CN109305352B - Unmanned aerial vehicle and manufacturing method of body shell of unmanned aerial vehicle - Google Patents
Unmanned aerial vehicle and manufacturing method of body shell of unmanned aerial vehicle Download PDFInfo
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- CN109305352B CN109305352B CN201811439281.5A CN201811439281A CN109305352B CN 109305352 B CN109305352 B CN 109305352B CN 201811439281 A CN201811439281 A CN 201811439281A CN 109305352 B CN109305352 B CN 109305352B
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/04—Helicopters
- B64C27/08—Helicopters with two or more rotors
- B64C27/10—Helicopters with two or more rotors arranged coaxially
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C44/00—Shaping by internal pressure generated in the material, e.g. swelling or foaming ; Producing porous or cellular expanded plastics articles
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C69/00—Combinations of shaping techniques not provided for in a single one of main groups B29C39/00 - B29C67/00, e.g. associations of moulding and joining techniques; Apparatus therefore
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/04—Helicopters
- B64C27/12—Rotor drives
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C5/00—Stabilising surfaces
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- 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
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- 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
- B64D27/30—Aircraft characterised by electric power plants
- B64D27/35—Arrangements for on-board electric energy production, distribution, recovery or storage
- B64D27/353—Arrangements for on-board electric energy production, distribution, recovery or storage using solar cells
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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
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Arrangement Or Mounting Of Propulsion Units For Vehicles (AREA)
Abstract
The invention discloses an unmanned aerial vehicle, which comprises a solar cell, a coaxial motor, an upper rotor, a lower rotor, a working part, a stability-increasing rotor and a load part, wherein the solar cell is arranged on the upper rotor; be provided with three rotor, promoted unmanned aerial vehicle's load-carrying ability greatly, along with load-carrying ability's promotion, can increase the function of load portion like this, unmanned aerial vehicle has multiple functions and effect promptly. The upper rotor wing generates airflow during operation, and a stable 'pre-compression' layer with rapid and high-air-tightness airflow is formed on the lower rotor wing, so that the operation of the lower rotor wing is more efficient and stable, and the lower rotor wing has high maneuverability and high stability. Thereby through the angle control unmanned aerial vehicle of first steering wheel and the coaxial motor of second steering wheel joint control direction, because the control pendulum angle of first steering wheel and second steering wheel is the vertical direction, consequently, unmanned aerial vehicle makes meticulous direction operation, installs solar cell, has promoted unmanned aerial vehicle's duration. The invention also discloses a manufacturing method of the unmanned aerial vehicle shell.
Description
Technical Field
The invention relates to the field of unmanned aerial vehicles, in particular to an unmanned aerial vehicle and a manufacturing method of a body shell of the unmanned aerial vehicle.
Background
At present, most of coaxial helicopters, also called coaxial contra-rotor helicopters, share a transmission shaft by double-layer blades, but the rotation directions are opposite, so that the unidirectional rotation deflection moment is balanced, the first layer provides 'pre-compression' for the second layer, and the second layer has larger 'air intake/exhaust volume' and 'airflow density', although the effect is less than 2 times, the improvement is obvious. The inventor finds in the research process that the conventional coaxial helicopter has at least the following disadvantages: the lifting speed is slow; the use effect is poor; the energy loss of one transmission shaft is large.
The upper rotor and the lower rotor of a practical coaxial rotor helicopter are usually two, at most three, rotors. Because the number of the rotors is limited, the improvement of the lift force of the helicopter is prevented, and the possibility of further upsizing of the helicopter with the coaxial rotors rotating in the opposite directions is also restricted. Meanwhile, the number of the rotors is limited, so that the rotor arm spread can only be increased for ensuring the lift force, and therefore when large-aircraft flight is carried out, the upper rotor and the lower rotor are easy to collide with each other, and flight accidents occur. Moreover, the advantages of coaxial rotor counter-rotating helicopters are also offset by the structural weight increase due to the long shaft, long rotor, and complex control devices.
