CN116215904A - Multi-stage multi-degree-of-freedom ion wind aircraft - Google Patents
Multi-stage multi-degree-of-freedom ion wind aircraft Download PDFInfo
- Publication number
- CN116215904A CN116215904A CN202310521738.1A CN202310521738A CN116215904A CN 116215904 A CN116215904 A CN 116215904A CN 202310521738 A CN202310521738 A CN 202310521738A CN 116215904 A CN116215904 A CN 116215904A
- Authority
- CN
- China
- Prior art keywords
- pole plate
- plate
- freedom
- degree
- supports
- 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
- 230000002093 peripheral effect Effects 0.000 claims description 18
- 239000003822 epoxy resin Substances 0.000 claims description 5
- 229920000647 polyepoxide Polymers 0.000 claims description 5
- 230000007306 turnover Effects 0.000 claims description 3
- 239000004020 conductor Substances 0.000 claims description 2
- 239000011810 insulating material Substances 0.000 claims description 2
- 239000000463 material Substances 0.000 claims description 2
- 150000002500 ions Chemical class 0.000 description 65
- 238000010586 diagram Methods 0.000 description 8
- 238000003698 laser cutting Methods 0.000 description 6
- 238000004519 manufacturing process Methods 0.000 description 4
- 238000005520 cutting process Methods 0.000 description 3
- 239000011888 foil Substances 0.000 description 3
- 230000005540 biological transmission Effects 0.000 description 2
- 238000003763 carbonization Methods 0.000 description 2
- 238000006243 chemical reaction Methods 0.000 description 2
- 230000007547 defect Effects 0.000 description 2
- 238000009826 distribution Methods 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- 230000005684 electric field Effects 0.000 description 2
- 239000000835 fiber Substances 0.000 description 2
- 239000000446 fuel Substances 0.000 description 2
- 239000013307 optical fiber Substances 0.000 description 2
- XUIMIQQOPSSXEZ-UHFFFAOYSA-N Silicon Chemical compound [Si] XUIMIQQOPSSXEZ-UHFFFAOYSA-N 0.000 description 1
- 229910001069 Ti alloy Inorganic materials 0.000 description 1
- 230000001133 acceleration Effects 0.000 description 1
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 description 1
- 229910052782 aluminium Inorganic materials 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000015556 catabolic process Effects 0.000 description 1
- 230000008859 change Effects 0.000 description 1
- 238000002485 combustion reaction Methods 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 230000006872 improvement Effects 0.000 description 1
- 239000012535 impurity Substances 0.000 description 1
- 238000002347 injection Methods 0.000 description 1
- 239000007924 injection Substances 0.000 description 1
- 230000002427 irreversible effect Effects 0.000 description 1
- 238000005259 measurement Methods 0.000 description 1
- 230000007246 mechanism Effects 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 230000005404 monopole Effects 0.000 description 1
- 239000011664 nicotinic acid Substances 0.000 description 1
- 239000011148 porous material Substances 0.000 description 1
- 238000010248 power generation Methods 0.000 description 1
- 230000008569 process Effects 0.000 description 1
- 238000012545 processing Methods 0.000 description 1
- 238000011160 research Methods 0.000 description 1
- 229910052710 silicon Inorganic materials 0.000 description 1
- 239000010703 silicon Substances 0.000 description 1
- 230000000087 stabilizing effect Effects 0.000 description 1
- 239000000126 substance Substances 0.000 description 1
- 230000003245 working effect Effects 0.000 description 1
Images
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C39/00—Aircraft not otherwise provided for
- B64C39/02—Aircraft not otherwise provided for characterised by special use
- B64C39/028—Micro-sized aircraft
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
- B64D27/02—Aircraft characterised by the type or position of power plants
- B64D27/24—Aircraft characterised by the type or position of power plants using steam or spring force
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02A—TECHNOLOGIES FOR ADAPTATION TO CLIMATE CHANGE
- Y02A90/00—Technologies having an indirect contribution to adaptation to climate change
- Y02A90/10—Information and communication technologies [ICT] supporting adaptation to climate change, e.g. for weather forecasting or climate simulation
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Air-Conditioning For Vehicles (AREA)
Abstract
The invention relates to the technical field of aircrafts, in particular to a multi-degree-of-freedom ion wind aircraft which is formed by vertically distributing a plurality of multi-degree-of-freedom ion wind aircrafts in a derivative mode, wherein the multi-degree-of-freedom ion wind aircrafts comprise an upper pole plate, a middle pole plate and a lower pole plate, the upper pole plate, the middle pole plate and the lower pole plate are fixed together through a connecting bracket, an ion emitting device is arranged on the upper pole plate and the middle pole plate, and a sensor chip is also arranged on the upper pole plate. The invention can embed most small and medium-sized micro devices into the unmanned aerial vehicle to realize multifunctional ion wind unmanned aerial vehicle.
