Foldable nested telescopic wing structure

Abstract

The invention relates to a foldable nested telescopic wing structure, and belongs to the field of unmanned aerial vehicles. Comprising a left wing, a right wing, a fuselage assembly (3), a wing rotating shaft assembly (4) and a wing rotation locking assembly (5), the left wing and the right wing are the same in structure, the wings are folded in a segmented mode through the wing rotating shaft assembly (4), then nested and contracted to the belly of the fuselage assembly (3) and locked through the wing rotating locking assembly (5), the unmanned aerial vehicle is unfolded through a driving torsion spring (43) in the wing rotating shaft assembly (4) after being launched, and after the unmanned aerial vehicle reaches the rotating locking position, locking of the telescopic mechanism is relieved, and the unmanned aerial vehicle is locked. And the left wing and the right wing slide outwards and extend. Through a'folding + stretching 'composite deformation mechanism, the wings are folded in sections and then nested and shrunk at the abdomen of the fuselage, so that the transportation and storage volume is obviously reduced.

Description

Technical Field

[0001] The present invention belongs to the field of unmanned aerial vehicles (UAVs), and in particular relates to a foldable, nested, and telescopic wing structure. Background Art

[0002] Currently, wing systems with a deep rotation lock function are primarily used in the design of small folding-wing aircraft. Their core function is to meet the space requirements of aircraft in scenarios such as loading and transportation, ground launch, and aerial delivery. Through wing folding and deformation technology, the entire aircraft can be adapted to the geometric constraints of the cylindrical launch tube, thereby achieving efficient storage and transportation and rapid deployment. Existing technical solutions mainly cover various structural forms such as single-axis rotating wings, telescopic wings, single-axis folding wings, and Z-folding wings. However, with the diversification of mission scenarios, more stringent technical indicators are being put forward for the aerodynamic performance and structural reliability of folding-wing UAVs.

[0003] Taking a typical single-axis rotary wing system as an example, its design has a significant dual constraint: in the longitudinal dimension, the wing span is limited by the fuselage length; in the lateral dimension, the chord length design needs to be strictly controlled within the fuselage width. Although this geometric constraint ensures that the aircraft forms a nearly cylindrical profile after folding and adapts to the size of the launch tube, it directly leads to the compression of the wing area. The resulting attenuation of lift characteristics seriously restricts the low-speed performance of the aircraft. In particular, when it is necessary to perform tasks with high low-speed control requirements such as long-term reconnaissance, the existing configuration is difficult to meet actual needs. In addition, the above-mentioned size limitations also lead to a narrowing of the optimization space for the wing aspect ratio, further affecting the aerodynamic efficiency and structural integrity of the aircraft. Summary of the Invention

[0004] (1) Technical issues to be resolved

[0005] The technical problem to be solved by the present invention is to provide a foldable nested telescopic wing structure to solve the problem that the existing configuration is difficult to meet actual needs.

[0006] (2) Technical solution

[0007] In order to solve the above technical problems, the present invention provides a foldable nested telescopic wing structure, comprising: a left wing, a right wing, a fuselage assembly 3, a wing shaft assembly 4, and a wing rotation locking assembly 5;

[0008] The left and right wings have the same structure. The wings are folded in sections through the wing shaft assembly 4 and then nested and retracted in the belly of the fuselage assembly 3, and locked by the wing rotation locking assembly 5. After the UAV is launched, the driving torsion spring 43 in the wing shaft assembly 4 is used to unfold. When the rotation locking position is reached, the telescopic mechanism is unlocked, and the left and right wings slide outward and extend.

