CN105675202A - Space engine plume field vacuum micro differential pressure measurement system - Google Patents
Space engine plume field vacuum micro differential pressure measurement system Download PDFInfo
- Publication number
- CN105675202A CN105675202A CN201610022015.7A CN201610022015A CN105675202A CN 105675202 A CN105675202 A CN 105675202A CN 201610022015 A CN201610022015 A CN 201610022015A CN 105675202 A CN105675202 A CN 105675202A
- Authority
- CN
- China
- Prior art keywords
- pressure
- deflection cone
- differential pressure
- measuring pipe
- probe
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
Classifications
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01L—MEASURING FORCE, STRESS, TORQUE, WORK, MECHANICAL POWER, MECHANICAL EFFICIENCY, OR FLUID PRESSURE
- G01L13/00—Devices or apparatus for measuring differences of two or more fluid pressure values
- G01L13/06—Devices or apparatus for measuring differences of two or more fluid pressure values using electric or magnetic pressure-sensitive elements
Landscapes
- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Measuring Fluid Pressure (AREA)
Abstract
The invention discloses a space engine plume field vacuum micro differential pressure measurement system. A conical surface diversion cone is adopted, a plurality of through holes are arranged on the surface of the diversion cone for installation of sensors, and thus engine flame pressure distributed in different spaces can be accurately measured; and the diversion cone is machined into a conical surface, thereby preventing high-heat gas from quickly rebounding and damaging an engine spray pipe.
Description
Technical field
The invention belongs to space propulsion technical field, be specifically related to a kind of suitable in the space propulsion plume vacuum differential pressure measurement system under vacuum condition.
Background technology
Space propulsion is widely used on the spacecraft such as rocket, satellite. When electromotor is lighted a fire under vacuum conditions, the Vacuum Plume of external environment free wxpansion will be formed at nozzle. The spacecraft surface being pointed in plume is produced to clash into by Vacuum Plume, and causes power, heat and surface contamination effect. In plume, the local in short-term of pressure raises the surface properties that will destroy spacecraft or damages scientific instrument, shortens the spacecraft life-span, even results in spacecraft and lost efficacy.
At present, the pressure investigation method of plume includes plume numerical simulation, space carrying flight test and plume ground experiment. Plume numerical simulation relies primarily on the method for CFD and DSMC coupling and Vacuum Plume pressure is modeled and analyzes, it is possible to carry out the numerical simulation of the calculating of single thruster/many thruster plumes field, some complicated air-flows and effect thereof. But, Study on Numerical Simulation needs test data to be verified, some of complex operating mode, as the change of plume boundary member pressure cannot by emulating Accurate Analysis; Space carrying flight test is directly to measure the pressure information obtaining key position in the practical flight process of spacecraft, is characterized in that measurement result is authentic and valid, but test number (TN) is few, and single test cost height, cycle length, acquisition data volume are limited; The system Construction one-time investment of plume ground experiment is big, but single test cost is low, and can repeat test. Can also carrying out multi-state, multi-mode principle and proving test, the data of acquisition are more suitable for being analyzed and studying.
At present gas pressure change situation measured by conventional pitot tube, but due to the particularity of high-altitude plume pressure field measurement, and the selection of probe shape and size and point position are provided with higher requirement. And the plume change near spout is acutely, the variation characteristic that cannot accurately record plume pressure measured by pitot tube, will be inevitably generated measurement error.
For the Financial cost that plume ground experiment is high, domestic existing plume Pressure Analysis is still in theory analysis and modeling and simulating stage, and the indivedual plume testings having be carried out are also because condition shortcoming causes measurement result to there is certain deviation.
Summary of the invention
In view of this, it is an object of the invention to provide a kind of space propulsion plume vacuum differential pressure and measure system, it is possible to accurately measure the pressure change of vacuum plume in engine working process.
