A wing folding mechanism for a water-air cross-medium vehicle

Abstract

The utility model relates to a wing folding mechanism for water-air cross-medium vehicle, and relates to a wing folding mechanism. The utility model discloses a wing folding mechanism that solves the problem of large resistance when the existing folding wing structure is used for underwater navigation. The utility model discloses a rack, a sliding block and two groups of folding units. The sliding block is in sliding connection with the rack. The two groups of folding units are symmetrically arranged on both sides of the rack. The lower wing surface of each wing rod in the folding unit is in a plane. The thickness of the folding unit is reduced. The side vertical surface of each wing rod abuts after the folding unit is folded. Overlapping of each wing rod is avoided. The volume after folding is minimized. The underwater resistance is reduced. On the basis of ensuring the actual function of the vehicle underwater and in the air, each part of the folding unit adopts a simple design principle. The processing and installation difficulty is reduced. The reliability and stability of the folding mechanism are increased. The utility model belongs to the technical field of vehicle wing design.

Description

TECHNICAL FIELD

[0001] The present application relates to a wing folding mechanism, in particular to a wing folding mechanism for a water-air cross-medium vehicle, and belongs to the technical field of vehicle wing design. BACKGROUND

[0002] The water-air cross-medium vehicle is a vehicle that can freely cross the water-air interface and navigate underwater and in the air. In recent years, great attention has been paid to it. The water exit process of the vehicle is the most difficult process in its research and design. Not only does it need to consider the sufficient propulsion force needed to achieve the water exit of the vehicle, but also it needs to pay attention to the influence of water on the wing of the water-air cross-medium vehicle after the water exit.

[0003] When the vehicle adopts a fixed rigid wing, not only does the wing need to withstand a large impact during the water exit process, increasing the requirement for structural strength, but also the wing generates a large resistance when navigating underwater, increasing energy consumption. When the vehicle adopts a folding rigid wing, the wing cavity designed to reduce the weight of the wing will easily be flooded, increasing the weight of the wing after the water exit of the water-air cross-medium vehicle, or even affecting the balance of the water-air cross-medium vehicle when the water entry degree of the wings on both sides is uneven. Even if drainage holes are added to the wing, it is difficult to quickly drain water.

[0004] For example, the patent with publication number CN219404623U discloses a crank slider type wing folding mechanism, which has the functions of folding and unfolding as a folding mechanism of a flapping wing vehicle, can support a flexible film wing, and meets the needs of wing flapping, light weight, and avoids water entry.

[0005] Although the above-mentioned patent discloses a folding mechanism with a rigid skeleton, the connecting rod is arranged in a stacked manner along the thickness direction of the fuselage, and the design object of this patent is a flapping wing vehicle. If this mechanism is applied to a vehicle, it will generate additional resistance when navigating underwater, so the above-mentioned patent is not suitable as a folding wing structure for a water-air cross-medium vehicle.

[0006] In view of the above technical problems, how to provide a wing folding mechanism has become a problem to be solved by the present technical personnel in the field. SUMMARY

[0007] The present application provides a wing folding mechanism for a water-air cross-medium vehicle.

[0008] The technical scheme of the present application is: a wing folding mechanism for a water-air cross-medium vehicle, comprising a rack, a sliding block and two sets of folding units, the rack is integrally provided with a hinge column, the sliding block is slidingly connected with the rack, and the two sets of folding units are symmetrically arranged on both sides of the rack.

[0009] The folding unit comprises a first wing rod, a second wing rod, a third wing rod, a fourth wing rod, a transmission rod, a first chain link, a second chain link and a third chain link.

[0010] The end of the first wing rod is hingedly connected with the hinge column, one end of the first chain link is mounted on the hinge column and the first chain link can rotate relative to the hinge column, and the other end of the first chain link is fixedly connected with the end of the second wing rod.

[0011] One end of the second chain link is mounted on the second wing rod and the second wing rod can rotate relative to the end of the second wing rod, and the other end of the second chain link is fixedly connected with the end of the third wing rod.

[0012] One end of the third chain link is mounted on the third wing rod and the third chain link can rotate relative to the end of the third wing rod, and the other end of the third chain link is fixedly connected with the end of the fourth wing rod.

[0013] The two ends of the transmission rod are hingedly connected with the sliding block and the middle part of the fourth wing rod respectively, and the sliding block can drive the fourth wing rod, the third wing rod, the second wing rod and the first wing rod to unfold or fold in sequence.

