CN105515251A - High-synchronism electromechanical servo mechanism with follow-up heat insulation tiles - Google Patents
High-synchronism electromechanical servo mechanism with follow-up heat insulation tiles Download PDFInfo
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- CN105515251A CN105515251A CN201510890502.0A CN201510890502A CN105515251A CN 105515251 A CN105515251 A CN 105515251A CN 201510890502 A CN201510890502 A CN 201510890502A CN 105515251 A CN105515251 A CN 105515251A
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- thermal insulation
- insulation tile
- procapsid
- electromechanical
- back casing
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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)
- Transmission Devices (AREA)
Abstract
The invention relates to a high-synchronism electromechanical servo mechanism with follow-up heat insulation tiles, and the servo mechanism is applied for adjusting a nozzle opening of one aircraft engine; by adopting an integrated design between follow-up light rigid ceramic heat insulation tiles and an electromechanical actuator, the electromechanical actuator can continuously work for 1h in 400 DEG C of high temperature environment near the engine. The electromechanical servo mechanism adopts a system scheme of one control and drive device simultaneously controlling three electromechanical actuators, and the high synchronism of the output actions of the three electromechanical actuators can be ensured through a position-speed-current three-loop control. The electromechanical actuators are arranged near the engine nozzle, the heat insulation tiles are coated on the surfaces of the electromechanical actuators through threads and heat insulation adhesive, the heat insulation tiles can stretch along the output end of the electromechanical servo mechanism to realize a complete covering, and the high temperature resistance of the electromechanical servo mechanism is 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 the electromechanical coupling system technical field for spacecraft engine.
Background technology
Existing electromechanical coupling system is without special heat protection design, and the modes such as coated heat insulation asbestos cloth, alkali-free glass fibre band or metallized film silicon rubber that adopt carry out simple thermal protection more, and there are the following problems for traditional thermal protection method:
The output of electromechanical actuator can be elastic, traditional thermal protection measure only can the standing part of coating machine electric servo, cannot the movable part of coating machine electric servo, therefore cannot realize completely coated, sealing is poor simultaneously, and overall thermal protection effect is not good;
Traditional thermal protection is coated without strict solid shape, or is that strip material is wound around, or cuts out shaping for soft material, and fix finally by strapping, this kind of fastening means is not firm, easily produces fifth wheel, causes engine or servomechanism fault;
Traditional control and drive system is separate to the control algolithm for three electromechanical actuators, after three given identical instructions of electromechanical actuator, there will be asynchronous, makes engine jet pipe clamping stagnation, cause engine or servomechanism fault in motion process;
Summary of the invention
The technical problem that the present invention solves is: overcome prior art cannot follow electromechanical actuator motion, cannot the deficiency of coating machine motor-driven cylinder completely, a kind of high synchronism electromechanical coupling system with trailing type thermal insulation tile is provided, the complete coating machine motor-driven cylinder of thermal insulation tile in electromechanical actuator telescopic process can be ensured, significantly improve 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, comprising: thermal insulation tile structure and servomechanism;
Thermal insulation tile structure, comprising: thermal insulation tile 1, thermal insulation tile 2, thermal insulation tile 3, thermal insulation tile 4, thermal insulation tile 5;
Servomechanism, comprise: a control and drive system and three electromechanical actuators, every platform electromechanical actuator comprises high-temperature servo motor, gear reduction unit, ball screw assembly, Displacement Feedback transducer, operating bar, front journal, rear journal stirrup, procapsid, back casing, front bearing, rear support;
The outer surface of procapsid, back casing comprises the first side and the second side respectively, the first side and the second side composition hollow cavity, and the first side is U-shaped, and the second side is plane;
