CN2473606Y - Injection flow variable water vortex dynamometer - Google Patents
Injection flow variable water vortex dynamometer Download PDFInfo
- Publication number
- CN2473606Y CN2473606Y CN 01223198 CN01223198U CN2473606Y CN 2473606 Y CN2473606 Y CN 2473606Y CN 01223198 CN01223198 CN 01223198 CN 01223198 U CN01223198 U CN 01223198U CN 2473606 Y CN2473606 Y CN 2473606Y
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Abstract
The utility model discloses a dynamometer which is provided with a force measurement mechanism part which is connected on one side of outer shell of the device part. The other side of the device part is connected with a static part. The left and right bearing outer shells and the outer shells of the device part are respectively connected with a water filling part and a water discharging part. A water discharging actuator is connected with the water discharging port in the water filling part and the water discharging part. A rotor and a left and a right side shell cooperating with the rotor are installed on the main shaft of the device part. Blades which form an included angle of 45 degrees with the corresponding end face are provided in the side shells. The utility model provides a changeable charging quantity swirling water dynamometer with stability, reliability, a small volume, a long brake torque, a high measuring accuracy, a high response speed, capability of realizing high accurate transient speed measurement and a more reasonable structure. The utility model overcomes the shortcomings of various dynamometers used in the prior power machine measurement field.
Description
The utility model relates to a kind of power detection device, especially a kind of injection flow variable water vortex dynamometer that changes the size of absorbed power by the pressure that changes water in the dynamometer working chamber.
In engine test industry, the dynamometer of using has electric vortex type, electric power formula, waterpower formula at present.Electric vortex type dynamometer price is expensive than hydraulic dynamometer, and in only limiting to measure, low-powered engine; Electric power formula dynamometer costs an arm and a leg, and the general user can not bear; And hydraulic dynamometer is suitable for the general equal energy of power machine of large, medium and small power and basic, normal, high rotating speed, and the hydraulic dynamometer kind is also more, domestic general have disc type, excellent pillar and eddy current type.Though disc type, excellent pillar price are cheap, measuring accuracy is low, open loop control and structures shape thereof its test unstable, response speed does not wait deficiency soon, though and the gate valve type eddy current dynamometer to have stable testing good, can't obtain response speed faster.
The purpose of this utility model provide a kind of reliable and stable, volume is little, braking moment is big, measuring accuracy is high, response speed is fast, can realize that the high precision transient speed measures, the quick load control of automatically controlled butterfly valve, convenient operating maintenance, structure be the injection flow variable water vortex dynamometer more reasonably.It has overcome the shortcoming that used various dynamometers exist in the existing engine test industry.
The purpose of this utility model is achieved in that it is by airframe components, the force measuring machine parts, advance water drainage part, the draining actuator, compositions such as quiet school parts, one side of the body fuselage of described airframe components is connected with the force measuring machine parts, the opposite side of body fuselage is connected with quiet school parts, the left and right sides bearing shell and the body fuselage of airframe components are connected with into water drainage part respectively, the draining actuator links to each other with freeing port in advancing water drainage part, rotor and associated left and right sides shell are installed on the main shaft of described airframe components, have groove on the two sides of its rotor, be provided with spinner blade in it, also have groove on left and right sides shell and the rotor opposite flank, be provided with blade in it.
The direction blade of described spinner blade and left and right sides shell is opposite, spinner blade and left and right sides shell blade and end face angle at 45 separately.
The lower surface of described spinner blade and left and right sides shell blade and separately end face angle at 45, upper surface becomes 40 ° of angles with separately end face.
The both sides of the main shaft upper rotor part of described airframe components are set with the slit seal axle sleeve, and the gap of 0.1mm～0.3mm is arranged between described slit seal axle sleeve and the main shaft.
The smart casting of spinner blade in the described rotor and rotor one forms, and the smart casting of blade in the left and right sides shell and left and right sides shell one forms, and has inlet opening and air hole on the reinforcement of left and right sides shell blade, is recessed garden arc groove in the middle of the external diameter of rotor.
The brake arm of described force measuring machine parts is fixed on the shell of airframe components, supporting base is fixed on the base of mechanism components, pull pressure sensor links to each other with supporting base with brake arm respectively by the oscillating bearing that is equipped with on the swing bolt up and down, and there are support bar and portable plate in the top of described pull pressure sensor by bolt.
