A non-similar dual-redundancy servo device for an aircraft air damper

Abstract

The present invention belongs to the technical field of aircraft accessories, and particularly relates to a non-similar dual-redundancy servo device for an aircraft air damper, which includes a motor, a control mechanism, a pneumatic mechanism, and a control component; by providing a control mechanism in the device that is compatible with both electric control and pneumatic control in the present invention, redundant control of the aircraft air damper under different control modes is achieved. Compatible switching can be carried out between electric control and pneumatic control, reducing the problem of control failure caused by similar faults, thereby improving the reliability of the control system and greatly enhancing flight safety.

Description

Technical Field

[0001] The present invention belongs to the technical field of aviation accessories, and particularly relates to a non-similar dual-redundancy servo device for an aircraft air damper. Background Art

[0002] The aircraft servo air damper is mainly applied to the auxiliary power unit (APU) located at the tail end of the aircraft, and controls the on-off of the air intake of the air turbine starter and the adjustment of the air volume through the on-board control signal. Before the aircraft takes off, the auxiliary power unit (APU) provides power and air source for the main engine of the aircraft. During the flight of the aircraft, if the main engine stops in the air, at a certain altitude, the auxiliary power unit (APU) can be started at high altitude to provide power for the restart of the engine. Therefore, while improving the reliability of the aircraft auxiliary power unit (APU), it is very necessary to increase the safety protection of the air duct valve controller for the auxiliary power unit (APU).

[0003] At present, the servo air dampers of aircraft at home and abroad are mostly in the form of motor or electric motor manipulation, and the safety margin of this manipulation form is low, and there are a series of problems such as the device malfunctioning caused by a single fault. Especially, the engine air duct air damper device has high requirements for reliability and safety margin, and its minor faults may cause catastrophic consequences. Therefore, an important method to improve the reliability of the aircraft air duct valve device is to develop redundant technology. In this regard, the dual-motor form can effectively improve the reliability, but the failure modes of the dual-motor structure form are the same, and the occurrence of the motor failure rate cannot be completely avoided. Summary of the Invention

[0004] In view of this, the present invention provides a non-similar redundant servo device for an aircraft air damper, which realizes the redundant control of the aircraft air damper under different manipulation modes by setting a manipulation mechanism compatible with electric manipulation and pneumatic manipulation in the device. The electric manipulation and pneumatic manipulation can be compatibly switched, reducing the manipulation failure problem caused by similar faults, thereby improving the reliability of the control system and greatly improving the flight safety.

[0005] In order to achieve the above technical purpose, the specific technical solutions adopted by the present invention are as follows:

[0006] A non-similar dual-redundancy servo device for an aircraft air damper, used to control the air damper of the aircraft APU, includes:

[0007] A motor, a manipulation mechanism, a pneumatic mechanism, and a control component;

[0008] The motor is controlled by the control component and outputs an electric switch displacement torque for opening and closing the air damper;

[0009] The pneumatic mechanism is used to output a pneumatic switch displacement torque for opening and closing the air damper based on the air source or hydraulic source of the aircraft;

[0010] The operating mechanism is used to transfer the electric switch displacement torque or pneumatic switch displacement torque to the air damper.

[0011] Further, the operating mechanism includes a worm and worm gear, a sun gear, planet gears, a planet carrier, and an internal gear ring;

[0012] The worm end of the worm and worm gear is drivingly arranged with the motor, and the worm wheel end of the worm and worm gear is drivingly arranged with the sun gear; There are at least two groups of planet gears, all of which are meshed with the sun gear;

[0013] The internal gear ring is meshed with each of the planet gears based on internal teeth; The planet carrier is installed on each of the planet gears and is simultaneously drivingly arranged with the air damper;

[0014] The pneumatic mechanism is drivingly arranged with the internal gear ring; The pneumatic mechanism drives the internal gear ring to perform a lockable rotation coaxial with the sun gear.

[0015] Further, the pneumatic mechanism includes a two-position two-way solenoid valve, a two-position four-way hydraulic directional control valve, and an actuating cylinder;

[0016] The two-position two-way solenoid valve is controlled by the control component and is used to realize the reciprocating movement of the spool of the two-position four-way hydraulic directional control valve based on the air source or hydraulic source of the aircraft; The two-position four-way hydraulic directional control valve is controlled by the two-position two-way solenoid valve and is used to selectively transfer the air source or hydraulic source of the aircraft to the actuating cylinder; The actuating cylinder outputs the pneumatic switch displacement torque based on the selectively transferred air source or hydraulic source of the aircraft.

