CN109625249B - Locking device for external electromechanical actuator - Google Patents
Locking device for external electromechanical actuator Download PDFInfo
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- CN109625249B CN109625249B CN201910070793.7A CN201910070793A CN109625249B CN 109625249 B CN109625249 B CN 109625249B CN 201910070793 A CN201910070793 A CN 201910070793A CN 109625249 B CN109625249 B CN 109625249B
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- electromechanical actuator
- locking device
- permanent magnet
- reduction box
- gear reduction
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C13/00—Control systems or transmitting systems for actuating flying-control surfaces, lift-increasing flaps, air brakes, or spoilers
- B64C13/24—Transmitting means
- B64C13/38—Transmitting means with power amplification
- B64C13/50—Transmitting means with power amplification using electrical energy
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- Engineering & Computer Science (AREA)
- Automation & Control Theory (AREA)
- Aviation & Aerospace Engineering (AREA)
- Connection Of Motors, Electrical Generators, Mechanical Devices, And The Like (AREA)
Abstract
The invention provides a locking device for an external electromechanical actuator, wherein an actuating rod at one end of the electromechanical actuator is hinged with an air rudder rocker arm through a lower support lug, the other end of the electromechanical actuator is connected with a gear reduction box, a permanent magnet synchronous motor is arranged beside the electromechanical actuator, and a motor shaft of the permanent magnet synchronous motor penetrates through the gear reduction box and is connected to the locking device; the permanent magnet synchronous motor drives a ball screw pair in the electromechanical actuator to move through the gear reduction box so as to realize linear extension of the actuating rod, further realize that the actuating rod drives the air rudder rocker arm to rotate a control surface of the aircraft, and the locking device realizes the locking function of the control surface. The locking device is used for applying locking torque to a motor shaft of the electromechanical actuator, the working modes of the locking device are power-on unlocking and power-off locking, so that when the control surface on the aircraft is subjected to external interference such as impact or vibration, the control surface can be kept at a corresponding position by the electromechanical actuator without being powered on.
Description
Technical Field
The invention relates to a locking device for an external electromechanical actuator, which is suitable for locking a control surface in an aircraft.
Background
In the prior art, in the on-hook cruising process of an aircraft of a certain type, the tail vane of the aircraft needs to be prevented from swinging under the environmental conditions of airflow disturbance, aircraft vibration and the like, and in the process, the disturbance torque of the control surface can reach 250 Nm. However, since the space size and weight inside the aircraft are limited, it is difficult to directly implement the locking function on the rudder shaft by mechanical means. Therefore, there is a need for a properly designed transmission mechanism that sets the gear ratio to reduce the required locking torque to an acceptable level.
At present, the only transmission mechanism on the rudder shaft is an electromechanical actuator, and the function of the electromechanical actuator is to drive the rudder surface to rotate according to instructions after the electromechanical actuator is electrified. The speed reduction and the torque increase are processes from the motor of the electromechanical actuator to the rudder shaft of the aircraft. Therefore, when the electromechanical actuator is not electrified, a corresponding locking device is arranged on a motor shaft of the electromechanical actuator so as to provide the required locking torque of the control surface after speed reduction and torque increase.
Disclosure of Invention
Technical problem to be solved
In order to meet the requirements in the prior art, the invention provides a locking device for an external electromechanical actuator, which is used for applying a locking torque to a motor shaft of the electromechanical actuator, and the working modes of the locking device are power-on unlocking and power-off unlocking, so that when the control surface on an aircraft is subjected to external interference such as impact or vibration, the control surface can be kept at a corresponding position by the electromechanical actuator without being electrified.
(II) technical scheme
A locking device for an external electromechanical actuator is characterized in that an actuating rod at one end of the electromechanical actuator is hinged with an air rudder rocker arm through a lower support lug, the other end of the electromechanical actuator is connected with a gear reduction box, a permanent magnet synchronous motor is arranged beside the electromechanical actuator, and a motor shaft of the permanent magnet synchronous motor penetrates through the gear reduction box to be connected to the locking device; the permanent magnet synchronous motor drives a ball screw pair in the electromechanical actuator to move through a gear reduction box so as to realize linear extension and retraction of the actuating rod, and further realize that the actuating rod drives the air rudder rocker arm to rotate a control surface of the aircraft; an upper lug fixedly connected with the gear reduction box is arranged at a position opposite to the locking device, and the upper lug is fixedly hinged to the ring frame; the locking device realizes the locking function of the control surface.