[0014] The upper surfaces of the first wing rod, the second wing rod, the third wing rod and the fourth wing rod are fixedly connected with the flexible wing membrane, and the lower surfaces of the first wing rod, the second wing rod, the third wing rod and the fourth wing rod are abutted with the transmission rod.

[0015] Further, the upper surface of the first wing rod is integrally provided with a first square tenon, the upper surface and the lower surface of the second wing rod are integrally provided with a second square tenon and a third square tenon respectively, and the first chain link is provided with a first square groove and a second square groove.

[0016] The first square tenon is inserted into the first square groove, and the width of the first square groove is greater than the width of the first square tenon.

[0017] The second square tenon is inserted into the second square groove, and the width of the second square groove is equal to the width of the second square tenon.

[0018] The upper surface and the lower surface of the third wing rod are integrally provided with a fourth square tenon and a fifth square tenon respectively, and the second chain link is provided with a third square groove and a fourth square groove.

[0019] The third square tenon is inserted into the third square groove, and the width of the third square groove is greater than the width of the third square tenon; the fifth square tenon is inserted into the fourth square groove, and the width of the fourth square groove is equal to the width of the fifth square tenon.

[0020] The upper surface of the fourth wing rod is integrally provided with a sixth square tenon, and the third link is provided with a fifth square groove and a sixth square groove.

[0021] The fourth square tenon is inserted into the fifth square groove, and the width of the fifth square groove is greater than the width of the fourth square tenon; and the sixth square tenon is inserted into the sixth square groove, and the width of the sixth square groove is equal to the width of the sixth square tenon.

[0022] Further, the upper surfaces of the first, second and third wing rods are arc surfaces, and the length directions of the first, second and third wing rods are perpendicular to the axes of the arc surfaces; the lower surfaces of the first, second and third wing rods are planes; and the cross section of the fourth wing rod is a right triangle.

[0023] Further, the curvature radius of the arc surface of the first wing rod is smaller than that of the second wing rod, and the curvature radius of the arc surface of the second wing rod is smaller than that of the third wing rod.

[0024] Further, the length of the first wing rod is smaller than that of the second wing rod, the length of the second wing rod is smaller than that of the third wing rod, and the length of the third wing rod is smaller than that of the fourth wing rod.

[0025] Compared with the prior art, the present application has the following effects:

[0026] 1. The present application has a simple structure, and on the basis of ensuring the actual functions of the aircraft under water and in the air, the folding unit 300 adopts a simple design principle, reduces the processing and installation difficulty, and increases the reliability and stability of the folding mechanism.

[0027] 2. The lower surfaces of the wing rods in the folding unit 300 are in a plane, which reduces the thickness of the folding unit 300, and the side vertical surfaces of the wing rods abut after the folding unit 300 is folded, so as to avoid overlapping of the wing rods, thereby realizing maximum reduction of the volume after folding and reduction of the underwater resistance. BRIEF DESCRIPTION OF DRAWINGS

[0028] Figure 1 is an isometric view of the present application in an unfolded state;

[0029] Figure 2 is an isometric view of the present application in a folded state;

[0030] Figure 3 is a bottom view of the present application in an unfolded state;

[0031] Figure 4 is a schematic view of the connection of the folding unit 300 and the rack 100 of the present application;

[0032] Figure 5 is an exploded view of Figure 4 ​

[0033] Fig.:

[0034] 100, frame; 110, hinged column; 120, folding limiting block;

[0035] 130, unfolding limiting block; 200, sliding block;

[0036] 300, folding unit; 310, first wing rod; 311, first square tenon;

[0037] 320, second wing rod; 321, second square tenon; 322, third square tenon;

[0038] 330, third wing rod; 331, fourth square tenon; 332, fifth square tenon;

[0039] 340, fourth wing rod; 341, sixth square tenon; 350, transmission rod;

[0040] 360, first link; 361, first square groove; 362, second square groove;

[0041] 370, second link; 371, third square groove; 372, fourth square groove;

[0042] 380, third link; 381, fifth square groove; 382, sixth square groove. DETAILED DESCRIPTION

[0043] In order to make the invention purposes, features and advantages of the present application more obvious and easy to understand, the technical solutions in the embodiments of the present application will be described clearly and completely below in conjunction with the drawings in the embodiments of the present application.

[0044] Specific embodiment one: in conjunction with Figures 1 to 5 This embodiment is described, a wing folding mechanism for a water-air-space medium vehicle in this embodiment includes a frame 100, a sliding block 200 and two groups of folding units 300, the frame 100 is integrally provided with a hinged column 110, the sliding block 200 is slidingly connected with the frame 100, and the two groups of folding units 300 are symmetrically arranged on both sides of the frame 100.