A kind of space propulsion plume vacuum differential pressure measures system, including electric supply installation (3), data collecting system (5), industrial computer (6), crosses cabin connector (42), vacuum chamber (7) and is placed in the pressure front end measuring unit in vacuum chamber (7), common reference end pressure sensor (2) and deflection cone (9); Tested electromotor (8) is placed in described vacuum chamber (7); Described cabin connector (42) of crossing is arranged on the bulkhead of vacuum chamber (7);
Wherein, described pressure front end measuring unit includes pressure transducer (13), pressure-measuring pipe (12) and pressure measxurement probe (11);
Described deflection cone (9) is taper seat aluminium sheet, is arranged in electromotor (8) flame and carrys out flow path direction; The cone angle of deflection cone (9) is 20 °, and the upper surface of taper seat is surrounded by heat-barrier material, and deflection cone (9) has multiple through hole along the vertical direction processing of taper seat, is used for installing one end of described pressure measxurement probe (11); The other end of pressure measxurement probe (11) is connected on the pressure measurement port of described pressure transducer (13) by pressure-measuring pipe (12); The reference port of pressure transducer (13) connects described common reference end pressure sensor (2) by reference edge pressure-measuring pipe (14); Described common reference end pressure sensor (2) is placed in the one end in described vacuum chamber (7) away from electromotor (8);
Described electric supply installation (3) is powered for each described pressure transducer (13) by described cabin connector (42) of crossing; Electromotor (8) the spout pressure data that each pressure transducer (13) records delivers to described data collecting system (5) by described cabin connector (42) of crossing; The pressure data received is sent into described industrial computer (6) by data collecting system (5).
It is also preferred that the left the outer surface processing of described pressure measxurement probe (11) one end has screwed hole, with the screw-internal thread fit of the described through hole of the upper processing of described deflection cone (9); After pressure measxurement probe (11) screws in described through hole, forward end is concordant with the conical surface of deflection cone (9).
It is also preferred that the left described pressure measxurement probe (11) is provided with nut.
It is also preferred that the left the upper one end relative with deflection cone (9) of described pressure measxurement probe (11) connects described pressure-measuring pipe (12); Described pressure-measuring pipe (12) is teflon hose, and pressure-measuring pipe (12) is socketed in pressure measxurement probe (11) by the mode of interference fit.
It is also preferred that the left the thickness of described deflection cone (9) is 6mm, basal diameter is 1m, high 180mm.
It is also preferred that the left low temperature glue is smeared in the junction of pressure measxurement probe (11) and deflection cone (9).
It is also preferred that the left described pressure transducer (13) adopts BESTACE761 series differential pressure transmitter.
There is advantages that
A kind of space propulsion plume vacuum differential pressure of the present invention measures system, by adopting conical surface deflection cone, and has multiple through hole installation sensor on its surface, can accurately measure the electromotor flame pressure of different spaces distribution; Deflection cone is processed into the conical surface, high heat gas can be avoided to quick rebound destruction engine jet pipe.
Accompanying drawing explanation
Fig. 1 is that space propulsion plume vacuum differential pressure of the present invention measures system annexation schematic diagram;
Fig. 2 is the schematic diagram of pressure measurement cell in space propulsion plume vacuum differential pressure measurement system of the present invention.
Wherein, 11-measuring probe, 12-pressure-measuring pipe, 13-pressure transducer, 14-reference edge pressure-measuring pipe, 2-common reference end pressure sensor, 3-electric supply installation, 4-transfers link, 41-intravehicular activity cable, 42-crosses cabin connector, 43-extravehicular activity cable, 5-data collecting system, 6-industrial computer, 7-vacuum chamber, 8-electromotor, 9-deflection cone.
Detailed description of the invention
Develop simultaneously embodiment below in conjunction with accompanying drawing, describe the present invention.