Typically, the endurance of a rotary-wing drone is less than that of a fixed-wing drone, and therefore the endurance of a rotary-wing drone also needs to be improved.
Disclosure of Invention
The invention aims to provide an unmanned aerial vehicle aiming at the defects in the prior art, which comprises a solar cell, a coaxial motor, an upper rotor, a lower rotor, a working part, a stability-increasing rotor and a load part, wherein the solar cell is connected with the upper rotor;
the coaxial motor is fixed on the working part and is fixedly connected with the upper rotor wing and the lower rotor wing through the first rotating shaft; the working part is fixedly connected with the load part through a fixed shaft, the fixed shaft is fixedly provided with a hollow shaft motor, and the hollow shaft motor is fixedly connected with a stability-increasing rotor wing. Go up the rotor and be very close between the rotor down, when doing high maneuver, the lower rotor can up warp, sets up in the unmanned aerial vehicle middle section and increases steady rotor, increases steady rotor and undertakes more loads, and consequently unmanned aerial vehicle is more steady when high maneuver, and maneuverability can obtain promoting greatly. The air flow generated by the upper rotor wing when rotating forms pre-compression on the lower rotor wing, the air inflow and air density of the lower rotor wing are larger, and the working performance of the lower rotor wing is improved to a great extent. In a similar way, the working performance of the stability-increasing rotor wing is improved to a certain extent, so that the high maneuverability of the unmanned aerial vehicle is very superior in structural design, and the situations of tail flicking, overturning and the like cannot be caused.
And one or more of a shooting lens, a radar, a laser detector, an ultrasonic detector and an infrared scanner are arranged in the load part. The load part is provided with detection equipment which can detect forest fire prevention, meteorological detection, environmental pollution, emergency rescue and other purposes.
The solar cell is mounted on the working portion and the load portion housing.
As a further improvement of the above technical solution:
one of the upper rotor, the lower rotor and the stability augmentation rotor is opposite to the other two in rotation direction. Can balance respective deflection torque through the rotational speed of regulation and control upper rotor, lower rotor and the rotor that increases steady and according to the length of its rotor blade, the deflection torque is 0 or in very little within range, and unmanned aerial vehicle's course is stable, adjusts and controls upper rotor, lower rotor and the respective moment of torsion size of rotor that increases steady between the developments, and then can make the aircraft obtain the best balance point in stability and flexibility.
A fixed bottom plate is arranged at the bottom of the working part; the working part is provided with a first steering engine and a second steering engine; the first steering engine is fixedly arranged on the base, a first support frame is fixedly arranged on the base, the first support frame is provided with a cloud deck, and the second steering engine is fixedly arranged on the cloud deck; a first eccentric shaft is arranged on the first steering engine and is movably connected with the holder through a first connecting rod; the cradle head is fixedly provided with a second support frame, the second support frame is movably provided with a fixed sleeve, and the coaxial motor is fixed on the inner fixed sleeve; a second eccentric shaft is arranged on the second steering engine and is movably connected with the fixed sleeve through a second connecting rod;
the first eccentric shaft and the second eccentric shaft are vertically arranged; the first steering engine controls the angle change of the holder, and the second steering engine controls the angle change of the coaxial motor; therefore, the first steering engine controls the transverse pendulum motion of the coaxial motor, and the second steering engine controls the longitudinal pendulum motion of the coaxial motor, so that the change of the angle of the upper rotor wing and the lower rotor wing is controlled, and the direction of the unmanned aerial vehicle is controlled. More important, when unmanned aerial vehicle meets the air vortex or does high maneuver, balanced organism that can be fine.
The fixed bottom plate is fixedly connected with the base through a third support frame, a space is formed between the fixed bottom plate and the base, and a control module and a power supply are installed in the space;
the power supply provides electric energy for the coaxial motor, the first steering engine, the second steering engine, the hollow shaft motor and the control module; the control module is in electric data connection with the coaxial motor, the first steering engine, the second steering engine and the hollow shaft motor. Therefore, the control module can control the operation of the unmanned aerial vehicle.