The articulated shaft of lower journal stirrup with the articulated shaft space of upper journal stirrup is perpendicular.
The ball screw pair is specifically as follows: an output shaft of the gear reduction box drives a ball screw to rotate, and a nut on the ball screw is fixed on the actuating rod.
The locking device comprises an elastic piece, a coil, a permanent magnet, a dynamic friction disc and a shaft connecting disc; the coils are distributed annularly, the permanent magnets surround the coils and are also distributed annularly, and the two rings are coaxial; the permanent magnet is fixed to the gear reduction box, and the motor shaft penetrates out of the two annular axes; a connecting shaft connecting plate is fixed at the tail end of the motor shaft, and a dynamic friction disc is sleeved on the motor shaft; when the locking device is electrified, an electromagnetic field generated by the coil and a magnetic field generated by the permanent magnet are mutually offset, the dynamic friction disc is tightly attached to the shaft connecting disc, the elastic piece is in an initial state, a gap is formed between the dynamic friction disc and the permanent magnet, and the locking device is in an unlocking state; when the power is cut off, the dynamic friction disc and the permanent magnet are attracted by magnetic force and are tightly attached, the elastic piece is in a stretching state, and the locking device is in a locking state.
A limiting bump is arranged on the end face, facing the dynamic friction disc, of the shaft connecting disc, and a through hole is formed in the position, opposite to the limiting bump, of the dynamic friction disc; in the unlocking state, the limiting lug completely enters the through hole; and when the lock is in a locking state, the limiting lug is separated from the through hole.
The elastic piece is an arch spring.
And when the power is on, 24V direct current is introduced into the coil.
The motor shaft is fixedly connected with the shaft connecting disc through a plurality of fastening screws.
The number of the fastening screws is 3.
A shell is arranged outside the locking device and fixedly connected to the gear reduction box.
(III) advantageous effects
The locking device for the external electromechanical actuator is used for exerting locking torque on a motor shaft of the electromechanical actuator, and the working modes of the locking device are power-on unlocking and power-off unlocking, so that when a control surface on an aircraft is subjected to external interference such as impact or vibration, the control surface can be kept at a corresponding position by the electromechanical actuator without being electrified. In addition, the hinge shaft space of the lower support lug and the hinge shaft space of the upper support lug are vertical, so that the installation stability and the locking stability of the locking device are ensured; the shell of the locking device is dustproof and anti-pollution, the working stability of the locking device is ensured, and the shell and the gear reduction box are separately installed, so that the operation is convenient, the installation of the locking device is simplified, and the gap of the locking device is convenient to adjust.
Drawings
FIG. 1 is a general installation view of a lock assembly for an external electromechanical actuator in accordance with the present invention.
FIG. 2 is a perspective view of a locking device for an external electromechanical actuator in accordance with the present invention.
Fig. 3 is a schematic diagram of an unlocked state and a locked state of the locking device.
In the figure, 1-a control surface, 2-an air rudder rocker arm, 3-a lower lug, 4-an electromechanical actuator, 5-an electromagnetic lock, 6-an upper lug, 7-an actuating rod, 8-a permanent magnet synchronous motor, 9-a ring frame, 10-a gear reduction box, 11-a motor shaft, 12-an elastic part, 13-a coil, 14-a permanent magnet, 15-a gap, 16-a dynamic friction disk, 17-a shaft connecting disk and 18-a limit lug.
Detailed Description
Referring to fig. 1-2, the invention provides a locking device for an external electromechanical actuator, wherein an actuating rod 7 at one end of an electromechanical actuator 4 is hinged with an air rudder rocker arm 2 through a lower lug 3, the other end of the electromechanical actuator 4 is connected with a gear reduction box 10, a permanent magnet synchronous motor 8 is arranged beside the electromechanical actuator 4, and a motor shaft 11 of the permanent magnet synchronous motor 8 penetrates through the gear reduction box 10 to be connected to a locking device 5; the permanent magnet synchronous motor 8 drives a ball screw pair in the electromechanical actuator 4 to move through a gear reduction box 10 so as to realize linear extension and retraction of the actuating rod 7, and further realize that the actuating rod 7 drives the air rudder rocker arm 2 to rotate the control surface 1 of the aircraft; an upper lug 6 fixedly connected with the gear reduction box 10 is arranged at a position opposite to the locking device 5, and the upper lug 6 is fixedly hinged to a ring frame 9; the locking device 5 realizes the locking function of the control surface 1.
