A foldable edge strip wing structure with a synchronization unlocking function

Abstract

The application relates to the technical field of aircraft folding wing, and discloses a foldable edge strip wing structure with a synchronous unlocking function, which comprises a fixed wing, a movable wing, a torsion bar, a folding locking mechanism and an unfolding locking mechanism. The movable wing is rotationally connected with the fixed wing through a rotating shaft, and the torsion bar is arranged in the rotating shaft. The folding locking mechanism comprises an integral locking rod. When the locking rod is pulled, the first locking elements at both ends are synchronously released from the limiting position. The unlocking is completed by using a spring to push a locking cover, so that the unlocking jamming is avoided. After unlocking, the torsion bar releases the elastic force to drive the movable wing to unfold. When the movable wing is unfolded to the position, the normal and axial locking mechanisms in the unfolding locking mechanism mechanically engage the movable wing from two dimensions. The driving structure is compact, the jamming probability during unlocking of multiple mechanisms is effectively reduced, the double locking limits the shaking of the wing surface after unfolding, and the structural stability of the edge strip wing during work is improved.

Description

Technical Field

[0001] This invention relates to the field of aircraft folding wing technology, specifically a foldable leading edge wing structure with synchronous unlocking function. Background Technology

[0002] In the aerospace field, to increase the payload of fighter jets and accommodate the internal weapons bay space, airborne weapons typically employ foldable wing designs. Foldable wings remain folded during the loading phase to reduce the outer envelope size, and unfold after unloading to provide the aircraft with the necessary lift and maneuverability. As a common aerodynamic surface, the reliability of the folding and unfolding actions of leading-edge extensions (LEXs) directly affects the operational status of the aircraft.

[0003] Existing folding strake wings have some structural design shortcomings during use. During the folding, locking, and unlocking phases, to ensure the wing surface doesn't loosen during mounting, locking nodes are typically installed at both ends or multiple locations on the wing surface. However, most existing multi-point unlocking structures use independent drives or lack rigid physical synchronization mechanisms. In actual unlocking operations, due to manufacturing tolerances, uneven stress, and other factors, a time difference can easily occur where some mechanisms unlock first while others unlock later. This asynchrony can lead to uneven loading and mechanical jamming of internal connectors, resulting in slow wing surface deployment or complete failure.

[0004] During the locking phase after the wing has fully deployed, most current deployment locking devices rely on a single-directional spring pin for limitation. This one-dimensional locking method cannot effectively constrain the structure's degrees of freedom in other directions, resulting in a certain mechanical clearance. When the aircraft is flying at high speed and subjected to complex aerodynamic loads, the one-dimensional locking can cause the deployed wing to vibrate, reducing the structural stiffness of the wing and the aerodynamic stability of the aircraft. Furthermore, some existing folding wings rely on complex external push rods or additional power components as the deployment drive source, which increases the number of structural components and overall weight, hindering the compact design of the weapon's internal space. Summary of the Invention

[0005] To address the shortcomings of existing technologies, this invention provides a foldable wing structure with synchronous unlocking function, which solves the problems of existing foldable wings, such as asynchronous unlocking of multiple nodes leading to mechanical jamming, and single-dimensional locking after unfolding causing the wing surface to shake and the structure not being compact enough.

[0006] To achieve the above objectives, the present invention provides the following technical solution: a foldable wing structure with synchronous unlocking function, comprising a fixed wing, a movable wing, a torsion bar, a folding locking mechanism, and an unfolding locking mechanism; The movable wing includes a rotating shaft, and the movable wing is rotatably connected to the fixed wing through the rotating shaft. The torsion bar passes through the rotating shaft. The folding locking mechanism includes a locking rod, a first locking element, a locking cover, and a first spring. The locking rod and the first locking element are installed inside the fixed wing, and the locking cover and the first spring are installed on the rotating shaft of the movable wing. The locking rod abuts against the first locking element, the first locking element abuts against the locking cover, and the locking cover is connected to the first spring. The deployment locking mechanism includes a normal locking mechanism and an axial locking mechanism. The normal locking mechanism is disposed between the fixed wing and the moving wing, and the axial locking mechanism is disposed on the rotation shaft and the torsion bar.