[0009] Wherein, the left wing includes: a left inner wing assembly 6 and a left outer wing assembly 7;

[0010] The right wing comprises: a right outer wing assembly 1 and a right inner wing assembly 2;

[0011] The right outer wing assembly 1 and the left wing assembly 7 have the same structure and are in a mirror image relationship, and the right inner wing assembly 2 and the left wing assembly 6 have the same structure and are in a mirror image relationship;

[0012] The left inner wing assembly 6 and the left outer wing assembly 7 are described in detail below, wherein the left inner wing assembly 6 includes: a left wing root rib 61, a left wing joint 62, an outer wing locking hook 63, an inner hanging point 64 for a locking rope, a left inner wing main beam 65, a spring pin 66, a compression spring 67, a locking rope 68, and a left inner wing side rib 69;

[0013] The outer wing locking hook 63 is fixed to the left wing joint 62, and the left inner wing root rib 61, the left inner wing main beam 65, the left inner wing side rib 69 and the left inner wing skin are co-cured and formed;

[0014] The locking rope inner attachment point 64, spring pin 66, compression spring 67, and locking rope 68 are placed inside the wing. The locking rope 68 passes through the center of the compression spring 67, with one end fixed to the locking rope inner attachment point 64 and the other end fixed to the locking rope outer attachment point 73. The spring pin 66 is installed on the left inner wing side rib 69 to lock the left outer wing assembly 7.

[0015] The left outer wing assembly 7 includes: a left outer wing skin 71, a sliding sleeve 72, a locking rope external attachment point 73, an outer wing side rib 74, a sliding sleeve mounting seat 75, and an outer wing locking rope 76;

[0016] The left outer wing skin 71 and the outer wing edge rib 74 are co-cured and formed, the sliding sleeve 72 is sleeved on the sliding sleeve mounting seat 75, and the locking rope external attachment point 73 is installed inside the sliding sleeve mounting seat 75;

[0017] The inner wing main beam 65 and the sliding sleeve 72 are plugged into a guide rail structure, and the compression spring 67 is arranged inside the guide rail cavity so that the leading and trailing edges of the wing will not get stuck due to skew when the left outer wing assembly 7 slides out.

[0018] The fuselage assembly 3 includes: an unlocking pin 31, a wing mounting plate 32, and a fuselage shell 33;

[0019] The wing mounting plate 32 is provided on the fuselage shell, and the wing mounting plate 32 is provided with a wing shaft assembly 4 and an unlocking pin 31;

[0020] The left inner wing assembly 6 is mounted on the wing mounting plate 32 via the wing shaft assembly 4 .

[0021] The wing shaft assembly 4 includes: a wing pressure plate 41, an upper needle roller bearing 42, a driving torsion spring 43, a middle needle roller bearing 44, a torsion spring sleeve 45, a shaft seat 46, and a lower needle roller bearing 47;

[0022] The lower needle roller bearing 47 is arranged on the wing mounting plate 32, and a rotating shaft seat 46 is provided on the lower needle roller bearing 47. A driving torsion spring 43 is provided on the rotating shaft seat 46. A torsion spring sleeve 45 is provided on the driving torsion spring 43. The middle part of the driving torsion spring 43 is connected to the middle needle roller bearing 44, and the top of the driving torsion spring 43 is connected to the upper needle roller bearing 42. A wing pressure plate 41 is provided on the outside of the upper needle roller bearing 42. A screw hole is opened in the middle part of the wing pressure plate 41, and the wing pressure plate 41 is fixed to the wing mounting plate 32 by bolts.

[0023] When the wing is in the folded state, the torsion spring 43 is driven to be in a rotational energy storage state.

[0024] The wing rotation locking assembly 5 includes: a locking housing 51, a compression spring cover 52, a lock tongue compression spring 53, a lock tongue 54, and a buffer pad 55;

[0025] The lock tongue compression spring 53 is installed inside the locking shell 51 through the compression spring cover 52, with one end pressing against the lock tongue 54 and the other end pressing against the compression spring cover 52. The locking shell 51 is fixed on the fuselage assembly 3. When the wing rotates to a predetermined position, the lock tongue 54 pops out under the thrust of the lock tongue compression spring 53 and is inserted into the notch of the left wing joint 62 to achieve rotational locking of the wing.

[0026] Among them, when the wing is in the retracted state, the left outer wing assembly 7 is folded on the outside of the left inner wing assembly 6 and is hooked on the outer wing locking hook 63 by the outer wing locking rope 76. At this time, the compression spring 67 is in a strong compression state, and the stored elastic potential energy reaches the maximum.

