Aircraft and double-shaft rotary control surface thereof

Abstract

The invention relates to the technical field of aircraft control, and discloses an aircraft and a double-shaft rotary type control surface thereof, and the double-shaft rotary type control surface comprises a circular rotating disc which is rotatably installed on the surface of the aircraft through a rotating disc rotating shaft; the control surface is rotatably mounted on the circular turntable through a control surface rotating shaft, the control surface rotating shaft is perpendicular to the turntable rotating shaft, and when the control surface is folded, the control surface is flush with the surface of the aircraft; the rotary table power mechanism is connected with the rotary table rotating shaft and used for driving the circular rotary table to rotate by 360 degrees in the surface of the aircraft around the rotary table rotating shaft; the control surface power mechanism is connected with the control surface rotating shaft and used for driving the control surface to rotate around the control surface rotating shaft; and the turntable power mechanism and the control surface power mechanism are both in signal connection with the control device. Therefore, when the rotating shaft of the control surface and the incoming flow direction form an included angle, the control surface has the control capability in three directions of pitching, yawing and rolling at the same time, the compound control capability is strong, and the stability and the control performance of the aircraft can be improved.

Description

Technical Field

[0001] The present invention relates to the field of aircraft control technology, and more specifically, to a dual-axis rotary control surface. In addition, the present invention also provides an aircraft comprising the dual-axis rotary control surface. Background Art

[0002] Conventional aircraft use elevators for longitudinal control, rudders for heading control, and ailerons for lateral control. Both the wings and tail are equipped with control surfaces to maintain the stability of the aircraft.

[0003] With the development of aircraft technology, in order to achieve the goals of stealth, drag reduction, and weight reduction, it is necessary to reduce or even eliminate the tail. Eliminating the tail will lead to reduced stability and maneuverability of the aircraft. In order to compensate for the stability and maneuverability of the tailless layout, the aircraft can use innovative control surfaces such as full-moving wingtips, differential leading edge flaps, slotted spoilers, retractable rudders, and lower surface spoilers. The above-mentioned innovative control surfaces can be flush with the wing surface in the retracted state. When in use, the rudder surface deflects around a fixed axis to perform longitudinal, heading or lateral control. Due to the fixed axis, the above-mentioned innovative control surfaces can usually only perform manipulation in one direction, and multiple rudder combinations need to be programmed to complete longitudinal and lateral control.

[0004] In summary, how to achieve longitudinal and lateral control by using a control rudder surface is a problem that needs to be solved urgently by those skilled in the art. Summary of the invention

[0005] In view of this, an object of the present invention is to provide a dual-axis rotating control rudder surface. When the rudder surface rotation axis is set at an angle to the incoming flow direction, the control rudder surface has the control capability in three directions of pitch, yaw and roll at the same time, and has strong composite control capability, which is beneficial to improving the stability and maneuverability of the aircraft.

[0006] In addition, the present invention also provides an aircraft including the above-mentioned dual-axis rotating control surface.

[0007] In order to achieve the above object, the present invention provides the following technical solutions:

[0008] A dual-axis rotating control rudder surface, comprising:

[0009] A circular turntable is rotatably mounted on the surface of the aircraft via a turntable shaft;

[0010] A rudder surface, which is rotatably mounted on the circular turntable via a rudder surface rotation shaft, wherein the rudder surface rotation shaft is perpendicular to the turntable rotation shaft, and when the rudder surface is retracted, the rudder surface is flush with the surface of the aircraft;

[0011] A turntable power mechanism connected to the turntable shaft, used to drive the circular turntable to rotate 360° around the turntable shaft within the surface of the aircraft;

[0012] A rudder surface power mechanism connected to the rudder surface rotation shaft, used for driving the rudder surface to rotate around the rudder surface rotation shaft;

[0013] A control device, the turntable power mechanism and the rudder surface power mechanism are both connected to the control device by signal.

[0014] Preferably, the rudder surface rotation shaft is arranged along the diameter direction of the circular turntable, and the length of the rudder surface rotation shaft is equal to the diameter of the circular turntable.

[0015] Preferably, the rudder surface comprises a semicircular rudder surface, the center of the semicircular rudder surface coincides with the center of the circular turntable, and the diameter of the semicircular rudder surface is the same as the diameter of the circular turntable.

[0016] Preferably, the turntable power mechanism includes a turntable rotating motor, which is arranged in the fuselage or wing of the aircraft, and the output shaft of the turntable rotating motor is outer-circuited with a first driving gear, and the end of the circular turntable relatively away from the rudder surface is provided with a first passive gear, and the first passive gear is meshed with the first driving gear.