[0017] Further, the actuating cylinder includes an actuating cylinder outer cylinder, an actuating cylinder spring, and an actuating cylinder piston rod;

[0018] One end of the actuating cylinder piston rod is a piston and is arranged inside the actuating cylinder, and the other end is drivingly arranged with the internal gear ring, and the movement direction is parallel to the axis of the actuating cylinder;

[0019] The actuating cylinder spring is arranged inside the actuating cylinder outer cylinder, one end acts on the inner wall of the actuating cylinder, and the other end acts on the piston, and the direction of the pre-tightening force is parallel to the axis of the actuating cylinder.

[0020] Further, the pneumatic mechanism further includes a first one-way valve and a first speed control valve; The first one-way valve and the first speed control valve are arranged in parallel and act between an output end of the two-position four-way hydraulic directional control valve and an input end of the actuating cylinder; The allowable passage direction of the first one-way valve is from the actuating cylinder to the two-position four-way hydraulic directional control valve.

[0021] Further, the pneumatic mechanism further includes a second one-way valve and a second speed regulator valve; the second one-way valve and the second speed regulator valve are arranged in parallel and act between the other output end of the two-position four-way hydraulic directional control valve and the other input end of the actuating cylinder; the allowable passing direction of the second one-way valve is from the actuating cylinder to the two-position four-way hydraulic directional control valve.

[0022] Further, a reduction spur gear train is provided between the electric motor and the worm end of the worm and worm gear.

[0023] Further, external teeth are provided on the internal gear ring; a spur gear drive is provided between the piston rod and the internal gear ring; the spur gear meshes with the external teeth of the internal gear ring.

[0024] Further, the servo device further includes a displacement sensor; the displacement sensor is used to detect the opening amount of the air damper; the detection result of the displacement sensor is output to the control component.

[0025] Further, the servo device further includes a filter; the filter is electrically connected to the control component and is used to realize the transmission of the discrete signals of the aircraft to the control component. Description of the Drawings

[0026] In order to more clearly illustrate the technical solutions of the embodiments of the present disclosure, the drawings required for use in the embodiments will be briefly introduced below. Obviously, the drawings in the following description are only some embodiments of the present disclosure. For those of ordinary skill in the art, other drawings can be obtained based on these drawings without creative efforts.

[0027] Figure 1 It is a working principle diagram of a non-similar redundant servo device for an aircraft air damper in a specific embodiment of the present invention;

[0028] Wherein: 1. Electric motor; 2. Operating mechanism; 201. Spur gear train; 202. Worm and worm gear; 203. Bearing; 204. Sun gear; 205. Spur gear; 206. Internal gear ring; 207. Planet carrier; 208. Planet gear; 3. Pneumatic mechanism; 301. Two-position two-way solenoid valve; 302. Two-position four-way hydraulic directional control valve; 303. First one-way valve; 304. First speed regulator valve; 305. Outer cylinder of the actuating cylinder; 306. Spring of the actuating cylinder; 307. Piston rod of the actuating cylinder; 308. Second one-way valve; 309. Second speed regulator valve; 4. Angular displacement sensor; 5. Control component; 501. Control board; 502. Filter; 503. Socket; 6. Air damper. Detailed Embodiments

[0029] The following describes the embodiments of the present disclosure in detail with reference to the accompanying drawings.

[0030] The following uses specific specific examples to illustrate the implementation manners of the present disclosure. Those skilled in the art can easily understand other advantages and effects of the present disclosure from the content disclosed in this specification. Obviously, the described embodiments are only a part of the embodiments of the present disclosure, rather than all the embodiments. The present disclosure can also be implemented or applied through other different specific implementation manners. Various details in this specification can also be modified or changed based on different viewpoints and applications without departing from the spirit of the present disclosure. It should be noted that, without conflict, the following embodiments and the features in the embodiments can be combined with each other. Based on the embodiments in the present disclosure, all other embodiments obtained by those of ordinary skill in the art without making creative efforts belong to the scope of protection of the present disclosure.