Rear support is fixed on the body of aircraft engine, rear journal stirrup is fixed on rear support, back casing is fixedly mounted on rear journal stirrup, high-temperature servo motor is arranged on back casing inside, and the afterbody of high-temperature servo motor is near rear journal stirrup, space is had between high-temperature servo motor afterbody and rear journal stirrup, the output of high-temperature servo motor connects the input of gear reduction unit, ball screw assembly, is arranged on procapsid inside, and be connected with the output of gear reduction unit with the input of ball screw assembly, the output of ball screw assembly, stretches out procapsid; The output of ball screw assembly, connects front journal; Front journal is arranged on front bearing, and front bearing is connected with the synchronous ring of the engine of aircraft;
The cross section of procapsid and back casing is U-shaped, and the arcwall face of procapsid and back casing near the engine of aircraft, and has space with the engine of aircraft;
Thermal insulation tile 1 covers on U-shaped of procapsid and back casing, and the surface matching of U-shaped of the shape of thermal insulation tile 1 and procapsid and back casing; Thermal insulation tile 2 covers on the second side of procapsid and back casing; Thermal insulation tile 2 and thermal insulation tile 1 seamless link; Thermal insulation tile 5 is arranged on back casing one end near rear support, and thermal insulation tile 5 and thermal insulation tile 1 and thermal insulation tile 2 seamless link;
Thermal insulation tile 3 is the U-shaped cavity of both ends open, and thermal insulation tile 4 is arranged on an open end of thermal insulation tile 3, and with an open end seamless link of thermal insulation tile 3; The sectional dimension of another open end of thermal insulation tile 3 is slightly larger than the sectional dimension of the thermal insulation tile 1 be arranged on procapsid and thermal insulation tile 2; Thermal insulation tile 4 is arranged on front journal;
When high temperature servo electricity rotates forward or backwards, driven bearing before in the synchronous ring being arranged on aircraft engine by gear reduction unit, ball screw assembly, front journal band, point to the direction of procapsid along back casing or point to the direction moving linearly of back casing along procapsid; Now, thermal insulation tile 3 and thermal insulation tile 4 can move with the direction of motion of front journal.
It is control and drive system based on a kind of high synchronism electromechanical coupling system that described high-temperature servo motor is rotated forward or backwards, and this control and drive system comprises: communication module, DSP control circuit, multiple drive circuit, A/D converter, DC/DC power module;
+ the 28V of external power source voltage transitions is the independent current source on three kinds of not ground altogether by DC/DC power module, is respectively+5V ,+10V ,+15V; Communication module, under+5V voltage, receives the instruction of aircraft engine control system, is forwarded to DSP control circuit; A/D converter, receives the displacement signal of the analog voltage form of the Displacement Feedback sensor feedback of every platform electromechanical actuator, and after converting digital voltage signal to, delivers to DSP control circuit; DSP control circuit is according to the instruction of aircraft engine control system and each digital voltage signal, carry out the computing of PD control algolithm, generate multi-channel control instruction, give each drive circuit, each high-temperature servo motor is driven to rotate forward or backwards, straight-line displacement is exported by reduction gearing mechanism, deliver to Displacement Feedback transducer and the engine (synchronous ring in engine simultaneously, synchronous ring is used for regulating engine jet pipe openings of sizes), straight-line displacement is converted to the displacement signal of analog voltage form by Displacement Feedback transducer.
Three electromechanical actuators are in synchronization action under same control command, and under the maximal rate of described electromechanical actuator can reach the operating mode of 67mm/s, the displacement difference of three electromechanical actuators is less than or equal to 0.3mm.
Described high-temperature servo motor can bear the temperature of 200 DEG C.
Described seamless link is threaded connection and adiabatic gum bonding way, significantly can improve the heat sealability of thermal insulation tile structure, and then improve overall thermal barrier propterty.
The open end that described thermal insulation tile 3 coordinates with thermal insulation tile 1 and thermal insulation tile 2 is slightly larger than the sectional dimension of thermal insulation tile 1 and thermal insulation tile 2, there is the gap of 0.2mm, thermal insulation tile 3 relative insulation watt 1 and thermal insulation tile 2 can be pointed to the direction of procapsid with front journal along back casing or points to the direction moving linearly of back casing along procapsid, ensure the heat sealability of thermal insulation tile structure simultaneously, improve overall thermal barrier propterty.
