CN113955092B - Vertical take-off and landing fixed wing unmanned aerial vehicle with modularized duck-type layout - Google Patents
Vertical take-off and landing fixed wing unmanned aerial vehicle with modularized duck-type layout Download PDFInfo
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- CN113955092B CN113955092B CN202111454185.XA CN202111454185A CN113955092B CN 113955092 B CN113955092 B CN 113955092B CN 202111454185 A CN202111454185 A CN 202111454185A CN 113955092 B CN113955092 B CN 113955092B
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- 230000007246 mechanism Effects 0.000 claims abstract description 34
- 241000272525 Anas platyrhynchos Species 0.000 claims abstract description 28
- 229910052751 metal Inorganic materials 0.000 claims description 18
- 239000002184 metal Substances 0.000 claims description 18
- 229910052799 carbon Inorganic materials 0.000 claims description 7
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 claims description 6
- 230000000149 penetrating effect Effects 0.000 claims description 6
- 238000000034 method Methods 0.000 description 16
- 230000008569 process Effects 0.000 description 16
- 239000000295 fuel oil Substances 0.000 description 6
- 238000012423 maintenance Methods 0.000 description 5
- 230000003014 reinforcing effect Effects 0.000 description 5
- 238000009434 installation Methods 0.000 description 4
- 239000003921 oil Substances 0.000 description 4
- 230000002035 prolonged effect Effects 0.000 description 4
- 230000000694 effects Effects 0.000 description 2
- WHXSMMKQMYFTQS-UHFFFAOYSA-N Lithium Chemical compound [Li] WHXSMMKQMYFTQS-UHFFFAOYSA-N 0.000 description 1
- 230000008859 change Effects 0.000 description 1
- 238000004891 communication Methods 0.000 description 1
- 238000010276 construction Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 239000002828 fuel tank Substances 0.000 description 1
- 229910052744 lithium Inorganic materials 0.000 description 1
- 238000004904 shortening Methods 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
- 230000009466 transformation Effects 0.000 description 1
- 238000000844 transformation Methods 0.000 description 1
Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/04—Helicopters
- B64C27/08—Helicopters with two or more rotors
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C29/00—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft
- B64C29/02—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft having its flight directional axis vertical when grounded
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/38—Adjustment of complete wings or parts thereof
- B64C3/56—Folding or collapsing to reduce overall dimensions of aircraft
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C39/00—Aircraft not otherwise provided for
- B64C39/12—Canard-type aircraft
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D27/00—Arrangement or mounting of power plant in aircraft; Aircraft characterised thereby
- B64D27/02—Aircraft characterised by the type or position of power plant
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- B64D27/026—
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U10/00—Type of UAV
- B64U10/10—Rotorcrafts
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- 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
- B64U70/00—Launching, take-off or landing arrangements
- B64U70/80—Vertical take-off or landing, e.g. using rockets
Abstract
The invention discloses a modularized duck-type layout vertical take-off and landing fixed-wing unmanned aerial vehicle, which comprises a fuselage, a nose and wings, wherein the wings comprise middle wing sections, two ends of each middle wing section are respectively connected with outer wing sections, the bottom of the fuselage close to the rear end of the fuselage is connected with the center position of the top of each middle wing section, and a wing body driving mechanism for driving the outer wing sections to fold or unfold is arranged at the joint of each middle wing section and each outer wing section; a tail pushing engine is arranged at the end part of the rear end of the machine body, and a tail pushing propeller is arranged; the nose is arranged at the front end of the machine body, the two sides of the nose are respectively provided with a duck wing, the two sides of the machine body are respectively provided with a vertical rod, the vertical rods are connected with the duck wing and the middle wing section, and a plurality of rotor wing power systems are symmetrically arranged on the two vertical rods; the front-mounted duck wing layout is adopted, so that the lift-drag ratio and the aerodynamic efficiency of the unmanned aerial vehicle are improved, and the unmanned aerial vehicle has good maneuverability; the wings can be folded or unfolded, so that the area requirement on the landing site is reduced, and the vertical landing can be performed on the ground or a deck with smaller site.
Description
Technical Field
The invention relates to a vertical take-off and landing fixed wing unmanned aerial vehicle with a modularized duck-shaped layout, and belongs to the technical field of unmanned aerial vehicles.
Background
The vertical take-off and landing fixed wing unmanned aerial vehicle integrates the advantages of multiple rotors and fixed wings, has the advantages of large load, long endurance, high speed and capability of taking off and landing vertically, and is widely applied to the field of unmanned aerial vehicles at present; the following problems exist in the traditional vertical take-off and landing fixed wing unmanned aerial vehicle:
1. the single wing layout is adopted, the lift-drag ratio is low, and the pneumatic efficiency is still to be improved;
2. the volume is large, the design is integrated, the transportation and the use are not convenient, and the structure is not detachable;
3. the vertical take-off and landing rotor wing system generally adopts a four-rotor wing layout, so that the strong wind interference resistance is poor, and the reliability of the aircraft is poor;
4. the fixed wing has larger size and has large area requirement on the landing site;
5. a pure electric power system is usually adopted, and is limited by the energy density of a lithium battery, so that the voyage and the voyage are not long;
meanwhile, in order to improve the endurance performance and increase the air stagnation capacity of an airplane, a modern unmanned aerial vehicle mostly adopts a wing with a large aspect ratio, the large-span wing brings out higher requirements on the space size of the landing site of the unmanned aerial vehicle, and sometimes the landing can not be completed even in a specific site.
