CN210912900U - Rotary actuating mechanism of airplane oil receiving device - Google Patents
Rotary actuating mechanism of airplane oil receiving device Download PDFInfo
- Publication number
- CN210912900U CN210912900U CN201922038818.3U CN201922038818U CN210912900U CN 210912900 U CN210912900 U CN 210912900U CN 201922038818 U CN201922038818 U CN 201922038818U CN 210912900 U CN210912900 U CN 210912900U
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- China
- Prior art keywords
- motor
- brake
- spline
- receiving device
- shaft
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- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Expired - Fee Related
Links
- 230000007246 mechanism Effects 0.000 title description 4
- 230000009467 reduction Effects 0.000 claims abstract description 10
- 239000003638 chemical reducing agent Substances 0.000 claims description 19
- 238000006073 displacement reaction Methods 0.000 claims description 11
- 238000009434 installation Methods 0.000 abstract description 2
- 239000003921 oil Substances 0.000 description 18
- 230000003321 amplification Effects 0.000 description 2
- 239000000295 fuel oil Substances 0.000 description 2
- 230000010354 integration Effects 0.000 description 2
- 239000000346 nonvolatile oil Substances 0.000 description 2
- 238000003199 nucleic acid amplification method Methods 0.000 description 2
- 230000005856 abnormality Effects 0.000 description 1
- 230000002411 adverse Effects 0.000 description 1
- 230000004075 alteration Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
- 239000013585 weight reducing agent Substances 0.000 description 1
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- Connection Of Motors, Electrical Generators, Mechanical Devices, And The Like (AREA)
Abstract
The utility model discloses an aircraft oily device rotary actuator, include motor, stopper and the reduction gear that sets gradually from the right side to a left side, motor, stopper pass through bolt mounting with the reduction gear and be a body structure after together, the stopper includes the stopper body, the stopper body includes yoke and armature, install through the bolt between yoke and the armature to coil, spring, brake disc are installed respectively to inside between the two, the inboard of brake disc is equipped with the spline, the axle outer wall of motor and the axle center installation of spline to it wears out behind the axle center of spline and the hub connection of reduction gear. The utility model discloses, the operation of machine controller driving motor, the rethread reduction gear realizes that the rotational speed reduces and the torque enlargies, and direct drive receives oil pipe's rotation, realizes receiving the action of receiving of oil device.
Description
Technical Field
The utility model relates to an electric drive rotary actuator technical field specifically is an aircraft receives rotatory actuating mechanism of oil installation.
Background
Although the existing retractable oil receiving device on the airplane solves the adverse effect of the fixed oil receiving device, a linear electromechanical actuating system is usually adopted, so that the defects of high requirement on working space, large volume and weight and the like are overcome, and the weight reduction design of the airplane is not facilitated.
SUMMERY OF THE UTILITY MODEL
An object of the utility model is to provide an aircraft is received oily device and is rotated actuating mechanism realizes fuel oil system's miniaturization, lightweight and intelligent design, has solved the problem of proposing among the background art.
In order to achieve the above object, the utility model provides a following technical scheme: including motor, stopper and the reduction gear that sets gradually from right side to left side, motor, stopper pass through bolt mounting and are a body structure after together with the reduction gear.
The brake comprises a brake body, the brake body comprises a magnetic yoke and an armature, the magnetic yoke and the armature are installed through bolts, a coil, a spring and a brake disc are installed inside the magnetic yoke and the armature respectively, a spline is arranged on the inner side of the brake disc, the outer wall of a shaft of the motor is installed with the shaft center of the spline, and the outer wall of the shaft of the motor penetrates out of the shaft center of the spline and then is connected with the shaft of the speed reducer.
Preferably, an oil receiving pipe is fixed on the other shaft in the speed reducer, which is different from the position of the motor shaft.
Preferably, the motor incorporates a HALL sensor.
Preferably, an angular displacement sensor is arranged in the speed reducer.
Preferably, the brake system further comprises a motor controller, wherein the motor controller receives the motor HALL signal measured by the HALL sensor and the angular displacement signal measured by the angular displacement sensor, and sends a brake control signal to the brake.
Compared with the prior art, the beneficial effects of the utility model are as follows: the utility model aims at following the development trend of modern aircraft multi-electrification, intellectuality, integration and miniaturization, inventing a retractable oil receiving device electric drive rotary actuator who is applicable to modern aircraft fuel oil system to replace fixed oil receiving device and the straight-line retractable electromechanical drive oil receiving device on the traditional aircraft. The main innovation points are as follows:
(1) the rotary speed reducer is adopted to directly drive the oil receiving device, so that the oil receiving device has a simple structure;
(2) the working space of the oil receiving device is small, and the integration level is high;
(3) the actuator is light in weight.
Drawings
Fig. 1 is a schematic structural view of a cross-sectional view of a rear front view of the motor, the brake and the reducer of the present invention;
fig. 2 is a schematic structural view of a cross-sectional view of a front view of the brake of the present invention;
fig. 3 is a control block diagram of the motor controller of the present invention.
In the figure: 1-motor, 2-brake, 21-brake body, 22-spline, 23-magnetic yoke, 24-coil, 25-spring, 26-armature, 27-brake disc, 3-speed reducer.
Detailed Description
The technical solutions in the embodiments of the present invention will be described clearly and completely with reference to the accompanying drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only some embodiments of the present invention, not all embodiments. Based on the embodiments in the present invention, all other embodiments obtained by a person skilled in the art without creative work belong to the protection scope of the present invention.