The present invention's advantage is compared with prior art:
(1) the present invention is by thermal insulation tile and electromechanical actuator integrated design scheme, realize thermal insulation tile to stretch with the flexible of electromechanical actuator, ensure that in electromechanical actuator telescopic process, thermal insulation tile is completely coated, significantly improve thermal protective performance, realize electromechanical actuator continuous operation 1h in 400 DEG C of high-temperature hot environment;
(2) between thermal insulation tile 1, thermal insulation tile 2, thermal insulation tile 5 and thermal insulation tile 3, between thermal insulation tile 4 by screw thread and adiabatic gum fastening, improve the heat sealability of thermal insulation tile structure, realize electromechanical actuator continuous operation 1h in 400 DEG C of high-temperature hot environment;
(3) there is the gap of 0.2mm between thermal insulation tile 3 and thermal insulation tile 1, thermal insulation tile 2, thermal insulation tile 3 relative insulation watt 1 and thermal insulation tile 2 can point to the direction of procapsid with front journal along back casing or points to the direction moving linearly of back casing along procapsid, ensure that the heat sealability of thermal insulation tile structure simultaneously, improve overall thermal barrier propterty, realize electromechanical actuator continuous operation 1h in 400 DEG C of high-temperature hot environment.
(4) traditional thermal protection mode coating is without solid shape, not easily fastening, easily produces fifth wheel, cause aircraft engine fault, the thermal insulation tile of the present invention's design is machine and adds part, by screw thread and adiabatic gum fastening, fastening convenient and reliable, without fifth wheel hidden danger;
(5) three electromechanical actuators are in synchronization action under same control command, and under the maximal rate of described electromechanical actuator can reach the operating mode of 67mm/s, the displacement difference of three electromechanical actuators is less than or equal to 0.3mm;
Accompanying drawing explanation
Fig. 1 is electromechanical coupling system schematic diagram of the present invention;
Fig. 2 is the present invention's three electromechanical actuators layouts on the engine;
Fig. 3 is thermal insulation tile layout of the present invention;
Fig. 4 is the detailed structure view of electromechanical actuator of the present invention and thermal insulation tile;
Fig. 5 is the gap figure 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 control and drive system detailed schematic block diagram of the present invention.
Embodiment
Basic ideas of the present invention are: a kind of high synchronism electromechanical coupling system with trailing type thermal insulation tile, the jet pipe opening being applied to certain aircraft engine regulates, by servo-actuated light rigidity ceramic insulation watt and electromechanical actuator integrated design, make electromechanical actuator can in engine environment 400 DEG C of high-temperature hot environment continuous operation 1h.Electromechanical coupling system of the present invention adopts a control and drive system to control the system schema of three electromechanical actuators simultaneously, is ensured 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, thermal insulation tile is coated on electromechanical actuator surface by screw thread and adiabatic gum, can stretch with the flexible of the output of electromechanical coupling system, realize completely coated, significantly improve the resistance to elevated temperatures of electromechanical coupling system.
The present invention proposes thermal insulation tile and electromechanical actuator integrated design scheme, thermal insulation tile is divided into fixing (thermal insulation tile 1, thermal insulation tile 2, thermal insulation tile 5) and servo-actuated (thermal insulation tile 3, thermal insulation tile 4) two parts, thermal insulation tile 3 and thermal insulation tile 4 can stretch with the flexible of electromechanical actuator output, and ensure complete coating machine motor-driven cylinder in telescopic process, realize electromechanical actuator continuous operation 1h in 400 DEG C of high-temperature hot environment;
Below in conjunction with the drawings and specific embodiments, the present invention is described in further detail.
As shown in Figure 1 and Figure 2, electromechanical servo system of the present invention is primarily of electromechanical actuator and the control and drive system two large divisions composition of being with trailing type thermal insulation tile, and a control and drive system controls three electromechanical actuators simultaneously.
