CN201690329U - Dual-redundancy DC brushless servo motor of flight control system actuator loop - Google Patents
Dual-redundancy DC brushless servo motor of flight control system actuator loop Download PDFInfo
- Publication number
- CN201690329U CN201690329U CN2009202182742U CN200920218274U CN201690329U CN 201690329 U CN201690329 U CN 201690329U CN 2009202182742 U CN2009202182742 U CN 2009202182742U CN 200920218274 U CN200920218274 U CN 200920218274U CN 201690329 U CN201690329 U CN 201690329U
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- stator module
- magnetic steel
- motor
- housing
- rotor magnetic
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- Connection Of Motors, Electrical Generators, Mechanical Devices, And The Like (AREA)
Abstract
The utility model belongs to the automatic control technology of aviation flight, and relates to an improvement on an actuator motor of an aviation flight control system actuator loop. The motor includes a single motor including a casing (1), a front end cover (2), a rear end cover (3), a rotor shaft (4), a front bearing (5), a rear bearing (6), a sensor component (7), a rear rotor magnetic steel (8), a rear rotor component (9), and a first motor outgoing line (10). The utility model is characterized in that a front rotor magnetic steel (11) having the same structure and size as the rear rotor magnetic steel (8) is mounted on a rotor shaft (4), and a front stator component (12) having the same structure and size as the rear rotor component (9) is mounted in the casing (1). The utility model enables the servo motor to have double redundancy, solves the low reliability problem of the single motor, greatly improves the reliability, and ensures the safety of flying.
Description
Technical field
The utility model belongs to the automatic flight control technology of aviation, relates to the improvement to aviation flight control system rudder loop actuator motor.
Background technology
Existing aviation flight control system rudder loop actuator generally adopts single motor, when motor is short-circuited or opens circuit or during fault such as winding interturn short-circuit, will cause the inefficacy of controlling to rudder face because of electrical fault, has a strong impact on flight safety.
Summary of the invention
The purpose of this utility model is: propose a kind of coaxial pair of remaining direct current brushless servo motor, to solve the low problem of single motor reliability, guarantee flight safety.
The technical solution of the utility model is: be used for two remaining direct current brushless servo motors in flight control system rudder loop, comprise single motor of being made up of housing, front end housing, rear end cap, armature spindle, fore bearing, rear bearing, sensor cluster, back rotor magnetic steel, back stator module and the first motor lead-out wire; Front end housing is connected by screw with housing with rear end cap, the front end of armature spindle is connected with front end housing by fore bearing, the rear end of armature spindle is connected with rear end cap by rear bearing, sensor cluster is installed on the inner surface of rear end cap, the lead-out wire of sensor cluster is drawn from the fairlead of rear end cap, back rotor magnetic steel is fixed on the rear portion of armature spindle, back stator module is installed in the housing and the back corresponding position of rotor magnetic steel, the inner of the first motor lead-out wire is connected with the back stator module, and the outer end of the first motor lead-out wire passes by the fairlead on the housing; It is characterized in that, the axial dimension of housing prolongs 70%～90%, the also corresponding prolongation 70%～90% of the axial dimension of armature spindle, on armature spindle, the front of back rotor magnetic steel is equipped with a structure and size and the identical preceding rotor magnetic steel of back rotor magnetic steel, in housing, the front of back stator module is equipped with a structure and size and the identical preceding stator module of back stator module, the installation site of preceding stator module is corresponding with preceding rotor magnetic steel, one second motor lead-out wire is arranged, its the inner is connected with preceding stator module, and its outer end passes by the fairlead on the housing; Constitute the rear end motor by back stator module and back rotor magnetic steel, constitute the front end motor by preceding stator module and preceding rotor magnetic steel, the electrical null position of back stator module and the electrical null position of preceding stator module differ 15 °～16 °.
The utility model has the advantages that: make servomotor have two remainings, when one of them motor breaks down, another motor can be taken over job, thereby solved the low problem of single motor reliability, guaranteed that the rudder loop can move reliably, improve the reliability of motor greatly, guaranteed flight safety.
Description of drawings
Fig. 1 is a structural principle schematic diagram of the present utility model.
Specific implementation process
Below the utility model is described in further details.Referring to Fig. 1, the two remaining direct current brushless servo motors that are used for flight control system rudder loop comprise single motor of being made up of housing 1, front end housing 2, rear end cap 3, armature spindle 4, fore bearing 5, rear bearing 6, sensor cluster 7, back rotor magnetic steel 8, back stator module 9 and the first motor lead-out wire 10; Front end housing 2 and rear end cap 3 and housing 1 are connected by screw, the front end of armature spindle 4 is connected with front end housing 2 by fore bearing 5, the rear end of armature spindle 4 is connected with rear end cap 3 by rear bearing 5, sensor cluster 7 is installed on the inner surface of rear end cap 3, the lead-out wire of sensor cluster 7 is drawn from the fairlead of rear end cap 3, back rotor magnetic steel 8 is fixed on the rear portion of armature spindle 4, back stator module 9 is installed in the housing 1 position corresponding with back rotor magnetic steel 8, the inner of the first motor lead-out wire 10 is connected with back stator module 9, and the outer end of the first motor lead-out wire 10 passes by the fairlead on the housing 1; It is characterized in that, the axial dimension of housing 1 prolongs 70%～90%, the also corresponding prolongation 70%～90% of the axial dimension of armature spindle 4, on armature spindle 4, the front of back rotor magnetic steel 8 is equipped with the identical preceding rotor magnetic steel 11 of a structure and size and back rotor magnetic steel 8, in housing 1, the front of back stator module 9 is equipped with the identical preceding stator module 12 of a structure and size and back stator module 9, before the installation site of stator module 12 corresponding with preceding rotor magnetic steel 11, one second motor lead-out wire 13 is arranged, its the inner is connected with preceding stator module 12, and its outer end passes by the fairlead on the housing 1; Constitute the rear end motor by back stator module 9 and back rotor magnetic steel 8, constitute the front end motor by preceding stator module 12 and preceding rotor magnetic steel 11, the electrical null position of the electrical null position of back stator module 9 and preceding stator module 12 differs 15 °～16 °.
