CN219406927U - Water-air dual-purpose unmanned aerial vehicle - Google Patents
Water-air dual-purpose unmanned aerial vehicle Download PDFInfo
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- CN219406927U CN219406927U CN202320449720.0U CN202320449720U CN219406927U CN 219406927 U CN219406927 U CN 219406927U CN 202320449720 U CN202320449720 U CN 202320449720U CN 219406927 U CN219406927 U CN 219406927U
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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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Abstract
The utility model discloses a water-air dual-purpose unmanned aerial vehicle, which comprises a body, a vertical lifting mechanism, a folding solar panel power generation system and an air bag component, wherein the vertical lifting mechanism is respectively arranged on two main wings of the body, the vertical lifting mechanism is crisscrossed with the main wings, a tail pushing propeller is arranged between two tail wings on the body, the folding solar panel power generation system and the air bag component are respectively symmetrically arranged on two landing gears of the body, the folding solar panel power generation system is arranged above the air bag component, and the tail parts of the two landing gears are respectively provided with the water pushing propeller. The utility model adopts the vertical take-off and landing fixed wing unmanned aerial vehicle, the air bag component and the folding solar panel are charged for continuous voyage, which is a development of continuous voyage function of the unmanned aerial vehicle, has higher practicability and has popularization and application prospect.
Description
Technical Field
The utility model relates to an unmanned aerial vehicle, in particular to a water-air dual-purpose unmanned aerial vehicle.
Background
The amphibious unmanned aerial vehicle combines the advantages of an aircraft and a submarine, can fly in the air and can navigate in water, and the key technology is stable and reliable power and water-air switching.
The underwater rotor unmanned aerial vehicle can take off and land vertically on the water surface, navigate underwater and fly in the air, but the application field is limited by the cruising and air flying or underwater/water navigation speed.
Patent CN114644112a proposes a water-air dual-purpose unmanned aerial vehicle, which can realize underwater, water surface and air operations, but the above scheme has air propellers, water-pushing propellers, rotors and the like simultaneously, so that multiple power propulsion may greatly reduce the endurance time of the unmanned aerial vehicle, and especially limit the space-time range of cruising at sea and air.
Disclosure of Invention
The utility model aims to: aiming at the problems, the utility model aims to provide the water-air dual-purpose unmanned aerial vehicle, which improves the application range and the long-time operation capability of the unmanned aerial vehicle.
The technical scheme is as follows: the utility model provides a dual-purpose unmanned aerial vehicle in water and air, including fuselage, vertical take-off and landing mechanism, folding solar panel power generation system and balloon subassembly, install a vertical take-off and landing mechanism respectively on two main wings of fuselage, vertical take-off and landing mechanism is the cross with the main wing along, installs the tail between two fin on the fuselage and pushes away the screw, installs folding solar panel power generation system and balloon subassembly on two undercarriage of fuselage respectively symmetry, wherein, folding solar panel power generation system sets up in balloon subassembly top, and a water push screw is installed respectively to the afterbody of two undercarriage.
The tail pushing propeller is connected with the unmanned aerial vehicle avionics system. The landing gear belongs to a skid-like structure, is symmetrically arranged about the machine body and fixedly connected with the machine body, and is in a strictly watertight hollow square shape as a whole. And the aircraft body inner avionics system and the power supply lead-out cable are connected with a water-pushing propeller, a folding solar panel power generation system, a balloon component and the like from the watertight space in the landing gear.
Further, the vertical take-off and landing mechanism comprises a horn and a rotor wing, wherein the horn is arranged below the main wing in a crisscross manner, the middle part of the horn is connected with the main wing, and the upper surfaces of the two ends of the horn are respectively provided with the rotor wing. The rotor on the horn is connected with avionics system through control cable communication.
When flying in the air, realize unmanned aerial vehicle lift-off through perpendicular take-off and landing mechanism, the rotation of tail push screw realizes the advancing of organism, and unmanned aerial vehicle reaches the rotor of certain speed and stops gradually, relies on the main wing to adopt fixed wing unmanned aerial vehicle flight mode, can in time change unmanned aerial vehicle configuration according to the flight mission.