[0045] The folding unit 300 includes a first wing rod 310, a second wing rod 320, a third wing rod 330, a fourth wing rod 340, a transmission rod 350, a first link 360, a second link 370 and a third link 380.

[0046] The end of the first wing rod 310 is hinged to the hinged column 110, one end of the first link 360 is mounted on the hinged column 110, and the first link 360 can rotate relative to the hinged column 110, and the other end of the first link 360 is fixedly connected with the end of the second wing rod 320.

[0047] One end of the second link 370 is mounted on the second wing rod 320, and the second wing rod 320 can rotate relative to the end of the second wing rod 320, and the other end of the second link 370 is fixedly connected with the end of the third wing rod 330.

[0048] One end of the third link 380 is mounted on the third wing rod 330, and the third link 380 can rotate relative to the end of the third wing rod 330, and the other end of the third link 380 is fixedly connected with the end of the fourth wing rod 340.

[0049] The two ends of the transmission rod 350 are respectively hinged with the sliding block 200 and the middle part of the fourth wing rod 340, and the sliding block 200 can drive the fourth wing rod 340, the third wing rod 330, the second wing rod 320 and the first wing rod 310 to unfold or fold in turn.

[0050] The upper wings of the first wing rod 310, the second wing rod 320, the third wing rod 330 and the fourth wing rod 340 are fixedly connected with the flexible wing film, and the lower wings of the first wing rod 310, the second wing rod 320, the third wing rod 330 and the fourth wing rod 340 are in abutment with the transmission rod 350. In this way, the lower wings of the wing rods are arranged in a plane, reducing the thickness of the folding unit 300, and the side vertical surfaces of the wing rods abut after the folding unit 300 is folded, avoiding overlapping of the wing rods, thereby realizing the maximum reduction of the volume after folding. For the water-air cross-medium vehicle, reducing the underwater resistance is an important goal in the design process, and reducing the volume after folding is very important for reducing the underwater resistance.

[0051] In this embodiment, the folding limiting block 120 and the unfolding limiting block 130 are integrally arranged on the rack 100, and when the folding unit 300 is unfolded in place, the sliding block 200 abuts against the unfolding limiting block 130, and when the folding unit 300 is folded in place, the sliding block 200 abuts against the folding limiting block 120.

[0052] In this embodiment, the flexible wing film is fixed on the upper wings of the wing rods by adhesion.

[0053] Specific implementation method two: in combination with Figure 1 , Figure 4 and Figure 5 This embodiment is described, and in this embodiment, the upper wing of the first wing rod 310 is integrally provided with a first square tenon 311, the upper wing and the lower wing of the second wing rod 320 are integrally provided with a second square tenon 321 and a third square tenon 322 respectively, and the first square groove 361 and the second square groove 362 are opened on the first link 360.

[0054] The first square tenon 311 is inserted into the first square groove 361, and the width of the first square groove 361 is greater than the width of the first square tenon 311; in this way, one end of the first link 360 can rotate relative to the first wing rod 310; the second square tenon 321 is inserted into the second square groove 362, and the width of the second square groove 362 is equal to the width of the second square tenon 321; in this way, one end of the first link 360 cannot rotate relative to the second wing rod 320. The upper wing surface and the lower wing surface of the third wing rod 330 are integrally provided with a fourth square tenon 331 and a fifth square tenon 332, respectively, and the second link 370 is provided with a third square groove 371 and a fourth square groove 372.

[0055] The third square tenon 322 is inserted into the third square groove 371, and the width of the third square groove 371 is greater than the width of the third square tenon 322; in this way, one end of the second link 370 can rotate relative to the second wing rod 320; the fifth square tenon 332 is inserted into the fourth square groove 372, and the width of the fourth square groove 372 is equal to the width of the fifth square tenon 332; in this way, the other end of the second link 370 cannot rotate relative to the third wing rod 330. The upper wing surface of the fourth wing rod 340 is integrally provided with a sixth square tenon 341, and the third link 380 is provided with a fifth square groove 381 and a sixth square groove 382.

[0056] The fourth square tenon 331 is inserted into the fifth square groove 381, and the width of the fifth square groove 381 is greater than the width of the fourth square tenon 331; in this way, one end of the third link 380 can rotate relative to the third wing rod 330; the sixth square tenon 341 is inserted into the sixth square groove 382, and the width of the sixth square groove 382 is equal to the width of the sixth square tenon 341; in this way, the other end of the third link 380 cannot rotate relative to the fourth wing rod 340. The other components and connection relationships are the same as in the specific embodiment.

