An inflatable rotary steering gear and an aircraft

Abstract

The present invention provides an inflatable rotary actuator, comprising: a plurality of inflatable modules, an inner-section mounting shell and an outer-section mounting shell; the inner-section mounting shell and the outer-section mounting shell form a cavity for accommodating a plurality of inflatable modules; a rotating plate located in the cavity is fixedly connected to the outer-section mounting shell, and a plurality of inflatable modules are arranged on both sides of the rotating plate. The inflatable modules can push the rotating plate to rotate, so as to realize the relative rotation of the inner-section mounting shell and the outer-section mounting shell. By using the expansion and contraction of the inflatable modules, rotations in different directions and at different angles can be realized, and the limiting of the rudder surface is realized during the rotation to prevent excessive rotation angles.

Description

Technical Field

[0001] The present invention belongs to the technical field related to aircraft, and particularly relates to an inflatable rotating servo and an aircraft. Background Art

[0002] The statements in this section merely provide background technical information related to the present invention and do not necessarily constitute prior art.

[0003] At present, most wing tilting mechanisms are composed of devices such as servos and hydraulics. The tilting mechanism is connected to the wing assembly, and the rotation of the wing assembly is driven by the servo in the tilting mechanism to achieve the tilting of the wing.

[0004] However, there are problems with wear of the internal components of the current tilting mechanism. Once severe wear occurs, it will cause the tilting mechanism to malfunction, resulting in the out-of-control of the aircraft. In addition, due to the large number of internal components in the current tilting mechanism, there are also problems of large occupied volume and large weight, and it cannot be installed in a narrow space. Summary of the Invention

[0005] To overcome the deficiencies of the above-mentioned prior art, the present invention provides an inflatable rotating servo and an aircraft, which utilize the expansion and contraction of the inflatable module to achieve rotation in different directions and at different angles, and limit the position of the rudder surface during rotation to prevent excessive rotation angles.

[0006] To achieve the above object, one or more embodiments of the present invention provide the following technical solutions: An inflatable rotating servo, comprising: a plurality of inflatable modules, an inner section mounting shell, and an outer section mounting shell;

[0007] The inner section mounting shell and the outer section mounting shell form a cavity capable of accommodating a plurality of inflatable modules;

[0008] A rotating plate located in the cavity is fixedly connected to the outer section mounting shell, and a plurality of inflatable modules are arranged on both sides of the rotating plate. The inflatable modules can push the rotating plate to rotate, thereby realizing the relative rotation of the inner section mounting shell and the outer section mounting shell.

[0009] Further, the inflatable module includes an airbag, an intake pipe communicating with the airbag, and an exhaust pipe, and both the intake pipe and the exhaust pipe are connected to an air pump.

[0010] Further, the inner section mounting shell and the outer section mounting shell are coaxially installed.

[0011] Further, a hollow shaft is fixedly connected to the center of the inner section mounting shell, and a mounting shaft is fixedly connected to the center of the outer section mounting shell, and the mounting shaft is installed in the hollow shaft.

[0012] Further, a partition is provided on the inner wall of the inner-section mounting housing, and a plurality of inflatable modules are symmetrically arranged on both sides of the partition.

[0013] Further, the plane where the partition is located is parallel to the plane of the non-rotatable inner-section wing of the aircraft.

[0014] Further, a pressure sensor is provided on the partition, and the pressure sensor is used to measure the pressure exerted on the partition by the inflatable module.

[0015] Further, a Hall sensor is further included. The Hall sensor is fixedly connected to the top surface of the inner-section mounting housing and the mounting shaft of the outer-section mounting housing respectively, and is used to measure the relative rotation angle between the inner-section mounting housing and the outer-section mounting housing.

[0016] Further, a controller is further included. The controller receives the angle measurement data of the Hall sensor, and the controller controls the operation of the air pump according to the received angle measurement data.

[0017] The second aspect of the present invention discloses an aircraft, including an inflatable rotary actuator as described above. The inner-section mounting housing of the rotary actuator is fixedly connected to the inner beam on the inner-section wing of the aircraft, and the outer-section mounting housing of the rotary actuator is fixedly connected to the outer beam on the outer-section wing of the aircraft.

