CN116573144A - Mongolian dandelion seed-imitated micro aircraft oriented to individual intelligent battlefield - Google Patents
Mongolian dandelion seed-imitated micro aircraft oriented to individual intelligent battlefield Download PDFInfo
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- CN116573144A CN116573144A CN202310850585.5A CN202310850585A CN116573144A CN 116573144 A CN116573144 A CN 116573144A CN 202310850585 A CN202310850585 A CN 202310850585A CN 116573144 A CN116573144 A CN 116573144A
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- 235000005187 Taraxacum officinale ssp. officinale Nutrition 0.000 title claims abstract description 40
- 241000245665 Taraxacum Species 0.000 title claims abstract description 39
- 238000003860 storage Methods 0.000 claims description 36
- 239000000178 monomer Substances 0.000 claims description 7
- 229920001721 polyimide Polymers 0.000 claims description 5
- 239000007787 solid Substances 0.000 claims description 3
- 238000009792 diffusion process Methods 0.000 abstract description 8
- 238000000926 separation method Methods 0.000 abstract description 7
- 238000004088 simulation Methods 0.000 description 12
- 108010066278 cabin-4 Proteins 0.000 description 5
- 238000013461 design Methods 0.000 description 5
- 238000002474 experimental method Methods 0.000 description 5
- 238000000034 method Methods 0.000 description 5
- 238000001514 detection method Methods 0.000 description 4
- 239000011664 nicotinic acid Substances 0.000 description 4
- 238000005516 engineering process Methods 0.000 description 3
- 230000002035 prolonged effect Effects 0.000 description 3
- 238000004364 calculation method Methods 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 238000011835 investigation Methods 0.000 description 2
- 238000012544 monitoring process Methods 0.000 description 2
- 230000008569 process Effects 0.000 description 2
- 238000003892 spreading Methods 0.000 description 2
- 230000007480 spreading Effects 0.000 description 2
- 208000035473 Communicable disease Diseases 0.000 description 1
- 240000001949 Taraxacum officinale Species 0.000 description 1
- 239000000809 air pollutant Substances 0.000 description 1
- 231100001243 air pollutant Toxicity 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000004140 cleaning Methods 0.000 description 1
- 230000008878 coupling Effects 0.000 description 1
- 238000010168 coupling process Methods 0.000 description 1
- 238000005859 coupling reaction Methods 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000009826 distribution Methods 0.000 description 1
- 239000012530 fluid Substances 0.000 description 1
- 208000015181 infectious disease Diseases 0.000 description 1
- 238000003698 laser cutting Methods 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 244000052769 pathogen Species 0.000 description 1
- 230000001717 pathogenic effect Effects 0.000 description 1
- 238000011160 research Methods 0.000 description 1
- 238000012360 testing method Methods 0.000 description 1
Classifications
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- 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; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D1/00—Dropping, ejecting, releasing, or receiving articles, liquids, or the like, in flight
- B64D1/02—Dropping, ejecting, or releasing articles
- B64D1/08—Dropping, ejecting, or releasing articles the articles being load-carrying devices
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D1/00—Dropping, ejecting, releasing, or receiving articles, liquids, or the like, in flight
- B64D1/02—Dropping, ejecting, or releasing articles
- B64D1/08—Dropping, ejecting, or releasing articles the articles being load-carrying devices
- B64D1/12—Releasing
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U10/00—Type of UAV
- B64U10/10—Rotorcrafts
- B64U10/13—Flying platforms
- B64U10/14—Flying platforms with four distinct rotor axes, e.g. quadcopters
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U2101/00—UAVs specially adapted for particular uses or applications
- B64U2101/60—UAVs specially adapted for particular uses or applications for transporting passengers; for transporting goods other than weapons
- B64U2101/69—UAVs specially adapted for particular uses or applications for transporting passengers; for transporting goods other than weapons the UAVs provided with means for airdropping goods, e.g. deploying a parachute during descent
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- 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
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/50—On board measures aiming to increase energy efficiency
Abstract
The application discloses a dandelion seed-imitated micro aircraft for an individual intelligent battlefield, which comprises at least one single aircraft, wherein the single aircraft comprises a central disc, disc slats and a load cabin, the load cabin is arranged below the central disc, the disc slats are arranged around the central disc, the disc slats are of multi-aperture structures, the disc slats on two sides of the central disc are bent upwards, each disc slat comprises a plurality of fixed shafts and a fixed ring, one end of each fixed shaft is connected with the central disc, the fixed shafts are uniformly distributed around the central disc, gaps are formed between every two adjacent fixed shafts, the other ends of the fixed shafts are connected with the fixed rings, and the width of one end of each fixed shaft close to each fixed ring is larger than the width of one end of each fixed shaft close to each central disc. The single aircraft is designed by referring to the principle of dandelion seed induced generation of separation vortex ring, and has the advantages of simple structure, stable performance, long stagnation time and wide diffusion range.
