Compact rapid unfolding and locking mechanism for air rudder

Abstract

The invention provides a compact quick unfolding and locking mechanism for an air rudder, which comprises a control surface, a rudder fork and an unfolding and locking mechanism, a control surface rotating shaft hole and a rudder fork rotating shaft hole are correspondingly formed in the control surface and the rudder fork, and the unfolding and locking mechanism comprises a torsion spring and a locking device; the two ends of the torsion spring are connected with the control surface and the rudder fork in a fastening mode respectively, and when the control surface is in a folded state, the torsion spring is provided with a pre-torsion angle for providing unfolding torque; the locking device comprises a compression spring and a locking block, a clamping groove is formed in the hole wall of the control surface rotating shaft hole, and when the control surface is in an unfolded state, the locking block is inserted into the control surface rotating shaft hole and abuts against the clamping groove of the control surface rotating shaft hole. The air rudder unfolding torque is provided through the torsion spring, and the positioning and locking effects of the rudder surface and the rudder fork after the air rudder is unfolded are achieved through the locking spring and the compression spring; and by adopting an unfolding and locking integrated structure, the space volume can be reduced, the structural mass can be reduced, and the problem of uneven stress can be effectively solved.

Description

Technical Field

[0001] The invention relates to the technical field of foldable air rudders, and in particular to a compact rapid unfolding and locking mechanism for an air rudder. Background Art

[0002] Air rudders are important components of missiles, rockets and other aircraft. Air rudders are installed on the outside of the aircraft and generate lateral control force by changing the air flow, thereby changing the aircraft's attitude. With the demand for miniaturization of airborne embedded and launch boxes, folding air rudders has become the main means to reduce the lateral size of missiles in storage and transportation and improve operational and tactical maneuverability; after the aircraft is launched, the air rudder can be quickly deployed and self-locked under the action of the deployment and locking mechanism, and has sufficient structural strength.

[0003] The existing Chinese patent with publication number CN113619774A discloses a foldable air rudder, including a mounting seat and a folding wing arranged on the mounting seat, the folding wing is rotatably mounted on the mounting seat through a rotating shaft, the rotating shaft is provided with a torsion spring assembly for providing an unfolding force for the folding wing, and the mounting seat is provided with a horizontal locking assembly and a vertical locking assembly. After the folding wing is unfolded by the torsion spring assembly, the horizontal locking assembly and the vertical locking assembly both lock the folding wing. When the horizontal locking assembly and the vertical locking assembly are both opened, the folding wing can be rotated and folded on the mounting seat.

[0004] In the prior art, the deployment and locking mechanism mainly includes two sets of devices to realize the deployment and locking functions respectively, but such mechanisms have problems such as large mass, large structural space, and uneven force, which affects the load-bearing capacity and lightweight effect of the air rudder and even the aircraft. Therefore, it is necessary to provide a compact and fast deployment and locking mechanism for the air rudder, which can reduce the space volume, reduce the structural mass, and effectively solve the problem of uneven force. Summary of the invention

[0005] In view of the defects in the prior art, an object of the present invention is to provide a compact rapid deployment and locking mechanism for an air rudder.

[0006] A compact rapid deployment and locking mechanism for an air rudder provided by the present invention comprises: a rudder surface, a rudder fork and a deployment and locking mechanism, wherein the rudder surface comprises a folded state and an deployed state, and a rudder surface rotating shaft hole and a rudder fork rotating shaft hole are correspondingly arranged inside the rudder surface and the rudder fork, and the deployment and locking mechanism comprises a torsion spring and a locking device;

[0007] The torsion spring is installed inside the rudder surface rotation shaft hole and the rudder fork rotation shaft hole, and the two ends of the torsion spring are respectively fastened to the rudder surface and the rudder fork. When the rudder surface is in a folded state, the torsion spring is provided with a pre-twisted angle for providing a deployment torque;

[0008] The locking device is installed inside the rudder fork shaft hole, and the locking device includes a compression spring and a locking block. The two ends of the compression spring are respectively tightly connected to the rudder fork and the locking block. A slot is formed on the hole wall of the rudder surface shaft hole. When the rudder surface is in the unfolded state, the locking block is inserted into the rudder surface shaft hole and tightly pressed against the slot of the rudder surface shaft hole.

[0009] Preferably, a front torsion head and a rear torsion head are respectively provided at both ends of the torsion spring, the front torsion head is tightly connected to the rudder fork, the rear torsion head is tightly connected to the rudder surface, the torsion spring is drivingly connected to the rudder surface via the rear torsion head, and the rudder surface can rotate around the central axis of the torsion spring.

