CN112158347A - 5G-based aircraft data acquisition device and use method thereof - Google Patents
5G-based aircraft data acquisition device and use method thereof Download PDFInfo
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- CN112158347A CN112158347A CN202011156777.9A CN202011156777A CN112158347A CN 112158347 A CN112158347 A CN 112158347A CN 202011156777 A CN202011156777 A CN 202011156777A CN 112158347 A CN112158347 A CN 112158347A
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- acquisition device
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- 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
- B64D47/00—Equipment not otherwise provided for
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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
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01D—MEASURING NOT SPECIALLY ADAPTED FOR A SPECIFIC VARIABLE; ARRANGEMENTS FOR MEASURING TWO OR MORE VARIABLES NOT COVERED IN A SINGLE OTHER SUBCLASS; TARIFF METERING APPARATUS; MEASURING OR TESTING NOT OTHERWISE PROVIDED FOR
- G01D21/00—Measuring or testing not otherwise provided for
- G01D21/02—Measuring two or more variables by means not covered by a single other subclass
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- G—PHYSICS
- G05—CONTROLLING; REGULATING
- G05D—SYSTEMS FOR CONTROLLING OR REGULATING NON-ELECTRIC VARIABLES
- G05D1/00—Control of position, course or altitude of land, water, air, or space vehicles, e.g. automatic pilot
- G05D1/10—Simultaneous control of position or course in three dimensions
- G05D1/101—Simultaneous control of position or course in three dimensions specially adapted for aircraft
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- 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
Abstract
The invention discloses a 5G-based aircraft data acquisition device, which comprises an aircraft body and a data acquisition device, wherein the data acquisition device is arranged on a rotating mechanism arranged at the lower end of the aircraft body, a transverse plate is arranged at the top of the aircraft body, a cylindrical groove is formed in the side surface of the transverse plate in a penetrating manner, a supporting plate is fixed on the transverse plate through the cylindrical groove and extends upwards perpendicular to the transverse plate, a protective plate is arranged at the top end of the supporting plate, an extension baffle is arranged in the protective plate, and the extension baffle protrudes out of the outer surface of the protective plate and covers the data acquisition device assembled at the lower end of the aircraft body. The invention can avoid the collision of the external environment to the data acquisition device, and the acquisition device is an independent component, thereby being convenient for assembly and replacement and simultaneously improving the applicability of the data acquisition device.
Description
Technical Field
The invention relates to the technical field of aircrafts, in particular to an aircraft data acquisition device based on 5G and a using method thereof.
Background
With the rapid development of the unmanned aerial vehicle industry, in order to avoid faults in the flight process of the unmanned aerial vehicle, monitoring of various performances of the unmanned aerial vehicle is very important, and data acquisition in the monitoring process is very important.
The original data acquisition of the unmanned aerial vehicle is carried out and the flight data is usually acquired according to the flight control system of the unmanned aerial vehicle, the acquired data is single, the performance of the unmanned aerial vehicle can not be comprehensively analyzed, inconvenience is brought to performance monitoring of the unmanned aerial vehicle, and the data acquisition device is arranged outside the unmanned aerial vehicle, is easy to collide with the external environment and cause damage, and influences normal acquisition work.
Disclosure of Invention
The invention aims to solve the technical problems to a certain extent, and provides a 5G-based aircraft data acquisition device which can avoid the collision of the external environment on the data acquisition device, is an independent component, is convenient to assemble and replace, and can improve the applicability of the data acquisition device.
The technical scheme adopted by the invention for solving the technical problems is as follows: the utility model provides an aircraft data acquisition device based on 5G, including aircraft body and data acquisition device, data acquisition device locates on the rotary mechanism that aircraft body lower extreme set up, aircraft body top is equipped with the diaphragm, and the diaphragm side runs through and is equipped with the post groove to be fixed with the backup pad on the diaphragm through the post groove, and the perpendicular diaphragm of this backup pad upwards extends the setting, the backup pad top is equipped with the guard plate, the inside extension baffle that is equipped with of guard plate, the outstanding guard plate surface of extension baffle covers the data acquisition device of aircraft body lower extreme assembly.