The upper rotor wing, the lower rotor wing and the stability augmentation rotor wing can be folded up and down, and the force required by folding any one of the rotor wings is greater than the sum of the gravity of the unmanned aerial vehicle and the resistance borne by the maximum speed; when preventing to break down because of mechanical failure or motor, under extreme circumstances, only probably a rotor can work, be in the environment out of control or fast-speed moreover, ensure that unmanned aerial vehicle can also normal operating, be unlikely to the damage. The solar cell is a thin film solar cell or a flexible solar cell.
The control module has the functions of receiving, storing, processing, transmitting and sending data. The control module is a highly integrated electronic module, is interactively connected with other intelligent equipment, controls the operation of the unmanned aerial vehicle through other intelligent equipment, and completes some tasks. The annunciator is in electrical data connection with the control module, so that information received by the annunciator can be transmitted to the control module, and the control module can also transmit the information through the annunciator. The carbon fiber layer on the shell not only greatly improves the strength of the shell, but also plays a good role in shielding and protecting the control module.
The shooting lens, the radar, the laser detector, the ultrasonic detector or the infrared scanner are powered by a power supply, and the shooting lens, the radar, the laser detector, the ultrasonic detector or the infrared scanner are in electrical data connection with the control module.
The control module is provided with a real-time data transmission module; the shooting lens is one of a double-optical lens, a low-light lens, a zoom lens and an anti-shake lens; the radar is a millimeter wave radar or a micron wave radar. Along with the increase of the precision of electronic detection equipment, unmanned aerial vehicle's accuse is surveyed the function and is also promoted greatly, under the regional and usage circumstances of difference, can be selective install different detection equipment, also not only limit shooting lens, radar, laser detector, ultrasonic detector or infrared scanner.
The shell of the working part and the shell of the load part are cylindrical, the shell comprises a strut layer, a fixing layer and a carbon fiber layer, the solar cell is arranged on the outer side of the shell, the solar cell is connected in series and is connected with the battery through a lead, and a rectifying circuit, a filter circuit and an inversion voltage regulating circuit are arranged in a connecting circuit of the solar cell and the battery; like this, unmanned aerial vehicle's duration has been promoted. The working part is provided with a annunciator which penetrates through the shell; the annunciator is in electrical data connection with the control module.
The strut layer and the fixing layer are made of light materials such as resin or aluminum alloy. Through special structure and material design, mainly alleviate unmanned aerial vehicle's self weight, strengthened the intensity of unmanned aerial vehicle casing simultaneously. The carbon fiber material is 5 times of the strength of steel and 1/6 of the mass, so that the structural strength of the shell is greatly improved, and the weight is reduced.
A method of making the housing of claim 1,
the first step is as follows: adding 10-15 parts of thermoplastic resin particles into a heating furnace, stirring and heating to a molten state;
the second step is that: adding 1-2 parts of foaming agent and 0.2-0.5 part of the linen fiber storage cloth into a heating furnace, and quickly and uniformly stirring to obtain a mixed solution; the structural strength of the shell strut layer and the fixing layer is enhanced by the linen fiber stored in the storage cloth;
the third step: pouring the mixed solution into a support column layer and a fixed layer mold, heating at 10 ℃ per hour under the air pressure of 0.5-0.6MPa, and cooling to normal temperature at 60 ℃ per hour when bubbles are generated in the mixed solution to obtain a support column layer and a fixed layer; the gas is difficult to escape from the mixed liquid by pressurization, pores are formed in the cooling process, and under the condition of the same material thickness, the larger the pores are, the more the pores are, the lighter the weight is;
the fourth step: placing the obtained support layer and the obtained fixed layer into GaCO3 or GaSO3 suspension for soaking for 10-15 minutes, and then taking out and drying at 50-60 ℃; after the support column is soaked in GaCO3 or GaSO3 suspension liquid and dried, GaCO3 or GaSO3 is partially filled in the pores, so that the stress in the support column layer and the fixing layer is reduced, and the structural strength is improved;
the fifth step: polishing the fixed layer, and then installing and curing the upper carbon fiber layer; the carbon fibers are reinforced on the fixed layer through glue or other methods, and the structural strength of the shell is obviously improved. Meanwhile, the shielding effect and the good heat conductivity are achieved, and the internal heat dissipation of the unmanned aerial vehicle is facilitated;
and a sixth step: and a solar cell is arranged on the carbon fiber layer on the outer layer of the shell.