[0017] Preferably, the rudder surface power mechanism comprises a rudder surface rotating motor, an output shaft outer sleeve of the rudder surface rotating motor is provided with a second driving gear, an outer sleeve of the rudder surface rotating shaft is provided with a second passive gear, and the second passive gear is meshed with the second driving gear.

[0018] Preferably, it also includes an azimuth detection sensor for detecting the azimuth angle of the circular turntable, and the azimuth detection sensor is connected to the control device by signal.

[0019] Preferably, the orientation detection sensor comprises a detection magnetic strip and a magnetic sensor, the detection magnetic strip is arranged in a turntable mounting hole of the aircraft, and the magnetic sensor is arranged on the outer edge of the circular turntable.

[0020] Preferably, it also includes a pitch detection sensor for detecting the pitch angle of the rudder surface, and the pitch detection sensor is connected to the control device signal.

[0021] Preferably, the pitch detection sensor comprises a potentiometer, and the potentiometer is arranged on the rudder surface rotating shaft.

[0022] An aircraft comprises the dual-axis rotating control surface as described in any one of the above items.

[0023] The dual-axis rotating control rudder provided by the present invention can perform the functions of elevator, rudder or aileron by adjusting the azimuth angle of the circular turntable and the pitch angle of the control rudder. When the rotation axis of the control rudder is set at an angle with the incoming flow direction, the control rudder has the control capabilities of pitch, yaw and roll at the same time, and has a strong composite control capability, which is beneficial to improving the stability and control performance of the aircraft, and can replace a plurality of control rudders with separate control capabilities, thereby reducing the overall mass of the aircraft.

[0024] At the same time, when the rudders are retracted, they are flush with the surface of the aircraft, maintaining the low resistance and high stealth characteristics of the aircraft.

[0025] In addition, the present invention also provides an aircraft including the above-mentioned dual-axis rotating control surfaces, whose control surfaces have the ability to control pitch, yaw and roll in three directions at the same time, which is beneficial to reducing the number of control surfaces and optimizing the layout of the control surfaces, which not only reduces the overall mass of the aircraft, but also ensures the reliability and controllability of the aircraft. BRIEF DESCRIPTION OF THE DRAWINGS

[0026] In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings required for use in the embodiments or the description of the prior art will be briefly introduced below. Obviously, the drawings described below are only embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on the provided drawings without paying creative work.

[0027] Figure 1 This is a structural schematic diagram of a specific embodiment 1 of the dual-axis rotary control rudder provided by the present invention in an open state;

[0028] Figure 2 for Figure 1 A schematic diagram of the structure of the dual-axis rotary control rudder surface in a closed state;

[0029] Figure 3 It is a structural schematic diagram of a specific embodiment 2 of a dual-axis rotary control rudder surface;

[0030] Figure 4 It is a structural schematic diagram of specific embodiment 3 of the dual-axis rotary control rudder surface.

[0031] Figure 1-Figure 4 middle:

[0032] 01-aircraft; 1-circular turntable; 2-turntable shaft; 3-rudder surface; 4-rudder surface shaft. DETAILED DESCRIPTION

[0033] The following will be combined with the drawings in the embodiments of the present invention to clearly and completely describe the technical solutions in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0034] The core of the present invention is to provide a dual-axis rotating control rudder surface. When the rudder surface rotation axis is set at an angle to the incoming flow direction, the control rudder surface has the control capability of pitch, yaw and roll at the same time, and has strong composite control capability, which is beneficial to improving the stability and control performance of the aircraft.

[0035] In addition, the present invention also provides an aircraft including the above-mentioned dual-axis rotating control surface.

[0036] The dual-axis rotating control rudder surface provided by the present invention comprises:

[0037] A circular turntable 1 is rotatably mounted on the surface of the aircraft 01 via a turntable shaft 2;

[0038] The rudder surface 3 is rotatably mounted on the circular turntable 1 through the rudder surface rotation shaft 4. The rudder surface rotation shaft 4 is perpendicular to the turntable rotation shaft 2. When the rudder surface 3 is retracted, the rudder surface 3 is flush with the surface of the aircraft 01;

[0039] The turntable power mechanism connected to the turntable shaft 2 is used to drive the circular turntable 1 to rotate 360° around the turntable shaft 2 within the surface of the aircraft 01;

[0040] A rudder surface power mechanism connected to the rudder surface rotating shaft 4 is used to drive the rudder surface 3 to rotate around the rudder surface rotating shaft 4;

[0041] The control device, the turntable power mechanism and the rudder surface power mechanism are all connected with the control device signal.