Disclosure of Invention
The invention aims at solving the problems in the prior art and provides a vertical take-off and landing fixed wing unmanned aerial vehicle with a modularized duck-type layout, wherein the leading duck-type wing layout is adopted, so that the lift-drag ratio and aerodynamic efficiency of the unmanned aerial vehicle are improved, and the unmanned aerial vehicle has better maneuverability; the modularized design is adopted, so that the whole detachability of the unmanned aerial vehicle is realized, meanwhile, the replaceability of each module of the unmanned aerial vehicle is realized, and the daily maintenance, storage and transportation are facilitated; the fixed wing of the unmanned aerial vehicle can be folded or unfolded, so that the area requirement on a landing site is reduced, and the unmanned aerial vehicle can vertically land on the ground or a deck with smaller site; strong wind interference resistance, and also improves the range and the endurance of the vertical take-off and landing fixed-wing unmanned aerial vehicle.
In order to achieve the above object, the present invention adopts the following technical scheme:
the vertical take-off and landing fixed-wing unmanned aerial vehicle comprises a fuselage, a nose and wings, wherein the wings comprise middle wing sections, two ends of each middle wing section are respectively connected with outer wing sections, the bottom of the fuselage, which is close to the rear end of the fuselage, is connected with the center position of the top of each middle wing section, and a wing body driving mechanism is arranged at the joint of each middle wing section and each outer wing section and is used for driving the outer wing sections to fold or unfold; a tail pushing engine is arranged at the end part of the rear end of the machine body, and a tail pushing propeller is arranged on an output shaft of the tail pushing engine; the nose is arranged at the front end of the machine body, the two sides of the nose are respectively provided with a duck wing, the two sides of the machine body are respectively provided with a vertical lifting rod, the front end of the vertical lifting rod is connected with the duck wing, the top of the vertical lifting rod close to the rear end of the vertical lifting rod is connected with the middle wing section, and a plurality of rotor wing power systems are symmetrically arranged on the two vertical lifting rods; the bottom of the vertical rod close to the rear end of the vertical rod is connected with a vertical tail, and the bottom of the vertical rod close to the front end of the vertical rod is connected with a landing gear.
As a further preferred aspect of the present invention, three rotor power systems are provided at the top of each of the lifting bars, wherein two rotor power systems are provided at the top of the lifting bar between the middle wing section and the duck wing, and the other rotor power system is provided at the top of the rear end of the lifting bar; six rotor power systems are arranged on the vertical rods at two sides of the fuselage, the rotor power systems arranged on the two vertical rods are symmetrically arranged, and the wings, the vertical rods and the fuselage adopt lifting structures, so that the structural reliability is improved; compared with the traditional four-rotor mechanism layout, the six-rotor mechanism layout is adopted, so that the unmanned aerial vehicle has stronger stability under the strong wind condition, can still normally land when a certain rotor power system fails, and the reliability of the unmanned aerial vehicle is greatly improved.
As a further preferred aspect of the present invention, the rotor power system is an electric rotor power system, the tail-pushing engine is a fuel oil type tail-pushing engine, an oil tank and a battery pack for supplying power are arranged in the machine body, and an oil tank cover is arranged at the top of the machine body; the power system of the unmanned aerial vehicle adopts oil-electricity hybrid power, adopts different power systems under different flight states, adopts an electric rotor power system during the vertical take-off and landing process, and adopts a fuel oil type tail pushing engine power system during the cruise flight process of the fixed wing, thereby greatly improving the range and the endurance of the vertical take-off and landing fixed wing unmanned aerial vehicle.
As a further preferred mode of the invention, a plurality of first through holes penetrating through the middle wing section along the thickness direction of the middle wing section are formed in the middle wing section, a plurality of second through holes correspondingly matched with the first through holes are formed in the bottom of the machine body, and the machine body and the middle wing section are detachably connected through a bolt and nut assembly penetrating through the corresponding second through holes and the first through holes; a rear machine body cover is arranged at the top of the machine body corresponding to the second through holes; the rear fuselage cover at the top of the fuselage is opened, and the bolt and nut assembly can be operated, so that the fuselage and the middle wing section can be quickly disassembled and assembled.
As a further preferable mode of the invention, the outer side surfaces of the middle wing section main beam and the middle wing section auxiliary beam are respectively provided with a middle wing metal piece, the top of the vertical rod is provided with a self-locking nut correspondingly matched with the two middle wing metal pieces, and the middle wing metal pieces are detachably connected with the self-locking nuts through bolts; an opening through which a bolt passes is formed in the top skin of the middle wing section corresponding to the middle wing metal piece; the quick assembly disassembly is realized between the middle wing section and the vertical rod.
As a further preferable mode of the invention, a sleeve is arranged at one end of the duck wing far away from the machine head, a carbon tube is arranged at the front end of the hanging rod, and the carbon tube at the front end of the hanging rod is inserted into the sleeve of the duck wing and is detachably connected with the duck wing through a plurality of screws; realizing the quick disassembly and assembly between the vertical rod and the duck wing; the front end face of the machine body is provided with a machine body end plate, the top of the machine body close to the front end of the machine body is provided with a front machine body cover, the connecting end of the machine head and the machine body is provided with a machine head end plate, and the machine body end plate and the machine head end plate are detachably connected through a plurality of screws; the front machine body cover at the top of the machine body is opened, and a plurality of screws for connecting the machine body end plate and the machine head end plate can be operated, so that the machine body and the machine head can be quickly disassembled and assembled; the duck wing and the machine head adopt an integrated forming structure.
As a further preferable mode of the invention, the vertical tail and the landing gear are detachably connected with the vertical rod through a plurality of screws respectively, and rubber pads are arranged at the bottom ends of the vertical tail and the landing gear respectively; quick assembly disassembly is convenient for carry out between vertical fin and undercarriage and the vertical pole, and two vertical fin can regard as the undercarriage to use moreover, have avoided arranging extra weight and the air resistance of undercarriage alone.