[0031] It should be noted that the following describes various aspects of the embodiments within the scope of the appended claims. It should be obvious that the aspects described herein can be embodied in a wide variety of forms, and any specific structure and / or function described herein is illustrative only. Based on the present disclosure, those skilled in the art should understand that one aspect described herein can be implemented independently of any other aspect, and two or more of these aspects can be combined in various ways. For example, any number of aspects described herein can be used to implement the device and / or practice the method. In addition, this device and / or this method can be implemented using other structures and / or functions in addition to one or more of the aspects described herein.

[0032] It should also be noted that the diagrams provided in the following embodiments only illustrate the basic concept of the present disclosure in a schematic manner. The diagrams only show the components related to the present disclosure rather than being drawn according to the number, shape, and size of the components in actual implementation. The type, quantity, and ratio of each component in its actual implementation can be an arbitrary change, and the component layout type may also be more complex.

[0033] In addition, in the following description, specific details are provided to facilitate a thorough understanding of the examples. However, those skilled in the art will understand that the described aspects can be practiced without these specific details.

[0034] In an embodiment of the present invention, a non-similar dual-redundancy servo device for the aircraft damper 6 is proposed, which is used to control the damper 6 of the aircraft APU, as Figure 1 shown, including:

[0035] a motor 1, a control mechanism 2, a pneumatic mechanism 3, and a control component 5;

[0036] The motor 1 is controlled by the control component 5 and outputs an electric switch displacement torque for opening and closing the air damper 6.

[0037] The pneumatic mechanism 3 is used to output a pneumatic switch displacement torque for opening and closing the air damper 6 based on the aircraft's air source or hydraulic source.

[0038] The operating mechanism 2 is used to transfer the electric switch displacement torque or the pneumatic switch displacement torque to the air damper 6.

[0039] In this embodiment, the operating mechanism 2 includes a worm and worm gear 202, a sun gear 204, planet gears 208, a planet carrier 207, and an internal gear ring 206.

[0040] The worm end of the worm and worm gear 202 is in transmission connection with the motor 1, and the worm wheel end of the worm and worm gear 202 is in transmission connection with the sun gear 204; there are at least two sets of planet gears 208, all of which are meshed with the sun gear 204.

[0041] The internal gear ring 206 is meshed with each planet gear 208 based on internal teeth; the planet carrier 207 is installed on each planet gear 208 and is simultaneously in transmission connection with the air damper 6.

[0042] The pneumatic mechanism 3 is in transmission connection with the internal gear ring 206; the pneumatic mechanism 3 drives the internal gear ring 206 to perform a lockable rotation coaxial with the second speed control valve 309 of the sun gear 204.

[0043] In this embodiment, the pneumatic mechanism 3 includes a two-position two-way solenoid valve 301, a two-position four-way hydraulic directional control valve 302, and an actuating cylinder.

[0044] The two-position two-way solenoid valve 301 is controlled by the control component 5 and is used to realize the reciprocating movement of the spool of the two-position four-way hydraulic directional control valve 302 based on the aircraft's air source or hydraulic source; the two-position four-way hydraulic directional control valve 302 is controlled by the two-position two-way solenoid valve 301 and is used to selectively transfer the aircraft's air source or hydraulic source to the actuating cylinder; the actuating cylinder outputs a pneumatic switch displacement torque based on the selectively transferred aircraft's air source or hydraulic source.

[0045] In this embodiment, the actuating cylinder includes an actuating cylinder outer cylinder 305, an actuating cylinder spring 306, and an actuating cylinder piston rod 307.

[0046] One end of the actuating cylinder piston rod 307 is a piston and is arranged inside the actuating cylinder, and the other end is in transmission connection with the internal gear ring 206, and the movement direction is parallel to the axial direction of the actuating cylinder.

[0047] The actuating cylinder spring is arranged inside the actuating cylinder outer cylinder 305, one end acts on the inner wall of the actuating cylinder, and the other end acts on the piston, and the direction of the pre-tightening force is parallel to the axial direction of the actuating cylinder.

[0048] In this embodiment, the pneumatic mechanism 3 further includes a first one-way valve 303 and a first speed control valve 304; the first one-way valve 303 and the first speed control valve 304 are arranged in parallel and act between an output end of the two-position four-way hydraulic directional control valve 302 and an input end of the actuating cylinder; the allowable flow direction of the first one-way valve 303 is from the actuating cylinder to the two-position four-way hydraulic directional control valve 302.