Description
Technical Field
The application relates to an individual intelligent battlefield-oriented dandelion seed-imitating micro aircraft, and belongs to the technical field of aircrafts.
Background
In modern warfare, soldiers often have difficulty in intuitively perceiving the surrounding combat environment due to the complexity of the terrain and environment, and still are a great difficulty for pre-war investigation and post-war cleaning. However, existing detection means, such as large-scale radio detection technology or aerial photography with traditional unmanned aerial vehicles, mostly have the defects of poor concealment, small detection range, short endurance time and high cost. The micro aircraft has the characteristics of small volume, good concealment and the like.
The dandelion is a light herbal structure, has light weight and small volume, can be diffused to a far range along with wind, and has extremely gentle flight process and long dead time. Researches show that the coronary hair of dandelion has a porous characteristic, when wind blows, a pressure difference is formed between air flowing around dandelion seeds, so that the dandelion can generate a unique vortex ring separating phenomenon in the flying process, and the dandelion can maintain good flying performance. The advantages of dandelion can be well applied to the design of miniature aircrafts facing modern war.
Therefore, a new dandelion seed-imitated micro-aircraft facing an individual intelligent battlefield is needed to solve the problems.
Disclosure of Invention
The application aims to provide an individual intelligent battlefield-oriented dandelion seed-imitating micro aircraft so as to solve the problems in the background technology.
The utility model provides a imitative dandelion seed miniature vehicle towards individual soldier's intelligent battlefield, includes at least one monomer aircraft, the monomer aircraft includes central disc, dish slat and load cabin, the below of central disc is provided with the load cabin, be provided with around the central disc the dish slat, the dish slat of central disc both sides is crooked upwards, the dish slat includes many fixed axles and a solid fixed ring, the one end of fixed axle is connected the central disc, fixed axle evenly distributed is in around the central disc, adjacent be provided with the space between the fixed axle, the other end of fixed axle is connected gu fixed ring, the fixed axle is close to gu fixed ring's one end width is greater than the fixed axle is close to the one end width of central disc.
Still further, the number of the fixed shafts is 52.
Further, the diameter of the central disc is 28mm, the length of the fixed shaft is 10mm, the arc length of one end of the fixed shaft, which is close to the central disc, is 0.08mm, and the arc length of the other end of the fixed shaft is 0.732mm.
Still further, the curvature of the disk slat is 0.0563.
Still further, the disk slat has a porosity of 31.6%.
Still further, a solar panel is included, the solar panel being disposed above the central disk.
Still further still, still include unmanned aerial vehicle and aircraft and put in the casket, aircraft puts in the casket setting and is in unmanned aerial vehicle's below, aircraft puts in the casket and is provided with at least one the monomer aircraft.