In some preferred embodiments, the rotating mechanism includes a fixed part and a rotating part, the fixed part is a cavity structure with an opening at one end, the opening of the fixed part is tightly assembled in a groove arranged at the bottom of the aircraft body, a boss structure is formed at a position of the fixed part protruding out of the groove, the rotating part is sleeved on a boss of the fixed part, a bolt is arranged at the outer side of the rotating part, the bolt penetrates through the rotating part and extends into a rotating groove arranged in the fixed part, the fixed part and the rotating part coaxially penetrate through a rotating shaft, one end of the rotating shaft is electrically connected with a motor inside the aircraft body, the other end of the rotating shaft is in transmission connection with the rotating part, and the data acquisition device is assembled at the bottom of the rotating part and rotates along. So data acquisition device rotates along with rotary mechanism, improves its precision of using to can 360 degrees rotations gather the data of equidirectional when the flight.
In some preferred embodiments, the data acquisition device comprises a shell and a data acquisition assembly installed in the shell, the periphery of the top surface of the shell extends upwards to form a guide post, a fixing ring with internal threads is arranged outside the guide post, the fixing ring can rotate around the axis of the guide post forwards and backwards on the guide post, the guide post extends into a clamping groove of a connecting rod arranged on the bottom surface of the rotating part, and the connecting rod is provided with external threads matched with the fixing ring. Therefore, the shell is assembled on the rotating mechanism through the fixing ring, so that the position stability of the collecting device is ensured, and the collecting device can be conveniently disassembled, assembled and replaced.
In some preferred embodiments, a through groove is formed in the side face of the shell, a moving plate is arranged in the shell in a direction opposite to the through groove, the moving plate is in transmission connection with a gear assembled at the bottom of a rotating shaft extending into the shell, the data acquisition assembly comprises a temperature sensor, a humidity sensor and an air speed sensor which are respectively assembled, and the temperature sensor, the humidity sensor and the air speed sensor are respectively in data connection with a data acquisition module in the shell. So make temperature sensor, humidity transducer, air velocity transducer arrange the casing inside under the state that does not make, avoid the external world to collide temperature sensor, humidity transducer, air velocity transducer and cause the damage.
In some preferred embodiments, the bottom surface of the inner part of the shell extends upwards to form a rotating boss, and the rotating shaft extends into the rotating boss and is connected with a bearing in the rotating boss. Therefore, the rotating shaft can rotate more smoothly to avoid blocking, and the acquisition of data in different directions during rotation is improved.
In some preferred embodiments, the bottom surface of the inside of the shell is symmetrically provided with sliding plates extending upwards, the sliding plates are provided with sliding blocks in a sliding fit mode, the moving plate is mounted on the sliding blocks through bolts, and the side surfaces of the moving plate are provided with saw-tooth-shaped protrusions in meshed connection with the gears. So make the movable plate take temperature sensor, humidity transducer, air velocity transducer to shift out from the casing through gear drive's mode, the rupture that the speed was too fast caused when avoiding stretching out, the slider can guarantee more smoothly when the movable plate shifts out simultaneously.
In some preferred embodiments, the casing is provided with a cover plate at the through groove, one end of the cover plate is hinged to the upper end of the through groove, the other end of the cover plate is covered on the through groove under the action of self gravity, the cover plate faces the end surface inside the casing and is provided with a traction block above the hinged part, the traction block is connected with a traction wire, and the other end of the traction wire is connected with a pulling block arranged on the end surface of the moving plate moving back to the opening direction of the cover plate. So the apron receives traction force and can open simultaneously when the movable plate shifts out, avoids the apron to hit the movable plate, and the apron can seal logical groove when not gathering simultaneously, guarantees internals's safety.
In some preferred embodiments, the pull wire is an elastic band or a spring.
In some preferred embodiments, supporting legs are arranged around the bottom surface of the shell, a cushion pad is assembled at the bottom of the supporting legs, a return spring is sleeved outside the supporting legs, and when the cushion pad is stressed, the return spring compresses and drives the supporting legs to move in a movable groove arranged on the bottom surface of the shell. The blotter drives the supporting legs and plays the buffering effect when so aircraft descends, avoids shaking too big and causes the displacement to collection system.
