WO2023087602A1 - 一种可拆卸固定翼无人机 - Google Patents

一种可拆卸固定翼无人机 Download PDF

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Publication number
WO2023087602A1
WO2023087602A1 PCT/CN2022/085244 CN2022085244W WO2023087602A1 WO 2023087602 A1 WO2023087602 A1 WO 2023087602A1 CN 2022085244 W CN2022085244 W CN 2022085244W WO 2023087602 A1 WO2023087602 A1 WO 2023087602A1
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WO
WIPO (PCT)
Prior art keywords
rotor
fuselage
hook
wing
carbon tube
Prior art date
Application number
PCT/CN2022/085244
Other languages
English (en)
French (fr)
Inventor
刘十一
谢陵
胡汇
Original Assignee
中山福昆航空科技有限公司
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Filing date
Publication date
Application filed by 中山福昆航空科技有限公司 filed Critical 中山福昆航空科技有限公司
Publication of WO2023087602A1 publication Critical patent/WO2023087602A1/zh

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    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
    • B64C1/26—Attaching the wing or tail units or stabilising surfaces
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
    • B64C1/06—Frames; Stringers; Longerons ; Fuselage sections
    • B64C1/068—Fuselage sections
    • B64C1/0685—Tail cones
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
    • B64C1/30—Parts of fuselage relatively movable to reduce overall dimensions of 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
    • B64C27/26—Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft characterised by provision of fixed wings
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C39/00—Aircraft not otherwise provided for
    • B64C39/02—Aircraft not otherwise provided for characterised by special use
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U10/00—Type of UAV
    • B64U10/25—Fixed-wing aircraft
    • 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
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U30/00—Means for producing lift; Empennages; Arrangements thereof
    • B64U30/20—Rotors; Rotor supports
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U50/00—Propulsion; Power supply
    • B64U50/10—Propulsion
    • B64U50/19—Propulsion using electrically powered motors

Definitions

  • the invention relates to the field of unmanned aerial vehicles, in particular to a detachable fixed-wing unmanned aerial vehicle.
  • the fixed-wing UAV is disassembled, and the fixed-wing UAV is transported after disassembly, but the structure of the fixed-wing UAV is relatively complicated, and the disassembly efficiency is low, which is very inconvenient.
  • the purpose of the present invention is to overcome the deficiencies of the prior art.
  • the present invention provides a detachable fixed-wing unmanned aerial vehicle.
  • the unmanned aerial vehicle is designed to be detachable, and the wings and fuselage can be quickly disassembled to facilitate packing and transportation. With good convenience.
  • an embodiment of the present invention provides a detachable fixed-wing unmanned aerial vehicle, the unmanned aerial vehicle includes a fuselage, a tail cone, a first wing and a second wing, wherein:
  • One side of the fuselage is connected with the first wing, the other side of the fuselage is connected with the second wing, a fixed frame is arranged at the section of the tail cone and the fuselage, and the The fixed frame connects the tail vertebra and the fuselage together;
  • the section of the fuselage is provided with more than one bayonet and a third spring button;
  • the fixed frame includes a plurality of cross bars and more than one third bolts, the plurality of cross bars form a cross-sectional frame, and the more than one third bolts are fixed on the cross-sectional frame; the more than one One of the third pins is locked on one of the more than one bayonet sockets, and the inner wall of a cross bar of the fixed frame is fastened on the third spring button;
  • One side of the fuselage body is provided with a first connecting rod and a first spring button
  • the other side of the fuselage body is provided with a second connecting rod and a second spring button
  • the first wing is provided with a first spring button.
  • the second wing is provided with a second groove and a second button hole; the first connecting rod is inserted into the first groove, and the first button hole is clamped
  • the first spring button, the second connecting rod is inserted into the second groove, and the second button hole clamps the second spring button.
  • the fuselage includes a fuselage body and a rotor retractable assembly, wherein: the rotor retractable assembly is connected to the fuselage body;
  • the fuselage body is provided with a nacelle for placing the rotor retractable assembly, and the rotor retractable assembly is arranged in the nacelle;
  • the fuselage body is provided with a hatch for opening or closing the cabin
  • the rotor retractable assembly includes a stiffness disc, a first carbon tube and a second carbon tube, the first carbon tube is hinged to the second carbon tube, the stiffness disc is movably connected to the first carbon tube, and the The stiffness plate is flexibly connected with the second carbon tube;
  • the axis of the rigidity disk is provided with a connecting shaft, and the connecting shaft is connected to the first carbon tube and the second carbon tube;
  • the two ends of the first carbon tube are respectively provided with a first rotor and the second rotor, and the two ends of the second carbon tube are respectively provided with a third rotor and a fourth rotor.
  • the rotor retractable assembly further includes a first support, a second support, a third support and a fourth support, the first support, the second support, the third support
  • the first support and the fourth support are sequentially arranged on the lower side of the circumference of the stiffness plate, the first support is connected to the first carbon tube, and the second support is connected to the second carbon tube , the third support is connected to the first carbon tube, and the fourth support is connected to the second carbon tube.
  • the fuselage is provided with a power mechanism to control the expansion or contraction of the rotor retractable assembly
  • the power mechanism includes a first motor, a transmission shaft, a V-shaped adapter, a first rotating rod and a second rotating rod
  • the V-shaped adapter has a "V" structure, one end of the V-shaped adapter has a central connection end, the other end of the V-shaped adapter has a first connection end and a second connection end, and the transmission shaft One end is connected to the first motor, the other end of the transmission shaft is connected to the central connection end of the V-shaped adapter, the first connection end of the V-shaped adapter is connected to one end of the first rotating rod, and the V-shaped adapter
  • the second connecting end of the piece is connected to one end of the second rotating rod, the other end of the first rotating rod is connected to the first supporting member, and the other end of the second rotating rod is connected to the second supporting member.
  • the first rotor, the second rotor, the third rotor and the fourth rotor are of the same vertically symmetrical rotor structure, and the rotor structure includes a rotor locking mechanism and a rotor body, wherein:
  • the rotor locking mechanism is arranged on the outer periphery of the rotor body;
  • the rotor body includes a vertical motor and a rotating disk mounted on the vertical motor, and the rotating disk is driven by the vertical motor to rotate;
  • the rotor locking mechanism includes: a brake base, a DC motor and a link mechanism, the DC motor and the link mechanism are arranged on the brake base, and the DC motor can drive the extension hook on the link mechanism to The side of the rotating disk.
  • the fuselage further includes a top cover, the top cover is provided with a plurality of fixing hooks, the upper side of the fuselage body is provided with more than two interlocking hooks, and more than one interlocking hooks are arranged on the One end on the upper side of the fuselage body, and more than one interlocking hooks are arranged on the other end on the upper side of the fuselage body, and the top cover is fixedly connected by inserting the fixing hooks into the interlocking hooks of the fuselage.
  • the linkage hook includes a first hook assembly, a second hook assembly and a connecting rod, wherein:
  • Both ends of the connecting rod are respectively connected to the first hook assembly and the second hook assembly arranged in the same direction;
  • the connecting rod is provided with a first pin and a second pin, one end of the connecting rod is connected to the first hook assembly based on the first pin, and the other end of the connecting rod is connected to the first hook assembly based on the second pin.
  • One end of the first bolt is provided with a protruding straight rod
  • the first hook assembly and the second hook assembly are the same hook mechanism, the hook mechanism includes a fixed part and a movable part, and the fixed part is connected to the movable part based on a cylindrical pin;
  • the upper end of the movable part is a hook structure
  • a spring connected with the movable part is arranged under the cylindrical pin of the fixed part.
  • a first aileron is provided on the first wing, and a second aileron is provided on the first wing.
  • the underside of the fuselage is provided with a first landing gear assembly and a second landing gear assembly.
  • the tail cone is provided with a propeller.
  • the detachable fixed-wing unmanned aerial vehicle provided by the embodiment of the present invention is designed to be detachable, and the wings and the fuselage can be quickly disassembled, which is convenient for packing and transportation, and has good convenience;
  • the fuselage adopts the spring button The form clamps the wing and connects with the wing through the connecting rod.
  • the lateral force received by the wing is transmitted to the fuselage through the connecting rod to reduce the burden on the wing;
  • the buckle is fixed by a spring button, which is simple in structure, convenient and fast;
  • the top of the fuselage has a linkage hook, and the top cover of the fuselage can be quickly disassembled, which is very convenient for inspection and maintenance of the internal machinery of the fuselage.
  • Fig. 1 is a schematic structural view of a fixed-wing unmanned aerial vehicle according to an embodiment of the present invention.
  • Fig. 2 is a structural schematic diagram of the tail vertebra of the embodiment of the present invention.
  • Fig. 3 is a structural schematic diagram of a fuselage section of an embodiment of the present invention.
  • Fig. 4 is a schematic diagram of the connection structure between the fuselage body and the fixing block according to the embodiment of the present invention.
  • Fig. 5 is a structural schematic diagram of a fuselage in a top view according to an embodiment of the present invention.
  • Fig. 6 is a schematic structural view of the first wing according to the embodiment of the present invention.