[0042] Please refer to Figure 1 The circular turntable 1 is rotatably mounted on the surface of the aircraft 01 through the turntable shaft 2, and the turntable shaft 2 is arranged perpendicular to the surface of the aircraft 01; it can be understood that in order to ensure the aerodynamic performance of the control surface 3, the circular turntable 1 is arranged at a flat position on the surface of the aircraft 01, usually the fuselage or wing of the aircraft 01, and there are no other conventional control surfaces or airborne equipment around the circular turntable 1 to avoid mutual interference.

[0043] The turntable shaft 2 is connected to a turntable power mechanism, which is disposed in the aircraft 01 and is used to drive the circular turntable 1 to rotate 360° around the turntable shaft 2 within the surface of the aircraft 01 .

[0044] The turntable power mechanism includes a power source and a turntable transmission mechanism. The power source is preferably set to a turntable rotating motor, and the transmission mechanism can be set to a common transmission structure such as a gear transmission mechanism and a synchronous belt drive. Considering the requirements for the adjustment accuracy of the azimuth angle of the circular turntable 1 in actual operation, a gear transmission mechanism and other meshing transmission methods are usually used to transmit torque.

[0045] The rudder surface 3 is rotatably mounted on the circular turntable 1 via a rudder surface rotation shaft 4 . The rudder surface rotation shaft 4 is arranged parallel to the plane where the circular turntable 1 is located. Therefore, the rotation of the rudder surface 3 around the rudder surface rotation shaft 4 can be regarded as the pitch adjustment of the rudder surface 3 .

[0046] Since the control surface 3 is installed on the outer surface of the circular turntable 1, the shape of the control surface 3 is a part of the circular turntable 3 or an inscribed polygon, such as Figure 3 The trapezoidal rudder surface shown, Figure 4 The triangular rudder surface shown;

[0047] Taking into account that the rudder surface area of ​​the rudder surface 3 will affect the stability and maneuverability of the rudder surface 3, it is preferred to arrange the rudder surface shaft 4 along the diameter direction of the circular turntable 1, and the length of the rudder surface shaft 4 is equal to the diameter of the circular turntable 1, so that the length of one side of the rudder surface 3 used for rotationally connecting with the circular turntable 1 is equal to the diameter of the circular turntable 1, thereby obtaining a relatively large rudder surface area while keeping the size of the circular turntable 1 unchanged.

[0048] Preferably, the rudder surface 3 can be arranged to include a semicircular rudder surface, the center of the semicircular rudder surface coincides with the center of the circular turntable 1, and the diameter of the semicircular rudder surface is the same as the diameter of the circular turntable 1. Compared with the rudder surface 3 with a multi-deformation structure inscribed in a circle, the semicircular rudder surface not only has a larger rudder surface area, but also the transition of the outer edge of the rudder surface 3 is smoother, and the aerodynamic performance is relatively better.

[0049] The rudder surface rotating shaft 4 is connected to the rudder surface power mechanism, which is arranged in the circular turntable 1. The rudder surface power mechanism is used to drive the rudder surface 3 to perform a pitch adjustment of 0-180° relative to the circular turntable 1 around the rudder surface rotating shaft 4.

[0050] The rudder surface power mechanism includes a power source and a turntable transmission mechanism. The power source is preferably set to a turntable rotating motor, and the transmission mechanism can be set to a common transmission structure such as a gear transmission mechanism and a synchronous belt transmission. Considering the requirements for the adjustment accuracy of the azimuth angle of the rudder surface 3 in actual operation, a gear transmission mechanism and other meshing transmission methods are usually used to transmit torque.

[0051] The control device is connected to the turntable power mechanism and the rudder surface power mechanism signals, and is used to control the azimuth adjustment and pitch adjustment of the rudder surface 3. At the same time, the control device is connected to the flight control system signal of the aircraft 01, so as to receive the instructions of the flight control system to adjust the azimuth and pitch angles of the rudder surface 3.

[0052] When the circular turntable 1 rotates to the position where the control surface rotation axis 4 is parallel to the incoming flow direction, the control surface 3 is opened, and the control surface 3 is deflected relative to the incoming flow direction by rotating the circular turntable 1, so that the yaw moment of the aircraft 01 can be changed, and the heading of the aircraft 01 can be controlled;

[0053] When the circular turntable 1 rotates to the position where the rudder surface shaft 4 is perpendicular to the incoming flow direction, the rudder surface 3 is opened, and the circular turntable 1 is rotated to deflect the rudder surface 3 relative to the incoming flow direction, thereby changing the local lift of the aircraft 01 and achieving longitudinal control of the aircraft 01. When asymmetric lift is differentially generated on the left and right sides of the aircraft 01, a rolling moment can be generated to achieve lateral control of the aircraft 01.