Further, the folding solar panel power generation system comprises rectangular solar panels and first rotating shafts, wherein two rectangular solar panels are arranged in parallel at intervals, main wings on the corresponding side are positioned between the two rectangular solar panels, each rectangular solar panel is formed by arranging a plurality of first solar unit panels in a rectangular mode, the two adjacent first solar unit panels are connected through the first rotating shafts, and the first solar unit panel is connected with the side face of the landing gear through the first rotating shaft. The first solar unit plates are sequentially hinged through a plurality of hinges.
Optimally, the folding solar panel power generation system further comprises a fan-shaped solar panel and a rotating shaft II, wherein the fan-shaped solar panel is arranged at the front end of the landing gear through the rotating shaft II.
The folding solar panel power generation system further comprises a solar controller and a storage battery, folding control of the rectangular solar panel is achieved through the first rotating shaft, unfolding of the fan-shaped solar panel is achieved through the second rotating shaft, the first rotating shaft and the second rotating shaft are rotated through respective rotating motors, the second rotating shaft is further provided with a rotating shaft, the folding solar panel power generation system can solve the problem that the unmanned aerial vehicle is charged and cruises on the sea due to insufficient electric power, the sea area range of the unmanned aerial vehicle is enlarged, and meanwhile the unmanned aerial vehicle is not hindered from flying.
Further, the air bag assembly comprises an air bag box, the air bag box is arranged on the undercarriage on the corresponding side, an inflating and deflating mechanism and an air bag body are arranged in the air bag box, the air bag body is inflated through the inflating and deflating mechanism and is ejected out of the air bag box, and the air bag body is arranged at the bottom of the undercarriage after being unfolded.
Further, the inflation and deflation mechanism comprises an inflation tube, a stop valve and an air bag storage tube groove, the air bag body is arranged in the air bag storage tube groove, the air bag storage tube groove is provided with the inflation valve and an exhaust valve, the inflation valve is connected with the inflation tube through the stop valve, and a pressure sensor is arranged in the air bag body and is in signal connection with the stop valve.
The outside parcel of gasbag body has the protective coat, plays the effect of protection to the gasbag body, prevents the gasbag body damage, prolongs its life, and inflation valve and discharge valve all expose the protective coat and inflate and deflate.
The gasbag subassembly mainly is used when unmanned aerial vehicle takes place to descend the sea, makes unmanned aerial vehicle float at the surface of water through the gasbag body, also can play the cushioning effect when unmanned aerial vehicle descends, reduces the impact force when unmanned aerial vehicle falls to the ground. The airbag body is arranged in the airbag storage tube groove at the lower part of the airbag box when not unfolded, the filling gas of the airbag body can be helium or nitrogen, and the airbag body is symmetrically arranged at two sides of the machine body after being inflated and is unfolded along the length direction. The air bag body is provided with the air charging valve and the exhaust valve, the air bag body can be inflated through the air charging valve, and the air in the air bag body can be discharged through the exhaust valve, so that the air bag is simple in structure and convenient to use.
In addition, through the discharge valve of rational arrangement gasbag body, the recoil force that produces when utilizing the gasbag to exhaust assists unmanned aerial vehicle surface of water to slide and lift off.
Optimally, the landing gear is hollow and provided with a cable hole and a connecting hole connected with the bottom of the air bag box, and a cable is led out from the avionic system through the cable hole and/or the connecting hole and is respectively connected with the air bag box, the water-pushing propeller and the solar panel power generation system.
A connecting hole is formed between the bottom of the air bag box and the landing gear, and the lead-out cable is used for controlling the inflation and deflation mechanism to achieve inflation or deflation of the air bag.
Optimally, the tail end of the landing gear is vertically provided with a chute, and a propeller central shaft of the water-pushing propeller is connected with the landing gear through the chute. The central shaft of the propeller is arranged in a chute behind the landing gear and is also connected with the avionics system through a cable, so that the propeller can slide up and down to prevent the unmanned aerial vehicle from being influenced by the take-off and landing and the navigation on the water surface.