Description
Technical Field
The invention relates to the technical field of aircrafts, in particular to a multi-stage multi-degree-of-freedom ion wind aircraft which can be applied to slight unmanned aerial vehicles in various fields and provides a new thought for the development of aircrafts.
Background
Aviation aircrafts are indispensable transportation tools in modern society and are widely used in military and civil fields. A conventional aerospace vehicle includes: the fixed wing, rotary wing type and flapping wing type aircrafts generally adopt fuel power, electric power engines to drive movable parts such as propellers, turbofans, flapping wings and the like so as to generate propulsion force, or adopt chemical fuel combustion injection to form the propulsion force to realize flying. The aircraft has the defects of numerous mechanism impurities, low energy conversion efficiency, high noise and the like.
At present, unmanned aerial vehicles can be divided into rotor unmanned aerial vehicles (bionic unmanned aerial vehicles), the rotor unmanned aerial vehicles need large-scale motion driving components such as motors and engines to ensure that enough thrust force is provided for the unmanned aerial vehicles, and the flapping-wing unmanned aerial vehicles need to be strictly designed to control networks and have a certain technical bottleneck in the manufacturing and assembly process.
Disclosure of Invention
The invention provides and designs the multi-stage multi-degree-of-freedom ion wind aircraft which is compact in structure, high in precision and wide in application. The invention can be used as unmanned aerial vehicle in most fields, and the performance of each aspect is more ideal than that of a single-stage unmanned aerial vehicle with the same principle due to a multi-stage structure. Meanwhile, various micro devices are embedded, so that the multifunctional device is realized. The invention uses the ion force generated by ion power generation as the thrust, does not need to add any power device on the equipment, improves the ratio of thrust to weight and reduces the duty ratio in the three-dimensional space. In addition, the single-stage ion wind unmanned aerial vehicle can provide limited kinetic energy, and because the structure is simpler, not enough space can embed other equipment again, has partly restricted its working property and usage. Therefore, the multistage ion wind aircraft disclosed by the invention can solve the defects of a single-stage aircraft and is a device with wider application range.
The invention adopts the specific technical scheme that:
the multi-stage multi-degree-of-freedom ion wind aircraft consists of a plurality of multi-degree-of-freedom ion wind aircraft derivatives which are vertically distributed, wherein the multi-degree-of-freedom ion wind aircraft comprises an upper pole plate, a middle pole plate and a lower pole plate, the upper pole plate, the middle pole plate and the lower pole plate are fixed together through a connecting bracket, and ion emitting devices are arranged on the upper pole plate and the middle pole plate and further comprise a sensor chip.
The upper electrode plate is an equilateral triangle, three corners of the equilateral triangle are connecting holes for fixing the connecting support for the upper electrode plate, the edges of the equilateral triangle are peripheral supports for the upper electrode plate, a circular upper electrode plate center end point is arranged at the position of the geometric center of the upper electrode plate, fixing supports for fixing the ion emitting device are set as upper electrode plate fixing supports in a way that the upper electrode plate center end point extends to the periphery, the number of the upper electrode plate fixing supports is three, the angles between every two of the three upper electrode plate fixing supports are 120 degrees, and the ion emitting device is fixed below the upper electrode plate fixing supports.
