CN112937912A - Array plasma-based rotation body lateral force control experimental device - Google Patents
Array plasma-based rotation body lateral force control experimental device Download PDFInfo
- Publication number
- CN112937912A CN112937912A CN202110082062.1A CN202110082062A CN112937912A CN 112937912 A CN112937912 A CN 112937912A CN 202110082062 A CN202110082062 A CN 202110082062A CN 112937912 A CN112937912 A CN 112937912A
- Authority
- CN
- China
- Prior art keywords
- plasma
- force control
- array
- lateral force
- exciting
- 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.)
- Granted
Links
- 238000012545 processing Methods 0.000 claims description 8
- 230000005284 excitation Effects 0.000 claims description 6
- 239000003990 capacitor Substances 0.000 claims description 4
- RYGMFSIKBFXOCR-UHFFFAOYSA-N Copper Chemical compound [Cu] RYGMFSIKBFXOCR-UHFFFAOYSA-N 0.000 claims description 3
- 229910052802 copper Inorganic materials 0.000 claims description 3
- 239000010949 copper Substances 0.000 claims description 3
- 239000003822 epoxy resin Substances 0.000 claims description 3
- 229920000647 polyepoxide Polymers 0.000 claims description 3
- WFKWXMTUELFFGS-UHFFFAOYSA-N tungsten Chemical compound [W] WFKWXMTUELFFGS-UHFFFAOYSA-N 0.000 claims description 3
- 229910052721 tungsten Inorganic materials 0.000 claims description 3
- 239000010937 tungsten Substances 0.000 claims description 3
- 238000004146 energy storage Methods 0.000 claims 1
- 239000000463 material Substances 0.000 claims 1
- 238000000034 method Methods 0.000 abstract description 9
- 238000012360 testing method Methods 0.000 abstract description 3
- 238000005265 energy consumption Methods 0.000 abstract description 2
- 238000012423 maintenance Methods 0.000 abstract description 2
- 238000010586 diagram Methods 0.000 description 6
- 238000009987 spinning Methods 0.000 description 4
- 238000005516 engineering process Methods 0.000 description 3
- 239000007772 electrode material Substances 0.000 description 2
- 238000004088 simulation Methods 0.000 description 2
- RZVHIXYEVGDQDX-UHFFFAOYSA-N 9,10-anthraquinone Chemical compound C1=CC=C2C(=O)C3=CC=CC=C3C(=O)C2=C1 RZVHIXYEVGDQDX-UHFFFAOYSA-N 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 239000008358 core component Substances 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000002347 injection Methods 0.000 description 1
- 239000007924 injection Substances 0.000 description 1
- 238000007750 plasma spraying Methods 0.000 description 1
- 238000011160 research Methods 0.000 description 1
- 239000000243 solution Substances 0.000 description 1
- 239000007921 spray Substances 0.000 description 1
Images
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
- B64F5/60—Testing or inspecting aircraft components or systems
Landscapes
- Engineering & Computer Science (AREA)
- Manufacturing & Machinery (AREA)
- Transportation (AREA)
- Aviation & Aerospace Engineering (AREA)
- Plasma Technology (AREA)
Abstract
本发明公开了一种基于阵列式等离子体的旋成体侧向力控制实验装置，包括外壳，外壳包括前端和后端，前端为圆锥体结构，前端底部设有凹槽，凹槽内设有高压直流电源，前端卡接有等离子体激励器，后端一端连接前端，另一端两侧设有侧翼，后端为中空圆柱体，外壳内还设有与等离子体激励器连接的控制系统。本发明的实验装置能够预先模拟测试可以有效减少在真实飞行过程中遇到的问题，同时频率响应速度快、能耗较低，可靠性高，成本低、维护相对简单、寿命长。
The invention discloses an experimental device for controlling lateral force of a spiral body based on an array plasma, comprising a casing, the casing includes a front end and a rear end, the front end is a cone structure, a groove is arranged at the bottom of the front end, and a high voltage is arranged in the groove DC power supply, the front end is clamped with a plasma exciter, one end of the rear end is connected to the front end, the other end is provided with flanks on both sides, the rear end is a hollow cylinder, and a control system connected to the plasma exciter is also arranged in the shell. The experimental device of the present invention can simulate the test in advance and can effectively reduce the problems encountered in the actual flight process, meanwhile, the frequency response speed is fast, the energy consumption is low, the reliability is high, the cost is low, the maintenance is relatively simple, and the service life is long.