Float with bend pipe and draining support respectively by " O " shape rubber seal and be connected in the described two ends of entering the intake-discharge pipe road of water drainage part.
The motor gear of the motor output end of described draining actuator and duplicate gear engagement, duplicate gear is meshed with sector gear on being contained in valve shaft, one end of valve shaft is equipped with a torsion spring, the other end is set with potentiometer by " O " shape rubber seal, " O " shape rubber seal snare also is housed between potentiometer and the shell, one end of draining actuator shell has the potentiometer adjustment hole, and the below of draining actuator shell has two apopores that communicate with valve shaft.
Cock is equipped with in the lower end of described airframe components shell.
Because the utility model has adopted said structure, obvious improvement and advantage are compared with prior art arranged, specific as follows: structure is more reasonable, moderate, volume is little, braking moment is big, measuring accuracy is high, response speed soon, accurately and reliably, can realize the measurement of high precision transient speed, the quick load control of automatically controlled butterfly valve, reliable and stable, convenient operating maintenance accurately records the power of engine by the pressure that changes water.
The utility model is described in further detail below in conjunction with drawings and Examples.
Fig. 1 is a structural representation of the present utility model;
Fig. 2 is a side view of the present utility model;
Fig. 3 is an airframe components structural representation of the present utility model;
Fig. 4 is a rotor structure synoptic diagram of the present utility model;
Fig. 5 is the A-A cut-open view of Fig. 4;
Fig. 6 is a left and right sides shell structure synoptic diagram of the present utility model;
Fig. 7 is the cut-open view of Fig. 6;
Fig. 8 is the E-E cut-open view of Fig. 6;
Fig. 9 is the C-C cut-open view of Fig. 6;
Figure 10 is a force measuring machine modular construction synoptic diagram of the present utility model;
Figure 11 is the water drainage part structural representation that advances of the present utility model;
Figure 12 is the bend pipe structure synoptic diagram that advances water drainage part of the present utility model;
Figure 13 is the supporting structure synoptic diagram that advances water drainage part of the present utility model;
Figure 14 is a draining actuator structure synoptic diagram of the present utility model.
Among the figure: the parts of the quiet school of 1-; 2-draining actuator; 3-force measuring machine parts; 4-advances water drainage part; The 5-airframe components; The 6-base; 7-Y-axis bearing; The 8-main shaft; The 9-shaft coupling; The 10-bearing plate; The 11-outside framework oil seal; The 12-axle sleeve; 13,14-slit seal axle sleeve; 15-left and right sides bearing shell; 16-left and right sides shell; The 17-plug screw; The 18-rotor; The 19-body fuselage; 20 water shutoff circles; The 21-measure speed gears; The 22-speed probe; The 23-overflow pipe; The 24-cock; The 25-spinner blade; The 26-blade; The 27-air hole; The 28-inlet opening; The 29-brake arm; The 30-pull pressure sensor; The 31-swing bolt; The 32-supporting base; The 33-oscillating bearing; The 34-protective cover; The 35-portable plate; The 36-bolt; The 37-support bar; The 39-permeability cell; The 40-water inlet member; The 41-water drainage part; The 42-bend pipe; The 43-pipeline; The 44-support; 45-" O " shape rubber seal; 46-draining support; The 47-drainage pipeline; The 48-elbow; 49-actuator shell; The 50-motor; The 51-motor gear; The 52-duplicate gear; The 53-sector gear; The 54-valve shaft; The 55-torsion spring; The 56-valve block; The 57-apopore; The 58-potentiometer; 59-" O " shape rubber seal.
This device by airframe components 5, force measuring machine parts 3, advance water drainage part 4, draining actuator 2, quiet school parts 1 and form, wherein airframe components 5 respectively with force measuring machine parts 3, advance water drainage part 4 and link to each other, draining actuator 2 links to each other with freeing port in advancing water drainage part 4, link to each other with airframe components 5 during the quiet school of quiet school parts 1, quiet school parts 1 remove behind the quiet school, load onto corresponding counterbalance weight, total is very compact.