An aircraft data acquisition method comprises the following steps,
s1, setting a flight route of an aircraft in a flight acquisition mode, and determining a flight starting point and a flight finishing point, wherein a temperature sensor, a humidity sensor and a wind speed sensor are arranged in a shell part;
s2, the aircraft starts to collect a certain flight route, the expansion baffle is opened at the moment to avoid the influence on the aircraft in rainy and snowy weather, meanwhile, the rotating mechanism rotates, the rotating shaft drives the movable plate in the shell to move, the movable plate pulls the cover plate and moves the movable plate outwards, so that the temperature sensor, the humidity sensor and the wind speed sensor extend out of the shell to collect data of the external environment;
s3, the aircraft flies at the highest speed, the aircraft spirals after flying for a certain distance, meanwhile, the temperature sensor, the humidity sensor and the wind speed sensor transmit the acquired data to the data acquisition module in the shell, and the data acquisition module analyzes the flight route information of the section and the flight speed of the aircraft at the temperature, the humidity and the wind speed;
and S4, sending out a command to return the aircraft or land in place.
Compared with the prior art, the beneficial effects are that: the acquisition device of the invention is assembled on the aircraft by adopting an independent structure, is convenient to assemble and replace, can improve the applicability of the data acquisition device, can adapt to the comprehensive analysis of the performance of the unmanned aerial vehicle, improves the convenience of monitoring the performance of the unmanned aerial vehicle,
simultaneously the extension baffle at aircraft top is outstanding the guard plate surface and is covered the data acquisition device of aircraft body lower extreme assembly, can avoid external environment to data acquisition device's collision, and is further, makes the movable plate take temperature sensor, humidity transducer, air velocity transducer to shift out from the casing through gear drive's mode, and the rupture that the speed caused when avoiding stretching out is too fast, and the slider can guarantee that the movable plate is more smooth and easy when shifting out simultaneously.
Additional aspects and advantages of the invention will be set forth in part in the description which follows, and in part will be obvious from the description, or may be learned by practice of the invention.
Drawings
The invention is further illustrated with reference to the following figures and examples.
FIG. 1 is a block diagram of a 5G based aircraft according to the present invention.
FIG. 2 is a block diagram of a 5G based aircraft according to the present invention.
Fig. 3 is an assembly view of the aircraft body and data acquisition device of the present invention.
Fig. 4 is an assembly view of the data acquisition device of the present invention.
Fig. 5 is an exploded view of the data acquisition device of the present invention.
Description of the drawings: 1. an aircraft body; 2. a data acquisition device; 201. a housing; 202. a guide post; 203. a fixing ring; 204. a connecting rod; 3. a rotation mechanism; 301. a fixing member; 302. a rotating member; 303. a bolt; 304. a rotating tank; 305. a rotating shaft; 4. a transverse plate; 5. a support plate; 6. a protection plate; 7. an expansion baffle; 8. moving the plate; 9. a gear; 10. rotating the boss; 11. a bearing; 12. a slide plate; 13. a slider; 14. a cover plate; 15. a traction block; 16. a pull wire; 17. pulling the block; 18. supporting legs; 19. a cushion pad.
Detailed Description
The present invention will now be described in further detail with reference to the accompanying drawings. These drawings are simplified schematic views illustrating only the basic structure of the present invention in a schematic manner, and thus show only the constitution related to the present invention.
In the present invention, it should be noted that the terms "upper", "lower", "inner", "outer", etc. indicate the orientation or positional relationship based on the orientation or positional relationship shown in the drawings, which are only for the convenience of describing the invention and simplifying the description, but do not indicate or imply that the referred device or element must have a specific orientation, be constructed in a specific orientation and operation, and thus should not be construed as limiting the invention; the terms "first", "second" and "first" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance; furthermore, unless expressly stated or limited otherwise, the terms "mounted," "connected," and "connected" are to be construed broadly, as they may be fixedly connected, detachably connected, or integrally connected, for example; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meaning of the above terms in the present invention can be understood in specific cases to those skilled in the art.
The invention is implemented as follows: 1-5G-based aircraft data acquisition device and use method thereof, including aircraft body 1 and data acquisition device 2, data acquisition device 2 is located on rotary mechanism 3 that aircraft body 1 lower extreme set up, aircraft body 1 top is equipped with diaphragm 4, diaphragm 4 side runs through and is equipped with the post groove, and be fixed with backup pad 5 on diaphragm 4 through the post groove, and this backup pad 5 perpendicular diaphragm 4 upwards extends the setting, the backup pad 5 top is equipped with guard plate 6, the inside extension baffle 7 that is equipped with of guard plate 6, extension baffle 7 is outstanding 6 surfaces outside the guard plate and is covered aircraft body 1 lower extreme assembled data acquisition device 2.