[0010] Preferably, the torsion spring is provided with a pre-twist angle of not less than 2°.

[0011] Preferably, the torsion spring comprises a cross-shaped, tower-shaped, or circular cross-section.

[0012] Preferably, the rudder fork is arranged in the middle of the bottom edge of the rudder surface, the rudder surface rotation axis holes are arranged on both sides of the rudder fork, two rudder fork rotation axis holes are correspondingly arranged inside the rudder fork, and a group of locking devices are respectively arranged in the two rudder fork rotation axis holes.

[0013] Preferably, two rudder fork shaft holes are symmetrically arranged inside the rudder fork, two groups of locking devices are symmetrically arranged in the two rudder fork shaft holes, the torsion spring extends into one of the rudder fork shaft holes, and the front twist head is fastened to the middle part of the rudder fork.

[0014] Preferably, the rudder fork rotation axis hole and the rudder surface rotation axis hole are coaxial and have the same diameter.

[0015] Preferably, two ends of the compression spring are respectively connected to the bottom of the rudder fork shaft hole and the locking block, and the compression spring is always in a compressed state.

[0016] Preferably, the locking block is cylindrical, a key is provided on the outer wall of the cylinder, the diameter of the rudder surface shaft hole matches the outer diameter of the cylinder, the size of the slot on the hole wall of the rudder surface shaft hole matches the key, when the rudder surface is in a folded state, the key does not contact the slot, and when the rudder surface is in an unfolded state, the key is inserted into the slot.

[0017] Preferably, a guide groove matching the key is provided on the rudder fork shaft hole, the key is slidably matched with the guide groove, and the key does not completely leave the guide groove.

[0018] Compared with the prior art, the present invention has the following beneficial effects:

[0019] 1. The present invention adopts a front twist head, a rear twist head and a torsion spring to jointly provide an air rudder deployment torque. The locking block moves outward along the rudder surface shaft hole under the thrust of the compression spring. The locking and the compression spring jointly achieve the positioning and locking effect of the rudder surface and the rudder fork after the air rudder is deployed. The deployment-locking integrated form of the deployment locking mechanism helps to reduce the space volume, helps to reduce the structural quality, and can effectively solve the problem of uneven force.

[0020] 2. The present invention adopts a variety of high-strength materials to make the deployment and locking mechanism have a higher specific stiffness, and has a better structural lightweight effect under the same pneumatic load conditions.

[0021] 3. The present invention adopts two sets of identical locking devices symmetrically placed on both sides of the rudder fork to jointly bear the aerodynamic force, which has a more uniform force effect under aerodynamic load conditions. BRIEF DESCRIPTION OF THE DRAWINGS

[0022] Other features, objects and advantages of the present invention will become more apparent from the detailed description of non-limiting embodiments made with reference to the following drawings:

[0023] Figure 1 The present invention mainly embodies the structural schematic diagram of a compact rapid deployment and locking mechanism for an air rudder in a deployed state;

[0024] Figure 2 The present invention mainly embodies the structural schematic diagram of a compact rapid deployment and locking mechanism for an air rudder in a folded state;

[0025] Figure 3 This is a schematic diagram of the structure of the locking block mainly embodied in the present invention.

[0026] As shown in the figure:

[0027] Rudder 1 Rudder shaft hole 11 Rudder fork 2

[0028] Rudder fork shaft hole 21 front twist head 31 compression spring 32

[0029] Locking block 33 Torsion spring 34 Screw 35

[0030] Back turn 36 DETAILED DESCRIPTION

[0031] The present invention is described in detail below in conjunction with specific embodiments. The following embodiments will help those skilled in the art to further understand the present invention, but are not intended to limit the present invention in any form. It should be noted that, for those of ordinary skill in the art, several changes and improvements can also be made without departing from the concept of the present invention. These all belong to the protection scope of the present invention.