  • Fig. 7 is a schematic structural view of the second wing according to the embodiment of the present invention.
  • Fig. 8 is a structural schematic diagram of an open nacelle according to an embodiment of the present invention.
  • Fig. 9 is a structural schematic diagram of a fixed-wing unmanned aerial vehicle according to an embodiment of the present invention.
  • Fig. 10 is a schematic structural view of the rotor retractable assembly and the power mechanism of the embodiment of the present invention.
  • Fig. 11 is a structural schematic diagram of the rotor structure of the embodiment of the present invention.
  • Fig. 12 is a schematic structural view of the rotor locking mechanism of the embodiment of the present invention.
  • Fig. 13 is a schematic structural diagram of the connection of the second motor according to the embodiment of the present invention.
  • Fig. 14 is a schematic structural view of the brake base according to the embodiment of the present invention.
  • Fig. 15 is a schematic diagram of the cut-away structure of the fuselage body according to the embodiment of the present invention.
  • Fig. 16 is a schematic structural diagram of the linkage hook according to the embodiment of the present invention.
  • Fig. 17 is a schematic structural diagram of a fixing member according to an embodiment of the present invention.
  • Fig. 18 is a schematic structural diagram of the movable part of the embodiment of the present invention.
  • Fig. 1 shows the structural representation of the fixed-wing unmanned aerial vehicle of the embodiment of the present invention
  • described unmanned aerial vehicle comprises fuselage, tail vertebra 20, first wing 31 and second wing 32, wherein: described fuselage One side is connected with the first wing 31, the other side of the fuselage is connected with the second wing 32, the cross section of the tail cone 20 and the fuselage is provided with a fixed frame 21, the The fixed frame 21 connects the tail cone 20 and the fuselage together.
  • the UAV is disassembled into several parts, and several parts are designed to be detachable.
  • the UAV can be transported by packing, which is very convenient.
  • the specific detachable structure is as follows:
  • Fig. 2 shows the structural representation of the tail vertebra of the embodiment of the present invention
  • Fig. 3 shows the structural representation of the fuselage section of the embodiment of the present invention
  • Fig. 4 shows the structure of the fuselage body and the fixed block of the embodiment of the present invention
  • Schematic diagram of connection structure the section of the fuselage is provided with more than one bayonet 141 and the third spring button 142;
  • a cross-sectional frame is formed, and the more than one third pins 211 are fixed on the cross-sectional frame; one of the more than one third pins 211 is clamped in more than one bayonet socket 141
  • the inner wall of a cross bar 212 of the fixed frame is buckled on the spring button; the third spring button 142 is used to clamp the fixed frame 21 .
  • the third pin 211 on the fixed frame 21 is inserted into the bayonet 141 from top to bottom, the cross bar 212 on the lower side of the fixed frame 21 slides over the third spring button 142, and is bounced up by the third spring button 142 and locked.
  • the crossbar 212 holding the lower side of the fixed frame 21 prevents the fixed frame 21 from moving upwards, and the bayonet 141 blocks the third pin 211 of the fixed frame 21 to prevent the fixed frame 21 from moving in other directions, through the third spring button 142 and the bayonet 141
  • the fixing frame 21 is fixed on the fuselage body 10, thereby realizing the fixing of the tail vertebra 20 and the fuselage body 10.
  • the fuselage body 10 is provided with five bayonet sockets 141, wherein, the cross section of the fuselage and tail cone 20 is rectangular, the left side of the fuselage section has two bayonet sockets 141, and the right side of the fuselage section has two bayonet sockets.
  • the fixing frame 21 is fixedly arranged on the coccyx 20, and the fixing methods can be various, such as screws, bolts and the like.
  • the latch 211, the cross bar 212 on the lower side of the fixed frame 21 is pressed through the third spring button 142, and the third spring button 142 pops up to prevent the fixed frame 21 from moving upwards.
  • Such an arrangement makes the four sides of the tail vertebrae 20 Both are fixed, and have a good effect of enhancing the fixation.
  • the tailbone 20 is provided with an opening 22 near the position of the third spring button 142, and the tailbone 20 is provided with a sealing plate that seals the opening 22.
  • the third spring button 142 can be pressed through the opening 22.
  • the tail cone 20 is provided with a propeller 23, and the propeller 23 is electrically connected with the third motor to provide power for the drone.
  • the fixed frame 21 forms an octagon based on a plurality of cross bars 212, and the fixed frame also includes a plurality of fixed bars, and one of the plurality of fixed bars 213 is connected to one of the pairs in the octagon.
  • One end of some fixed rods 213 is connected to a corner of the octagon, and the other end of some fixed rods 213 is connected to other fixed rods 213.
  • Such fixed rods 213 can increase the stability of the fixed frame 21.
  • the tail cone is provided with a motor and a propeller 23, and the motor is connected with the propeller 23.
  • the motor is arranged in the tailbone, and the propeller 23 is arranged on the other side relative to the section of the tailbone.
  • Propeller 23 is used for providing thrust for UAV.
  • Installation method hold the coccyx 20, align the pin 211 of the fixed frame 21 with the bayonet 141 and push down until the cross bar 212 on the lower side of the fixed frame 21 passes through the spring button 142 and the spring button 142 pops up at the same time, the assembly is completed, and use The sealing plate seals the opening 22 .
  • Disassembly method remove the sealing plate, press the spring button 142 through the opening 22 with one hand, and push up at the same time, the coccyx 20 can be disassembled.
  • Fig. 5 shows the structural schematic view of the fuselage top view of the embodiment of the present invention
  • Fig. 6 shows the structural schematic view of the first wing of the embodiment of the present invention
  • Fig. 7 shows the second wing of the embodiment of the present invention Structural schematic diagram
  • the first wing 31 and the second wing 32 are respectively arranged on both sides of the fuselage
  • the first wing 31 and the second wing 32 are in a symmetrical relationship, which can better control unmanned flight of the machine.
  • a first connecting rod 151 and a first spring button 153 are arranged on one side of the fuselage
  • a second connecting rod 152 and a second spring button 154 are arranged on the other side of the fuselage.
  • the wing 31 is provided with a first groove 311 and a first button hole 312, and the second wing 32 is provided with a second groove 321 and a second button hole 322;
  • the first connecting rod 151 is inserted into the first Groove 311, the first button hole 312 clamps the first spring button 153, the second connecting rod 152 is inserted into the second groove 321, and the second button hole 322 clamps the second Spring button 154;
  • the first connecting rod 151 and the second connecting rod 152 can be the same long straight rod, and the first wing 31 and the second wing 32 are arranged oppositely, so that the same height of the fuselage can be set to keep the unmanned aerial vehicle balance.
  • the first groove 311 of the first wing 31 is inserted into the first connecting rod 151 of the fuselage body 10, and at the same time, the first button hole 312 clamps the first spring button 153 to complete the installation of the first wing 31 , in the same way, complete the installation of the second wing 32; when dismounting, press the first spring button 153, the first spring button 153 can fall off in the first button hole 312, pull out the first wing 31 to complete the disassembly, and simultaneously After that, the disassembly of the second wing 32 is completed.
  • the detachable design of the wings can facilitate the packing of the drone.
  • the first wing 31 is provided with a first aileron 313
  • the first wing 31 is provided with a second aileron 323 .
  • the drone can steer the drone by controlling the ailerons.
  • Fig. 8 shows a schematic structural diagram of an open cabin of an embodiment of the present invention
  • the fuselage includes a fuselage body 10 and a rotor retractable assembly, wherein: the rotor retractable assembly is connected to the fuselage body 10;
  • Fuselage body 10 is provided with the nacelle 11 that places described rotor retractable assembly, and described rotor retractable assembly is arranged in described nacelle 11;
  • Described fuselage body 10 is provided with the cabin door that opens or closes nacelle 11;
  • the rotor adopts a retractable design instead, and when not in use, the rotor is contracted in the fuselage body 10 for easy carrying, and the rotor is expanded to provide lift during flight.
  • FIG. 9 shows a schematic structural view of a fixed-wing unmanned aerial vehicle according to an embodiment of the present invention.
  • the hatch includes a first hatch 111 and a second hatch 112.
  • the first hatch 111 is arranged on one side of the fuselage body 10.
  • the second hatch 112 is arranged on the other side of the fuselage body 10; specifically, the first hatch 111 is hinged on one side of the fuselage body 10, and the second hatch 112 is hinged on the other side of the fuselage body 10 , the hinged way can be hinge, bolt and so on.
  • Fig. 10 shows the schematic structural view of the rotor retractable assembly and the power mechanism of the embodiment of the present invention
  • the rotor retractable assembly includes a stiffness disc 83, a first carbon tube 81 and a second carbon tube 82, the first carbon tube 81 is hinged with the second carbon tube 82 , the rigidity disc 83 is movably connected with the first carbon tube 81 , and the rigidity disc 83 is movably connected with the second carbon tube 82 .
  • a connecting shaft 831 is provided at the center of the stiffness disk 83 , and the connecting shaft 831 is connected to the first carbon tube 81 and the second carbon tube 82 .