Description
Technical Field
The invention belongs to the technical field of aerodynamics, plasma physics and flow control, and relates to a rotation body lateral force control experimental device based on array type plasma.
Background
Most of the prior flying weapons are winged flying weapons, which mainly depend on the generated aerodynamic force to carry out maneuvering flight. The winged flying weapon generally requires a good aerodynamic shape, and the common winged flying weapons all adopt a slender rotating body structure, which can effectively reduce the air resistance in the flying process.
The flow control method mainly comprises active flow control and passive flow control, and the plasma flow control method is an active flow control method for improving the pneumatic performance of a rotating body model by adopting a plasma exciter. The plasma flow control can improve the aerodynamic characteristics of the rotating body model by methods of reducing drag, increasing lift, improving stall attack angle and maneuverability, reducing noise, reducing vibration, improving flow field quality of an air inlet/exhaust system, forming new flight control force and the like. At present, synthetic jet is mostly researched in plasma flow control, the synthetic jet technology is a brand-new active flow control technology, and a core component of the technology is a synthetic jet actuator. When the vibration exciter starts to work, no actuating part except the vibration of the vibration film is needed, and the frequency, the amplitude and the phase of an electric signal of the exciter are changed, so that the adjustment and the control can be carried out according to requirements. Meanwhile, the synthetic jet actuator has the advantages of simple structure, greatly reduced structural weight and regulation function because a jet supply and injection system is not needed. The research shows that: at 100mJ the individual jet pulses produced an impulse of 14[ mu.N.s ], and if the pulse discharge energy was further increased to 500mJ, the individual jet pulses produced an impulse of about 130[ mu.N.s ], but the resultant vortex formed by the individual jet pulses in combination with the incoming flow was not sufficient to produce a sufficient control moment.
Disclosure of Invention
The invention aims to provide a rotating body lateral force control experimental device based on array type plasma, which has the characteristic of reducing problems of an aircraft in real flight through a pre-simulation test.
The technical scheme adopted by the invention is that the experimental device for controlling the lateral force of the spinning body based on the array type plasma is characterized by comprising a shell, wherein the shell comprises a front end and a rear end, the front end is of a cone structure, a groove is formed in the bottom of the front end, a high-voltage direct-current power supply is arranged in the groove, the front end is connected with a plasma exciter in a clamping mode, one end of the rear end is connected with the front end, side wings are arranged on two sides of the other end of the rear end, the rear end is of a hollow cylinder, and a control system connected with the plasma exciter is further arranged in the shell.
The invention is also characterized in that:
the number of the plasma exciters is 2-6, and the plasma exciters are arranged at the front end in an array.
The distance between the plasma exciters is equal and the plasma exciters are positioned on the same bus of the shell.
An electrode unit is arranged in the plasma exciter and comprises an exciting positive electrode and an exciting negative electrode, and the exciting positive electrode and the exciting negative electrode are both connected with a control system.
The electrode materials of the exciting positive electrode and the exciting negative electrode are both tungsten rods or copper rods.
The exposed lengths of the exciting positive electrode and the exciting negative electrode in the plasma exciter are both 2mm-4mm, and the spacing distance between the exciting positive electrode and the exciting negative electrode is 6mm-8 mm.
The control system comprises an acquisition module and a processing module, wherein the acquisition module comprises a sensor arranged at the front end, the sensor is connected with a signal acquisition card arranged at the rear end, and the signal acquisition card is connected with the processing module.
The high-voltage direct-current power supply is connected with a capacitor for storing energy.
The other end of the rear end is connected with a long handle shaft.
The shell is made of epoxy resin.