[0007] Preferably, the folding locking mechanism is provided in two sets, and the two sets of folding locking mechanisms are symmetrically installed at both ends of the fixed wing and the moving wing. The locking rod is an integral structure, and the two ends of the locking rod respectively abut against the first locking element in the two sets of folding locking mechanisms.

[0008] Preferably, the locking rod has a locking rod groove, and the first locking element slides in conjunction with the locking rod groove.

[0009] Preferably, the rotating shaft has a rotating shaft groove inside, the first spring is installed in the rotating shaft groove, and the locking cover is slidably engaged with the rotating shaft groove; When the first locking element is fully positioned within the locking rod groove, the surface of the locking cover becomes flush with the surface of the rotating shaft under the push of the first spring.

[0010] Preferably, the normal locking mechanism includes a second spring, a second locking element, and a moving wing limiting hole, wherein the second spring is sleeved on the outside of the second locking element; The axial locking mechanism includes a slide lock and a slide key.

[0011] Preferably, the second spring and the second locking element are installed inside the fixed wing, the moving wing limiting hole is opened on the moving wing, the two ends of the second spring abut against the inside of the fixed wing and the second locking element respectively, when the moving wing rotates to be on the same plane as the fixed wing, the second locking element is aligned with the moving wing limiting hole, and the end of the second locking element is movably inserted into the moving wing limiting hole.

[0012] Preferably, the sliding lock is sleeved on the outside of the torsion bar, and the sliding lock is connected to the moving wing through the sliding key, and the sliding lock can rotate synchronously with the moving wing.

[0013] Preferably, the slide lock is provided with a protrusion, and the rotating shaft is provided with a rotating shaft groove that cooperates with the protrusion. The axial locking mechanism also includes an axial spring, which is sleeved on the outside of the torsion bar, and the two ends of the axial spring abut against the moving wing and the slide lock respectively. The slide lock can slide along the axial direction of the torsion bar under the action of the axial spring so that the protrusion is inserted into the rotating shaft groove.

[0014] Preferably, the deployment locking mechanism further includes a limiting groove, which includes a fixed wing groove disposed on the fixed wing and a moving wing groove disposed on the moving wing. When the moving wing rotates to be on the same plane as the fixed wing, the fixed wing groove and the moving wing groove abut against each other.

[0015] Preferably, the fixed wing is provided with a fixed wing rotation shaft, a hexagonal limiting post is fixedly provided on the fixed wing rotation shaft, a cylindrical limiting post is fixedly provided on the rotation shaft, and the two ends of the torsion bar are fixedly connected to the hexagonal limiting post and the cylindrical limiting post respectively. When the moving wing and the fixed wing are in a folded state, the torsion bar is in a torsional energy storage state.

[0016] This invention provides a foldable wing structure with synchronous unlocking function. It has the following advantages: 1. This invention features an integral locking rod, with both ends abutting against the first locking elements in two symmetrically arranged folding locking mechanisms. During the unfolding action, the drive device only needs to pull the integral locking rod to simultaneously release the first locking elements at both ends. Subsequently, the first spring pushes the locking cover to unlock. This structure achieves mechanical synchronous linkage between the locking mechanisms on both sides, reduces the probability of mechanical jamming caused by time differences when unlocking multiple nodes independently, and improves the reliability of the structure's unlocking action.

