Lateral force plate device for improving lateral maneuvering characteristics of aircraft and aircraft

Abstract

The utility model provides a lateral force plate device for improving lateral maneuvering characteristics of an aircraft and the aircraft. In the side force plate device, a side force plate is connected to the outer side of the fuselage through a folding mechanism and can automatically rotate to an unfolding position from a folding position under the action of the folding mechanism; the limiting mechanism keeps the side force plate at the folding position; the side force plate is locked at the unfolding position by the positioning pin; in the folding mechanism, a support is fixed to the machine body, a rotating part sleeves the support and can rotate relative to the support, a torsional spring sleeves the rotating part, a side force plate sleeves the torsional spring and is connected with the rotating part, one end of the torsional spring is fixedly connected to the support, the other end of the torsional spring is fixedly connected to the side force plate, and a cover plate limits the side force plate to prevent the side force plate from being separated from the machine body. The aerodynamic force borne by the lateral maneuvering flight of the aircraft can be increased, and the lateral maneuvering flight performance is greatly improved; and the method can be used for complex flight conditions such as strong wind or strong airflow environment, and can more stably control the aircraft to quickly yaw, turn, avoid obstacles and other maneuvering flight.

Description

Technical Field

[0001] The utility model belongs to the technical field of lateral maneuver control of aircraft, and particularly relates to a side force plate device for improving the lateral maneuver performance of an aircraft and an aircraft including the side force plate device. Background Technique

[0002] An aircraft usually completes maneuvering flight in the horizontal plane by means of the lateral aerodynamic force provided by a vertical tail or a rudder; when the aircraft encounters situations such as quickly avoiding obstacles, counteracting strong winds, and performing emergency tasks, it needs to rely on a large lateral aerodynamic force to complete behaviors such as quick turning or yawing. There are the following two defects in relying solely on the vertical tail for maneuvering flight:

[0003] First, the effective area is insufficient: The vertical tail of an aircraft is usually small, and compared with the main and auxiliary wings of the aircraft, there is not enough area to generate a large aerodynamic force.

[0004] Second, the control efficiency is limited: The vertical tail of an aircraft is used as a control surface, and it is mainly used for yawing, that is, changing the heading of the aircraft. The change in its angle has little effect on the high-maneuver flight of the aircraft, and it is difficult to achieve complex lateral maneuvering flight. Content of the Utility Model

[0005] The purpose of the utility model is to solve the problems existing in the prior art that the aircraft completes flight in the horizontal plane through the vertical tail or the rudder, resulting in a small lateral aerodynamic force and difficulty in achieving complex lateral maneuvering flight, and provides a side force plate device for improving the lateral maneuver performance of the aircraft and an aircraft including the side force plate device.

[0006] To achieve the above purpose, the technical solution provided by the utility model is:

[0007] A side force plate device for improving the lateral maneuver performance of an aircraft, comprising a side force plate, a folding mechanism, a limiting mechanism, and a positioning pin;

[0008] The side force plate is connected to the outside of the aircraft fuselage through the folding mechanism and can automatically rotate from the folded position to the deployed position under the action of the folding mechanism. In the folded position, the side force plate is parallel to the length direction of the fuselage, and in the deployed position, the side force plate is parallel to the height direction of the fuselage;

[0009] The limiting mechanism is installed on the fuselage for holding the side force plate in the folded position and can automatically release the side force plate;

[0010] The positioning pin is fixedly connected to the fuselage and is used to automatically insert into the pin hole on the side force plate when the side force plate is in the deployed position, so as to lock the side force plate in the deployed position;

[0011] The folding mechanism includes a support, a rotating member, a torsion spring, and a cover plate. The support is fixed to the fuselage. The rotating member is coaxially sleeved on the support and can rotate relative to it. The torsion spring is sleeved on the rotating member. The side force plate is sleeved outside the torsion spring and connected to the rotating member. One end of the torsion spring is fixedly connected to the support, and the other end is fixedly connected to the side force plate, so that the side force plate can be automatically unfolded by the acting force of the torsion spring. The cover plate is used to limit the side force plate to prevent it from detaching from the fuselage, and is connected to the support outside the side force plate.

[0012] Furthermore, the limiting mechanism includes an explosive bolt and a limiting plate. The explosive bolt passes through the fuselage and is connected to the limiting plate, and the connection force of the bolt is released by its own explosion.