As shown in Figure 3, electromechanical actuator is by high-temperature servo motor, gear reduction unit, ball screw assembly, Displacement Feedback transducer, operating bar, front journal, rear journal stirrup, procapsid, back casing, front bearing, rear support forms, rear journal stirrup and rear support are installed on the engine, back casing and rear journal stirrup are connected, high-temperature servo motor is arranged on back casing, pass through gear reduction unit, ball screw assembly, the transmission of operating bar, drive front journal, front bearing points to the direction of procapsid along back casing or points to the direction moving linearly of back casing along procapsid, thus drive synchronous ring to seesaw.Three electromechanical actuators promote synchronous ring simultaneously, realize engine jet pipe openings of sizes and regulate.
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 is fixed on the rear journal stirrup that is connected with engine, with thermal insulation tile 1, thermal insulation tile 2 by screw thread and adiabatic gum fastening, thermal insulation tile 3, thermal insulation tile 4 are fixed on front journal, point to the direction of procapsid or the direction moving linearly along procapsid sensing back casing with front journal along back casing.
As shown in Figure 5, between thermal insulation tile 3 and thermal insulation tile 1, thermal insulation tile 2, gap is 0.2mm, test shows: this gap amount can ensure that thermal insulation tile 3 can not produce frictional resistance with thermal insulation tile 1,2 with during front journal rectilinear motion, gap value is very little simultaneously, ensure that the heat seal effect of whole thermal insulation tile structure, realize electromechanical actuator continuous operation 1h in 400 DEG C of high-temperature hot environment.
Rigid ceramic thermal insulation tile selected by heat-barrier material, and its Thermal Parameter is as shown in table 1.
Table 1 rigid ceramic thermal insulation tile Thermal Parameter
Continue to calculate for 1 hour by rigid ceramic thermal insulation tile thickness 15mm, outer surface 400 DEG C of high temperature, its inner surface maximum temperature can be obtained and reach 97 DEG C, meet the demands.Because thermal protection is irregular eutectic, theory calculate is accurate not, therefore by the lasting 1 hour thermal environment condition of outer surface 400 DEG C of high temperature and thermal protection profile, thermodynamics emulation is carried out to it, result as shown in Figure 6, known thermal protection shield inner surface maximum temperature is about 104 DEG C, and the elements such as high-temperature servo motor can bear 200 DEG C of high temperature, meet thermal protection requirement.Finally carry out heat run test by true thermal environment, the high synchronism electromechanical coupling system of band trailing type thermal insulation tile of the present invention normally works in test, meets thermal protection requirement.
The rigid ceramic thermal insulation tile density little (0.33g/cm3) that the present invention adopts, therefore the quality of thermal insulation tile structure is light, is only about 1/5 of traditional thermal protection scheme.
As shown in Figure 7, it is that control and drive system by a kind of high synchronism electromechanical coupling system realizes that high-temperature servo motor is rotated forward or backwards, this control and drive system comprises: communication module, DSP control circuit, multiple drive circuit (be simple and clear statement, only draw in figure), A/D converter, DC/DC power module;
+ the 28V of external power source voltage transitions is the independent current source on three kinds of not ground altogether by DC/DC power module, is respectively+5V ,+10V ,+15V; Communication module, under+5V voltage, receives the instruction of aircraft engine control system, is forwarded to DSP control circuit through RS422 change-over circuit; A/D converter receives the displacement signal of the analog voltage form of the angle feed-back sensor feedback of every platform electromechanical actuator, and after converting digital voltage signal to, delivers to DSP control circuit; DSP control circuit is according to the instruction of aircraft engine control system and each digital voltage signal, carry out the computing of PD control algolithm, generate multi-channel PWM pulse-width signal and F/R rotating control command, give each drive circuit, drive circuit receives HA, HB, HC three-phase position signal, drives high-temperature servo motor to rotate forward or backwards by driving A, B, C three-phase current;
Wherein, 32 fixed-point dsp TMS320F2812 of DSP control circuit main control chip type selecting TI company, system processing power reaches 150MIPS, it is the digital signal processor that TI company aims at Electric Machine Control exploitation, the 24X series of digital signals processor of its code and previous generation Electric Machine Control is completely compatible, has the feature of digital signal processor and microcontroller simultaneously.The AD7891 of what A/D converter was selected is AD company, is a 8 passages, the data acquisition system of 12, can selects parallel interface or serial line interface, all can provide standard control inputs and fast data access time response, can realize light interface with DSP.The ADM2682 of what RS422 change-over circuit was selected is AD company, this device has built-in 5kVrms isolated DC-DC integrated power supply, do not need to adopt outside DC-DC isolation module, simplify circuit design, and traffic rate can reach 16Mbps.