[0049] In this embodiment, the pneumatic mechanism 3 further includes a second one-way valve 308 and a second speed control valve 309; the second one-way valve 308 and the second speed control valve 309 are arranged in parallel and act between the other output end of the two-position four-way hydraulic directional control valve 302 and the other input end of the actuating cylinder; the allowable flow direction of the second one-way valve 308 is from the actuating cylinder to the two-position four-way hydraulic directional control valve 302.

[0050] In this embodiment, the motor 1 and the worm end of the worm and gear 202 are driven based on the spur gear train 201.

[0051] In this embodiment, external teeth are provided on the internal gear ring 206; the piston rod and the internal gear ring 206 are driven based on the spur gear 205; the spur gear 205 meshes with the external teeth of the internal gear ring 206.

[0052] In this embodiment, the servo device further includes a displacement sensor; the displacement sensor is used to detect the opening amount of the air damper 6; the detection result is output to the control component 5.

[0053] In this implementation, the displacement sensor is the angular displacement sensor 4.

[0054] In this embodiment, the servo device further includes a filter 502; the filter 502 is electrically connected to the control component 5 and is used to realize the transmission of the discrete signals of the aircraft to the control component 5.

[0055] The dissimilar dual-redundancy servo device for the aircraft air damper 6 of this embodiment includes a motor 1, a control mechanism 2, a pneumatic mechanism 3, an angular displacement sensor 4, a control component 5, and an air damper 6. The flange mounting plate of the motor 1 is connected to the housing of the control mechanism 2 by bolts. The flange mounting plate of the pneumatic mechanism 3 is connected to the housing of the control mechanism 2 by bolts. The control mechanism 2 and the air damper 6 are connected in the form of splines or branch ports. The flange mounting plate of the angular displacement sensor 4 is connected to the housing of the control mechanism 2 by bolts, and the rotating shaft is connected to the output shaft of the air damper 6 by a flat key. The control component 5 is installed in the housing of the control mechanism 2. The control mechanism 2 includes a spur gear train 201, a worm and worm gear 202, bearings 203, a sun gear 204, spur gears 205, an internal gear ring 206, a planet carrier 207, and planet gears 208. The pneumatic mechanism 3 is highly integrated and includes a two-position two-way solenoid valve 301, a two-position four-way hydraulic directional control valve 302, a first check valve 303, a second check valve 308, a first flow control valve 304, a second flow control valve 309, an actuator outer cylinder 305, an actuator spring 306, and an actuator piston rod 307. A parallel arrangement of the first check valve 303 and the first flow control valve 304 is provided on the rodless cavity side of the actuator. A parallel arrangement of the second check valve 308 and the second flow control valve 309 is provided on the rod side of the actuator. And the first check valve 303 and the second check valve 308 are arranged in the same direction. Through the first flow control valve 304 and the second flow control valve 309, the smooth movement of the actuator piston rod 307 is realized, and at the same time, the rotation speed of the air damper 6 is adjusted by the first flow control valve 304 and the second flow control valve 309. The control component 5 includes a control board 501, a filter 502, and a socket 503. The control component 5 is integrated in the housing of the control mechanism 2 and is connected to the aircraft through the socket 503. The air damper 6 includes a valve body, a valve flap, a sealing plate, a connecting shaft, a plug, and bearings 203, and the structural forms include ball valves, slide gates, and butterfly valves.

[0056] In the control mechanism 2, the external teeth of the internal gear ring 206 mesh with the rack of the actuator piston rod 307 through the spur gear 205. The outer surface of the internal gear ring 206 is pasted with a modified polytetrafluoroethylene fabric through a special process to achieve low-friction torque rotation. And the clearance of gear meshing can be eliminated by adjusting the pre-tightening force of the spring, realizing zero-clearance meshing between the external teeth of the internal gear ring 206 and the spur gear 205 and the rack of the actuator piston rod 307. One end of the spur gear train 201 is connected to the output shaft of the motor 1 by a pin, and the other end is connected to the worm and worm gear 202 by a locking nut. The angular displacement sensor 4 usually adopts a precision conductive potentiometer or an RVDT to realize synchronous feedback of the angular position.

[0057] The medium of the pneumatic mechanism 3 directly comes from the bleed air of the auxiliary power unit APU, which is convenient to obtain.