[0018] The above one or more technical solutions have the following beneficial effects:

[0019] In the present invention, the inflation and contraction of the airbag are used to achieve rotation in different directions and at different angles. The space occupied by the airbag is small, the operating noise is low, the number of parts is small, and the weight is light, so it can be installed and used in a narrow space.

[0020] In the present invention, a plurality of airbags can be arranged in the cavity of the rotary actuator as backups. When the working airbag fails, the backup airbag can be used, thereby improving safety.

[0021] In the present invention, the airbags are symmetrically arranged on both sides of the partition. When one airbag expands to push the rotating plate, the other airbag ensures that the outer-section mounting housing does not rotate excessively through relative contraction, realizing the limit of the rudder surface.

[0022] The advantages of the additional aspects of the present invention will be partially given in the following description, partially will become obvious from the following description, or will be understood through the practice of the present invention. BRIEF DESCRIPTION OF THE DRAWINGS

[0023] The specification drawings forming a part of the present invention are used to provide a further understanding of the present invention. The schematic embodiments of the present invention and their descriptions are used to explain the present invention and do not constitute an improper limitation to the present invention.

[0024] Figure 1 This is the overall schematic diagram of the inflatable rotary actuator in the present invention;

[0025] Figure 2 This is the exploded view of the inflatable rotary actuator in the present invention;

[0026] Figure 3 This is the exploded view of the inflatable rotary actuator in the present invention;

[0027] Figure 4 This is the schematic diagram of the connection between the inflatable rotary actuator and the aircraft in the present invention.

[0028] Among them, 1. Inner section mounting shell, 2. Outer section mounting shell, 3. Airbag, 4. Intake pipe, 5. Exhaust pipe, 6. Pressure sensor, 7. Hall sensor, 8. Hollow shaft, 9. Mounting shaft, 10. Rotating plate 10, 11. Partition 11, 12. Inner beam, 13. Outer beam, 14. Inflatable rotary actuator Detailed implementation manners

[0029] It should be noted that the following detailed description is exemplary and is intended to provide further explanation of the present invention. Unless otherwise specified, all technical and scientific terms used herein have the same meaning as commonly understood by those of ordinary skill in the technical field to which the present invention belongs.

[0030] It should be noted that the terms used herein are only for describing specific implementation manners and are not intended to limit the exemplary embodiments according to the present disclosure. As used herein, unless the context clearly indicates otherwise, the singular form is also intended to include the plural form. In addition, it should be understood that when the terms "include" and / or "comprise" are used in this specification, they indicate the presence of features, steps, operations, devices, components, and / or combinations thereof.

[0031] In the present disclosure, terms such as "fixed connection", "connected", "connected to" should be understood in a broad sense, which may mean a fixed connection, an integral connection or a detachable connection; it may be directly connected or indirectly connected through an intermediate medium. For those skilled in the relevant scientific research or technology in this field, the specific meanings of the above terms in the present disclosure can be determined according to specific situations, and should not be construed as a limitation to the present disclosure.

[0032] The present invention discloses an inflatable rotary actuator, comprising: a plurality of inflatable modules, an inner section mounting shell and an outer section mounting shell;

[0033] The inner section mounting shell and the outer section mounting shell form a cavity for accommodating a plurality of inflatable modules;

[0034] A rotating plate located inside the cavity is fixedly connected to the outer section mounting shell, and a plurality of inflatable modules are arranged on both sides of the rotating plate. The inflatable modules can push the rotating plate to rotate, thereby realizing the relative rotation of the inner section mounting shell and the outer section mounting shell.

[0035] Embodiment 1

[0036] This embodiment discloses an inflatable rotating steering gear 14, which is described by taking two inflatable modules as an example.

[0037] As Figures 1-3 shown, in this embodiment, the inflatable modules are located inside the cavity formed by the inner section mounting shell 1 and the outer section mounting shell 2. The inflatable modules are symmetrically arranged on both sides of the rotating plate 10. By inflating one of the inflatable modules, the rotating plate 10 is pushed to rotate under the action of the inflatable module. Since the rotating plate 10 is fixedly connected to the outer section mounting shell 2, the rotational movement of the outer section mounting shell 2 relative to the inner section mounting shell 1 is realized.

[0038] When one of the inflatable modules is inflated and expanded, at this time, the other inflatable module is also inflated and expanded to an appropriate position to limit the excessive rotation of the rotating plate 10 and play a role in limiting the position.

