CN117342008A - But quick assembly disassembly's high navigational speed mixes wing unmanned aerial vehicle - Google Patents

But quick assembly disassembly's high navigational speed mixes wing unmanned aerial vehicle Download PDF

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Publication number
CN117342008A
CN117342008A CN202311457386.4A CN202311457386A CN117342008A CN 117342008 A CN117342008 A CN 117342008A CN 202311457386 A CN202311457386 A CN 202311457386A CN 117342008 A CN117342008 A CN 117342008A
Authority
CN
China
Prior art keywords
wing
tail
assembly
middle wing
unmanned aerial
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
CN202311457386.4A
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Chinese (zh)
Inventor
王君睿
王江浩
高繁
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.)
Anhui Yunyi Aviation Technology Co ltd
Original Assignee
Anhui Yunyi Aviation 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 Anhui Yunyi Aviation Technology Co ltd filed Critical Anhui Yunyi Aviation Technology Co ltd
Priority to CN202311457386.4A priority Critical patent/CN117342008A/en
Publication of CN117342008A publication Critical patent/CN117342008A/en
Pending legal-status Critical Current

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Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U10/00—Type of UAV
    • B64U10/20—Vertical take-off and landing [VTOL] aircraft
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C27/00—Rotorcraft; Rotors peculiar thereto
    • B64C27/22—Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U10/00—Type of UAV
    • B64U10/70—Convertible aircraft, e.g. convertible into land vehicles
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U30/00—Means for producing lift; Empennages; Arrangements thereof
    • B64U30/10—Wings
    • B64U30/12—Variable or detachable wings, e.g. wings with adjustable sweep
    • B64U30/14—Variable or detachable wings, e.g. wings with adjustable sweep detachable
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U30/00—Means for producing lift; Empennages; Arrangements thereof
    • B64U30/40—Empennages, e.g. V-tails

Abstract

The invention discloses a fast-disassembly high-navigational speed mixed wing unmanned aerial vehicle which comprises a fuselage assembly, a middle wing assembly, two rotor wing assemblies, two flank assemblies, two tail support assemblies and a horizontal tail assembly, wherein the tail of the fuselage assembly is provided with a spiral wing driving mechanism, the middle wing assembly is connected with the fuselage assembly, the two rotor wing assemblies are respectively connected with two ends of the middle wing assembly, the two flank assemblies are respectively connected with the outer sides of the corresponding rotor wing assemblies, the front ends of the two tail support assemblies are connected with the middle wing assembly, and the horizontal tail assembly is connected between the rear ends of the two tail support assemblies. The middle wing assembly and the machine body assembly, the middle wing and the two rotors and the side wings, the middle wing assembly and the two tail support assemblies, and the tail support assembly and the horizontal tail assembly can be quickly assembled and disassembled, disassembly parts required by boxing can be quickly completed, time and labor are saved, and the double-purpose function of one machine can be realized by conveniently switching between the two types of the vertical take-off and landing hybrid wing unmanned aerial vehicle and the fixed wing.