[0027] Among them, when the drone is launched out of the tube, the wings are released, and the torque stored in the driving torsion spring 43 is quickly released to drive the wings to rotate and open. At this time, the left outer wing is still restrained by the outer wing locking hook 63 and the outer wing locking rope 76 and cannot slide outward;

[0028] When the wing rotates nearly 90°, the outer wing locking rope 76 touches the unlocking pin 31, and the outer wing locking rope 76 slips off the outer wing locking hook 63. The compression spring 67 inside the left inner wing assembly 6 quickly releases energy to push the outer wing assembly 7 to slide outward. After reaching the predetermined position, it stops sliding due to the length limit of the locking rope 68. At the same time, the spring pin 66 pops out and inserts into the locking hole of the outer wing skin 71 to achieve outer wing locking.

[0029] (3) Beneficial effects

[0030] Compared with the existing technology, the present invention has the following beneficial effects: the UAV wings are folded in sections through a "folding + telescopic" composite deformation mechanism, and then nested and retracted in the belly of the fuselage, which significantly reduces the transportation and storage volume, and at the same time makes it possible to launch in a tube; by rotating the torsion spring to unfold, when it reaches the rotational locking position, the telescopic mechanism lock is released, and the outer wing slides and extends outward, increasing the wing area, increasing the wingspan, optimizing the lift-to-drag ratio, reducing cruise energy consumption, and improving low-speed performance. The multi-stage mechanical locking system completes the wing surface attitude fixation within milliseconds, ensuring anti-vibration stability during flight. At the same time, the fully mechanical transmission structure does not need to rely on motors or complex circuits, reduces the failure rate, adapts to extreme environments, and avoids the failure risk of the electric drive system. BRIEF DESCRIPTION OF THE DRAWINGS

[0031] Figure 1 This is a main axonometric view of the UAV of the present invention with its wings in a locked state;

[0032] Figure 2 This is a main axonometric view of the UAV of the present invention with its wings in a folded state;

[0033] Figure 3 is a cross-sectional view of the UAV wing shaft assembly of the present invention;

[0034] Figure 4 This is a main axonometric view of the UAV wing locking assembly of the present invention;

[0035] Figure 5 This is an axonometric view and local detail view of the folded and nested UAV of the present invention;

[0036] Figure 6 It is an axonometric view and local detail view of the outer wing locking mechanism of the UAV of the present invention. DETAILED DESCRIPTION

[0037] In order to make the purpose, content, and advantages of the present invention more clear, the specific implementation methods of the present invention are further described in detail below with reference to the accompanying drawings and examples.

[0038] In this embodiment, a foldable nested telescopic wing structure includes: a left wing, a right wing, a fuselage assembly 3, a wing shaft assembly 4, and a wing rotation locking assembly 5;

[0039] The left and right wings have the same structure. The wings are folded in sections through the wing shaft assembly 4 and then nested and retracted in the belly of the fuselage assembly 3, and locked by the wing rotation locking assembly 5. After the UAV is launched, the driving torsion spring 43 in the wing shaft assembly 4 is used to unfold. When the rotation locking position is reached, the telescopic mechanism is unlocked, and the left and right wings slide outward and extend.

[0040] Wherein, the left wing includes: a left inner wing assembly 6 and a left outer wing assembly 7;

[0041] The right wing comprises: a right outer wing assembly 1 and a right inner wing assembly 2;

[0042] The right outer wing assembly 1 and the left wing assembly 7 have the same structure and are in a mirror image relationship, and the right inner wing assembly 2 and the left wing assembly 6 have the same structure and are in a mirror image relationship;

[0043] The left inner wing assembly 6 and the left outer wing assembly 7 are described in detail below, wherein the left inner wing assembly 6 includes: a left wing root rib 61, a left wing joint 62, an outer wing locking hook 63, an inner hanging point 64 for a locking rope, a left inner wing main beam 65, a spring pin 66, a compression spring 67, a locking rope 68, and a left inner wing side rib 69;