[0057] Specific embodiment three: combined Figures 1 to 5 In this embodiment, the upper wing surfaces of the first wing rod 310, the second wing rod 320, and the third wing rod 330 are all arc surfaces, and the length directions of the first wing rod 310, the second wing rod 320, and the third wing rod 330 are all perpendicular to the axes of the arc surfaces; the lower wing surfaces of the first wing rod 310, the second wing rod 320, and the third wing rod 330 are all planes; in this way, the advantages are as follows:

[0058] (1) Improving the lift of the folding unit 300: when the aircraft jumps out of the water and flies in the air, the folding unit 300 is unfolded, and the air flow flows above the arc-shaped upper wing surface at a high speed and at a low pressure, thereby generating greater lift. Based on the Bernoulli principle, the folding unit 300 can generate greater lift, which helps to maintain the stability of the aircraft in flight and reduces the difficulty of control due to changes in air flow.

[0059] (2) improve the aerodynamic efficiency of the folding unit 300: on the one hand, the flat lower wing surface helps to control the stability of the airflow, and reduces the air resistance; on the other hand, the flat lower wing surface is relatively simple in design and manufacture, which reduces the production cost.

[0060] Further, the curvature radius of the arc surface of the first wing rod 310 is smaller than that of the second wing rod 320, and the curvature radius of the arc surface of the second wing rod 320 is smaller than that of the third wing rod 330, so that the thickness of the first wing rod 310 to the third wing rod 330 gradually decreases, which helps to reduce the weight of the folding unit 300, so that the aircraft can consume less power at the same speed, thereby improving the range.

[0061] Further, the cross section of the fourth wing rod 340 is a right triangle, and the upper wing surface of the fourth wing rod 340 is integrally provided with a reinforcing rib, so that when the aircraft flies in the air, the fourth wing rod 340 bears the maximum stress, and the reinforcing rib further improves the structural strength.

[0062] Other components and connection relationships are the same as those in the first or second embodiment.

[0063] Specific embodiment four: in combination Figure 1 And Figure 2 In this embodiment, the length of the first wing rod 310 is less than the length of the second wing rod 320, the length of the second wing rod 320 is less than the length of the third wing rod 330, and the length of the third wing rod 330 is less than the length of the fourth wing rod 340. The design of gradually increasing the length of the first wing rod 310 to the fourth wing rod 340 makes the folding unit 300 have sufficient wing span length, thereby generating greater lift, making the aircraft fly more stably in the air.

[0064] Other components and connection relationships are the same as those in the first, second or third embodiment.

[0065] Working principle

[0066] In combination Figures 1 to 5 The working principle of the present application is explained as follows:

[0067] The sliding block 200 is slidingly connected with the rack 100, and the sliding block 200 is driven by the servo cylinder on the fuselage, that is, when the extension rod of the servo cylinder is extended, the sliding block 200 slides towards the unfolding limiting block 130, and when the extension rod is retracted, the sliding block 200 slides towards the folding limiting block 120.

[0068] The two sets of folding units 300 are symmetrically arranged on both sides of the rack 100, and the two ends of the transmission rod 350 are respectively hinged with the sliding block 200 and the middle part of the fourth wing rod 340,

[0069] In the process of unfolding the folding unit 300, the slider 200 slides, the two ends of the transmission rod 350 rotate relative to the hinge joints of the slider 200 and the fourth wing rod 340, then the fourth wing rod 340 drives the third wing rod 330 to rotate through the third link 380, so as to unfold the flexible wing membrane between the fourth wing rod 340 and the third wing rod 330;

[0070] Then the third wing rod 330 drives the second wing rod 320 to rotate through the second link 370, so as to unfold the flexible wing membrane between the third wing rod 330 and the second wing rod 320; finally, the second wing rod 320 drives the first wing rod 310 to rotate through the first link 360, so as to unfold the flexible wing membrane between the second wing rod 320 and the first wing rod 310; until each folding unit 300 is unfolded in place, the slider 200 abuts against the unfolding limiting block 130.

[0071] In the process of folding the folding unit 300, the movement mode of each part is consistent with that in the unfolding process, which will not be repeated here.

[0072] The present application has been disclosed in the above-mentioned preferred embodiments, however, is not intended to limit the present application, any person skilled in the art, without departing from the technical solution of the present application, according to the technical essence of the present application, any simple modification, equivalent change and modification of the above-mentioned embodiments, still belongs to the technical solution range of the present application.