Still further, aircraft drop in casket includes storage cabin, cabin cover and connecting rod, the below of storage cabin is provided with the opening, the opening part is provided with the cabin cover, one side of cabin cover with storage cabin one side is passed through the connecting rod is connected.
Still further, the storage cabin is divided into a plurality of storage areas, and the below of every storage area all is provided with the opening, and every opening all is provided with the cabin cover, every the cabin cover all passes through the connecting rod is connected the storage cabin, the connecting rod passes through solenoid valve control. Each storage area is connected with an electromagnetic valve through a connecting rod, and the opening of the hatch cover is controlled independently, so that the aircraft can be conveniently put in a plurality of times.
Further, the disk slat is prepared by using polyimide film. The polyimide film is degradable, making the monomeric aircraft environmentally friendly.
The principle of the application: the single aircraft disclosed by the application is obtained by simulation by utilizing the advantages of stable flying, wide diffusion range and long dead time of dandelion seeds, wherein the single aircraft comprises a central disc and a porous disc slat, and a payload is carried below the central disc. The disk slat can generate a separation vortex ring around the disk slat to provide lift force when in passive flight, so that the disk slat has stable flight performance, long dead time and wide diffusion range.
The beneficial effects are that: the single aircraft of the dandelion seed-imitated micro aircraft for the individual intelligent battlefield is designed by referring to the principle of dandelion seed induced generation of separation vortex ring, and has the advantages of simple structure, reasonable design, stable flight performance, long idle time and wide diffusion range.
Drawings
FIG. 1 is a schematic diagram of an individual intelligent battlefield-oriented dandelion-seed-imitated micro-aircraft and a throwing system thereof;
FIG. 2 is a schematic structural view of an individual intelligent battlefield-oriented dandelion-seed-imitated micro-aircraft;
FIG. 3 is a front view of an individual intelligent battlefield oriented dandelion-like seed micro-aircraft;
FIG. 4 is a top view of an individual intelligent battlefield oriented dandelion-like seed micro-aircraft;
FIG. 5 is a schematic view of a micro-aircraft drop box structure
FIG. 6 is a real dandelion seed wake display experiment;
FIG. 7 is a pneumatic simulated flow diagram of an individual intelligent battlefield oriented dandelion-seed-simulated micro-aircraft;
FIG. 8 is a graph of drag coefficient at different Reynolds numbers;
fig. 9 is a graph of drag coefficient at different payloads.
Reference numerals: 1-single aircraft, 2-unmanned aerial vehicle, 3-aircraft throwing box, 4-storage cabin, 5-cabin cover, 6-connecting rod, 7-center disc, 8-disc slat, 9-solar panel, 10-load cabin.
Description of the embodiments
The present application is further illustrated in the accompanying drawings and detailed description which are to be understood as being merely illustrative of the application and not limiting of its scope, and various modifications of the application, which are equivalent to those skilled in the art upon reading the application, will fall within the scope of the application as defined in the appended claims.
Referring to fig. 1-4, the dandelion seed-imitating micro-aircraft for an individual intelligent battlefield comprises at least one single aircraft 1, wherein the single aircraft comprises a central disc 7, disc slats 8 and a load cabin 10, the load cabin 10 is arranged below the central disc 7, the disc slats 8 are arranged around the central disc 7, the disc slats 8 on two sides of the central disc 7 are bent upwards, the disc slats 8 comprise a plurality of fixed shafts and a fixed ring, one ends of the fixed shafts are connected with the central disc 7, the fixed shafts are uniformly distributed around the central disc 7, gaps are arranged between adjacent fixed shafts, the other ends of the fixed shafts are connected with the fixed ring, and the width of one ends of the fixed shafts, which are close to the fixed ring, is larger than that of one ends of the fixed shafts, which are close to the central disc 7. Wherein the width of the fixed shaft gradually and uniformly changes from one end to the other end. The gap of the disk slat 8 is gradually increased from the central disk to the fixed ring, so that the structure is more similar to that of dandelion seeds. Specifically, the number of fixed shafts is 52. The diameter of the central disc 7 is 28mm, the length of the fixed shaft is 10mm, the arc length of one end of the fixed shaft close to the central disc 7 is 0.08mm, and the arc length of the other end of the fixed shaft is 0.732mm. The curvature of the disk slat 8 is 0.0563. The porosity of the disk slat 8 was 31.6%.