[0017] 2. This invention utilizes a torsion bar as the driving source for the deployment of the moving wing. The torsion bar is inserted inside the rotating shaft of the moving wing, with its two ends fixedly connected to the fixed wing and the moving wing, respectively. When the moving wing is in the folded state, the torsion bar is twisted and stores preload. When the folding locking mechanism is unlocked, the torsion bar releases the stored torque, directly driving the moving wing to rotate around the rotating shaft to the deployed state. This driving method utilizes the internal space to achieve energy storage and driving, eliminating the need for complex external power components. This makes the internal structure of the leading-edge wing compact and facilitates control of the overall size of the equipment.

[0018] 3. The deployment locking mechanism of the present invention adopts a dual locking design of normal and axial directions. When the movable wing is deployed to the same plane as the fixed wing, the second spring pushes the second locking element into the movable wing limiting hole to achieve normal locking; at the same time, the axial spring pushes the slide lock to slide along the axial direction, so that the protrusion on the slide lock is inserted into the rotating shaft groove of the fixed wing to achieve axial locking. Through the mechanical engagement of two mutually perpendicular directions in space, the degree of freedom of movement of the movable wing after deployment is restricted, the vibration of the wing surface under the action of external airflow is reduced, and the structural stability of the strake wing in the deployed state is ensured. Attached Figure Description

[0019] Figure 1 This is a schematic diagram of the unfolded state of the present invention; Figure 2 This is a schematic diagram of the folded state of the present invention; Figure 3 This is a schematic diagram of the folding locking mechanism of the present invention; Figure 4 This is a schematic diagram of the unfolding and locking mechanism of the present invention; Figure 5 This is a schematic diagram of the limiting groove structure of the present invention.

[0020] Among them, 1. locking rod; 2. first locking element; 3. locking cover; 4. first spring; 5. second spring; 6. second locking element; 7. moving wing limiting hole; 8. sliding lock; 9. sliding key; 10. limiting groove. Detailed Implementation

[0021] The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. 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 are within the scope of protection of the present invention.

[0022] Please see the appendix Figure 1 -Appendix Figure 3 This invention provides a foldable wing structure with synchronous unlocking function, including a fixed wing, a movable wing, a torsion bar, a folding locking mechanism, and an unfolding locking mechanism; The movable wing includes a rotating shaft, which rotatably connects the movable wing to the fixed wing. A torsion bar passes through the rotating shaft. The folding locking mechanism includes a locking rod 1, a first locking element 2, a locking cover 3, and a first spring 4. The locking rod 1 and the first locking element 2 are installed inside the fixed wing, and the locking cover 3 and the first spring 4 are installed on the rotating shaft of the movable wing. The locking rod 1 abuts against the first locking element 2, the first locking element 2 abuts against the locking cover 3, and the locking cover 3 is connected to the first spring 4. The deployment locking mechanism includes a normal locking mechanism and an axial locking mechanism. The normal locking mechanism is located between the fixed wing and the moving wing, and the axial locking mechanism is located between the torsion bar and the rotation shaft.

[0023] The foldable strake structure is designed to maintain a folded state when missiles are mounted, thereby reducing the missile's outer envelope radius and increasing the aircraft's payload. After missile launch, it unfolds to enhance the missile's lift and maneuverability. The torsion bar is a metal elastic torsion bar, which provides driving force to rapidly unfold the strake after it is unlocked. The strake, in conjunction with the torsion bar, rotates around its axis, achieving the effect of rotating the strake from a folded state to an unfolded state where it is on the same horizontal plane as the fixed wing. The first spring 4, in conjunction with the locking cover 3 and the first locking element 2, performs a linear pushing motion. When the drive device pulls the locking rod 1, the first spring 4 pushes the locking cover 3, and the locking cover 3 pushes the first locking element 2 to fully enter the groove of the locking rod 1, so that the surface of the locking cover 3 is just flush with the surface of the rotating shaft, thus achieving the effect of unlocking the moving wing. The normal locking mechanism, in conjunction with the axial locking mechanism, performs a double locking motion, which reduces the instability of the wing surface after the moving wing is fully deployed and improves the stability of the wing surface after it is fully deployed.