As a further improvement of the above technical solution:
the foaming agent is one or more of sodium bicarbonate, azodiisobutyronitrile, azodicarbonamide, benzene sulfonyl hydrazide, p-toluene sulfonyl hydrazide, a foaming agent DPT, a foaming agent BN, diazo phenyl aminobenzene, a foaming agent and urea. After heating, gas is generated, and bubbles are formed in the mixed liquid.
The solar cell is a thin-film solar cell or a flexible solar cell, has good flexibility, is very thin in thickness and light in weight, generates electric energy under direct irradiation of light, and improves the cruising ability of the unmanned aerial vehicle.
The technical solutions of the embodiments of the present invention can be combined, and the technical features of the embodiments can also be combined to form a new technical solution.
The unmanned aerial vehicle has the beneficial effects that the three rotors are arranged, so that the load capacity of the unmanned aerial vehicle is greatly improved, and along with the improvement of the load capacity, the function of a load part can be increased, namely the unmanned aerial vehicle has multiple functions and effects. The upper rotor wing generates airflow during operation, a stable pre-compression layer with high-speed and high-air-tightness airflow is formed for the lower rotor wing, so that the lower rotor wing can operate more efficiently and stably, and similarly, the stability-increasing rotor wing is also realized, so that the unmanned aerial vehicle disclosed by the invention has high maneuverability and high stability. Unmanned aerial vehicle has multiple functions and effect. Can be applied to various places and environments to carry out various operations. Thereby through the angle control unmanned aerial vehicle of first steering wheel and the joint control coaxial motor of second steering wheel direction, because the control pendulum angle of first steering wheel and second steering wheel is the vertical direction, consequently, unmanned aerial vehicle makes meticulous direction operation. Go up rotor, lower rotor and increase the folding design of steady rotor, reduced unmanned aerial vehicle's storage space greatly. One of the upper rotor wing, the lower rotor wing and the stability-increasing rotor wing is opposite to the other two in turning direction, and the respective torque of the upper rotor wing, the lower rotor wing and the stability-increasing rotor wing is regulated and controlled in a dynamic state, so that the aircraft can obtain the optimal balance point in stability and flexibility. The angle of the rotor wing is changed, so that the direction of the thrust generated by the rotor wing in operation can be controlled. The strut layer and the fixing layer of the shell are made of foamed plastic and are cured by the carbon fiber layer, and under the condition of the same thickness as the material, the weight of the shell is reduced by at least half, so that the cruising ability and the loading ability are improved. And the thin-film solar cell or the flexible solar cell is light in weight, so that the energy consumption of the unmanned aerial vehicle is very low.
Drawings
FIG. 1 is a partial cross-sectional view of one embodiment of the present invention.
FIG. 2 is a partial cross-sectional view of one embodiment of the present invention.
Fig. 3 is a schematic structural view of the working portion and the upper and lower rotors according to an embodiment of the present invention.
Fig. 4 is a longitudinal sectional structural view of an embodiment of the housing of the present invention.
Fig. 5 is a longitudinal sectional structural view of an embodiment of the housing of the present invention.
