CN105515251B - A kind of high synchronism electromechanical coupling system with trailing type thermal insulation tile - Google Patents
A kind of high synchronism electromechanical coupling system with trailing type thermal insulation tile Download PDFInfo
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- CN105515251B CN105515251B CN201510890502.0A CN201510890502A CN105515251B CN 105515251 B CN105515251 B CN 105515251B CN 201510890502 A CN201510890502 A CN 201510890502A CN 105515251 B CN105515251 B CN 105515251B
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- thermal insulation
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- H—ELECTRICITY
- H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
- H02K—DYNAMO-ELECTRIC MACHINES
- H02K5/00—Casings; Enclosures; Supports
- H02K5/04—Casings or enclosures characterised by the shape, form or construction thereof
-
- H—ELECTRICITY
- H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
- H02K—DYNAMO-ELECTRIC MACHINES
- H02K5/00—Casings; Enclosures; Supports
- H02K5/04—Casings or enclosures characterised by the shape, form or construction thereof
- H02K5/10—Casings or enclosures characterised by the shape, form or construction thereof with arrangements for protection from ingress, e.g. water or fingers
-
- H—ELECTRICITY
- H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
- H02K—DYNAMO-ELECTRIC MACHINES
- H02K7/00—Arrangements for handling mechanical energy structurally associated with dynamo-electric machines, e.g. structural association with mechanical driving motors or auxiliary dynamo-electric machines
- H02K7/10—Structural association with clutches, brakes, gears, pulleys or mechanical starters
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- H—ELECTRICITY
- H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
- H02P—CONTROL OR REGULATION OF ELECTRIC MOTORS, ELECTRIC GENERATORS OR DYNAMO-ELECTRIC CONVERTERS; CONTROLLING TRANSFORMERS, REACTORS OR CHOKE COILS
- H02P6/00—Arrangements for controlling synchronous motors or other dynamo-electric motors using electronic commutation dependent on the rotor position; Electronic commutators therefor
- H02P6/04—Arrangements for controlling or regulating the speed or torque of more than one motor
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- Engineering & Computer Science (AREA)
- Power Engineering (AREA)
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Abstract
A kind of high synchronism electromechanical coupling system with trailing type thermal insulation tile, jet pipe opening applied to certain aircraft engine is adjusted, pass through servo-actuated light rigidity ceramic insulation watt and electromechanical actuator integrated design so that electromechanical actuator can continuously work 1h in 400 DEG C of high thermal environments of engine environment.The electromechanical coupling system of the present invention controls the system schema of three electromechanical actuators using a control driver simultaneously, ensures the high synchronism of three electromechanical actuator output actions by position-speed-electric current three close-loop control.Electromechanical actuator is arranged near engine jet pipe, and thermal insulation tile is coated on electromechanical actuator surface by screw thread and adiabatic gum, can be realized cladding completely with the flexible and flexible of the output end of electromechanical coupling system, the resistance to elevated temperatures of electromechanical coupling system greatly improved.
Description
Technical field
The present invention relates to a kind of high synchronism electromechanical coupling system with trailing type thermal insulation tile, belong to and start for spacecraft
The electromechanical coupling system technical field of machine.