In this embodiment, the rotating mechanism 3 includes a fixed component 301 and a rotating component 302, the fixed component 301 has a cavity structure with an opening at one end, the opening of the rotary piece is downwards fastened and assembled in a groove arranged at the bottom of the aircraft body 1, a boss structure is formed at the position of the fixed piece 301 protruding out of the groove, the rotary piece 302 is sleeved on the boss of the fixed piece 301, the outer side of the aircraft is provided with a plug pin 303, the plug pin 303 penetrates through the rotating piece 302 and extends into a rotating groove 304 arranged on the fixed piece 301, the fixed piece 301 and the rotating piece 302 are coaxially penetrated with a rotating shaft 305, one end of the rotating shaft 305 is electrically connected with a motor inside the aircraft body 301, the other end is connected with the rotating part 302 in a transmission way, the data acquisition device 2 is assembled at the bottom of the rotating part 302, and rotate with rotating member 302, so that data acquisition device 2 rotates with rotary mechanism 3, improves its precision of use to can 360 degrees rotations gather the data of different directions when flying.
In this embodiment, as shown in fig. 4-5, the data acquisition device 2 includes a housing 201 and a data acquisition assembly installed in the housing 201, the periphery of the top surface of the housing 201 extends upward to be provided with a guide post 202, a fixing ring 203 with internal threads is arranged outside the guide post 202, the fixing ring 203 can rotate forward and backward on the guide post 202 around the axis of the guide post 202, the guide post 202 extends into a slot of a connecting rod 204 arranged on the bottom surface of the rotating member 302, and the connecting rod 204 is provided with external threads matched with the fixing ring 203, so that the housing 201 is assembled on the rotating mechanism 3 through the fixing ring 203, and the position stability of the acquisition device is ensured and the disassembly and the assembly can be conveniently carried out.
Further, casing 201 side is equipped with logical groove, casing 201 is inside to be equipped with movable plate 8 to the direction that leads to the groove, this movable plate 8 is connected with the gear 9 transmission that stretches into its bottom assembly of the inside rotation axis 305 of casing 201, the data acquisition subassembly is including assembling temperature sensor respectively, humidity transducer, air velocity transducer, a weighing sensor and a temperature sensor, humidity transducer, air velocity transducer respectively with the inside data acquisition module data connection of casing 201, so make temperature sensor, humidity transducer, air velocity transducer arrange inside the casing under the state that does not make, avoid the external world to collide temperature sensor, humidity transducer, air velocity transducer causes the damage.
In this embodiment, a rotating boss 10 extends upward from the bottom surface inside the housing 201, and the rotating shaft 305 extends into the rotating boss 10 and is connected to the bearing 11 in the rotating boss 10, so that the rotating shaft 305 is more smoothly prevented from being stuck during rotation, and the acquisition of data in different directions during rotation is improved, further, sliding plates 12 extend upward from the bottom surface inside the housing 201 symmetrically, sliders 13 are mounted on the sliding plates 12 in a sliding manner, the moving plate 8 is bolted on the sliders 13, and the side surfaces of the moving plate are provided with saw-toothed protrusions engaged with the gears 9, so that the moving plate is driven by the gears to move out of the housing with the temperature sensor, the humidity sensor and the wind speed sensor, thereby preventing the moving plate from being broken due to too fast extension, and the sliders 13 can ensure that the moving plate 8 can move out more smoothly;
furthermore, a cover plate 14 is arranged at the through groove of the shell 201, one end of the cover plate 14 is hinged to the upper end of the through groove, the other end of the cover plate 14 is covered on the through groove under the action of self gravity, a traction block 15 is arranged on the end surface of the cover plate 14 facing the inside of the shell 201 and above the hinged part, a traction wire 16 is connected to the traction block 15, the traction wire 16 is made of elastic band or spring, the other end of the traction wire 16 is connected with a pulling block 17 arranged on the end surface of a moving plate 8 moving back to the opening direction of the cover plate 14, so that the cover plate 14 is opened when the moving plate 8 is moved out under the traction force, the cover plate 14 is prevented from colliding with the moving plate 8, and the cover plate 14 can seal the;
simultaneously, casing 201 bottom surface is equipped with supporting legs 18 all around, and supporting legs 18 bottom is equipped with blotter 19, and the outside cover of supporting legs 18 is equipped with reset spring, makes reset spring compression and drive supporting legs 18 and remove in the movable slot that casing 201 bottom surface set up when blotter 19 atress, and blotter 19 drives supporting legs 18 and plays the cushioning effect when so aircraft descends, avoids shaking too big and causes the displacement to collection system.