In the reference symbols: 1. an upper rotor; 2. a lower rotor; 3. a first rotating shaft; 4. a second rotating shaft; 5. a stability augmentation rotor; 6. a hollow shaft motor; 7. a fixed shaft; 8. a working part; 9. a coaxial motor; 10. a first steering engine; 11. a first link; 12. a holder; 13. a second steering engine; 14. a second link; 15. a first eccentric shaft; 16. a second eccentric shaft; 17. a first support frame; 18. a base; 19. a second support frame; 20. fixing a sleeve; 21. a third support frame; 22. a space; 23. a load section; 24. a base plate; 25. a solar cell; 26. a housing; 2601. a strut layer; 2602. a fixed layer; 2603. a carbon fiber layer; 27 a signaler.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
As shown in fig. 1 to 5, the unmanned aerial vehicle of the present embodiment includes a solar cell 25, a coaxial motor 9, an upper rotor 1, a lower rotor 2, a working portion 8, a stability-enhancing rotor 5, and a load portion 23; the solar cell 25 is mounted on the working portion 8 and the load portion 23 housing.
The coaxial motor 9 is fixed on the working part 8, and the coaxial motor 9 is fixedly connected with the upper rotor wing 1 and the lower rotor wing 2 through the first rotating shaft 3 and the second rotating shaft 4; the working part 8 is fixedly connected with the load part 23 through a fixed shaft 7, the fixed shaft 7 is fixedly provided with a hollow shaft motor 6, and the hollow shaft motor 6 is fixedly connected with the stability-increasing rotor wing 5. Go up the rotor 1 and be very close between the rotor 2 down, when doing high maneuver, lower rotor 2 can up warp, sets up in the unmanned aerial vehicle middle section and increases steady rotor 5, increases steady rotor 5 and undertakes more loads, and consequently unmanned aerial vehicle is more steady when high maneuver, and maneuverability can obtain promoting greatly. The air current that upper rotor 1 produced when rotating forms "precompression" to lower rotor 2, and the air input and the air density of lower rotor 2 are bigger, have improved the working property of lower rotor 2 to a great extent. In a similar way, the working performance of the stability-increasing rotor wing 5 is improved to a certain extent, so that the high maneuverability of the unmanned aerial vehicle is very superior in structural design, and the situations of tail flicking, overturning and the like cannot be caused.
One or more of a photographing lens, a radar, a laser detector, an ultrasonic detector and an infrared scanner are installed in the load portion 23. The load part 23 is provided with different detection devices, and can detect forest fire prevention, meteorological detection, environmental pollution, emergency rescue and other purposes.
One of the upper rotor wing 1, the lower rotor wing 2 and the stability augmentation rotor wing 5 is opposite to the other two in rotation direction. Can balance respective deflection torque through the rotational speed of regulation and control upper rotor 1, lower rotor 2 and increase steady rotor 5 and according to the length of its rotor blade, deflection torque is 0 or in very little within range, and unmanned aerial vehicle's course is stable, regulates and control upper rotor 1, lower rotor 2 increase steady rotor 5 respective torque size between the developments, and then can make the aircraft obtain the best balance point in stability and flexibility.
Go up rotor 1, lower rotor 2 and increase steady rotor 5's blade can change its inclination in certain extent according to its direction of rotation change, can ensure like this that upper rotor 1, lower rotor 2 and increase steady rotor 5 can both produce ascending pulling force when turning to in the difference.
The bottom of the working part 8 is provided with a fixed bottom plate 24; the working part 8 is provided with a first steering engine 10 and a second steering engine 13; the first steering engine 10 is fixedly arranged on a base 18, a first support frame 17 is fixedly arranged on the base 18, the first support frame 17 is provided with a pan-tilt 12, and the second steering engine 13 is fixedly arranged on the pan-tilt 12; a first eccentric shaft 15 is arranged on the first steering engine 10, and the first eccentric shaft 15 is movably connected with the pan-tilt 12 through a first connecting rod 11; the cradle head 12 is fixedly provided with a second support frame 19, the second support frame 19 is movably provided with a fixed sleeve 20, and the coaxial motor 9 is fixed on the inner fixed sleeve 20; a second eccentric shaft 16 is arranged on the second steering engine 13, and the second eccentric shaft 16 is movably connected with the fixed sleeve 20 through a second connecting rod 14;
the first eccentric shaft 15 and the second eccentric shaft 16 are vertically arranged; the first steering engine 10 controls the angle change of the pan-tilt head 12, and the second steering engine 13 controls the angle change of the coaxial motor 9;
the first eccentric shaft 15 and the second eccentric shaft 16 are vertically arranged; therefore, the first steering engine 10 controls the transverse pendulum motion of the coaxial motor 9, and the second steering engine 13 controls the longitudinal pendulum motion of the coaxial motor 9, so as to control the change of the angle between the upper rotor 1 and the lower rotor 2, thereby controlling the direction of the unmanned aerial vehicle. More important, when unmanned aerial vehicle meets the air vortex or does high maneuver, balanced organism that can be fine.