Description

But quick assembly disassembly's high navigational speed mixes wing unmanned aerial vehicle
Technical Field
The invention relates to the technical field of hybrid wing unmanned aerial vehicles, in particular to a high-navigational speed hybrid wing unmanned aerial vehicle capable of being quickly disassembled and assembled.
Background
Under the vigorous development of aviation technology, the aircraft has greatly improved functions and performances, and has obvious improvement in the aspects of use experience and convenience. In the unmanned aerial vehicle field, people not only have a great deal of demands on unmanned aerial vehicle operability, security and intelligence, but also have more of said demands on the aspects of functionality, assembly, disassembly and transportation and site requirements.
As the vertical take-off and landing type hybrid wing unmanned aerial vehicle, the requirement on the take-off and landing field requirement is very low, and after the fixed wing mode is switched, the range and the functionality are very large, so that the hybrid wing unmanned aerial vehicle is a good choice for functions such as investigation, patrol, rescue and the like. As a fixed wing unmanned aerial vehicle, the excellent flight endurance, speed, maneuverability, stability, safety, and the like are outstanding in the field of unmanned aerial vehicles.
The existing vertical lifting type mixed wing unmanned aerial vehicle and fixed wing unmanned aerial vehicle have the problems of inconvenient disassembly and assembly when being switched, and are not beneficial to packaging and transportation. Meanwhile, the existing wing structure has the problem of high flight resistance.
Disclosure of Invention
The invention aims to provide a fast-detachable high-navigational speed hybrid wing unmanned aerial vehicle which is used for solving the technical problems in the background technology.
The technical scheme of the invention provides a fast-disassembly high-navigational speed mixed wing unmanned aerial vehicle, which comprises a fuselage assembly, a middle wing assembly, two rotor wing assemblies, two flank assemblies, two tail support assemblies and a horizontal tail assembly, wherein the tail of the fuselage assembly is provided with a spiral wing driving mechanism, the middle wing assembly is connected with the fuselage assembly, the two rotor wing assemblies are respectively connected with two ends of the middle wing assembly, the two flank assemblies are respectively connected with the outer sides of the corresponding rotor wing assemblies, the two tail support assemblies are connected with the middle wing assembly at the front ends of the two tail support assemblies, and the horizontal tail assembly is connected between the rear ends of the two tail support assemblies;
the fuselage assembly comprises a fuselage bearing framework, a airspeed tube, a landing gear assembly, a battery mounting rack, an oil tank, a wing quick-release piece, a landing gear assembly, a front hatch cover and a rear hatch cover; the landing gear component is a supporting frame with a roller structure;
the middle wing assembly comprises a middle wing framework, two fuselage connecting carbon tubes and two vertical tail connecting carbon tubes which are fixed on the middle wing framework, two middle wing inserting boxes which are fixed at two ends of the middle wing framework respectively, two hasp connecting pieces which are fixed by depending on the middle wing inserting boxes, and a threaded connecting piece which is fixed at the tail end of the vertical tail connecting carbon tubes;
the two rotor wing assemblies comprise two motor power systems with spiral wings, two rotor wing connecting pieces, buckles fixed by the rotor wing connecting pieces, and two buckle connecting pieces arranged on one side of the wing assemblies, which is in butt joint with the wing assemblies;
the two side wing assemblies comprise side wing frameworks, two side wing plugboards fixed at the wider end of the side wing frameworks and side wing buckles fixed by depending on the side wing plugboards;
the two tail support assemblies comprise a middle wing connecting carbon tube, a middle wing connecting metal piece close to the head end of the middle wing connecting carbon tube and a vertical tail fixedly connected with the middle wing connecting carbon tube.
In a preferred embodiment, the battery mounting frame is slidably arranged on the body bearing framework, and the battery mounting frame is provided with two rows of mounting holes.