The control algolithm that control and drive system adopts is PD control algolithm, its principle is: DSP is by poor for the displacement signal of the analog voltage form of the instruction of aircraft engine control system and angle feed-back sensor feedback, (previous error is denoted as e0 to obtain error signal e, this error is denoted as e1), error signal and the proportionality coefficient kp preset and differential coefficient kd computing, obtain controlled quentity controlled variable U, its computing formula is:
U＝kp*e1+kd*(e1-e0)(1)
In formula, U is the controlled quentity controlled variable calculated;
Kp is proportionality coefficient, and span is 30 ~ 50, preferred kp=43;
Kd is differential coefficient, and span is 50 ~ 100, preferred kd=87;
E1 is this error;
E0 is previous error;
Control and drive system generates PWM pulse-width signal according to the size of controlled quentity controlled variable U, generates F/R rotating control command, gives each drive circuit, drive high-temperature servo motor rotating according to the sign of controlled quentity controlled variable U.
According to above-mentioned control algolithm and preferred version, three electromechanical actuators are in synchronization action under same control command, and under the maximal rate of described electromechanical actuator can reach the operating mode of 67mm/s, the displacement difference of three electromechanical actuators is less than or equal to 0.3mm.
Non-elaborated part of the present invention belongs to techniques well known.
Claims (6)
1. the high synchronism electromechanical coupling system with trailing type thermal insulation tile, is characterized in that comprising: thermal insulation tile structure and servomechanism;
Thermal insulation tile structure, comprising: thermal insulation tile 1, thermal insulation tile 2, thermal insulation tile 3, thermal insulation tile 4, thermal insulation tile 5;
Servomechanism, comprise: a control and drive system and three electromechanical actuators, every platform electromechanical actuator comprises high-temperature servo motor, gear reduction unit, ball screw assembly, Displacement Feedback transducer, operating bar, front journal, rear journal stirrup, procapsid, back casing, front bearing, rear support;
The outer surface of procapsid, back casing comprises the first side and the second side respectively, the first side and the second side composition hollow cavity, and the first side is U-shaped, and the second side is plane;
Rear support is fixed on the body of aircraft engine, rear journal stirrup is fixed on rear support, back casing is fixedly mounted on rear journal stirrup, high-temperature servo motor is arranged on back casing inside, and the afterbody of high-temperature servo motor is near rear journal stirrup, space is had between high-temperature servo motor afterbody and rear journal stirrup, the output of high-temperature servo motor connects the input of gear reduction unit, ball screw assembly, is arranged on procapsid inside, and be connected with the output of gear reduction unit with the input of ball screw assembly, the output of ball screw assembly, stretches out procapsid; The output of ball screw assembly, connects front journal; Front journal is arranged on front bearing, and front bearing is connected with the synchronous ring of the engine of aircraft;
The cross section of procapsid and back casing is U-shaped, and the arcwall face of procapsid and back casing near the engine of aircraft, and has space with the engine of aircraft;
Thermal insulation tile 1 covers on U-shaped of procapsid and back casing, and the surface matching of U-shaped of the shape of thermal insulation tile 1 and procapsid and back casing; Thermal insulation tile 2 covers on the second side of procapsid and back casing; Thermal insulation tile 2 and thermal insulation tile 1 seamless link; Thermal insulation tile 5 is arranged on back casing one end near rear support, and thermal insulation tile 5 and thermal insulation tile 1 and thermal insulation tile 2 seamless link;
Thermal insulation tile 3 is the U-shaped cavity of both ends open, and thermal insulation tile 4 is arranged on an open end of thermal insulation tile 3, and with an open end seamless link of thermal insulation tile 3; The sectional dimension of another open end of thermal insulation tile 3 is slightly larger than the sectional dimension of the thermal insulation tile 1 be arranged on procapsid and thermal insulation tile 2; Thermal insulation tile 4 is arranged on front journal;
When high temperature servo electricity rotates forward or backwards, driven bearing before in the synchronous ring being arranged on aircraft engine by gear reduction unit, ball screw assembly, front journal, point to the direction of procapsid along back casing or point to the direction moving linearly of back casing along procapsid; Now, thermal insulation tile 3 and thermal insulation tile 4 can move with the direction of motion of front journal.