  • the rigidity plate 83 is fixedly connected to the fuselage body 10 based on a plurality of rigidity plate fixing parts 832, the middle position of the first carbon tube 81 has a through hole 5125, and the second carbon tube 82 passes through the through hole 5125 of the first carbon tube 81. hole 5125, while the connecting shaft 831 runs through the first carbon tube 81 and the second carbon tube 82, the first carbon tube 81 and the second carbon tube 82 are hinged based on the through hole 5125 and the connecting shaft 831, and the wing retractable assembly is realized based on the hinge Contraction or expansion of carbon tubes.
  • a first rotor 811 and a second rotor 812 are respectively provided at both ends of the first carbon tube 81
  • a third rotor 821 and a fourth rotor 822 are respectively provided at both ends of the second carbon tube 82 .
  • the rotor retractable assembly unfolds the first carbon tube 81 and the second carbon tube 82 when the hatch of the fuselage body 10 is opened, and the rotors on the first carbon tube 81 and the second carbon tube 82 can drive the unmanned aerial vehicle Raised to take off in any terrain.
  • the rotor retractable assembly also includes a first support 84, a second support 85, a third support 86 and a fourth support 87, the first support 84, the second support 85, the The third support member 86 and the fourth support member 87 are sequentially arranged on the lower side of the circumference of the rigidity plate 83 and are slidably connected, the first support member 84 is connected to the first carbon tube 81, and the first support member 84
  • the second support 85 is connected to the second carbon tube 82
  • the third support 86 is connected to the first carbon tube 81
  • the fourth support 87 is connected to the second carbon tube 82 .
  • the first supporting member 84, the second supporting member 85, the third supporting member 86 and the fourth supporting member 87 are in contact with the stiffness plate 83, and can transmit the force generated by the rotor from the carbon tube to the stiffness plate 83, and then to the fuselage.
  • the fuselage body 10 is provided with a power mechanism 90 for controlling the expansion or contraction of the rotor retractable assembly
  • the power mechanism 90 includes a first motor 91, a transmission shaft 92, a V-shaped adapter 93, a second A rotating rod 94 and a second rotating rod 95, one end of the transmission shaft 92 is connected to the first motor 91, the V-shaped adapter 93 is a "V" structure, and one end of the V-shaped adapter 93 has a central connection end, the other end of the V-shaped adapter 93 has a first connecting end 931 and a second connecting end 932, the other end of the transmission shaft 92 is connected to the central connecting end of the V-shaped adapter 93, and the V-shaped adapter
  • the first connecting end 931 of the piece 93 is connected to one end of the first rotating rod 94
  • the second connecting end 932 of the V-shaped adapter 93 is connected to one end of the second rotating rod 95, and the other end of the first rotating rod 94
  • a support member 84 the other end of the second rotating rod 95 is connected to the second support member 85 .
  • the height of the second connecting end 932 is higher than that of the first connecting end 931; therefore, the second rotating rod 95 and the V-shaped adapter
  • the space gap is larger, and the space gap can accommodate the first rotating rod 94.
  • the distance between the first support member 84 and the first connection end 931 is shortened, and the distance between the second support member 85 and the second connection end 932 is shortened. Due to the first rotation lever 94 and the second rotation The role of the rod 95, the first carbon tube 81 and the second carbon tube 82 are opened; when the rotor retractable assembly shrinks, the first motor 91 provides rotational force to the V-shaped adapter 93 through the transmission shaft 92, and the V-shaped adapter 93 reverses 180 degrees, and the first rotating rod 94 and the second rotating rod 95 change from a parallel state to a crossing state. The distance between 85 and the second connecting end 932 becomes longer, and due to the effects of the first rotating rod 94 and the second rotating rod 95, the first carbon tube 81 and the second carbon tube 82 shrink.
  • Figure 11 shows a schematic structural view of the rotor structure of the embodiment of the present invention
  • Figure 12 shows a schematic structural view of the rotor locking mechanism of the embodiment of the present invention
  • Figure 13 shows a schematic structural view of the second motor connection of the embodiment of the present invention
  • the rotor structure includes rotor locking Mechanism 70 and rotor body 60, wherein: the rotor locking mechanism 70 is arranged on the outer circumference of the rotor body 60; the rotor body 60 includes a propeller 62, a vertical motor and a rotating disk 61 installed on the vertical motor, so The rotating disk 61 is driven to rotate by the lifting motor, and the propeller 62 is sleeved on the rotating disk 61 .
  • the rotor locking mechanism 70 is arranged on the outer periphery of the rotor, and the rotor locking mechanism 70 can be directly maintained without disassembling the rotor, which has good convenience;
  • the rotating disc 61 can be replaced by lowering the propeller 62, which avoids the dismantling of complicated rotors and is very convenient.
  • the rotor locking mechanism includes: a brake base 72, a DC motor 73 and a link mechanism, the DC motor 73 and the link mechanism are arranged on the brake base 72, and the DC motor 73 can The extension hook 76 on the drive link mechanism is stuck on the side of the rotating disk 61 .
  • the rotor locking mechanism 70 is arranged on the side of the rotor, and the DC motor 73 can drive the extension hook 76 of the link mechanism to move to the side of the rotating disk 61, so that the extension hook 76 is engaged with the rotating disk 61 and brakes, so as to realize the locking of the rotor. locking.
  • Described link mechanism comprises: rocking arm 74, connecting rod 75 and extension hook 76, and described rocking arm 74 one end is connected with described DC motor 73, and the other end of described rocking arm 74 is connected with described connecting rod 75, so One end of the connecting rod 75 is connected to the rocker arm 74 , and the other end of the connecting rod 75 is connected to the extension hook 76 .
  • the connecting rod 75 includes: a connecting arm and a first connecting shaft and a second connecting shaft located on the connecting arm, the connecting rod 75 is connected to the connecting hole of the rocker arm 74 based on the first connecting shaft, The connecting rod 75 is connected to the connecting hole of the extension hook 76 based on the second connecting shaft.
  • the rocking arm 74 is connected with the DC motor 73 to realize transmission connection, the connecting rod 75 is in transmission connection with the rocking arm 74 based on the first connecting shaft, and the connecting rod 75 is in transmission connection with the extension hook 76 based on the second connecting shaft, then the connecting rod 75, the rocking arm 74 is linked with the extension hook 76, and the DC motor 73 drives the rocking arm 74 to realize the extension or retraction of the extension hook 76.
  • the extension hook 76 includes: a first extension arm 761, a second extension arm 762 and a third extension arm 763, one end of the first extension arm 761 is hinged on the brake base 72, the The other end of the first extension arm 761 is connected to the second extension arm 762; one end of the second extension arm 762 is connected to the first extension arm 761, and the other end of the second extension arm 762 is subjected to the direct current.
  • the drive of the motor 73 can be stuck on the slot; one end of the third extension arm 763 is connected to the arm of the first extension arm 761, and the other end of the third extension arm 763 is connected to the arm of the second extension arm 762. arm.
  • the arm portion of the first extension arm 761 refers to the non-two ends of the first extension arm 761, that is, the middle portion of the first extension arm 761 non-two ends; the arm portion of the second extension arm 762 refers to the non-two ends of the second extension arm 762
  • the position, that is, the second extension arm 762 is not the middle position of the two ends.
  • the first extension arm 761 and the second extension arm 762 intersect to form an acute angle, and the second extension arm 762 forms a straight line or an arc from the connection with the first extension arm 761 to the Card slot extension.
  • a connecting hole on the third extension arm 763 is connected with the second connecting shaft of the connecting rod 75 to realize the connection of the structure;
  • the second extension arm 762 moves in a circle with the hinged structure of the brake base 72 as the center of the circle, and finally the second extension arm 762 is stuck on the side of the rotating disk 61, That is, the DC motor 73 can drive the extension hook 76 on the link mechanism to be stuck on the side of the rotating disk 61 .
  • the brake base 72 includes: a door post 721 and a hinge structure 722, the first extension arm 761 of the extension hook 76 is hinged to the hinge structure 722, and the door post 721 is provided with a through hole through which the extension hook 76 passes.
  • the second extension arm 762 of the extension hook 76 passes through the through hole of the door post 721 .
  • the lower end of the doorpost 721 is hollowed out 725
  • the hinged structure 722 is arranged on the edge of the hollowed out 725
  • the direction of the through hole is toward the hinged structure 722, and the through hole limits the extension hook 76 to prevent the extension hook 76 from swinging and losing its function.
  • the hollow 725 facilitates the installation of the extension hook 76, the second extension arm 762 of the extension hook 76 first passes through the through hole, and the first extension arm 761 is installed on the hinge structure 722, and the extension hook 76 is installed on the brake base 72 .
  • the brake base plate has a motor slot 723 for installing the DC motor 73, and there are two fixed blocks 726 beside the motor slot 723, the DC motor 73 can be fixed on the fixed block 726 by screws, the motor slot 723 limits the DC motor 73, and the fixed block 726 fixes the DC motor 73 on the motor slot by screws;
  • the brake chassis has several columns 724, and several columns 724 are located on both sides of the connecting rod 75, forming a gap between the several columns 724, and the connecting rod 75 is stuck in the gap Limiting is performed on the top, so that the connecting rod 75 moves along the axial direction of the gap to prevent the connecting rod 75 from coming out.
