CN115285362A - Multi-rotor solar long-endurance unmanned aerial vehicle - Google Patents

Multi-rotor solar long-endurance unmanned aerial vehicle Download PDF

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Publication number
CN115285362A
CN115285362A CN202210979730.5A CN202210979730A CN115285362A CN 115285362 A CN115285362 A CN 115285362A CN 202210979730 A CN202210979730 A CN 202210979730A CN 115285362 A CN115285362 A CN 115285362A
Authority
CN
China
Prior art keywords
solar
frame
solar energy
main part
energy electroplax
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Pending
Application number
CN202210979730.5A
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Chinese (zh)
Inventor
付晓亮
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Shenzhen Beinuosi Technology Co ltd
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Shenzhen Beinuosi Technology Co ltd
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Shenzhen Beinuosi Technology Co ltd filed Critical Shenzhen Beinuosi Technology Co ltd
Priority to CN202210979730.5A priority Critical patent/CN115285362A/en
Publication of CN115285362A publication Critical patent/CN115285362A/en
Pending legal-status Critical Current

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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
    • B64D27/00—Arrangement or mounting of power plant in aircraft; Aircraft characterised thereby
    • B64D27/02—Aircraft characterised by the type or position of power plant
    • B64D27/24—Aircraft characterised by the type or position of power plant using steam, electricity, or spring force
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B60—VEHICLES IN GENERAL
    • B60L—PROPULSION OF ELECTRICALLY-PROPELLED VEHICLES; SUPPLYING ELECTRIC POWER FOR AUXILIARY EQUIPMENT OF ELECTRICALLY-PROPELLED VEHICLES; ELECTRODYNAMIC BRAKE SYSTEMS FOR VEHICLES IN GENERAL; MAGNETIC SUSPENSION OR LEVITATION FOR VEHICLES; MONITORING OPERATING VARIABLES OF ELECTRICALLY-PROPELLED VEHICLES; ELECTRIC SAFETY DEVICES FOR ELECTRICALLY-PROPELLED VEHICLES
    • B60L8/00—Electric propulsion with power supply from forces of nature, e.g. sun or wind
    • B60L8/003—Converting light into electric energy, e.g. by using photo-voltaic systems
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C21/00—Influencing air flow over aircraft surfaces by affecting boundary layer flow
    • B64C21/10—Influencing air flow over aircraft surfaces by affecting boundary layer flow using other surface properties, e.g. roughness
    • 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
    • H—ELECTRICITY
    • H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
    • H02S—GENERATION OF ELECTRIC POWER BY CONVERSION OF INFRARED RADIATION, VISIBLE LIGHT OR ULTRAVIOLET LIGHT, e.g. USING PHOTOVOLTAIC [PV] MODULES
    • H02S20/00—Supporting structures for PV modules
    • H02S20/30—Supporting structures being movable or adjustable, e.g. for angle adjustment
    • H02S20/32—Supporting structures being movable or adjustable, e.g. for angle adjustment specially adapted for solar tracking
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B60—VEHICLES IN GENERAL
    • B60L—PROPULSION OF ELECTRICALLY-PROPELLED VEHICLES; SUPPLYING ELECTRIC POWER FOR AUXILIARY EQUIPMENT OF ELECTRICALLY-PROPELLED VEHICLES; ELECTRODYNAMIC BRAKE SYSTEMS FOR VEHICLES IN GENERAL; MAGNETIC SUSPENSION OR LEVITATION FOR VEHICLES; MONITORING OPERATING VARIABLES OF ELECTRICALLY-PROPELLED VEHICLES; ELECTRIC SAFETY DEVICES FOR ELECTRICALLY-PROPELLED VEHICLES
    • B60L2200/00—Type of vehicles
    • B60L2200/10—Air crafts

Abstract

The invention discloses a multi-rotor solar long-endurance unmanned aerial vehicle, which comprises: fuselage main part, spiral leaf, solar energy electroplax, modulation capture subassembly and tortuous become and fall and hinder the subassembly, the terminal surface transversely is fixed with the stake body around the fuselage main part, each relatively pivoted symmetry is provided with the spiral leaf on the stake body, the up end arrangement of fuselage main part is provided with a plurality of solar energy electroplaxs, and is a plurality of the inverter in solar energy electroplax and the fuselage main part is connected, and each the below of solar energy electroplax still is equipped with the modulation and catches the subassembly, the modulation catches the one end of subassembly with the fuselage main part is connected, it falls and hinders the subassembly still to overlap on the solar energy electroplax to be equipped with the tortuous change.