[0044] The outer wing locking hook 63 is fixed to the left wing joint 62, and the left inner wing root rib 61, the left inner wing main beam 65, the left inner wing side rib 69 and the left inner wing skin are co-cured and formed;

[0045] The locking rope inner attachment point 64, spring pin 66, compression spring 67, and locking rope 68 are placed inside the wing. The locking rope 68 passes through the center of the compression spring 67, with one end fixed to the locking rope inner attachment point 64 and the other end fixed to the locking rope outer attachment point 73. The spring pin 66 is installed on the left inner wing side rib 69 to lock the left outer wing assembly 7.

[0046] The left outer wing assembly 7 includes: a left outer wing skin 71, a sliding sleeve 72, a locking rope external attachment point 73, an outer wing side rib 74, a sliding sleeve mounting seat 75, and an outer wing locking rope 76;

[0047] The left outer wing skin 71 and the outer wing edge rib 74 are co-cured and formed, the sliding sleeve 72 is sleeved on the sliding sleeve mounting seat 75, and the locking rope external attachment point 73 is installed inside the sliding sleeve mounting seat 75;

[0048] The inner wing main beam 65 and the sliding sleeve 72 are plugged into a guide rail structure, and the compression spring 67 is arranged inside the guide rail cavity so that the leading and trailing edges of the wing will not get stuck due to skew when the left outer wing assembly 7 slides out.

[0049] The fuselage assembly 3 includes: an unlocking pin 31, a wing mounting plate 32, and a fuselage shell 33;

[0050] The wing mounting plate 32 is provided on the fuselage shell, and the wing mounting plate 32 is provided with a wing shaft assembly 4 and an unlocking pin 31;

[0051] The left inner wing assembly 6 is mounted on the wing mounting plate 32 via the wing shaft assembly 4 .

[0052] The wing shaft assembly 4 includes: a wing pressure plate 41, an upper needle roller bearing 42, a driving torsion spring 43, a middle needle roller bearing 44, a torsion spring sleeve 45, a shaft seat 46, and a lower needle roller bearing 47;

[0053] The lower needle roller bearing 47 is arranged on the wing mounting plate 32, and a rotating shaft seat 46 is provided on the lower needle roller bearing 47. A driving torsion spring 43 is provided on the rotating shaft seat 46. A torsion spring sleeve 45 is provided on the driving torsion spring 43. The middle part of the driving torsion spring 43 is connected to the middle needle roller bearing 44, and the top of the driving torsion spring 43 is connected to the upper needle roller bearing 42. A wing pressure plate 41 is provided on the outside of the upper needle roller bearing 42. A screw hole is opened in the middle part of the wing pressure plate 41, and the wing pressure plate 41 is fixed to the wing mounting plate 32 by bolts.

[0054] When the wing is in the folded state, the torsion spring 43 is driven to be in a rotational energy storage state.

[0055] The wing rotation locking assembly 5 includes: a locking housing 51, a compression spring cover 52, a lock tongue compression spring 53, a lock tongue 54, and a buffer pad 55;

[0056] The lock tongue compression spring 53 is installed inside the locking shell 51 through the compression spring cover 52, with one end pressing against the lock tongue 54 and the other end pressing against the compression spring cover 52. The locking shell 51 is fixed on the fuselage assembly 3. When the wing rotates to a predetermined position, the lock tongue 54 pops out under the thrust of the lock tongue compression spring 53 and is inserted into the notch of the left wing joint 62 to achieve rotational locking of the wing.

[0057] Among them, when the wing is in the retracted state, the left outer wing assembly 7 is folded on the outside of the left inner wing assembly 6 and is hooked on the outer wing locking hook 63 by the outer wing locking rope 76. At this time, the compression spring 67 is in a strong compression state, and the stored elastic potential energy reaches the maximum.