The whole middle pole plate is an equilateral triangle, three corners of the equilateral triangle are connecting holes for fixing the middle pole plate to the connecting supports, the connecting holes are set as middle pole plate support connecting holes, the edges of the equilateral triangle are middle pole plate peripheral supports, an ion emitting device is fixed below the middle pole plate peripheral supports, a round middle pole plate center endpoint is arranged at the position of the middle pole plate geometric center, a sensor chip is arranged at the middle pole plate center endpoint, supports are arranged on the middle pole plate center endpoint in a circumferential extending mode to set middle pole plate supports, the number of the middle pole plate supports is three, and the angle between every two of the three middle pole plate supports is 120 degrees.
The whole lower electrode plate is an equilateral triangle, three corners of the equilateral triangle are connecting holes of the lower electrode plate for fixing the connecting support, the connecting holes are set as connecting holes of the lower electrode plate support, the edges of the equilateral triangle are peripheral supports of the lower electrode plate, and the center of the lower electrode plate is provided with an inner support of the lower electrode plate; the middle pole plate support and the lower pole plate peripheral support adopt hollow structures.
In the technical scheme, the multistage miniature unmanned aerial vehicle is formed by vertically distributing a plurality of ion wind air vehicles with multiple degrees of freedom in a derivative mode, the two-stage unmanned aerial vehicle comprises an upper stage and a lower stage, and a total of six ion emitting devices (the length of each ion emitting device is determined by distribution) formed by vertically distributed pins, an upper polar plate, a middle polar plate, a lower polar plate and six connecting supports. The upper polar plate is used for fixing the ion emitting device and stabilizing the integral structure. The three small holes symmetrically distributed on the middle polar plate are used for embedding the three connecting brackets, a group of open pore structures are arranged on each edge of the middle polar plate and used for better assisting the distribution of an electric field, the direction of ion flow is ensured to be consistent with the expected direction, and when a certain negative voltage is applied to the middle polar plate or the potential difference between the transmitting end of the ion transmitting device and the collector electrode is increased, the collector electrode can enhance the flow of positive ions, so that the size of ion wind can be increased. The center line of the lower plate is formed with a set of openings to promote the flow of ionic wind so that the air flow generally follows the desired direction specified by the present invention, neither the upper fence structure nor the lower open structure should be too tight, and if the openings are too tight, the gas flow is not favored, while the mass is also increased.
According to the invention, the upper end of the connecting bracket is composed of four groups of fence structures, two mounting grooves which are respectively an upper mounting groove and a lower mounting groove are arranged in the middle of the connecting bracket, and the lower structure of the connecting bracket keeps the connecting bracket to be horizontally and parallelly erected on a plane. If the connecting bracket is too long, the ion thrust is reduced while the mass is increased, if the connecting bracket is too short, when the applied electric field is slightly too large, ion conduction breakdown is easily formed between the emitting end and the collecting end, so that the device is burnt out to form irreversible damage, and meanwhile, from the manufacturing point of view, the assembly time length is greatly increased when the connecting bracket is too short, so that the control bracket is also a subject worthy of research, and the control bracket is generally worth trying to take the length of not more than 150 mm.
The ion emission device comprises a strip device for fixing the ion emission level pin, the two ends of the strip device are provided with corner hooking buckles which are convenient to fix at the gap formed by four groups of fences at the top of the connecting support, and the angle of the ion emission level pin is between 5 degrees and 15 degrees. Because the ion emission level needle arrangement is a miniature angle of 5 degrees to 15 degrees and is perpendicular to the strip device, most of the repelled positive ions can move towards the direction of the three-dimensional horizontally placed collecting end, so that other ions are pushed to be electrified and move towards the direction of the collecting end, and finally, ion wind is formed to push the aircraft to carry out flight operation.