[0013] Furthermore, the support includes a base plate and a boss that are connected to each other. The base plate is connected to the inner side of the fuselage, and the boss passes through the fuselage and extends to the outside of the fuselage. The rotating member is sleeved on the boss, and the cover plate is sleeved at the end face of the boss.

[0014] Furthermore, a recess for accommodating the rotating member is provided on the base plate.

[0015] Furthermore, the rotating member includes a base portion, a rotating shaft and a connecting rod extending from the base portion. The rotating shaft is located in the middle of the base portion. The connecting rod extends parallel to the rotating shaft outside the rotating shaft. The rotating shaft is sleeved on the support, and the connecting rod is fixedly connected to the side force plate.

[0016] Furthermore, the folding mechanism further includes a gasket, which is arranged between the support and the rotating member to reduce friction.

[0017] Furthermore, the positioning pin is a spring pin.

[0018] An aircraft includes a fuselage, a vertical tail, and the above-mentioned side force plate device for improving the lateral maneuverability of the aircraft symmetrically arranged on both sides of the fuselage.

[0019] The advantages of the present utility model are as follows:

[0020] 1. For the side force plate device of the present utility model for improving the lateral maneuverability of the aircraft, the side force plate is connected to the aircraft fuselage through a folding mechanism, maintained in the folded position through a limiting mechanism, and when a large lateral aerodynamic force is required and complex lateral maneuvering flight is to be achieved, the side force plate can be automatically rotated and unfolded under the action of the folding mechanism, and can be locked in the unfolded position. Therefore, the present utility model can increase the aerodynamic force received by the lateral maneuvering flight of the aircraft, greatly improve the lateral maneuvering flight performance; and can be used in complex flight conditions, such as strong wind or strong airflow environment, and can more stably control the aircraft to perform maneuvering flights such as rapid yawing, turning and obstacle avoidance.

[0021] 2. After receiving the unfolding instruction, the side force plate of the side force plate device of the present utility model can be completely autonomously unfolded and locked through a spring pin, without additional power drive, and has the advantages of safety, reliability and low cost.

[0022] 3. Compared with existing aircraft, the aircraft of the present utility model is provided with a side force plate device including side force plates, which can increase the aerodynamic force received during the lateral maneuvering flight of the aircraft, greatly improving the lateral maneuvering flight performance of the aircraft; and enables the aircraft to be used in complex flight conditions and can more stably control maneuvers such as rapid yaw, turning, and obstacle avoidance of the aircraft. In addition, when the aircraft of the present utility model is in use, it is not necessary to change the structure of the existing aircraft, and only the side force plate device of the present utility model needs to be added to the fuselage of the aircraft, which is easy to implement, has a low improvement cost, and has strong applicability. Description of the Drawings

[0023] Through the following description with reference to the drawings, the above and / or other features and advantages of the present utility model will become more easily understood. The drawings are not drawn to scale, and some features are enlarged or reduced to show the details of specific components. In the drawings:

[0024] Figure 1 is an exploded view of the side force plate device for improving the lateral maneuvering performance of the aircraft of the present utility model, wherein the side force plates are in the deployed position;

[0025] Figure 2 is an assembled view of the side force plate device for improving the lateral maneuvering performance of the aircraft of the present utility model, wherein the side force plates are in the folded position;

[0026] Figure 3 is a three-dimensional view of the structure of the folding mechanism in the present utility model;

[0027] Figure 4 is a cross-sectional view of the installation structure of the folding mechanism and the side force plates in the present utility model;

[0028] Figure 5 is a structural diagram of the support in the present utility model;

[0029] Figure 6 is a structural diagram of the rotating member in the present utility model.

[0030] In the drawings: 1 - side force plate; 2 - folding mechanism, 21 - support, 211 - base plate, 2111 - recess, 2112 - torsion spring hole, 212 - boss, 213 - mounting hole, 214 - connecting hole, 22 - rotating member, 221 - base portion, 222 - rotating shaft, 223 - connecting rod, 23 - torsion spring, 24 - cover plate, 25 - gasket; 3 - limiting mechanism, 31 - explosive bolt, 32 - limiting plate; 4 - positioning pin, 100 - fuselage. Detailed Description of the Preferred Embodiment

[0031] The present invention will be described in detail below with reference to the accompanying drawings by means of exemplary embodiments of the present invention. It should be noted that the following detailed description of the present invention is for illustrative purposes only and does not limit the present invention.

