, those skilled in the art should understand that the technical solutions of the present application can still be modified or replaced by the equivalent, and these modifications or replacements cannot make the modified technical solutions deviate from the spirit and scope of the technical solutions of the present application.

Claims

1. A chord-wise folded and rapidly deployable wing structure, characterized by: The chord-wise foldable wing section is divided into several wing sections along the chord direction, the separating planes of two adjacent wing sections are both planes, grooves are formed in the separating planes of two adjacent wing edges, buffer pads and strong magnets are arranged in the grooves, and the two adjacent wing sections are connected through film hinges; A guide vane is arranged above the connecting gap of the two adjacent wing edges; The wing section close to the one-third chord line among the several wing sections is a main load-bearing wing section, and the root of the main load-bearing wing section is fixedly connected with the wing; Two groups of strong magnets are arranged between every two adjacent wing sections, the two groups of strong magnets are fixed at the same position on the two separating planes, and the end parts of the two groups of strong magnets close to each other are magnetically opposite; The film hinges are distributed on the lower surfaces of the adjacent wing sections along the span direction, and the main materials of the film hinges are polypropylene, polyester film, nylon cloth and tensile reinforcing fiber materials along the chord direction; The shape of the guide vane is consistent with the geometric shape of the wing, the length of the guide vane is the same as the span length of the wing section, the width of the guide vane is 5mm-50mm, and the thickness of the guide vane is 0.2mm-1.0mm.

2. A chord-wise folding and rapid deployment wing structure according to claim 1, characterized in that: The total number of the main load-bearing wing sections and the shape-maintaining wing sections is 3-5.

3. A chord-wise folding and rapid deployment wing structure according to claim 2, characterised in that: The grooves include groove one and several groove twos, the strong magnets are fixedly arranged in the groove twos, the buffer pads are fixedly arranged in the groove one, the inner surface of the buffer pad is flush with the outer surface of the strong magnet, and the outer surface of the buffer pad is flush with the separating plane.

4. A chord-wise folding and rapid unfolding wing structure according to claim 3, characterized in that: The material of the buffer pad is polystyrene foam, or polyurethane foam, or polyethylene foam.

5. A chord-wise folded and quick-erecting wing structure according to claim 4, characterized in that: In the width direction, the leading edge of the guide vane is bonded to the upper surface of the trailing edge of the wing section, the trailing edge of the guide vane is suspended, and the leading edge and the trailing edge of the guide vane are both in a gentle slope structure.

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