As a further preferred mode of the invention, the wing body driving mechanism comprises a driving rotation mechanism and a driven rotation mechanism, the driving rotation mechanism comprises a middle wing tab of the main beam and an outer wing tab of the main beam, the middle wing tab of the main beam is arranged on the inner side surface of the main beam of the middle wing section, the outer wing tab of the main beam is arranged on the inner side surface of the main beam of the outer wing section, the outer wing tab of the main beam is rotationally connected with the top of the middle wing tab of the main beam through a hinge, an arc-shaped sliding limiting hole is formed in the bottom of the middle wing tab of the main beam, a linear steering engine is arranged between the middle wing tab of the main beam and the outer wing tab of the main beam, the tail end of the linear steering engine is rotationally connected with the top of the outer wing tab of the main beam, and the end part of an actuating rod of the linear steering engine is rotationally connected in the sliding limiting hole; the driven rotating mechanism comprises an auxiliary beam middle wing tab and an auxiliary beam outer wing tab, wherein the auxiliary beam middle wing tab is arranged on the inner side surface of the middle wing section auxiliary beam, the auxiliary beam outer wing tab is arranged on the inner side surface of the outer wing section auxiliary beam, and the auxiliary beam outer wing tab is rotationally connected with the top of the auxiliary beam middle wing tab through a hinge.
In the outer wing section unfolding state, the end part of the actuating rod of the linear steering engine is positioned at the initial position of the arc-shaped limiting stroke of the sliding limiting hole, and the exposed length of the actuating rod of the linear steering engine is in the shortest state; when the outer wing section is required to be folded, the actuating rod is driven to stretch, the outer wing section starts to be overturned and folded upwards by the thrust of the tail end of the linear steering engine along with the gradual stretching of the actuating rod of the linear steering engine, the end part of the actuating rod of the linear steering engine slides along the arc-shaped limiting stroke of the sliding limiting hole, when the exposed length of the actuating rod of the linear steering engine extends out of the opening reaches the longest state, the angle of the upward overturning and folding of the outer wing section reaches the maximum value, and at the moment, the end part of the actuating rod of the linear steering engine slides from the initial position of the arc-shaped limiting stroke of the sliding limiting hole to the final position of the arc-shaped limiting stroke of the sliding limiting hole, so that the outer wing section is in a folded state; the outer wing segments of the vertical take-off and landing fixed wing unmanned aerial vehicle wings are parked in a folded state, so that the size of the machine position or the warehouse space required by the unmanned aerial vehicle can be reduced; in addition, the fatigue problem of the wing structure in the ground carrying process is relieved, the service life is prolonged, and the disassembly and the installation of the wing structure and adjacent parts are facilitated; in the process of taking off and landing of the outer wing section of the vertical take-off and landing fixed-wing unmanned aerial vehicle wing in a folded state, the normal taking-off and landing under the condition of insufficient space of the take-off and landing site can be realized, and the related geometric index requirements of the carrier-based aircraft can be realized more easily; the vertical take-off and landing fixed wing unmanned aerial vehicle has larger aspect ratio, and meets the related limit requirements of airports while improving the endurance performance.
As a further preferred mode of the invention, the end part of the middle wing tab of the main beam, which faces the outer wing tab of the main beam, is provided with two side walls, the outer wing tab of the main beam is rotationally connected between the two side walls at the top of the middle wing tab of the main beam through a hinge, the two side walls at the bottom of the middle wing tab of the main beam are respectively provided with arc-shaped sliding limiting holes which correspond to each other, and the end part of the actuating rod of the linear steering engine is positioned between the two side walls and is in sliding connection with the two sliding limiting holes; the device is used for improving the sliding connection effect of the end part of the actuating rod of the linear steering engine in the sliding limiting hole and guaranteeing the structural stress uniformity of the wing lugs in the main beam.
As a further preferred aspect of the present invention, the end of the actuating rod of the linear steering engine is provided with a pipe body, the axis of the pipe body is perpendicular to the axis of the actuating rod, the pipe body is located between the sliding limiting holes of the two side walls, the length of the pipe body is smaller than the distance between the two side walls, a rotating shaft is slidably arranged in the sliding limiting holes of the two side walls, the rotating shaft movably passes through the pipe body at the end of the actuating rod of the linear steering engine, one end of the rotating shaft is provided with a limiting plate, the end surface of the other end of the rotating shaft is provided with a threaded hole, a limiting bolt is in threaded connection with the threaded hole, a locking plate is movably sleeved on the screw rod of the limiting bolt, and the limiting plate and the locking plate are respectively located on the outer side surfaces of the two side walls of the wing lugs in the main beam; make the actuating lever tip of sharp steering wheel pass through pivot sliding connection in sliding limiting hole, when the wearing and tearing appear in the pivot, can in time change the pivot for guarantee the normal work of sharp steering wheel, simultaneously, can also make the actuating lever tip of sharp steering wheel break away from between two lateral walls when daily maintenance.