In a preferred embodiment, two ends of the fuselage-connection carbon tube of the middle wing assembly are provided with metal bushings for quick plug-in insertion on the fuselage assembly, the two vertical tail-connection carbon tubes are fixed inside the middle wing assembly, the tail parts of the vertical tail-connection carbon tubes are fixedly connected through screw connectors and spring locking mechanisms, and the outward end faces of the vertical tail-connection carbon tubes are provided with error-preventing notches.
In a preferred embodiment, two pairs of strong magnets with opposite magnetic poles are arranged in the motor, one end of the strong magnets is fixed on the motor base and kept still, and the other end of the strong magnets is fixed near the rotating shaft and rotates along with the rotor.
In a preferred embodiment, the wing insert is inserted either into the slot of the corresponding rotor connection or into the middle wing insert box, and after complete insertion, the locking is accomplished with the corresponding snap connection by means of a snap.
In a preferred embodiment, two vertical fin plates and a vertical fin connector fixed by the vertical fin plates are fixed on the vertical fin, the outer ends of the two vertical fin plates and the vertical fin connector extend out of the vertical fin, and the outer ends of the vertical fin plate and the vertical fin connector on one vertical fin face the outer ends of the vertical fin plate and the vertical fin connector on the other vertical fin.
In a preferred embodiment, the front end of the middle wing connecting carbon tube is inserted into the corresponding vertical tail connecting carbon tube of the middle wing assembly so that the front end and the vertical tail connecting carbon tube are mutually nested and clamped, and the middle wing connecting metal piece is in threaded connection with the threaded connecting piece on the middle wing assembly.
In a preferred embodiment, the middle wing connecting metal piece is a threaded sleeve with an anti-misplug boss, and the threaded connecting piece is a threaded sleeve.
In a preferred embodiment, two horizontal tail slots are respectively arranged at two ends of the horizontal tail assembly, one of the horizontal tail slots is provided with a boss, and when the two tail support assemblies are assembled with the horizontal tail assembly, two vertical tail inserting plates on the vertical tail are respectively inserted into the two horizontal tail slots on the horizontal tail assembly.
The technical scheme of the invention has the beneficial effects that:
the middle wing assembly and the machine body assembly, the middle wing, the two rotary wings and the side wings, the middle wing assembly, the two tail support assemblies and the tail support assembly and the horizontal tail assembly can be quickly assembled and disassembled, and disassembly parts required for boxing can be quickly completed, so that time and labor are saved; the motor of the rotor arm has a locking function, and can automatically return to the position with the same line as the axis of the carbon tube after the rotor wing is stopped rotating, so that the wind resistance can be reduced and the navigational speed can be improved when the fixed wing flies; the battery mounting frame can move back and forth and be fixed on the central axis of the machine body, so that the gravity center can be adjusted under different task loads; the invention can be conveniently switched between the vertical take-off and landing mixed wing unmanned aerial vehicle and the fixed wing unmanned aerial vehicle, and realizes the function of one machine.
Drawings
Fig. 1 is a complete machine diagram of the present invention.
Figure 2 is a cross-sectional view of a fuselage assembly of the present invention.
Figure 3 is a top view of the fuselage assembly of the present invention.
FIG. 4 is a schematic view of the structure of the connection between the fuselage assembly and the middle wing assembly of the present invention.
Figure 5 is a cross-sectional view of a wing assembly of the present invention.
FIG. 6 is a combined view of a tail boom assembly and a horizontal tail assembly of the present invention.
Detailed Description
The invention will be described in further detail with reference to the drawings and the detailed description. The embodiments of the present invention have been presented for purposes of illustration and description, and are not intended to be exhaustive or limited to the invention in the form disclosed. Many modifications and variations will be apparent to those of ordinary skill in the art. The embodiments were chosen and described in order to best explain the principles of the invention and the practical application, and to enable others of ordinary skill in the art to understand the invention for various embodiments with various modifications as are suited to the particular use contemplated.