2. a kind of high synchronism electromechanical coupling system with trailing type thermal insulation tile according to claim 1, it is characterized in that: it is that control and drive system by a kind of high synchronism electromechanical coupling system realizes that described high-temperature servo motor is rotated forward or backwards, and this control and drive system comprises: communication module, DSP control circuit, multiple drive circuit, A/D converter, DC/DC power module;
+ the 28V of external power source voltage transitions is the independent current source on three kinds of not ground altogether by DC/DC power module, is respectively+5V ,+10V ,+15V; Communication module, under+5V voltage, receives the instruction of aircraft engine control system, is forwarded to DSP control circuit; A/D converter, receives the displacement signal of the analog voltage form of the Displacement Feedback sensor feedback of every platform electromechanical actuator, and after converting digital voltage signal to, delivers to DSP control circuit; DSP control circuit is according to the instruction of aircraft engine control system and each digital voltage signal, carry out the computing of PD control algolithm, generate multi-channel control instruction, give each drive circuit, each high-temperature servo motor is driven to rotate forward or backwards, export straight-line displacement by reduction gearing mechanism, deliver to Displacement Feedback transducer and engine simultaneously, straight-line displacement is converted to the displacement signal of analog voltage form by Displacement Feedback transducer.
3. a kind of high synchronism electromechanical coupling system with trailing type thermal insulation tile according to claim 2, it is characterized in that: described three electromechanical actuators are in synchronization action under same control command, under the maximal rate of described electromechanical actuator can reach the operating mode of 67mm/s, the displacement difference of three electromechanical actuators is less than or equal to 0.3mm.
4. a kind of high synchronism electromechanical coupling system with trailing type thermal insulation tile according to claim 1, is characterized in that: described high-temperature servo motor can bear the temperature of 200 DEG C.
5. a kind of high synchronism electromechanical coupling system with trailing type thermal insulation tile according to claim 1, is characterized in that: described seamless link is threaded connection and adiabatic gum bonding way.
6. a kind of high synchronism electromechanical coupling system with trailing type thermal insulation tile according to claim 1, it is characterized in that: the open end that described thermal insulation tile 3 coordinates with thermal insulation tile 1 and thermal insulation tile 2 is slightly larger than the sectional dimension of thermal insulation tile 1 and thermal insulation tile 2, there is the gap of 0.2mm, thermal insulation tile 3 relative insulation watt 1 and thermal insulation tile 2 can be pointed to the direction of procapsid with front journal along back casing or point to the direction moving linearly of back casing along procapsid, ensure the heat sealability of thermal insulation tile structure simultaneously.
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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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| 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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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN106502161A (en) * | 2016-11-11 | 2017-03-15 | 北京精密机电控制设备研究所 | Triple channel Flow-rate adjustment control method and SERVO CONTROL drive system |
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| JPH11332180A (en) * | 1998-05-08 | 1999-11-30 | Yaskawa Electric Corp | Servomotor |
| DE102005000642A1 (en) * | 2004-01-14 | 2005-08-04 | Caterpillar Inc., Peoria | Cooling system for an electric motor |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN106502161A (en) * | 2016-11-11 | 2017-03-15 | 北京精密机电控制设备研究所 | Triple channel Flow-rate adjustment control method and SERVO CONTROL drive system |
| 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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| CN105515251B (en) | 2018-01-05 |
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