[0032] The present invention provides a side force plate device for improving the lateral maneuverability of an aircraft and an aircraft including the side force plate device, which can greatly increase the effective lateral force receiving area of the aircraft, improve the lateral aerodynamic force of the aircraft, and is beneficial to improving the stability and agility of the aircraft when performing actions such as rapid turning, sideslipping, and tilting.

[0033] First, the side force plate device for improving the lateral maneuverability of an aircraft provided by the present invention will be described.

[0034] Refer to Figure 1 and Figure 2 As an exemplary embodiment of the present invention, the side force plate device for improving the lateral maneuverability of an aircraft includes a side force plate 1, a folding mechanism 2, a limiting mechanism 3, and a positioning pin 4. The side force plate 1 is connected to the fuselage 100 of the aircraft and is in the shape of a thin plate. The length of the plate is greater than the height of the fuselage and is used to assist the aircraft in performing maneuvering flights in the horizontal plane. It can greatly increase the effective lateral force receiving area of the aircraft, improve the lateral aerodynamic force of the aircraft, and is beneficial to improving the stability and agility of the aircraft when performing actions such as rapid turning, sideslipping, and tilting. The folding mechanism 2 is used to deploy the side force plate 1. The limiting mechanism 3 is used to keep the side force plate 1 in the folded position in the non-working state. In the folded position, the side force plate 1 is parallel to the length direction of the fuselage. The positioning pin 4 is used to keep the side force plate 1 in the deployed position in the working state. In the deployed position, the side force plate 1 is parallel to the height direction of the fuselage.

[0035] The side force plate 1 is connected to the outside of the fuselage 100 through the folding mechanism 2 and can automatically rotate from the folded position to the deployed position under the action of the folding mechanism 2. The rotation axis is perpendicular to the fuselage mounting surface of the side force plate on the fuselage.

[0036] As Figure 2As shown, the limiting mechanism 3 is installed on the fuselage 100, used to hold the side force plate 1 in the folded position, and can automatically release the side force plate 1 to allow the side force plate 1 to rotate and unfold. To facilitate the holding and release of the side force plate 1 in the folded position, in some embodiments, the limiting mechanism 3 includes an explosive bolt 31 and a limiting plate 32. The limiting plate 32 is connected to the outside of the fuselage, and the explosive bolt 31 passes through the fuselage 100 and is connected to the limiting plate 32, which can keep the side force plate 1 in the folded position. The explosive bolt 31 releases the connection force of the bolt through its own explosion. Specifically, one end of the limiting plate 32 is installed on the fuselage through the explosive bolt 31, and the other end cooperates with the side force plate 1. A hook-shaped portion can be provided to engage with the side force plate 1, thereby restricting the side force plate 1 in the folded position. When the explosive bolt 31 explodes, the limiting plate 32 is thrown out, thereby unlocking and releasing the side force plate 1.

[0037] As Figure 1 shown, the positioning pin 4 is fixedly connected to the fuselage 100, used to automatically insert into a pin hole (not shown in the figure) on the side force plate 1 when the side force plate 1 is in the unfolded position, thereby locking the side force plate 1 in the unfolded position. Preferably, the positioning pin 4 is a spring pin. In this way, the side force plate can be locked in the unfolded position without additional power drive.

[0038] Combined Figure 3 and Figure 4 , the folding mechanism 2 includes a support 21, a rotating member 22, a torsion spring 23, and a cover plate 24.

[0039] Figure 5 The support 21 is shown. The support 21 is fixed to the fuselage 100 and serves as the installation base of the folding mechanism 2. To make the side force plate device and the aircraft structure compact, the support 21 can particularly include a base plate 211 and a boss 212 connected to each other. The base plate 211 is connected to the inside of the fuselage 100 and can be connected by using bolts to pass through the mounting holes 213 at the protruding parts on the base plate 211. A recess 2111 for accommodating the rotating member 22 can be provided on the base plate 211. The boss 212 passes through the fuselage 100 and extends to the outside of the fuselage 100 to cooperate with the side force plate 1 and the rotating member 22, torsion spring 23, and cover plate 24 to be specifically described below. The side force plate 1 is provided with a protruding portion protruding towards the fuselage. A part of this protruding portion, a part of the rotating member 22, and a part of the torsion spring 23 can all be located inside the fuselage.

