Foldable tail vane of rotary wing aircraft
By designing a flipping and locking mechanism for a foldable tail rudder, the problem of the inability to fold the tail rudder of a rotary-wing aircraft was solved, enabling the tail wing to be stored and deployed, thus improving the space utilization and transportation convenience of the aircraft.
Patent Information
- Application Number
- CN202511784286.1
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- Filing Date
- 2025-12-01
- Publication Date
- 2026-02-03
AI Technical Summary
The tail rudders of existing rotary-wing aircraft are rigidly connected and cannot be folded, resulting in them occupying a large space when not in flight, increasing the difficulty of transportation and storage.
A foldable tail fin was designed. Through a combination of a flipping mechanism, a locking mechanism and a power source, the tail fin can be stored and deployed. An elastic element provides a restoring force, the power source drives the tail fin to rotate, and the locking mechanism ensures the stability of the tail fin in different states.
The tail fin functions during flight and can be folded up when not in flight, reducing space occupation and improving transportation and storage convenience.
Smart Images
Figure CN121448596A_ABST
Abstract
Description
TECHNICAL FIELD
[0001] The present application relates to the technical field of flight equipment, in particular to a foldable tail rudder of a rotary wing aircraft. BACKGROUND
[0002] In the field of aircraft design, as a key control component, the structure design of the tail rudder directly affects the flight stability and maneuverability of the aircraft. The tail rudder is usually designed in a fixed connection manner, and the tail surface is rigidly fixed with the fuselage to ensure the structural stability during flight. The existing tail rudder design has obvious space occupation problem. Since the tail surface is rigidly connected with the fuselage, it cannot be folded and stored, resulting in that the aircraft needs to occupy a large space in the non-flying state, increasing the transportation cost and storage difficulty. SUMMARY
[0003] In order to solve the above technical problems, the present application provides a foldable tail rudder of a rotary wing aircraft, comprising: A turnover mechanism is installed on the fuselage of the rotary wing aircraft, the turnover mechanism comprises an elastic member and a bearing plate, the bearing plate has a bearing surface, and the bearing plate has a tendency to turn from a retracted state to a deployed state based on the elastic restoring force of the elastic member; A first locking mechanism is arranged between the bearing plate and the fuselage, and the first locking mechanism is used to limit the bearing plate in the retracted state; A tail wing has a wing tip, a wing root and two side end faces, a connecting shaft is protrudingly arranged on the first end face, the connecting shaft penetrates through the bearing plate, and the first end face is attached to the bearing surface of the bearing plate; A power source is arranged on the fuselage, the power source has an output end, and when the bearing plate is in the deployed state, the output end can be locked with the connecting shaft to drive the tail wing to rotate by the power source; Wherein, when the bearing plate is in the retracted state, the bearing surface is perpendicular to the surface of the fuselage where the turnover mechanism is installed.
[0004] Preferably, the first locking mechanism comprises a baffle plate arranged in the fuselage in a telescopic manner, and a driving member arranged in the fuselage, the driving member is used to drive the baffle plate to extend out of or retract into the fuselage, so as to control whether the baffle plate blocks the turnover of the bearing plate.
[0005] Preferably, the baffle plate is provided with a rack at one end in the fuselage, and the driving member is a gear driving assembly arranged in the fuselage.
[0006] Preferably, it further comprises a second locking mechanism, and the second locking mechanism is used to limit the bearing plate in the deployed state.
[0007] Preferably, the second locking mechanism comprises a clamping plate arranged on the bearing plate and a clamping buckle arranged on the fuselage, and the clamping plate is in clamping engagement with the clamping buckle when the bearing plate is in the unfolded state.
[0008] Preferably, a hinge hole is arranged on the bearing plate, the bearing plate is rotatably arranged on the fuselage through the hinge hole, and the elastic member is a torsion spring arranged at the hinge hole.
[0009] Preferably, when the output end is in engagement with the connecting shaft, the output end is sleeved outside the connecting shaft, a slot hole is arranged on the inner wall of the output end, a protrusion is arranged on the connecting shaft and in engagement with the slot hole, the output end is arranged in the fuselage in a telescopic manner, and a compression spring is arranged on the side of the output end or the power source away from the connecting shaft.
