CN214776531U - Electric brake device for helicopter - Google Patents
Electric brake device for helicopter Download PDFInfo
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- CN214776531U CN214776531U CN202021024213.5U CN202021024213U CN214776531U CN 214776531 U CN214776531 U CN 214776531U CN 202021024213 U CN202021024213 U CN 202021024213U CN 214776531 U CN214776531 U CN 214776531U
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Abstract
The utility model belongs to the technical field of helicopter brake, and discloses an electric brake device for a helicopter, which comprises a motor, a gear set, a brake disc, a first brake pad, a second brake pad and a lead screw nut; the motor drives the screw nut through the gear set, the screw nut is connected with the first brake block, and the brake disc is arranged between the first brake block and the second brake block. The device can be used for a brake system of a helicopter, particularly a brake system of an unmanned helicopter, the weight and the installation space of products are obviously reduced, the brake fault diagnosis capability is improved by utilizing the controller assembly, the maintenance and repair time is short, and the maintenance cost is low.
Description
Technical Field
The utility model belongs to the technical field of the helicopter brake, a helicopter electric brake device is related to, specifically an electric brake device for helicopter.
Background
At present, the brake devices used by domestic helicopters have three types, namely hydraulic drive, pneumatic drive and mechanical drive. The hydraulic driving brake device inputs brake pressure to a hydraulic piston cavity of the brake device through a brake system, a piston moves forwards together with a screw cap under the action of the brake pressure, a return spring is compressed to enable a static disc and a movable disc to be axially compressed, and friction torque is generated between the static disc and the rotating movable disc to brake an airplane wheel assembly so as to brake an airplane. The pneumatic driving brake device is generally used as an emergency brake, the working principle is consistent with that of hydraulic driving, and only a brake medium is replaced by compressed gas. The mechanical driving brake device utilizes a mechanical structure to extrude a movable disc to reach a certain static moment index so as to lock the airplane wheel.
However, with the development of full-electric automation and high integration of the unmanned helicopter, the electric unmanned helicopter is more convenient to brake by adopting electricity as a power source of a brake system.
SUMMERY OF THE UTILITY MODEL
The utility model provides an electric brake device for helicopter replaces current mechanical control formula and hydraulic pressure and actuates the mechanism, realizes the mechanism of helicopter brake braking action.
The technical scheme of the utility model is that: an electric brake device for a helicopter comprises a motor, a gear set, a brake disc, a first brake pad, a second brake pad and a lead screw nut; the motor drives a screw rod in a screw nut to rotate through a gear set, the nut in the screw nut is connected with a first brake pad, and a brake disc is arranged between the first brake pad and a second brake pad.
Furthermore, the gear set comprises a speed reducer, a primary gear and a secondary gear, wherein the primary gear is a pinion, the secondary gear is a gearwheel, the output shaft of the motor is connected with the input shaft of the speed reducer, the output shaft of the speed reducer is connected with the primary gear, the primary gear is connected with the secondary gear in a gear-to-gear manner, and the secondary gear is connected with a screw rod in a screw nut in a shaft-to-shaft manner.
Furthermore, a needle bearing is arranged at the joint of the secondary gear and the screw rod in the screw rod nut.
Further, the speed reducer is a planetary gear speed reducer.
Alternatively, the speed reducer is a ramp gear speed reduction mechanism.
Further, the motor is a high-speed, low-torque and low-power brushless DC motor.
Furthermore, the brake device also comprises a brake shell, wherein the motor, the gear set, the brake disc, the first brake pad, the second brake pad and the screw nut are arranged in the brake shell, and the outer side of the second brake pad is abutted against the brake shell.
The brake device is characterized by also comprising a controller assembly, wherein the controller assembly is connected with and controls the motor, when the brake device performs a braking action, the controller assembly controls the motor to rotate forwards, and the output of small torque and high rotating speed of the motor after passing through the gear set is changed into the output of large torque and low rotating speed to drive the screw rod on the screw rod nut to rotate, so that the nut on the screw rod nut generates linear motion, and the first brake pad is pushed to press the brake disc to realize braking; when the brake is released, the controller assembly controls the motor to rotate reversely, the output of small torque and high rotating speed of the motor after passing through the gear set is changed into the output of large torque and low rotating speed to drive the screw rod on the screw rod nut to rotate, so that the nut on the screw rod nut generates reverse linear motion, the first brake pad and the brake disc are released, and the brake is released.