[0039] The rotating plate 10 can rotate in two directions, clockwise or counterclockwise, under the action of the inflatable module, and thus can realize the forward or reverse rotation of controlling the tilting direction of the wing.

[0040] Optionally, the shape of the inner section mounting shell can be a hollow cylinder, and the outer section mounting shell is also circular. The diameter of the inner section mounting shell is the same as the diameter of the outer section mounting shell to enable the sealed installation of the inner section mounting shell and the outer section mounting shell.

[0041] In a specific embodiment, the inflatable module includes an airbag 3, an air inlet pipe 4 and an exhaust pipe 5 communicated with the airbag 3. Both the air inlet pipe 4 and the exhaust pipe 5 are connected to an air pump (not shown in the figure), and the expansion or contraction of the airbag 3 is realized under the action of the air pump.

[0042] In one embodiment, a through hole is provided on the top surface of the inner section mounting shell 1, and the air inlet pipe 4 and the exhaust pipe 5 connected to the airbag 3 pass through the through hole and are connected to the air pump.

[0043] It can be understood that the number of through holes can be one or more.

[0044] In one embodiment, a hollow shaft 8 is fixedly connected to the center position of the inner section mounting shell 1, and a mounting shaft 9 is fixedly connected to the center position of the outer section mounting shell 2. The inner section mounting shell 1 and the outer section mounting shell 2 are coaxially installed. When assembling the inner section mounting shell 1 and the outer section mounting shell 2, the mounting shaft 9 is inserted into the hollow shaft 8 to realize the installation.

[0045] It can be understood that the outer diameter of the mounting shaft 9 is slightly smaller than the inner diameter of the hollow shaft 8, and the length of the mounting shaft 9 is adapted to the length of the hollow shaft 8 to achieve the installation of the mounting shaft 9 and the hollow shaft 8.

[0046] A partition 11 is provided between the inner wall of the inner section mounting shell 1 and the hollow shaft 8. The partition 11 is fixedly connected to the inner wall of the inner section mounting shell 1. The partition 11 is located between the airbags 3. The plane where the partition 11 is located is parallel to the plane of the non-rotatable inner section wing of the aircraft. The partition 11 on the inner wall of the inner section mounting shell is non-rotatable, and the airbags 3 are symmetrically distributed on both sides of the partition 11.

[0047] It can be understood that when the airbag is not inflated and expanded, the rotating plate 10 and the partition 11 are located on the same horizontal plane, and the airbags are symmetrically distributed on both sides of the rotating plate 10 and the partition 11.

[0048] In one embodiment, pressure sensors 6 are respectively provided on both sides of the partition 11. The pressure sensors 6 are used to measure the pressure exerted by the airbags 3 on the partition 11, so as to adjust the pressure inside the airbags according to the measured value, so as to ensure that the pressure inside the airbags is within the normal value.

[0049] In one embodiment, a Hall sensor 7 is further included. The Hall sensor 7 is installed at the center of the top surface of the inner section mounting shell 1. The Hall sensor 7 is connected to the top surface of the inner section mounting shell 1 and the mounting shaft 9 on the outer section mounting shell 2. The Hall sensor 7 is tightly fitted with the inner section mounting shell 1 and the mounting shaft 9. The rotating component of the Hall sensor itself is used to measure the relative angle between the inner section mounting shell 1 and the outer section mounting shell 2 to determine the rotation angle.

[0050] In this embodiment, a control method for an inflatable rotating servo is disclosed as follows:

[0051] According to the direction (forward rotation or reverse rotation) required for the wing to tilt, the controller controls the air pump to inflate or deflate the two airbags. The controller also receives the deflection angle measured by the Hall sensor between the inner section mounting shell and the outer section mounting shell to determine the rotation angle, and controls the inflation or deflation size of the airbags by the air pump according to the received angle information to achieve the control of the rotation angle; at the same time, the controller also receives the pressure value measured by the pressure sensor of the pressure exerted by the airbag on the partition 11 of the inner section mounting shell, and controls the inflation or deflation size of the airbag by the air pump according to the received pressure value, so that the pressure inside the airbag is within the normal range.