  • the extension hook 76 includes: a first extension arm 761, a second extension arm 762 and a third extension arm 763, one end of the first extension arm 761 is hinged on the brake base 72, and the first extension arm 761
  • the other end of the second extension arm 762 is connected to the second extension arm 762; one end of the second extension arm 762 is connected to the first extension arm 761, and the other end of the second extension arm 762 is driven by the DC motor 73 so that On the slot; one end of the third extension arm 763 is connected to the arm of the first extension arm 761 , and the other end of the third extension arm 763 is connected to the arm of the second extension arm 762 .
  • the arm portion of the first extension arm 761 refers to the non-two ends of the first extension arm 761, that is, the middle portion of the first extension arm 761 non-two ends; the arm portion of the second extension arm 762 refers to the non-two ends of the second extension arm 762
  • the position, that is, the second extension arm 762 is not the middle position of the two ends.
  • the first extension arm 761 and the second extension arm 762 intersect to form an acute angle, and the second extension arm 762 forms a straight line or an arc from the connection with the first extension arm 761 to the Card slot extension.
  • a connecting hole on the third extension arm 763 is connected with the second connecting shaft of the connecting rod 75 to realize the connection of the structure;
  • the second extension arm 762 moves in a circle with the hinged structure of the brake base 72 as the center of the circle, and finally the second extension arm 762 is stuck on the side of the rotating disk 61, That is, the DC motor 73 can drive the extension hook 76 on the link mechanism to be stuck on the side of the rotating disk 61 .
  • the rotor locking mechanism 70 is provided with a top cover 71 matching with the brake base 72, and the top cover 71 is fixed on the brake disc base 72 by screws and bolts.
  • DC motor 73, rocking arm 74, extension hook 76 and connecting rod 75 are arranged between top cover 71 and brake base 72, structures such as DC motor 73, rocking arm 74, extension hook 76 and connecting rod 75 are protected by top cover 71 , reduce the damage rate.
  • the side of the rotating disk 61 has more than one engaging slot, and the DC motor 73 can drive the extension hook 76 on the link mechanism to engage in the engaging slot of the rotating disk 61 .
  • the rotating disk 61 in the present utility model is provided with two grooves 611 matching with the extension hook 76 .
  • the outer edge of the rotating disk 61 guides the groove 611 in a spiral shape.
  • the extension hook 76 guides the groove 611 along the outer edge of the rotating disk 61, and the extension hook 76 is stuck in the groove 611 to complete the braking of the rotor and realize the self-locking of the rotor.
  • the extension hook 76, the brake base 72, the rocker arm 74, the extension hook 76 and the connecting rod 75 are made of carbon fiber material, which has the characteristics of high temperature resistance, friction resistance and corrosion resistance, and the rotor locking mechanism 70 is made of carbon fiber material, which is light in weight and has excellent high temperature resistance, friction resistance and corrosion resistance, and can adapt to various weather environments.
  • Figure 15 shows a schematic structural view of the fuselage body of the embodiment of the present invention
  • Figure 16 shows a schematic structural view of the linkage hook of the embodiment of the present invention
  • Figure 17 shows the structure of the fixing part of the embodiment of the present invention
  • Schematic diagram Fig. 18 shows a schematic structural diagram of the movable part of the embodiment of the present invention.
  • the fuselage also includes a top cover 40, the top cover 40 is provided with a plurality of fixing hooks 41, the upper side of the fuselage body 10 is provided with more than two interlocking hooks 50, and more than one interlocking hooks 50 One end is arranged on the upper side of the fuselage body 10, and more than one interlocking hook 50 is arranged on the other end on the upper side of the fuselage body 10; specifically, the interlocking hook 50 includes a first hook assembly 51 , the second hook assembly 52 and the connecting rod 53, wherein: the two ends of the connecting rod 53 are respectively connected to the first hook assembly 51 and the second hook assembly 52 arranged in the same direction; 53 is provided with a first pin 531 and a second pin 532, one end of the connecting rod 53 is connected to the first hook assembly 51 based on the first pin 531, and the other end of the connecting rod 53 is connected based on the second pin 532
  • the second hook assembly 52; one end of the first latch 531 is provided with a protruding straight rod 5311,
  • the fixed part 512 is connected to the movable part 511 based on a cylindrical pin 5126; the upper end of the movable part 511 is a hook structure 5111; the cylindrical pin 5126 of the fixed part 512 A spring 5123 connected to the movable member 511 is arranged below.
  • the straight rod 5311 has a relatively long length and can extend out of the fuselage, and the extended fuselage part can be manually toggled to control the opening of the first hook assembly and the second hook assembly of the linkage hook; the linkage hook 50 It is composed of two hook assemblies, the first hook assembly 51 and the second hook assembly 52 are linked together through the connecting rod 53, and the straight rod 5311 of the first latch 531 is moved to connect with the first latch 531.
  • the hook component 51 is opened, and the second hook component 52 is also opened based on the linkage of the connecting rod, so that both hooks are opened, and quick disassembly can be realized.
  • the straight rod 5311 is the part where the first pin 531 protrudes from the first hook assembly 51, the length of the straight rod 5311 is 10mm to 35mm, and the length of the straight rod 5311 can be 10mm, 15mm, 20mm, 25mm, 30mm and 35mm Wait, the extended straight rod 5311 is convenient to move by hand to control the whole structure.
  • the fixing member 512 is provided with a first fixing nut 5121 and a second fixing nut 5122, the first fixing nut 5121 is located at the top of the fixing member 512, and the second fixing nut 5122 is located at the bottom of the fixing member 512, so that The fixing effect of the fixing member 512 can be enhanced.
  • the fixed part 512 is provided with a connecting groove 5124 embedded in the movable part 511, and the connecting groove 5124 can play an alignment role when the fixed hook 41 is connected with the movable part 511, so as to prevent deviation from occurring, resulting in failure to achieve the expected fixed effect.
  • the fixing member 512 is provided with a through hole 5125 passing through the connecting groove 5124 .
  • the through hole 5125 reduces the weight of the interlocking hook 50 while ensuring the strength of the structure, and observes the docking of the two hooks; the interlocking hook 50 is fixed on the fuselage through the first fixing nut 5121 and the second fixing nut 5122 .
  • the upper end of the movable part 511 is a hook structure 5111, the lower end of the movable part 511 is connected with the connecting rod 53 based on the latch, the middle of the movable part is movably connected with the fixed part 512 based on the cylindrical pin 5126, and a Spring 5123, one end of the spring 5123 is in contact with the movable part 511, and the other end of the spring 5123 is in contact with the fixed part 512; specifically, the movable part 511 of the first hook assembly 51 is hinged with the connecting rod 53 based on the first latch 531, the second The movable part 511 of the second hook assembly 52 is hinged to the connecting rod 53 based on the second pin 532 .
  • the lower side of the fuselage body 10 is provided with a first landing gear 131 assembly and a second landing gear 132 assembly.
  • the first landing gear 131 assembly and the second landing gear 132 assembly are U-shaped supports, and the first landing gear 131 and the second landing gear 132 are used to support the drone; when the drone is placed on the ground or landed, the first landing gear 131 and the second landing gear 132 are in contact with the ground to protect the unmanned aerial vehicle, preventing the fuselage of the unmanned aerial vehicle from contacting the ground and causing damage.
  • the fuselage is made of carbon fiber material, which takes into account the light weight of the structure while ensuring the strength.
  • the detachable fixed-wing unmanned aerial vehicle provided by the embodiment of the present invention is designed to be detachable, and the wings and the fuselage can be quickly disassembled, which is convenient for packing and transportation, and has good convenience;
  • the fuselage adopts the spring button The form clamps the wing and is connected with the wing through the connecting rod. The lateral force received by the wing is transmitted to the fuselage through the connecting rod to reduce the burden on the wing;
  • the fuselage has a detachable tail cone 20, which is connected with the fuselage It is in the form of a buckle, and is fixed by a spring button.
  • the structure is simple, convenient and quick; the top of the fuselage has a linkage hook 50, and the top cover 40 of the fuselage can be quickly disassembled, which is very convenient for inspection and maintenance of the internal machinery of the fuselage. .