Airframe components 5 is made up of base 6, Y-axis bearing 7, main shaft 8, left and right sides shaft coupling 9, bearing plate 10, outside framework oil seal 11, slit seal axle sleeve 13,14, left and right sides bearing shell 15, left and right sides shell (stator) 16, rotor 18, body fuselage 19, water shutoff circle 20, measure speed gears 21, speed probe 22 etc.Y-axis bearing 7 is fixed on the base 6, by rolling bearing supporting spindle 8, rotor 18 hot jackets are in the middle of main shaft 8, left and right sides shell 16 (also being the stationary part of this device) and left and right sides bearing shell 15 symmetry respectively are installed on rotor 18 both sides, rotor 18 has groove with left and right sides shell 16, evenly arrange in it several spinner blades 25 and blade 26, the spinner blade 25 on the rotor 18 is opposite with blade 26 directions on the left and right sides shell 16.The direction of dynamometer rotor 18, spinner blade 25 and blade 26 separately with its end face angle at 45, be recessed garden arc groove in the middle of rotor 18 external diameters, be convenient to discharge water thus, left and right sides shell (stator) 16 strengthens on the blade reinforcement, have several inlet openings 28 and an air hole 27 on it, inlet opening 28 is used for intaking when surveying engine power, the effect of air hole 27 is discharged air, so that allow water enter in the dynamometer, spinner blade 25, the 26 formation work cup chambeies of rotor 18 and left and right sides shell 16, water forms eddy current in the cup chamber when work; Slit seal axle sleeve 13; 14 are fixed on the both sides of main shaft 8 upper rotor parts 18 of airframe components; slit seal axle sleeve 13; 14 and main shaft 8 between the gap of 0.1mm～0.3mm is arranged; water high speed rotating in the cup chamber forms in the process of eddy current when dynamometer is worked like this; though water shutoff circle 20 is housed in the both sides of main shaft 8; but also having little water overflows; enter in the rolling bearing of the left and right sides; its water inlet is damaged; this structure is at slit seal axle sleeve 13; 14 and main shaft 8 between the gap of 0.1mm～0.3mm is arranged; and on left and right sides bearing shell 15, be provided with overflow pipe 23; the water that overflows like this is from slit seal axle sleeve 13; flow out by overflow pipe 23 in 14 gap; can not damage bearing, play a protective role, slit seal axle sleeve 13; 14 are designed to labyrinth type; be not easy into water, further protected airframe components 5.Axle head inside and outside circle at left and right sides bearing shell 15 is provided with the bearing retaining, the pendulum bearing internal diameter is enclosed within on its axle head cylindrical, the endoporus close-fitting of outer ring and Y-axis bearing 7, the axle head endoporus close-fitting of the outer ring of rolling bearing and left and right sides bearing shell 15 on the main shaft 8, internal diameter and main shaft 8 close-fittings; Bearing shell 15 big end outer rings in the left and right sides are provided with the inlet opening.Left and right sides shell (stator) 16 is fixed on the left and right sides bearing shell 15, and body fuselage 19 is fixed between the left and right sides shell 16, has osculum on the body fuselage 19.The endoporus of left and right sides shaft coupling 9 is provided with 1: 30 the conical surface, is processed with the triangle helical oil groove of certain depth on the conical surface, and the oil hole that is provided with shaft coupling 9 communicates.Shaft coupling 9 fixedly be by the dedicated hydraulic mounting or dismounting tools, make shaft coupling 9 radial dilatation, make on its spreading sleeve after injecting hydraulic oil, the hydraulic method of axial compression carries out simultaneously.In the bottom of body fuselage 19 cock 24 is housed, can be used for discharging ponding in the dynamometer in the long-term not time spent of dynamometer.
Force measuring machine parts 3 are made up of brake arm 29, pull pressure sensor 30, swing bolt 31, supporting base 32, oscillating bearing 33, protective cover 34 etc.Brake arm 29 is fixed on the body fuselage 19 of airframe components 5; supporting base 32 is fixed on the base 6 of airframe components 5; pull pressure sensor 30 links to each other with supporting base 32 with brake arm 29 respectively by the oscillating bearing 33 that is equipped with on the swing bolt 31 up and down; like this because the effect of oscillating bearing 33; can make the swing of pull pressure sensor 30 any directions; make the shell that brake arm 29 is housed when stressed swing; it is stressed that pull pressure sensor 30 remains rectilinear direction, and protective cover 34 covers pull pressure sensor 30 and is fixed on the base 6 of airframe components 5.The protective device of forming fixation of sensor 30 by support bar 37, portable plate 35 by bolt 36.Support bar 37 and portable plate 35 are installed in the sensor top, play fixedly protective effect, in order to avoid its vibration in running and use is malfunctioning.