[0052] Embodiment 2

[0053] This embodiment discloses an inflatable rotary actuator. Different from the first embodiment, the inflatable rotary actuator disclosed in this embodiment includes multiple pairs of backup inflatable modules. The multiple pairs of backup inflatable modules are also located in the cavity formed by the inner mounting shell and the outer mounting shell. Each pair of inflatable modules is located on both sides of the partition 11 and is symmetrically arranged. The rest is the same as that of the first embodiment and will not be elaborated here.

[0054] During use, two inflatable modules work. When one of the inflatable modules fails, the backup inflatable module can be enabled.

[0055] Embodiment Three

[0056] As Figure 4 shown, this embodiment discloses an aircraft, which includes an inflatable rotary actuator described in the first embodiment or the second embodiment. The inflatable rotary actuator is installed between the inner beam and the outer beam of the wing of the aircraft. The inner beam 12 is located on the inner section of the wing fixedly connected to the fuselage, and the outer beam 13 is located on the outer section of the wing of the fuselage and is fixedly connected to the outer section of the wing. The inner mounting shell of the inflatable rotary actuator is fixedly connected to the inner beam, and the outer mounting shell is fixedly connected to the outer beam. By rotating the inflatable rotary actuator, the outer beam drives the outer section of the wing to rotate.

[0057] Although the specific implementation manners of the present invention are described above in conjunction with the drawings, it does not limit the protection scope of the present invention. Those skilled in the art should understand that based on the technical solutions of the present invention, various modifications or deformations that can be made without creative labor by those skilled in the art are still within the protection scope of the present invention.

Claims

1. An inflatable rotary steering gear, characterized in that, Comprising: A plurality of inflatable modules, an inner-section mounting shell and an outer-section mounting shell; The inner-section mounting shell and the outer-section mounting shell form a cavity capable of accommodating a plurality of inflatable modules; A rotating plate located inside the cavity is fixedly connected to the outer-section mounting shell, and a plurality of inflatable modules are arranged on both sides of the rotating plate. The inflatable modules can push the rotating plate to rotate, so as to realize the relative rotation of the inner-section mounting shell and the outer-section mounting shell; The rotating plate can rotate in two directions, clockwise or counterclockwise, under the action of the inflatable modules, and thus can realize the forward or reverse rotation for controlling the tilting direction of the wing; A partition is arranged on the inner wall of the inner-section mounting shell, and a plurality of inflatable modules are symmetrically arranged on both sides of the partition; The inflatable module includes an airbag, an air inlet pipe and an exhaust pipe communicated with the airbag. Both the air inlet pipe and the exhaust pipe are connected to an air pump; The airbags are symmetrically arranged on both sides of the partition. When one airbag expands to push the rotating plate, the other airbag contracts relatively to ensure that the outer-section mounting shell will not rotate excessively, so as to realize the limit of the control surface; 2. The inflatable rotary steering gear according to claim 1, characterized in that, The inner-section mounting shell and the outer-section mounting shell are coaxially mounted; 3. The inflatable rotary steering gear according to claim 1, characterized in that, A hollow shaft is fixedly connected to the center of the inner-section mounting shell, and a mounting shaft is fixedly connected to the center of the outer-section mounting shell. The mounting shaft is installed inside the hollow shaft; 4. The inflatable rotary steering gear according to claim 1, characterized in that, The plane where the partition is located is parallel to the plane of the non-rotatable inner-section wing of the aircraft; 5. The inflatable rotary steering gear according to claim 1, characterized in that, A pressure sensor is arranged on the partition, and the pressure sensor is used for measuring the pressure exerted by the inflatable module on the partition; 6. The inflatable rotary steering gear according to claim 3, characterized in that, It further includes a Hall sensor, which is fixedly connected to the top surface of the inner-section mounting shell and the mounting shaft of the outer-section mounting shell respectively, and is used for measuring the relative rotation angle between the inner-section mounting shell and the outer-section mounting shell; 7. The inflatable rotary steering gear according to claim 6, characterized in that, It further includes a controller. The controller receives the angle measurement data of the Hall sensor, and the controller controls the action of the air pump according to the received angle measurement data; 8. An aircraft, comprising an inflatable rotary actuator according to any one of claims 1-7. The inner-section mounting shell of the rotary actuator is fixedly connected to the inner beam on the inner-section wing of the aircraft, and the outer-section mounting shell of the rotary actuator is fixedly connected to the outer beam on the outer-section wing of the aircraft.

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