The invention has the advantages that:
the leading duck type wing layout is adopted, so that the lift-drag ratio and the aerodynamic efficiency of the unmanned aerial vehicle are improved, and the unmanned aerial vehicle has good maneuverability; the modularized design is adopted, so that the whole detachability of the unmanned aerial vehicle is realized, meanwhile, the replaceability of each module of the unmanned aerial vehicle is realized, and the daily maintenance, storage and transportation are facilitated; six rotor power systems are arranged on the vertical rods at two sides of the fuselage, the rotor power systems arranged on the two vertical rods are symmetrically arranged, and the wings, the vertical rods and the fuselage adopt lifting structures, so that the structural reliability is improved; compared with the traditional four-rotor mechanism layout, the six-rotor mechanism layout is adopted, so that the unmanned aerial vehicle has stronger stability under the strong wind condition, can still normally land when a certain rotor power system fails, the reliability of the unmanned aerial vehicle is greatly improved, and the anti-strong wind disturbance capability is strong; the power system of the unmanned aerial vehicle adopts oil-electricity hybrid power, adopts different power systems under different flight states, adopts an electric rotor power system during the vertical take-off and landing process, and adopts a fuel oil type tail pushing engine power system during the cruise flight process of the fixed wing, thereby greatly improving the range and the endurance of the vertical take-off and landing fixed wing unmanned aerial vehicle; the fixed wing of the unmanned aerial vehicle can be folded or unfolded, so that the area requirement on a landing site is reduced, and the unmanned aerial vehicle can vertically land on the ground or a deck with smaller site; according to the invention, the outer wing section of the vertical take-off and landing fixed-wing unmanned aerial vehicle wing is parked in a folded state, so that the required machine position size or warehouse space of the unmanned aerial vehicle can be reduced; in addition, the fatigue problem of the wing structure in the ground carrying process is relieved, the service life is prolonged, and the disassembly and the installation of the wing structure and adjacent parts are facilitated; in the process of taking off and landing of the outer wing section of the vertical take-off and landing fixed-wing unmanned aerial vehicle wing in a folded state, the normal taking-off and landing under the condition of insufficient space of the take-off and landing site can be realized, and the related geometric index requirements of the carrier-based aircraft can be realized more easily; the vertical take-off and landing fixed wing unmanned aerial vehicle has larger aspect ratio, and meets the related limit requirements of airports while improving the endurance performance.
Drawings
FIG. 1 is a schematic view of the overall structure of an outer panel of the wing of the present invention in a deployed state;
FIG. 2 is a schematic diagram of an exploded construction of the present invention;
FIG. 3 is a schematic view of the overall structure of the outer panel of the wing of the present invention in a folded condition;
FIG. 4 is a second overall schematic of the outer panel of the wing of the present invention in a folded condition;
FIG. 5 is a schematic illustration of the connection of a wing segment to a fuselage in a wing according to the present invention;
FIG. 6 is a schematic view of the outer panel driven by the wing body drive mechanism of the present invention in a deployed configuration;
FIG. 7 is a second schematic view of the outer panel driven by the wing body drive mechanism of the present invention during deployment;
FIG. 8 is a schematic view of the structure of the wing body drive mechanism of the present invention driving the outer wing section when folded;
FIG. 9 is a second schematic illustration of the configuration of the wing body drive mechanism of the present invention driving the outer wing section when folded;
FIG. 10 is a schematic view of the junction between the outer panel and the inner panel in the present invention;
FIG. 11 is a schematic cross-sectional structure of the end of the actuating rod of the linear steering engine of the present invention slidingly connected in the sliding limiting hole through a rotating shaft;
meaning of reference numerals in the drawings:
1-fuselage, 2-nose, 3-middle wing section, 4-outer wing section, 5-tail push engine, 6-tail push propeller, 7-duck wing, 8-vertical boom, 9-rotor power system, 10-vertical tail, 11-through hole I, 12-through hole II, 13-bolt and nut assembly, 14-landing gear, 15-fuel tank cap, 16-aft fuselage cover, 17-middle wing section girder, 18-middle wing section auxiliary girder, 19-middle wing metal piece, 20-self-locking nut, 21-bolt, 22-sleeve, 23-carbon tube, 25-front fuselage cover, 26-rubber pad, 27-outer wing section girder, 28-outer wing section auxiliary girder, 29-hinge, 30-slide limiting hole, 31-main girder middle wing lug, 32-main girder outer wing lug, 33-straight steering engine, 34-actuating lever, 35-pipe body, 36-rotating shaft, 37-limiting lug, 38-limiting bolt, 39-locking lug, 41-auxiliary girder middle wing lug, 42-auxiliary girder outer wing lug.
Detailed Description
The invention is described in detail below with reference to the drawings and the specific embodiments.
As shown in fig. 1-10, the embodiment is a vertical take-off and landing fixed wing unmanned aerial vehicle with modularized duck-type layout, which comprises a fuselage 1, a nose 2 and wings, wherein the wings comprise a middle wing section 3, two ends of the middle wing section 3 are respectively connected with an outer wing section 4, the bottom of the fuselage 1 close to the rear end of the fuselage 1 is connected with the top center position of the middle wing section 3, a wing body driving mechanism is arranged at the joint of the middle wing section 3 and the outer wing section 4, and the wing body driving mechanism is used for driving the outer wing section 4 to fold or unfold; a tail pushing engine 5 is arranged at the rear end part of the machine body 1, and a tail pushing propeller 6 is arranged on an output shaft of the tail pushing engine 5; the nose 2 is arranged at the front end of the machine body 1, the two sides of the nose 2 are respectively provided with a duck wing 7, the two sides of the machine body 1 are respectively provided with a vertical rod 8, the front end of the vertical rod 8 is connected with the duck wing 7, the top of the vertical rod 8 close to the rear end of the vertical rod 8 is connected with the middle wing section 3, and a plurality of rotor power systems 9 are symmetrically arranged on the two vertical rods 8; the bottom of the vertical rod 8 near the rear end of the vertical rod 8 is connected with a vertical tail 10, and the bottom of the vertical rod 8 near the front end of the vertical rod 8 is connected with a landing gear 14.
In the embodiment, three rotor power systems 9 are arranged at the top of each lifting rod 8, wherein two rotor power systems 9 are arranged at the top of the lifting rod 8 between the middle wing section 3 and the duck wings 7, and the other rotor power system 9 is arranged at the top of the rear end of the lifting rod 8; six rotor power systems 9 are arranged on the vertical rods 8 on two sides of the machine body 1 in total, the rotor power systems 9 arranged on the two vertical rods 8 are symmetrically arranged, and the wings and the vertical rods 8 and the machine body 1 adopt lifting structures, so that the structural reliability is improved; the rotor mechanism layout of the unmanned aerial vehicle of this embodiment adopts six rotor mechanism's layout mode, for traditional four rotor mechanism layout, six rotor mechanism's layout mode makes unmanned aerial vehicle stability stronger under the strong wind condition, still can normally descend when certain rotor driving system 9 trouble, has improved unmanned aerial vehicle's reliability greatly.