The brake further comprises a force sensor, and the force sensor is arranged between the second brake pad and the brake shell. For measuring the braking force.
Still include hall sensor, hall sensor connects lead screw nut. For measuring the amount of rectilinear motion of the lead screw nut.
The force sensor and the Hall sensor are connected with the controller assembly, and the controller assembly judges the braking state through data transmitted by the force sensor and the Hall sensor.
The utility model has the advantages that:
1. compared with a hydraulic brake system, the helicopter electric brake of the application avoids the problem of faults caused by leakage of hydraulic oil;
2. the weight and the installation space of the product are obviously reduced;
3. the brake fault diagnosis capability is improved by utilizing the controller assembly;
4. short maintenance time and low maintenance cost.
Drawings
Fig. 1 is a schematic structural diagram of an embodiment of the present invention;
fig. 2 is a functional block diagram of an embodiment of the present invention;
fig. 3 is a schematic diagram of the mechanism of the embodiment of the present invention;
the brake comprises a motor 1, a gear set 2, a brake disc 3, a first brake pad 4, a second brake pad 5, a lead screw nut 7, a brake shell 8, a controller assembly 9, a force sensor 10 and a Hall sensor 10.
Detailed Description
This section is an embodiment of the present invention for explaining and explaining the technical solution of the present invention.
An electric brake device for a helicopter comprises a motor 1, a gear set 2, a brake disc 3, a first brake pad 4, a second brake pad 5 and a lead screw nut 6; the motor 1 drives a screw rod in a screw nut 6 to rotate through a gear set 2, the nut in the screw nut 6 is connected with a first brake block 4, a brake disc 3 is arranged between the first brake block 4 and a second brake block 5, the components are arranged in a brake shell 7, the outer side of the second brake block 5 abuts against the brake shell 7, and the brake shell 7 provides bearing force for the second brake block 5.
The gear set 2 specifically comprises a speed reducer, a primary gear and a secondary gear, wherein the primary gear is a pinion, the secondary gear is a gearwheel, namely the diameter of the primary gear is smaller than that of the secondary gear, the difference proportion is calculated according to specific braking torque, an output shaft of a motor is in shaft connection with an input shaft of the speed reducer, an output shaft of the speed reducer is in shaft connection with the primary gear, the primary gear is in gear connection with the secondary gear, the secondary gear is in shaft connection with a screw rod in a screw nut 6, and a needle bearing is arranged at the joint of the secondary gear and the screw rod in the screw nut 6.
The speed reducer can be a planetary gear speed reducer or a bevel gear speed reducing mechanism.
The motor 1 is a high-speed, low-torque and low-power brushless DC motor.
The brake device is also provided with a controller component 8, the controller component 8 is connected with and controls the motor 1, when the brake action is implemented, the controller component 8 controls the motor to rotate forwards, the small torque and high rotating speed output of the motor after passing through the gear set is changed into the large torque and low rotating speed output to drive the screw rod on the screw rod nut 6 to rotate, so that the nut on the screw rod nut 6 generates linear motion, and the first brake block 4 is pushed to compress the brake disc 3 to realize the brake; when the brake releasing action is implemented, the controller component 8 controls the motor to reversely rotate, the output of small torque and high rotating speed of the motor after passing through the gear set is changed into the output of large torque and low rotating speed, so as to drive the screw rod on the screw rod nut 6 to rotate, the nut on the screw rod nut 6 generates reverse linear motion, the first brake block 4 and the brake disc 3 are released, and the brake releasing is realized.
The brake further comprises a force sensor 9 and a Hall sensor 10, wherein the force sensor 9 is arranged between the second brake pad 5 and the brake shell and used for measuring the brake force. The hall sensor 10 is connected to the lead screw nut 6, and is used for measuring the amount of rectilinear motion of the lead screw nut 6. The force sensor 9 and the Hall sensor 10 are connected with the controller assembly 8, and the controller assembly 8 judges the braking state through data transmitted by the force sensor 9 and the Hall sensor 10.
