An aeronautical electric machine protection device and a protection method

Abstract

The application belongs to the field of aviation electric machines, and particularly relates to an aviation electric machine protection device and a protection method. The device comprises a protection device shell (1), an armature (2), an electromagnet winding (3), a positioning pin spring (5), a positioning pin (6), a baffle (7), a hollow shaft connecting sleeve (10), and an elastic shaft connecting sleeve (11). The device can disconnect the electric machine from the engine and other matched equipment when the electric machine fails without damaging the elastic shaft of the electric machine, thereby protecting the electric machine and the matched equipment. The device has the advantages of simple structure, low production cost, and reusability, and can effectively avoid the risk of damage of the electric machine itself and the engine and other matched equipment caused by the failure of the aviation electric machine.

Description

Technical Field

[0001] This invention belongs to the field of aviation motors, and specifically relates to an aviation motor protection device and protection method. Background Technology

[0002] During operation, aircraft motors may experience malfunctions such as rotor rubbing, seizure, or reverse rotation due to unforeseen circumstances. To protect the engine and other supporting equipment, the most common method in the industry is to install a shear section on the motor's elastic shaft. The outer diameter of the shear section is smaller than the diameter of the elastic shaft, and therefore the maximum torque it can withstand is also smaller. Once the motor's operating condition malfunctions, the abnormally increased torque will shear off the elastic shaft shear end, causing the motor to detach from the engine and other supporting equipment. This method is destructive to the elastic shaft and is a way of sacrificing the motor to protect other equipment; it does not actually protect the motor. Summary of the Invention

[0003] An aviation motor protection device is provided, which can disconnect the motor from the engine and other supporting equipment when the motor fails without damaging the motor's elastic shaft, thereby protecting the motor and supporting equipment.

[0004] To achieve the above objectives, the present invention provides the following technical solution: an aviation motor protection device, comprising a protection device housing 1, an armature 2, an electromagnet winding 3, a positioning pin spring 5, a positioning pin 6, a baffle 7, a hollow shaft connecting sleeve 10, and an elastic shaft connecting sleeve 11; the electromagnet winding 3 is installed inside the protection device housing 1 and is electrically connected to the armature 2; the positioning pin spring 5 is fitted on the positioning pin 6, and the positioning pin spring 5 and the positioning pin 6 are movably mounted on the protection device housing 1; the baffle 7 is secured below the positioning pin; the hollow shaft connecting sleeve 10 is fixedly connected to the hollow shaft 8 of the motor; and the elastic shaft connecting sleeve 11 is fixedly connected to the elastic shaft 9 of the motor.

[0005] A spring 4 is added between the housing 1 of the protective device and the baffle 7. Under normal conditions, the spring is in a compressed state, so that the baffle can stably lock the positioning pin 6.

[0006] A spring switch 13 is fixed on the housing 1 of the protective device, and the spring switch 13 is connected in series with the electromagnet winding 3. When the elastic shaft 9 moves to the left a certain distance, it will touch the spring switch 13, cutting off the current in the electromagnet winding 3 and preventing the electromagnet winding 3 from being energized for a long time and causing other safety hazards.

[0007] The elastic shaft connecting sleeve 11 is threadedly connected to the elastic shaft 9.

[0008] The thread direction of the elastic shaft connecting sleeve 11 and the elastic shaft 9 is opposite to the direction of motor rotation.

[0009] The aircraft motor protection device is fixed on the tail end cover of the generator.

[0010] The baffle 7 is disc-shaped with a hole in the middle, allowing the elastic shaft 9 to pass through. The baffle 7 has a step, which holds the positioning pin 6 in place.

[0011] A protection method for an aircraft motor protection device: When the generator is working normally under the drive of the engine, and the aircraft motor controller detects abnormal operation of the motor, the aircraft motor controller connects the electromagnet winding 3. Under the action of electromagnetic attraction, the armature 2 attracts the baffle 7 to move to the left. The two positioning pins 6 blocked by the baffle 7 are popped out under the action of the positioning pin spring 5, and then jam the elastic shaft connecting sleeve 11. Under the action of torque, the screws 12 and 15 connecting the elastic shaft connecting sleeve 11 and the hollow shaft connecting sleeve 10 are broken, and the elastic shaft connecting sleeve 11 stops rotating. Since the elastic shaft connecting sleeve 11 and the elastic shaft 9 are threadedly connected, the continuing to rotate elastic shaft 9 moves to the left under the action of the thread, and finally disengages from the spline sleeve of the engine output shaft, and the motor stops running.