The fixed bottom plate 24 is fixedly connected with the base 18 through a third support frame 21, a space 22 is formed between the fixed bottom plate 24 and the base 18, and a control module and a power supply are installed in the space 22;
the power supply provides electric energy for the coaxial motor 9, the first steering engine 10, the second steering engine 13, the hollow shaft motor 6 and the control module; the control module is in electric data connection with the coaxial motor 9, the first steering engine 10, the second steering engine 13 and the hollow shaft motor 6.
The upper rotor wing 1, the lower rotor wing 2 and the stability augmentation rotor wing 5 can be folded up and down, and the force required by folding any one of the rotor wings is greater than the sum of the gravity of the unmanned aerial vehicle and the resistance received by the maximum speed.
The control module has the functions of receiving, storing, processing, transmitting and sending data. The control module is electrically connected with the annunciator 27 through data, and since the carbon fiber layer 2603 on the shell has a shielding effect, data interaction between the control module and the outside is realized through the annunciator 27.
The shooting lens, the radar, the laser detector, the ultrasonic detector or the infrared scanner are powered by a power supply, and are in electrical data connection with the control module.
The control module is provided with a real-time data transmission module; the shooting lens is one of a double-optical lens, a low-light lens, a zoom lens and an anti-shake lens; the radar is a millimeter wave radar or a micron wave radar. Along with the increase of the precision of electronic detection equipment, unmanned aerial vehicle's accuse is surveyed the function and is also promoted greatly, under the regional and usage circumstances of difference, can be selective install different detection equipment, also not only limit shooting lens, radar, laser detector, ultrasonic detector or infrared scanner.
The working portion 8 and the housing 26 of the load portion 23 are cylindrical, and the housing 26 includes a strut layer 2601, a fixing layer 2602, and a carbon fiber layer 2603. The pillar layer 2601 and the fixing layer 2602 are made of resin or aluminum alloy. Mainly alleviate unmanned aerial vehicle's self weight, strengthened the intensity of unmanned aerial vehicle casing simultaneously. The carbon fiber material is 5 times of the strength of steel and 1/6 of the mass, so that the structural strength of the shell is greatly improved, and the weight is reduced. The loading portion 23 is provided with a space where a photographing lens, a radar, a laser detector, an ultrasonic detector or an infrared scanner is installed, and is not shielded by the housing 26. The carbon fiber material has excellent conductivity and has a shielding effect on electromagnetic waves. The working part 8 is provided with an annunciator 27, and the annunciator 27 penetrates through the shell 26; the annunciator 27 is in electrical data communication with the control module. The annunciator 27 has the functions of receiving and sending data, and avoids the shielding of the carbon fiber layer to the control module, i.e. the unmanned aerial vehicle can normally receive instructions and send information.
The solar cell 25 is a thin film solar cell or a flexible solar cell, and the solar cell 25 is mounted outside the case 26.