The sensor chip is fixed at the center end point of the middle polar plate through epoxy resin, the sensor chip adopts a nine-axis inertial sensor chip, three accelerometers, three turnover angle meters and three magnetic intensity meters are arranged in the sensor chip, and data are transmitted into a computer through a transmission line so as to acquire flight information. Meanwhile, track tracking is put in, so that intelligent measurement and control are realized.
According to a further improvement of the invention, the upper electrode plate, the middle electrode plate and the lower electrode plate are made of conductive materials, such as titanium alloy foil, aluminum foil or silicon foil; the connecting bracket material is made of insulating materials, such as pet film; the connection points of the upper polar plate, the middle polar plate and the lower polar plate with the connecting bracket are reinforced by epoxy resin.
Since the micro-aircraft itself is small in size, any small burrs or errors will have a large interference and impact on the results, the manufacturing tools of the various components in the present application employ laser cutters: both fiber laser cutting and ultraviolet laser cutting machines can be used to make devices. The fiber laser cutting machine is processed in a vibrating mirror scanning mode, so that the cutting power is high, the cutting time is short, but the edge is seriously carbonized, deformation is easy to generate, and even burrs are generated; the ultraviolet laser cutting machine has lower processing efficiency than the optical fiber laser cutting machine and long cutting time, but the processed finished product has good effect, no burr on the edge, low carbonization degree and no deformation of the edge due to heat influence. In the present invention, an ultraviolet laser cutter is used when the upper, middle and lower electrode plates are used, and an optical fiber laser cutter is used for the rest.
In the invention, the upper electrode plate and the middle electrode plate combination or the middle electrode plate and the lower electrode plate combination can be used as a monopole ion wind aircraft, and the multistage multi-degree-of-freedom ion wind aircraft can be overlapped and combined in the same way, and is not limited to a two-stage double-layer structure.
The invention has the beneficial effects that: the invention respectively introduces three independently addressable high-voltage direct currents into the emitting end of each layer of ion emitting device, and at the initial stage, the voltages are constant, so that the aircraft can keep a stable horizontal posture in the step of taking off, then the data transmitted by the built-in 9-axis inertial sensor chip are read out, the height, the posture and the acceleration are transmitted into a computer algorithm for operation, the operation value is transmitted to a power supply control end through the data-voltage algorithm, and the unmanned aircraft is subjected to flight state adjustment by changing the independently addressable voltage. The invention has more ideal performance than single-stage unmanned aerial vehicle with the same principle due to the multi-stage structure, and each stage can be used as a single-stage ion wind aircraft in which various micro devices are embedded, thereby realizing multiple functions.
Drawings
Fig. 1 is a schematic perspective view of a two-pole multi-degree-of-freedom ion wind aircraft in the invention.
Fig. 2 is a schematic structural diagram of the upper plate in fig. 1.
Fig. 3 is a schematic structural diagram of the middle-layer plate in fig. 1.
Fig. 4 is a schematic structural diagram of the lower plate in fig. 1.
Fig. 5 is a schematic structural view of the connection bracket in fig. 1.
Fig. 6 is a schematic structural diagram of the ion emitting apparatus in fig. 1.
Fig. 7 is a schematic diagram of the overall circuit connection of the present invention.
Fig. 8 is a schematic diagram of the overall circuit control connection of the present invention.
In the figure, 1-upper electrode plate, 2-middle electrode plate, 3-lower electrode plate, 4-connecting support, 5-ion emitting device, 6-sensor chip, 101-upper electrode plate support connecting hole, 102-upper electrode plate fixing support, 103-upper electrode plate peripheral support, 104-upper electrode plate center end point, 201-middle electrode plate support connecting hole, 202-middle electrode plate support, 203-middle electrode plate peripheral support, 204-middle electrode plate center end point, 301-lower electrode plate support connecting hole, 302-lower electrode plate inner support, 303-lower electrode plate peripheral support, 401-fence, 402-cuttable part, 403-upper mounting groove, 404-lower mounting groove, 405-lower structure, 501-strip device, 502-emitting stage row needle, 503-corner hooking buckle.
