CN101594024B - Fault isolation device of linear output executing mechanism of electromechanical actuator - Google Patents
Fault isolation device of linear output executing mechanism of electromechanical actuator Download PDFInfo
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- CN101594024B CN101594024B CN2009100881272A CN200910088127A CN101594024B CN 101594024 B CN101594024 B CN 101594024B CN 2009100881272 A CN2009100881272 A CN 2009100881272A CN 200910088127 A CN200910088127 A CN 200910088127A CN 101594024 B CN101594024 B CN 101594024B
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- 230000007246 mechanism Effects 0.000 title claims abstract description 33
- 238000002955 isolation Methods 0.000 title claims abstract description 23
- 230000002194 synthesizing effect Effects 0.000 claims abstract description 12
- 230000033001 locomotion Effects 0.000 claims abstract description 11
- 230000008878 coupling Effects 0.000 claims abstract description 4
- 238000010168 coupling process Methods 0.000 claims abstract description 4
- 238000005859 coupling reaction Methods 0.000 claims abstract description 4
- 238000007789 sealing Methods 0.000 claims description 7
- 239000000428 dust Substances 0.000 claims description 6
- 238000009434 installation Methods 0.000 claims description 2
- 230000001066 destructive effect Effects 0.000 abstract description 3
- 230000000694 effects Effects 0.000 description 5
- 230000009471 action Effects 0.000 description 3
- 238000005516 engineering process Methods 0.000 description 2
- 230000009467 reduction Effects 0.000 description 2
- RZVHIXYEVGDQDX-UHFFFAOYSA-N 9,10-anthraquinone Chemical compound C1=CC=C2C(=O)C3=CC=CC=C3C(=O)C2=C1 RZVHIXYEVGDQDX-UHFFFAOYSA-N 0.000 description 1
- 230000002457 bidirectional effect Effects 0.000 description 1
- 230000005540 biological transmission Effects 0.000 description 1
- 230000008859 change Effects 0.000 description 1
- 238000000354 decomposition reaction Methods 0.000 description 1
- 230000005611 electricity Effects 0.000 description 1
- 239000003344 environmental pollutant Substances 0.000 description 1
- 239000010720 hydraulic oil Substances 0.000 description 1
- 239000007788 liquid Substances 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 231100000719 pollutant Toxicity 0.000 description 1
- 230000008569 process Effects 0.000 description 1
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Abstract
The invention provides a fault isolation device applied to a linear output executing mechanism of an electromechanical actuator, which is mainly used for isolating stuck faults of the linear output executing mechanism to avoid influencing movement of a control surface. The fault isolation device mainly comprises a main body, an end cover, a valve seat, a two-position two-way solenoid valve, a piston type output rod and related accessories. The left end of the main body is fixedly connected with the tail end of the linear output executing mechanism through a coupling, while the right end is fixedly connected with the end cover through threads. The two-position two-way solenoid valve is communicated with a control chamber in the main body through the valve seat fixedly arranged on the upper part of the main body. The final output end of the electromechanical actuator is the piston type output rod which is arranged in the main body, and the right end of the piston type output rod is directly fixedly connected with a force synthesizing arm. When the linear output executing mechanism of the electromechanical actuator has the stuck faults, the output end of the electromechanical actuator can follow the movement of the rest normally working output ends of the actuator to move, and the electromechanical actuator cannot generate destructive torque on the force synthesizing arm so as to improve the safe reliability.
Description
Technical field
The present invention relates to the airborne actuating system technical field that flies to control, be specifically related to a kind of structural design that is applicable to the linear output executing mechanism of electromechanical actuator fault isolation device.
Background technology
Airbornely fly to control actuating system and be meant and realize on machine that some has output, a whole set of system mechanical action, relatively independent of suitable power, controls aircraft flight attitude and flight path by the servo-drive rudder face.The actuator form that the crucial rudder face of aircraft adopts usually has: traditional hydraulic actuator and power-by-wire actuator.The development of electricity/electric aircraft technology along with how, electric energy will progressively replace hydraulic pressure energy, air pressure can etc. become main energy sources on the aircraft of new generation.Therefore, the power-by-wire actuator will progressively replace traditional hydraulic actuator, and the first-selection that becomes on the aircraft of new generation flies to control the actuating system form.Electronic quiet liquid actuator and electromechanical actuator are two kinds of principal modes of power-by-wire actuator.The former compares with traditional hydraulic actuator, though do not need the central hydraulic source that energy is provided, it needs still independently that motor-driven hydraulic pumps provides energy, can't be completely free of the hydraulic pressure energy; The latter then adopts electric energy to drive fully, meets the development trend of electric aircraft fully.