Referring to fig. 1 to 3, the present invention provides a technical solution: including motor 1, stopper 2 and the reduction gear 3 that sets gradually from right side to left side, motor 1, stopper 2 are an organic whole structure after passing through the bolt mounting together with reduction gear 3, so the integrated level is high, small, light in weight.
The brake 2 comprises a brake body 21, the brake body 21 comprises a magnetic yoke 23 and an armature 26, the magnetic yoke 23 and the armature 26 are installed through bolts, a coil 24, a spring 25 and a brake disc 27 are respectively installed inside the magnetic yoke 23 and the armature 26, a spline 22 is arranged on the inner side of the brake disc 27, the outer wall of the shaft of the motor 1 is installed with the shaft center of the spline 22, penetrates through the shaft center of the spline 22 and then is connected with the shaft of the speed reducer 3.
An oil receiving pipe is fixed on the other shaft in the speed reducer 3, which is different from the position of the shaft of the motor 1.
The motor 1 incorporates a HALL sensor for detecting a HALL signal of the motor 1.
An angular displacement sensor is arranged in the speed reducer 3 and used for detecting an angular displacement signal of the speed reducer 3.
The controller of the motor 1 receives the HALL signal of the motor 1 measured by the HALL sensor and the angular displacement signal measured by the angular displacement sensor, and sends a control signal of the brake 2 to the brake 2.
Further explanation for the above is as follows:
the motor controller outputs motor phase current and drives the motor to run according to control signals of the upper computer by adopting a PWM control technology, the rotating speed and the torque output by the motor are reduced by the speed reducer 3, and the torque is amplified. The rotary driving disc operating arm on the speed reducer 3 drives the oil receiving pipe to rotate, and the oil receiving device is retracted and extended.
Motor controller functions: receiving command information sent by an upper computer, driving the motor 1 to rotate forwards and backwards, simultaneously carrying out closed-loop control on the rotating speed and current of the motor 1, and implementing fault protection when abnormality occurs; and detecting a rotation angle displacement signal (RVDT) on the speed reducer in real time, controlling a brake to perform braking operation after the oil receiving device rotates to the position, and locking the oil receiving device.
Permanent magnet brushless motor (containing HALL sensor): under the drive of the motor controller, the forward rotation and the reverse rotation are realized, and the rotating speed and the torque are output.
A brake: before the motor needs to be controlled to operate, the motor controller outputs a brake control signal to realize the brake release of the brake to the shaft of the motor, and when the roller screw pulls the weapon hanger to hoist or place in place, the controller outputs the brake control signal to brake the shaft of the motor in an embracing way to realize the locking of the hanger.
Speed reducer: the rotating speed of the motor is reduced, meanwhile, the amplification of the output torque is realized, and the rotating speed and the torque are output to the oil receiving pipe.
The working principle is as follows: when the oil receiving device is used, the motor controller drives the motor 1 to operate, then the rotating speed reduction and the torque amplification are realized through the speed reducer 3, the rotation of the oil receiving pipe is directly driven, and the retraction and release actions of the oil receiving device are realized.
Although embodiments of the present invention have been shown and described, it will be appreciated by those skilled in the art that changes, modifications, substitutions and alterations can be made in these embodiments without departing from the principles and spirit of the invention, the scope of which is defined in the appended claims and their equivalents.
Claims (5)
1. The utility model provides an aircraft oily device rotary actuator, includes motor (1), stopper (2) and reduction gear (3) that set gradually from right side to left, its characterized in that: the motor (1), the brake (2) and the speed reducer (3) are arranged together through bolts and then form an integral structure;
the brake (2) comprises a brake body (21), the brake body (21) comprises a magnetic yoke (23) and an armature (26), the magnetic yoke (23) and the armature (26) are installed through bolts, a coil (24), a spring (25) and a brake disc (27) are installed inside the magnetic yoke (23) and the armature (26) respectively, a spline (22) is arranged on the inner side of the brake disc (27), the outer wall of the shaft of the motor (1) is installed on the shaft center of the spline (22), and the outer wall penetrates through the shaft center of the spline (22) and then is connected with the shaft of the speed reducer (3).
2. The rotary actuator of an aircraft oil-receiving device according to claim 1, characterized in that: an oil receiving pipe is fixed on the other shaft in the speed reducer (3) which is different from the position of the shaft of the motor (1).
3. The rotary actuator of an aircraft oil-receiving device according to claim 1, characterized in that: the motor (1) is internally provided with a HALL sensor.
4. The rotary actuator of an aircraft oil-receiving device according to claim 1, characterized in that: an angular displacement sensor is arranged in the speed reducer (3).
5. An aircraft oil-receiving device rotary actuator according to claim 3, characterized in that: the brake system is characterized by further comprising a motor (1) controller, wherein the motor (1) controller receives a motor (1) HALL signal measured by the HALL sensor and an angular displacement signal measured by the angular displacement sensor and sends a brake (2) control signal to the brake (2).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201922038818.3U CN210912900U (en) | 2019-11-23 | 2019-11-23 | Rotary actuating mechanism of airplane oil receiving device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201922038818.3U CN210912900U (en) | 2019-11-23 | 2019-11-23 | Rotary actuating mechanism of airplane oil receiving device |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN210912900U true CN210912900U (en) | 2020-07-03 |
Family
ID=71368666
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201922038818.3U Expired - Fee Related CN210912900U (en) | 2019-11-23 | 2019-11-23 | Rotary actuating mechanism of airplane oil receiving device |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN210912900U (en) |
-
2019
- 2019-11-23 CN CN201922038818.3U patent/CN210912900U/en not_active Expired - Fee Related
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20200703 |