Background technology
Existing electromechanical coupling system is more using cladding heat-insulated asbestos cloth, alkali-free glass fibre without special heat protection design
The mode such as band or metallized film silicon rubber carries out simple thermal protection, and there are the following problems for traditional thermal protection method：
The output end of electromechanical actuator can be elastic, and traditional thermal protection measure is only capable of coating consolidating for electromechanical coupling system
Determine part, the movable part of electromechanical coupling system can not be coated, therefore complete cladding can not be realized, while sealing is poor, it is overall
Thermal protection is ineffective；
Traditional thermal protection is coated without strict solid shape, or is wound for strip material, or is cut into for soft material
Type, fixed finally by strapping, such a fastening means is not firm, is also easy to produce fifth wheel, causes engine or servo control mechanism event
Barrier；
Traditional control driver is separate to the control algolithm for three electromechanical actuators, three electromechanical actuators
After given identical instruction, occur in motion process asynchronous so that engine jet pipe clamping stagnation, cause engine or servo
Structure failure；
The content of the invention
Present invention solves the technical problem that it is：Overcome prior art can not follow electromechanical actuator motion, can not wrap completely
Cover the deficiency of electromechanical actuator, there is provided a kind of high synchronism electromechanical coupling system with trailing type thermal insulation tile, it is ensured that in electromechanics
Thermal insulation tile coats electromechanical actuator completely in actuator telescopic process, greatly improves thermal protective performance；
The technical scheme that the present invention solves is：A kind of high synchronism electromechanical coupling system with trailing type thermal insulation tile, including：
Heat-insulated tile structure and servo control mechanism；
Heat-insulated tile structure, including：Thermal insulation tile 1, thermal insulation tile 2, thermal insulation tile 3, thermal insulation tile 4, thermal insulation tile 5；
Servo control mechanism, including：One control driver and three electromechanical actuators, every electromechanical actuator are watched including high temperature
Take motor, gear reduction unit, ball screw assembly, Displacement Feedback sensor, operating bar, front journal, rear journal stirrup, procapsid, rear shell
Body, preceding bearing, rear support；
Procapsid, the outer surface of back casing include first side and second side, first side and second side group respectively
Into hollow cavity, first side is U-shaped face, and second side is plane；
Rear support is fixed on the body of aircraft engine, and rear journal stirrup is fixed on rear support, and back casing is fixedly mounted
On rear journal stirrup, high-temperature servo motor is arranged on inside back casing, and the afterbody of high-temperature servo motor is watched close to rear journal stirrup, high temperature
Taking has space between motor afterbody and rear journal stirrup, the input of the output end connection gear decelerator of high-temperature servo motor, ball wire
Thick stick is secondary to be arranged on inside procapsid, and is connected with the output end of the input of ball screw assembly, and gear reduction unit, ball-screw
Secondary output end stretches out procapsid；The output end connection front journal of ball screw assembly,；Front journal is arranged on preceding bearing, preceding bearing
Ring synchronous with the engine of aircraft is connected；
The cross section of procapsid and back casing is U-shaped, and the arcwall face of procapsid and back casing starts close to aircraft
Machine, and have space with the engine of aircraft；
Thermal insulation tile 1 is covered on the U-shaped face of procapsid and back casing, and the shape of thermal insulation tile 1 and procapsid and back casing
U-shaped face surface matching；Thermal insulation tile 2 is covered in the second side of procapsid and back casing；Thermal insulation tile 2 and the nothing of thermal insulation tile 1
Seam connection；Thermal insulation tile 5 is arranged on back casing close to one end of rear support, and thermal insulation tile 5 and thermal insulation tile 1 and the seamless chain of thermal insulation tile 2
Connect；
Thermal insulation tile 3 be both ends open U-shaped cavity body, thermal insulation tile 4 be arranged on thermal insulation tile 3 an open end, and with it is heat-insulated
A watts 3 open end seamless link；The sectional dimension of another open end of thermal insulation tile 3, which is slightly larger than, to be arranged on procapsid
The sectional dimension of thermal insulation tile 1 and thermal insulation tile 2；Thermal insulation tile 4 is arranged on front journal；
When high temperature servo electricity rotates forward or backwards, peace is driven by gear reduction unit, ball screw assembly, front journal band
Preceding bearing on the synchronous ring of aircraft engine, point to the direction of procapsid along back casing or point to rear shell along procapsid
The direction of body is for linear motion；Now, thermal insulation tile 3 and thermal insulation tile 4 can move with the direction of motion of front journal.