The invention has the beneficial effects that:
1. the experimental device for controlling the lateral force of the revolution body based on the array type plasma fills up the vacancy of the existing experimental device for controlling the revolution body model, can completely simulate the dynamic change condition of the revolution body model in the actual flight process, and has important reference significance for controlling the lateral force around the actual revolution body model through data and conclusions obtained by simulating the flight environment in the experimental device;
2. according to the arrangement mode of the array type plasma exciter of the experimental device for controlling the lateral force of the spinning body based on the array type plasma, under the condition that the resistance is minimum, switches of different plasma exciters are controlled to spray airflow, the strength of the plasma spraying airflow is increased, and the lateral force around the spinning body model is well controlled;
3. the experimental device for controlling the lateral force of the rotating body based on the array type plasma carries out feedback control on the current state of the rotating body model by connecting the embedded closed-loop control system, and can adopt different strategies to control the switch jet air flow of the plasma exciter under different attack angle states so as to achieve the optimal control effect;
4. according to the experimental device for controlling the lateral force of the rotating body based on the array type plasma, the tail long handle shaft is connected with the inside of the plasma exciter in a conducting mode, so that the control of the lateral force of the rotating body model at any angle can be realized, the limitation of the control direction is broken through, and the control efficiency is greatly improved.
Drawings
FIG. 1 is a schematic structural diagram of an experimental apparatus for controlling force of a rotating body side based on an array plasma according to the present invention;
FIG. 2 is a schematic structural diagram of a plasma actuator in an array-type plasma-based rotational bulk-lateral force control experimental apparatus according to the present invention;
FIG. 3 is a block diagram of the operation of a control module in an experimental apparatus for controlling the lateral force of a rotating body based on an array plasma according to the present invention;
FIG. 4 is a diagram of the gas flow ejected from a plasma actuator in an array-based plasma-based rotational-lateral force control experimental apparatus according to the present invention.
In the figure, 1 is a high-voltage direct-current power supply, 2 is a plasma exciter, 3 is a control system, 4 is a shell, 5 is a long handle shaft, 6 is an exciting positive electrode, and 7 is an exciting negative electrode.
Detailed Description
The present invention will be described in detail below with reference to the accompanying drawings and specific embodiments.
The invention relates to a rotation body lateral force control experimental device based on array type plasma, which comprises a shell 4, wherein the shell 4 comprises a front end and a rear end, the front end is of a cone structure, the bottom of the front end is provided with a groove, a high-voltage direct-current power supply 1 is arranged in the groove, the front end is connected with a plasma exciter 2 in a clamping manner, one end of the rear end is connected with the front end, two sides of the other end are provided with side wings, the rear end is a hollow cylinder, a control system 3 connected with the plasma exciter 2 is also arranged in the shell 4, and the control system 3 is an embedded closed-loop control system;
2-6 plasma exciters 2 are arranged at the front end in an array, the plasma exciters 2 which are closer to the front end of the shell 4 have stronger control force on lateral force, and the control force of the plasma exciters 2 is weakened in sequence along with the increasing distance;
the distances between the plasma exciters 2 are equal and are positioned on the same bus of the shell 4;
as shown in fig. 2, an electrode unit is arranged in the plasma exciter 2, the electrode unit comprises an exciting positive electrode 6 and an exciting negative electrode 7, and both the exciting positive electrode 6 and the exciting negative electrode 7 are connected with the control system 3; the electrode materials of the excitation positive electrode 6 and the excitation negative electrode 7 are both tungsten rods or copper rods; the exposed lengths of the exciting positive electrode 6 and the exciting negative electrode 7 in the plasma exciter 2 are both 2mm-4mm, and the spacing distance between the exciting positive electrode 6 and the exciting negative electrode 7 is 6mm-8 mm; the plasma exciter 2 is correspondingly connected with an exciting positive electrode and an exciting negative electrode from the inside of the shell 4 through leads, and finally, the exciting positive electrode 6 and the exciting negative electrode 7 are respectively connected with the embedded closed-loop control system 3 through binding posts;
the embedded closed-loop control system 3 is connected with the positive electrode and the negative electrode of the plasma exciter 2 through the binding post to control the switch of the exciter, the embedded closed-loop control system 3 comprises an acquisition module and a processing module, the acquisition module comprises a sensor arranged at the front end, the sensor is connected with an ART2153 signal acquisition card arranged at the rear end, the signal acquisition card is connected with the processing module, and the processing module is PCM-3365; the positive pole of the sensor output is connected to the positive channel of an ART3153 signal acquisition card, the negative pole of the output line and the grounding end of the ART3153 signal acquisition card, it is mainly used for measuring the flight state parameter of the slender body model, and transmit the digital signal gathered directly and store in the ART3153 signal acquisition card; the ART3153 signal acquisition card transmits the stored flight state parameters to a PCM-3365 system in real time for analysis and processing, the PCM-3365 system is connected with the ART3153 signal acquisition card through a USB line to read the data stored in the acquisition card, and simultaneously, various initially optimized parameter values are set, and closed loop feedback control is performed according to initial values;