Referring to fig. 1, a fast detachable high-speed hybrid wing unmanned aerial vehicle comprises a fuselage assembly 1 with a spiral wing driving mechanism 10 at the tail, a middle wing assembly 2 connected to the top end of the fuselage assembly 1, two rotor wing assemblies 3 and 5 respectively connected to two ends of the middle wing assembly 2, two flank assemblies 4 and 6 respectively connected to the middle wing assembly 3 and two corresponding rotor wing assemblies 3 and 5, two tail support assemblies 8 and 9 with the front end connected to the middle wing assembly 2, and a horizontal tail assembly 7 connected between the rear ends of the two tail support assemblies 8 and 9 through a connecting plate 12 on the tail support assembly;
referring to fig. 2, 3 and 4, the fuselage assembly 1 includes a pitot tube 22, a front hatch 20, a landing gear assembly, an oil tank 23, a rear hatch 21, a motor housing 19, a battery mount 13, a fuselage load frame 14, a wing quick disconnect 16 and an anti-slip screw sleeve 15.
Referring to fig. 2, the landing gear assembly includes a nose landing gear 17 and a rear landing gear 18, and the nose landing gear 17 and the rear landing gear 18 are support frames with roller structures that can implement both a vertical take-off and landing function and a running-off and landing capability.
Referring to fig. 3, the battery mounting frame 13 can move back and forth in a platform area of the frame 14 and is fixed by corresponding holes on the frame 14, which is more beneficial to adjusting the center of gravity under different task loads, and the frame component is made of composite material mainly comprising carbon fiber.
Referring to fig. 4 and 5, the wing quick release member 16 penetrates through the fuselage bearing skeleton 14, and extends out of the fuselage assembly 1 to be partially inserted into the fuselage connecting carbon tube 32 in the middle wing assembly 2, and the outer end is screwed with the anti-release screw sleeve 15 to prevent the wing from falling off, so that the fuselage-middle wing quick fixation is completed.
Referring to fig. 5, the middle wing assembly 2 includes a middle wing skeleton, two fuselage connecting carbon tubes 32 fixed on the middle wing skeleton, two vertical connecting carbon tubes 29, a threaded connector 30 fixed on the tail of the vertical connecting carbon tubes 29, two middle wing boxes 28 at two ends, and two snap connectors 26 fixed by depending on the middle wing boxes 28. The fuselage of well wing subassembly 2 connect carbon tube 32 both ends and be provided with the metal bush that is used for the quick-insert male on the fuselage subassembly, two perpendicular to the tail connect carbon tube 29 fix inside well wing subassembly 2, perpendicular to the tail connect the threaded connection spare 30 that carbon tube 29 afterbody threaded connection has spring locking mechanism 31, the tail connects the end face design that carbon tube 29 outwards has the mistake proofing notch.
Both rotor assemblies 3, 5 comprise two motor power systems with flighting, two rotor connectors 27, a clasp 24 secured by means of the rotor connectors, and two clasp connectors 26 on the side of the wing assemblies that interfaces. The wing assemblies 4, 6 each comprise a wing framework, two wing insert plates 25 fixed at the wider end of the wing framework and wing buckles 24 fixed by the wing insert plates 25.
Wherein the rotor attachment 27 extends out of the rotor assembly towards the middle wing assembly end face portion of the same size as the portion of the wing insert 25 extending out of the wing assembly. One end of the rotor wing connecting piece is a slot, the other end is an inserting plate, the inserting plate end is inserted into a middle wing inserting box of the middle wing assembly, and fixing and locking are completed through a hasp. The side wing plugboard 25 can be inserted into the slot end of the rotor wing connector or the middle wing plug box, and is assembled according to the use requirement, and the fixing and locking of the side wing plugboard 25 are completed through snap connection. The two motor power systems with the spiral wings comprise the spiral wings and a motor, wherein the motor comprises an automatic locking structure, and the spiral wings can be locked in the axial direction of the rotor carbon tube.