Description of the embodiments
The present invention will be further described in detail with reference to the drawings and examples, which are only for the purpose of illustrating the invention and are not to be construed as limiting the scope of the invention.
Examples: as shown in fig. 1, the multi-level multi-degree-of-freedom ion wind aircraft is formed by vertically distributing a plurality of multi-level-of-freedom ion wind aircraft derivatives, the multi-level-of-freedom ion wind aircraft comprises an upper pole plate 1, a middle pole plate 2 and a lower pole plate 3, the upper pole plate 1, the middle pole plate 2 and the lower pole plate 3 are fixed together through a connecting bracket 4, an ion emitting device 5 is arranged on the upper pole plate 1 and the middle pole plate 2, and the multi-level-of-freedom ion wind aircraft further comprises a sensor chip 6.
As shown in fig. 2, the upper electrode plate 1 is an equilateral triangle, three corners of the equilateral triangle are connecting holes of the upper electrode plate 1 for fixing the connecting support, the connecting holes are set as upper electrode plate support connecting holes 101, the sides of the equilateral triangle are upper electrode plate peripheral supports 103, a circular upper electrode plate center end point 104 is arranged at the geometric center of the upper electrode plate 1, fixing supports for fixing the ion emitting device 5 are set as upper electrode plate fixing supports 102 in a manner that the upper electrode plate center end point 104 extends to the periphery, the number of the upper electrode plate fixing supports 102 is three, the angles between every two of the three upper electrode plate fixing supports 102 are 120 degrees, and the ion emitting device 5 is fixed below the upper electrode plate fixing supports 102.
As shown in fig. 3, the middle pole plate 2 is an equilateral triangle, three corners of the equilateral triangle are connecting holes for fixing the middle pole plate 2 and connecting the support 4, and are set as middle pole plate support connecting holes 201, the sides of the equilateral triangle are middle pole plate peripheral supports 203, an ion emitting device 5 is fixed below the middle pole plate peripheral supports 203, a circular middle pole plate center end 204 is arranged at the position of the geometric center of the middle pole plate 2, a sensor chip 6 is arranged at the middle pole plate center end 204, the sensor chip 6 is fixed by epoxy resin, the sensor chip 6 adopts nine-axis inertial sensor chips, three accelerometers, three turnover angle meters and three magnetic intensity meters are arranged in the sensor chip 6, data are transmitted into a computer through transmission lines to obtain flight information, the middle pole plate center end 204 extends to the periphery and is provided with support setting middle pole plate supports 202, the number of the middle pole plate supports 202 is three, the angle between every two middle pole plate supports 202 is 120 °, and the support of the middle pole plate 1 adopts a hollowed structure.
As shown in fig. 4, the lower electrode plate 3 is an equilateral triangle, three corners of the equilateral triangle are connecting holes of the lower electrode plate 3 for fixing the connecting support 4, and are set as lower electrode plate support connecting holes 301, the sides of the equilateral triangle are lower electrode plate peripheral supports 302, a lower electrode plate inner support 303 is arranged at the center of the lower electrode plate 3, and the lower electrode plate peripheral supports 302 adopt a hollow structure.
The upper end of the connecting bracket 4 consists of four groups of fence 401 structures, three groups of gap structures are reserved, so that the connecting bracket is convenient to connect and fix, meanwhile, the three-dimensional space structures of the three groups of brackets are also kept in one-to-one symmetry, otherwise, the generated force is inconsistent, immeasurable interference is generated in subsequent control, and a cuttable part 402 is arranged in the middle of the connecting bracket 4. The connection bracket 4 substructure 405 keeps the connection bracket horizontally parallel to the plane.