[0012] After the motor stops running, the elastic shaft 9 continues to move to the left and touches the spring switch 13, which is fixed on the housing 1 of the protective device and connected in series with the electromagnet winding 3. The spring switch 13 changes to the open state, and the electromagnet winding 3 is de-energized.

[0013] A ground power-on inspection method for an aircraft motor protection device: In the non-working state, the positioning pin 6 is stuck by the baffle 7 and will not pop out; connect the first and last lead b and lead a of the electromagnet winding 3 together, and apply 27V DC power to the other end of the electromagnet winding (3), the baffle 7 moves to the left, and the positioning pin 6 pops out freely, which can be used to determine that the ground power-on inspection of the aircraft motor protection device is good; otherwise, it can be determined that the aircraft motor protection device cannot work properly.

[0014] This invention has the following advantages and beneficial effects: It proposes an aircraft motor protection device, which has the advantages of simple structure, low production cost and reusability, and can effectively avoid the risk of damage to the motor itself and supporting equipment such as the engine due to aircraft motor failure. Attached Figure Description

[0015] Figure 1 This is a schematic diagram of the structure of the present invention.

[0016] Figure 2 This is a schematic diagram of the ground detection wiring of the present invention.

[0017] The components are: 1. Protective device housing, 2. Armature, 3. Electromagnet winding, 4. Spring, 5. Positioning pin spring, 6. Positioning pin, 7. Baffle, 8. Hollow shaft, 9. Elastic shaft, 10. Hollow shaft connecting sleeve, 11. Elastic shaft connecting sleeve, 12. Connecting screw a, 13. Spring switch, 15. Connecting screw b, 16. Lead wire protective sleeve, 17. Lead wire, 18. Marking heat shrink tubing. Detailed Implementation

[0018] The invention will now be further described with reference to the accompanying drawings.

[0019] An aviation motor protection device includes a protection device housing 1, an armature 2, an electromagnet winding 3, a positioning pin spring 5, a positioning pin 6, a baffle 7, a hollow shaft connecting sleeve 10, and an elastic shaft connecting sleeve 11. The electromagnet winding 3 is installed inside the protection device housing 1 and is electrically connected to the armature 2. The positioning pin spring 5 is sleeved on the positioning pin 6, and the positioning pin spring 5 and the positioning pin 6 are movably installed on the protection device housing 1. The baffle 7 is stuck below the positioning pin. The hollow shaft connecting sleeve 10 is fixedly connected to the hollow shaft 8 of the motor, and the elastic shaft connecting sleeve 11 is fixedly connected to the elastic shaft 9 of the motor.

[0020] A spring 4 is added between the housing 1 of the protective device and the baffle 7. Under normal conditions, the spring is in a compressed state, so that the baffle can stably lock the positioning pin 6.

[0021] A spring switch 13 is fixed on the housing 1 of the protective device, and the spring switch 13 is connected in series with the electromagnet winding 3. When the elastic shaft 9 moves to the left a certain distance, it will touch the spring switch 13, cutting off the current in the electromagnet winding 3 and preventing the electromagnet winding 3 from being energized for a long time and causing other safety hazards.

[0022] The elastic shaft connecting sleeve 11 is threadedly connected to the elastic shaft 9.

[0023] The thread direction of the elastic shaft connecting sleeve 11 and the elastic shaft 9 is opposite to the direction of motor rotation.

[0024] The aircraft motor protection device is fixed on the tail end cover of the generator.

[0025] The baffle 7 is disc-shaped with a hole in the middle, allowing the elastic shaft 9 to pass through. The baffle 7 has a step, which holds the positioning pin 6 in place.

[0026] A protection method for an aircraft motor protection device: When the generator is working normally under the drive of the engine, and the aircraft motor controller detects abnormal operation of the motor, the aircraft motor controller connects the electromagnet winding 3. Under the action of electromagnetic attraction, the armature 2 attracts the baffle 7 to move to the left. The two positioning pins 6 blocked by the baffle 7 are popped out under the action of the positioning pin spring 5, and then jam the elastic shaft connecting sleeve 11. Under the action of torque, the screws 12 and 15 connecting the elastic shaft connecting sleeve 11 and the hollow shaft connecting sleeve 10 are broken, and the elastic shaft connecting sleeve 11 stops rotating. Since the elastic shaft connecting sleeve 11 and the elastic shaft 9 are threadedly connected, the continuing to rotate elastic shaft 9 moves to the left under the action of the thread, and finally disengages from the spline sleeve of the engine output shaft, and the motor stops running.