the high-voltage direct-current power supply 1 is also connected with a capacitor for storing energy, the capacitance of the capacitor is 0.05-0.5, and the withstand voltage is not less than 5000V
The end part of the other end of the rear end is connected with a long handle shaft 5;
the shell 4 is made of epoxy resin;
as shown in fig. 3, which is a working block diagram of the embedded closed-loop control system, when the rotating body model flies in a straight line at a constant speed and the plasma exciter 2 is in an off state, the embedded closed-loop control system 3 does not work, and the rotating body model does not need to be adjusted in real time according to the current state; when the rotating body model is inclined, the change conditions of a pitch angle and a roll angle of the rotating body model in the flying process are detected through the MEMS sensor 3, and data are transmitted to the embedded closed-loop control system 3;
as shown in fig. 4, which is a schematic diagram of the airflow state around the front end of the rear rotating body model after the experimental apparatus of the present invention is started, since the embedded closed-loop control system 3 presets a small attack angle range of 0-15 degrees and a large attack angle range of more than 15 degrees, when the MEMS sensor 3 measures that the current rotating body model is in the small attack angle range, the embedded closed-loop control system 3 controls the front two plasma actuators 2 close to the front end of the housing to open to inject the airflow to change the lateral force around the rotating body model; when the MEMS sensor 3 measures that the current rotating body model state is in a large attack angle range, the embedded closed-loop control system 3 starts all the plasma exciters 2 to jet air flow so as to change the lateral force around the rotating body model; the control of the motion direction of the rotary body model can be realized by the long stem shaft 5 connected with the tail part, the long stem shaft 5 is connected with the tail part of the shell 4 through a bearing, and the bearing is connected with the front end of the shell and is reinforced through a screw, so that the function of the rotation angle is realized.
The experimental device of the invention has the following advantages: firstly, the vacancy of the conventional spinning integral model experimental device is filled, and the problems encountered in the real flight process can be effectively reduced through the pre-simulation test of the experimental device; secondly, a novel array-type plasma exciter is provided, the jet airflow of the switch of the plasma exciter is controlled through an embedded closed-loop control system, and the jet force of the airflow of the plasma exciter is enhanced; thirdly, the long handle shaft connected with the tail part of the rotary body model can measure experimental parameters at any angle, and the limitation of measuring angles is broken through; fourthly, the experimental device is simple in structure, flexible and convenient, and high in applicability, and one row of the experimental device is suitable for most flight weapons in consideration of small diameter of real flight weapons; and fifthly, no mechanical element exists, electric triggering is realized, the frequency response speed is high, the energy consumption is low, and the reliability is high. Sixthly, the cost is low, the maintenance is relatively simple, the service life is long, the weight of the system is greatly reduced compared with other solutions, and the reliability is improved.
Claims (10)
1. The utility model provides a rotation body lateral force control experimental apparatus based on array plasma, its characterized in that, includes shell (4), shell (4) include front end and rear end, the front end is the cone structure, the front end bottom is equipped with the recess, be equipped with high voltage direct current power supply (1) in the recess, the front end joint has plasma excitation ware (2), the front end is connected to rear end one end, and other end both sides are equipped with the flank, the rear end is hollow circular cylinder, still be equipped with control system (3) of being connected with plasma excitation ware (2) in shell (4).
2. The array plasma-based rotational volumetric force control experimental apparatus as claimed in claim 1, wherein said plasma actuators (2) are 2-6 and arranged in array at the front end.
3. The array plasma-based rotational volumetric force control experimental apparatus as claimed in claim 2, wherein the distance between the plasma actuators (2) is equal and located on the same bus of the housing (4).
4. The array plasma-based rotational volumetric lateral force control experimental device according to claim 1, wherein an electrode unit is arranged in the plasma exciter (2), the electrode unit comprises an exciting positive electrode (6) and an exciting negative electrode (7), and the exciting positive electrode (6) and the exciting negative electrode (7) are both connected with the control system (3).
5. The array plasma-based rotor lateral force control experimental device as claimed in claim 4, wherein the excitation positive electrode (6) and the excitation negative electrode (7) are made of tungsten rod or copper rod.