The method for manufacturing the shell according to claim 1 comprises the following steps:
the first step is as follows: adding 10-15 parts of thermoplastic resin particles into a heating furnace, stirring and heating to a molten state;
the second step is that: adding 1-2 parts of foaming agent and 0.2-0.5 part of the linen fiber storage cloth into a heating furnace, and quickly and uniformly stirring to obtain a mixed solution; the structural strength of the shell strut layer and the fixing layer is enhanced by the linen fiber stored in the storage cloth;
the third step: pouring the mixed solution into a mold for the support layer 2601 and the fixing layer 2602, heating at 10 ℃ per hour under the air pressure of 0.5-0.6MPa, and cooling to normal temperature at 60 ℃ per hour when bubbles are generated in the mixed solution to obtain the support layer 2601 and the fixing layer 2602; the gas is difficult to escape from the mixed liquid due to pressurization, pores are formed in the cooling process, and under the condition of the same material thickness, the larger the pore size is, the more the pore size is,
the fourth step: soaking the obtained support layer 2601 and fixed layer 2602 in GaCO3 or GaSO3 suspension for 10-15 min, and oven drying at 50-60 deg.C; after the support column is soaked in GaCO3 or GaSO3 suspension liquid and dried, GaCO3 or GaSO3 is partially filled in the pores, so that the stress in the support column layer and the fixing layer is reduced, and the structural strength is improved;
the fifth step: polishing the fixed layer 2602, and then installing and curing the upper carbon fiber layer 2603; the carbon fibers are reinforced on the fixed layer through glue or other methods, and the structural strength of the shell is obviously improved. Meanwhile, the shielding effect and the good heat conductivity are achieved, and the internal heat dissipation of the unmanned aerial vehicle is facilitated;
and a sixth step: the solar cell 25 is mounted on the carbon fiber layer 2603 of the outer layer of the case.
The foaming agent is one or more of sodium bicarbonate, azodiisobutyronitrile, azodicarbonamide, benzenesulfonylhydrazide, p-toluenesulfonylhydrazide, foaming agent DPT, foaming agent BN, diazophenylaminobenzene, frother and urea. After heating, gas is generated, and bubbles are formed in the mixed liquid.
The solar cell 25 is a thin film solar cell or a flexible solar cell.
Although embodiments of the present invention have been shown and described, it will be appreciated by those skilled in the art that changes, modifications, substitutions and alterations can be made in these embodiments without departing from the principles and spirit of the invention, the scope of which is defined in the appended claims and their equivalents.
Claims (5)
1. An unmanned aerial vehicle, its characterized in that: the high-stability solar energy hybrid power generation device comprises a solar cell (25), a coaxial motor (9), an upper rotary wing (1), a lower rotary wing (2), a working part (8), a stability-increasing rotary wing (5) and a load part (23);
the coaxial motor (9) is fixed on the working part (8), the coaxial motor (9) is fixedly connected with the upper rotor wing (1) through the first rotating shaft (3), and the coaxial motor (9) is fixedly connected with the lower rotor wing (2) through the second rotating shaft (4); the working part (8) is fixedly connected with the load part (23) through a fixed shaft (7), the fixed shaft (7) is fixedly provided with a hollow shaft motor (6), and the hollow shaft motor (6) is fixedly connected with a stability-increasing rotor (5);
one or more of a shooting lens, a radar, a laser detector, an ultrasonic detector and an infrared scanner are arranged in the load part (23);
the solar cell (25) is mounted on the working part (8) shell (26) and the loading part (23) shell (26);
the solar energy battery pack comprises a working part (8), a load part (23) and a shell (26), wherein the shell (26) of the working part (8) and the shell (26) of the load part (23) are both cylindrical, the shell (26) comprises a strut layer (2601), a fixing layer (2602) and a carbon fiber layer (2603), a solar battery (25) is installed on the outer side of the shell (26), the solar battery (25) is connected in series and is connected with a battery through a lead, and a rectifying circuit, a filter circuit and an inverter voltage regulating circuit are arranged in a connecting line of the solar battery (25) and the battery; the working part (8) is provided with an annunciator (27), and the annunciator (27) penetrates through the shell (26); the annunciator (27) is electrically connected with the control module in a data mode;
the strut layer (2601) and the fixing layer (2602) are made of resin or aluminum alloy;
the manufacturing method of the shell comprises the following steps:
the first step is as follows: adding 10-15 parts of thermoplastic resin particles into a heating furnace, stirring and heating to a molten state;
the second step is that: adding 1-2 parts of foaming agent and 0.2-0.5 part of the linen fiber storage cloth into a heating furnace, and quickly and uniformly stirring to obtain a mixed solution;
the third step: pouring the mixed solution into a support layer (2601) and fixed layer (2602) mold, heating at 10 ℃ per hour under the air pressure of 0.5-0.6MPa, and cooling to normal temperature at 60 ℃ per hour when bubbles are generated in the mixed solution to obtain a support layer (2601) and a fixed layer (2602);
the fourth step: soaking the obtained support layer (2601) and the obtained fixed layer (2602) in GaCO3 or GaSO3 suspension for 10-15 min, taking out, and oven drying at 50-60 deg.C;
the fifth step: polishing the fixed layer (2602), and then installing and curing an upper carbon fiber layer (2603);
and a sixth step: a solar cell (25) is mounted on the carbon fiber layer (2603) of the outer shell layer.