Preferably, a solar panel 9 is also included, the solar panel 9 being arranged above the central disc 7. If necessary, a certain energy source is provided for the effective load in the lower load cabin, and the acting time is prolonged.
Preferably, the unmanned aerial vehicle further comprises an unmanned aerial vehicle 2 and an aircraft throwing box 3, wherein the aircraft throwing box 3 is arranged below the unmanned aerial vehicle 2, and the aircraft throwing box 3 is provided with at least one single aircraft 1. Specifically, the aircraft delivery box 3 comprises a storage cabin 4, a cabin cover 5 and a connecting rod 6, an opening is formed in the lower portion of the storage cabin 4, the cabin cover 5 is arranged at the opening, and one side of the cabin cover 5 is connected with one side of the storage cabin 4 through the connecting rod 6. Preferably, the storage compartment 4 is divided into a plurality of storage areas, an opening is arranged below each storage area, a compartment cover 5 is arranged on each opening, each compartment cover 5 is connected with the storage compartment 4 through a connecting rod 6, and the connecting rod 6 is controlled through an electromagnetic valve. Each storage area is connected with an electromagnetic valve through a connecting rod, and the opening of the hatch cover is controlled independently, so that the aircraft can be conveniently put in a plurality of times.
Preferably, the disk slat 8 is made from polyimide film. The polyimide film has the characteristics of degradability and high temperature resistance, so that the monomer aircraft is environment-friendly.
The principle of the application: the single aircraft disclosed by the application is obtained by simulation by utilizing the advantages of stable flying, wide diffusion range and long dead time of dandelion seeds, wherein the single aircraft comprises a central disc and a porous disc slat, and a payload is carried below the central disc. The disk slat can generate a separation vortex ring around the disk slat to provide lift force when in passive flight, so that the disk slat has stable flight performance, long dead time and wide diffusion range.
The single aircraft of the dandelion seed-imitated micro aircraft for the individual intelligent battlefield is designed by referring to the principle of dandelion seed induced generation of separation vortex ring, and has the advantages of simple structure, reasonable design, stable flight performance, long idle time and wide diffusion range.
The application discloses a design method of an dandelion seed-imitated micro aircraft for an individual intelligent battlefield, which comprises the following steps:
(1) Observing the structure characteristics of dandelion seeds through a microscope, preliminarily determining that the bionic structure is a porous structure, determining the lean mass of the dandelion seeds through a precise balance, and preliminarily determining the effective load;
(2) Constructing models of various different structural parameters aiming at the bionic structure, performing hydrodynamic simulation, and determining the structural parameters of the aircraft;
(3) Carrying out pneumatic characteristic fluid-solid coupling on the aircraft which is designed, so as to ensure stable flying performance;
(4) And manufacturing an aircraft object, performing a vertical wind tunnel experiment, and verifying the flight performance of the aircraft object.
Firstly, observing the structural characteristics of dandelion seeds, constructing a plurality of models which accord with the structural characteristics of the dandelion seeds, and carrying out hydrodynamic pneumatic simulation; and selecting a bionic structure and structural parameters thereof according to simulation results, and primarily designing the aircraft. And after the real object is manufactured by using a laser cutting technology, the flying performance of the aircraft is further verified by combining a vertical wind tunnel experiment, and the structural parameters of the aircraft are further improved.