[0010] The application provides a foldable tail fin of a rotary-wing aircraft. The tail fin is arranged on the fuselage of the aircraft through a turnover mechanism. The turnover mechanism comprises an elastic member and a bearing plate. The elastic member of the turnover mechanism is used to provide an elastic restoring force for the bearing plate to change from a folded state to an unfolded state. A first locking mechanism is arranged between the bearing plate and the fuselage, and is used to limit the bearing plate in the folded state. A power source is arranged on the fuselage, and has an output end. When the bearing plate is in the folded state, the body of the tail fin arranged on the bearing surface of the bearing plate is attached to the fuselage. When the bearing plate is in the unfolded state, the output end can be engaged with a connecting shaft on the tail fin and drive the tail fin to rotate, so that the pose of the tail fin on the fuselage can be adjusted, and the tail fin can play its role of improving flight stability and maneuverability. Therefore, the application can make the tail fin play its due role in the flight state, and the tail fin can be folded in the non-flight state, so that the space occupation is reduced and the storage is facilitated. BRIEF DESCRIPTION OF DRAWINGS
[0011] Figure 1 is a structure schematic diagram of a folded state of a foldable tail fin of a rotary-wing aircraft provided by the application; Figure 2 is a structure schematic diagram of an unfolded state of a foldable tail fin of a rotary-wing aircraft provided by the application; Figure 3 is a structure schematic diagram of a working state of a tail fin of a foldable tail fin of a rotary-wing aircraft provided by the application; In the drawings, 1 is a fuselage, 11 is a hinge part, 2 is a tail fin, 21 is a connecting shaft, 3 is a bearing plate, and 4 is an output end. DETAILED DESCRIPTION
[0012] In order to make the purposes, technical solutions and advantages of the embodiments of the present application clearer, the technical solutions in the embodiments of the present application will be described clearly and completely below with reference to the drawings in the embodiments of the present application. Obviously, the described embodiments are some but not all of the embodiments of the present application. Based on the embodiments in the present application, all other embodiments obtained by a person of ordinary skill in the art without creative work fall within the protection scope of the present application.
[0013] Figure 1 is a structural schematic diagram of a folding tail rudder of a rotary wing aircraft in a stowed state according to an embodiment of the present application; Figure 2 is a structural schematic diagram of a folding tail rudder of a rotary wing aircraft in a deployed state according to an embodiment of the present application; Figure 3 is a structural schematic diagram of a tail wing of a folding tail rudder of a rotary wing aircraft in a working state according to an embodiment of the present application.
[0014] As shown in Figures 1 to 3 , the present application provides a folding tail rudder of a rotary wing aircraft, which comprises a turnover mechanism mounted on a fuselage 1 of the rotary wing aircraft, the turnover mechanism comprising an elastic member and a bearing plate 3, the bearing plate 3 having a bearing surface, and the bearing plate 3 having a tendency to turn over from a stowed state to a deployed state based on an elastic restoring force of the elastic member (as shown in Figure 1 and Figure 2 the state of the bearing plate 3); The tail wing 2 has a wing tip, a wing root and two end surfaces, and a connecting shaft 21 is protrusively arranged on a first end surface, the connecting shaft 21 penetrating through the bearing plate 3 so that the first end surface is attached to the bearing surface of the bearing plate 3, and the tail wing 2 can turn over with the bearing plate 3, and a power source is further arranged on the fuselage 1, the power source having an output end 4, which can be locked and matched with the connecting shaft 21 when the bearing plate 3 is in the deployed state, so that the power source drives the tail wing 2 to rotate, and further forms a pose state as shown in Figure 2 from a pose as shown in Figure 3 .
[0015] When the folding tail rudder of the rotary wing aircraft according to the present application is in the stowed state as shown in Figure 1 , the tail wing 2 can be attached to the surface of the fuselage 1, so that the rotary wing aircraft is more convenient to store; when the rotary wing aircraft is flying, the tail wing 2 needs to be deployed to realize its guiding and stabilizing flow effect, at this time, the bearing plate 3 of the turnover mechanism turns over under the action of the elastic restoring force of the elastic member, so that the tail wing 2 and the bearing plate 3 are switched to the state as shown in Figure 2 , at this time, the connecting shaft 21 of the tail wing 2 is matched with the output end 4, the output end 4 can drive the tail wing 2 to rotate around the axis of the connecting shaft 21, and further adjust the pose of the tail wing 2, so that the tail wings 2 on both sides of the fuselage 1 can be deployed as shown in Figure 3The V-shaped structure can play a good guiding role when the aircraft is flying.