In the embodiment, the rotor power system 9 is an electric rotor power system, the tail pushing engine 5 is a fuel oil type tail pushing engine, an oil tank and a battery pack for supplying power are arranged in the machine body 1, and the top of the machine body 1 is provided with an oil tank cover 15; according to the embodiment, the power system of the unmanned aerial vehicle adopts oil-electricity hybrid power, different power systems are adopted under different flight states, an electric rotor power system is adopted in the vertical take-off and landing process, and a fuel oil type tail pushing engine power system is adopted in the fixed wing cruising and flying process, so that the range and the endurance of the vertical take-off and landing fixed wing unmanned aerial vehicle are greatly improved.
In the embodiment, a plurality of first through holes 11 penetrating through the middle wing section 3 along the thickness direction of the middle wing section 3 are formed in the middle wing section 3, a plurality of second through holes 12 correspondingly matched with the plurality of first through holes 11 are formed in the bottom of the machine body 1, and the machine body 1 and the middle wing section 3 are detachably connected through a bolt and nut assembly 13 penetrating through the corresponding second through holes 12 and the first through holes 11; a rear body cover 16 is arranged at the top of the body 1 corresponding to the plurality of second through holes 12; the bolt and nut assembly 13 can be operated by opening the rear fuselage cover 16 at the top of the fuselage 1, so that the fuselage 1 and the middle wing section 3 can be quickly disassembled and assembled; in practical application, the middle wing section 3 can be embedded into a middle wing metal reinforcing frame, the middle wing metal reinforcing frame is provided with a first through hole 11, the machine body 1 corresponding to the middle wing metal reinforcing frame is embedded into a machine body metal reinforcing piece, and the machine body metal reinforcing piece is provided with a second through hole 12 for improving the strength of a connecting structure between the two.
In the embodiment, the outer side surfaces of a middle wing section main beam 17 and a middle wing section auxiliary beam 18 are respectively provided with a middle wing metal piece 19, the top of a vertical rod 8 is provided with a self-locking nut 20 correspondingly matched with the two middle wing metal pieces 19, and the middle wing metal pieces 19 are detachably connected with the self-locking nuts 20 through bolts 21; an opening through which the bolt 21 passes is formed in the top skin of the middle wing section 3 corresponding to the middle wing metal piece 19; the quick assembly disassembly between the middle wing section 3 and the vertical rod 8 is realized.
In the embodiment, a sleeve 22 is arranged at one end of the duck wings 7 far away from the machine head 2, a carbon tube 23 is arranged at the front end of the hanging rod 8, and the carbon tube 23 at the front end of the hanging rod 8 is inserted into the sleeve 22 of the duck wings 7 and detachably connected with the duck wings 7 through a plurality of screws; the quick assembly and disassembly between the hanging rod 8 and the duck wings 7 are realized; the front end face of the machine body 1 is provided with a machine body end plate, the top of the machine body 1 close to the front end of the machine body 1 is provided with a front machine body cover 25, the connecting end of the machine head 2 and the machine body 1 is provided with a machine head end plate, and the machine body end plate and the machine head end plate are detachably connected through a plurality of screws; the front machine body cover 25 at the top of the machine body 1 is opened, and a plurality of screws for connecting the machine body end plate and the machine head end plate can be operated, so that the machine body 1 and the machine head 2 can be quickly disassembled and assembled; in this embodiment, the duck wings 7 and the machine head 2 are integrally formed.
In the embodiment, the vertical tail 10 and the landing gear 14 are detachably connected with the vertical rod 8 through a plurality of screws respectively, and rubber pads 26 are arranged at the bottom ends of the vertical tail 10 and the landing gear 14 respectively; the vertical tails 10, the landing gear 14 and the vertical lifting rods 8 are convenient to disassemble and assemble quickly, and the two vertical tails 10 can be used as the landing gear 14, so that the extra weight and air resistance of the landing gear 14 which are independently arranged are avoided.
In this embodiment, the wing body driving mechanism includes a driving rotation mechanism and a driven rotation mechanism, the driving rotation mechanism includes a middle wing tab 31 and an outer wing tab 32 of the main beam, the middle wing tab 31 of the main beam is installed on the inner side surface of the middle wing section main beam 17, the outer wing tab 32 of the main beam is installed on the inner side surface of the outer wing section main beam 27, the outer wing tab 32 of the main beam is rotationally connected with the top of the middle wing tab 31 of the main beam through a hinge 29, an arc-shaped sliding limiting hole 30 is arranged at the bottom of the middle wing tab 31 of the main beam, a linear steering engine 33 is arranged between the middle wing tab 31 of the main beam and the outer wing tab 32 of the main beam, the tail end of the linear steering engine 33 is rotationally connected with the top of the outer wing tab 32 of the main beam, and the end of an actuating rod 34 of the linear steering engine 33 is slidingly connected in the sliding limiting hole 30; the driven rotation mechanism comprises an auxiliary beam middle wing lug 41 and an auxiliary beam outer wing lug 42, wherein the auxiliary beam middle wing lug 41 is arranged on the inner side surface of the middle wing section auxiliary beam 18, the auxiliary beam outer wing lug 42 is arranged on the inner side surface of the outer wing section auxiliary beam 28, and the auxiliary beam outer wing lug 42 is rotatably connected with the top of the auxiliary beam middle wing lug 41 through a hinge 29.