2. A drone according to claim 1, characterized in that: one of the upper rotor wing (1), the lower rotor wing (2) and the stability augmentation rotor wing (5) is opposite to the other two in rotation direction.
3. A drone according to claim 1, characterized in that: a fixed bottom plate (24) is arranged at the bottom of the working part (8); the working part (8) is provided with a first steering engine (10) and a second steering engine (13); the first steering engine (10) is fixedly arranged on a base (18), a first support frame (17) is fixedly arranged on the base (18), a pan-tilt (12) is arranged on the first support frame (17), and the second steering engine (13) is fixedly arranged on the pan-tilt (12); a first eccentric shaft (15) is arranged on the first steering engine (10), and the first eccentric shaft (15) is movably connected with the holder (12) through a first connecting rod (11); the cradle head (12) is fixedly provided with a second support frame (19), the second support frame (19) is movably provided with a fixed sleeve (20), and the coaxial motor (9) is fixed in the fixed sleeve (20); a second eccentric shaft (16) is arranged on the second steering engine (13), and the second eccentric shaft (16) is movably connected with the fixed sleeve (20) through a second connecting rod (14);
the first eccentric shaft (15) and the second eccentric shaft (16) are vertically arranged;
the fixed bottom plate (24) is fixedly connected with the base (18) through a third support frame (21), a space (22) is formed between the fixed bottom plate (24) and the base (18), and a control module and a power supply are installed in the space (22);
the power supply provides electric energy for the coaxial motor (9), the first steering engine (10), the second steering engine (13), the hollow shaft motor (6) and the control module; the control module is in electric data connection with the coaxial motor (9), the first steering engine (10), the second steering engine (13) and the hollow shaft motor (6).
4. A drone according to claim 3, characterized in that: the control module has the functions of receiving, storing, processing, transmitting and sending data.
5. A drone according to claim 1, characterized in that: the foaming agent is one or more of sodium bicarbonate, azodiisobutyronitrile, azodicarbonamide, benzene sulfonyl hydrazide, p-toluene sulfonyl hydrazide, a foaming agent DPT, a foaming agent BN, diazo phenyl aminobenzene, a foaming agent and urea.
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| EP2394914A1 (en) * | 2010-06-12 | 2011-12-14 | Promark Sp. z o.o. | A rotorcraft with a coaxial rotor system |
| CN205554581U (en) * | 2015-12-31 | 2016-09-07 | 歌尔科技有限公司 | Aircraft |
| CN207523930U (en) * | 2017-11-23 | 2018-06-22 | 安徽民生信息股份有限公司 | A kind of foldable DCB Specimen individual soldier unmanned plane |
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Inventor after: Zhou Xiang Inventor after: Chen Pu Inventor after: He Hongtao Inventor before: Chen Pu Inventor before: Zhou Xiang Inventor before: He Hongtao |