Electromechanical actuator is mainly by controller, bidirectional speed governing motor, gear reduction unit with can realize reciprocating output executing mechanism.Wherein, actuator mainly is made up of output of ball (roller) leading screw straight line or gear rotation output mechanism.The effect of gear reduction unit is the motor of the little torque of high speed to be exported the mechanical rotation that is converted into low speed high torque export to ball (roller) leading screw or gear rotary actuator.The torque limit mechanism of safeguard protection effect and friction clutch etc. also have been housed in the general decelerator.Friction clutch can by rubbing action with the output transmission of torque of motor to output executing mechanism, when drive motors breaks down, motor can be separated with output executing mechanism by clutch, thus with Fault Isolation.Usually, crucial rudder face on the aircraft all has the above actuator of two covers to constitute redundant actuating system by force synthesizing arm, when wherein a cover actuator is when breaking down, flight control system will be cut off the control action to it, guarantee normal manipulation to rudder face by the actuator of controlling remainder.Simultaneously, the actuator that requires to break down can not exert an influence to the manipulation of force synthesizing arm and rudder face.But when stuck fault took place the output executing mechanism of electromechanical actuator, original friction clutch can't be isolated this fault.At this moment, though electromechanical actuator is not directly controlled force synthesizing arm, but since between its output executing mechanism and the force synthesizing arm for being rigidly connected, when the actuator continuation of remainder is controlled force synthesizing arm, on force synthesizing arm, generation had destructive moment of torsion, normal manipulation to rudder face exerts an influence the most at last, and then has influence on the flight safety of aircraft.
Summary of the invention
Can't implement the shortcoming of effectively isolating when stuck fault takes place the linear output executing mechanism that exists at above-mentioned electromechanical actuator, the present invention has designed a kind of fault isolation device that is applied to linear output executing mechanism of electromechanical actuator, be mainly used to isolate the stuck fault of linear output executing mechanism, avoid rudder face motion is impacted.
The technical solution used in the present invention is: the end at linear output executing mechanism of electromechanical actuator has increased a fault isolation device, mainly is made up of main body, end cap, valve seat, 2/2-way electromagnetically operated valve, piston type take-off lever and related accessories.The left end of main body is fixedlyed connected with the terminal of linear output executing mechanism by shaft coupling, and its right-hand member is fixedlyed connected by screw thread with end cap.The piston type take-off lever is installed in body interior, and main body is divided into left and right two control chambers.Valve seat is installed on the mounting platform of main body top by screw.The 2/2-way electromagnetically operated valve is installed in valve seat top by screw, the pipeline by valve seat inside respectively with main body in about two control chambers be communicated with, its control signal is from the controller of electromechanical actuator.The final output of electromechanical actuator is the piston type take-off lever.The right-hand member of piston type take-off lever is directly fixedlyed connected with force synthesizing arm.When the electromechanical actuator operate as normal, the 2/2-way electromagnetically operated valve is in normally closed position, is not communicated with between two control chambers of main body, and linear output executing mechanism drives fault isolation device and directly drives the rudder face motion; When stuck fault took place the linear output executing mechanism of electromechanical actuator, controller control 2/2-way electromagnetically operated valve was shown in an open position, and two control chambers of main body is communicated with, thereby makes that the piston type take-off lever can free movement in main body.
The invention has the advantages that: electromechanical actuator is after increasing this fault isolation device, when stuck fault appears in its linear output executing mechanism, its output can follow remaining operate as normal the actuator output motion and move, and can not produce destructive moment of torsion, thereby improved the security reliability that flies to control actuating system to force synthesizing arm.In addition, this fault isolation device is simple in structure, easy to process, is easy to realize.
Description of drawings
Fig. 1 is the outline drawing of fault isolation device of the present invention;
Fig. 2 is the STRUCTURE DECOMPOSITION figure of fault isolation device of the present invention;
Fig. 3 is the cutaway view of Fig. 1.