In the unfolded state of the outer wing section 4, the end part of the actuating rod 34 of the linear steering engine 33 is positioned at the initial position of the arc-shaped limiting stroke of the sliding limiting hole 30, and the exposed length of the actuating rod 34 of the linear steering engine 33 is in the shortest state; when the outer wing section 4 is required to be folded, the linear steering engine 33 drives the actuating rod 34 to stretch, along with the gradual stretching of the actuating rod 34 of the linear steering engine 33, the outer wing section 4 starts to be overturned and folded upwards by the thrust of the tail end of the linear steering engine 33, the end part of the actuating rod 34 of the linear steering engine 33 slides along the arc-shaped limiting stroke of the sliding limiting hole 30, when the exposed length of the actuating rod 34 of the linear steering engine 33 reaches the longest state, the upward overturning and folding angle of the outer wing section 4 reaches the maximum value, and at the moment, the end part of the actuating rod 34 of the linear steering engine 33 slides from the initial position of the arc-shaped limiting stroke of the sliding limiting hole 30 to the end position of the arc-shaped limiting stroke of the sliding limiting hole 30, so that the outer wing section 4 is in a folded state; the outer wing section 4 of the vertical take-off and landing fixed wing unmanned aerial vehicle wing is parked in a folded state, so that the size of the machine position or the warehouse space required by the unmanned aerial vehicle can be reduced; in addition, the fatigue problem of the wing structure in the ground carrying process is relieved, the service life is prolonged, and the disassembly and the installation of the wing structure and adjacent parts are facilitated; in the process of taking off and landing in a folded state, the outer wing section 4 of the vertical take-off and landing fixed-wing unmanned aerial vehicle wing can realize normal taking off and landing under the condition of insufficient space of a take-off and landing site, and the related geometric index requirements of the carrier-based aircraft are easier to realize; the vertical take-off and landing fixed wing unmanned aerial vehicle has larger aspect ratio, and meets the related limit requirements of airports while improving the endurance performance.
In this embodiment, the end of the middle wing tab 31 of the main beam facing the outer wing tab 32 of the main beam has two side walls, the outer wing tab 32 of the main beam is rotatably connected between the two side walls at the top of the middle wing tab 31 of the main beam through a hinge 29, two corresponding arc-shaped sliding limiting holes 30 are respectively arranged on the two side walls at the bottom of the middle wing tab 31 of the main beam, and the end of the actuating rod 34 of the linear steering engine 33 is located between the two side walls and is slidably connected in the two sliding limiting holes 30; the sliding connection effect of the end part of the actuating rod 34 of the linear steering engine 33 in the sliding limiting hole 30 is improved, and structural stress uniformity of the lug 31 in the main beam is ensured.
In this embodiment, the end of the actuating rod 34 of the linear steering engine 33 is provided with a tube 35, the axis of the tube 35 is perpendicular to the axis of the actuating rod 34, the tube 35 is located between the sliding limiting holes 30 of the two side walls, the length of the tube is smaller than the distance between the two side walls, a rotating shaft 36 is slidably arranged in the sliding limiting holes 30 of the two side walls, the rotating shaft 36 movably passes through the tube 35 at the end of the actuating rod 34 of the linear steering engine 33, one end of the rotating shaft 36 is provided with a limiting plate 37, the end surface of the other end of the rotating shaft 36 is provided with a threaded hole, a limiting bolt 38 is in threaded connection with the threaded hole, a locking plate 39 is movably sleeved on the threaded rod of the limiting bolt 38, and the limiting plate 37 and the locking plate 39 are respectively located on the outer side surfaces of the two side walls of the lug 31 in the main beam; the end part of the actuating rod 34 of the linear steering engine 33 is slidably connected in the sliding limiting hole 30 through the rotating shaft 36, when the rotating shaft 36 is worn, the rotating shaft 36 can be replaced timely to ensure the normal work of the linear steering engine 33, and meanwhile, the end part of the actuating rod 34 of the linear steering engine 33 can be separated from the two side walls during daily maintenance.
According to the unmanned aerial vehicle, the front-mounted duck wing layout is adopted, so that the lift-drag ratio and aerodynamic efficiency of the unmanned aerial vehicle are improved, and the unmanned aerial vehicle has good maneuverability; the modularized design is adopted, so that the whole detachability of the unmanned aerial vehicle is realized, meanwhile, the replaceability of each module of the unmanned aerial vehicle is realized, and the daily maintenance, storage and transportation are facilitated; six rotor power systems are arranged on the vertical rods at two sides of the fuselage, the rotor power systems arranged on the two vertical rods are symmetrically arranged, and the wings, the vertical rods and the fuselage adopt lifting structures, so that the structural reliability is improved; compared with the traditional four-rotor wing mechanism layout, the six-rotor wing mechanism layout is adopted, so that the unmanned aerial vehicle is stronger in stability under the strong wind condition, can still normally land when a certain rotor wing power system fails, the reliability of the unmanned aerial vehicle is greatly improved, and the anti-strong wind disturbance capability is strong; according to the embodiment, the power system of the unmanned aerial vehicle adopts oil-electricity hybrid power, different power systems are adopted under different flight states, an electric rotor power system is adopted in the vertical take-off and landing process, and a fuel oil type tail pushing engine power system is adopted in the fixed wing cruising and flying process, so that the range and the endurance of the vertical take-off and landing fixed wing unmanned aerial vehicle are greatly improved.