Description

Multi-rotor solar long-endurance unmanned aerial vehicle
Technical Field
The invention belongs to the technical field of unmanned aerial vehicle equipment, and particularly relates to a multi-rotor solar long-endurance unmanned aerial vehicle.
Background
The solar unmanned aerial vehicle mainly adopts solar radiation as an energy source, and is a product combining an aviation scientific technology and a new energy technology. The solar panel laid on the surface of the machine body converts absorbed solar radiation energy into electric energy for charging the energy storage battery, releasing the electric energy stored in the energy storage battery and maintaining the normal operation of the whole system. However, most solar unmanned aerial vehicles in the prior art are easily influenced by the solar panels when ascending or descending to cause too large flight resistance, and in order to ensure the flight safety of the solar unmanned aerial vehicles, most solar panels are selected to be tiled and fixed on the aircraft body, so that the photoelectric conversion efficiency of the solar unmanned aerial vehicles is too low, and the solar unmanned aerial vehicles become flying chicken ribs.
Therefore, the technical personnel in the field provide a multi-rotor solar long-endurance unmanned aerial vehicle to solve the problems provided in the background art.
Disclosure of Invention
In order to achieve the purpose, the invention provides the following technical scheme: the utility model provides a many rotors solar energy long endurance unmanned aerial vehicle, it includes: fuselage main part, spiral leaf, solar energy electroplax, modulation are caught subassembly and bent and are fallen and hinder the subassembly, the terminal surface transversely is fixed with the stake body around the fuselage main part, each relatively pivoted symmetry is provided with the spiral leaf on the stake body, the up end of fuselage main part is arranged and is provided with a plurality of solar energy electroplaxs, and is a plurality of the inverter in solar energy electroplax and the fuselage main part is connected, and each the below of solar energy electroplax still is equipped with the modulation and catches the subassembly, the modulation catch the one end of subassembly with the fuselage main part is connected, it falls and hinders the subassembly still to overlap the distortion on the solar energy electroplax.
Further, preferably, the modulation capturing component comprises: the solar photovoltaic cell module comprises a mounting bottom plate, adjusting screws, fine adjustment motors, a sliding frame and shaft frame rods, wherein the mounting bottom plate is fixed on a body main body, three adjusting screws are uniformly distributed in the circumferential direction of the mounting bottom plate and are horizontally and rotatably erected on the mounting bottom plate, the fine adjustment motors are correspondingly fixed on the mounting bottom plate, the output ends of the fine adjustment motors are connected with the adjusting screws, the sliding frame is connected onto the adjusting screws in a sliding mode through thread meshing transmission, the sliding frame is connected onto the adjusting screws in a sliding mode, the shaft frame rods are obliquely and universally hinged on the sliding frame, and the other ends of the shaft frame rods are universally hinged below a solar cell panel.
Further, preferably, a photosensitive sensor is further arranged on the mounting bottom plate.
Preferably, the solar panels are four arranged in an array, and can be transversely and longitudinally alternated under the action of the turning of the shaft frame rods in the turning capturing component.