[0024] Please see the appendix Figure 1 -Appendix Figure 3 The folding locking mechanism is provided in two sets, which are symmetrically installed at both ends of the fixed wing and the moving wing. The locking rod 1 is an integral structure, and the two ends of the locking rod 1 respectively abut against the first locking element 2 in the two sets of folding locking mechanisms.

[0025] The locking lever 1 is used to synchronously control the folding locking mechanisms at both ends, so that when the locking lever 1 is pulled, the two symmetrical folding locking mechanisms are unlocked at the same time, which greatly reduces the probability of jamming when multiple mechanisms are unlocked and improves the performance of the entire side slat wing structure.

[0026] Please see the appendix Figure 1 -Appendix Figure 3 The locking rod 1 has a locking rod 1 groove, and the first locking element 2 slides in conjunction with the locking rod 1 groove.

[0027] Please see the appendix Figure 4 The rotating shaft has a groove inside, the first spring 4 is installed in the groove, and the locking cover 3 slides in the groove. The locking cover 3 is designed to slide linearly in conjunction with the groove of the rotating shaft, so that it is pushed by the first spring 4 when the missile is launched, and further pushes the first locking element 2 to unlock.

[0028] When the first locking element 2 is fully located in the groove of the locking rod 1, the surface of the locking cover 3 is flush with the surface of the rotating shaft.

[0029] The first locking element 2, in conjunction with the locking rod 1, slides to achieve the effect of unlocking the wing when the first locking element 2 is fully inserted into the groove of the locking rod 1 and the surface of the locking cover 3 is just flush with the surface of the rotating shaft.

[0030] Please see the appendix Figure 4 The normal locking mechanism includes a second spring 5, a second locking element 6 and a moving wing limiting hole 7, with the second spring 5 sleeved on the outside of the second locking element 6; The axial locking mechanism includes a slide lock 8 and a slide key 9.

[0031] The second spring 5 is made of spring steel and its function is to store preload to push the second locking element 6. The normal locking mechanism works in conjunction with the axial locking mechanism to perform a double deployment locking motion, which reduces the instability of the wing surface after the wing is deployed and improves the stability of the wing surface after deployment.

[0032] Please see the appendix Figure 4 The second spring 5 and the second locking element 6 are installed inside the fixed wing. The moving wing limiting hole 7 is opened on the moving wing. The two ends of the second spring 5 abut against the inside of the fixed wing and the second locking element 6 respectively. When the moving wing rotates to be on the same plane as the fixed wing, the second locking element 6 is aligned with the moving wing limiting hole 7, and the end of the second locking element 6 is movably inserted into the moving wing limiting hole 7.

[0033] The second spring 5, in conjunction with the second locking element 6, performs a linear push-out motion, so that when the moving wing unfolds to the same plane as the fixed wing, the preload stored in the second spring 5 pushes out the second locking element 6 and inserts it into the moving wing limiting hole 7, thus achieving the effect of normal locking.

[0034] Please see the appendix Figure 4 The sliding lock 8 is fitted on the outside of the torsion bar. The sliding lock 8 is connected to the moving wing through the sliding key 9. The sliding lock 8 can rotate synchronously with the moving wing.

[0035] The sliding lock 8 is designed to rotate synchronously with the sliding key 9, achieving the effect that the rotation of the sliding lock 8 completely follows the rotation of the moving wing.

[0036] Please see the appendix Figure 4 The slide lock 8 is provided with a protrusion, and the rotating shaft is provided with a rotating shaft groove that cooperates with the protrusion. The axial locking mechanism also includes an axial spring, which is sleeved on the outside of the torsion bar, and the two ends of the axial spring abut against the moving wing and the slide lock 8 respectively. The slide lock 8 can slide along the torsion bar axial direction under the action of the axial spring so that the protrusion is inserted into the rotating shaft groove.