The simulation method of the single aircraft comprises the following steps of:
1) Respectively constructing a plurality of disc structures with diameters of 14, 21 and 28mm and porosities of 10% -100%;
2) Dividing grids of the constructed disc model by using ICEM software, wherein the number of the grids is 2000 ten thousand;
3) Solving of incompressible Navier-Stokes fluid dynamics equations is performed using Comsol software, as follows:
where Cd is the drag coefficient, F is the payload weight, u is the terminal velocity, A is the area of the aircraft cross-section (excluding the aperture), where,r is the aircraft radius, μ is the dynamic viscosity of air, ρ is the density of air, +.>And->Depending on the porosity of the aircraft;
4) Preliminarily selecting the diameter and the porosity of the aircraft according to the simulation result, and constructing a model of the single aircraft;
5) And carrying out hydrodynamic simulation on the built model of the single aircraft again to obtain drag coefficient curves under different Reynolds numbers and different payloads, and determining the payloads which can be borne by the aircraft.
The simulation results are shown in fig. 8 and 9.
The application designs the dandelion seed-imitated miniature aircraft facing the individual intelligent battlefield by utilizing the advantages of long lag time, wide diffusion range and stable flight attitude of dandelion seeds and by virtue of the bionic characteristics of a porous structure and uniform lean mass of the dandelion seeds, and the aircraft is a passive aircraft without power consumption. The aircraft system comprises a throwing structure and a single aircraft, the single aircraft is designed into a microminiature aircraft with the characteristics of simple structure, low price, long dead time, wide spreading range and the like according to dandelion seeds, and a plurality of single aircraft can be connected in series on a pull rod fixed below an unmanned aerial vehicle holder through a connecting cable to carry out large-scale cluster throwing, so that the efficiency of the microminiature aircraft is greatly improved.
The single aircraft can carry different functional loads to complete various tasks, so that the single detection task can be realized, and the single aircraft can also cooperate with cluster combat to perform battlefield investigation, thereby greatly improving the combat effectiveness. In addition, the aircraft can be used in civil fields such as air pollutant monitoring, urban infectious disease pathogen distribution monitoring, biological population observation, climate environment observation and the like.
The application discloses a method for throwing dandelion seed-imitated micro-aircraft for an individual intelligent battlefield, which comprises the following steps:
firstly, measuring the current wind speed and the wind direction by using an anemometer, carrying out calculation simulation according to the measured wind speed and wind direction, analyzing a possible flight route of a single aircraft, comprehensively selecting a throwing place, throwing by using an unmanned aerial vehicle at high altitude, fixing an aircraft throwing box below the unmanned aerial vehicle, and respectively loading a plurality of single aircraft imitating dandelions into different storage areas of the aircraft throwing box 3.
Secondly, when a certain height is reached, a given instruction is given to the throwing structure, the remote control electromagnetic valve controls the connecting rod 6 to rotate, the hatch cover 5 is opened, and the single aircraft 1 is released. Eight storage areas correspond to eight hatches 5 and eight connecting rods 6 respectively, and each connecting rod 6 and the hatches 5 are independently controlled, so that multiple times and multiple throwing can be realized.
Examples
As shown in fig. 1, a plurality of single aircraft 1 in the dandelion seed-imitated micro aircraft for the individual intelligent battlefield are stored in a micro aircraft throwing box, and the micro aircraft throwing box is fixed in a fixing clamping groove below an unmanned plane. When the device is in practical application, the anemometer is used for measuring the current wind speed and the wind direction, calculation simulation is carried out according to the measured wind speed and the wind direction, the possible flight route of the single aircraft 1 is analyzed, the throwing place is comprehensively selected, when a certain height is reached, a given instruction of a throwing structure is given, the electromagnetic valve is remotely controlled to control the connecting rod 6 to rotate, the storage cabin 4 is opened, and the single aircraft 1 is released. Wherein, the storage cabin 4 of the aircraft throwing box 3 is equally divided into eight storage areas, and each storage area is provided with a connecting rod and a cabin cover which can be independently controlled, so that the aircraft can be thrown in a plurality of times.