Operation principle of the present utility model is: distinguish the stator winding of forward end motor and the stator winding input three-phase PWM ripple of rear end motor by the lead-out wire of front end motor and the lead-out wire of rear end motor, the stator winding of the stator winding of front end motor and rear end motor will produce rotating magnetic field separately in air gap separately, wherein the rotating magnetic field of the stator winding of front end motor generation will be to front end rotor master magnet steel generation effect, the rotating magnetic field that the stator winding of rear end motor produces will be to rear end rotor master magnet steel generation effect, make the stator winding of the stator winding of front end motor and rear end motor produce the turning moment of an equidirectional to armature spindle, thereby the rotor rotation of drive motors, this has just guaranteed the work of not only turning round simultaneously in the mode of Hot Spare of front end motor and rear end motor, also can work alone in the mode of cold standby, when one of them motor breaks down, another motor can be taken over job, thereby this motor can be moved reliably.
Claims (1)
1. the two remaining direct current brushless servo motors that are used for flight control system rudder loop comprise single motor of being made up of housing [1], front end housing [2], rear end cap [3], armature spindle [4], fore bearing [5], rear bearing [6], sensor cluster [7], back rotor magnetic steel [8], back stator module [9] and the first motor lead-out wire [10]; Front end housing [2] is connected by screw with housing [1] with rear end cap [3], the front end of armature spindle [4] is connected with front end housing [2] by fore bearing [5], the rear end of armature spindle [4] is connected with rear end cap [3] by rear bearing [5], sensor cluster [7] is installed on the inner surface of rear end cap [3], the lead-out wire of sensor cluster [7] is drawn from the fairlead of rear end cap [3], back rotor magnetic steel [8] is fixed on the rear portion of armature spindle [4], back stator module [9] is installed in the housing [1] and the back corresponding position of rotor magnetic steel [8], the inner of the first motor lead-out wire [10] is connected with back stator module [9], and the outer end of the first motor lead-out wire [10] passes by the fairlead on the housing [1]; It is characterized in that, the axial dimension of housing [1] prolongs 70%～90%, the also corresponding prolongation 70%～90% of the axial dimension of armature spindle [4], on armature spindle [4], the front of back rotor magnetic steel [8] is equipped with a structure and size and the identical preceding rotor magnetic steel [11] of back rotor magnetic steel [8], in housing [1], the front of back stator module [9] is equipped with a structure and size and the identical preceding stator module [12] of back stator module [9], the installation site of preceding stator module [12] is corresponding with preceding rotor magnetic steel [11], one second motor lead-out wire [13] is arranged, its the inner is connected with preceding stator module [12], and its outer end passes by the fairlead on the housing [1]; Constitute the rear end motor by back stator module [9] and back rotor magnetic steel [8], constitute the front end motor by preceding stator module [12] and preceding rotor magnetic steel [11], the electrical null position of the electrical null position of back stator module [9] and preceding stator module [12] differs 15 °～16 °.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2009202182742U CN201690329U (en) | 2009-10-19 | 2009-10-19 | Dual-redundancy DC brushless servo motor of flight control system actuator loop |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2009202182742U CN201690329U (en) | 2009-10-19 | 2009-10-19 | Dual-redundancy DC brushless servo motor of flight control system actuator loop |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN201690329U true CN201690329U (en) | 2010-12-29 |
Family
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2009202182742U Expired - Fee Related CN201690329U (en) | 2009-10-19 | 2009-10-19 | Dual-redundancy DC brushless servo motor of flight control system actuator loop |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN201690329U (en) |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102097904A (en) * | 2011-03-30 | 2011-06-15 | 哈尔滨工业大学 | Sectional type cascade motor |
| CN105703582A (en) * | 2016-02-04 | 2016-06-22 | 精进电动科技（北京）有限公司 | Integrated type electric motor |
| CN108945485A (en) * | 2017-05-17 | 2018-12-07 | 通用电气公司 | Propulsion system for aircraft |
| CN110867992A (en) * | 2019-11-19 | 2020-03-06 | 芜湖市努尔航空信息科技有限公司 | Aviation magneto rotor |
| CN112532001A (en) * | 2020-10-29 | 2021-03-19 | 北京精密机电控制设备研究所 | Dual-stator dual-rotation small-size redundancy servo motor |
-
2009
- 2009-10-19 CN CN2009202182742U patent/CN201690329U/en not_active Expired - Fee Related
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102097904A (en) * | 2011-03-30 | 2011-06-15 | 哈尔滨工业大学 | Sectional type cascade motor |
| CN105703582A (en) * | 2016-02-04 | 2016-06-22 | 精进电动科技（北京）有限公司 | Integrated type electric motor |
| US11289983B2 (en) | 2016-02-04 | 2022-03-29 | Jing-Jin Electric Technologies Co., Ltd. | Integrated electrical motor |
| CN108945485A (en) * | 2017-05-17 | 2018-12-07 | 通用电气公司 | Propulsion system for aircraft |
| CN110867992A (en) * | 2019-11-19 | 2020-03-06 | 芜湖市努尔航空信息科技有限公司 | Aviation magneto rotor |
| CN112532001A (en) * | 2020-10-29 | 2021-03-19 | 北京精密机电控制设备研究所 | Dual-stator dual-rotation small-size redundancy servo motor |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| C17 | Cessation of patent right | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20101229 Termination date: 20121019 |