[0016] Further, the first locking mechanism is arranged between the bearing plate 3 and the fuselage 1, and is used to limit the bearing plate 3 in the storage state. By arranging the first locking mechanism, the bearing plate 3 can be stably in the storage state against the elastic force of the elastic member, and the tail wing 2 can be stably attached to the fuselage 1 in the storage state, thereby ensuring the storage effect.
[0017] The wing tip and the wing root of the tail wing 2 are streamlined guiding parts at the two ends of the tail wing when the aircraft is flying, and the side end surface of the tail wing 2 is the end surface of the streamlined surface of the tail wing 2. Figure 1 The right side end surface attached to the bearing plate 3 and the end surface on the other side.
[0018] In one preferred embodiment, the first telescopic mechanism includes a baffle telescopically arranged in the fuselage 1 and a driving member arranged in the fuselage 1. The driving member can be controlled by a signal to drive the baffle to extend or retract into the fuselage 1, thereby controlling whether the baffle can block the turning of the bearing plate 3. Figure 1 and Figure 2 In the illustrated embodiment, the baffle is arranged on the side of the bearing plate 3 close to the output end 4. When the baffle extends out of the fuselage, the freedom of turning of the bearing plate 3 can be limited, so that the bearing plate 3 can be limited in the storage state. When the tail wing needs to be unfolded, the driving member is controlled by a signal to retract the baffle and release the limitation on the bearing plate 3, so that the bearing plate 3 can turn under the elastic restoring force of the elastic member.
[0019] For example, the baffle and the driving member can adopt a rack and pinion driving assembly to enable the baffle to telescopically move on the fuselage 1, or other driving modes such as cylinder driving can be adopted to drive the baffle. It should be noted that the baffle only needs to block the turning of the bearing plate 3, and the specific structure of the baffle and the cooperation mode with the bearing plate 3 can be adjusted according to actual conditions, which will not be described here.
[0020] In one preferred embodiment, a second locking mechanism is further included, which is used to limit the bearing plate 3 in the unfolded state. In this way, the bearing plate 3 is unfolded under the action of the elastic member and is locked in the unfolded state by the second locking mechanism, so that the pose of the bearing plate 3 cannot be changed due to air flow disturbance and the like when the aircraft is flying, thereby ensuring the stability of the pose of the tail wing 2 and improving the use effect.
[0021] The second locking mechanism can adopt the cooperation of a buckle and a clamping plate. Specifically, a clamping plate is arranged on the bearing plate 3, and a buckle is arranged on the fuselage 1. When the bearing plate 3 is flipped, the clamping plate thereon can be clamped and cooperated with the buckle, so that the bearing plate 3 is fixed in the unfolded state. When it is needed to release the cooperation of the clamping plate and the buckle, generally at this time the airplane has completed the flight task and needs to be stored, therefore at this time the second locking mechanism can be manually released by the staff, and the bearing plate 3 is flipped and fixed in the stowed state under the action of the first locking mechanism. The buckle, the clamping plate, and the locking and unlocking modes of the two can also be controlled by a pneumatic cylinder or the like to make the buckle cooperate with or be separated from the clamping plate. The related technical solutions in the prior art can be referred to, and details are not described herein.
[0022] As shown in Figure 1 , a hinge hole is arranged on the bearing plate 3, and the hinge hole is hingedly connected with the hinge part 11 on the fuselage, so that the bearing plate 3 can rotate around the hinge part 11. The elastic member is a torsion spring arranged in the hinge part, so that the elastic member applies an elastic force to the bearing plate 3 to make it rotate around the shaft.