A kind of space propulsion plume vacuum differential pressure of the present invention measures system, as it is shown in figure 1, include electric supply installation 3, data collecting system 5, industrial computer 6, cross cabin connector 42, vacuum chamber 7 and the pressure front end measuring unit being placed in vacuum chamber 7, common reference end pressure sensor 2 and deflection cone 9; Tested electromotor 8 is placed in described vacuum chamber 7; Described cabin connector 42 of crossing is arranged on the bulkhead of vacuum chamber 7; Described pressure front end measuring unit includes pressure transducer 13, pressure-measuring pipe 12, pressure measxurement probe 11;
Described deflection cone 9 has multiple through hole along the vertical direction processing of taper seat, is used for installing described pressure measxurement probe 11; The other end of pressure measxurement probe 11 is connected on the pressure measurement port of described pressure transducer 13 by pressure-measuring pipe 12; The reference port of pressure transducer 13 connects described common reference end pressure sensor 2 by reference edge pressure-measuring pipe 14; Described common reference end pressure sensor 2 is placed in the one end in described vacuum chamber 7 away from electromotor;
Described electric supply installation is powered for each described pressure transducer by described cabin connector of crossing; The engine nozzle pressure data that each pressure transducer records delivers to described data collecting system by described cabin connector of crossing; The pressure data received is sent into described industrial computer by data collecting system, and pressure data shows on industrial computer 6, stores and process further.
Deflection cone 9 is the taper seat aluminium sheet that 6mm is thick, surface has the female thread of M6x1, basal diameter is 1m, high 180mm, cone angle is 20 °, is arranged in electromotor flame incoming flow direction, surface is surrounded by heat-barrier material, after the gas that engine nozzle place sprays downwards runs into deflection cone 9, spread to horizontal direction by the shape of deflection cone 9, to prevent high heat gas from quicking rebound destruction engine jet pipe.
Wherein, as in figure 2 it is shown, pressure measxurement probe 11 is stainless steel adapting piece, one end is the external screw thread of M6x1, is threaded connection with deflection cone 9 surface through hole, smears appropriate low temperature glue in the junction of pressure measxurement probe 11 with deflection cone 9 and ensures sealing; The other end of pressure measxurement probe 11 is connected with pressure-measuring pipe 12, is 4.6mm with pressure-measuring pipe 12 connected component diameter.
The described teflon hose that pressure-measuring pipe 12 is Φ 5/DN4.5, the pressure measxurement of one end and Φ 4.6 is popped one's head in 11 interference fit, and the other end is connected with the pressure tap of pressure transducer 13, and the diameter of pressure tap junction is slightly larger than the diameter of pressure-measuring pipe 12. Pressure-measuring pipe 12 length is 400-600mm.
Pressure transducer 13 adopts BESTACE761 series differential pressure transmitter, and range is 0～30KPa, and precision is 0.1%FS, carries two Φ 3/16 " turriform mechanical interface. One end is pressure tap, and the other end is reference edge interface of pressure measurement. Pressure tap is connected with pressure-measuring pipe 12, and smears appropriate low temperature glue at seam, it is ensured that connect reliable.
Common reference end is arranged on the far-end of vacuum chamber, common reference end pressure is measured interface and is connected with reference edge pressure-measuring pipe 14, reference edge pressure-measuring pipe 14 extends to the far-end of vacuum chamber, common reference end arranges reference edge vacuum pressure sensor 2, CPCA pressure transducer is adopted to measure the pressure of common reference end, range is 10KPa, and precision is 0.1%FS.
Electric supply installation 3 is D.C. regulated power supply, and supply voltage is 12-36VDC, adopts the supply voltage of 24VDC in test.
Switching link 4 includes intravehicular activity cable 41, crosses cabin connector 42 and extravehicular activity cable 43. Crossing cabin connector 42 and connect intravehicular activity cable 41 and extravehicular activity cable 43, the signal that pressure transducer 13 collects is transferred to acquisition system 5 through switching link 4, and electric supply installation 3 is powered to pressure transducer 13 by link 4 of transferring.
Data collecting system 5 includes transit cable and steady state data harvester, the electric calibration precision of steady state data harvester is 0.05%, adopt PCI-GPIB bus structures, the maximum sample rate of system is single channel 10KS/s, adopting the configuration of principal and subordinate's cabinet, largest passages number is up to 4096, and unit tankage is 16 slots, 128 passages, it is possible to carry out the flexible configuration of unit case or multiple cases cascade as required. Industrial computer 6 is connected with steady state data harvester by communication cable, realizing the functions such as data acquisition, analyzing and processing, storage, display, forwarded, data report generation, communication cable can be the communication cable of the communication cable of USB interface or gpib interface.