It is that the control based on a kind of high synchronism electromechanical coupling system is driven that the high-temperature servo motor rotates forward or backwards
Dynamic device, the control driver include：Communication module, DSP control circuits, multiple drive circuits, A/D converter, DC/DC power supply moulds
Block；
+ 28V the voltage conversions of external power source are three kinds of not independent current sources on ground altogether by DC/DC power modules, be respectively+
5V、+10V、+15V；Communication module receives the instruction of aircraft engine control system, is forwarded to DSP controls under+5V voltages
Circuit；A/D converter, receive the displacement letter of the analog voltage form of the Displacement Feedback sensor feedback of every electromechanical actuator
Number, and after being converted into digital voltage signal, deliver to DSP control circuits；DSP control circuits are according to aircraft engine control system
Instruction and each digital voltage signal, carry out PD control algorithm computing, generation multi-channel control instruction, give it is each driving electricity
Road, drive each high-temperature servo motor to rotate forward or backwards, straight-line displacement is exported by reduction gearing mechanism, while deliver to position
Move feedback transducer and engine (the synchronous ring in engine, synchronous ring are used for adjusting engine jet pipe openings of sizes), displacement
Feedback transducer is converted to straight-line displacement the displacement signal of analog voltage form.
Three electromechanical actuators act in synchronization under same control instruction, the maximal rate of the electromechanical actuator
Under the operating mode that 67mm/s can be reached, the displacement difference of three electromechanical actuators is less than or equal to 0.3mm.
The high-temperature servo motor can bear 200 DEG C of temperature.
The seamless connection is to be connected through a screw thread and adiabatic gum bonding way, can greatly improve the hot close of heat-insulated tile structure
Feng Xing, and then improve overall thermal protective performance.
The thermal insulation tile 3 and section of the open end that thermal insulation tile 1 and thermal insulation tile 2 coordinate slightly larger than thermal insulation tile 1 and thermal insulation tile 2
Size, 0.2mm gap be present, enable the relative insulation watt 1 of thermal insulation tile 3 and before thermal insulation tile 2 points to front journal along back casing
The direction of housing is for linear motion along the direction of procapsid sensing back casing, while ensures the heat sealability of heat-insulated tile structure,
Improve overall thermal protective performance.
The present invention compared with prior art the advantages of be：
(1) present invention realizes thermal insulation tile with electromechanical actuator by thermal insulation tile and electromechanical actuator integrated design scheme
It is flexible and stretch, thermal insulation tile coats completely in guarantee electromechanical actuator telescopic process, greatly improves thermal protective performance, realizes machine
Motor-driven cylinder continuous work 1h in 400 DEG C of high thermal environments；
(2) screw thread and adiabatic gum are passed through between thermal insulation tile 1, thermal insulation tile 2, thermal insulation tile 5 and between thermal insulation tile 3, thermal insulation tile 4
Fastening, the heat sealability of heat-insulated tile structure is improved, realize electromechanical actuator continuous work 1h in 400 DEG C of high thermal environments；
(3) 0.2mm gap between thermal insulation tile 3 and thermal insulation tile 1, thermal insulation tile 2 be present, thermal insulation tile 3 being capable of relative insulation watt 1
The direction of procapsid is pointed to front journal along back casing or make straight line fortune along the direction of procapsid sensing back casing with thermal insulation tile 2
It is dynamic, while the heat sealability of heat-insulated tile structure is ensure that, overall thermal protective performance is improved, realizes electromechanical actuator in 400 DEG C of height
Continuously work 1h in thermal environment.
(4) traditional thermal protection mode coating is not easy to fasten, is also easy to produce fifth wheel, cause aircraft without solid shape
Engine failure, the thermal insulation tile that the present invention designs is that machine adds part, is fastened by screw thread and adiabatic gum, fastens convenient and reliable, nothing
Fifth wheel hidden danger；
(5) three electromechanical actuators act in synchronization under same control instruction, the maximum of the electromechanical actuator
Speed can reach under 67mm/s operating mode, and the displacement difference of three electromechanical actuators is less than or equal to 0.3mm；
Brief description of the drawings
Fig. 1 is electromechanical coupling system schematic diagram of the present invention；
Fig. 2 is the layout of three electromechanical actuators of the invention on the engine；
Fig. 3 is laid out for thermal insulation tile of the present invention；
Fig. 4 is the detailed structure view of electromechanical actuator of the present invention and thermal insulation tile；
Gap figures of the Fig. 5 between thermal insulation tile 3 of the present invention and thermal insulation tile 1, thermal insulation tile 2；
Fig. 6 is thermal insulation tile inwall temperature rise curve of the present invention；
Fig. 7 is present invention control driver detailed schematic block diagram.
