CN113955092A - 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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- CN113955092A CN113955092A CN202111454185.XA CN202111454185A CN113955092A CN 113955092 A CN113955092 A CN 113955092A CN 202111454185 A CN202111454185 A CN 202111454185A CN 113955092 A CN113955092 A CN 113955092A
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- 230000007246 mechanism Effects 0.000 claims abstract description 41
- 241000272525 Anas platyrhynchos Species 0.000 claims abstract description 21
- 229910052751 metal Inorganic materials 0.000 claims description 18
- 239000002184 metal Substances 0.000 claims description 18
- 241000272517 Anseriformes Species 0.000 claims description 15
- 229910052799 carbon Inorganic materials 0.000 claims description 7
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 claims description 6
- 239000003921 oil Substances 0.000 claims description 6
- 230000000149 penetrating effect Effects 0.000 claims description 6
- 239000000295 fuel oil Substances 0.000 claims description 5
- 230000000712 assembly Effects 0.000 claims description 3
- 238000000429 assembly Methods 0.000 claims description 3
- 238000000034 method Methods 0.000 description 17
- 230000008569 process Effects 0.000 description 17
- 238000012423 maintenance Methods 0.000 description 5
- 230000003014 reinforcing effect Effects 0.000 description 5
- 230000002035 prolonged effect Effects 0.000 description 4
- 230000008859 change Effects 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- 239000000446 fuel Substances 0.000 description 2
- 230000007306 turnover Effects 0.000 description 2
- WHXSMMKQMYFTQS-UHFFFAOYSA-N Lithium Chemical compound [Li] WHXSMMKQMYFTQS-UHFFFAOYSA-N 0.000 description 1
- 239000002828 fuel tank Substances 0.000 description 1
- 229910052744 lithium Inorganic materials 0.000 description 1
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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
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
- B64D27/02—Aircraft characterised by the type or position of power plants
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
- B64D27/02—Aircraft characterised by the type or position of power plants
- B64D27/026—Aircraft characterised by the type or position of power plants comprising different types of power plants, e.g. combination of a piston engine and a gas-turbine
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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
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- 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
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Abstract
The invention discloses a vertical take-off and landing fixed wing unmanned aerial vehicle with a modularized duck-type layout, which comprises a fuselage, a nose and wings, wherein the wings comprise middle wing sections, two ends of the middle wing sections are respectively connected with outer wing sections, the bottom of the fuselage, close to the rear end of the fuselage, is connected with the top center of the middle wing sections, and the joints of the middle wing sections and the outer wing sections are provided with wing body driving mechanisms for driving the outer wing sections to fold or unfold; a tail pushing engine and a tail pushing propeller are arranged at the end part of the rear end of the machine body; the aircraft nose is installed in the front end of the fuselage, there are duck wings on both sides of the aircraft nose separately, there are vertical poles on both sides of the fuselage separately, the vertical pole is connected with duck wing and middle wing section, there are multiple rotor power systems symmetrically on two vertical poles; the invention adopts the layout of the front duck-type wings, improves the lift-drag ratio and the pneumatic efficiency of the unmanned aerial vehicle, and leads the unmanned aerial vehicle to have better maneuverability; the wings can be folded or unfolded, the area requirement on a take-off and landing site is reduced, and vertical take-off and landing can be performed on the ground or a deck with a smaller site.
Description
Technical Field
The invention relates to a modularized canard layout vertical take-off and landing fixed wing unmanned aerial vehicle, 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 vertical take-off and landing, and is widely applied to the field of unmanned aerial vehicles at present; the traditional vertical take-off and landing fixed wing unmanned aerial vehicle has the following problems:
1. the single-wing layout is adopted, the lift-drag ratio is low, and the aerodynamic efficiency is still to be improved;
2. the volume is large, the device is integrally designed, the transportation and the use are inconvenient, and the structure cannot be disassembled and assembled;
3. the vertical take-off and landing rotor system usually adopts a four-rotor layout, so that the strong wind interference resistance is poor, and the reliability of the airplane is poor;
4. the fixed wing has larger size and has large requirement on the area of a take-off and 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 time are short;
meanwhile, for improving the flight time performance, the air stagnation capacity of the airplane is improved, modern unmanned aerial vehicles mostly adopt wings with a large aspect ratio, the wings with large extension ratio provide higher requirements for the space size of the taking-off and landing field of the unmanned aerial vehicle, sometimes even the taking-off and landing can not be completed in a specific field, and in addition, the wings with large flexible extension ratio are in the ground carrying process, the fatigue problem of the wing structure can be caused due to road jolt, the service life of the wing structure can be shortened, and under the ground parking or standby state, a larger parking machine position or a warehouse space is also needed.