[0054] When the circular turntable 1 rotates until the rudder surface shaft 4 maintains an angle with the incoming flow direction (excluding the two being perpendicular), the control capabilities of the three directions of pitch, yaw or roll can be generated simultaneously.

[0055] In this embodiment, by adjusting the azimuth angle of the circular turntable 1 and the pitch angle of the control surface 3, the elevator, rudder or aileron functions can be performed. When the control surface rotation shaft 4 is set at an angle with the incoming flow direction, the control surface has the control capabilities of pitch, yaw and roll at the same time, and has a strong composite control capability, which is beneficial to improving the stability and maneuverability of the aircraft 01, and can replace multiple control surfaces with separate control capabilities, thereby reducing the overall mass of the aircraft 01.

[0056] At the same time, when the rudder surface 3 is retracted, the rudder surface 3 is flush with the surface of the aircraft 01, thereby maintaining the low resistance and high stealth characteristics of the aircraft 01.

[0057] On the basis of the above embodiments, the structure of the rotating power mechanism is defined, the turntable power mechanism includes a turntable rotating motor, the turntable rotating motor is arranged in the fuselage or wing of the aircraft 01, the output shaft outer sleeve of the turntable rotating motor is provided with a first driving gear, and the end of the circular turntable 1 relatively far away from the rudder surface 3 is provided with a first passive gear, and the first passive gear is meshed with the first driving gear.

[0058] When the turntable rotating motor rotates, its output shaft drives the first driving gear to rotate, and then drives the first driven gear meshing with the first driving gear to rotate, so that the circular turntable 1 rotates around the turntable shaft 2.

[0059] In this embodiment, the rotating power mechanism adopts a gear transmission method, which is not only simple in structure and convenient in layout, but also effectively ensures the adjustment accuracy of the azimuth angle of the circular turntable 1.

[0060] Similarly, the rudder surface power mechanism may include a rudder surface rotating motor, the output shaft of which is outer-circuited with a second driving gear, the rudder surface rotating shaft 4 is outer-circuited with a second passive gear, and the second passive gear is meshed with the second driving gear, so as to reduce the volume of the rudder surface power mechanism and improve the adjustment accuracy of the pitch angle of the rudder surface 3.

[0061] On the basis of the above embodiment, an azimuth detection sensor for detecting the azimuth angle of the circular turntable 1 may be further provided. The azimuth detection sensor is connected to the control device signal so as to form negative feedback control on the azimuth adjustment of the circular turntable 1 .

[0062] The orientation detection sensor can be either an angle encoder arranged on the turntable shaft 2, or it can be set to detect a magnetic strip and a magnetic sensor. The detection magnetic strip is arranged in the turntable mounting hole of the aircraft 01, and the magnetic sensor is arranged on the outer edge of the circular turntable 1. The magnetic sensor can determine the orientation and movement direction of the circular turntable 1 by detecting the orientation of the magnetic strip.

[0063] The specific type and model of the orientation detection sensor is determined according to the structure and shape of the circular turntable 1, turntable shaft 2 and turntable mounting hole of the aircraft 01 in actual production, as long as the orientation detection sensor is easy to install and does not interfere with the normal rotation of the circular turntable 1.

[0064] In this embodiment, an azimuth detection sensor is used to measure the azimuth of the circular turntable 1 to ensure that the actual azimuth of the circular turntable 1 is the same as the command azimuth, thereby realizing closed-loop control of the azimuth adjustment of the circular turntable 1 .

[0065] On the basis of the above embodiment, a pitch detection sensor for detecting the pitch angle of the rudder surface 3 may be further provided, and the pitch detection sensor is connected to the control device signal so as to form negative feedback control on the pitch adjustment of the rudder surface 3 .

[0066] The pitch detection sensor can be either an angle encoder arranged on the rudder rotating shaft 4 or a potentiometer arranged on the rudder rotating shaft 4. When the rudder 3 rotates, the potentiometer will produce corresponding potential changes, and the pitch angle of the rudder 3 is calculated based on the potential change.

[0067] The specific type and model of the pitch detection sensor can be determined according to the structure and size of the rudder surface 3 and the rudder surface shaft 4 in actual production, so as to ensure the detection accuracy while avoiding the pitch detection sensor interfering with the rotation of the rudder surface 3.