Embodiment
The present invention basic ideas be：A kind of high synchronism electromechanical coupling system with trailing type thermal insulation tile, applied to certain
The jet pipe opening regulation of aircraft engine, by being servo-actuated light rigidity ceramic insulation watt and electromechanical actuator integrated design,
Enable electromechanical actuator in 400 DEG C of high thermal environments of engine environment continuously work 1h.The electromechanical servo machine of the present invention
Structure controls the system schema of three electromechanical actuators using a control driver simultaneously, passes through position-ring of speed-electric current three
Control ensures the high synchronism of three electromechanical actuator output actions.Electromechanical actuator is arranged near engine jet pipe, heat-insulated
Watt electromechanical actuator surface is coated on by screw thread and adiabatic gum, can with the flexible and flexible of the output end of electromechanical coupling system,
Cladding completely is realized, the resistance to elevated temperatures of electromechanical coupling system greatly improved.
The present invention proposes thermal insulation tile and electromechanical actuator integrated design scheme, thermal insulation tile be divided into it is fixed (thermal insulation tile 1, every
Heat watt 2, thermal insulation tile 5) with being servo-actuated (thermal insulation tile 3, thermal insulation tile 4) two parts, thermal insulation tile 3 and thermal insulation tile 4 can be defeated with electromechanical actuator
Go out the flexible of end and stretch, and ensure to coat electromechanical actuator in telescopic process completely, realize electromechanical actuator in 400 DEG C of height
Continuously work 1h in thermal environment；
The present invention is described in further detail with specific embodiment below in conjunction with the accompanying drawings.
As shown in Figure 1 and Figure 2, electromechanical servo system of the present invention is mainly by the electromechanical actuator with trailing type thermal insulation tile and control
Driver two large divisions composition processed, a control driver control three electromechanical actuators simultaneously.
As shown in figure 3, electromechanical actuator is sensed by high-temperature servo motor, gear reduction unit, ball screw assembly, Displacement Feedback
Device, operating bar, front journal, rear journal stirrup, procapsid, back casing, preceding bearing, rear support composition, rear journal stirrup and rear support are arranged on
On engine, back casing is connected with rear journal stirrup, and high-temperature servo motor is arranged on back casing, passes through gear reduction unit, ball wire
Thick stick is secondary, the transmission of operating bar, drives front journal, preceding bearing to point to the direction of procapsid along back casing or point to rear shell along procapsid
The direction of body is for linear motion, so as to drive synchronous ring to move forward and backward.Three electromechanical actuators promote synchronous ring simultaneously, realize hair
Motivation jet pipe openings of sizes is adjusted.
As shown in figure 4, thermal insulation tile 1, thermal insulation tile 2 are fixed on actuator procapsid and back casing, thermal insulation tile 5 be fixed on
On the connected rear journal stirrup of engine, fastened with thermal insulation tile 1, thermal insulation tile 2 by screw thread and adiabatic gum, thermal insulation tile 3, thermal insulation tile 4 are solid
It is scheduled on front journal, points to the direction of procapsid along back casing with front journal or make straight line along the direction of procapsid sensing back casing
Motion.
As shown in figure 5, gap is 0.2mm between thermal insulation tile 3 and thermal insulation tile 1, thermal insulation tile 2, experiment shows：This gap amount can
Ensure that thermal insulation tile 3 will not produce frictional resistance, while gap value very little with thermal insulation tile 1,2 when being moved along a straight line with front journal, ensure
The heat seal effect of whole heat-insulated tile structure, realize electromechanical actuator continuous work 1h in 400 DEG C of high thermal environments.
Heat-barrier material selection rigid ceramic thermal insulation tile, its Thermal Parameter are as shown in table 1.