[0037] The axial spring is made of spring steel and its function is to push the slide lock 8 along the axial direction. The protrusion on the slide lock 8 cooperates with the rotating shaft groove to perform axial insertion movement, thereby achieving the effect of axial locking of the moving wing after it has been unfolded to the same plane.

[0038] Please see the appendix Figure 5 The locking mechanism also includes a limiting groove 10, which includes a fixed wing groove on the fixed wing and a moving wing groove on the moving wing. When the moving wing rotates to be on the same plane as the fixed wing, the fixed wing groove and the moving wing groove abut against each other.

[0039] The limiting groove 10 is designed to prevent the moving wing from continuing to rotate, thereby avoiding excessive deployment of the moving wing and facilitating stable locking by the normal and axial locking mechanisms.

[0040] Please see the appendix Figure 1 -Appendix Figure 5 The fixed wing is equipped with a fixed wing rotation shaft, a hexagonal limiting post is fixedly installed on the fixed wing rotation shaft, and a cylindrical limiting post is fixedly installed on the rotation shaft. The two ends of the torsion bar are fixedly connected to the hexagonal limiting post and the cylindrical limiting post respectively. When the moving wing and the fixed wing are in the folded state, the torsion bar is in the torsional energy storage state.

[0041] The torsion bar is designed to provide driving force after the moving wing is unlocked by the folding unlocking mechanism, thereby causing the moving wing to unfold rapidly, achieving the effect of quickly bringing the moving wing and the fixed wing to the same horizontal plane and completing the unfolding state.

[0042] Working principle: During the missile loading phase, the moving wing is in a folded state, the torsion bar is twisted and in a torsional energy storage state, and the locking rod 1 of the integral structure in the folding locking mechanism restricts the first locking element 2. The first locking element 2 abuts against the locking cover 3, so that the first spring 4 installed in the groove of the rotating shaft is in a compressed energy storage state, and the moving wing is locked in the folded position. When the missile is launched, the drive device (such as the existing linear motor or hydraulic push rod) pulls the locking rod 1, so that the first locking elements 2 at both ends are released simultaneously. The first spring 4 pushes the locking cover 3, and the locking cover 3 further pushes the first locking element 2 to slide in the groove of the locking rod 1. When the first locking element 2 is completely slid into the groove of the locking rod 1 and the surface of the locking cover 3 is flush with the surface of the rotating shaft, the folding locking mechanism at both ends is unlocked simultaneously. After unlocking, the torsion bar in the torsional energy storage state provides driving force, causing the movable wing to rotate around the rotation axis and move towards the deployed state. During the rotation of the movable wing, the sliding lock 8 rotates synchronously with the movable wing through the sliding key 9. When the movable wing rotates to the same plane as the fixed wing, the fixed wing groove on the fixed wing and the movable wing groove on the movable wing abut against each other to prevent the movable wing from continuing to rotate. At the same time, the second locking element 6 is aligned with the movable wing limiting hole 7, and the second spring 5 pushes the second locking element 6 out and inserts its end into the movable wing limiting hole 7 to complete the normal locking. The axial spring abutting against the sliding lock 8 pushes the sliding lock 8 to slide axially, so that the protrusion on the sliding lock 8 is inserted into the rotating shaft groove on the rotation axis to complete the axial locking. Through the dual locking of normal and axial directions, the movable wing remains in the deployed state, reducing the wing surface flutter and improving the structural stability of the strake wing after deployment.

Claims

1. A foldable wing structure with synchronous unlocking function, characterized in that, Includes fixed wing, movable wing, torsion bar, folding locking mechanism and unfolding locking mechanism; The movable wing includes a rotating shaft, and the movable wing is rotatably connected to the fixed wing through the rotating shaft. The torsion bar passes through the rotating shaft. The folding locking mechanism includes a locking rod (1), a first locking element (2), a locking cover (3), and a first spring (4). The locking rod (1) and the first locking element (2) are installed inside the fixed wing. The locking cover (3) and the first spring (4) are installed on the rotating shaft of the moving wing. The locking rod (1) abuts against the first locking element (2), the first locking element (2) abuts against the locking cover (3), and the locking cover (3) is connected to the first spring (4). The deployment locking mechanism includes a normal locking mechanism and an axial locking mechanism. The normal locking mechanism is disposed between the fixed wing and the moving wing and is embedded in the fixed wing. The axial locking mechanism is disposed on the rotating shaft and the torsion bar.