[0027] After the motor stops running, the elastic shaft 9 continues to move to the left and touches the spring switch 13, which is fixed on the housing 1 of the protection device and connected in series with the electromagnet winding 3. The spring switch 13 changes to the open state, and the electromagnet winding 3 is de-energized to prevent the electromagnet from being energized for a long time and causing other accidents.

[0028] A ground-based power-on inspection method for an aircraft motor protection device is provided. In the non-working state, the positioning pin 6 is blocked by the baffle 7 and will not pop out. There are four leads 17, namely lead 1, lead 2, lead 1a and lead 2b. Each lead is covered with a lead protective sleeve 16 and is marked with heat shrink tubing 18 for easy identification. The first and last leads b and lead a of the electromagnet winding 3 are connected together. 27V DC power is applied to the other two ends of the electromagnet winding (3), leads d and c. The baffle 7 moves to the left and the positioning pin 6 pops out freely. This indicates that the ground-based power-on inspection of the aircraft motor protection device is good and can play a protective role when the motor is abnormal. Otherwise, it can be determined that the aircraft motor protection device cannot work properly.

Claims

1. A protection method for an aircraft motor protection device, characterized in that, The protective device includes a protective device housing (1), an armature (2), an electromagnet winding (3), a positioning pin spring (5), a positioning pin (6), a baffle (7), a hollow shaft connecting sleeve (10), and an elastic shaft connecting sleeve (11). The electromagnet winding (3) is installed inside the protective device housing (1), and the electromagnet winding (3) is electrically connected to the armature (2). The positioning pin (6) is fitted with a positioning pin spring (5), and the positioning pin spring (5) and the positioning pin (6) are movably installed on the protective device housing (1). The baffle (7) is stuck below the positioning pin. The hollow shaft connecting sleeve (10) is fixedly connected to the hollow shaft (8) of the motor, and the elastic shaft connecting sleeve (11) is fixedly connected to the elastic shaft (9) of the motor. The protection method of the aviation motor protection device is as follows: When the generator is driven by the engine and works normally, when the aviation motor controller detects that the motor is working abnormally, the aviation motor controller connects the electromagnet winding (3). Under the action of electromagnetic attraction, the armature (2) attracts the baffle (7) to move to the left. The two positioning pins (6) blocked by the baffle (7) pop out under the action of the positioning pin spring (5) and then lock the elastic shaft connecting sleeve (11). Under the action of torque, the screws (12) and (15) connecting the elastic shaft connecting sleeve (11) and the hollow shaft connecting sleeve (10) are broken. The elastic shaft connecting sleeve (11) stops rotating. Since the elastic shaft connecting sleeve (11) and the elastic shaft (9) are threaded, the elastic shaft (9) that continues to rotate moves to the left under the action of the thread and finally disengages from the spline sleeve of the engine output shaft, and the motor stops running.

2. The protection method of the aircraft motor protection device according to claim 1, characterized in that: A spring (4) is added between the housing (1) of the protective device and the baffle (7). Under normal conditions, the spring is in a compressed state, so that the baffle can stably hold the positioning pin (6).

3. The protection method of the aircraft motor protection device according to claim 1, characterized in that: The elastic shaft connecting sleeve (11) is threadedly connected to the elastic shaft (9).

4. The protection method of the aircraft motor protection device according to claim 1, characterized in that: The thread direction of the elastic shaft connecting sleeve (11) and the elastic shaft (9) is opposite to the direction of motor rotation.

5. The protection method of the aircraft motor protection device according to claim 1, characterized in that: The aircraft motor protection device is fixed on the tail end cover of the generator.

6. The protection method of the aircraft motor protection device according to claim 1, characterized in that: The baffle (7) is disc-shaped and has a hole in the middle so that the elastic shaft can pass through. The baffle (7) is provided with a step, and the baffle (7) is stuck to the positioning pin (6) by the step.

7. The protection method of the aircraft motor protection device according to claim 1, characterized in that: After the motor stops running, the elastic shaft (9) continues to move to the left and touches the spring switch (13) which is fixed on the housing (1) of the protective device and connected in series with the electromagnet winding (3). The spring switch (13) changes to the open state and the electromagnet winding (3) is de-energized.

8. The protection method of the aircraft motor protection device according to claim 1, characterized in that: In the non-working state, the positioning pin (6) is stuck by the baffle (7) and will not pop out; at this time, connect the first and last lead b and lead a of the electromagnet winding (3) together, and apply 27V DC power to the other end of the electromagnet winding (3) lead d and lead c. The baffle (7) moves to the left and the positioning pin (6) pops out freely. It can be judged that the ground power-on inspection of the aviation motor protection device is good; otherwise, it can be judged that the aviation motor protection device cannot work properly.

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