[0032] like Figure 1 and 2 As shown, a compact rapid deployment and locking mechanism for an air rudder provided by the present invention comprises: a rudder surface 1, a rudder fork 2 and a deployment and locking mechanism, wherein the rudder surface 1 comprises a folded state and an deployed state, and the rudder surface 1 and the rudder fork 2 are provided with a rudder surface rotation axis hole 11 and a rudder fork rotation axis hole 21 respectively, and the deployment and locking mechanism comprises a torsion spring 34 and a locking device; the torsion spring 34 is installed in the rudder surface rotation axis hole 11 and the rudder fork rotation axis hole 21, and the two ends of the torsion spring 34 are respectively connected to the rudder surface 1 and the rudder fork 2 Tightly connected, when the rudder surface 1 is in a folded state, the torsion spring 34 is provided with a pre-twisted angle for providing an unfolding torque; the locking device is installed inside the rudder fork shaft hole 21, the locking device comprises a compression spring 32 and a locking block 33, the two ends of the compression spring 32 are respectively tightly connected with the rudder fork 2 and the locking block 33, a groove is formed on the hole wall of the rudder surface shaft hole 11, when the rudder surface 1 is in an unfolded state, the locking block 33 is inserted into the rudder surface shaft hole 11 and is tightly pressed against the groove of the rudder surface shaft hole 11.

[0033] The present application is installed in the rudder surface shaft hole 11 and the rudder fork shaft hole 21 through the deployment locking mechanism, which is used to connect the rudder fork 2 and the rudder surface 1 and realize the deployment-locking action of the rudder surface 1. The present application adopts the deployment-locking integrated form of the deployment locking mechanism, which effectively reduces the structural mass and space occupation, and solves the problem of uneven force.

[0034] The two ends of the torsion spring 34 are respectively provided with a front twist head 31 and a rear twist head 36, and the two ends of the torsion spring 34 are respectively fixedly connected to the front twist head 31 and the rear twist head 36 through cylindrical pins. The front twist head 31 is fastened to the rudder fork 2 through a screw 35, and the rear twist head 36 is fastened to the rudder surface 1 through a screw 35. The front twist head 31, the rear twist head 36 and the torsion spring 34 jointly provide the air rudder deployment torque. The torsion spring 34 is drivingly connected to the rudder surface 1 through the rear twist head 36, and the rudder surface 1 can rotate around the central axis of the torsion spring 34.

[0035] In order to improve the stability of the control surface 1 after deployment, the torsion spring 34 is provided with a pre-twist angle of not less than 2°. Preferably, the pre-twist angle is between 2° and 30°.

[0036] The torsion spring 34 adopts a cross-shaped, tower-shaped or circular cross-section design to fully utilize the space and increase the deployment torque.

[0037] The rudder fork 2 is arranged at the middle of the bottom edge of the rudder surface 1. Rudder surface rotation shaft holes 11 are arranged on both sides of the rudder fork 2. Two rudder fork rotation shaft holes 21 are correspondingly arranged inside the rudder fork 2. A group of locking devices are respectively arranged in the two rudder fork rotation shaft holes 21.

[0038] Two rudder fork shaft holes 21 are symmetrically arranged inside the rudder fork 2, and two sets of locking devices are symmetrically arranged in the two rudder fork shaft holes 21. The torsion spring 34 extends into one rudder fork shaft hole 21, and a through hole is opened at the center of the locking block 33. The torsion spring 34 passes through the compression spring 32 and the locking block 33 and extends to the bottom of the rudder fork shaft hole 21. The front twist head 31 is tightly connected to the middle of the rudder fork 2.

[0039] The rudder fork rotation axis hole 21 and the rudder surface rotation axis hole 11 are coaxial and have the same diameter.

[0040] The two ends of the compression spring 32 are connected to the bottom of the rudder fork shaft hole 21 and the locking block 33 respectively, and the compression spring 32 is always in a compressed state. The locking block 33 is located in the rudder fork shaft hole 21, and moves outward along the rudder surface shaft hole 11 under the thrust of the compression spring 32. The locking block 33 and the compression spring 32 jointly achieve the positioning and locking effect of the rudder surface 1 and the rudder fork 2 after the air rudder is deployed.

[0041] like Figure 3 As shown, the locking block 33 is a cylinder, and a key is provided on the outer wall of the cylinder. The diameter of the rudder shaft hole 11 matches the outer diameter of the cylinder, and the size of the slot on the hole wall of the rudder shaft hole 11 matches the key. When the rudder 1 is in a folded state, the key does not contact the slot, and when the rudder 1 is in an unfolded state, the key is inserted into the slot. A guide groove matching the key is provided on the rudder fork shaft hole 21, and the key and the guide groove are slidably matched, and the key does not completely leave the guide groove. The key provided on the locking block 33 can improve the ability of the air rudder to withstand aerodynamic loads when unfolded.