The rigid ceramic thermal insulation tile Thermal Parameter of table 1
Continue to calculate for 1 hour by the heat-insulated tilt sickness 15mm of rigid ceramic, 400 DEG C of outer surface high temperature, its inner surface can be obtained most
High-temperature meets to require up to 97 DEG C.Because thermal protection is irregular eutectic, theoretical calculation is not accurate enough, therefore presses outer surface 400
DEG C high temperature continues 1 hour thermal environment condition and thermal protection profile carries out thermodynamics emulation to it, as a result as shown in Figure 6, it is known that heat
Overcoat inner surface maximum temperature is about 104 DEG C, and the element such as high-temperature servo motor can bear 200 DEG C of high temperature, meet thermal protection
It is required that.Finally heat run experiment, the high synchronism electromechanical servo machine of the invention with trailing type thermal insulation tile are carried out by true thermal environment
Structure in test normal work, meets thermal protection requirement.
The rigid ceramic thermal insulation tile density that the present invention uses is small (0.33g/cm3), therefore the light weight of heat-insulated tile structure, only
For 1/5 or so of traditional thermal protection scheme.
As shown in fig. 7, it is by a kind of high synchronism electromechanical coupling system that high-temperature servo motor rotates forward or backwards
Driver is controlled to realize, the control driver includes：Communication module, DSP control circuits, multiple drive circuits (for concise statement,
In figure only draw one), A/D converter, DC/DC power modules；
+ 28V the voltage conversions of external power source are three kinds of not independent current sources on ground altogether by DC/DC power modules, be respectively+
5V、+10V、+15V；Communication module receives the instruction of aircraft engine control system under+5V voltages, and electricity is changed through RS422
Road is forwarded to DSP control circuits；A/D converter receives the analog voltage of the angle feed-back sensor feedback of every electromechanical actuator
The displacement signal of form, and after being converted into digital voltage signal, deliver to DSP control circuits；DSP control circuits are sent out according to aircraft
The instruction of motivation control system and each digital voltage signal, carry out PD control algorithm computing, generation multi-channel PWM pulsewidth modulation letter
Number and F/R rotating control instructions, give each drive circuit, drive circuit receives HA, HB, HC three-phase position signal, passes through
Driving A, B, C three-phase current driving high-temperature servo motor rotate forward or backwards；
Wherein, 32 fixed-point dsps of DSP control circuits main control chip type selecting TI companies
TMS320F2812, system processing power reaches 150MIPS, is the Digital Signal Processing that TI companies aim at motor control exploitation
Device, its code and the 24X series of digital signals processors of previous generation motor controls are completely compatible, while have Digital Signal Processing
The characteristics of device and microcontroller.That A/D converter is selected is the AD7891 of AD companies, is a 8 passage, the data acquisition of 12
System, parallel interface or serial line interface may be selected, standard control input and fast data access time response can be provided, with
DSP can realize light interface.That RS422 change-over circuits are selected is the ADM2682 of AD companies, and the device has built-in 5kVrms
Isolated DC-DC integrated power supply, it is not necessary to use outside DC-DC isolation module, simplify circuit design, and traffic rate can be with
Reach 16Mbps.
The control algolithm for controlling driver to use is PD control algorithm, and its principle is：DSP controls aircraft engine
It is poor that the displacement signal of the instruction of system and the analog voltage form of angle feed-back sensor feedback is made, and obtains error signal e (preceding once
Error be denoted as e0, this error is denoted as e1), error signal and proportionality coefficient kp set in advance and differential coefficient kd computings,
Controlled quentity controlled variable U is obtained, its calculation formula is：
U=kp*e1+kd* (e1-e0) (1)
In formula, U is the controlled quentity controlled variable being calculated；
Kp is proportionality coefficient, and span is 30~50, preferably kp=43；
Kd is differential coefficient, and span is 50~100, preferably kd=87；
E1 is this error；
E0 is previous error；
Control driver to generate PWM pulse-width signals according to controlled quentity controlled variable U size, given birth to according to controlled quentity controlled variable U sign
Into F/R rotating control instructions, each drive circuit is given, drives high-temperature servo motor rotating.