Further, preferably, the variogram resistance-reduction component includes: the film coating machine comprises an outer film frame, a transfer sleeve, an inner spring, a telescopic guide rod and an electric telescopic rod; the solar panel is characterized in that transmission sleeves are symmetrically embedded and fixed at the edges of two sides of the solar panel, the outer film frame is sleeved outside the solar panel in a sliding manner through the two transmission sleeves, the cross section of the outer film frame is of an oval structure, a fixing piece is arranged in the transmission sleeves in a limiting sliding manner, the fixing piece is fixed with the outer film frame, and a plurality of inner springs are connected between the transmission sleeves and the fixing piece; a plurality of telescopic guide rods are vertically arranged below the solar panel, the telescopic guide rods are of a two-section telescopic structure, one end of each telescopic guide rod is connected with the outer membrane frame, and a plurality of electric telescopic rods are vertically arranged above the solar panel;
and the two sides of the solar panel are also rotatably provided with tightening wheels, the tightening wheels are abutted against and contacted with the outer membrane frame, and the tightening wheels can be vertically and slidably adjusted relatively and are arranged in the solar panel.
Preferably, the upper end face of the outer film frame is further provided with a trimming plate frame in a covering connection mode.
Preferably, two ends of the fine adjustment plate frame are respectively arranged on the outer membrane frame in a limiting and sliding manner through inner guide pieces, a plurality of separating pieces are vertically fixed on the fine adjustment plate frame, each separating piece is vertically arranged on the outer membrane frame in a sealing and sliding manner, a plurality of airflow cavities are uniformly divided between the fine adjustment plate frame and the outer membrane frame, and a plurality of supporting springs are arranged between each separating piece and the outer membrane frame; and a plurality of guide pipes corresponding to the air flow cavities vertically penetrate and are fixedly arranged on the outer film frame, and one ends of the guide pipes are communicated with the mounting air pump.
Further, as preferred, all be provided with the gasbag body in each air current cavity, the coaxial interior pipe fitting that is provided with in the draught tube, interior pipe fitting with the gasbag body is linked together.
Further, as preferred, the outer membrane frame all adopts transparent plastic material with the fine setting grillage.
Compared with the prior art, the invention has the beneficial effects that:
1. the solar panels are arranged to ensure the photoelectric conversion efficiency, and the maximum power point tracking of the modulation capture component can be carried out by the solar panels to ensure that the solar panels can just face to the sun;
2. the bending resistance reduction assembly further arranged in the invention can simulate flying wings after adjustment, so that the flying wind resistance of the solar panel is reduced when the solar panel is used by leaning on an inclined frame or is used in a tiled mode, the stability of the main body of the unmanned aerial vehicle is improved, and the normal flying steering of the unmanned aerial vehicle is ensured.
Drawings
FIG. 1 is a schematic structural view of the present invention;
FIG. 2 is a schematic side view of the present invention;
FIG. 3 is a schematic view of a transpose capture assembly according to the present invention;
FIG. 4 is a schematic structural diagram of a curved resistance-reducing component according to the present invention;
FIG. 5 is a schematic view of the construction of a trim plate rack of the present invention;
FIG. 6 is a schematic view of the air flow under the tile of the solar panel of the present invention;
FIG. 7 is a schematic view of the air flow of the present invention with a plurality of solar panels in an inclined configuration;
in the figure: the device comprises a main body 1, spiral blades 11, a solar panel 2, a transferring and capturing component 3, a mounting bottom plate 31, an adjusting screw rod 32, a fine adjustment motor 33, a sliding frame 34, a shaft frame 35, a curved resistance reduction component 4, an outer film frame 41, a transmission sleeve 42, a fixing part 43, an inner spring 44, a telescopic guide rod 45, an electric telescopic rod 46, a tightening wheel 47, a fine adjustment plate frame 5, a separating part 51, a flow guide pipe 52, an inner pipe 53 and an air bag 54.
Detailed Description