[0068] In this embodiment, a pitch detection sensor is used to measure the pitch angle of the rudder surface 3 to ensure that the actual pitch angle of the rudder surface 3 is the same as the command pitch angle, thereby realizing closed-loop control of the azimuth angle adjustment of the rudder surface 3.

[0069] In addition to the above-mentioned dual-axis rotary control surfaces, the present invention also provides an aircraft 01 including the dual-axis rotary control surfaces disclosed in the above-mentioned embodiment, in particular a tailless aircraft. For the structures of other parts of the aircraft, please refer to the prior art and will not be repeated herein.

[0070] It should be noted that the first and second driving gears, as well as the first and second passive gears mentioned in the present application document are only used to distinguish the difference in position and do not contain any limitation on the order.

[0071] The various embodiments in this specification are described in a progressive manner, and each embodiment focuses on the differences from other embodiments. The same or similar parts between the various embodiments can be referenced to each other.

[0072] The above is a detailed introduction to the aircraft and the dual-axis rotary control surface provided by the present invention. Specific examples are used in this article to illustrate the principles and implementation methods of the present invention. The description of the above embodiments is only used to help understand the method of the present invention and its core idea. It should be pointed out that for ordinary technicians in this technical field, without departing from the principle of the present invention, several improvements and modifications can be made to the present invention, and these improvements and modifications also fall within the scope of protection of the claims of the present invention.

Claims

1. A dual-axis rotating control rudder surface, characterized in that: include: A circular turntable (1) rotatably mounted on the surface of the aircraft (01) via a turntable shaft (2); A rudder surface (3) is rotatably mounted on the circular turntable (1) via a rudder surface rotation shaft (4), the rudder surface rotation shaft (4) being perpendicular to the turntable rotation shaft (2), and when the rudder surface (3) is retracted, the rudder surface (3) is flush with the surface of the aircraft (01); A turntable power mechanism connected to the turntable shaft (2), used for driving the circular turntable (1) to rotate 360° around the turntable shaft (2) within the surface of the aircraft (01); A rudder surface power mechanism connected to the rudder surface rotating shaft (4), used for driving the rudder surface (3) to rotate around the rudder surface rotating shaft (4); A control device, the turntable power mechanism and the rudder surface power mechanism are both connected to the control device by signal.

2. The dual-axis rotary control rudder according to claim 1, characterized in that: The rudder surface rotating shaft (4) is arranged along the diameter direction of the circular rotating disk (1), and the length of the rudder surface rotating shaft (4) is equal to the diameter of the circular rotating disk (1).

3. The dual-axis rotary control rudder surface according to claim 2, characterized in that: The rudder surface (3) comprises a semicircular rudder surface, the center of the semicircular rudder surface coincides with the center of the circular turntable (1), and the diameter of the semicircular rudder surface is the same as the diameter of the circular turntable (1).

4. The dual-axis rotary control rudder according to claim 1, characterized in that: The turntable power mechanism comprises a turntable rotating motor, the turntable rotating motor is arranged in the fuselage or wing of the aircraft (01), the output shaft of the turntable rotating motor is outer-circuited with a first driving gear, and the end of the circular turntable (1) relatively far from the control surface (3) is provided with a first passive gear, and the first passive gear is meshed with the first driving gear.

5. The dual-axis rotary control rudder surface according to claim 1, characterized in that: The rudder surface power mechanism comprises a rudder surface rotating motor, the output shaft of the rudder surface rotating motor is provided with a second driving gear, the rudder surface rotating shaft (4) is provided with a second passive gear, and the second passive gear is meshed with the second driving gear.

6. The dual-axis rotary control rudder according to any one of claims 1 to 5, characterized in that: It also comprises an azimuth detection sensor for detecting the azimuth angle of the circular turntable (1), and the azimuth detection sensor is connected to the control device by signal.

7. The dual-axis rotary control rudder surface according to claim 6, characterized in that: The orientation detection sensor comprises a detection magnetic strip and a magnetic sensor, the detection magnetic strip is arranged in a turntable mounting hole of the aircraft (01), and the magnetic sensor is arranged on the outer edge of the circular turntable (1).

8. The dual-axis rotary control rudder according to any one of claims 1 to 5, characterized in that: It also comprises a pitch detection sensor for detecting the pitch angle of the control surface (3), and the pitch detection sensor is connected to the control device by signal.

9. The dual-axis rotary control rudder surface according to claim 8, characterized in that: The pitch detection sensor comprises a potentiometer, and the potentiometer is arranged on the rudder surface rotating shaft (4).

10. An aircraft, characterized in that: It comprises the dual-axis rotating control surface as described in any one of claims 1-9.

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