Claims

1. A wing folding mechanism for a water-air transmedium vehicle, characterized in that: It includes a frame (100), a slider (200) and two sets of folding units (300). A hinge column (110) is integrally provided on the frame (100). The slider (200) is slidably connected to the frame (100). The two sets of folding units (300) are symmetrically arranged on both sides of the frame (100). The folding unit (300) includes a first wing rod (310), a second wing rod (320), a third wing rod (330), a fourth wing rod (340), a transmission rod (350), a first link (360), a second link (370), and a third link (380); The end of the first wing rod (310) is hinged to the hinge post (110), one end of the first link (360) is mounted on the hinge post (110), and the first link (360) can rotate relative to the hinge post (110). The other end of the first link (360) is fixedly connected to the end of the second wing rod (320). One end of the second link (370) is mounted on the second wing rod (320), and the second link (370) can rotate relative to the end of the second wing rod (320). The other end of the second link (370) is fixedly connected to the end of the third wing rod (330). One end of the third link (380) is mounted on the third wing rod (330), and the third link (380) can rotate relative to the end of the third wing rod (330). The other end of the third link (380) is fixedly connected to the end of the fourth wing rod (340). The two ends of the transmission rod (350) are respectively hinged to the middle of the slider (200) and the fourth wing rod (340). The slider (200) can drive the fourth wing rod (340), the third wing rod (330), the second wing rod (320) and the first wing rod (310) to unfold or fold in sequence. The upper surfaces of the first wing rod (310), the second wing rod (320), the third wing rod (330), and the fourth wing rod (340) are all fixed to the flexible wing membrane; the lower surfaces of the first wing rod (310), the second wing rod (320), the third wing rod (330), and the fourth wing rod (340) abut against the transmission rod (350).

2. The wing folding mechanism for a water-air transmedium vehicle according to claim 1, characterized in that: The upper wing surface of the first wing rod (310) is integrally provided with a first square tenon (311), the upper wing surface and the lower wing surface of the second wing rod (320) are integrally provided with a second square tenon (321) and a third square tenon (322), and the first link (360) is provided with a first square groove (361) and a second square groove (362). The first square tenon (311) is inserted into the first square groove (361), and the width of the first square groove (361) is greater than the width of the first square tenon (311); The second square tenon (321) is inserted into the second square groove (362), and the width of the second square groove (362) is equal to the width of the second square tenon (321); The upper and lower surfaces of the third wing (330) are integrally provided with a fourth square tenon (331) and a fifth square tenon (332), respectively, and the second link (370) has a third square groove (371) and a fourth square groove (372). The third tenon (322) is inserted into the third groove (371), and the width of the third groove (371) is greater than the width of the third tenon (322); the fifth tenon (332) is inserted into the fourth groove (372), and the width of the fourth groove (372) is equal to the width of the fifth tenon (332); The upper surface of the fourth wing rod (340) is integrally provided with a sixth square tenon (341), and the third link (380) has a fifth square groove (381) and a sixth square groove (382); The fourth tenon (331) is inserted into the fifth slot (381), and the width of the fifth slot (381) is greater than the width of the fourth tenon (331); the sixth tenon (341) is inserted into the sixth slot (382), and the width of the sixth slot (382) is equal to the width of the sixth tenon (341).

3. The wing folding mechanism for a water-air transmedium vehicle according to claim 1, characterized in that: The upper surfaces of the first wing rod (310), the second wing rod (320), and the third wing rod (330) are all arc-shaped, and the length direction of the first wing rod (310), the second wing rod (320), and the third wing rod (330) is perpendicular to the axis of the arc-shaped surface. The lower surfaces of the first wing rod (310), the second wing rod (320), and the third wing rod (330) are all planar. The cross-section of the fourth wing rod (340) is a right triangle.

4. The wing folding mechanism for a water-air transmedium vehicle according to claim 3, characterized in that: The radius of curvature of the arc surface of the first wing rod (310) is smaller than that of the arc surface of the second wing rod (320), and the radius of curvature of the arc surface of the second wing rod (320) is smaller than that of the arc surface of the third wing rod (330).

5. The wing folding mechanism for a water-air transmedium vehicle according to claim 4, characterized in that: The length of the first wing rod (310) is less than the length of the second wing rod (320), the length of the second wing rod (320) is less than the length of the third wing rod (330), and the length of the third wing rod (330) is less than the length of the fourth wing rod (340).

6. The wing folding mechanism for a water-air transmedium vehicle according to claim 5, characterized in that: The upper surface of the fourth wing rod (340) is integrally provided with a reinforcing rib.

Images