[0058] The dissimilar dual-redundancy servo device for the aircraft air damper 6 of this embodiment has the following characteristics:

[0059] Non-similar dual-redundancy design

[0060] To prevent functional failures caused by similar faults, electric control and pneumatic control are combined in the design, effectively avoiding the occurrence of similar faults and truly improving the reliability of the product.

[0061] Modular design

[0062] To facilitate the quick and accurate operation and maintenance of the device in the field, the operating mechanism 2, pneumatic mechanism 3, and air damper 6 are designed as a combined type. The mounting end faces of the operating mechanism 2 and the air damper 6 have flange mounting plates, the mounting end faces of the pneumatic mechanism 3 and the operating mechanism 2 have flange mounting plates, and annular grooves corresponding to them are machined in the stepped holes of the mounting flange end face of the housing of the operating mechanism 2 to ensure the coaxiality when the pneumatic mechanism 3 and the air damper 6 are installed.

[0063] Integrated design

[0064] In the pneumatic mechanism 3, the two-position two-way solenoid valve 301, two-position four-way hydraulic directional control valve 302, first check valve 303, second check valve 308, first speed control valve 304, second speed control valve 309, and actuator are highly integrated into a valve block, meeting the requirements of small volume, light weight, and convenient maintenance.

[0065] Zero-clearance design

[0066] The connection between the external teeth of the internal gear ring 206 and the spur gear 205 and the rack of the actuator piston rod 307 is by gear-rack meshing. A spring is provided at the actuator piston rod 307, and the clearance of the gear-rack meshing can be eliminated by adjusting the compression amount of the spring, achieving zero-clearance meshing between the external teeth of the internal gear ring 206, the spur gear 205, and the rack of the actuator piston rod 307.

[0067] Low-friction and small-volume design

[0068] The internal gear ring 206 is a key component for the conversion between electric control and pneumatic control. The outer surface is pasted with modified polytetrafluoroethylene fabric through a special process to achieve low friction and small volume during the rotation of the internal gear ring 206 in the gear train.

[0069] Generalization and serialization design

[0070] The pneumatic mechanisms 3 are highly integrated together, and generalization and serialization among different media can be achieved by replacing different working media, such as hydraulic oil, kerosene, air, nitrogen, etc.

[0071] The working principle of this embodiment is:

[0072] 1. When the motor 1 is working, the pneumatic mechanism 3 is not working. Specifically, the control board 501 cuts off the power supply to the solenoid valve. The medium passes through the left position of the two-position four-way hydraulic directional control valve 302 and the second one-way valve 308 and enters the rod chamber with a rod of the actuating cylinder piston rod 307. The actuating cylinder piston rod 307 moves to the left extreme position under the action of the medium force, and under the action of the pre-tightening force of the spring, the inner gear ring 206 of the operating mechanism 2 is reliably locked by the piston rod rack and the spur gear 205. At the same time, the compression amount of the spring is adjusted, thereby realizing the adjustment of zero clearance between the gears.

[0073] a. An operation instruction is issued on the machine. The device acquires the opening instruction of the air damper 6 collected by the socket 503 in the control component 5. The control board 501 analyzes and processes the discrete quantity signal to realize the opening instruction of the air damper 6, controls the motor 1 to rotate forward, drives the air damper 6 to move in the opening direction through the output shaft of the operating mechanism 2. The angular displacement sensor 4 feeds back the signal that the air damper 6 is opened in place to the control board 501 and at the same time feeds it back to the machine through the socket 503. The control board 501 gives an instruction for the motor 1 to stop working. During the whole working process, the angular displacement sensor 4 collects signals in real time, and timely and accurately feeds back the angular position of the air damper 6 to the control component 5 and the machine. The machine combines the air intake requirement and issues a control current signal. The analog current acquisition and processing circuit in the control component 5 acquires and processes the control current, drives the motor 1 to complete the functions of rotation direction and rotation speed instruction information, so as to control the opening of the air damper 6 in real time;