The acquisition device is assembled on the aircraft in an independent structure, so that the data acquisition device is convenient to assemble and replace, the applicability of the data acquisition device can be improved, the comprehensive analysis of the performance of the unmanned aerial vehicle can be adapted, the monitoring convenience of the performance of the unmanned aerial vehicle is improved, meanwhile, the expansion baffle 7 at the top of the aircraft protrudes out of the outer surface of the protection plate 6 and covers the data acquisition device 2 assembled at the lower end of the aircraft body 1, the collision of the external environment on the data acquisition device 2 can be avoided, further, the movable plate is driven by the temperature sensor, the humidity sensor and the wind speed sensor to move out of the shell in a gear transmission mode, the fracture caused by the overhigh speed during extending is avoided, and meanwhile, the slide block can.
An aircraft data acquisition method comprises the following steps,
s1, setting a flight route of an aircraft in a flight acquisition mode, and determining a flight starting point and a flight finishing point, wherein a temperature sensor, a humidity sensor and a wind speed sensor are arranged in a shell part;
s2, the aircraft starts to collect a certain flight route, at the moment, the expansion baffle 7 is opened to avoid the influence on the aircraft in rainy and snowy weather, meanwhile, the rotating mechanism rotates, the rotating shaft 305 drives the moving plate 8 inside the shell 201 to move, the moving plate 8 pulls the cover plate 14 and moves the moving plate 8 outwards, so that the temperature sensor, the humidity sensor and the wind speed sensor extend out of the shell 201 to collect data of the external environment;
s3, the aircraft flies at the highest speed, the aircraft spirals after flying for a certain distance, meanwhile, the temperature sensor, the humidity sensor and the wind speed sensor transmit the acquired data to the data acquisition module in the shell, and the data acquisition module analyzes the flight route information of the section and the flight speed of the aircraft at the temperature, the humidity and the wind speed;
and S4, sending out a command to return the aircraft or land in place.
While there have been shown and described what are at present considered the fundamental principles and essential features of the invention and its advantages, it will be apparent to those skilled in the art that the invention is not limited to the details of the foregoing exemplary embodiments, but is capable of other specific forms without departing from the spirit or essential characteristics thereof. The present embodiments are therefore to be considered in all respects as illustrative and not restrictive, the scope of the invention being indicated by the appended claims rather than by the foregoing description, and all changes which come within the meaning and range of equivalency of the claims are therefore intended to be embraced therein. Any reference sign in a claim should not be construed as limiting the claim concerned.
Furthermore, it should be understood that although the present description refers to embodiments, not every embodiment may contain only a single embodiment, and such description is for clarity only, and those skilled in the art should integrate the description, and the embodiments may be combined as appropriate to form other embodiments understood by those skilled in the art.
Claims (10)
1. The utility model provides an aircraft data acquisition device based on 5G which characterized in that: including aircraft body and data acquisition device, data acquisition device locates on the rotary mechanism of aircraft body lower extreme setting, aircraft body top is equipped with the diaphragm, and the diaphragm side runs through and is equipped with the post groove to be fixed with the backup pad through the post groove on the diaphragm, and the perpendicular diaphragm of this backup pad upwards extends the setting, the backup pad top is equipped with the guard plate, the inside extension baffle that is equipped with of guard plate, the outstanding guard plate surface of extension baffle covers the data acquisition device of aircraft body lower extreme assembly.
2. The 5G-based aircraft data acquisition device according to claim 1, wherein: the rotary mechanism comprises a fixing part and a rotating part, the fixing part is of a cavity structure with an opening at one end, the opening of the fixing part is tightly assembled in a groove formed in the bottom of the aircraft body downwards, a boss structure is formed at the position of the protruding groove of the fixing part, the rotating part is sleeved on a boss of the fixing part, a bolt is arranged on the outer side of the rotating part and penetrates through the rotating part and extends into a rotary groove formed in the fixing part, a rotary shaft penetrates through the fixing part and the rotating part coaxially, one end of the rotary shaft is electrically connected with a motor inside the aircraft body, the other end of the rotary shaft is in transmission connection with the rotating part, and the data acquisition device is assembled at the bottom of the rotating part and rotates along with.