[0058] Among them, when the drone is launched out of the tube, the wings are released, and the torque stored in the driving torsion spring 43 is quickly released to drive the wings to rotate and open. At this time, the left outer wing is still restrained by the outer wing locking hook 63 and the outer wing locking rope 76 and cannot slide outward;

[0059] When the wing rotates nearly 90°, the outer wing locking rope 76 touches the unlocking pin 31, and the outer wing locking rope 76 slips off the outer wing locking hook 63. The compression spring 67 inside the left inner wing assembly 6 quickly releases energy to push the outer wing assembly 7 to slide outward. After reaching the predetermined position, it stops sliding due to the length limit of the locking rope 68. At the same time, the spring pin 66 pops out and inserts into the locking hole of the outer wing skin 71 to achieve outer wing locking.

[0060] After sliding into place here, a double locking mechanism of rope limit + pin locking is adopted to ensure rigid locking after deployment and resist flight vibration.

[0061] In this structure, the inner wing main beam 65 in the inner wing assembly 6 and the sliding sleeve 72 in the outer wing assembly 7 form a guide rail structure to ensure that when the outer wing assembly slides out, the leading and trailing edges of the wing will not get stuck due to skew, affecting the smooth sliding of the wing.

[0062] After the outer wing lock rope 76 touches the unlocking pin 31, the wing assembly continues to rotate until the left wing joint 62 hits the buffer pad 55 and stops rotating. The lock tongue 54 in the wing rotation locking assembly 5 pops out under the action of the lock tongue compression spring 53 and inserts into the side notch of the left wing joint 62 in the inner wing assembly 6, thereby achieving rotation locking of the wing.

[0063] After the above-mentioned wing rotation and outer wing sliding movement are completed and locked, the wing reaches a fully locked state.

[0064] The above is only a preferred embodiment of the present invention. It should be pointed out that for ordinary technicians in this technical field, several improvements and modifications can be made without departing from the technical principles of the present invention. These improvements and modifications should also be regarded as the scope of protection of the present invention.

Claims

1. A foldable nested telescopic wing structure, characterized in that: include: Left wing, right wing, fuselage assembly (3), wing shaft assembly (4), wing rotation locking assembly (5); The left and right wings have the same structure. The wings are folded in sections by the wing shaft assembly (4) and then nested and retracted in the belly of the fuselage assembly (3). The wings are locked by the wing rotation locking assembly (5). After the UAV is launched, the wings are unfolded by the driving torsion spring (43) in the wing shaft assembly (4). When the rotation locking position is reached, the telescopic mechanism is unlocked, and the left and right wings slide outward and extend.

2. The foldable nested telescopic wing structure according to claim 1, characterized in that: The left wing comprises: a left inner wing assembly (6) and a left outer wing assembly (7); The right wing comprises: a right outer wing assembly (1) and a right inner wing assembly (2); The right outer wing assembly (1) and the left wing assembly (7) have the same structure and are in a mirror image relationship, and the right inner wing assembly (2) and the left wing assembly (6) have the same structure and are in a mirror image relationship; The left inner wing assembly (6) and the left outer wing assembly (7) are described in detail below, wherein the left inner wing assembly (6) includes: a left wing root rib (61), a left wing joint (62), an outer wing lock hook (63), an inner hanging point of a locking rope (64), a left inner wing main beam (65), a spring pin (66), a compression spring (67), a locking rope (68), and a left inner wing side rib (69); The outer wing locking hook (63) is fixed on the left wing joint (62), and the left inner wing root rib (61), the left inner wing main beam (65), the left inner wing side rib (69) and the left inner wing skin are co-cured and formed; The locking rope inner hanging point (64), spring pin (66), compression spring (67), and locking rope (68) are placed inside the wing. The locking rope (68) passes through the center of the compression spring (67), one end of which is fixed to the locking rope inner hanging point (64), and the other end is fixed to the locking rope outer hanging point (73). The spring pin (66) is installed on the left inner wing side rib (69) to lock the left outer wing assembly (7). The left outer wing assembly (7) comprises: a left outer wing skin (71), a sliding sleeve (72), a locking rope external attachment point (73), an outer wing side rib (74), a sliding sleeve mounting seat (75), and an outer wing locking rope (76); The left outer wing skin (71) and the outer wing side rib (74) are co-cured and formed, the sliding sleeve (72) is sleeved on the sliding sleeve mounting seat (75), and the locking rope external hanging point (73) is installed inside the sliding sleeve mounting seat (75); The inner wing main beam (65) and the sliding sleeve (72) are plugged into a guide rail structure, and the compression spring (67) is arranged inside the guide rail cavity so that the left outer wing assembly (7) will not be stuck at the front and rear edges of the wing due to skewness when sliding out.