[0074] b. An operation instruction is issued on the machine. The device acquires the closing instruction of the air damper 6 collected by the socket 503 in the control component 5. The control board 501 analyzes and processes the discrete quantity signal to realize the closing instruction of the air damper 6, controls the motor 1 to rotate in reverse, drives the air damper 6 to move in the closing direction through the output shaft of the operating mechanism 2. The angular displacement sensor 4 feeds back the signal that the air damper 6 is closed in place to the control board 501 and at the same time feeds it back to the machine through the socket 503. The control board 501 gives an instruction for the motor 1 to stop working. During the whole working process, the angular displacement sensor 4 collects signals in real time, and timely and accurately feeds back the angular position of the air damper 6 to the control component 5 and the machine. The machine combines the air intake requirement and issues a control current signal. The analog current acquisition and processing circuit in the control component 5 acquires and processes the control current, drives the motor 1 to complete the functions of rotation direction and rotation speed instruction information, so as to control the opening of the air damper 6 in real time.

[0075] 2. When the pneumatic mechanism 3 is working, the control board 501 issues an instruction to cut off the power supply of the motor 1, and the motor 1 does not work. At the same time, the worm and worm gear 202 in the operating mechanism 2 is self-locked, locking the sun gear 204 in place. The output force of the pneumatic mechanism 3 outputs a rotational torque through the inner gear ring 206 and the planet carrier 207.

[0076] An operation instruction is issued on the machine. The device controls the two-position two-way solenoid valve 301 in the pneumatic mechanism 3 to be energized through the damper 6 opening instruction collected by the socket 503 in the control component 5. A high-pressure medium passes through the right position of the solenoid valve and enters the right side of the two-position four-way hydraulic directional control valve 302. The hydraulic pressure overcomes its spring force and pushes the spool of the two-position four-way hydraulic directional control valve 302 to move to the left. After the passage is switched to the right position of the two-position four-way hydraulic directional control valve 302, another high-pressure medium passes through the right position of the two-position four-way hydraulic directional control valve 302 and the first check valve 303 and enters the rodless cavity of the actuator. The hydraulic pressure overcomes the spring pre-tightening force and the load force, causing the piston rod to move in the extending direction, pushing the internal gear ring 206 in the gear train of the operating mechanism 2 to rotate through the spur gear 205. The sun gear 204 is locked and immobile, and the planet carrier 207 rotates correspondingly with the planet gear 208, driving the damper 6 to rotate in the opening direction through the output shaft. The medium return oil path passes through the rodless cavity of the actuator, the second speed control valve 309 to adjust the speed, and the two-position four-way hydraulic directional control valve 302 and enters the circuit.

[0077] An operation instruction is issued on the machine. The device controls the two-position two-way solenoid valve 301 in the pneumatic mechanism 3 to be de-energized through the damper 6 closing instruction collected by the socket 503 in the control component 5. Under the action of its spring force, a high-pressure channel is isolated. The spring force of the two-position four-way hydraulic directional control valve 302 pushes the spool to move to the right. After the passage is switched to the left position of the two-position four-way hydraulic directional control valve 302, another high-pressure medium passes through the left position of the two-position four-way hydraulic directional control valve 302 and the second check valve 308 and enters the rod cavity of the actuator, causing the piston rod to move in the retracting direction, pushing the internal gear ring 206 in the gear train of the operating mechanism 2 to rotate in the reverse direction through the spur gear 205. The sun gear 204 is locked and immobile, and the planet carrier 207 rotates correspondingly with the planet gear 208, driving the damper 6 to rotate in the closing direction through the output shaft. The medium return oil path passes through the first speed control valve 304 to adjust the speed and the directional control valve and enters the circuit.

[0078] During the entire working process, the angular displacement sensor 4 collects signals in real time and promptly and accurately feeds back the angular position of the damper 6 to the control component 5 and the machine. The machine combines the intake air volume requirement and issues a control current signal. The analog current acquisition and processing circuit in the control component 5 acquires and processes the control current, driving the motor 1 to complete the command information function, thereby controlling the opening of the damper 6 in real time. Combining the intake air volume requirement, the opening angle of the damper 6 is controlled in real time through the energization and de-energization instructions of the two-position two-way solenoid valve 301.

[0079] In this embodiment, a non-similar dual-redundancy servo device for the aircraft air damper 6 realizes highly reliable control of the aircraft air duct damper 6 by arranging a control mechanism 2 with compatible pneumatic and electric controls in the device, reduces the failure problems caused by similar faults, and greatly improves flight safety. At the same time, the non-similar dual-redundancy device has high integration, light weight, simple control logic, and can use different media as energy sources, and can be applied to other fields, having high practical utilization value.