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Abstract

一种可拆卸固定翼无人机，该无人机包括机身、尾椎（20）、第一机翼（31）和第二机翼（32），其中：机身一侧连接着第一机翼（31），机身另一侧连接着第二机翼（32），尾椎（20）与机身的截面处设置有固定框（21），固定框（21）将尾椎（20）和机身连接于一体；机身的截面设置有一个以上卡口（141）和第三弹簧按钮（142）；固定框（21）包括多个横杆（212）和一个以上的第三插销（211），多个横杆（212）组成一个横截面框，一个以上的第三插销（211）固定在横截面框上；一个以上的第三插销（211）中的一个第三插销（211）卡在一个以上的卡口（141）中的一个卡口（141）上，固定框（21）的一横杆（212）内壁卡扣在第三弹簧按钮（142）上。将无人机设计成可拆卸，对机翼以及机身进行快速拆卸，方便装箱运输，具有良好的便利性。

Description

一种可拆卸固定翼无人机 技术领域
本发明涉及无人机领域，具体涉及一种可拆卸固定翼无人机。
背景技术
固定翼无人机具有续航时间长、高空飞行的特点，现已广泛应用在测绘、地质、石油、农林等行业；但固定翼无人机的体型较大，机翼和机身的较长，占用很大的一个空间，运输比较麻烦。
现有对固定翼无人机进行拆卸，拆卸后对固定翼无人机进行运输，但固定翼无人机的结构较为复杂，拆卸的效率低下，十分不便利。
发明内容
本发明的目的在于克服现有技术的不足，本发明提供了一种可拆卸固定翼无人机，将无人机设计成可拆卸，对机翼以及机身进行快速拆卸，方便装箱运输，具有良好的便利性。
为了解决上述技术问题，本发明实施例提供了一种可拆卸固定翼无人机，所述无人机包括机身、尾椎、第一机翼和第二机翼，其中：
所述机身一侧连接着所述第一机翼，所述机身另一侧连接着所述第二机翼，所述尾椎与所述机身的截面处设置有固定框，所述固定框将所述尾椎和机身连接于一体；
所述机身的截面设置有一个以上卡口和第三弹簧按钮；
所述固定框包括多个横杆和一个以上的第三插销，所述多个横杆组成一个横截面框，所述一个以上的第三插销固定在所述横截面框上；所述一个以上的第三插销中的一个第三插销卡在一个以上的卡口中的一个卡口上，所述固定框的一横杆内壁卡扣在所述第三弹簧按钮上；
所述机身本体设置一侧设置有第一连杆和第一弹簧按钮，所述机身本体设置另一侧设置有第二连杆和第二弹簧按钮，所述第一机翼设置有第一凹槽和第一按钮孔，所述第二机翼设置有第二凹槽和第二按钮孔；所述第一连杆插入所述第一凹槽，所述第一按钮孔卡住所述第一弹簧按钮，所述 第二连杆插入所述第二凹槽，所述第二按钮孔卡住所述第二弹簧按钮。
优选的，所述机身包括机身本体和旋翼收放组件，其中：所述旋翼收放组件与所述机身本体连接；
所述机身本体设置有放置所述旋翼收放组件的机舱，所述旋翼收放组件设置在所述机舱内；
所述机身本体设置有打开或关闭机舱的舱门；
所述旋翼收放组件包括刚度盘、第一碳管和第二碳管，所述第一碳管与所述第二碳管铰接，所述刚度盘与所述第一碳管活动连接，所述刚度盘与所述第二碳管活动连接；
所述刚度盘的轴心设置有连接轴，所述连接轴连接着所述第一碳管和第二碳管；
所述第一碳管两端分别设置有第一旋翼和第二旋翼，所述第二碳管两端分别设置有第三旋翼和第四旋翼。
优选的，所述旋翼收放组件还包括第一支撑件、第二支撑件、第三支撑件和第四支撑件，所述第一支撑件、所述第二支撑件、所述第三支撑件和所述第四支撑件按顺序设置在刚度盘的圆周外沿下侧，所述第一支撑件连接着所述第一碳管，所述第二支撑件连接着所述第二碳管，所述第三支撑件连接着所述第一碳管，所述第四支撑件连接着所述第二碳管。
优选的，所述机身设置有控制旋翼收放组件张开或收缩的动力机构，所述动力机构包括第一电机、传动轴、V型转接件、第一转动杆和第二转动杆，所述V型转接件为“V”型结构，V型转接件的一端具有中心连接端，V型转接件的另一端具有第一连接端和第二连接端，所述传动轴的一端连接第一电机，所述传动轴的另一端连接V型转接件的中心连接端，所述V型转接件的第一连接端连接第一转动杆的一端，所述V型转接件的第二连接端连接第二转动杆的一端，第一转动杆的另一端连接第一支撑件，第二转动杆的另一端连接第二支撑件。
优选的，所述第一旋翼、所述第二旋翼、所述第三旋翼和所述第四旋翼为同一种上下对称设置的旋翼结构，所述旋翼结构包括旋翼锁定机构和旋翼本体，其中：
所述旋翼锁定机构设置在旋翼本体的外周上；
所述旋翼本体包括垂起电机以及安装在垂起电机上的转动盘，所述转动盘受所述垂起电机的驱动而转动；
所述旋翼锁定机构包括：刹车底座、直流电机和连杆机构，所述直流电机和所述连杆机构设置在所述刹车底座上，所述直流电机可驱动连杆机构上的延伸勾卡在所述转动盘的侧面。
优选的，所述机身还包括顶盖，所述顶盖设置有多个固定卡钩，所述机身本体上侧设置有两个以上的联动卡钩，一个以上的联动卡钩设置在所述机身本体上侧的一端，一个以上的联动卡钩设置在所述机身本体上侧的另一端，所述顶盖基于固定卡钩插入所述机身的联动卡钩内进行固定连接。
优选的，所述联动卡钩包括第一卡钩组件、第二卡钩组件和连接杆，其中：
所述连接杆的两端分别连接同向设置的所述第一卡钩组件和所述第二卡钩组件；
所述连接杆设置有第一插销和第二插销，所述连接杆的一端基于第一插销连接着所述第一卡钩组件，所述连接杆的另一端基于第二插销连接着所述第二卡钩组件；
所述第一插销的一端设置有凸出来的直杆；
所述第一卡钩组件和所述第二卡钩组件为同一种卡钩机构，所述卡钩机构包括固定件和活动件，所述固定件基于一圆柱销与所述活动件连接；
所述活动件上端是一个卡钩结构；
所述固定件的圆柱销下方设置有与所述活动件连接的弹簧。
优选的，所述第一机翼上设置有第一副翼，所述第一机翼上设置有第二副翼。
优选的，所述机身的下侧设置有第一起落架组件和第二起落架组件。
优选的，所述尾椎设置有螺旋桨。
本发明实施例提供的可拆卸固定翼无人机，将无人机设计成可拆卸，对机翼以及机身进行快速拆卸，方便装箱运输，具有良好的便利性；机身采用弹簧按钮的形式卡住机翼，通过连杆与机翼连接，机翼受到的横向力 通过连杆传递到机身，减轻机翼的负担；机身上具有可拆卸尾椎，尾椎与机身采用插扣的形式，在通过弹簧按钮固定，结构简单，方便快捷；机身的顶端具有联动卡钩，机身的顶盖可快速拆卸，可对机身内部机械进行检查维修，十分方便。
附图说明
为了更清楚地说明本发明实施例或现有技术中的技术方案，下面将对实施例或现有技术描述中所需要使用的附图作简单地介绍，显而易见的，下面描述中的附图仅仅是本发明的一些实施例，对于本领域普通技术人员来讲，在不付出创造性劳动的前提下，还可以根据这些附图获得其它的附图。
图1是本发明实施例的固定翼无人机的结构示意图。
图2是本发明实施例的尾椎的结构示意图。
图3是本发明实施例的机身截面的结构示意图。
图4是本发明实施例的机身本体与固定块的连接结构示意图。
图5是本发明实施例的机身俯视的结构示意图。
图6是本发明实施例的第一机翼的结构示意图。
图7是本发明实施例的第二机翼的结构示意图。
图8是本发明实施例的机舱打开的结构示意图。
图9是本发明实施例的固定翼无人机俯视的结构示意图。
图10是本发明实施例的旋翼收放组件及动力机构的结构示意图。
图11是本发明实施例的旋翼结构的结构示意图。
图12是本发明实施例的旋翼锁定机构的结构示意图。
图13是本发明实施例的第二电机连接的结构示意图。
图14是本发明实施例的刹车底座的结构示意图。
图15是本发明实施例的机身本体剖开的结构示意图。
图16是本发明实施例的联动卡钩的结构示意图。
图17是本发明实施例的固定件的结构示意图。
图18是本发明实施例的活动件的结构示意图。
具体实施方式
下面将结合本发明实施例中的附图，对本发明实施例中的技术方案进行清楚、完整地描述，显然，所描述的实施例仅仅是本发明一部分实施例，而不是全部的实施例。基于本发明中的实施例，本领域普通技术人员在没有作出创造性劳动前提下所获得的所有其它实施例，都属于本发明保护的范围。
实施例
图1示出了本发明实施例的固定翼无人机的结构示意图，所述无人机包括机身、尾椎20、第一机翼31和第二机翼32，其中：所述机身一侧连接着所述第一机翼31，所述机身另一侧连接着所述第二机翼32，所述尾椎20与所述机身的截面处设置有固定框21，所述固定框21将所述尾椎20和机身连接于一体。这里将无人机拆成几个部分，几个部分设计成可拆卸的形式，可通过装箱对无人机进行运输，十分便利。具体的可拆卸结构如下：