According to above-mentioned control algolithm and preferred scheme, three electromechanical actuators move in synchronization under same control instruction
Make, the maximal rate of the electromechanical actuator can reach under 67mm/s operating mode, and the displacement difference of three electromechanical actuators is less than
Equal to 0.3mm.
Non-elaborated part of the present invention belongs to techniques well known.
Claims (6)
- A kind of 1. high synchronism electromechanical coupling system with trailing type thermal insulation tile, it is characterised in that including：Heat-insulated tile structure and watch Take mechanism；Heat-insulated tile structure, including：Thermal insulation tile 1, thermal insulation tile 2, thermal insulation tile 3, thermal insulation tile 4, thermal insulation tile 5；Servo control mechanism, including：One control driver and three electromechanical actuators, every electromechanical actuator include high temperature servo electricity It is machine, gear reduction unit, ball screw assembly, Displacement Feedback sensor, operating bar, front journal, rear journal stirrup, procapsid, back casing, preceding Bearing, rear support；Procapsid, the outer surface of back casing include first side and second side respectively, during first side and second side form Cavity body, first side are U-shaped face, and second side is plane；Rear support is fixed on the body of the engine of aircraft, and rear journal stirrup is fixed on rear support, and back casing is fixedly mounted on Afterwards on journal stirrup, high-temperature servo motor is arranged on inside back casing, and the afterbody of high-temperature servo motor is close to rear journal stirrup, high temperature servo There are space, the input of the output end connection gear decelerator of high-temperature servo motor, ball-screw between motor afterbody and rear journal stirrup Pair is arranged on inside procapsid, and the output end of the input of ball screw assembly, and gear reduction unit connects, ball screw assembly, Output end stretches out procapsid；The output end connection front journal of ball screw assembly,；Front journal is arranged on preceding bearing, and preceding bearing is with flying The synchronous ring of the engine of row device is connected；The cross section of procapsid and back casing is U-shaped, the hair of the first side of procapsid and back casing close to aircraft Motivation, and have space with the engine of aircraft；Thermal insulation tile 1 is covered on the U-shaped face of procapsid and back casing, and the shape of thermal insulation tile 1 and procapsid and back casing is U-shaped The surface matching in face；Thermal insulation tile 2 is covered in the second side of procapsid and back casing；Thermal insulation tile 2 and 1 seamless company of thermal insulation tile Connect；Thermal insulation tile 5 is arranged on back casing close to one end of rear support, and thermal insulation tile 5 is seamlessly connected with thermal insulation tile 1 and thermal insulation tile 2；Thermal insulation tile 3 be both ends open U-shaped cavity body, thermal insulation tile 4 be arranged on thermal insulation tile 3 an open end, and with thermal insulation tile 3 One open end is seamlessly connected；The sectional dimension of another open end of thermal insulation tile 3 is slightly larger than respectively to be arranged on procapsid The sectional dimension of thermal insulation tile 1 and thermal insulation tile 2；Thermal insulation tile 4 is arranged on front journal；When high-temperature servo motor rotates forward or backwards, drive and be arranged on by gear reduction unit, ball screw assembly, front journal Preceding bearing on the synchronous ring of the engine of aircraft, point to the direction of procapsid along back casing or point to back casing along procapsid Direction it is for linear motion；Now, thermal insulation tile 3 and thermal insulation tile 4 can move with the direction of motion of front journal.