Among the figure, 1: main body, 2: prevent dust and change 3: guide ring, 4: sealing ring, 5: valve seat, 6: 2/2-way electromagnetically operated valve, 7: end cap, 8: piston type take-off lever, 9: cavity, 10: left control chamber, 11: right control chamber, 12: left side pipeline, 13: right side pipeline, 14: mounting platform, 15: dustproof groove A, 16: gathering sill A, 17: seal groove A, 18: gathering sill B, 19: seal groove B, 20: gathering sill C, 21: seal groove C, 22: gathering sill D, 23: dustproof groove B.
Embodiment
The present invention is described in further detail below in conjunction with accompanying drawing.
The present invention has increased a fault isolation device at the end of linear output executing mechanism of electromechanical actuator, as shown in Figure 1 and Figure 2.Among Fig. 3, the left end of main body 1 is fixedlyed connected with the terminal of linear output executing mechanism by shaft coupling, and its right-hand member is fixedlyed connected with end cap 7 by screw thread.Piston type take-off lever 8 is installed in the inside of main body 1, and main body 1 is divided into left control chamber 10 and right control chamber 11.The initial installation site of piston type take-off lever 8 in main body 1 should make left control chamber 10 identical with the volume of right control chamber 11.Valve seat 5 is installed on the mounting platform 14 of main body 1 top by screw.2/2-way electromagnetically operated valve 6 is installed in valve seat 5 tops by screw, and left side pipeline 12 by valve seat 5 inside and right side pipeline 13 are communicated with left control chamber 10 and right control chamber 11 in the main body 1 respectively, and its control signal is from the controller of electromechanical actuator.The final output of electromechanical actuator is a piston type take-off lever 8.The right-hand member of piston type take-off lever 8 is directly fixedlyed connected with force synthesizing arm.When the electromechanical actuator operate as normal, 2/2-way electromagnetically operated valve 6 is in normally closed position, is not communicated with between two control chambers 10 of main body 1 and 11, and linear output executing mechanism drives fault isolation device and directly drives the rudder face motion; When stuck fault took place the linear output executing mechanism of electromechanical actuator, controller control 2/2-way electromagnetically operated valve 6 was shown in an open position, and two control chambers 10 and 11 of main body 1 is communicated with, thereby makes that piston type take-off lever 8 can free movement in main body 1.When piston type take-off lever 8 moved right, cavity 9 can provide enough spaces to it.The initial length of cavity 9 should be identical with the initial length of left control chamber 10 and right control chamber 11.
Isolation between cavity 9 in the described main body 1 and the left control chamber 10 by be installed in dust ring 2 among the dustproof groove A15, among the gathering sill A16 guide ring 3, realize sealing ring 4 and the cooperating of piston type take-off lever 8 among the seal groove A17.Isolation between left control chamber 10 in the described main body 1 and the right control chamber 11 by be installed in guide ring 3 among the gathering sill B18, among the seal groove B19 sealing ring 4, realize guide ring 3 and the cooperating of piston type take-off lever 8 among the gathering sill C20.Isolation between right control chamber 11 in the described main body 1 and the external world is by being installed in realizing dust ring 2 and cooperating of piston type take-off lever 8 among the sealing ring 4 among the seal groove C21 on the end cap 7, the guide ring 3 among the gathering sill D22, the dustproof groove B23.The effect of described dust ring 2 is to remove pistons reciprocating formula take-off lever 8 to be exposed at pollutant accompanying on the surface of main body 1 outside, prevents that it from entering main body 1 inside.The effect of described guide ring 3 is the side forces that produced when absorbing 8 reciprocating motions of piston type take-off lever.The effect of described sealing ring 4 is the leakages that prevent hydraulic oil.
Claims (4)
1. a fault isolation device that is applied to linear output executing mechanism of electromechanical actuator is characterized in that: comprise main body, end cap, valve seat, 2/2-way electromagnetically operated valve, piston type take-off lever, dust ring, guide ring, sealing ring;
The piston type take-off lever is installed in body interior, and main body is divided into left and right two control chambers;
Main body and piston type take-off lever are being reserved cavity near left control chamber one side;
End near cavity on the main body is fixedlyed connected with the terminal of linear output executing mechanism by shaft coupling, and its other end is fixedlyed connected with end cap by screw thread;
Valve seat is installed on the mounting platform of main body top by screw;
The 2/2-way electromagnetically operated valve is installed in valve seat top by screw, the pipeline by valve seat inside respectively with main body in about two control chambers be communicated with;
The final output of electromechanical actuator is the piston type take-off lever;
Piston type take-off lever right-hand member is directly fixedlyed connected with force synthesizing arm.