[0042] The torsion spring 34 is made of ultra-high strength elastic alloy, and is provided with an anti-corrosion coating after surface treatment. The front twist head 34 and the rear twist head 36 are made of heat-resistant steel or titanium alloy. The locking block 33 is made of heat-resistant steel or high-temperature titanium alloy. The compression spring 32 is made of ultra-high strength elastic alloy.

[0043] The assembly process of the present application is as follows: two sets of compression springs 32 and locking blocks 33 are sequentially installed into the rudder fork shaft hole 21 of the rudder fork 2, and the two locking blocks 33 are pressed into the interior of the rudder fork 2 along the shaft by a tooling, and the compression spring 32 enters a compressed state. After the rudder fork 2 and the rudder surface 1 are positioned, the tooling is released, and the compression spring 32 releases a part of the thrust to extend one end of the locking block 33 into the rudder surface shaft hole 11 of the rudder surface 1, so as to achieve the connection between the rudder fork 2 and the rudder surface 1; then the front twist head 31, the rear twist head 36, and the torsion spring 34 are assembled into one by a cylindrical pin, extending from the rudder surface shaft hole 11 of the rudder surface 1 to the center of the rudder fork 2, and the rudder fork 2 and the front twist head 31 are fixed by screws 35, and then the tooling is used to apply a 2-degree pre-twist angle to the rear twist head 36, and it is fixedly connected to the rudder surface 1 by screws 35. The torsion spring 34 adopts a cross-shaped, tower-shaped or circular cross-section design to make full use of space and increase the deployment torque.

[0044] For ultra-long-range aircraft, the air rudder needs to withstand a large thermal load, and the unfolding and locking mechanism needs to be made of heat-resistant materials, so the front twist head 31, the rear twist head 36 and the locking block 33 can be made of heat-resistant steel or high-temperature titanium alloy. For the torsion spring 34 and the compression spring 32, in order to provide a larger torque or spring effect, an ultra-high-strength elastic alloy with higher material properties can be used.

[0045] When the air rudder is in a folded state under the influence of external constraints, the rudder surface 1 and the rudder fork 2 form a certain angle, the front twist head 31 fixedly connected to the rudder fork 2 remains stationary, and the rear twist head 36 fixedly connected to the rudder surface 1 rotates together with the rudder surface 1, and the torsion spring 34 is elastically deformed by the front twist head 31 and the rear twist head 36 to provide torque for subsequent deployment. The two sets of compression springs 32 inside the rudder fork 2 push the locking block 33 respectively, and the cylindrical section of the locking block 33 enters the rudder surface shaft hole 11 on the rudder surface 1 structure, and the key on the locking block 33 cannot enter the rudder surface 1.

[0046] When the air rudder enters the deployment state, the torsion spring 34 recovers its deformation to provide the deployment torque, and the rudder surface 1 rotates to be parallel to the rudder fork 2 under the torque drive, and the groove on the rudder surface 1 turns to the corresponding position of the key on the locking block 33, and then the key of the locking block 33 enters the groove on the rudder surface 1 under the push of the compression spring 32, and the rudder surface 1 is deployed. When the air rudder is subjected to aerodynamic loads, the locking block 33 realizes the stable connection between the rudder surface 1 and the rudder fork 2 through its own shear resistance.

[0047] The present application adopts the front twist head 31, the rear twist head 36 and the torsion spring 34 to jointly provide the air rudder deployment torque. The locking block 33 moves outward along the rudder surface shaft hole 11 under the thrust of the compression spring 32. The locking block 33 and the compression spring 32 jointly achieve the positioning and locking effect of the rudder surface 1 and the rudder fork 2 after the air rudder is deployed.

[0048] The present application adopts an integrated deployment-locking deployment and locking mechanism, which occupies 15% less structural space than the existing air rudder deployment and locking mechanism of the same size and torque.

[0049] The present application adopts a variety of high-strength materials to make the deployment and locking mechanism have a higher specific stiffness, and under the same pneumatic load conditions, it has a better structural lightweight effect.

[0050] The present application adopts two sets of identical locking devices symmetrically placed on both sides of the rudder fork 2 to jointly bear the aerodynamic force, which has a more uniform force effect under aerodynamic load conditions.

[0051] In the description of the present application, it should be understood that the terms "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside", etc., indicating orientations or positional relationships, are based on the orientations or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the present application and simplifying the description, and do not indicate or imply that the referred device or element must have a specific orientation, be constructed and operated in a specific orientation, and therefore should not be understood as a limitation on the present application.