Advancing water drainage part 4 is made up of overflow pipe 38, permeability cell 39, water inlet member 40, water drainage part 41 etc.Overflow pipe 38 links to each other with left and right sides bearing shell 15 in the airframe components 5, and permeability cell 39 links to each other with left and right sides shell 16 in the airframe components 5; Inlet opening on the left and right sides bearing shell 15 in water inlet member 40 and the airframe components 5 is connected, and water drainage part 41 is connected with osculum on the body fuselage 19; The two ends of pipeline 43 and drainage pipeline 47 all are made up of to float with bend pipe 42, draining support 46 respectively " O " shape rubber seal 45 and are connected, thereby can reverse when making 19 rotations of dynamometer body fuselage and do not damage into water drainage part 4.
Draining actuator 2 is connected the osculum position in the water drainage part 4 into, is the SMZ27 type, and it is made up of actuator shell 49, rare-earth electric motor 50, train of reduction gears, valve shaft 54, butterfly valve valve block 56, torsion spring 55, potentiometer " O " shape rubber seal 59 etc.The motor output shaft end is equipped with motor gear 51 and duplicate gear 52 engagements, compares with original technology, and this assembling is simple, and it is more reliable to work, and the transmission torque is big; Duplicate gear 52 is meshed with sector gear 53 on being contained in valve shaft 54, carries out the double reduction transmission, opens butterfly valve thereby increase torque drive by reducing gear.End at valve shaft 54 is equipped with torsion spring 55, under its effect train of reduction gears is remained and closely cooperates, and has eliminated gear clearance; The other end at valve shaft 54 is equipped with potentiometer 58, potentiometer 58 at first is sleeved on valve shaft 54 ends by " O " shape rubber seal, between 58 4 jiaos in potentiometer and shell, fill up again then and load onto " O " shape rubber seal 59, carry out flexible joints by three roads " O " shape rubber seal and valve shaft 54 like this; One end of actuator shell 49 has the potentiometer adjustment hole, can directly adjust and need not remove potentiometer 58, pulls down after need shutting down than original dynamometer to refill after potentiometer is regulated repeatedly, and technology is advanced more; Butterfly valve is installed in the middle of the valve shaft 54, and the below of draining actuator actuator shell 49 has two apopores 57 that communicate with valve shaft 54, and from then on the water that butterfly valve is overflowed when draining drain in order to avoid potentiometer 58 water inlets are damaged; Potentiometer 58 is provided with seven core socket wiring and controller joins, and makes controller be controlled draining actuator 2.
Quiet school parts 1 are made up of correction arm, drop hanger parts, suspension rod, pallet, counterweight.Proofread and correct arm and link to each other with the body fuselage 19 of airframe components 5 when quiet school, the drop hanger parts hang on the corner block of proofreading and correct arm, and suspension rod links to each other with the drop hanger parts, and pallet is suspended on the suspension rod, and counterweight then is added on the pallet.Quiet school parts 1 remove behind quiet school, and with balancing weight for it, this is not the protection domain of this patent, does not describe in detail at this.
During use tested engine output terminal is linked to each other with the shaft coupling 9 of dynamometer; electrical equipment control line on the dynamometer (not being the protection domain of this patent) links to each other with switch board respectively; standard-sized sheet draining butterfly valve valve block 56 (load minimum position); start engine and drive dynamometer main shaft 8 with same rotating speed rotation; after treating that engine works well; standard-sized sheet water intaking valve, and scalable draining butterfly valve opening size are up to consistent with the engine operating mode.The water of certain pressure enters the back side of left and right sides shell 16 from the inlet opening of water inlet member 40 on the left and right sides of airframe components bearing shell 15 of advancing water drainage part 4, under certain pressure, enter into through the inlet opening on the left and right sides shell 16 28 between the work cup chamber of the spinner blade 25 of left and right sides shell 16 and rotor 18 and blade 26, since rotor 18 rotation the effect of the centrifugal force that produces and spinner blade 25, water produces strong water turbulence in work cup chamber, it gives body fuselage 19 1 rotating torques in the airframe components 5, make the torque of engine pass to body fuselage 19 by rotor 18, the brake arm 29 that is contained on the body fuselage 19 will rotate a minute angle together along with body fuselage 19, thereby damping force is passed to the pull pressure sensor 30 that is connected with brake arm 29, make foil gauge distortion on the pull pressure sensor 30, demonstrate the size of corresponding damping force by connected electronic digital display apparatus.