2. The foldable wing structure with synchronous unlocking function according to claim 1, characterized in that, The folding locking mechanism is provided in two sets, and the two sets of folding locking mechanisms are symmetrically installed at both ends of the fixed wing and the moving wing. The locking rod (1) is an integral structure, and the two ends of the locking rod (1) respectively abut against the first locking element (2) in the two sets of folding locking mechanisms.

3. A foldable wing structure with synchronous unlocking function according to claim 1, characterized in that, The locking rod (1) has a locking rod groove, and the first locking element (2) slides in cooperation with the locking rod groove.

4. A foldable wing structure with synchronous unlocking function according to claim 1, characterized in that, The rotating shaft has a groove inside, the first spring (4) is installed in the groove, and the locking cover (3) slides in the groove. When the first locking element (2) is fully located in the groove of the locking rod, the surface of the locking cover (3) is flush with the surface of the rotating shaft under the push of the first spring (4).

5. A foldable wing structure with synchronous unlocking function according to claim 1, characterized in that, The normal locking mechanism includes a second spring (5), a second locking element (6), and a moving wing limiting hole (7), wherein the second spring (5) is sleeved on the outside of the second locking element (6); The axial locking mechanism includes a slide lock (8) and a slide key (9).

6. A foldable wing structure with synchronous unlocking function according to claim 4, characterized in that, The second spring (5) and the second locking element (6) are installed inside the fixed wing. The moving wing limiting hole (7) is opened on the moving wing. The two ends of the second spring (5) abut against the inside of the fixed wing and the second locking element (6) respectively. When the moving wing rotates to be on the same plane as the fixed wing, the second locking element (6) is aligned with the moving wing limiting hole (7), and the end of the second locking element (6) is movably inserted into the moving wing limiting hole (7).

7. A foldable wing structure with synchronous unlocking function according to claim 4, characterized in that, The sliding lock (8) is sleeved on the outside of the torsion bar. The sliding lock (8) is connected to the moving wing through the sliding key (9). The sliding lock (8) can rotate synchronously with the moving wing.

8. A foldable wing structure with synchronous unlocking function according to claim 6, characterized in that, The slide lock (8) is provided with a protrusion, and the rotating shaft is provided with a rotating shaft groove that cooperates with the protrusion. The axial locking mechanism also includes an axial spring, which is sleeved on the outside of the torsion bar, and the two ends of the axial spring abut against the moving wing and the slide lock (8) respectively. The slide lock (8) can slide along the torsion bar axial direction under the action of the axial spring so that the protrusion is inserted into the rotating shaft groove.

9. A foldable wing structure with synchronous unlocking function according to claim 1, characterized in that, The deployment locking mechanism also includes a limiting groove (10), which includes a fixed wing groove on the fixed wing and a moving wing groove on the moving wing. When the moving wing rotates to be on the same plane as the fixed wing, the fixed wing groove and the moving wing groove abut against each other.

10. A foldable wing structure with synchronous unlocking function according to claim 1, characterized in that, The fixed wing is provided with a fixed wing rotation shaft, a hexagonal limiting post is fixedly installed on the fixed wing rotation shaft, and a cylindrical limiting post is fixedly installed on the rotation shaft. The two ends of the torsion bar are fixedly connected to the hexagonal limiting post and the cylindrical limiting post, respectively. When the moving wing and the fixed wing are in a folded state, the torsion bar is in a torsional energy storage state.

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