[0052] The above describes the specific embodiments of the present invention. It should be understood that the present invention is not limited to the above specific embodiments, and those skilled in the art can make various changes or modifications within the scope of the claims, which does not affect the essence of the present invention. In the absence of conflict, the embodiments of the present application and the features in the embodiments can be combined with each other arbitrarily.

Claims

1. A compact rapid deployment and locking mechanism for an air rudder, characterized in that: include: A rudder surface (1), a rudder fork (2), and an unfolding and locking mechanism, wherein the rudder surface (1) includes a folded state and an unfolded state, a rudder surface rotating shaft hole (11) and a rudder fork rotating shaft hole (21) are correspondingly arranged inside the rudder surface (1) and the rudder fork (2), and the unfolding and locking mechanism includes a torsion spring (34) and a locking device; The torsion spring (34) is installed inside the rudder surface rotation shaft hole (11) and the rudder fork rotation shaft hole (21), and the two ends of the torsion spring (34) are respectively firmly connected to the rudder surface (1) and the rudder fork (2); when the rudder surface (1) is in a folded state, the torsion spring (34) is provided with a pre-twisted angle for providing a deployment torque; The locking device is installed inside the rudder fork shaft hole (21), and comprises a compression spring (32) and a locking block (33). The two ends of the compression spring (32) are respectively tightly connected to the rudder fork (2) and the locking block (33). A slot is formed on the hole wall of the rudder surface shaft hole (11). When the rudder surface (1) is in an unfolded state, the locking block (33) is inserted into the rudder surface shaft hole (11) and tightly abuts against the slot of the rudder surface shaft hole (11).

2. The compact rapid deployment and locking mechanism for an air rudder according to claim 1, characterized in that: A front twisting head (31) and a rear twisting head (36) are respectively provided at both ends of the torsion spring (34); the front twisting head (31) is tightly connected to the rudder fork (2); the rear twisting head (36) is tightly connected to the rudder surface (1); the torsion spring (34) is drivingly connected to the rudder surface (1) via the rear twisting head (36); and the rudder surface (1) can rotate around the central axis of the torsion spring (34).

3. The compact rapid deployment and locking mechanism for an air rudder according to claim 1, characterized in that: The torsion spring (34) is provided with a pre-twist angle of not less than 2°.

4. The compact rapid deployment and locking mechanism for an air rudder according to claim 1, characterized in that: The torsion spring (34) includes a cross-shaped, tower-shaped, or circular cross section.

5. The compact rapid deployment and locking mechanism for an air rudder according to claim 2, characterized in that: The rudder fork (2) is arranged at the middle of the bottom edge of the rudder surface (1), and the rudder surface rotation axis holes (11) are arranged on both sides of the rudder fork (2). Two rudder fork rotation axis holes (21) are correspondingly arranged inside the rudder fork (2), and a group of the locking devices are respectively arranged in the two rudder fork rotation axis holes (21).

6. The compact rapid deployment and locking mechanism for an air rudder according to claim 5, characterized in that: Two rudder fork rotating shaft holes (21) are symmetrically arranged inside the rudder fork (2), two groups of locking devices are symmetrically arranged in the two rudder fork rotating shaft holes (21), the torsion spring (34) extends into one of the rudder fork rotating shaft holes (21), and the front twisting head (31) is tightly connected to the middle part of the rudder fork (2).

7. The compact rapid deployment and locking mechanism for an air rudder according to claim 1, characterized in that: The rudder fork rotating shaft hole (21) and the rudder surface rotating shaft hole (11) are coaxial and have the same diameter.

8. The compact rapid deployment and locking mechanism for an air rudder according to claim 5, characterized in that: The two ends of the compression spring (32) are respectively connected to the bottom of the rudder fork rotating shaft hole (21) and the locking block (33), and the compression spring (32) is always in a compressed state.

9. The compact rapid deployment and locking mechanism for an air rudder according to claim 1, characterized in that: The locking block (33) is in the form of a cylinder, a key is arranged on the outer wall of the cylinder, the diameter of the rudder surface shaft hole (11) matches the outer diameter of the cylinder, the size of the slot on the hole wall of the rudder surface shaft hole (11) matches the key, when the rudder surface (1) is in a folded state, the key does not contact the slot, and when the rudder surface (1) is in an unfolded state, the key is inserted into the slot.

10. The compact rapid deployment and locking mechanism for an air rudder according to claim 1, characterized in that: The rudder fork rotating shaft hole (21) is provided with a guide groove matching the key, the key is slidably matched with the guide groove, and the key does not completely leave the guide groove.

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