Another embodiment of the present invention is described below with reference to the drawings.
The electromechanical actuating brake device comprises a brake shell 7, a motor 1, a gear set 2, a screw nut 6, a brake disc 4, a first brake pad 4, a second brake pad 5, a force sensor 9, a Hall sensor 10 and other parts and components, and is shown in figure 3.
The functional block diagram of the electromechanical brake device is shown in fig. 2 below, and the mechanism principle is shown in fig. 3. The braking action of the brake is as follows: the motor 1 rotates forwards and is decelerated through the planetary reducer, and then is steered through the gear set 2, so that the output of small torque and high rotating speed of the motor is changed into the output of large torque and low rotating speed to drive the screw rod to rotate, a nut on the screw rod generates linear motion, and the brake disc 3 is pressed by pushing the first brake block 4 to realize the brake function; and (3) brake release action: the motor 1 rotates reversely to drive the planetary reducer to decelerate and rotate reversely, and then the planetary reducer rotates through the gear set 2, so that the output of small torque and high rotating speed of the motor is changed into the output of large torque and low rotating speed to drive the screw rod to rotate, the nut on the screw rod generates reverse linear motion, and the first brake block 4 and the brake disc 3 are loosened to realize the brake loosening function.
Other key design points of the present application are as follows:
1. structural design of mechanism
The structural design of the electromechanical actuation brake device has three main problems, and a the layout and the installation space of the electromechanical actuation brake device are main constraint conditions of the electromechanical actuation brake device, because the installation space of the electromechanical actuation brake device is larger than the installation space of a mechanical control mechanism and a hydraulic piston mechanism; b, when a rolling screw pair and a gear set are selected in the design of the electromechanical actuating brake device, the electromechanical actuating brake device is required to have a reasonable transmission ratio and higher transmission efficiency, and the transmission efficiency of the electromechanical actuating brake device directly influences the control mode and efficiency of braking; and c, the quality of the motor directly influences the performance of the whole electromechanical actuating brake device.
A planetary gear speed reducing mechanism with high space utilization rate is selected for solving the problem of installation space, and a group of large gears (namely secondary gears) and a group of small gears (namely primary gears) are designed through multiple optimization analysis in favor of layout; in order to improve the working efficiency of the mechanism, a lead screw nut with high transmission efficiency and a thrust bearing are adopted; in order to improve the quick response of the mechanism, a high-speed, small-torque and low-power direct-current brushless motor is adopted.
2. How to avoid thermal influence of temperature field and heat conduction on force sensor
The force sensor is sensitive to temperature change, the use temperature range of the force sensor is-40 ℃ to 70 ℃, and the storage temperature is-45 ℃ to 85 ℃. When the brake device brakes, the temperature of the position, attached to the brake pad, of the brake shell is increased to about 120 ℃ due to brake heat conduction, and can reach-55 ℃ along with the lowest temperature around the sensor when the airplane sails in the air at normal time, so that the sensor can influence the correctness and stability of an all-electric brake instruction during braking under the conditions that the use temperature specified by the sensor is exceeded and the sensor has no protective measures, and how to protect the sensor from the influence of external limit temperature is very important.
In order to overcome the influence of the limit temperature on the load cell, the design is solved by the following three aspects: a, when the structure is designed, the sensor is far away from a heat radiation source as far as possible, so that the influence of high temperature on the performance of the sensor is reduced; b, performing thermal protection or thermal insulation treatment on the sensor to prevent the influence of high temperature on the performance of the sensor; and c, the sensor has the environmental performance of resisting the low temperature of-55 ℃ through professional improvement, or the sensor is protected against low temperature.
3. Weight control of a mechanism
The mounting space and the weight of the electromechanical actuating brake device are larger than those of a mechanical control mechanism and a hydraulic piston actuating mechanism, the space needs to be fully utilized on the basis of meeting the requirements of functions, strength and rigidity, particularly, the requirements of the small unmanned helicopter on the mounting space and the weight of the whole electromechanical actuating brake device are more strict, the design of the electromechanical actuating brake device is more challenging, and the mounting space and the weight of the electromechanical actuating brake device become important indexes for measuring the quality of the whole product.