When the unmanned aerial vehicle needs to land on the water due to insufficient power or other reasons, a sunny sea area is searched through the avionic system, the rotor wing of the vertical take-off and landing mechanism is started, the air bag body is inflated by the inflation and deflation mechanism in the air bag box, the floating of the body in the water can be realized, when the water is on the sea, the water pushing propeller shaft is immersed into the water through the sliding groove, and the navigation of the body is realized through the forward and backward rotation of the water pushing propeller.
The unmanned aerial vehicle can be further provided with a light-following system and a two-rotation-degree-of-freedom serial driving device, and is used for adjusting the power generation posture of the folding solar panel so as to control the light-incident area and the angle of the solar panel; the light tracking system adopts a photoelectric tracking light tracking system or a sun-viewing movement track tracking light tracking system, so that the maximization of light utilization is realized.
The beneficial effects are that: compared with the prior art, the utility model has the advantages that: the unmanned aerial vehicle has the advantages that the unmanned aerial vehicle can guarantee the long-period operation capacity, the amphibious unmanned aerial vehicle can realize the air-sea three-dimensional monitoring capacity, the large-area long-time cruising and fixed-point observation of a specific sea area integrated with the sea and the air can be realized, the foldable folding solar panel power generation system, the unmanned ship hull structure and the fixed-wing unmanned aerial vehicle with the rotor wing can take off and land vertically are combined, the unmanned aerial vehicle can be effectively combined with an unmanned ship, the flight advantages of the two unmanned aerial vehicles and the water surface navigation capacity are simultaneously realized according to requirements, and when the unmanned aerial vehicle can be forced to land on the water due to insufficient electric power, the charging cruising of the foldable folding solar panel power generation system can be realized, and the sea-air three-dimensional monitoring capacity and the large-area cruising of the specific sea area can be realized.
Drawings
FIG. 1 is a schematic perspective view of the present utility model;
FIG. 2 is a rear view of the present utility model;
FIG. 3 is a top view of the present utility model;
FIG. 4 is a side view of the present utility model;
FIG. 5 is an enlarged view of a portion of the landing gear;
FIG. 6 is a schematic perspective view of a water-propelled propeller;
fig. 7 is a schematic structural view of the airbag module.
Detailed Description
The utility model will be further elucidated with reference to the drawings and to specific embodiments, it being understood that these embodiments are only intended to illustrate the utility model and are not intended to limit the scope thereof.
A water-air dual-purpose unmanned plane is shown in figures 1-7 and comprises a plane body 1, a vertical lifting mechanism, a folding solar panel power generation system and an air bag assembly.
The two main wings 2 of the fuselage 1 are respectively provided with a vertical lifting mechanism, the vertical lifting mechanism is crisscross with the main wings 2 along the edge, the vertical lifting mechanism comprises a horn 3 and a rotor wing 4, the horn 3 is crisscross arranged below the main wings 2, the middle part of the horn 3 is connected with the main wings 2, and the upper surfaces of the two ends of the horn 3 are respectively provided with the rotor wing 4.
A tail pushing propeller 6 is arranged between two tail wings 5 on a machine body 1, two landing gears 12 of the machine body 1 are symmetrically provided with a folding solar panel power generation system and an airbag assembly respectively, wherein the folding solar panel power generation system is arranged above the airbag assembly and comprises a rectangular solar panel 8 and a first rotating shaft 10, two rectangular solar panels 8 are arranged at intervals in parallel, a main wing 2 on one corresponding side is positioned between the two rectangular solar panels 8, the rectangular solar panels 8 are formed by arranging a plurality of first solar panels in a rectangular mode, two adjacent first solar panels are connected through the first rotating shaft 10, and the first solar panels are connected with the side faces of the landing gears 12 through the second rotating shaft 10. In order to utilize the illumination area as much as possible, the folding solar panel power generation system further comprises a fan-shaped solar panel 9 and a rotating shaft II 14 except for the rectangular solar panels 8 on two sides of the machine body, and the fan-shaped solar panel 9 is arranged at the front end of the landing gear 12 through the rotating shaft II 14. A rotary driving control device (such as a PLC) is also arranged in the landing gear, and the solar panel is folded and unfolded by combining a rotary motor.