Referring to fig. 1, in the embodiment of the present invention, a multi-rotor solar long-endurance unmanned aerial vehicle is characterized in that: it comprises the following steps: the aircraft comprises an aircraft body 1, spiral blades 11, solar panels 2, a transfer capturing component 3 and a deflection resistance reducing component 4, wherein support bodies are transversely fixed on the front end face and the rear end face of the aircraft body 1, the spiral blades 11 are symmetrically arranged on the support bodies in a relative rotating mode, the solar panels 2 are arranged on the upper end face of the aircraft body 1 and connected with an inverter (not shown in the figure) on the aircraft body 1, the area of the solar panels is three quarters of the aircraft body, the light spot conversion efficiency of the aircraft body is guaranteed, flying ribs are avoided, the deflection capturing component 3 is arranged below each solar panel 2, one end of the deflection capturing component 3 is connected with the aircraft body 1, the deflection resistance reducing component 4 is sleeved on each solar panel 2 and used for adjusting the curvature of the solar panels in flying, and the like wings of a simulated aircraft are achieved, air flow is adjusted, and wind resistance is reduced.
In this embodiment, the modulation capturing component 3 includes: the solar energy electric plate comprises a mounting bottom plate 31, adjusting screws 32, fine adjustment motors 33, a sliding frame 34 and shaft frame rods 35, wherein the mounting bottom plate 31 is fixed on a body main body 1, three adjusting screws 32 are uniformly distributed in the circumferential direction of the mounting bottom plate 31, each adjusting screw 32 is erected on the mounting bottom plate 31 in a horizontal rotating mode, the fine adjustment motors 33 are correspondingly fixed on the mounting bottom plate 31, the output ends of the fine adjustment motors 33 are connected with the adjusting screws 32, the sliding frame 34 is connected to the adjusting screws 32 in a sliding mode through thread meshing transmission in a sliding mode, the shaft frame rods 35 are hinged to the sliding frame 34 in an inclined mode in a universal mode, the other ends of the shaft frame rods 35 are hinged to the lower portion of a solar energy electric plate 2 in a universal mode, in use, each solar energy electric plate can synchronously conduct deflection adjustment through a deflection capturing component through adjustment, and photoelectric conversion in flight is guaranteed.
In a preferred embodiment, a photosensitive sensor (not shown) is further disposed on the mounting base plate 31 for finding out a best illumination angle in real time to realize maximum power point tracking.
In this embodiment, the solar panels 2 are four arranged in a row, and the solar panels can be horizontally and longitudinally alternated under the action of the shaft frame 35 in the modulation capturing component 3, so that the directions of the curved resistance-reducing components on the solar panels can be adjusted in flight, and the airflow guidance in flight can be realized.
In this embodiment, the distortion and resistance reduction component 4 includes: an outer membrane frame 41, a transfer sleeve 42, an inner spring 44, a telescopic guide rod 45 and an electric telescopic rod 46; the solar panel is characterized in that the edges of two sides of the solar panel 2 are symmetrically embedded and fixed with transmission sleeves 42, the outer film frame 41 is sleeved outside the solar panel 2 in a sliding manner through the two transmission sleeves 42, the cross section of the outer film frame 41 is of an oval structure, a fixing piece 43 is arranged in the transmission sleeves 42 in a limiting and sliding manner, the fixing piece 43 is fixed with the outer film frame 41, and a plurality of inner springs 44 are connected between the transmission sleeves 42 and the fixing piece 43; a plurality of telescopic guide rods 45 are also vertically arranged below the solar panel 2, the telescopic guide rods 45 are of a two-section telescopic structure, one end of each telescopic guide rod 45 is connected with the outer film frame 41, and a plurality of electric telescopic rods 46 are also vertically