In order to reduce the installation space and the weight of the electromechanical actuating brake device, a planetary gear train speed reducing mechanism (or a bevel gear speed reducing mechanism) with small space and light weight is selected as the speed reducing mechanism; the brake disc and other structural parts are optimized to reduce weight on the premise of meeting the strength; the structure of the electric brake device is designed to be as tight as possible, and the parts such as the shell, the protecting cover and the like are made of aluminum alloy with lower density.
Claims (10)
1. An electric brake device for a helicopter is characterized by comprising a motor (1), a gear set (2), a brake disc (3), a first brake pad (4), a second brake pad (5) and a screw nut (6); the motor (1) drives a screw rod in the screw nut (6) to rotate through the gear set (2), the nut in the screw nut (6) is connected with the first brake block (4), and the brake disc (3) is arranged between the first brake block (4) and the second brake block (5).
2. An electric brake device for helicopter according to claim 1, characterized by that said gear set (2) comprises a speed reducer, a primary gear, a secondary gear, wherein the primary gear is a pinion gear, the secondary gear is a bull gear, the output shaft of the motor is connected to the input shaft of the speed reducer, the output shaft of the speed reducer is connected to the primary gear, the primary gear is connected to the secondary gear, and the secondary gear is connected to the lead screw shaft in the lead screw nut (6).
3. An electric brake device for helicopter according to claim 2 characterized in that the connection of said secondary gear and the screw in the screw nut (6) is provided with needle bearings.
4. An electric brake device for helicopters, according to claim 2, characterized in that said reducer is a planetary gear reducer.
5. An electric brake device for helicopters according to claim 2, characterized in that said speed reducer is a bevel gear reduction mechanism.
6. An electric brake device for helicopters, according to claim 1, characterized in that said electric motor (1) is a high-speed, low-torque and low-power brushless dc motor.
7. An electric brake device for helicopters, according to claim 1, characterized by further comprising a brake housing (7), wherein the electric motor (1), the gear train (2), the brake disc (3), the first brake pad (4), the second brake pad (5) and the screw nut (6) are arranged in the brake housing, and the outside of the second brake pad (5) abuts against the brake housing (7).
8. The electric brake device for the helicopter according to claim 1, further comprising a controller assembly (8), wherein the controller assembly (8) is connected with and controls the motor (1), when the brake action is implemented, the controller assembly (8) controls the motor to rotate forward, and the low-torque and high-speed output of the motor after passing through the gear set is changed into the high-torque and low-speed output to drive the screw rod on the screw nut (6) to rotate, so that the nut on the screw nut (6) generates linear motion, and the first brake pad (4) is pushed to press the brake disc (3), thereby realizing the brake; when the brake is released, the controller assembly (8) controls the motor to rotate reversely, the output of small torque and high rotating speed of the motor after passing through the gear set is changed into the output of large torque and low rotating speed to drive the screw rod on the screw rod nut (6) to rotate, so that the nut on the screw rod nut (6) generates reverse linear motion, the first brake pad (4) and the brake disc (3) are released, and the brake is released.
9. An electric brake device for helicopters, according to claim 8, characterized by further comprising a force sensor (9) and a hall sensor (10), the force sensor (9) being arranged between the second brake pad (5) and the brake housing, the hall sensor (10) being connected to the lead screw nut (6).
10. An electric brake device for helicopter according to claim 9 characterized in that said force sensor (9) and hall sensor (10) are connected to the controller assembly (8), and the controller assembly (8) determines the braking status by the data transmitted from the force sensor (9) and hall sensor (10).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202021024213.5U CN214776531U (en) | 2020-06-05 | 2020-06-05 | Electric brake device for helicopter |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202021024213.5U CN214776531U (en) | 2020-06-05 | 2020-06-05 | Electric brake device for helicopter |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN214776531U true CN214776531U (en) | 2021-11-19 |
Family
ID=78662879
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202021024213.5U Active CN214776531U (en) | 2020-06-05 | 2020-06-05 | Electric brake device for helicopter |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN214776531U (en) |
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2020
- 2020-06-05 CN CN202021024213.5U patent/CN214776531U/en active Active
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