The articulated shaft of lower journal stirrup 3 with the articulated shaft space of upper journal stirrup 6 is perpendicular.
The ball screw pair is specifically as follows: an output shaft of the gear reduction box 10 drives a ball screw to rotate, and a nut on the ball screw is fixed on the actuating rod 7.
Referring to fig. 3, the locking device 5 includes an elastic member 12, a coil 13, a permanent magnet 14, a dynamic friction disk 16, a shaft connecting disk 17; the coil 13 is distributed annularly, the permanent magnet 14 surrounds the coil 13 and is also distributed annularly, and the two rings are coaxial; the permanent magnet 14 is fixed to the gear reduction box 10, and the motor shaft 11 penetrates out of two annular axes; a connecting shaft connecting plate 17 is fixed at the tail end of the motor shaft 11, and a dynamic friction disc 16 is further sleeved on the motor shaft 11; when the power is on, the electromagnetic field generated by the coil 13 and the magnetic field generated by the permanent magnet 14 are mutually offset, the dynamic friction disc 16 is tightly attached to the shaft connecting disc 17, the elastic piece 12 is in an initial state, a gap 15 is formed between the dynamic friction disc 16 and the permanent magnet 14, and the locking device 5 is in an unlocking state; when the power is cut off, the dynamic friction disc 16 and the permanent magnet 14 are attracted by magnetic force and are tightly attached, the elastic piece 12 is in a stretching state, and the locking device 5 is in a locking state.
A limit lug 18 is arranged on the end surface of the shaft connecting plate 17 facing the dynamic friction disc 16, and a through hole is arranged at the position of the dynamic friction disc 16 opposite to the limit lug 18; in the unlocking state, the limiting lug 18 completely enters the through hole; in the locked state, the limiting lug 18 is separated from the through hole.
The elastic member 12 is a bow spring.
When the power is supplied, 24V direct current is introduced into the coil 13.
The motor shaft 11 is fixedly connected with the shaft connecting disc 17 through a plurality of fastening screws.
The number of the fastening screws is 3.
A shell is arranged outside the locking device 5 and fixedly connected to the gear reduction box 10.
Claims (8)
1. A locking device for an external electromechanical actuator is characterized in that an actuating rod at one end of the electromechanical actuator is hinged with an air rudder rocker arm through a lower support lug, the other end of the electromechanical actuator is connected with a gear reduction box, a permanent magnet synchronous motor is arranged beside the electromechanical actuator, and a motor shaft of the permanent magnet synchronous motor penetrates through the gear reduction box and is connected to the locking device; the permanent magnet synchronous motor drives a ball screw pair in the electromechanical actuator to move through a gear reduction box so as to realize linear extension and retraction of the actuating rod, and further realize that the actuating rod drives the air rudder rocker arm to rotate a control surface of the aircraft; an upper lug fixedly connected with the gear reduction box is arranged at a position opposite to the locking device, and the upper lug is fixedly hinged to the ring frame; the locking device realizes the locking function of the control surface;
the locking device comprises an elastic piece, a coil, a permanent magnet, a dynamic friction disc and a shaft connecting disc; the coils are distributed annularly, the permanent magnets surround the coils and are also distributed annularly, and the two rings are coaxial; the permanent magnet is fixed to the gear reduction box, and the motor shaft penetrates out of the two annular axes; a connecting shaft connecting plate is fixed at the tail end of the motor shaft, and a dynamic friction disc is sleeved on the motor shaft; when the locking device is electrified, an electromagnetic field generated by the coil and a magnetic field generated by the permanent magnet are mutually offset, the dynamic friction disc is tightly attached to the shaft connecting disc, the elastic piece is in an initial state, a gap is formed between the dynamic friction disc and the permanent magnet, and the locking device is in an unlocking state; when the power is cut off, the dynamic friction disc and the permanent magnet are attracted by magnetic force and are tightly attached, the elastic piece is in a stretching state, and the locking device is in a locking state;
a limiting bump is arranged on the end face, facing the dynamic friction disc, of the shaft connecting disc, and a through hole is formed in the position, opposite to the limiting bump, of the dynamic friction disc; in the unlocking state, the limiting lug completely enters the through hole; and when the lock is in a locking state, the limiting lug is separated from the through hole.