3. The 5G-based aircraft data acquisition device according to claim 1, wherein: the data acquisition device includes the casing and installs the data acquisition subassembly in the casing, casing top surface border upwards extends all around and is equipped with the guide post, and the guide post outside is equipped with the solid fixed ring of in-band screw thread, and this solid fixed ring can be around the axial lead of guide post on the guide post just, the counter-rotation, the guide post stretches into in the draw-in groove of the connecting rod that the rotating member bottom surface set up, and the connecting rod be equipped with solid fixed ring assorted external screw thread.
4. The 5G-based aircraft data acquisition device according to claim 3, wherein: the novel wind power generation device is characterized in that a through groove is formed in the side face of the shell, a movable plate is arranged in the shell in a direction opposite to the through groove and connected with a gear which stretches into the shell and is assembled at the bottom of a rotating shaft, the data acquisition assembly comprises a temperature sensor, a humidity sensor and a wind speed sensor which are assembled respectively, and the temperature sensor, the humidity sensor and the wind speed sensor are in data connection with a data acquisition module in the shell respectively.
5. The 5G-based aircraft data acquisition device according to claim 4, wherein: the inside bottom surface of casing upwards extends and is equipped with rotatory boss, the rotation axis stretches into in the rotatory boss to be connected with the bearing in the rotatory boss.
6. The 5G-based aircraft data acquisition device according to claim 4, wherein: the sliding plates symmetrically extend upwards from the bottom surface inside the shell, the sliding plates are slidably mounted on the sliding plates, the moving plate bolts are mounted on the sliding plates, and the side surfaces of the moving plate bolts are provided with saw-toothed protrusions in meshed connection with the gears.
7. The 5G-based aircraft data acquisition device according to claim 4, wherein: the casing is located logical groove department and is equipped with the apron, and the one end of apron articulates in the upper end that leads to the groove, and its other end receives self action of gravity to cover logical groove, the apron is equipped with the traction block towards the inside terminal surface of casing and the position that is located articulated position top, be connected with the pull wire on the traction block, the other end of this pull wire is connected with the pulling piece that sets up on its terminal surface of movable plate that the direction removed was opened to the apron dorsad.
8. The 5G-based aircraft data acquisition device according to claim 7, wherein: the traction wire is an elastic band or a spring.
9. The 5G-based aircraft data acquisition device according to claim 1, wherein: supporting legs are arranged on the periphery of the bottom surface of the shell, buffering cushions are assembled at the bottoms of the supporting legs, return springs are sleeved outside the supporting legs, and the return springs compress to drive the supporting legs to move in movable grooves formed in the bottom surface of the shell when the buffering cushions are stressed.
10. An aircraft data acquisition method, characterized by: comprises the following steps of (a) carrying out,
s1, setting a flight route of an aircraft in a flight acquisition mode, and determining a flight starting point and a flight finishing point, wherein a temperature sensor, a humidity sensor and a wind speed sensor are arranged in a shell part;
s2, the aircraft starts to collect a certain flight route, the expansion baffle is opened at the moment to avoid the influence on the aircraft in rainy and snowy weather, meanwhile, the rotating mechanism rotates, the rotating shaft drives the movable plate in the shell to move, the movable plate pulls the cover plate and moves the movable plate outwards, so that the temperature sensor, the humidity sensor and the wind speed sensor extend out of the shell to collect data of the external environment;
s3, the aircraft flies at the highest speed, the aircraft spirals after flying for a certain distance, meanwhile, the temperature sensor, the humidity sensor and the wind speed sensor transmit the acquired data to the data acquisition module in the shell, and the data acquisition module analyzes the flight route information of the section and the flight speed of the aircraft at the temperature, the humidity and the wind speed;
and S4, sending out a command to return the aircraft or land in place.
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN117087891A (en) * | 2023-10-20 | 2023-11-21 | 北京建工环境修复股份有限公司 | Soil remediation land image acquisition aircraft |
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