The airbag module comprises an airbag case 11, the airbag case 11 is arranged on a landing gear 12 on the corresponding side, an inflation and deflation mechanism 20 and an airbag body 13 are arranged in the airbag case 11, the airbag body 13 is inflated through the inflation and deflation mechanism 20 and is ejected out of the airbag case 11, and the airbag body 13 is positioned at the bottom of the landing gear 12 after being unfolded.
The inflation and deflation mechanism 20 comprises an inflation tube 21, a stop valve 22 and an airbag storage tube groove 24, the airbag body 13 is arranged in the airbag storage tube groove 24, the airbag storage tube groove 24 is provided with an inflation valve 23 and an exhaust valve 25, the inflation valve 23 is connected with the inflation tube 21 through the stop valve 22, and a pressure sensor is arranged in the airbag body 13 and is in signal connection with the stop valve 22.
The tail parts of the two landing gears 12 are respectively provided with a water-pushing screw propeller 7, a cylindrical protective cover 17 is arranged outside the water-pushing screw propeller 7, a chute 18 is vertically arranged at the tail end of the landing gear 12, and a screw propeller central shaft 19 of the water-pushing screw propeller 7 is connected with the landing gear 12 through the chute 18. The water pushing propeller 7 can slide up and down according to the navigation requirement of the unmanned aerial vehicle and can be driven by an air cylinder.
The landing gear 12 is hollow and provided with a cable hole 16 and a connecting hole 15 connected with the bottom of the air bag box 11, and a cable is led out from the avionics system through the cable hole 16 and/or the connecting hole 15 and is respectively connected with the air bag box 11, the water-pushing propeller 7 and the solar panel power generation system.
When the unmanned aerial vehicle flies in the air, the unmanned aerial vehicle is lifted off and assisted to advance through the vertical lifting mechanism, and the tail pushing propeller 6 rotates to advance the body. The unmanned aerial vehicle reaches a certain speed, the rotor 4 gradually stops, the fixed wing unmanned aerial vehicle flight mode is adopted by the main wing 2, and the actual operation unmanned aerial vehicle can timely change the flight mode according to the flight task. When the unmanned aerial vehicle needs to land on the water due to insufficient power or other reasons, the avionics system is used for searching for a sea area with sufficient illumination, the rotor 4 of the vertical take-off and landing mechanism is started, the unmanned aerial vehicle hovers gradually, the air bag body 13 is inflated by the air bag in-box inflation and deflation mechanism 20, the body floats in the water, the water pushing propeller 7 is immersed in the water gradually, and the water surface navigation of the body is realized.
Then solar panel expansion work, rectangular solar panel 8 and fan-shaped solar panel 9 expand, and through the expansion of pivot control solar panel, realized unmanned aerial vehicle need the sea of forced landing because of reasons such as electric power insufficiency's the continuation of journey that charges, enlarged unmanned aerial vehicle's sea area scope of using, promoted unmanned aerial vehicle duration.
When the water surface is lifted off again, the rotor 4 is lifted off in a land lifting mode, and the air bag body 13 discharges air through the tail exhaust valve 25 and then is recovered into the pipe groove 24 of the air bag box.
When the unmanned aerial vehicle takes off to the air, 4 rotor wings extending from front to back are arranged on the main wings to provide lifting force, when the unmanned aerial vehicle climbs to a certain height, the aircraft can cruise by virtue of the fixed wings when flying stably in the air, an airbag box connected by the landing gear is controlled to be inflated to open an airbag when the unmanned aerial vehicle falls to the water surface, and the 2 propellers behind the landing gear provide thrust when sailing, so that the functions of flying in the air and sailing on the water surface can be realized. After the air bag is opened, the folding solar panel solidified by the landing gear is unfolded to charge the unmanned aerial vehicle. According to the utility model, the fixed-wing unmanned aerial vehicle is added with the vertical take-off and landing mechanism, and is effectively combined with the unmanned ship, so that the unmanned aerial vehicle has the flight advantages and the water surface navigation capability of the two unmanned aerial vehicles at the same time according to the requirements, when the unmanned aerial vehicle can be forced to land on the water surface due to insufficient power, the unmanned aerial vehicle can be charged by the solar panel for cruising, and the whole device can realize the three-dimensional monitoring capability of the sea and the large-area cruising of a specific sea area.