As shown in fig. 6, the ion emission device 5 includes a strip device 501 for fixing ion emission stage pins 503, two ends of the strip device 501 are provided with hook angle buckles 502 so as to be conveniently fixed at a gap formed by four groups of fences 401 at the top of the connecting bracket 4, the angle of each pin can be 5-15 degrees, the pins are orderly arranged at the emission end, and high positive voltage is connected to the pins to ionize surrounding air, so that positive ions generated are shown as a needle point; during manufacture, a proper laser cutting machine and proper power are selected, otherwise, the finished product has serious carbonization reaction and light spots. Because the invention needs a plurality of groups of transmitting ends with different specifications, the length of the transmitting end needs to be changed according to different requirements, and the transmitting ends are scaled.
Fig. 7 is a schematic diagram of the overall circuit connection of the present invention, wherein the ion emitting device of the upper electrode plate is connected to the positive electrode of the high voltage power supply, the middle electrode plate is connected to the negative electrode of the high voltage power supply or grounded, the ion emitting device of the middle electrode plate is connected to the positive electrode of the high voltage power supply, and the lower electrode plate is connected to the negative electrode of the high voltage power supply. The middle-layer polar plate not only collects charged ion wind for the upper-stage ion emitting device, but also connects and fixes the ion emitting device for the lower stage, plays a role in supporting the upper and lower stages, forms potential difference with the upper-stage emitting end by connecting negative voltage or grounding to the middle-stage polar plate, can be used for receiving charged positive ions transmitted by the upper-stage ion emitting device, and standardizes the circulation direction and track of the ions to a certain extent. The lower electrode plate is connected with negative voltage or grounded, and a potential difference is formed between the lower electrode plate and the middle electrode plate, so that the lower electrode plate can be used for receiving charged positive ions transmitted by the upper ion transmitting device and normalizing the circulation direction and track of the ions to a certain extent.
Fig. 5 is a circuit connection mode of the multi-stage ion wind unmanned aerial vehicle, wherein two positive voltages are respectively connected to the emitting stages of the upper layer and the lower layer, so that directional ion wind from the emitting stage to the collecting stage is generated, and the magnitude of the ion wind speed can be controlled by changing the voltages, so that directional and constant-speed control is formed.
Fig. 8 is a schematic diagram of an overall circuit control connection of the invention, which can intelligently regulate and control the input voltage values of the upper layer and the lower layer by PID control and analysis on data transmitted by a sensor chip embedded in the ion wind aircraft, and change the input value of a power supply in real time, thereby realizing the functions of self-steady cruising, remote control of the flight direction and the like of the ion wind aircraft. Meanwhile, the connecting wire adopts a flying wire with the thickness of 0.02mm, so that the voltage is effectively transmitted, a good insulating effect is achieved, and the weight of the connecting wire can be ignored.
The technical features of the above embodiments may be arbitrarily combined, and for brevity, all of the possible combinations of the technical features of the above embodiments are not described, and meanwhile, no specific picture is displayed on the multi-stage ion wind turbine, however, as long as there is no contradiction between the combinations of the technical features, all should be considered as the scope described in the present specification.
Claims (9)
1. The multi-stage multi-degree-of-freedom ion wind aircraft is characterized by being formed by vertically distributing a plurality of multi-degree-of-freedom ion wind aircraft derivatives, the multi-degree-of-freedom ion wind aircraft comprises an upper pole plate, a middle pole plate and a lower pole plate, the upper pole plate, the middle pole plate and the lower pole plate are fixed together through a connecting bracket, and ion emitting devices are arranged on the upper pole plate and the middle pole plate and further comprise sensor chips.
2. The multi-stage multi-degree-of-freedom ionic wind aircraft of claim 1, wherein the upper polar plate is an equilateral triangle as a whole, three corners of the equilateral triangle are connecting holes of the upper polar plate for fixing the connecting support, the connecting holes are set as upper polar plate support connecting holes, the edges of the equilateral triangle are peripheral supports of the upper polar plate, a circular upper polar plate center endpoint is arranged at the geometric center of the upper polar plate, fixing supports for fixing the ion emitting device are set as upper polar plate fixing supports in a way that the upper polar plate center endpoint extends to the periphery, the number of the upper polar plate fixing supports is three, the angles between every two of the three upper polar plate fixing supports are 120 degrees, and the ion emitting device is fixed below the upper polar plate fixing supports.