Along with the power of engine constantly is absorbed, the kinetic energy of the water ring in the dynamometer working chamber is converted into the heat energy of water, and the butterfly valve valve 56 of the osculum from body fuselage 19 through water drainage part 41, draining actuator 2 discharged.By control draining actuator 2, the valve 56 aperture sizes of regulating the draining butterfly valve promptly change the pressure of the water in the dynamometer working chamber, change the size of engine load.Thereby record the power that can record engine behind the rotating speed of engine by speed probe 22.
Claims (9)
1. injection flow variable water vortex dynamometer, by airframe components (5), force measuring machine parts (3), advance water drainage part (4), draining actuator (2), quiet school parts compositions such as (1), it is characterized in that: a side of the body fuselage of described airframe components (19) is connected with force measuring machine parts (3), the opposite side of body fuselage (19) is connected with quiet school parts (1), the left and right sides bearing shell (15) of airframe components (5) and body fuselage (19) are connected with into water drainage part (4) respectively, draining actuator (2) links to each other with freeing port in advancing water drainage part (4), rotor (18) and associated left and right sides shell (16) are installed on the main shaft (8) of described airframe components (5), have groove on the two sides of its rotor (18), be provided with spinner blade (25) in it, also have groove on left and right sides shell (16) and rotor (18) opposite flank, be provided with blade (26) in it.
2. injection flow variable water vortex dynamometer according to claim 1 is characterized in that: blade (26) direction of described spinner blade (25) and left and right sides shell is opposite, spinner blade (25) and left and right sides shell blade (26) and end face angle at 45 separately.
3. injection flow variable water vortex dynamometer according to claim 1 is characterized in that: the lower surface of described spinner blade (25) and left and right sides shell blade (26) and end face angle at 45 separately, upper surface becomes 40 ° of angles with separately end face.
4. injection flow variable water vortex dynamometer according to claim 1, it is characterized in that: the both sides of main shaft (8) upper rotor part (18) of described airframe components (5) are set with slit seal axle sleeve (13,14), and the gap of 0.1mm～0.3mm is arranged between described slit seal axle sleeve (13,14) and the main shaft (8).
5. injection flow variable water vortex dynamometer according to claim 1, it is characterized in that: the spinner blade (25) in the described rotor (18) forms with the smart casting of rotor (18) one, blade (26) in the left and right sides shell (16) forms with the smart casting of left and right sides shell (16) one, having inlet opening (28) and air hole (27) on the reinforcement of left and right sides shell blade (26), is recessed garden arc groove in the middle of the external diameter of rotor (18).
6. injection flow variable water vortex dynamometer according to claim 1, it is characterized in that: the brake arm (29) of described force measuring machine parts (3) is fixed on the body fuselage (19) of airframe components (5), supporting base (32) is fixed on the base (6) of mechanism components (5), pull pressure sensor (30) links to each other with supporting base (32) with brake arm (29) respectively by the oscillating bearing (33) that is equipped with on the swing bolt (31) up and down, and the top of described pull pressure sensor (30) is fixed with support bar (37) and portable plate (35) by bolt (36).
7. injection flow variable water vortex dynamometer according to claim 1 is characterized in that: the two ends in the described intake-discharge pipe road that advances water drainage part (4) by " O " shape rubber seal (45) respectively with bend pipe (42) with draining support (46) is unsteady is connected.