图2示出了本发明实施例的尾椎的结构示意图，图3示出了本发明实施例的机身截面的结构示意图，图4示出了本发明实施例的机身本体与固定块的连接结构示意图，所述机身的截面设置有一个以上卡口141和第三弹簧按钮142；所述固定框包括多个横杆212和一个以上的第三插销211，所述多个横杆212组成一个横截面框，所述一个以上的第三插销211固定在所述横截面框上；所述一个以上的第三插销211中的一个第三插销211卡在一个以上的卡口141中的一个卡口141上，所述固定框的一横杆212内壁卡扣在所述弹簧按钮上；所述第三弹簧按钮142用于卡住固定框21。具体的，该固定框21上的第三插销211从上往下插入到卡口141，固定框21下侧的横杆212滑过第三弹簧按钮142，由第三弹簧按钮142弹起并卡住固定框21下侧的横杆212防止固定框21往上移动，卡口141卡住固定框21的第三插销211防止固定框21往其他方向移动，通过第三弹簧按钮142和卡口141的配合固定固定框21于机身本体10上，从而实现尾椎20与机身本体10的固定。
该机身本体10上设置有五个卡口141，其中，机身与尾椎20的截面呈 矩形，机身截面的左侧具有两个卡口141，机身截面的右侧具有两个卡口141，机身截面的上侧具有一个卡口141，机身截面的下侧具有第三弹簧按钮142。机身本体10与尾椎20连接时，固定框21的第三插销211是从上往下插入机身本体10的卡口141里，而第三弹簧按钮142位于机身连接面的下侧，通过卡住固定框21的下侧外框，可防止固定框21脱落。
该固定框21固定设置在尾椎20上，固定方式可以是多种的，比如螺丝、螺栓等。该固定框21上具有五个第三插销211，固定框21的左侧设置两个第三插销211，固定框21的右侧设置两个第三插销211，固定框21上侧设置一个第三插销211，固定框21的下侧的横杆212压过第三弹簧按钮142后第三弹簧按钮142弹起防止固定框21往上移动，，这样的设置方式使尾椎20的四个侧边都进行固定，具有良好的增强固定效果。
尾椎20在靠近第三弹簧按钮142的位置上设置有开孔22，尾椎20设置有密封开孔22的封板，在拆卸时，可通过开孔22按下第三弹簧按钮142，所述尾椎20设置有螺旋桨23，该螺旋桨23与第三电机电性连接，为无人机提供动力。
所述固定框21基于多个横杆212形成八边形，所述固定框还包括有多个固定杆，所述多个固定杆213中的一个固定杆213连接所述八角形内其中一个对角，部分固定杆213一端连接八边形的一个角，部分固定杆213另一端连接其他的固定杆213，这样的固定杆213能增加固定框21的稳定性。
所述尾椎设置有电机和螺旋桨23，所述电机与螺旋桨23连接。所述电机设置在尾椎内，所述螺旋桨23设置在相对于尾椎截面的另一侧。螺旋桨23用于为无人机提供推力。
安装方法：拿着尾椎20使固定框21的插销211对准卡口141向下推，直到固定框21下侧的横杆212穿过弹簧按钮142同时弹簧按钮142弹起，组装完成，并用封板封住开孔22。
拆卸方法：拆下封板，一只手通过开孔22按下弹簧按钮142，同时往上推，即可拆卸尾椎20。
图5示出了本发明实施例的机身俯视的结构示意图，图6示出了本发 明实施例的第一机翼的结构示意图，图7示出了本发明实施例的第二机翼的结构示意图，所述机身两侧分别设置所述第一机翼31和所述第二机翼32，该第一机翼31和第二机翼32为对称关系，能更好的控制无人机的飞行。具体的，所述机身设置一侧设置有第一连杆151和第一弹簧按钮153，所述机身设置另一侧设置有第二连杆152和第二弹簧按钮154，所述第一机翼31设置有第一凹槽311和第一按钮孔312，所述第二机翼32设置有第二凹槽321和第二按钮孔322；所述第一连杆151插入所述第一凹槽311，所述第一按钮孔312卡住所述第一弹簧按钮153，所述第二连杆152插入所述第二凹槽321，所述第二按钮孔322卡住所述第二弹簧按钮154；第一连杆151和第二连杆152可为同一条长直杆，第一机翼31和第二机翼32相对设置，能够设置机身的同一高度来保持无人机的平衡性。第一机翼31的第一凹槽311插入机身本体10的第一连杆151，同时，所述第一按钮孔312卡住所述第一弹簧按钮153，完成第一机翼31的安装，同理，完成第二机翼32的安装；拆卸时，按下第一弹簧按钮153，第一弹簧按钮153即可第一按钮孔312中脱落，拔出第一机翼31完成拆卸，同理，完成第二机翼32的拆卸。机翼的可拆卸设计能方便无人机的装箱。
需要说明的是，所述第一机翼31上设置有第一副翼313，所述第一机翼31上设置有第二副翼323。无人机可通过控制副翼实现对无人机的转向。
图8示出了本发明实施例的机舱打开的结构示意图，所述机身包括机身本体10和旋翼收放组件，其中：所述旋翼收放组件与所述机身本体10连接；所述机身本体10设置有放置所述旋翼收放组件的机舱11，所述旋翼收放组件设置在所述机舱11内；所述机身本体10设置有打开或关闭机舱11的舱门；这里将旋翼改用可收放设计，在不使用时旋翼收缩在机身本体10内方便携带，飞行时将旋翼展开来提供升力。
图9示出了本发明实施例的固定翼无人机俯视的结构示意图，该舱门包括第一舱门111和第二舱门112，第一舱门111设置在机身本体10的一侧，第二舱门112设置在机身本体10的另一侧；具体的，第一舱门111铰接在机身本体10的一侧，第二舱门112铰接在机身本体10的另一侧，铰接方式可为合页、插销等方式。
图10示出了本发明实施例的旋翼收放组件及动力机构的结构示意图，所述旋翼收放组件包括刚度盘83、第一碳管81和第二碳管82，所述第一碳管81与所述第二碳管82铰接，所述刚度盘83与所述第一碳管81活动连接，所述刚度盘83与所述第二碳管82活动连接。所述刚度盘83的轴心设置有连接轴831，所述连接轴831连接着所述第一碳管81和第二碳管82。具体的，该刚度盘83基于多个刚度盘固定件832与机身本体10固定连接，第一碳管81的中间位置具有通孔5125，第二碳管82穿过第一碳管81的通孔5125，同时连接轴831贯穿第一碳管81以及第二碳管82，第一碳管81和第二碳管82基于通孔5125以及连接轴831实现铰接，该翼收放组件基于铰接实现碳管的收缩或者张开。
需要说明的是，所述第一碳管81两端分别设置有第一旋翼811和第二旋翼812，所述第二碳管82两端分别设置有第三旋翼821和第四旋翼822。该旋翼收放组件在机身本体10的舱门打开的状态下展开第一碳管81和第二碳管82，第一碳管81和第二碳管82上的旋翼，能带动无人机升起，可在任何地形下起飞。
所述旋翼收放组件还包括第一支撑件84、第二支撑件85、第三支撑件86和第四支撑件87，所述第一支撑件84、所述第二支撑件85、所述第三支撑件86和所述第四支撑件87按顺序设置在刚度盘83的圆周外沿下侧且滑动连接，所述第一支撑件84连接着所述第一碳管81，所述第二支撑件85连接着所述第二碳管82，所述第三支撑件86连接着所述第一碳管81，所述第四支撑件87连接着所述第二碳管82。第一支撑件84、第二支撑件85、第三支撑件86和第四支撑件87与刚度盘83接触，能将旋翼产生的力从碳管传递到刚度盘83，再传递至机身。
需要说明的是，所述机身本体10设置有控制旋翼收放组件张开或收缩的动力机构90，所述动力机构90包括第一电机91、传动轴92、V型转接件93、第一转动杆94和第二转动杆95，所述传动轴92的一端连接第一电机91，所述V型转接件93为“V”型结构，V型转接件93的一端具有中心连接端，V型转接件93的另一端具有第一连接端931和第二连接端932，所述传动轴92的另一端连接V型转接件93的中心连接端，所述V型转接 件93的第一连接端931连接第一转动杆94的一端，所述V型转接件93的第二连接端932连接第二转动杆95的一端，第一转动杆94的另一端连接第一支撑件84，第二转动杆95的另一端连接第二支撑件85。具体的，该第一连接端931与第二连接端932存在高度差的，第二连接端932的高度比第一连接端931的高度高；因此，第二转动杆95与V型转接器的空间间隙较大，该空间间隙能容纳第一转动杆94。旋翼收放组件张开时，第一电机91通过传动轴92向V型转接件93提供转动力，V型转接件93正转180度，第一转动杆94与第二转动杆95从交叉状态转变成平行状态，在此过程中，第一支撑件84与第一连接端931的距离缩短，第二支撑件85与第二连接端932的距离缩短，由于第一转动杆94和第二转动杆95的作用，第一碳管81和第二碳管82张开；旋翼收放组件收缩时，第一电机91通过传动轴92向V型转接件93提供转动力，V型转接件93反转180度，第一转动杆94与第二转动杆95从平行状态转变成交叉状态，在此过程中，第一支撑件84与第一连接端931的距离变长，第二支撑件85与第二连接端932的距离变长，由于第一转动杆94和第二转动杆95的作用，第一碳管81和第二碳管82收缩。