3. The foldable nested telescopic wing structure according to claim 2, characterized in that: The fuselage assembly (3) comprises: an unlocking pin (31), a wing mounting plate (32), and a fuselage shell (33); The wing mounting plate (32) is arranged on the fuselage shell, and the wing mounting plate (32) is provided with a wing shaft assembly (4) and an unlocking pin (31); The left inner wing assembly (6) is mounted on the wing mounting plate (32) via the wing shaft assembly (4).

4. The foldable nested telescopic wing structure according to claim 3, wherein: The wing shaft assembly (4) comprises: a wing pressure plate (41), an upper needle roller bearing (42), a driving torsion spring (43), a middle needle roller bearing (44), a torsion spring sleeve (45), a shaft seat (46), and a lower needle roller bearing (47); The lower needle roller bearing (47) is arranged on the wing mounting plate (32), the lower needle roller bearing (47) is provided with a rotating shaft seat (46), the rotating shaft seat (46) is provided with a driving torsion spring (43), the driving torsion spring (43) is provided with a torsion spring sleeve (45), the middle part of the driving torsion spring (43) is connected to the middle needle roller bearing (44), the top of the driving torsion spring (43) is connected to the upper needle roller bearing (42), the outer part of the upper needle roller bearing (42) is provided with a wing pressure plate (41), the middle part of the wing pressure plate (41) is provided with a screw hole, and the wing pressure plate (41) is fixed to the wing mounting plate (32) by bolts; When the wing is in the folded state, the torsion spring (43) is driven to be in a rotation energy storage state.

5. The foldable nested telescopic wing structure according to claim 4, characterized in that: The wing rotation locking assembly (5) comprises: a locking housing (51), a compression spring cover plate (52), a lock tongue compression spring (53), a lock tongue (54), and a buffer pad (55); The locking tongue compression spring (53) is installed inside the locking housing (51) through the compression spring cover (52), with one end supporting the locking tongue (54) and the other end supporting the compression spring cover (52). The locking housing (51) is fixed on the fuselage assembly (3). When the wing rotates to a predetermined position, the locking tongue (54) pops out under the thrust of the locking tongue compression spring (53) and is inserted into the notch of the left wing joint (62), thereby realizing the rotation locking of the wing.

6. The foldable nested telescopic wing structure according to claim 5, characterized in that: When the wing is in the retracted state, the left outer wing assembly (7) is nested on the outside of the left inner wing assembly (6) and is hooked on the outer wing lock hook (63) by the outer wing lock rope (76). At this time, the compression spring (67) is in a strong compression state and the stored elastic potential energy reaches the maximum.

7. The foldable nested telescopic wing structure according to claim 6, wherein: When the drone is launched out of the tube, the wings are released, and the torque stored in the driving torsion spring (43) is quickly released to drive the wings to rotate and open. At this time, the left outer wing is still restrained by the outer wing lock hook (63) and the outer wing lock rope (76) and cannot slide outward; When the wing rotates close to 90 degrees, the outer wing locking rope (76) touches the unlocking pin (31), and the outer wing locking rope (76) slips off the outer wing locking hook (63). The compression spring (67) inside the left inner wing assembly (6) quickly releases energy to push the outer wing assembly (7) to slide outward. After reaching the predetermined position, it stops sliding due to the length limit of the locking rope (68). At the same time, the spring pin (66) pops out and inserts into the locking hole of the outer wing skin (71), thereby locking the outer wing.

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