6. The array plasma-based rotation body lateral force control experimental device is characterized in that the exposed length of the exciting positive electrode (6) and the exciting negative electrode (7) in the plasma exciter (2) is 2mm-4mm, and the spacing distance between the exciting positive electrode (6) and the exciting negative electrode (7) is 6mm-8 mm.
7. The array plasma-based rotational volumetric force control experimental apparatus as claimed in claim 1, wherein the control system (3) comprises an acquisition module and a processing module, the acquisition module comprises a sensor disposed at a front end, the sensor is connected to a signal acquisition card disposed at a rear end, and the signal acquisition card is connected to the processing module.
8. The array plasma-based rotational volumetric lateral force control experimental apparatus as claimed in claim 1, wherein the high voltage direct current power supply (1) is connected with a capacitor for energy storage.
9. The array plasma-based rotational volumetric lateral force control experimental apparatus as claimed in claim 1, wherein the other end of the rear end is connected with a long stem (5).
10. The array plasma-based rotational volumetric force control experimental apparatus as claimed in claim 1, wherein the material of the housing (4) is epoxy resin.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110082062.1A CN112937912B (en) | 2021-01-21 | 2021-01-21 | Rotary formation body lateral force control experimental device based on array type plasma |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110082062.1A CN112937912B (en) | 2021-01-21 | 2021-01-21 | Rotary formation body lateral force control experimental device based on array type plasma |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN112937912A true CN112937912A (en) | 2021-06-11 |
| CN112937912B CN112937912B (en) | 2023-08-15 |
Family
ID=76235800
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202110082062.1A Active CN112937912B (en) | 2021-01-21 | 2021-01-21 | Rotary formation body lateral force control experimental device based on array type plasma |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN112937912B (en) |
Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| RU2040445C1 (en) * | 1992-05-22 | 1995-07-25 | Головное конструкторское бюро научно-производственного объединения "Энергия" им.акад.С.П.Королева | Combined electric jet-propulsion engine unit for spacecraft, method of creating controlling moments and three-channel electric jet-propulsion engine |
| FR2880236A1 (en) * | 2004-12-23 | 2006-06-30 | Air Liquide | Plasma microwave excitation device for use in the treatment of effluent gas from processes for the deposition and engraving of thin films during the fabrication of semiconductors |
| CA2560520A1 (en) * | 2005-09-27 | 2007-03-27 | Institut Franco-Allemand De Recherches De Saint-Louis | On-board low voltage device for generating plasma discharges for controlling a supersonic or hypersonic engine |
| US7624941B1 (en) * | 2006-05-02 | 2009-12-01 | Orbital Research Inc. | Method of controlling aircraft, missiles, munitions and ground vehicles with plasma actuators |
| US20110050076A1 (en) * | 2008-04-01 | 2011-03-03 | Bae Systems Bofors Ab | Plasma generator for electrothermal-chemical weapon system comprising improved connectors, and method for preventing the electrical contact of the plasma generator from being broken |
| CN108406017A (en) * | 2018-01-25 | 2018-08-17 | 西安理工大学 | A kind of plasma micro-arc electric discharge cutter device and cutting method |
| CN108684130A (en) * | 2018-03-23 | 2018-10-19 | 厦门大学 | A kind of program-controlled array plasma jet exciter system |
| CN112179215A (en) * | 2020-09-21 | 2021-01-05 | 西安理工大学 | Flight guidance weapon control device based on plasma jet technology |
-
2021
- 2021-01-21 CN CN202110082062.1A patent/CN112937912B/en active Active
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| RU2040445C1 (en) * | 1992-05-22 | 1995-07-25 | Головное конструкторское бюро научно-производственного объединения "Энергия" им.акад.С.П.Королева | Combined electric jet-propulsion engine unit for spacecraft, method of creating controlling moments and three-channel electric jet-propulsion engine |
| FR2880236A1 (en) * | 2004-12-23 | 2006-06-30 | Air Liquide | Plasma microwave excitation device for use in the treatment of effluent gas from processes for the deposition and engraving of thin films during the fabrication of semiconductors |