2. The lock assembly for an external electromechanical actuator of claim 1 wherein the hinge axis of said lower leg is spaced perpendicular to the hinge axis of said upper leg.
3. The lock assembly of claim 1, wherein the ball screw assembly is embodied as: an output shaft of the gear reduction box drives a ball screw to rotate, and a nut on the ball screw is fixed on the actuating rod.
4. The lock assembly of claim 1, wherein the resilient member is a bow spring.
5. The lock-out mechanism for an external electromechanical actuator of claim 4, wherein when energized, 24V DC is applied to said coil.
6. The lock assembly of claim 4, wherein the motor shaft is fixedly coupled to the shaft coupling plate by a plurality of fastening screws.
7. The lock assembly of claim 6, wherein the number of fastening screws is 3.
8. The lock-out mechanism for an external electromechanical actuator of claim 1, wherein a housing is provided external to the lock-out mechanism, the housing being fixedly attached to the gear reducer.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910070793.7A CN109625249B (en) | 2019-01-25 | 2019-01-25 | Locking device for external electromechanical actuator |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910070793.7A CN109625249B (en) | 2019-01-25 | 2019-01-25 | Locking device for external electromechanical actuator |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN109625249A CN109625249A (en) | 2019-04-16 |
| CN109625249B true CN109625249B (en) | 2021-11-02 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201910070793.7A Active CN109625249B (en) | 2019-01-25 | 2019-01-25 | Locking device for external electromechanical actuator |
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| CN (1) | CN109625249B (en) |
Families Citing this family (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112173070B (en) * | 2020-09-25 | 2022-02-08 | 兰州万里航空机电有限责任公司 | Electric control surface lock mechanism |
| CN114013632A (en) * | 2021-11-12 | 2022-02-08 | 四川凌峰航空液压机械有限公司 | Redundancy emergency electromechanical actuator |
| CN115694055A (en) * | 2022-09-19 | 2023-02-03 | 亿航智能设备（广州）有限公司 | Linear actuator integrated with gear vernier encoder and control method thereof |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104590548A (en) * | 2013-10-30 | 2015-05-06 | 北京精密机电控制设备研究所 | Steering engine zero-position locking mechanism |
| CN105634191A (en) * | 2014-10-31 | 2016-06-01 | 北京精密机电控制设备研究所 | Modular parallel type electromechanical actuator |
| CN108167268A (en) * | 2017-12-20 | 2018-06-15 | 中国航发长春控制科技有限公司 | A kind of actuator locks modular structure |
Family Cites Families (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP2837556B1 (en) * | 2013-08-12 | 2016-04-27 | Airbus Defence and Space GmbH | Pneumatically activated decoupling device |
| CN103625638B (en) * | 2013-12-13 | 2016-01-20 | 北京航空航天大学 | A kind of blocking device realizing rotation steering wheel desired location and cut off self-lock |
| FR3053956B1 (en) * | 2016-07-18 | 2019-06-28 | Airbus Operations | CROCODILE GOVERNMENT FOR AIRCRAFT |
-
2019
- 2019-01-25 CN CN201910070793.7A patent/CN109625249B/en active Active
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104590548A (en) * | 2013-10-30 | 2015-05-06 | 北京精密机电控制设备研究所 | Steering engine zero-position locking mechanism |
| CN105634191A (en) * | 2014-10-31 | 2016-06-01 | 北京精密机电控制设备研究所 | Modular parallel type electromechanical actuator |
| CN108167268A (en) * | 2017-12-20 | 2018-06-15 | 中国航发长春控制科技有限公司 | A kind of actuator locks modular structure |
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| Publication number | Publication date |
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| CN109625249A (en) | 2019-04-16 |
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