The fixed wing of the unmanned aerial vehicle can be folded or unfolded, so that the area requirement on the landing site is reduced, and the unmanned aerial vehicle can vertically land on the ground or a deck with smaller site; in the outer wing section unfolding state, the end part of the actuating rod of the linear steering engine is positioned at the initial position of the arc-shaped limiting stroke of the sliding limiting hole, and the exposed length of the actuating rod of the linear steering engine is in the shortest state; when the outer wing section is required to be folded, the actuating rod is driven to stretch, the outer wing section starts to be overturned and folded upwards by the thrust of the tail end of the linear steering engine along with the gradual stretching of the actuating rod of the linear steering engine, the end part of the actuating rod of the linear steering engine slides along the arc-shaped limiting stroke of the sliding limiting hole, when the exposed length of the actuating rod of the linear steering engine extends out of the opening reaches the longest state, the angle of the upward overturning and folding of the outer wing section reaches the maximum value, and at the moment, the end part of the actuating rod of the linear steering engine slides from the initial position of the arc-shaped limiting stroke of the sliding limiting hole to the final position of the arc-shaped limiting stroke of the sliding limiting hole, so that the outer wing section is in a folded state; when the outer wing section is required to be restored to the unfolding state, the linear steering engine drives the actuating rod to be shortened, the outer wing section starts to overturn downwards to be unfolded under the pulling force of the tail end of the linear steering engine along with the gradual shortening of the actuating rod of the linear steering engine, the end part of the actuating rod of the linear steering engine slides along the arc-shaped limiting stroke of the sliding limiting hole, and when the actuating rod of the linear steering engine is shortened to the shortest exposed length, the outer wing section realizes overturn downwards to be unfolded, and at the moment, the end part of the actuating rod of the linear steering engine slides from the end position of the arc-shaped limiting stroke of the sliding limiting hole to the initial position of the arc-shaped limiting stroke of the sliding limiting hole, so that the outer wing section is restored to the unfolding state; the outer wing segments of the vertical take-off and landing fixed wing unmanned aerial vehicle wings are parked in a folded state, so that the size of the machine position or the warehouse space required by the unmanned aerial vehicle can be reduced; in addition, the fatigue problem of the wing structure in the ground carrying process is relieved, the service life is prolonged, and the disassembly and the installation of the wing structure and adjacent parts are facilitated; in the process of taking off and landing of the outer wing section of the vertical take-off and landing fixed-wing unmanned aerial vehicle wing in a folded state, the normal taking-off and landing under the condition of insufficient space of the take-off and landing site can be realized, and the related geometric index requirements of the carrier-based aircraft can be realized more easily; the vertical take-off and landing fixed wing unmanned aerial vehicle has larger aspect ratio, and meets the related limit requirements of airports while improving the endurance performance.
In the description of the present invention, it should be understood that the terms "center", "longitudinal", "lateral", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc. indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, are merely for convenience in describing the present invention and simplifying the description, and do not indicate or imply that the devices or elements referred to must have a specific orientation, be configured and operated in a specific orientation, and thus should not be construed as limiting the present invention; furthermore, the terms "a," "an," and "two" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance.
In the description of the present invention, it should be noted that, unless explicitly stated and limited otherwise, the terms "mounted," "connected," and "configured" are to be construed broadly, and may be, for example, fixedly connected, configured, detachably connected, configured, or integrally connected, configured; can be mechanically or electrically connected; can be directly connected, can also be indirectly connected through an intermediate medium, and can also be the communication between the two elements; the specific meaning of the above terms in the present invention can be understood by those of ordinary skill in the art according to the specific circumstances.
The foregoing has shown and described the basic principles, principal features and advantages of the invention; it will be appreciated by persons skilled in the art that the above embodiments are not intended to limit the invention in any way, and that all technical solutions obtained by means of equivalent substitutions or equivalent transformations fall within the scope of the invention.
Claims (9)
1. The vertical take-off and landing fixed wing unmanned aerial vehicle is characterized by comprising a fuselage, a nose and wings, wherein the wings comprise middle wing sections, two ends of each middle wing section are respectively connected with outer wing sections, the bottom of the fuselage, which is close to the rear end of the fuselage, is connected with the top center position of each middle wing section, and a wing body driving mechanism is arranged at the joint of each middle wing section and each outer wing section and is used for driving the outer wing sections to fold or unfold; a tail pushing engine is arranged at the end part of the rear end of the machine body, and a tail pushing propeller is arranged on an output shaft of the tail pushing engine; the nose is arranged at the front end of the machine body, the two sides of the nose are respectively provided with a duck wing, the two sides of the machine body are respectively provided with a vertical lifting rod, the front end of the vertical lifting rod is connected with the duck wing, the top of the vertical lifting rod close to the rear end of the vertical lifting rod is connected with the middle wing section, and a plurality of rotor wing power systems are symmetrically arranged on the two vertical lifting rods; the bottom of the vertical rod close to the rear end of the vertical rod is connected with a vertical tail, and the bottom of the vertical rod close to the front end of the vertical rod is connected with a landing gear;
the wing body driving mechanism comprises a driving rotation mechanism and a driven rotation mechanism, the driving rotation mechanism comprises a main beam middle wing lug and a main beam outer wing lug, the main beam middle wing lug is arranged on the inner side surface of a main beam of the middle wing section, the main beam outer wing lug is arranged on the inner side surface of a main beam of the outer wing section, the main beam outer wing lug is rotationally connected with the top of the main beam middle wing lug through a hinge, an arc-shaped sliding limiting hole is formed in the bottom of the main beam middle wing lug, a linear steering engine is arranged between the main beam middle wing lug and the main beam outer wing lug, the tail end of the linear steering engine is rotationally connected with the top of the main beam outer wing lug, and the end part of an executing rod of the linear steering engine is slidingly connected in the sliding limiting hole; the driven rotating mechanism comprises an auxiliary beam middle wing tab and an auxiliary beam outer wing tab, wherein the auxiliary beam middle wing tab is arranged on the inner side surface of the middle wing section auxiliary beam, the auxiliary beam outer wing tab is arranged on the inner side surface of the outer wing section auxiliary beam, and the auxiliary beam outer wing tab is rotationally connected with the top of the auxiliary beam middle wing tab through a hinge.