| CA2560520A1 (en) * | 2005-09-27 | 2007-03-27 | Institut Franco-Allemand De Recherches De Saint-Louis | On-board low voltage device for generating plasma discharges for controlling a supersonic or hypersonic engine |
| US7624941B1 (en) * | 2006-05-02 | 2009-12-01 | Orbital Research Inc. | Method of controlling aircraft, missiles, munitions and ground vehicles with plasma actuators |
| US20110050076A1 (en) * | 2008-04-01 | 2011-03-03 | Bae Systems Bofors Ab | Plasma generator for electrothermal-chemical weapon system comprising improved connectors, and method for preventing the electrical contact of the plasma generator from being broken |
| CN108406017A (en) * | 2018-01-25 | 2018-08-17 | 西安理工大学 | A kind of plasma micro-arc electric discharge cutter device and cutting method |
| CN108684130A (en) * | 2018-03-23 | 2018-10-19 | 厦门大学 | A kind of program-controlled array plasma jet exciter system |
| CN112179215A (en) * | 2020-09-21 | 2021-01-05 | 西安理工大学 | Flight guidance weapon control device based on plasma jet technology |
Non-Patent Citations (1)
| Title |
|---|
| 陈新海: "旋转式地空导弹控制系统分析", 《西北工业大学学报》 * |
Also Published As
| Publication number | Publication date |
|---|---|
| CN112937912B (en) | 2023-08-15 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN103066885B (en) | Wind-energy piezoelectric conversion generator by using vortex-induced vibration | |
| US6234751B1 (en) | Oscillating air jets for reducing HSI noise | |
| CN101012808A (en) | Wind turbine generator | |
| US9447771B2 (en) | Piezoelectric-based wind turbine | |
| CN112874757B (en) | A device for realizing active flow control method of pulse synergistic jet | |
| CN108684130A (en) | A kind of program-controlled array plasma jet exciter system | |
| CN108216617A (en) | A kind of method for inhibiting helicopter paddle-vortex interaction noise | |
| CN112937912A (en) | Array plasma-based rotation body lateral force control experimental device | |
| CN201723373U (en) | Retractable wind driven generator | |
| Gerdes et al. | Wing performance characterization for flapping wing air vehicles | |
| CN219565464U (en) | A deicing device | |
| Bryant et al. | Toward efficient aeroelastic energy harvesting: device performance comparisons and improvements through synchronized switching | |
| CN114910355B (en) | Device capable of directly generating tensile stress wave | |
| Li et al. | Numerical simulation investigation on the suction stroke and blowing stroke of synthetic jet circulation control | |
| CN111990392A (en) | Bird repellent device for electric power overhead line | |
| CN105818977B (en) | Ultrasonic detection unmanned aerial vehicle based on Internet of things | |
| CN106742049A (en) | One test device of superminiature rotor elevating movement propulsive performance | |
| CN103158880B (en) | Empty sky electric helicopter | |
| CN109319169A (en) | Device and method for improving airfoil separation stall by radio frequency discharge plasma excitation | |
| CN112179215B (en) | Flight guidance weapon control device based on plasma jet technology | |
| CN201837503U (en) | Automobile engine knocking sensor test stand and motor control circuit | |
| CN207311827U (en) | A kind of multiaxis unmanned plane high pressure concatenates motor | |
| CN223031280U (en) | Swan wing fan-like aircraft | |
| CN200959786Y (en) | Remote bird-scaring machine in airport | |
| CN101893514A (en) | Experiment bench with knock sensor for automobile engine and motor control circuit |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| TA01 | Transfer of patent application right | ||
| TA01 | Transfer of patent application right |
Effective date of registration: 20230417 Address after: 518000 1002, Building A, Zhiyun Industrial Park, No. 13, Huaxing Road, Henglang Community, Longhua District, Shenzhen, Guangdong Province Applicant after: Shenzhen Wanzhida Technology Co.,Ltd. Address before: 710048 Shaanxi province Xi'an Beilin District Jinhua Road No. 5 Applicant before: XI'AN University OF TECHNOLOGY |
|
| TA01 | Transfer of patent application right | ||
| TA01 | Transfer of patent application right |
Effective date of registration: 20230721 Address after: No. 12, Zhuoxi Road, Pukou District, Nanjing, Jiangsu 210000 Applicant after: Nanjing Nanhua Aviation Industry Co.,Ltd. Address before: 518000 1002, Building A, Zhiyun Industrial Park, No. 13, Huaxing Road, Henglang Community, Longhua District, Shenzhen, Guangdong Province Applicant before: Shenzhen Wanzhida Technology Co.,Ltd. |
|
| GR01 | Patent grant | ||
| GR01 | Patent grant |