图11示出了本发明实施例的旋翼结构的结构示意图，图12示出了本发明实施例的旋翼锁定机构的结构示意图，图13示出了本发明实施例的第二电机连接的结构示意图，图14本发明实施例的刹车底座的结构示意图，第一旋翼811、第二旋翼812、第三旋翼821和第四旋翼822为同一种上下对称设置的旋翼结构，所述旋翼结构包括旋翼锁定机构70和旋翼本体60，其中：所述旋翼锁定机构70设置在旋翼本体60的外周上；所述旋翼本体60包括旋桨62、垂起电机以及安装在垂起电机上的转动盘61，所述转动盘61受所述垂起电机的驱动而转动，旋桨62套接在转动盘61的上方。这里将旋翼锁定机构70设置在旋翼的外周上，可直接对旋翼锁定机构70进行维修，无需对旋翼进行拆卸，具有良好的便利性；该转动盘61设置在旋翼本体60的旋桨下，拆下旋桨62即可对转动盘61进行替换，避免了拆卸复杂的旋翼，十分便利。
需要说明的是，所述旋翼锁定机构包括：刹车底座72、直流电机73和 连杆机构，所述直流电机73和所述连杆机构设置在所述刹车底座72上，所述直流电机73可驱动连杆机构上的延伸勾76卡在所述转动盘61的侧面。该旋翼锁定机构70设置在旋翼的侧边，直流电机73可以驱动连杆机构的延伸勾76运动至转动盘61侧面，使得延伸勾76与转动盘61卡接接触并进行刹车，实现对旋翼的锁定。
所述连杆机构包括：摇臂74、连杆75和延伸勾76，所述摇臂74一端连接着所述直流电机73，所述摇臂74的另一端连接着所述连杆75，所述连杆75一端连接在所述摇臂74上，所述连杆75的另一端连接着所述延伸勾76。具体的，所述连杆75包括：连接臂和位于连接臂上的第一连接轴和第二连接轴，所述连杆75基于第一连接轴连接在所述摇臂74的连接孔上，所述连杆75基于第二连接轴连接在所述延伸勾76的连接孔上。该摇臂74与直流电机73连接实现传动连接，连杆75基于第一连接轴与摇臂74传动连接，连杆75基于第二连接轴与延伸勾76传动连接，则连杆75、摇臂74和延伸勾76联动，直流电机73驱动摇臂74即可实现延伸勾76的延伸或回缩。
需要说明的是，所述延伸勾76包括：第一延伸臂761、第二延伸臂762和第三延伸臂763，所述第一延伸臂761的一端铰接在所述刹车底座72上，所述第一延伸臂761的另一端连接所述第二延伸臂762；所述第二延伸臂762的一端连接着所述第一延伸臂761，所述第二延伸臂762的另一端受所述直流电机73驱动可卡在所述卡槽上；所述第三延伸臂763的一端连接着第一延伸臂761的臂部，所述第三延伸臂763的另一端连接着第二延伸臂762的臂部。第一延伸臂761的臂部指第一延伸臂761的非两端的部位，即第一延伸臂761非两端的中间部位；第二延伸臂762的臂部指第二延伸臂762的非两端的部位，即第二延伸臂762非两端的中间部位。具体的，所述第一延伸臂761和所述第二延伸臂762交叉形成一锐角，所述第二延伸臂762从与所述第一延伸臂761的连接处呈直线或者弧线向所述卡槽延伸。第三延伸臂763上一连接孔与连杆75的第二连接轴连接，实现结构的连接；直流电机73驱动连杆机构，动力从摇臂74传动至连杆74，再从连杆75传动至延伸勾76，由于第一延伸臂761与刹车底座72铰接，则第二延伸臂 762以刹车底座72的铰接结构为圆心做圆周运动，最终第二延伸臂762卡在转动盘61的侧面，即直流电机73可驱动连杆机构上的延伸勾76卡在所述转动盘61的侧面。
所述刹车底座72包括：门柱721和铰接结构722，所述延伸勾76的第一延伸臂761与所述铰接结构722铰接，所述门柱721上设置有延伸勾76通过的通孔，所述延伸勾76的第二延伸臂762穿过所述门柱721的通孔。具体的，该门柱721下端镂空725，该铰接结构722设置在镂空725的边缘，该通孔的方向向着铰接结构722，该通孔对延伸勾76进行限位，防止延伸勾76摆动失去功能；该镂空725方便延伸勾76的安装，该延伸勾76的第二延伸臂762先穿过通孔，第一延伸臂761再安装在铰接结构722，则完成延伸勾76在刹车底座72的安装。
刹车底板具有安装直流电机73的电机槽723，电机槽723的旁边具有两个固定块726，直流电机73可通过螺丝固定在固定块726上，电机槽723对直流电机73进行限位，固定块726通过螺丝将直流电机73固定在电机槽上；该刹车底盘具有几个立柱724，几个立柱724位在连杆75的两侧，几个立柱724间形成一个间隙，连杆75卡在间隙上进行限位，使连杆75沿着间隙的轴线方向移动防止连杆75脱离出来。
所述延伸勾76包括：第一延伸臂761、第二延伸臂762和第三延伸臂763，所述第一延伸臂761的一端铰接在所述刹车底座72上，所述第一延伸臂761的另一端连接所述第二延伸臂762；所述第二延伸臂762的一端连接着所述第一延伸臂761，所述第二延伸臂762的另一端受所述直流电机73驱动可卡在所述卡槽上；所述第三延伸臂763的一端连接着第一延伸臂761的臂部，所述第三延伸臂763的另一端连接着第二延伸臂762的臂部。第一延伸臂761的臂部指第一延伸臂761的非两端的部位，即第一延伸臂761非两端的中间部位；第二延伸臂762的臂部指第二延伸臂762的非两端的部位，即第二延伸臂762非两端的中间部位。具体的，所述第一延伸臂761和所述第二延伸臂762交叉形成一锐角，所述第二延伸臂762从与所述第一延伸臂761的连接处呈直线或者弧线向所述卡槽延伸。第三延伸臂763上一连接孔与连杆75的第二连接轴连接，实现结构的连接；直流电机73 驱动连杆机构，动力从摇臂74传动至连杆74，再从连杆75传动至延伸勾76，由于第一延伸臂761与刹车底座72铰接，则第二延伸臂762以刹车底座72的铰接结构为圆心做圆周运动，最终第二延伸臂762卡在转动盘61的侧面，即直流电机73可驱动连杆机构上的延伸勾76卡在所述转动盘61的侧面。
所述旋翼锁定机构70设置有配合所述刹车底座72的顶盖71，顶盖71固定在刹车盘底座72上，固定方式可以是螺丝和螺栓等。直流电机73、摇臂74、延伸勾76和连杆75设置在顶盖71和刹车底座72之间，由顶盖71保护着直流电机73、摇臂74、延伸勾76和连杆75等结构，降低损坏率。需要说明的是，所述转动盘61的侧面具有一个以上的卡槽，所述直流电机73可驱动连杆机构上的延伸勾76卡在所述转动盘61的卡槽上。本实用新型中的所述转动盘61设置有两个配合延伸勾76的凹槽611。具体的，所述转动盘61的外沿呈螺旋状导向所述凹槽611。延伸勾76伸出时，延伸勾76沿着转动盘61的外沿导向凹槽611，该延伸勾76卡在凹槽611完成对旋翼的刹车，实现旋翼的自锁。
所述延伸勾76、所述刹车底座72、所述摇臂74、所述延伸勾76和所述连杆75采用碳纤维材料，碳纤维材料具有耐高温、抗摩擦及耐腐蚀等特性，旋翼锁定机构70采用碳纤维材料，重量较轻的同时具有优良的耐高温、抗摩擦及耐腐蚀，能适应多种天气环境。
图15示出了本发明实施例的机身本体剖开的结构示意图，图16示出了本发明实施例的联动卡钩的结构示意图，图17示出了本发明实施例的固定件的结构示意图，图18示出了本发明实施例的活动件的结构示意图。所述机身还包括顶盖40，所述顶盖40设置有多个固定卡钩41，所述机身本体10上侧设置有两个以上的联动卡钩50，一个以上的联动卡钩50设置在所述机身本体10上侧的一端，一个以上的联动卡钩50设置在所述机身本体10上侧的另一端；具体的，所述联动卡钩50包括第一卡钩组件51、第二卡钩组件52和连接杆53，其中：所述连接杆53的两端分别连接同向设置的所述第一卡钩组件51和所述第二卡钩组件52；所述连接杆53设置有第一插销531和第二插销532，所述连接杆53的一端基于第一插销531连 接着所述第一卡钩组件51，所述连接杆53的另一端基于第二插销532连接着所述第二卡钩组件52；所述第一插销531的一端设置有凸出来的直杆5311，该直杆5311具有较长的长度，可伸出机身，且伸出机身部位可手拨动来控制联动卡钩的第一卡钩组件和第二卡钩组件打开；所述第一卡钩组件51和所述第二卡钩组件52为同一种卡钩机构，所述卡钩机构包括固定件512和活动件511，所述固定件512基于一圆柱销5126与所述活动件511连接；所述活动件511上端是一个卡钩结构5111；所述固定件512的圆柱销5126下方设置有与所述活动件511连接的弹簧5123。该直杆5311具有较长的长度，可伸出机身，且伸出机身部位可手拨动来控制联动卡钩的第一卡钩组件和第二卡钩组件打开；该联动卡钩50是由两个卡钩组件组成，第一卡钩组件51和第二卡钩组件52通过连接杆53联动在一起，拨动第一插销531的直杆5311与第一插销531连接的第一卡钩组件51张开，第二卡钩组件52基于连接杆的联动也张开，这样两个钩子都张开，即可实现快速拆卸。