[0040] Figure 6The rotary member 22 is shown. The rotary member 22 is coaxially sleeved on the support 21, especially on the boss 212 of the support 21 and can rotate relative thereto. The rotary member 22 is connected to the side force plate 1 so that the two move together. In a specific embodiment, the rotary member 22 includes a base 221, a rotating shaft 222 and a connecting rod 223 extending from the base 221. The rotating shaft 222 is located in the middle of the base 221, and the connecting rod 223 extends parallel to the rotating shaft 222 outside the rotating shaft 222. The base 221 can be placed in the recess 2111 of the support 21, the rotating shaft 222 is sleeved on the support 21, and the connecting rod 223 is fixedly connected to the side force plate 1, specifically inserted into the side force plate 1, so that the rotary member 22 and the side force plate 1 move together, thereby enabling the folding and unfolding of the side force plate 1 to proceed smoothly.

[0041] The torsion spring 23 is sleeved on the rotary member 22, especially on the rotating shaft 222, and is located between the rotating shaft 222 and the connecting rod 223. The side force plate 1 is sleeved outside the torsion spring 23. One end of the torsion spring 23 is fixedly connected to the support 21, especially hooked on the support 21 through the torsion spring hole 2112, and the other end is fixedly connected to the side force plate 1 and can be clamped in the groove of the side force plate 1, so that the side force plate 1 can be automatically unfolded by the acting force of the torsion spring 23.

[0042] The cover plate 24 is used to limit the side force plate 1 to prevent it from detaching from the fuselage 100, and is connected to the support 21 outside the side force plate 1. The cover plate 24 can be sleeved at the end face of the boss 212 and fixed by bolts passing through the connection holes 214 on the end face of the boss 212.

[0043] Therefore, in the case where a small lateral aerodynamic force is required and the side force plate does not need to work, the side force plate 1 can be manually folded and held in the folded state under the action of the limiting mechanism 3. When a large lateral aerodynamic force is required and for example, in a strong wind or strong airflow environment, complex lateral maneuvering flights are needed and the side force plate needs to work to more stably control the maneuvering flights of the aircraft such as rapid yaw, turning and obstacle avoidance, the aircraft control system issues an unlocking instruction for the limiting mechanism. The limiting mechanism unlocks and releases the side force plate 1. At this time, the side force plate 1 will automatically rotate and quickly unfold under the action of the folding mechanism 2 without the need for additional electric drive. After unfolding in place, the positioning pin 4 is inserted into the side force plate 1 to autonomously lock the side force plate 1 in the unfolded position, which has the advantages of simple structure, easy implementation, safety and reliability, and low cost.

[0044] To reduce the friction between the support 21 and the rotary member 22, in the preferred embodiment of the present invention, the folding mechanism 2 further includes a gasket, and the gasket is arranged between the support 21 and the rotary member 22, especially placed in the recess 2111 of the support 21 and sleeved on the boss 212 of the support 21.

[0045] As described above, the side force plate device for improving the lateral maneuverability of the aircraft of the present utility model has the side force plates connected to the aircraft fuselage through a folding mechanism, maintained in the folded position by a limiting mechanism, and when a large lateral aerodynamic force is required and complex lateral maneuvering flight is to be achieved, the side force plates can automatically rotate and unfold under the action of the folding mechanism and can be locked in the unfolded position. Therefore, the present utility model can increase the aerodynamic force received by the aircraft during lateral maneuvering flight, greatly improve the lateral maneuvering flight performance; and can be used in complex flight conditions, such as strong wind or strong air current environment, and can more stably control the aircraft for maneuvering flights such as rapid yawing, turning, and obstacle avoidance.

[0046] Next, the aircraft provided by the present utility model will be described.

[0047] The aircraft as an exemplary embodiment of the present utility model includes a fuselage, a vertical tail, and the above-described side force plate devices for improving the lateral maneuverability of the aircraft symmetrically arranged on both sides of the fuselage. The side force plate devices can be installed on both sides of the front half of the aircraft fuselage. For the specific installation structure of the side force plate devices and the fuselage, reference can be made to the above description.