3. The multi-stage multi-degree-of-freedom ionic wind aircraft of claim 2, wherein the middle pole plate is an equilateral triangle as a whole, three corners of the equilateral triangle are connecting holes for fixing the middle pole plate to the connecting support, the connecting holes are set as middle pole plate support, the edges of the equilateral triangle are the middle pole plate peripheral support, an ion emitting device is fixed below the middle pole plate peripheral support, a circular middle pole plate center end point is arranged at the position of the middle pole plate geometric center, a sensor chip is arranged at the middle pole plate center end point, supports for setting middle pole plate supports are arranged in a extending mode from the middle pole plate center end point to the periphery, the number of the middle pole plate supports is three, and the angles between every two of the three middle pole plate supports are 120 degrees.
4. The multi-stage multi-degree-of-freedom ionic wind aircraft of claim 3, wherein the lower plate is an equilateral triangle as a whole, three corners of the equilateral triangle are connecting holes of the lower plate for fixing the connecting support, the connecting holes are set as lower plate support connecting holes, the sides of the equilateral triangle are peripheral supports of the lower plate, and an inner support of the lower plate is arranged in the center of the lower plate.
5. The multi-stage multi-degree-of-freedom ionic wind aircraft of claim 4, wherein the upper end of the connecting bracket is composed of four groups of fence structures, two mounting grooves are respectively an upper mounting groove and a lower mounting groove in the middle position of the connecting bracket, and the lower structure of the connecting bracket keeps the connecting bracket horizontally and parallelly standing on a plane.
6. The multi-stage multi-degree-of-freedom ionic wind aircraft of claim 4 wherein the ionic emission device comprises a strip device for fixing the ionic emission stage pin header, wherein hook angle buckles are arranged at two ends of the strip device and are convenient to fix at gaps formed by four groups of fences at the top of the connecting support, and the angle of the ionic emission stage pin header is between 5 degrees and 15 degrees.
7. The multi-stage multi-degree-of-freedom ionic wind aircraft of claim 5, wherein the sensor chip is fixed at the center end point of the middle-layer polar plate through epoxy resin, and nine-axis inertial sensor chips are adopted as the sensor chip, and three accelerometers, three turnover angle meters and three magnetic intensity meters are built in the sensor chip.
8. The multi-stage, multi-degree of freedom ionic wind aircraft of any one of claims 1-7 wherein the upper, middle and lower plates are made of conductive material and the connecting bracket material is made of insulating material, and the connection points of the upper, middle and lower plates to the connecting bracket are reinforced with epoxy resin.