The structure of the single aircraft 1 is shown in fig. 2-4, and the single aircraft 1 comprises a central disc 7, a disc slat 8, a solar panel 9 and a load compartment 10, wherein the central disc 7 has a diameter of 28mm and a thickness of 0.1mm. The porosity of the disk slat 8 is 31.6%, the disk slat consists of 52 fixed shafts, the arc length of the large end of each shaft is 0.732mm, the arc length of the small end of each shaft is 0.08mm, and the shaft length is 10mm. The periphery of the disk slat 8 is provided with a circular ring with the width of 1mm, so that the aircraft has certain rigidity. The disk slats 8 on both sides of the central disk 7 are bent upwards to ensure the stability of the descending posture.
The bottom of the central disc 7 is connected with a load cabin 10, and the load cabin 10 is loaded with task loads. The payload mass of the load compartment 10 of the present application is 30-50mg. The central disc 7 and the load compartment 10 are detachably connected to each other and together form a compartment for receiving an applied load. A detachable solar panel 9 is arranged above the central disc 7, and provides a certain energy source for effective load in the lower load cabin when necessary, so that the acting time of the solar panel is prolonged.
The aircraft drop box 3 is constructed as shown in fig. 5, and the aircraft drop box 3 comprises a storage compartment 4, a hatch 5 and a connecting rod 6. Wherein the storage compartment 4 is 60mm long, 120mm wide, 60mm high and 5mm thick on the inner wall. The storage compartment 4 is divided into eight independent storage areas of equal volume, each storage area having a volume of 54000mm 3 20 individual aircraft may be loaded. The storage compartment 4 is connected with the hatches 5 by connecting rods 6, each hatch 530mm long, 28mm wide and 4mm thick.
Referring to fig. 6, in order to verify that the designed aircraft has good flight performance, through high-precision numerical simulation and wake display experiments of dandelion seeds in nature, it is found that a pair of separation vortex rings similar to the dandelion seeds appear above the single aircraft, as shown in fig. 7. The separation vortex ring generates a stronger low-pressure area above the single aircraft 1, so that the single aircraft 1 generates lifting force, and the dead time of the single aircraft is effectively prolonged.
Referring to fig. 8 and 9, in order to ensure that the single aircraft of the present application can maintain a stable flight attitude and good flight performance in practical applications, a flight test is performed on a processed entity through a vertical wind tunnel experiment, and the result shows that the flight performance of the single aircraft is good.
The dandelion seed-imitated miniature aircraft for the individual intelligent battlefield has the characteristics of long dead time, wide spreading range, stable flying attitude, small volume, strong concealment and low cost.
Claims (10)
1. The utility model provides a imitative dandelion seed miniature vehicle towards individual soldier's intelligent battlefield, its characterized in that includes at least one monomer aircraft (1), the monomer aircraft includes central disc (7), dish slat (8) and load cabin (10), the below of central disc (7) is provided with load cabin (10), be provided with around central disc (7) dish slat (8), dish slat (8) are porous structure, dish slat (8) of central disc (7) both sides are crooked upwards, dish slat (8) include many fixed axles and a solid fixed ring, center disc (7) are connected to the one end of fixed axle, fixed axle evenly distributed is in around central disc (7), adjacent be provided with the space between the fixed axle, the other end of fixed axle is connected gu fixed ring, the fixed axle is close to gu fixed ring's one end width is greater than the fixed axle is close to the one end width of central disc (7).
2. The individual intelligent battlefield oriented dandelion-like seed micro-aircraft of claim 1, wherein: the number of the fixed shafts is 52.
3. The individual intelligent battlefield oriented dandelion-like seed micro-aircraft of claim 1, wherein: the diameter of the center disc (7) is 28mm, the length of the fixed shaft is 10mm, the arc length of one end of the fixed shaft, which is close to the center disc (7), is 0.08mm, and the arc length of the other end of the fixed shaft is 0.732mm.