8. injection flow variable water vortex dynamometer according to claim 1, it is characterized in that: the motor gear (51) of the motor output end of described draining actuator (2) and duplicate gear (52) engagement, duplicate gear (52) is meshed with sector gear (53) on being contained in valve shaft (54), one end of valve shaft (54) is equipped with a torsion spring (55), the other end is set with potentiometer (58) by " O " shape rubber seal, " O " shape rubber seal (59) also is housed between potentiometer (58) and the shell, one end of draining actuator shell has the potentiometer adjustment hole, and the below of draining actuator shell has the apopore (57) that two and valve shaft (54) communicate.
9. injection flow variable water vortex dynamometer according to claim 1 is characterized in that: cock (24) is equipped with in the lower end of the body fuselage of described airframe components (19).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 01223198 CN2473606Y (en) | 2001-05-14 | 2001-05-14 | Injection flow variable water vortex dynamometer |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 01223198 CN2473606Y (en) | 2001-05-14 | 2001-05-14 | Injection flow variable water vortex dynamometer |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN2473606Y true CN2473606Y (en) | 2002-01-23 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN 01223198 Ceased CN2473606Y (en) | 2001-05-14 | 2001-05-14 | Injection flow variable water vortex dynamometer |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN2473606Y (en) |
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103162887A (en) * | 2013-03-19 | 2013-06-19 | 重庆德马变频电机研发制造有限公司 | Seal floating type power measuring device |
| CN103207038A (en) * | 2013-03-20 | 2013-07-17 | 重庆德马变频电机研发制造有限公司 | Enclosed floating power measuring integrated device |
| CN103217242A (en) * | 2013-03-20 | 2013-07-24 | 重庆德马变频电机研发制造有限公司 | Upright floating dynamometer integrated device |
| CN106556485A (en) * | 2015-09-28 | 2017-04-05 | 李启飞 | Very big load regulatable magnetic force dynamometer |
| CN107356357A (en) * | 2017-09-13 | 2017-11-17 | 中国船舶重工集团公司第七0三研究所 | A kind of through-flow component quick change construction of Novel disc-type hydraulic dynamometer |
| CN107449961A (en) * | 2017-09-13 | 2017-12-08 | 中国船舶重工集团公司第七0三研究所 | A kind of through-flow structure of novel hydropower dynamometer |
| CN107607236A (en) * | 2016-07-11 | 2018-01-19 | 李启飞 | The special-shaped very big load regulatable magnetic force dynamometer of tandem type |
| CN107687950A (en) * | 2017-09-30 | 2018-02-13 | 广西玉柴机器股份有限公司 | A kind of convenient detection method and device of load sensor dynamic property |
-
2001
- 2001-05-14 CN CN 01223198 patent/CN2473606Y/en not_active Ceased
Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103162887A (en) * | 2013-03-19 | 2013-06-19 | 重庆德马变频电机研发制造有限公司 | Seal floating type power measuring device |
| CN103207038A (en) * | 2013-03-20 | 2013-07-17 | 重庆德马变频电机研发制造有限公司 | Enclosed floating power measuring integrated device |
| CN103217242A (en) * | 2013-03-20 | 2013-07-24 | 重庆德马变频电机研发制造有限公司 | Upright floating dynamometer integrated device |
| CN106556485A (en) * | 2015-09-28 | 2017-04-05 | 李启飞 | Very big load regulatable magnetic force dynamometer |
| CN107607236A (en) * | 2016-07-11 | 2018-01-19 | 李启飞 | The special-shaped very big load regulatable magnetic force dynamometer of tandem type |
| CN107356357A (en) * | 2017-09-13 | 2017-11-17 | 中国船舶重工集团公司第七0三研究所 | A kind of through-flow component quick change construction of Novel disc-type hydraulic dynamometer |
| CN107449961A (en) * | 2017-09-13 | 2017-12-08 | 中国船舶重工集团公司第七0三研究所 | A kind of through-flow structure of novel hydropower dynamometer |
| CN107449961B (en) * | 2017-09-13 | 2023-05-26 | 中国船舶重工集团公司第七0三研究所 | Novel hydraulic dynamometer through-flow structure |
| CN107687950A (en) * | 2017-09-30 | 2018-02-13 | 广西玉柴机器股份有限公司 | A kind of convenient detection method and device of load sensor dynamic property |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| C35 | Partial or whole invalidation of patent or utility model | ||
| IW01 | Full invalidation of patent right |
Decision date of declaring invalidation: 20021022 Decision number of declaring invalidation: 4598 |