CN211618099U - Aviation seat adjustment mechanism - Google Patents
Aviation seat adjustment mechanism Download PDFInfo
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- CN211618099U CN211618099U CN201921069395.5U CN201921069395U CN211618099U CN 211618099 U CN211618099 U CN 211618099U CN 201921069395 U CN201921069395 U CN 201921069395U CN 211618099 U CN211618099 U CN 211618099U
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- brake
- motor
- seat
- adjustment mechanism
- permanent magnet
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Abstract
The invention relates to an adjusting mechanism of an aviation seat, in particular to an adjusting mechanism with small volume and high braking reliability. The adjusting mechanism comprises a driving motor and a brake, and the brake is a clapper type electromagnetic brake; the clapper type electromagnetic brake is provided with two groups of brake coils, wherein one group is connected in series in the motor circuit, and the other group is connected in parallel in the motor circuit; a diode is arranged in a brake coil which is connected with the motor circuit in parallel, and when the seat descends along the movement direction of the motor, the diode is conducted; the driving motor is a permanent magnet motor. The technical scheme is applied to an electric mechanism for adjusting the aviation seat, the size and the weight of the mechanism are reduced, the performance requirement is met, and the problem that the height of the aviation seat cannot be adjusted due to the fact that the brake malfunction during the work of the brake caused by the fact that the electromagnetic attraction cannot overcome the elastic force of the spring when the brake is in the electrified state in the process of the seat being electrified is solved.
Description
Technical Field
The invention relates to an adjusting mechanism of an aviation seat, in particular to an adjusting mechanism with small volume and high braking reliability.
Background
When the motor in the aircraft seat is electrified, 28V DC is introduced into a circuit, the current rises sharply from 0V, electromagnetic torque is generated in the armature winding Q2, and electromagnetic force for attracting the brake is generated in the brake coil Q1. When the current rises to the attracting current of the brake, the brake attracts and releases the braking state of the motor rotor; the current continues to rise, and the rotor of the motor rotates after the generated electromagnetic torque overcomes the load moment.
When the motor is powered off, the 28V DC of the power supply voltage in the line is disconnected, the current is sharply reduced to 0V from the rated current, and when the current reaches the release current of the brake, the brake is released, and friction force is generated to brake the rotor of the motor.
The motor drives the seat to move up and down by rotating clockwise and anticlockwise. When the seat moves downward, the load on the motor becomes smaller and the required operating current becomes smaller. With the development of motor design technology, the design efficiency of the driving motor is gradually improved, and the working current is smaller and smaller. The current in the brake coil Q1 is also smaller and smaller due to the comprehensive factors, when the electromagnetic attraction generated by the Q1 cannot overcome the elastic force of the spring, the brake is closed, the motor shaft is braked, and the brake malfunctions when the brake works, so that the pilot cannot adjust the height of the aircraft seat.
Disclosure of Invention
The technical problems solved by the invention are as follows: the adjusting mechanism is small in size and high in braking reliability.
The technical scheme of the invention is as follows: an aircraft seat adjustment mechanism characterized by: the adjusting mechanism comprises a driving motor and a brake, and the brake is a clapper type electromagnetic brake; the clapper type electromagnetic brake is provided with two groups of brake coils, wherein one group is connected in series in the motor circuit, and the other group is connected in parallel in the motor circuit; a diode is arranged in a brake coil which is connected with the motor circuit in parallel, and when the seat descends along the movement direction of the motor, the diode is conducted; the driving motor is a permanent magnet motor. When the seat is lifted, the series brake coil and the armature winding work simultaneously, the series brake coil releases the brake state, and the armature winding drives the motor to work. When the seat descends, the parallel brake coil and the series brake coil release the brake state, and the armature winding drives the motor to work. When the seat is adjusted, the parallel brake coil and the series brake coil are completely powered off when the seat is static, the brake is in a braking state, and static torque is output. The technical scheme is applied to an electric mechanism for adjusting the aviation seat, the size and the weight of the mechanism are reduced, the performance requirement is met, and the problem that the height of the aviation seat cannot be adjusted due to the fact that the brake malfunction during the work of the brake caused by the fact that the electromagnetic attraction cannot overcome the elastic force of the spring when the brake is in the electrified state in the process of the seat being electrified is solved.