该直杆5311为第一插销531伸出第一卡钩组件51的部分，所述直杆5311的长度为10mm至35mm，直杆5311的长度可为10mm、15mm、20mm、25mm、30mm和35mm等等，伸出的直杆5311方便用手拨动来控制整个结构活动。
需要说明的是，所述固定件512设置有第一固定螺母5121和第二固定螺母5122，第一固定螺母5121位于固定件512的顶部，第二固定螺母5122位于固定件512的底部，这样设置能增强固定件512的固定效果。所述固定件512设置有嵌入活动件511的连接凹槽5124，连接凹槽5124在固定卡钩41与活动件511连接时能起到对正的作用，防止发生偏移，导致无法达到预期的固定效果。具体的，所述固定件512设置有贯穿连接凹槽5124的通孔5125。该通孔5125在保证结构的强度的同时减轻联动卡钩50的重量，以及观察两个卡钩对接情况；联动卡钩50通过第一固定螺母5121和第二固定螺母5122固定在机身上。
该活动件511的上端为卡钩结构5111，活动件511的下端基于插销与连接杆53连接，该活动件的中间基于圆柱销5126与固定件512活动连接， 在圆柱销5126的下方设置有一个弹簧5123，该弹簧5123一端与活动件511接触，该弹簧5123的另一端与固定件512接触；具体的，第一卡钩组件51的活动件511基于第一插销531与连接杆53铰接，第二卡钩组件52的活动件511基于第二插销532与连接杆53铰接。
所述机身本体10下侧设置有第一起落架131组件和第二起落架132组件。该第一起落架131组件和第二起落架132组件为U形支撑，第一起落架131和第二起落架132用于对无人机进行支撑；在无人机放置地面或者降落时，第一起落架131以及第二起落架132与地面接触，对无人机进行保护，避免无人机的机身与地面接触，造成损坏。
该机身采用碳纤维材料制成，在保证强度的同时兼顾了结构的轻量化。
本发明实施例提供的可拆卸固定翼无人机，将无人机设计成可拆卸，对机翼以及机身进行快速拆卸，方便装箱运输，具有良好的便利性；机身采用弹簧按钮的形式卡住机翼，通过连杆与机翼连接，机翼受到的横向力通过连杆传递到机身，减轻机翼的负担；机身上具有可拆卸尾椎20，尾椎20与机身采用插扣的形式，在通过弹簧按钮固定，结构简单，方便快捷；机身的顶端具有联动卡钩50，机身的顶盖40可快速拆卸，可对机身内部机械进行检查维修，十分方便。
另外，以上对本发明实施例进行了详细介绍，本文中应采用了具体个例对本发明的原理及实施方式进行了阐述，以上实施例的说明只是用于帮助理解本发明的方法及其核心思想；同时，对于本领域的一般技术人员，依据本发明的思想，在具体实施方式及应用范围上均会有改变之处，综上所述，本说明书内容不应理解为对本发明的限制。

Claims (10)

  1. 一种可拆卸固定翼无人机，其特征在于，所述无人机包括机身、尾椎、第一机翼和第二机翼，其中：
    所述机身一侧连接着所述第一机翼，所述机身另一侧连接着所述第二机翼，所述尾椎与所述机身的截面处设置有固定框，所述固定框将所述尾椎和机身连接于一体；
    所述机身的截面设置有一个以上卡口和第三弹簧按钮；
    所述固定框包括多个横杆和一个以上的第三插销，所述多个横杆组成一个横截面框，所述一个以上的第三插销固定在所述横截面框上；所述一个以上的第三插销中的一个第三插销卡在一个以上的卡口中的一个卡口上，所述固定框的一横杆内壁卡扣在所述第三弹簧按钮上；
    所述机身本体设置一侧设置有第一连杆和第一弹簧按钮，所述机身本体设置另一侧设置有第二连杆和第二弹簧按钮，所述第一机翼设置有第一凹槽和第一按钮孔，所述第二机翼设置有第二凹槽和第二按钮孔；所述第一连杆插入所述第一凹槽，所述第一按钮孔卡住所述第一弹簧按钮，所述第二连杆插入所述第二凹槽，所述第二按钮孔卡住所述第二弹簧按钮。
  2. 根据权利要求1所述的无人机，其特征在于，所述机身包括机身本体和旋翼收放组件，其中：所述旋翼收放组件与所述机身本体连接；
    所述机身本体设置有放置所述旋翼收放组件的机舱，所述旋翼收放组件设置在所述机舱内；
    所述机身本体设置有打开或关闭机舱的舱门；
    所述旋翼收放组件包括刚度盘、第一碳管和第二碳管，所述第一碳管与所述第二碳管铰接，所述刚度盘与所述第一碳管活动连接，所述刚度盘与所述第二碳管活动连接；
    所述刚度盘的轴心设置有连接轴，所述连接轴连接着所述第一碳管和第二碳管；
    所述第一碳管两端分别设置有第一旋翼和第二旋翼，所述第二碳管两端分别设置有第三旋翼和第四旋翼。
  3. 根据权利要求2所述的无人机，其特征在于，所述旋翼收放组件还 包括第一支撑件、第二支撑件、第三支撑件和第四支撑件，所述第一支撑件、所述第二支撑件、所述第三支撑件和所述第四支撑件按顺序设置在刚度盘的圆周外沿下侧，所述第一支撑件连接着所述第一碳管，所述第二支撑件连接着所述第二碳管，所述第三支撑件连接着所述第一碳管，所述第四支撑件连接着所述第二碳管。
  4. 根据权利要求3所述的无人机，其特征在于，所述机身设置有控制旋翼收放组件张开或收缩的动力机构，所述动力机构包括第一电机、传动轴、V型转接件、第一转动杆和第二转动杆，所述V型转接件为“V”型结构，V型转接件的一端具有中心连接端，V型转接件的另一端具有第一连接端和第二连接端，所述传动轴的一端连接第一电机，所述传动轴的另一端连接V型转接件的中心连接端，所述V型转接件的第一连接端连接第一转动杆的一端，所述V型转接件的第二连接端连接第二转动杆的一端，第一转动杆的另一端连接第一支撑件，第二转动杆的另一端连接第二支撑件。
  5. 根据权利要求2所述的无人机，其特征在于，所述第一旋翼、所述第二旋翼、所述第三旋翼和所述第四旋翼为同一种上下对称设置的旋翼结构，所述旋翼结构包括旋翼锁定机构和旋翼本体，其中：
    所述旋翼锁定机构设置在旋翼本体的外周上；
    所述旋翼本体包括垂起电机以及安装在垂起电机上的转动盘，所述转动盘受所述垂起电机的驱动而转动；
    所述旋翼锁定机构包括：刹车底座、直流电机和连杆机构，所述直流电机和所述连杆机构设置在所述刹车底座上，所述直流电机可驱动连杆机构上的延伸勾卡在所述转动盘的侧面。
  6. 根据权利要求2所述的无人机，其特征在于，所述机身还包括顶盖，所述顶盖设置有多个固定卡钩，所述机身本体上侧设置有两个以上的联动卡钩，一个以上的联动卡钩设置在所述机身本体上侧的一端，一个以上的联动卡钩设置在所述机身本体上侧的另一端，所述顶盖基于固定卡钩插入所述机身的联动卡钩内进行固定连接。
  7. 根据权利要6所述的无人机，其特征在于，所述联动卡钩包括第一卡钩组件、第二卡钩组件和连接杆，其中：
    所述连接杆的两端分别连接同向设置的所述第一卡钩组件和所述第二卡钩组件；
    所述连接杆设置有第一插销和第二插销，所述连接杆的一端基于第一插销连接着所述第一卡钩组件，所述连接杆的另一端基于第二插销连接着所述第二卡钩组件；
    所述第一插销的一端设置有凸出来的直杆；
    所述第一卡钩组件和所述第二卡钩组件为同一种卡钩机构，所述卡钩机构包括固定件和活动件，所述固定件基于一圆柱销与所述活动件连接；
    所述活动件上端是一个卡钩结构；
    所述固定件的圆柱销下方设置有与所述活动件连接的弹簧。
  8. 根据权利要求1所述的无人机，其特征在于，所述第一机翼上设置有第一副翼，所述第一机翼上设置有第二副翼。
  9. 根据权利要求1所述的无人机，其特征在于，所述机身的下侧设置有第一起落架组件和第二起落架组件。
  10. 根据权利要求1所述的无人机，其特征在于，所述尾椎设置有螺旋桨。
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CN114013625A (zh) * 2021-11-17 2022-02-08 中山福昆航空科技有限公司 一种可拆卸固定翼无人机

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