The motor is internally provided with two pairs of strong magnets with opposite magnetic poles, one end of the strong magnets is fixed on the motor base and kept motionless, and the other end of the strong magnets is fixed near the rotating shaft and rotates along with the rotor. After the spiral wing rotates, if the direction is not at the axial position of the carbon tube, the two pairs of magnets generate repulsive force to rotate, and after the two pairs of magnets rotate to the axial position, the two pairs of magnets attract each other, so that the spiral wing is locked.
When the vertical take-off and landing type hybrid wing unmanned aerial vehicle is assembled, the middle wing assembly 2, the two rotor wing assemblies 3 and 5 and the two side wings 4 and 6 are inserted into each other in sequence according to the positions shown in fig. 5.
Referring to fig. 5 and 6, the end face of the middle wing connecting metal piece 39 on the tail support assembly is provided with an anti-misplug boss, the tail support carbon tube 41 is inserted into the vertical tail connecting carbon tube 29 of the middle wing assembly during assembly, the end face of the middle wing connecting metal piece 39 is attached to the end face of the threaded connecting piece 30, the threaded sleeve 40 is screwed with the threaded connecting piece 30, and the tooth clamping groove on the threaded sleeve 40 is buckled with the spring locking mechanism 31 to complete locking.
The two tail support assemblies comprise a middle wing connecting carbon tube, a middle wing connecting metal piece close to the head end of the middle wing connecting carbon tube and a vertical tail fixedly connected with the tail end of the carbon tube. The vertical fin is fixed with two vertical fin inserting plates 34 and 36 and a vertical fin connecting piece fixed by the vertical fin inserting plates, the outer end parts of the two vertical fin inserting plates and the vertical fin connecting piece extend out of the vertical fin, and the outer ends of the vertical fin inserting plates and the vertical fin connecting piece on one vertical fin face the outer ends of the vertical fin inserting plates and the vertical fin connecting piece on the other vertical fin. The front end part of the middle wing connecting carbon tube is inserted into the vertical tail connecting carbon tube corresponding to the middle wing component, so that the front end part and the vertical tail connecting carbon tube are mutually nested and clamped, and the middle wing connecting metal piece is in threaded connection with the threaded connecting piece on the middle wing component.
The middle wing connecting metal piece is a threaded sleeve with misplug preventing protrusions, and the threaded connecting piece 30 on the middle wing component 2 is a threaded sleeve. When the two are connected, the threaded sleeve 30 is screwed by using the threaded sleeve, the spring locking mechanism 31 on the threaded sleeve 30 automatically locks and prevents the disconnection, and when the threaded sleeve is disassembled, the spring locking mechanism 31 is only required to move towards the direction of compressing the spring, and then the threaded sleeve is loosened and pulled out.
Two horizontal tail slots 37 and 38 are formed in two ends of the horizontal tail assembly, a boss is arranged on the horizontal tail slot 37, when the two horizontal tail support assemblies are assembled with the horizontal tail assembly, the vertical tail inserting plates 34 and 36 on the vertical tail are respectively inserted into the horizontal tail slots 37 and 38, the buckling device 35 is fixed on the vertical tail inserting plate 34, after the vertical tail is completely abutted with the horizontal tail, the buckling device 35 can be automatically buckled with the boss on the horizontal tail slot 37, and after the two-side tail support assemblies are assembled with the horizontal tail, the two-side tail support assemblies are fixedly spliced with the middle wing. After the vertical tails on two sides are fixed with the horizontal tails, the horizontal tails can be clamped, and the risk of falling out of the horizontal tails is avoided.
In the use of complete machine, two rotor assemblies can assemble as required, are vertical take-off and landing formula hybrid wing unmanned aerial vehicle when assembling, are pure fixed wing unmanned aerial vehicle when not adorning.
It will be apparent that the described embodiments are only some, but not all, embodiments of the invention. All other embodiments, which can be made by those skilled in the art and which are included in the embodiments of the present invention without the inventive step, are intended to be within the scope of the present invention. Structures, devices and methods of operation not specifically described and illustrated herein, unless otherwise indicated and limited, are implemented according to conventional means in the art.