Space propulsion plume vacuum differential pressure measures the measurement process of system, comprises the following steps:
(1) by the measuring probe 11 through hole by nut precession deflection cone 9 thereon; Check the connection sealing of pressure-measuring pipe 12 and the pressure tap of pressure transducer 13, check the connection sealing of reference edge pressure-measuring pipe 14 and the reference port of pressure transducer 13, it is ensured that air-flow can pass through;
(2) in electromotor 8 ignition process, will forming the Vacuum Plume of external environment free wxpansion at nozzle, Vacuum Plume constantly spreads by the planform of deflection cone 9;
(3) screwed hole of the M6x1 that the surface of deflection cone 9 has, in order to measure the pressure changing of plume;
(4) plume vacuum differential pressure is delivered to the pressure tap of pressure transducer 13 by measuring probe 11, pressure-measuring pipe 12, pressure transducer 13 measure distribution and the situation of change of plume pressure;
(5) reference port of pressure transducer 13 connects reference edge pressure-measuring pipe 14, and extends to vacuum chamber 7 far-end, and reference edge vacuum pressure sensor 15 witness mark end pressure changes;
(6) pressure difference value between pressure tap and the reference port of pressure transducer 13 is the vacuum differential pressure situation of change of plume;
(7) the vacuum differential pressure that pressure transducer 13 records is transferred to acquisition system 5 by link 4 of transferring, and electric supply installation 3 is powered to pressure transducer 13 by link 4 of transferring simultaneously. The terminals of pressure transducer 13 and intravehicular activity cable 41 are joined directly together, and intravehicular activity cable 41 passed through cabin connector 42 with extravehicular activity cable 43 and is connected, and extravehicular activity cable 43 and data collecting system 5 are directly connected to;
(8) data collecting system 5 is with to the vacuum differential pressure measurement collected, and meanwhile, data collecting system 5 is connected with industrial computer 6;
(9) data that data collecting system is collected by industrial computer 6 show in real time, store, call and subsequent treatment.
In sum, these are only presently preferred embodiments of the present invention, be not intended to limit protection scope of the present invention. All within the spirit and principles in the present invention, any amendment of making, equivalent replacement, improvement etc., should be included within protection scope of the present invention.
Claims (7)
1. a space propulsion plume vacuum differential pressure measures system, it is characterized in that, including electric supply installation (3), data collecting system (5), industrial computer (6), cross cabin connector (42), vacuum chamber (7) and be placed in the pressure front end measuring unit in vacuum chamber (7), common reference end pressure sensor (2) and deflection cone (9);Tested electromotor (8) is placed in described vacuum chamber (7); Described cabin connector (42) of crossing is arranged on the bulkhead of vacuum chamber (7);
Wherein, described pressure front end measuring unit includes pressure transducer (13), pressure-measuring pipe (12) and pressure measxurement probe (11);
Described deflection cone (9) is taper seat aluminium sheet, is arranged in electromotor (8) flame and carrys out flow path direction; The cone angle of deflection cone (9) is 20 °, and the upper surface of taper seat is surrounded by heat-barrier material, and deflection cone (9) has multiple through hole along the vertical direction processing of taper seat, is used for installing one end of described pressure measxurement probe (11); The other end of pressure measxurement probe (11) is connected on the pressure measurement port of described pressure transducer (13) by pressure-measuring pipe (12); The reference port of pressure transducer (13) connects described common reference end pressure sensor (2) by reference edge pressure-measuring pipe (14); Described common reference end pressure sensor (2) is placed in the one end in described vacuum chamber (7) away from electromotor (8);
Described electric supply installation (3) is powered for each described pressure transducer (13) by described cabin connector (42) of crossing; Electromotor (8) the spout pressure data that each pressure transducer (13) records delivers to described data collecting system (5) by described cabin connector (42) of crossing; The pressure data received is sent into described industrial computer (6) by data collecting system (5).