2. a kind of according to claim 1 fault isolation device that is applied to linear output executing mechanism of electromechanical actuator, it is characterized in that: when the electromechanical actuator operate as normal, the 2/2-way electromagnetically operated valve is in normally closed position, be not communicated with between two control chambers of main body, linear output executing mechanism drives fault isolation device and directly drives the rudder face motion; When stuck fault took place the linear output executing mechanism of electromechanical actuator, controller control 2/2-way electromagnetically operated valve was shown in an open position, and two control chambers of main body is communicated with, thereby makes that the piston type take-off lever can free movement in main body.
3. a kind of according to claim 1 fault isolation device that is applied to linear output executing mechanism of electromechanical actuator is characterized in that: the initial installation site of piston type take-off lever in main body should make the volume of left control chamber and right control chamber identical; The initial length of cavity should be identical with the initial length of left control chamber and right control chamber.
4. a kind of according to claim 1 fault isolation device that is applied to linear output executing mechanism of electromechanical actuator is characterized in that: main body, end cap, valve seat, 2/2-way electromagnetically operated valve, piston type take-off lever, dust ring, guide ring, sealing ring become one by main body.
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2009100881272A CN101594024B (en) | 2009-07-06 | 2009-07-06 | Fault isolation device of linear output executing mechanism of electromechanical actuator |
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| Application Number | Priority Date | Filing Date | Title |
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| CN2009100881272A CN101594024B (en) | 2009-07-06 | 2009-07-06 | Fault isolation device of linear output executing mechanism of electromechanical actuator |
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| CN101594024A CN101594024A (en) | 2009-12-02 |
| CN101594024B true CN101594024B (en) | 2011-05-04 |
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| CN113028017B (en) * | 2021-02-24 | 2022-06-14 | 内蒙古工业大学 | Clamping stagnation prevention hydraulic backup type electromechanical actuator and control method thereof |
Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2658812B2 (en) * | 1993-08-12 | 1997-09-30 | 日本電気株式会社 | Piezo actuator |
| CN2936452Y (en) * | 2006-07-07 | 2007-08-22 | 陈连方 | Lateral plate type cyclic movement bias block exciter |
-
2009
- 2009-07-06 CN CN2009100881272A patent/CN101594024B/en active Active
Patent Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2658812B2 (en) * | 1993-08-12 | 1997-09-30 | 日本電気株式会社 | Piezo actuator |
| CN2936452Y (en) * | 2006-07-07 | 2007-08-22 | 陈连方 | Lateral plate type cyclic movement bias block exciter |
Non-Patent Citations (2)
| Title |
|---|
| 李清等.自修复飞行控制系统舵面/作动器故障检测与隔离.《航空学报》.1997,第18卷(第6期),693-697. * |
| 祁晓野等.功率电传动机载作动系统方案分析.《北京航空航天大学学报》.1999,第25卷(第4期),426-430. * |
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| CN101594024A (en) | 2009-12-02 |
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Owner name: DONGFANG JINGYUAN ELECTRONIC TECHNOLOGY (BEIJING) Free format text: FORMER OWNER: BEIHANG UNIVERSITY Effective date: 20150805 |
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Effective date of registration: 20150805 Address after: 100176, Beijing economic and Technological Development Zone, Beijing No. four road, No. 156, No. 12 hospital building Patentee after: DONGFANG JINGYUAN ELECTRON Ltd. Address before: 100191 Haidian District, Xueyuan Road, No. 37, Patentee before: Beihang University |
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Address after: 100176 building 12, yard 156, Jinghai 4th Road, Beijing Economic and Technological Development Zone, Daxing District, Beijing Patentee after: Dongfang Jingyuan Microelectronics Technology (Beijing) Co.,Ltd. Address before: Building 12, No. 156 Jinghai Fourth Road, Beijing Economic and Technological Development Zone, 100176 Patentee before: DONGFANG JINGYUAN ELECTRON Ltd. |