9. The multi-stage multi-degree-of-freedom ionic wind aircraft of claim 8, wherein the middle-layer polar plate support and the lower-layer polar plate peripheral support adopt hollow structures.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202310521738.1A CN116215904A (en) | 2023-05-10 | 2023-05-10 | Multi-stage multi-degree-of-freedom ion wind aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202310521738.1A CN116215904A (en) | 2023-05-10 | 2023-05-10 | Multi-stage multi-degree-of-freedom ion wind aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN116215904A true CN116215904A (en) | 2023-06-06 |
Family
ID=86570099
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202310521738.1A Pending CN116215904A (en) | 2023-05-10 | 2023-05-10 | Multi-stage multi-degree-of-freedom ion wind aircraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN116215904A (en) |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102128138A (en) * | 2010-11-29 | 2011-07-20 | 李树广 | Multilayer stacking combined vertical type wind power generation system |
| US20190127063A1 (en) * | 2016-04-22 | 2019-05-02 | Burak Gozluklu | Three dimensional scalable and modular aircraft |
| US20190152625A1 (en) * | 2014-08-07 | 2019-05-23 | Ethan Daniel Krauss | Ion propelled vehicle |
| CN110228583A (en) * | 2019-05-23 | 2019-09-13 | 中国科学院合肥物质科学研究院 | A kind of ion wind solid state flight device and its control method |
| CN113056418A (en) * | 2018-11-16 | 2021-06-29 | 渥美不动产有限公司 | Flight body and flight body control system |
| CN116002050A (en) * | 2022-11-14 | 2023-04-25 | 中国科学院合肥物质科学研究院 | Self-rotating type multi-freedom-degree solid-state aircraft based on dislocation needle-line structure and control method thereof |
-
2023
- 2023-05-10 CN CN202310521738.1A patent/CN116215904A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102128138A (en) * | 2010-11-29 | 2011-07-20 | 李树广 | Multilayer stacking combined vertical type wind power generation system |
| US20190152625A1 (en) * | 2014-08-07 | 2019-05-23 | Ethan Daniel Krauss | Ion propelled vehicle |
| US20190127063A1 (en) * | 2016-04-22 | 2019-05-02 | Burak Gozluklu | Three dimensional scalable and modular aircraft |
| CN113056418A (en) * | 2018-11-16 | 2021-06-29 | 渥美不动产有限公司 | Flight body and flight body control system |
| CN110228583A (en) * | 2019-05-23 | 2019-09-13 | 中国科学院合肥物质科学研究院 | A kind of ion wind solid state flight device and its control method |
| CN116002050A (en) * | 2022-11-14 | 2023-04-25 | 中国科学院合肥物质科学研究院 | Self-rotating type multi-freedom-degree solid-state aircraft based on dislocation needle-line structure and control method thereof |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US8083173B2 (en) | Rotarycraft power and propulsion system | |
| CN206218239U (en) | Unmanned vehicle | |
| Ahmed et al. | Modeling and analysis of quadcopter F450 frame | |
| CN204965186U (en) | Vacant lot amphibious robot that patrols and examines of integration | |
| CN108327926B (en) | Modular spacecraft capable of on-orbit allosteric | |
| US11161631B2 (en) | Ion propelled vehicle | |
| US20130313948A1 (en) | Electric Motor/Generator With Multiple Individually Controlled Turn-Less Structures | |
| WO2013078860A1 (en) | Concentric-winding permanent magnet synchronous planar motor | |
| CN111591451A (en) | Ionic wind propelled airplane and propelling method thereof | |
| US3130945A (en) | Ionocraft | |
| CN116215904A (en) | Multi-stage multi-degree-of-freedom ion wind aircraft | |
| CN110228583A (en) | A kind of ion wind solid state flight device and its control method | |
| CN111854541A (en) | Folding wing micro missile platform | |
| CN212951119U (en) | Correcting device based on unmanned aerial vehicle fuselage slope | |
| JP3980353B2 (en) | Power supply mechanism for ROSAR transponder including transmission / reception antenna for ROSAR device | |
| CN116002050A (en) | Self-rotating type multi-freedom-degree solid-state aircraft based on dislocation needle-line structure and control method thereof | |
| CN116923744A (en) | Plasma vertical take-off and landing unmanned aerial vehicle | |
| CN207374652U (en) | Unmanned plane | |
| CN109606623A (en) | Intelligent modularized solar energy unmanned plane | |
| CN101813074B (en) | Simplified annular atmosphere power machine | |
| KR20220125768A (en) | Drone having energy harvesting device | |
| Zabunov | XZ-Series of Unmanned Aerial Vehicles in 2020 | |
| Guizani | Low energy system proposal for UAV applications using flexible solar cells | |
| CN102490907A (en) | Airplane for aerial photography | |
| Poon et al. | Noiseless and vibration-free ionic propulsion technology for indoor surveillance blimps |
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 | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20230606 |
|
| RJ01 | Rejection of invention patent application after publication |