[0080] As described above, the above are only specific embodiments of the present disclosure, but the protection scope of the present disclosure is not limited thereto. Any changes or substitutions that can be easily thought of by those skilled in the art within the technical scope disclosed by the present disclosure should be covered within the protection scope of the present disclosure. Therefore, the protection scope of the present disclosure should be subject to the protection scope of the claims.

Claims

1. A non-similar dual-redundancy servo device for an aircraft damper, used to control the damper of an aircraft APU, It is characterized in that Including electric motor, operating mechanism, pneumatic mechanism and control components; The motor is controlled by the control assembly to output an electric switch displacement torque for opening and closing the damper; The pneumatic mechanism is used to output a pneumatic switch displacement torque for opening and closing the damper based on an air source or a hydraulic source of the aircraft; The operating mechanism is used to transmit the electric switch displacement torque or the pneumatic switch displacement torque to the damper; Wherein: the operating mechanism includes a worm gear, a sun gear, a planetary gear, a planetary carrier and an inner gear ring; The worm end of the worm gear is arranged in transmission with the motor, and the worm wheel end of the worm gear is arranged in transmission with the sun gear; the planetary gears are at least two groups, and both are meshed with the sun gear; The inner gear ring is meshed with each of the planetary gears based on the inner teeth; the planet carrier is mounted on each of the planetary gears and is also arranged in transmission with the damper; The pneumatic mechanism is arranged to be driven by the inner gear ring; the pneumatic mechanism drives the inner gear ring to perform a lockable rotation coaxially with the sun gear; The pneumatic mechanism includes a two-position two-way solenoid valve, a two-position four-way hydraulic reversing valve and an actuator; The two-position two-way solenoid valve is controlled by the control component and is used to realize the reciprocating movement of the valve core of the two-position four-way hydraulic reversing valve based on the air source or hydraulic source of the aircraft; the two-position four-way hydraulic reversing valve is controlled by the two-position two-way solenoid valve and is used to route the air source or hydraulic source of the aircraft to the actuator cylinder; the actuator cylinder outputs the pneumatic switch displacement torque based on the routed air source or hydraulic source of the aircraft.

2. The servo device according to claim 1, It is characterized in that The actuator comprises an actuator outer cylinder, an actuator spring and an actuator piston rod; One end of the piston rod of the actuating cylinder is a piston and is arranged in the actuating cylinder, and the other end is arranged in a transmission manner with the inner gear ring, and the movement direction is parallel to the axial direction of the actuating cylinder; The actuating cylinder spring is arranged in the outer cylinder of the actuating cylinder, one end of which acts on the inner wall of the actuating cylinder and the other end of which acts on the piston, and the direction of the preload force is parallel to the axial direction of the actuating cylinder.

3. The servo device according to claim 2, It is characterized in that The pneumatic mechanism also includes a first one-way valve and a first speed regulating valve; the first one-way valve and the first speed regulating valve are arranged in parallel, acting between an output end of the two-position four-way hydraulic reversing valve and an input end of the actuator cylinder; the allowed flow direction of the first one-way valve is from the actuator cylinder to the two-position four-way hydraulic reversing valve.

4. The servo device according to claim 1, It is characterized in that The pneumatic mechanism also includes a second one-way valve and a second speed regulating valve; the second one-way valve and the second speed regulating valve are arranged in parallel, acting between the other output end of the two-position four-way hydraulic reversing valve and the other input end of the actuator cylinder; the allowed flow direction of the second one-way valve is from the actuator cylinder to the two-position four-way hydraulic reversing valve.

5. The servo device according to claim 1, It is characterized in that The motor is driven based on a reduction spur gear train with respect to the worm end of the worm and worm gear.

6. The servo device according to claim 2, wherein, external teeth are provided on the internal gear ring; the piston rod is driven based on spur gears with respect to the internal gear ring; the spur gears mesh with the external teeth of the internal gear ring.

7. The servo device according to claim 1, wherein, the servo device further includes a displacement sensor; the displacement sensor is used to detect the opening amount of the air damper; the detection result of the displacement sensor is output to the control component.

8. The servo device according to claim 1, wherein, the servo device further includes a filter; the filter is electrically connected to the control component and is used to realize the transmission of the discrete signals of the aircraft to the control component.

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