arranged above the solar panel 2; that is, the curvature of the lower end surface of the outer membrane frame is changed by the corresponding telescopic adjustment action of the plurality of electric telescopic rods during use, at the moment, the curvature of the lower end surface of the outer membrane frame is adjusted by the telescopic guide rod through the elastic action of the central springs (refer to fig. 6), so that the air above the outer membrane frame has higher flowing speed and low pressure intensity in flight, the air below the outer membrane frame has lower flowing speed and high pressure intensity, and an upward lifting force is achieved in the pressure difference formed by the upper part and the lower part, so that the flight windage is reduced, and the wing effect of a simulated aircraft is achieved;
and the both sides of solar energy electroplax 2 still rotate and are provided with tightening wheel 47, tightening wheel 47 and adventitia frame 41 counterbalance are leaned on the contact, but the installation of tightening wheel 47 vertical sliding adjustment relatively in solar energy electroplax 2, especially, tightening wheel can make the adventitia frame can laminate completely on the solar energy electroplax surface in sliding displacement, can realize that the camber is zero this moment.
In this embodiment, the up end of adventitia frame 41 still covers and is provided with fine setting grillage 5, that is to say, fine setting grillage can further assist the adjustment adventitia frame upper surface camber, reaches the fine setting effect of camber.
As a preferred embodiment, two ends of the fine adjustment plate frame 5 are respectively disposed on the outer membrane frame 41 in a limited sliding manner through inner guide members, a plurality of partition members 51 are vertically fixed on the fine adjustment plate frame 5, each partition member 51 is vertically and hermetically disposed on the outer membrane frame 41 in a sliding manner, a plurality of airflow cavities are uniformly divided between the fine adjustment plate frame 5 and the outer membrane frame 41, and a plurality of support springs are disposed between the partition members 51 and the outer membrane frame 41; go up perpendicular run through on the adventitia frame 41 be fixed with a plurality ofly with the honeycomb duct 52 that the air current cavity is corresponding, the one end and the installation air pump of honeycomb duct 52 are linked together, especially, through installation air pump gas injection pressure boost for it can finely tune the breathing to correspond each air current cavity, and the adventitia frame upper surface curvature change precision is higher this moment, and surface continuity is stronger simultaneously, further improves flight stability.
In this embodiment, an air bag body 54 is disposed in each of the air flow cavities, an inner pipe 53 is coaxially disposed in the flow guide pipe 52, and the inner pipe 54 is communicated with the air bag body 54.
In this embodiment, the outer membrane frame 41 all adopts transparent plastic material with fine setting grillage 5, avoids influencing the normal work of solar energy electroplax.
Specifically, the solar energy electroplax can the level lay on the one hand fuselage main part surface, and on the other hand accessible is transferred and is caught the subassembly slope and erect in the fuselage main part, for reducing flight windage this moment, falls the subassembly by the curvedness and hinders the component and to the accurate accent of solar energy electroplax surface curvature according to flight state, can mutually support (can present different inclination) between a plurality of solar energy electroplax simultaneously to fuselage main part stability in guaranteeing to fly.
The above description is only for the preferred embodiment of the present invention, but the scope of the present invention is not limited thereto, and any person skilled in the art should be considered to be within the technical scope of the present invention, and equivalent substitutions or changes according to the technical solution and the inventive concept of the present invention should be covered by the scope of the present invention.