2. The modular duck-type layout vertical lift fixed wing unmanned aerial vehicle of claim 1, wherein three rotor power systems are provided at the top of each vertical lift mast, two of which are provided at the top of the vertical lift mast between the middle wing section and the duck wing, and the other rotor power system is provided at the top of the rear end of the vertical lift mast.
3. The vertical lift fixed wing unmanned aerial vehicle of a modular duck-type layout according to claim 1 or 2, wherein the rotor power system is an electric rotor power system, the tail-push engine is a fuel-type tail-push engine, an oil tank and a battery pack for supplying power are arranged in the fuselage, and an oil tank cover is arranged at the top of the fuselage.
4. The vertical take-off and landing fixed wing unmanned aerial vehicle with the modularized duck type layout according to claim 1, wherein a plurality of first through holes penetrating through the middle wing section along the thickness direction of the middle wing section are formed in the middle wing section, a plurality of second through holes correspondingly matched with the first through holes are formed in the bottom of the fuselage, and the fuselage and the middle wing section are detachably connected through a bolt and nut assembly penetrating through the corresponding second through holes and the first through holes; and a rear machine body cover is arranged at the top of the machine body corresponding to the second through holes.
5. The vertical take-off and landing fixed wing unmanned aerial vehicle with the modularized duck-shaped layout according to claim 1, wherein the outer side surfaces of the main beam and the auxiliary beam of the middle wing section are respectively provided with a middle wing metal piece, the top of the vertical lifting rod is provided with self-locking nuts correspondingly matched with the two middle wing metal pieces, and the middle wing metal pieces are detachably connected with the self-locking nuts through bolts; and an opening for a bolt to pass through is formed in the top skin of the middle wing section corresponding to the middle wing metal piece.
6. The vertical take-off and landing fixed wing unmanned aerial vehicle with the modularized duck-shaped layout according to claim 1, wherein a sleeve is arranged at one end of the duck wing far away from the machine head, a carbon tube is arranged at the front end of a hanging rod, and the carbon tube at the front end of the hanging rod is inserted into the sleeve of the duck wing and is detachably connected with the duck wing through a plurality of screws; the front end face of the machine body is provided with a machine body end plate, a front machine body cover is arranged at the top of the machine body close to the front end of the machine body, the connecting end of the machine head and the machine body is provided with a machine head end plate, and the machine body end plate and the machine head end plate are detachably connected through a plurality of screws.
7. The vertical take-off and landing fixed wing unmanned aerial vehicle with the modularized duck-type layout according to claim 1, wherein the vertical tail and the landing gear are detachably connected with the vertical lifting rod through a plurality of screws respectively, and rubber pads are arranged at the bottom ends of the vertical tail and the landing gear respectively.
8. The vertical take-off and landing fixed wing unmanned aerial vehicle with the modularized duck-shaped layout according to claim 1, wherein the end part of the middle wing tab of the main beam, which faces the outer wing tab of the main beam, is provided with two side walls, the outer wing tab of the main beam is rotationally connected between the two side walls of the top part of the middle wing tab of the main beam through a hinge, the two side walls of the bottom part of the middle wing tab of the main beam are respectively provided with arc-shaped sliding limiting holes which correspond to each other, and the end part of the actuating rod of the linear steering engine is positioned between the two side walls and is in sliding connection with the two sliding limiting holes.
9. The vertical lifting fixed wing unmanned aerial vehicle with the modularized duck-shaped layout according to claim 8, wherein the end part of the actuating rod of the linear steering engine is provided with a tube body, the axis of the tube body is perpendicular to the axis of the actuating rod, the tube body is positioned between sliding limiting holes of two side walls, the length of the tube body is smaller than the distance between the two side walls, a rotating shaft is slidably arranged in the sliding limiting holes of the two side walls, the rotating shaft movably passes through the tube body of the end part of the actuating rod of the linear steering engine, one end of the rotating shaft is provided with a limiting plate, the end surface of the other end of the rotating shaft is provided with a threaded hole, a limiting bolt is connected in the threaded hole in a threaded mode, a locking plate is movably sleeved on a screw rod of the limiting bolt, and the limiting plate and the locking plate are respectively positioned on the outer side surfaces of the two side walls of the lug plates in the main beam.
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| CN110844065A (en) * | 2019-12-06 | 2020-02-28 | 宇领星际航空(苏州)有限公司 | Unmanned aerial vehicle with strong loading capacity and capable of vertically taking off and landing |
| CN211685607U (en) * | 2019-12-16 | 2020-10-16 | 宇领星际航空(苏州)有限公司 | But folding unmanned aerial vehicle of VTOL tail seat |
| CN111846216A (en) * | 2019-04-28 | 2020-10-30 | 上海峰飞航空科技有限公司 | Vertical take-off and landing fixed wing unmanned aerial vehicle |
| CN214451855U (en) * | 2021-01-08 | 2021-10-22 | 天峋（常州）智能科技有限公司 | Duck wing VTOL unmanned aerial vehicle |
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| AU2018355573A1 (en) * | 2017-10-27 | 2020-05-14 | Elroy Air, Inc. | Compound multi-copter aircraft |
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| CN207274984U (en) * | 2017-10-14 | 2018-04-27 | 上海歌尔泰克机器人有限公司 | A kind of aircraft |
| CN111846216A (en) * | 2019-04-28 | 2020-10-30 | 上海峰飞航空科技有限公司 | Vertical take-off and landing fixed wing unmanned aerial vehicle |
| CN110844065A (en) * | 2019-12-06 | 2020-02-28 | 宇领星际航空(苏州)有限公司 | Unmanned aerial vehicle with strong loading capacity and capable of vertically taking off and landing |
| CN211685607U (en) * | 2019-12-16 | 2020-10-16 | 宇领星际航空(苏州)有限公司 | But folding unmanned aerial vehicle of VTOL tail seat |
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