The following specifically provides an operation method of the device, which comprises the following steps:
step one: the unmanned aerial vehicle ascends on the land. When this unmanned aerial vehicle received the instruction of taking off, rotor 4 starts, can realize unmanned aerial vehicle lift-off and supplementary advancing, and the rotation of tail push screw 6 realizes advancing of organism, and unmanned aerial vehicle reaches the rotor 4 of certain speed and stops gradually, relies on main wing 2 to adopt fixed wing unmanned aerial vehicle flight mode, aerial operation reducible energy consumption under this mode.
Step two: the unmanned aerial vehicle lands on the sea surface. When the unmanned aerial vehicle needs to land on the water due to insufficient power or other reasons, the unmanned aerial vehicle firstly searches a calm sea area with sufficient illumination through the avionic system, the rotor 4 is started, and the unmanned aerial vehicle hovers gradually. The inflation and deflation mechanism 20 in the air bag box inflates the air bag body 13 through the inflation valve 23, and a pressure sensor can be stuck in the air bag body, wherein when the pressure reaches a threshold value, the stop valve 22 cuts off the inflation. The air bag realizes that the machine body floats in water, the water pushing screw propeller 7 is gradually immersed in water through the chute 18, and the water surface navigation of the machine body is realized. And then the solar cell panel is unfolded, and the fan-shaped solar cell panel 9 of the rectangular solar cell panel 8 is unfolded through the first rotating shaft 10 and the second rotating shaft 14 respectively to charge and cruise the unmanned aerial vehicle.
Step three: the unmanned aerial vehicle is lifted off the sea. When the lift-off instruction is received on the sea surface, the rotor wing 4 starts the unmanned aerial vehicle to suspend, the water-pushing propeller 7 is lifted, the driving device controls the solar panel to fold and retract, gas in the air bag body is discharged by the tail exhaust valve 25, the gas is discharged and then is retracted into the air bag storage tube groove 24 in the air bag box 11, and then a quasi-land lift-off mode is adopted, so that a certain speed is achieved, and a fixed wing unmanned aerial vehicle flight mode is adopted.
Step four: the unmanned aerial vehicle lands on the land, the tail pushing screw propeller 6 rotates reversely to realize speed reduction, the rotor wing 4 is started to hover and approach the ground, and the water pushing screw propeller 7 slides to the top end of the chute 18; the inflation and deflation mechanism 20 can be synchronously started to open the air bag body 13 during emergency landing, so that the impact force on the ground is reduced.
In addition, can carry on the fuselage equipment such as radar, sonar detector, camera, can carry the detection equipment in water on the undercarriage, carry different detection equipment according to the in-service use demand, the flexibility is high.
The device for landing, cruising and reeveleaving of the small fixed-wing unmanned aerial vehicle on the water surface adopts the vertical-lifting fixed-wing unmanned aerial vehicle, the floating air bag and the folding solar panel are charged for cruising, and the device is extension and innovation of the cruising function of the unmanned aerial vehicle, and has better novelty, practicability and larger popularization and application prospect.
Claims (8)
1. A water-air dual-purpose unmanned aerial vehicle which is characterized in that: the solar energy power generation system comprises a machine body (1), a vertical lifting mechanism, a folding solar panel power generation system and an air bag component, wherein the vertical lifting mechanism is respectively arranged on two main wings (2) of the machine body (1), the vertical lifting mechanism is crisscrossed with the main wings (2), a tail pushing propeller (6) is arranged between two tail wings (5) on the machine body (1), the folding solar panel power generation system and the air bag component are respectively symmetrically arranged on two landing gears (12) of the machine body (1), the folding solar panel power generation system is arranged above the air bag component, and a water pushing propeller (7) is respectively arranged at the tail parts of the two landing gears (12).
2. A water-air dual-purpose unmanned aerial vehicle as claimed in claim 1, wherein: the vertical take-off and landing mechanism comprises a horn (3) and rotary wings (4), wherein the horn (3) is arranged below the main wing (2) in a crisscross manner, the middle part of the horn is connected with the main wing (2), and the upper surfaces of the two ends of the horn (3) are respectively provided with one rotary wing (4).