Claims (9)

1. The utility model provides a many rotors solar energy long endurance unmanned aerial vehicle which characterized in that: it includes: fuselage main part 1, spiral leaf (11), solar energy electroplax (2), modulation capture subassembly (3) and bent resistance reduction subassembly (4), the terminal surface transversely is fixed with the stake body around fuselage main part (1), each the pivoted symmetry relatively is provided with spiral leaf (11) on the stake body, the up end arrangement of fuselage main part (1) is provided with a plurality of solar energy electroplax (2), and is a plurality of solar energy electroplax (2) are connected with the dc-to-ac converter on fuselage main part (1), and each the below of solar energy electroplax (2) still is equipped with modulation capture subassembly (3), the modulation capture the one end of subassembly (3) with fuselage main part (1) is connected, it is equipped with bent resistance reduction subassembly (4) still to overlap on solar energy electroplax (2).
2. A multi-rotor solar long endurance drone according to claim 1 and wherein: the transpose capture component (3) includes: mounting plate (31), adjusting screw (32), fine setting motor (33), carriage (34) and axle hack lever (35), be fixed with mounting plate (31) on fuselage main part (1), each the circumferencial direction evenly distributed of mounting plate (31) has three adjusting screw (32), each the equal level rotation of adjusting screw (32) erects on mounting plate (31), it is fixed with fine setting motor (33) to correspond on mounting plate (31), the output of fine setting motor (33) with adjusting screw (32) are connected, sliding rack (34) have been cup jointed through the screw-thread meshing transmission slip on adjusting screw (32), it has axle hack lever (35) to slope to articulate on carriage (34), the other end universal of axle hack lever (35) articulates in solar energy electroplax (2) below.
3. A multi-rotor solar long endurance drone according to claim 1 and wherein: and a photosensitive sensor is also arranged on the mounting bottom plate (31).
4. A multi-rotor solar long endurance drone according to claim 3 and wherein: the solar panels (2) are arranged in four rows, and can be transversely and longitudinally alternated under the action of the shaft frame rods (35) in the transferring and capturing component (3).
5. A multi-rotor solar long endurance drone according to claim 1 and wherein: the variogram resistance-reducing component (4) comprises: the device comprises an outer film frame (41), a transmission sleeve (42), an inner spring (44), a telescopic guide rod (45) and an electric telescopic rod (46); the solar panel is characterized in that the edges of two sides of the solar panel (2) are symmetrically embedded and fixed by transmission sleeves (42), the outer film frame (41) is slidably sleeved outside the solar panel (2) through the two transmission sleeves (42), the cross section of the outer film frame (41) is of an oval structure, a fixing piece (43) is arranged in the transmission sleeves (42) in a limiting and sliding mode, the fixing piece (43) is fixed with the outer film frame (41), and a plurality of inner springs (44) are connected between the transmission sleeves (42) and the fixing piece (43); a plurality of telescopic guide rods (45) are vertically arranged below the solar panel (2), the telescopic guide rods (45) are of two-section type telescopic structures, one end of each telescopic guide rod is connected with the outer film frame (41), and a plurality of electric telescopic rods (46) are vertically arranged above the solar panel (2);
and both sides of solar energy electroplax (2) still rotate and are provided with tighten up wheel (47), tighten up wheel (47) and adventitia frame (41) butt contact, install in solar energy electroplax (2) that tighten up wheel (47) vertical sliding relatively adjusted.
6. A multi-rotor solar long-endurance unmanned aerial vehicle according to claim 5, wherein: the upper end face of the outer film frame (41) is also covered with a fine adjustment plate frame (5).
7. A multi-rotor solar long endurance drone according to claim 6 and wherein: the two ends of the fine adjustment plate frame (5) are respectively arranged on the outer membrane frame (41) in a limiting sliding mode through inner guide pieces, a plurality of partition pieces (51) are vertically fixed on the fine adjustment plate frame (5), each partition piece (51) is vertically arranged on the outer membrane frame (41) in a sealing sliding mode, a plurality of airflow cavities are uniformly divided between the fine adjustment plate frame (5) and the outer membrane frame (41), and a plurality of supporting springs are arranged between the partition pieces (51) and the outer membrane frame (41); a plurality of guide pipes (52) corresponding to the airflow cavities vertically penetrate and are fixed on the outer film frame (41), and one end of each guide pipe (52) is communicated with an air pump.
8. A multi-rotor solar long-endurance unmanned aerial vehicle according to claim 7, wherein: an air bag body (54) is arranged in each air flow cavity, an inner pipe fitting (53) is coaxially arranged in the guide pipe (52), and the inner pipe fitting (54) is communicated with the air bag body (54).
9. A multi-rotor solar long endurance drone according to claim 8, wherein: the outer film frame (41) and the fine tuning plate frame (5) are made of transparent plastic materials.
CN202210979730.5A 2022-08-16 2022-08-16 Multi-rotor solar long-endurance unmanned aerial vehicle Pending CN115285362A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
CN202210979730.5A CN115285362A (en) 2022-08-16 2022-08-16 Multi-rotor solar long-endurance unmanned aerial vehicle

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CN202210979730.5A CN115285362A (en) 2022-08-16 2022-08-16 Multi-rotor solar long-endurance unmanned aerial vehicle

Publications (1)

Publication Number Publication Date
CN115285362A true CN115285362A (en) 2022-11-04

Family

ID=83830166

Family Applications (1)

Application Number Title Priority Date Filing Date
CN202210979730.5A Pending CN115285362A (en) 2022-08-16 2022-08-16 Multi-rotor solar long-endurance unmanned aerial vehicle

Country Status (1)

Country Link
CN (1) CN115285362A (en)

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