Disclosure of Invention
The invention aims to solve 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 a front duck-type wing layout is adopted, so that the lift-drag ratio and the pneumatic efficiency of the unmanned aerial vehicle are improved, and the unmanned aerial vehicle has better maneuverability; the modular design is adopted, so that the integral detachability of the unmanned aerial vehicle is realized, and the replaceability of each module of the unmanned aerial vehicle is realized, thereby facilitating daily maintenance, storage and transportation; the fixed wing wings of the unmanned aerial vehicle can be folded or unfolded, so that the requirement on the area of a take-off and landing site is reduced, and the unmanned aerial vehicle can take off and land vertically on the ground or a deck with a smaller site; the strong wind interference resistance is strong, and the range and the time of the vertical take-off and landing fixed wing unmanned aerial vehicle are also improved.
In order to achieve the above object, the present invention adopts the following technical solutions:
a modularized canard layout vertical take-off and landing fixed wing unmanned aerial vehicle comprises a body, 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 body close to the rear end of the body is connected with the center of the top of each middle wing section, a wing body driving mechanism is arranged at the joint of each middle wing section and each outer wing section, and the wing body driving mechanism is used for driving the outer wing sections to fold or unfold; a tail pushing engine is arranged at the rear end of the machine body, and a tail pushing propeller is mounted on an output shaft of the tail pushing engine; the aircraft nose is arranged at the front end of the aircraft body, duck wings are respectively arranged on two sides of the aircraft nose, the two sides of the aircraft body are respectively provided with a vertical rod, the front end of the vertical rod is connected with the duck wings, the top of the vertical rod close to the rear end of the vertical rod is connected with the middle wing section, and a plurality of rotor wing power systems are symmetrically arranged on the two vertical 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 an undercarriage.
As a further preferred of the invention, three rotor power systems are arranged on the top of each vertical rod, wherein two rotor power systems are arranged on the top of the vertical rod between the middle wing section and the canard, and the other rotor power system is arranged on the top of the rear end of the vertical rod; the six rotor wing power systems are arranged on the two vertical rods on the two sides of the fuselage, the rotor wing power systems arranged on the two vertical rods are mutually symmetrically arranged, and the wings, the vertical rods and the fuselage are in a lifting structure, so that the structural reliability is improved; the rotor mechanism layout of the unmanned aerial vehicle adopts a layout mode of six rotor mechanisms, and compared with the traditional four-rotor mechanism layout, the layout mode of the six rotor mechanisms ensures that the unmanned aerial vehicle has stronger stability under the strong wind condition, and can still normally land when a certain rotor power system fails, thereby greatly improving the reliability of the unmanned aerial vehicle.
As a further preferred aspect of the present invention, the rotor power system is an electric rotor power system, the tail-thrust engine is a fuel-oil tail-thrust engine, an oil tank and a battery pack for supplying power are disposed inside the airframe, and an oil tank cover is disposed on the top of the airframe; the power system of the unmanned aerial vehicle adopts oil-electricity hybrid power, different power systems are adopted in different flight states, an electric rotor power system is adopted in the vertical take-off and landing process, and a fuel oil type tail-thrust engine power system is adopted in the fixed wing cruise flight process, so that the voyage and the time of the vertical take-off and landing fixed wing unmanned aerial vehicle are greatly improved.
As a further preferred aspect 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 fuselage, and the fuselage is detachably connected with the middle wing section through bolt and nut assemblies 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 plurality of second through holes; the rear body cover at the top of the body is opened, so that the bolt and nut assembly can be operated, and the body and the middle wing section can be quickly disassembled and assembled.
As a further preference 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 and the self-locking nut are detachably connected 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 middle wing section and the vertical rod can be quickly disassembled and assembled.
As a further preferred aspect of the invention, a sleeve is arranged at one end of the duck wing, which is far away from the machine head, a carbon tube is arranged at the front end of the vertical rod, and the carbon tube at the front end of the vertical rod is inserted into the sleeve of the duck wing and is detachably connected with the duck wing through a plurality of screws; the fast assembly and disassembly between the vertical rods and the duck wings are realized; the end face of the front end 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 end plate of the machine head is arranged at the connecting end of the machine head and the machine body, 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, so that a plurality of screws for connecting the machine body end plate and the machine head end plate can be operated, and the quick assembly and disassembly between the machine body and the machine head are realized; the duck wing and the machine head adopt an integrated forming structure.
As a further preferred option of the invention, the vertical fin 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 fin and the landing gear respectively; the vertical fin and the undercarriage are convenient to be quickly disassembled and assembled with the vertical rod, and the two vertical fins can be used as the undercarriage, so that the extra weight and air resistance of the undercarriage are avoided.