3. A water-air dual-purpose unmanned aerial vehicle as claimed in claim 1, wherein: the folding solar panel power generation system comprises rectangular solar panels (8) and first rotating shafts (10), wherein two rectangular solar panels (8) are arranged at parallel intervals, a main wing (2) on one corresponding side is positioned between the two rectangular solar panels (8), each rectangular solar panel (8) is formed by arranging a plurality of first solar unit panels in a rectangular mode, two adjacent first solar unit panels are connected through the first rotating shaft (10), and the first solar unit panel is connected with the side face of the landing gear (12) through the first rotating shaft (10).
4. A water-air dual-purpose unmanned aerial vehicle according to claim 3, wherein: the folding solar panel power generation system further comprises a fan-shaped solar panel (9) and a second rotating shaft (14), wherein the fan-shaped solar panel (9) is arranged at the front end of the landing gear (12) through the second rotating shaft (14).
5. A water-air dual-purpose unmanned aerial vehicle as claimed in claim 1, wherein: the airbag assembly comprises an airbag box (11), the airbag box (11) is arranged on a landing gear (12) on one side correspondingly, an inflating and deflating mechanism (20) and an airbag body (13) are arranged in the airbag box (11), the airbag body (13) is inflated through the inflating and deflating mechanism (20) to be ejected out of the airbag box (11), and the airbag body (13) is arranged at the bottom of the landing gear (12) after being unfolded.
6. The water-air dual-purpose unmanned aerial vehicle of claim 5, wherein: the inflation and deflation mechanism (20) comprises an inflation tube (21), a stop valve (22) and an air bag storage tube groove (24), wherein the air bag body (13) is arranged in the air bag storage tube groove (24), the air bag storage tube groove (24) is provided with the inflation valve (23) and an exhaust valve (25), the inflation valve (23) is connected with the inflation tube (21) through the stop valve (22), a pressure sensor is arranged in the air bag body (13), and the pressure sensor is in signal connection with the stop valve (22).
7. The water-air dual-purpose unmanned aerial vehicle of claim 5, wherein: the landing gear (12) is hollow and provided with a cable hole (16) and a connecting hole (15) connected with the bottom of the air bag box (11), and a cable is led out from the avionic system through the cable hole (16) and/or the connecting hole (15) and is respectively connected with the air bag box (11), the water-pushing propeller (7) and the solar panel power generation system.
8. A water-air dual-purpose unmanned aerial vehicle as claimed in claim 1, wherein: a chute (18) is vertically arranged at the tail end of the landing gear (12), and a propeller central shaft (19) of the water-pushing propeller (7) is connected with the landing gear (12) through the chute (18).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202320449720.0U CN219406927U (en) | 2023-03-10 | 2023-03-10 | Water-air dual-purpose unmanned aerial vehicle |
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| Application Number | Priority Date | Filing Date | Title |
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| CN202320449720.0U CN219406927U (en) | 2023-03-10 | 2023-03-10 | Water-air dual-purpose unmanned aerial vehicle |
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| CN219406927U true CN219406927U (en) | 2023-07-25 |
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| CN202320449720.0U Active CN219406927U (en) | 2023-03-10 | 2023-03-10 | Water-air dual-purpose unmanned aerial vehicle |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN117262267A (en) * | 2023-11-21 | 2023-12-22 | 山东字节信息科技有限公司 | Amphibious unmanned plane |
| CN117885923A (en) * | 2024-03-14 | 2024-04-16 | 航大汉来（天津）航空技术有限公司 | Long-endurance patrol unmanned aerial vehicle |
-
2023
- 2023-03-10 CN CN202320449720.0U patent/CN219406927U/en active Active
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN117262267A (en) * | 2023-11-21 | 2023-12-22 | 山东字节信息科技有限公司 | Amphibious unmanned plane |
| CN117262267B (en) * | 2023-11-21 | 2024-02-09 | 山东字节信息科技有限公司 | Amphibious unmanned plane |
| CN117885923A (en) * | 2024-03-14 | 2024-04-16 | 航大汉来（天津）航空技术有限公司 | Long-endurance patrol unmanned aerial vehicle |
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