- A kind of 2. high synchronism electromechanical coupling system with trailing type thermal insulation tile according to claim 1, it is characterised in that： The high-temperature servo motor rotates forward or backwards to be realized by a kind of control driver of high synchronism electromechanical coupling system, The control driver includes：Communication module, DSP control circuits, multiple drive circuits, A/D converter, DC/DC power modules；+ 28V the voltage conversions of external power source are three kinds of not independent current sources on ground altogether by DC/DC power modules, be respectively+5V ,+ 10V、+15V；Communication module receives the instruction of the engine control system of aircraft under+5V voltages, is forwarded to DSP control electricity Road；A/D converter, the displacement signal of the analog voltage form of the Displacement Feedback sensor feedback of every electromechanical actuator is received, And after being converted into digital voltage signal, deliver to DSP control circuits；DSP control circuits are according to the engine control system of aircraft Instruction and each digital voltage signal, carry out PD control algorithm computing, generation multi-channel control instruction, give it is each driving electricity Road, drive each high-temperature servo motor to rotate forward or backwards, straight-line displacement is exported by reduction gearing mechanism, while deliver to position The engine of feedback transducer and aircraft is moved, Displacement Feedback sensor is converted to straight-line displacement the displacement of analog voltage form Signal.
- A kind of 3. high synchronism electromechanical coupling system with trailing type thermal insulation tile according to claim 2, it is characterised in that： Three electromechanical actuators act in synchronization under same control instruction, and the maximal rate of the electromechanical actuator can Under the operating mode for reaching 67mm/s, the displacement difference of three electromechanical actuators is less than or equal to 0.3mm.
- A kind of 4. high synchronism electromechanical coupling system with trailing type thermal insulation tile according to claim 1, it is characterised in that： The high-temperature servo motor can bear 200 DEG C of temperature.
- A kind of 5. high synchronism electromechanical coupling system with trailing type thermal insulation tile according to claim 1, it is characterised in that： The seamless connection is to be connected through a screw thread or adiabatic gum bonding way.
- A kind of 6. high synchronism electromechanical coupling system with trailing type thermal insulation tile according to claim 1, it is characterised in that： The open end that the thermal insulation tile 3 coordinates with thermal insulation tile 1 and thermal insulation tile 2 is respectively slightly larger than thermal insulation tile 1 and the section chi of thermal insulation tile 2 Very little, the open end that thermal insulation tile 3 coordinates with thermal insulation tile 1 and thermal insulation tile 2 exists with the sectional dimension of thermal insulation tile 1 and thermal insulation tile 2 respectively 0.2mm gap, the relative insulation watt 1 of thermal insulation tile 3 and thermal insulation tile 2 is set to point to the direction of procapsid along back casing with front journal Or it is for linear motion along the direction of procapsid sensing back casing, while ensure the heat sealability of heat-insulated tile structure.
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| CN201510890502.0A CN105515251B (en) | 2015-12-07 | 2015-12-07 | A kind of high synchronism electromechanical coupling system with trailing type thermal insulation tile |
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| CN106502161B (en) * | 2016-11-11 | 2023-10-27 | 北京精密机电控制设备研究所 | Three-channel flow regulation control method, device and servo control driving system |
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| US8304969B2 (en) * | 2010-01-13 | 2012-11-06 | Asia Vital Components Co., Ltd. | Heat insulation structure for cooling fan |
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| CN204481641U (en) * | 2015-01-22 | 2015-07-15 | 珠海格力电器股份有限公司 | Motor housing and servo motor |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| JP4140082B2 (en) * | 1998-05-08 | 2008-08-27 | 株式会社安川電機 | Servomotor |
| JP6114144B2 (en) * | 2013-08-21 | 2017-04-12 | 東洋ゴム工業株式会社 | Wall surface construction method |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE102005000642A1 (en) * | 2004-01-14 | 2005-08-04 | Caterpillar Inc., Peoria | Cooling system for an electric motor |
| CN101315548A (en) * | 2007-05-29 | 2008-12-03 | 欧颖国际有限公司 | Devices and methods for controlling servomotor |
| US8304969B2 (en) * | 2010-01-13 | 2012-11-06 | Asia Vital Components Co., Ltd. | Heat insulation structure for cooling fan |
| CN204481641U (en) * | 2015-01-22 | 2015-07-15 | 珠海格力电器股份有限公司 | Motor housing and servo motor |
| CN104682655A (en) * | 2015-03-24 | 2015-06-03 | 上海新跃仪表厂 | Power component and transmission mechanism integrated servo mechanism |
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