2. a kind of space propulsion plume vacuum differential pressure as claimed in claim 1 measures system, it is characterized in that, the outer surface processing of described pressure measxurement probe (11) one end has screwed hole, with the screw-internal thread fit of the described through hole of the upper processing of described deflection cone (9); After pressure measxurement probe (11) screws in described through hole, forward end is concordant with the conical surface of deflection cone (9).
3. a kind of space propulsion plume vacuum differential pressure as claimed in claim 2 measures system, it is characterised in that be provided with nut in described pressure measxurement probe (11).
4. a kind of space propulsion plume vacuum differential pressure as claimed in claim 2 measures system, it is characterised in that the upper one end relative with deflection cone (9) of described pressure measxurement probe (11) connects described pressure-measuring pipe (12); Described pressure-measuring pipe (12) is teflon hose, and pressure-measuring pipe (12) is socketed in pressure measxurement probe (11) by the mode of interference fit.
5. a kind of space propulsion plume vacuum differential pressure as claimed in claim 1 measures system, it is characterised in that the thickness of described deflection cone (9) is 6mm, and basal diameter is 1m, high 180mm.
6. a kind of space propulsion plume vacuum differential pressure as claimed in claim 1 measures system, it is characterised in that low temperature glue is smeared in the junction of pressure measxurement probe (11) and deflection cone (9).
7. a kind of space propulsion plume vacuum differential pressure as claimed in claim 1 measures system, it is characterised in that described pressure transducer (13) adopts BESTACE761 series differential pressure transmitter.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610022015.7A CN105675202A (en) | 2016-01-13 | 2016-01-13 | Space engine plume field vacuum micro differential pressure measurement system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610022015.7A CN105675202A (en) | 2016-01-13 | 2016-01-13 | Space engine plume field vacuum micro differential pressure measurement system |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN105675202A true CN105675202A (en) | 2016-06-15 |
Family
ID=56300420
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610022015.7A Pending CN105675202A (en) | 2016-01-13 | 2016-01-13 | Space engine plume field vacuum micro differential pressure measurement system |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN105675202A (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107860544A (en) * | 2017-10-24 | 2018-03-30 | 北京特种机械研究所 | A kind of Vacuum Plume water conservancy diversion ground experiment protector |
| CN107894320A (en) * | 2017-11-07 | 2018-04-10 | 北京特种机械研究所 | The plume water conservancy diversion ground experiment protector of detector is disposed vertically in vacuum chamber |
| CN110455544A (en) * | 2019-08-29 | 2019-11-15 | 中国航空工业集团公司北京长城计量测试技术研究所 | Engine testsand inlet flow field based on fixed measuring point monitors system and method |
| CN113148239A (en) * | 2021-02-25 | 2021-07-23 | 北京空间飞行器总体设计部 | Spacecraft plume guiding device suitable for take-off of extraterrestrial celestial body |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20120025069A1 (en) * | 2007-07-20 | 2012-02-02 | The George Washington University | Laser Ablation Electrospray Ionization (LAESI) for Atmospheric Pressure, In Vivo, and Imaging Mass Spectrometry |
| CN102455231A (en) * | 2010-10-25 | 2012-05-16 | 北京卫星环境工程研究所 | Testing system for pressure and temperature of supersonic engine plume field |
| CN103616154A (en) * | 2013-11-29 | 2014-03-05 | 北京航空航天大学 | Vacuum plume aerodynamic force measuring system and method |
-
2016
- 2016-01-13 CN CN201610022015.7A patent/CN105675202A/en active Pending
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20120025069A1 (en) * | 2007-07-20 | 2012-02-02 | The George Washington University | Laser Ablation Electrospray Ionization (LAESI) for Atmospheric Pressure, In Vivo, and Imaging Mass Spectrometry |