4. The individual intelligent battlefield oriented dandelion-like seed micro-aircraft of claim 1, wherein: the curvature of the disk slat (8) is 0.0563.
5. The individual intelligent battlefield oriented dandelion-like seed micro-aircraft of claim 1, wherein: the porosity of the disk slat (8) is 31.6%.
6. The individual intelligent battlefield oriented dandelion-like seed micro-aircraft of claim 1, wherein: the solar energy disc also comprises a solar energy electric plate (9), wherein the solar energy electric plate (9) is arranged above the central disc (7).
7. The individual intelligent battlefield oriented dandelion-like seed micro-aircraft of claim 1, wherein: still include unmanned aerial vehicle (2) and aircraft release casket (3), aircraft release casket (3) set up the below of unmanned aerial vehicle (2), aircraft release casket (3) are provided with at least one monomer aircraft (1).
8. The individual intelligent battlefield oriented dandelion-like seed micro-aircraft of claim 7, wherein: the aircraft delivery box (3) comprises a storage cabin (4), a cabin cover (5) and a connecting rod (6), an opening is formed in the lower portion of the storage cabin (4), the cabin cover (5) is arranged at the opening, and one side of the cabin cover (5) is connected with one side of the storage cabin (4) through the connecting rod (6).
9. The individual soldier intelligent battlefield oriented dandelion seed micro-aircraft of claim 8, wherein: the storage cabin (4) is divided into a plurality of storage areas, openings are formed in the lower portion of each storage area, the cabin covers (5) are arranged in each opening, each cabin cover (5) is connected with the storage cabin (4) through the connecting rod (6), and the connecting rod (6) is controlled through the electromagnetic valve.
10. The individual intelligent battlefield oriented dandelion-like seed micro-aircraft of claim 1, wherein: the disk slat (8) is prepared by using a polyimide film.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202310850585.5A CN116573144A (en) | 2023-07-12 | 2023-07-12 | Mongolian dandelion seed-imitated micro aircraft oriented to individual intelligent battlefield |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202310850585.5A CN116573144A (en) | 2023-07-12 | 2023-07-12 | Mongolian dandelion seed-imitated micro aircraft oriented to individual intelligent battlefield |
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| Publication Number | Publication Date |
|---|---|
| CN116573144A true CN116573144A (en) | 2023-08-11 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202310850585.5A Pending CN116573144A (en) | 2023-07-12 | 2023-07-12 | Mongolian dandelion seed-imitated micro aircraft oriented to individual intelligent battlefield |
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Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20140043172A1 (en) * | 2012-08-08 | 2014-02-13 | Meso, Inc. | Next generation wireless sensor system for environmental monitoring |
| CN109502021A (en) * | 2018-11-12 | 2019-03-22 | 浙江大学 | Unpowered type imitates dandelion aircraft and its control method |
| CN114148547A (en) * | 2021-12-06 | 2022-03-08 | 浙江大学 | Dandelion-like mars aircraft and device and control method thereof |
| CN115320861A (en) * | 2021-05-11 | 2022-11-11 | 南京理工大学 | Disc structure for inducing separation vortex ring |
-
2023
- 2023-07-12 CN CN202310850585.5A patent/CN116573144A/en active Pending
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20140043172A1 (en) * | 2012-08-08 | 2014-02-13 | Meso, Inc. | Next generation wireless sensor system for environmental monitoring |
| CN109502021A (en) * | 2018-11-12 | 2019-03-22 | 浙江大学 | Unpowered type imitates dandelion aircraft and its control method |
| CN115320861A (en) * | 2021-05-11 | 2022-11-11 | 南京理工大学 | Disc structure for inducing separation vortex ring |
| CN114148547A (en) * | 2021-12-06 | 2022-03-08 | 浙江大学 | Dandelion-like mars aircraft and device and control method thereof |
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