[0023] As shown in Figure 1 , in one preferred embodiment, when the output end 4 cooperates with the connecting shaft 21, the output end 4 is sleeved outside the connecting shaft 21, a slot hole is arranged on the inner wall of the output end 4, and a protrusion that cooperates with the slot hole is arranged on the connecting shaft 21, so that the connecting shaft 21 and the output end 4 can form a key groove cooperation, and thus the output end 4 can drive the connecting shaft 21 to rotate. Further, the power source can adopt a servo motor, and a compression spring is arranged on the side of the output end 4 or the servo motor away from the connecting shaft 21. When the bearing plate 3 is flipped, if the connecting shaft 21 interferes with the hole of the output end 4, the output end 4 is pressed into the fuselage 1. When the bearing plate 3 is flipped to the position, the connecting shaft 21 is perpendicular to the surface of the fuselage 1 and coaxial with the hole of the output end 4. Under the action of the compression spring, the output end 4 has a tendency to approach the connecting shaft 21. The servo motor drives the output end 4 to slowly rotate until the slot hole of the output end 4 cooperates with the protrusion of the connecting shaft 21. At this time, the output end 4 is popped out, and then the servo motor can drive the connecting shaft 21 and the tail wing 2 to rotate, so as to adjust the pose state of the tail wing 2. In addition, the servo motor can also be movably arranged in the fuselage 1, and the servo motor and the output end 4 are driven by the compression spring to make the output end 4 axially reciprocate, so that the connecting shaft 21 can cooperate with the output end 4 when the bearing plate 3 is flipped.
[0024] Preferably, when the output end matches the connecting shaft, the output end is sleeved outside the connecting shaft, a slot hole is arranged on the inner wall of the output end, a protrusion matched with the slot hole is arranged on the connecting shaft, the output end is arranged in the machine body in a telescopic mode, and a compression spring is arranged on the side of the output end or the power source away from the connecting shaft Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present application but not limit the present application. Although the present application is described in detail with reference to the embodiments, those skilled in the art should understand that the modification or equivalent replacement of the technical solutions of the present application does not deviate from the spirit and scope of the present application, and should be covered in the scope of claims of the present application.
Claims
1. A foldable tail rudder for a rotary-wing aircraft, characterized in that, include: A flipping mechanism is installed on the fuselage of a rotorcraft. The flipping mechanism includes an elastic element and a support plate. The support plate has a bearing surface. Based on the elastic restoring force of the elastic element, the support plate has a tendency to flip from a retracted state to an extended state. A first locking mechanism is disposed between the support plate and the body, and the first locking mechanism is used to restrict the support plate to the retracted state; The tail fin has a wingtip, a wing root and two end faces on both sides. A connecting shaft is provided on the first end face. The connecting shaft passes through the support plate, so that the first end face is in contact with the support surface of the support plate. A power source is mounted on the fuselage. The power source has an output end. When the support plate is in the unfolded state, the output end can be locked with the connecting shaft so that the power source drives the tail fin to rotate. When the support plate is in the retracted state, the support surface is perpendicular to the surface of the body on which the flipping mechanism is installed.
2. The foldable tail rudder of the rotorcraft according to claim 1, characterized in that, The first locking mechanism includes a baffle that can be telescopically disposed within the body, and a drive component located within the body. The drive component is used to drive the baffle to extend or retract into the body to control whether the baffle blocks the flipping of the support plate.
3. The foldable tail rudder of the rotorcraft according to claim 2, characterized in that, The baffle is provided with a rack at one end inside the body, and the driving component is a gear drive assembly provided inside the body.
4. The foldable tail rudder of the rotorcraft according to claim 1, characterized in that, It also includes a second locking mechanism for restricting the support plate in the unfolded state.
5. The foldable tail rudder of the rotorcraft according to claim 4, characterized in that, The second locking mechanism includes a locking plate disposed on the support plate and a buckle disposed on the machine body. When the support plate is in the unfolded state, the locking plate and the buckle engage.
6. The foldable tail rudder of the rotorcraft according to claim 1, characterized in that, The support plate has a hinge hole, and the support plate is rotatably mounted on the machine body through the hinge hole. The elastic element is a torsion spring installed at the hinge hole.
7. The foldable tail rudder of the rotorcraft according to claim 1, characterized in that, When the output end is engaged with the connecting shaft, the output end is sleeved outside the connecting shaft, a slot is provided on the inner wall of the output end, a protrusion is provided on the connecting shaft to engage with the slot, the output end is telescopically disposed within the machine body, and a compression spring is provided on the output end or the side of the power source away from the connecting shaft.