| CN102455231A (en) * | 2010-10-25 | 2012-05-16 | 北京卫星环境工程研究所 | Testing system for pressure and temperature of supersonic engine plume field |
| CN103616154A (en) * | 2013-11-29 | 2014-03-05 | 北京航空航天大学 | Vacuum plume aerodynamic force measuring system and method |
Non-Patent Citations (2)
| Title |
|---|
| 王文龙等: "钟型喷管10N推力器冷流羽流气动力试验研究", 《空间控制技术与应用》 * |
| 马树微等: "氢氧发动机模型真空羽流场试验和仿真研究", 《航天器环境工程》 * |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107860544A (en) * | 2017-10-24 | 2018-03-30 | 北京特种机械研究所 | A kind of Vacuum Plume water conservancy diversion ground experiment protector |
| CN107860544B (en) * | 2017-10-24 | 2019-09-10 | 北京特种机械研究所 | A kind of Vacuum Plume water conservancy diversion ground experiment protective device |
| CN107894320A (en) * | 2017-11-07 | 2018-04-10 | 北京特种机械研究所 | The plume water conservancy diversion ground experiment protector of detector is disposed vertically in vacuum chamber |
| CN110455544A (en) * | 2019-08-29 | 2019-11-15 | 中国航空工业集团公司北京长城计量测试技术研究所 | Engine testsand inlet flow field based on fixed measuring point monitors system and method |
| CN113148239A (en) * | 2021-02-25 | 2021-07-23 | 北京空间飞行器总体设计部 | Spacecraft plume guiding device suitable for take-off of extraterrestrial celestial body |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN105675202A (en) | Space engine plume field vacuum micro differential pressure measurement system | |
| Dorschner et al. | On the formation and recurrent shedding of ligaments in droplet aerobreakup | |
| CN106840591B (en) | A kind of experimental rig directly measuring jet flow thrust | |
| CN201318980Y (en) | Helium mass spectrometer leak detector used for detecting integral leakage of product | |
| CN101300467A (en) | Flight air data measuring system | |
| CN110793746A (en) | Wind tunnel test device for thrust measurement of oblique cutting nozzle of hypersonic vehicle | |
| CN205785823U (en) | A kind of space propulsion plume measures heat flow transducer fixing device | |
| CN102120071A (en) | Method for measuring concentration of extinguishing agent in engine cabin of airplane | |
| CN111964848A (en) | Small pressure container trace gas leakage emergency ultrasonic detection system and method | |
| CN111474110A (en) | Visual image monitoring flowing corrosion test device for bent pipe | |
| CN101806261B (en) | Method and device for measuring pneumatic thrust indirectly | |
| CN109655228B (en) | Jet thrust calibration and measurement device for spray pipes with different molded surfaces | |
| CN110567673A (en) | Wind tunnel test method for thrust measurement of oblique cutting nozzle of hypersonic vehicle | |
| CN205679242U (en) | A kind of aircraft survey height in situ tests the speed and uses pitot auxiliary test unit | |
| CN104482995A (en) | Fuel consumption instrument calibration detecting device | |
| CN205228771U (en) | Experimental minute -pressure measurement system in low speed wind tunnel flow field | |
| Wolf | The subsonic near-wake of bluff bodies | |
| RU2381471C1 (en) | Device for identification of traction characteristics in imitators of air-feed jet engines (afje), method for detection of traction characteristics of afje imitators and method for control of validity in detection of traction characteristics of afje imitators | |
| Nikoueeyan et al. | Evaluating the utility of pressure scanners for unsteady pressure measurements in wind tunnel characterization of the space launch system | |
| CN106595394B (en) | A kind of method using sonic boom measurement supersonic speed body point of impact | |
| CN103474311B (en) | Based on the plasma flow display unit of glow discharge principle | |
| CN103712681B (en) | Gas-flow noise monitoring system launched by a kind of carrier rocket | |
| CN113899523A (en) | Electronic scanning valve protection device | |
| CN210375613U (en) | Wind tunnel test device for thrust measurement of oblique cutting nozzle of hypersonic vehicle | |
| CN104180926B (en) | Jet-flow reflection temperature field testing method |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| RJ01 | Rejection of invention patent application after publication | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20160615 |