Preferably, the number of pole pairs of the permanent magnet motor is 1. This design, on the one hand can satisfy the needs of seat regulatory function, and on the other hand, furthest has reduced the volume of motor.
Preferably, the permanent magnet motor magnetic steel material is 2:17 samarium cobalt permanent magnet. The design improves the temperature resistance and the working reliability of the motor and meets the requirement of the aviation product on the severe working environment.
Preferably, the number of commutator segments is twice the number of armature slots. The design is adopted in the system, the reversing is stable, and the electromagnetic compatibility of the motor is improved.
Drawings
Fig. 1 is a schematic diagram of the technical solution.
Detailed Description
The specific implementation mode of the invention is as follows: an aviation seat adjusting mechanism comprises a permanent magnet motor and an electromagnetic brake. The permanent magnet motor comprises 1 pair of poles of samarium-cobalt magnetic steel, 9 slot armatures, a commutator with 18 commutator segments, a shell and the like. The end of the motor shaft is mechanically connected with an electromagnetic brake in a hexagonal mode, and the electromagnetic brake comprises a series brake coil, a parallel brake coil, a diode, a brake shell, a friction disc, a spring and the like. The brake is a clapper type electromagnetic brake; the clapper type electromagnetic brake is provided with two groups of brake coils, wherein one group is connected in series in the motor circuit, and the other group is connected in parallel in the motor circuit; a diode is arranged in a brake coil which is connected with the motor circuit in parallel, and when the seat descends along the movement direction of the motor, the diode is conducted; the driving motor is a permanent magnet motor.
When the seat is lifted, the series brake coil and the armature winding work simultaneously, the series brake coil generates electromagnetic force after being electrified to release the brake state of the brake, and the armature winding drives the motor to work. When the seat descends, the diode is conducted, the parallel brake coil and the series brake coil are simultaneously electrified, the same-direction electromagnetic force is generated, the brake state of the brake is released, and the armature winding drives the motor to work. The seat is adjusted, and after all power-off, the brake coil is in a braking state, and outputs static torque to ensure that the position of the seat is unchanged.
Claims (5)
1. An aircraft seat adjustment mechanism characterized by: the adjusting mechanism comprises a driving motor and a brake, and the brake is a clapper type electromagnetic brake;
the clapper type electromagnetic brake is provided with two groups of brake coils, wherein one group is connected in series in the motor circuit, and the other group is connected in parallel in the motor circuit;
a diode is arranged in a brake coil which is connected with the motor circuit in parallel, and the diode is conducted when the seat descends along the movement direction of the motor.
2. An aircraft seat adjustment mechanism according to claim 1, wherein: the driving motor is a permanent magnet motor.
3. An aircraft seat adjustment mechanism according to claim 2, wherein: the number of pole pairs of the permanent magnet motor is 1.
4. An aircraft seat adjustment mechanism according to claim 2, wherein: the permanent magnet motor magnetic steel material is 2:17 samarium cobalt permanent magnet.
5. An aircraft seat adjustment mechanism according to claim 2, wherein: the number of commutator segments is twice the number of armature slots.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201921069395.5U CN211618099U (en) | 2019-07-09 | 2019-07-09 | Aviation seat adjustment mechanism |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201921069395.5U CN211618099U (en) | 2019-07-09 | 2019-07-09 | Aviation seat adjustment mechanism |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN211618099U true CN211618099U (en) | 2020-10-02 |
Family
ID=72616494
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201921069395.5U Active CN211618099U (en) | 2019-07-09 | 2019-07-09 | Aviation seat adjustment mechanism |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN211618099U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110228593A (en) * | 2019-07-11 | 2019-09-13 | 中国航发哈尔滨东安发动机有限公司 | A kind of aero seat regulating mechanism |
-
2019
- 2019-07-09 CN CN201921069395.5U patent/CN211618099U/en active Active
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110228593A (en) * | 2019-07-11 | 2019-09-13 | 中国航发哈尔滨东安发动机有限公司 | A kind of aero seat regulating mechanism |
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