As a further preferred aspect of the invention, the wing body driving mechanism comprises a driving rotating mechanism and a driven rotating mechanism, the driving rotating mechanism comprises a girder middle wing lug and a girder outer wing lug, the girder middle wing lug is installed on the inner side surface of a middle wing section girder, the girder outer wing lug is installed on the inner side surface of an outer wing section girder, the girder outer wing lug is rotatably connected with the top of the girder middle wing lug through a hinge, an arc-shaped sliding limiting hole is formed in the bottom of the girder middle wing lug, a linear steering engine is arranged between the girder middle wing lug and the girder outer wing lug, the tail end of the linear steering engine is rotatably connected with the top of the girder outer wing lug, and the end of an actuating lever of the linear steering engine is slidably connected in the sliding limiting hole; the driven rotating mechanism comprises a aileron middle wing lug and an aileron outer wing lug, the aileron middle wing lug is arranged on the inner side surface of the middle wing section aileron, the aileron outer wing lug is arranged on the inner side surface of the outer wing section aileron, and the aileron outer wing lug is rotatably connected with the top of the aileron middle wing lug through a hinge.
Under the unfolding state of the outer wing section, the end part of an actuating rod of the linear steering engine is positioned at the initial position of the arc 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 linear steering engine drives the execution rod to extend, the outer wing section starts to be turned upwards and folded under the thrust of the tail end of the linear steering engine along with the gradual extension of the execution rod of the linear steering engine, the end part of the execution rod of the linear steering engine slides along the arc limiting stroke of the sliding limiting hole, when the extended exposed length of the execution rod of the linear steering engine reaches the longest state, the upward turning and folding angle of the outer wing section reaches the maximum value, and at the moment, the end part of the execution rod of the linear steering engine slides from the initial position of the arc limiting stroke of the sliding limiting hole to the end position of the arc limiting stroke of the sliding limiting hole, so that the outer wing section is in a folded state; the outer wing sections of the wings of the vertical take-off and landing fixed wing unmanned aerial vehicle are parked in a folded state, so that the size of a machine position or the space of a warehouse required by the unmanned aerial vehicle can be reduced; moreover, the fatigue problem of the wing structure in the ground transportation process is relieved, the service life is prolonged, and the wing structure and adjacent parts are convenient to disassemble and install; in the process of taking off and landing the outer wing sections of the wings of the vertical take-off and landing fixed-wing unmanned aerial vehicle in a folded state, normal taking off and landing can be realized under the condition of insufficient space of a take-off and landing field, and the requirements of relevant geometric indexes of a carrier-based aircraft are easily met; make VTOL fixed wing unmanned aerial vehicle possess bigger aspect ratio, when improving the time spent performance, satisfy the relevant restriction requirement in airport.
As a further preferred aspect of the invention, the end of the main beam middle wing lug facing the main beam outer wing lug is provided with two side walls, the main beam outer wing lug is rotatably connected between the two side walls at the top of the main beam middle wing lug through a hinge, the two side walls at the bottom of the main beam middle wing lug are respectively provided with arc-shaped sliding limiting holes corresponding to each other, and the end of the actuating rod of the linear steering engine is located between the two side walls and is slidably connected in the two sliding limiting holes; the sliding connection effect of the end part of the execution rod of the linear steering engine in the sliding limiting hole is improved, and the structural stress uniformity of the middle wing lug of the main beam is guaranteed.
As a further preferable mode of the invention, the end part of the actuating rod of the linear actuator 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 positioned 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 arranged in the sliding limiting holes of the two side walls in a sliding manner, the rotating shaft movably penetrates through the pipe body at the end part of the actuating rod of the linear actuator, one end of the rotating shaft is provided with a limiting piece, 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 manner, a locking piece is movably sleeved on a screw rod of the limiting bolt, and the limiting piece and the locking piece are respectively positioned on the outer side surfaces of the two side walls of the middle wing ear piece of the main beam; make the executive rod tip of sharp steering wheel pass through pivot sliding connection in the spacing hole that slides, when 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 executive rod tip of sharp steering wheel break away from between two lateral walls when routine maintenance.