[0048] Compared with existing aircraft, the aircraft of the present utility model, due to the addition of the side force plate devices including side force plates, can increase the aerodynamic force received by the aircraft during lateral maneuvering flight, greatly improve the lateral maneuvering flight performance of the aircraft; and enables the aircraft to be used in complex flight conditions and can more stably control the aircraft for maneuvering flights such as rapid yawing, turning, and obstacle avoidance. In addition, when the aircraft of the present utility model is in use, it is not necessary to change the structure of the existing aircraft. It only needs to add the side force plate devices of the present utility model to the aircraft fuselage, which is easy to implement, has a low improvement cost, and has strong applicability.

[0049] Finally, it should be noted that the features mentioned and / or shown in the above description of the exemplary embodiments of the present utility model can be combined in the same or similar manner into one or more other embodiments, combined with the features in other embodiments or replace the corresponding features in other embodiments. The technical solutions obtained through such combination or replacement should also be regarded as being included within the protection scope of the present utility model.

Claims

1. A side force plate device for improving the lateral maneuverability of an aircraft, characterized in that: It includes a side force plate, a folding mechanism, a limiting mechanism and a positioning pin; The side force plate is connected to the outer side of the aircraft fuselage through the folding mechanism and can automatically rotate from the folded position to the unfolded position under the action of the folding mechanism. In the folded position, the side force plate is parallel to the longitudinal direction of the fuselage, and in the unfolded position, the side force plate is parallel to the height direction of the fuselage; The limiting mechanism is installed on the fuselage to hold the side force plate in the folded position and can automatically release the side force plate; The positioning pin is fixedly connected to the fuselage and is used to automatically insert into the pin hole on the side force plate when the side force plate is in the unfolded position, so as to lock the side force plate in the unfolded position; The folding mechanism includes a support, a rotary member, a torsion spring and a cover plate. The support is fixed to the fuselage. The rotary member is coaxially sleeved on the support and can rotate relative to it. The torsion spring is sleeved on the rotary member. The side force plate is sleeved outside the torsion spring and is connected to the rotary member. One end of the torsion spring is fixedly connected to the support, and the other end is fixedly connected to the side force plate, so that the side force plate can be automatically unfolded by the acting force of the torsion spring. The cover plate is used to limit the side force plate to prevent it from detaching from the fuselage and is connected to the support on the outer side of the side force plate.

2. The side force plate device for improving the lateral maneuverability of an aircraft according to claim 1, wherein: The limiting mechanism includes an explosive bolt and a limiting plate. The explosive bolt passes through the fuselage and is connected to the limiting plate, and releases the connection force of the bolt through its own explosion.

3. The side force plate device for improving the lateral maneuverability of an aircraft according to claim 1 or 2, characterized in that: The support includes a base plate and a boss connected to each other. The base plate is connected to the inner side of the fuselage, and the boss passes through the fuselage and extends to the outer side of the fuselage. The rotary member is sleeved on the boss, and the cover plate is sleeved at the end face of the boss.

4. The side force plate device for improving the lateral maneuverability of an aircraft according to claim 3, characterized in that: A recess for accommodating the rotary member is provided on the base plate.

5. The side force plate device for improving the lateral maneuverability of an aircraft according to claim 1 or 2, characterized in that: The rotary member includes a base portion, a rotating shaft and a connecting rod extending from the base portion. The rotating shaft is located in the middle of the base portion. The connecting rod extends parallel to the rotating shaft outside the rotating shaft. The rotating shaft is sleeved on the support, and the connecting rod is fixedly connected to the side force plate.

6. The side force plate device for improving the lateral maneuverability of an aircraft according to claim 1 or 2, characterized in that: The folding mechanism further includes a gasket, which is arranged between the support and the rotary member to reduce friction.

7. The side force plate device for improving the lateral maneuverability of an aircraft according to claim 1 or 2, characterized in that: The positioning pin is a spring pin.

8. An aircraft, characterized in that: It includes a fuselage, a vertical tail, and side force plate devices for improving the lateral maneuverability of the aircraft symmetrically arranged on both sides of the fuselage according to any one of claims 1 to 7.

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