Claims (9)

1. But quick assembly disassembly's high navigational speed mixes wing unmanned aerial vehicle, its characterized in that: the device comprises a machine body component, a middle wing component, two rotor wing components, two flank components, two tail support components and a horizontal tail component, wherein the tail part of the machine body component is provided with a spiral wing driving mechanism, the middle wing component is connected with the machine body component, the two rotor wing components are respectively connected with two ends of the middle wing component, the two flank components are respectively connected with the outer sides of the corresponding rotor wing components, the front end of the two tail support components are connected with the middle wing component, and the horizontal tail component is connected between the rear ends of the two tail support components;
the fuselage assembly comprises a fuselage bearing framework, a airspeed tube, a landing gear assembly, a battery mounting rack, an oil tank, a wing quick-release piece, a landing gear assembly, a front hatch cover and a rear hatch cover; the landing gear component is a supporting frame with a roller structure;
the middle wing assembly comprises a middle wing framework, two fuselage connecting carbon tubes and two vertical tail connecting carbon tubes which are fixed on the middle wing framework, two middle wing inserting boxes which are fixed at two ends of the middle wing framework respectively, two hasp connecting pieces which are fixed by depending on the middle wing inserting boxes, and a threaded connecting piece which is fixed at the tail end of the vertical tail connecting carbon tubes;
the two rotor wing assemblies comprise two motor power systems with spiral wings, two rotor wing connecting pieces, buckles fixed by the rotor wing connecting pieces, and two buckle connecting pieces arranged on one side of the wing assemblies, which is in butt joint with the wing assemblies;
the two side wing assemblies comprise side wing frameworks, two side wing plugboards fixed at the wider end of the side wing frameworks and side wing buckles fixed by depending on the side wing plugboards;
the two tail support assemblies comprise a middle wing connecting carbon tube, a middle wing connecting metal piece close to the head end of the middle wing connecting carbon tube and a vertical tail fixedly connected with the middle wing connecting carbon tube.
2. The fast detachable high-speed hybrid wing unmanned aerial vehicle according to claim 1, wherein: the battery mounting frame is arranged on the machine body bearing framework in a sliding mode, and two rows of mounting holes are formed in the battery mounting frame.
3. The fast detachable high-speed hybrid wing unmanned aerial vehicle according to claim 1, wherein: the utility model discloses a middle wing subassembly's fuselage connect carbon tube both ends be provided with and be used for fuselage subassembly on quick-insert male metal bush, two perpendicular to the end connection carbon tube fix inside the middle wing subassembly, perpendicular to the end connection carbon tube afterbody fixed thread connecting spare, spring locking mechanism, perpendicular to the end face design that the end connection carbon tube outwards has the mistake proofing notch.
4. The fast detachable high-speed hybrid wing unmanned aerial vehicle according to claim 1, wherein: the motor is internally provided with two pairs of strong magnets with opposite magnetic poles, one end of the strong magnets is fixed on the motor base and kept motionless, and the other end of the strong magnets is fixed near the rotating shaft and rotates along with the rotor.
5. The fast detachable high-speed hybrid wing unmanned aerial vehicle according to claim 1, wherein: the side wing plugboard can be inserted into the slot of the corresponding rotor wing connector or the middle wing plug box, and is locked with the corresponding hasp connector through the hasp after the side wing plugboard is completely inserted.
6. The fast detachable high-speed hybrid wing unmanned aerial vehicle according to claim 1, wherein: the vertical fin is fixedly provided with two vertical fin inserting plates and a vertical fin connecting piece fixed by depending on the vertical fin inserting plates, the outer end parts of the two vertical fin inserting plates and the vertical fin connecting piece extend out of the vertical fin, and the outer ends of the vertical fin inserting plates and the vertical fin connecting piece on one vertical fin face the outer ends of the vertical fin inserting plates and the vertical fin connecting piece on the other vertical fin.
7. The fast detachable high-speed hybrid wing unmanned aerial vehicle of claim 6, wherein: the front end part of the middle wing connecting carbon tube is inserted into the vertical tail connecting carbon tube corresponding to the middle wing component, so that the front end part and the vertical tail connecting carbon tube are mutually nested and clamped, and the middle wing connecting metal piece is in threaded connection with the threaded connecting piece on the middle wing component.
8. The fast detachable high-speed hybrid wing unmanned aerial vehicle of claim 6, wherein: the middle wing connecting metal piece is a threaded sleeve with misplug preventing protrusions, and the threaded connecting piece is a threaded sleeve.
9. The fast detachable high-speed hybrid wing unmanned aerial vehicle according to claim 1, wherein: two horizontal tail slots are formed in two ends of the horizontal tail assembly, one of the horizontal tail slots is provided with a boss, and when the two tail support assemblies are assembled with the horizontal tail assembly, two vertical tail inserting plates on the vertical tail are respectively inserted into the two horizontal tail slots on the horizontal tail assembly.
CN202311457386.4A 2023-11-03 2023-11-03 But quick assembly disassembly's high navigational speed mixes wing unmanned aerial vehicle Pending CN117342008A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
CN202311457386.4A CN117342008A (en) 2023-11-03 2023-11-03 But quick assembly disassembly's high navigational speed mixes wing unmanned aerial vehicle

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CN202311457386.4A CN117342008A (en) 2023-11-03 2023-11-03 But quick assembly disassembly's high navigational speed mixes wing unmanned aerial vehicle

Publications (1)

Publication Number Publication Date
CN117342008A true CN117342008A (en) 2024-01-05

Family

ID=89363083

Family Applications (1)

Application Number Title Priority Date Filing Date
CN202311457386.4A Pending CN117342008A (en) 2023-11-03 2023-11-03 But quick assembly disassembly's high navigational speed mixes wing unmanned aerial vehicle

Country Status (1)

Country Link
CN (1) CN117342008A (en)

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