The invention has the advantages that:
by adopting the layout of the front duck type wings, the lift-drag ratio and the pneumatic efficiency of the unmanned aerial vehicle are improved, so that the unmanned aerial vehicle has better maneuverability; the modular design is adopted, so that the integral detachability of the unmanned aerial vehicle is realized, and the replaceability of each module of the unmanned aerial vehicle is realized, thereby facilitating daily maintenance, storage and transportation; the six rotor wing power systems are arranged on the two vertical rods on the two sides of the fuselage, the rotor wing power systems arranged on the two vertical rods are mutually symmetrically arranged, and the wings, the vertical rods and the fuselage are in a lifting structure, so that the structural reliability is improved; the layout of the rotor wing mechanisms of the unmanned aerial vehicle adopts a layout mode of six rotor wing mechanisms, and compared with the layout of the traditional four rotor wing mechanisms, the layout mode of the six rotor wing mechanisms ensures that the unmanned aerial vehicle has stronger stability under the condition of strong wind and can still normally land when a certain rotor wing power system fails, so that the reliability of the unmanned aerial vehicle is greatly improved, and the strong wind interference resistance is strong; the power system of the unmanned aerial vehicle adopts oil-electricity hybrid power, different power systems are adopted in different flight states, an electric rotor power system is adopted in the vertical take-off and landing process, and a fuel oil type tail-thrust engine power system is adopted in the fixed wing cruising flight process, so that the voyage and the voyage of the vertical take-off and landing fixed wing unmanned aerial vehicle are greatly improved; the fixed wing wings of the unmanned aerial vehicle can be folded or unfolded, so that the requirement on the area of a take-off and landing site is reduced, and the unmanned aerial vehicle can take off and land vertically on the ground or a deck with a smaller site; the outer wing sections of the wings of the vertical take-off and landing fixed wing unmanned aerial vehicle are parked in a folded state, so that the size of a machine position or the space of a warehouse required by the unmanned aerial vehicle can be reduced; moreover, the fatigue problem of the wing structure in the ground transportation process is relieved, the service life is prolonged, and the wing structure and adjacent parts are convenient to disassemble and install; in the process of taking off and landing the outer wing sections of the wings of the vertical take-off and landing fixed-wing unmanned aerial vehicle in a folded state, normal taking off and landing can be realized under the condition of insufficient space of a take-off and landing field, and the requirements of relevant geometric indexes of a carrier-based aircraft are easily met; make VTOL fixed wing unmanned aerial vehicle possess bigger aspect ratio, when improving the time spent performance, satisfy the relevant restriction requirement in airport.
Drawings
FIG. 1 is a schematic view of the overall structure of an outer wing section of a wing of the present invention in a deployed condition;
FIG. 2 is a schematic view of an exploded structure of the present invention;
FIG. 3 is a first schematic view of the overall structure of the outer wing section of the wing of the present invention in a folded state;
FIG. 4 is a second schematic view of the overall structure of the outer wing section of the present invention in a folded condition;
FIG. 5 is a schematic view of the connection structure of the wing section and the fuselage of the wing of the present invention;
FIG. 6 is a first schematic view of the wing body drive mechanism of the present invention driving the outer wing section in the deployed configuration;
FIG. 7 is a schematic view of the outer wing section of the wing body drive mechanism of the present invention in its deployed configuration;
FIG. 8 is a first schematic view of the outer wing section driven by the wing body driving mechanism of the present invention when folded;
FIG. 9 is a second schematic structural view of the outer wing section driven by the wing body driving mechanism of the present invention when folded;
FIG. 10 is a schematic view of the junction of the wing section and the outer wing section of the present invention;
FIG. 11 is a schematic cross-sectional view of the actuator rod of the linear actuator of the present invention, which is slidably connected to the sliding position-limiting hole through a shaft;
the meaning of the reference symbols in the figures:
1-fuselage, 2-nose, 3-center wing section, 4-outer wing section, 5-tail-push engine, 6-tail-push propeller, 7-duck wing, 8-vertical pole, 9-rotor power system, 10-vertical tail, 11-through hole one, 12-through hole two, 13-bolt-nut assembly, 14-undercarriage, 15-fuel tank cap, 16-rear fuselage cap, 17-center wing section girder, 18-center wing section girder, 19-center wing metal piece, 20-self-locking nut, 21-bolt, 22-sleeve, 23-carbon tube, 25-front fuselage cap, 26-rubber pad, 27-outer wing section girder, 28-outer wing section girder, 29-hinge, 30-slide limit hole, 31-girder middle wing tab, 32-main beam outer wing lug, 33-linear steering engine, 34-actuating rod, 35-pipe body, 36-rotating shaft, 37-limiting piece, 38-limiting bolt, 39-locking piece, 41-auxiliary beam middle wing lug and 42-auxiliary beam outer wing lug.
Detailed Description
The invention is described in detail below with reference to the figures and the embodiments.
As shown in fig. 1-10, the embodiment is a vertical take-off and landing fixed wing unmanned aerial vehicle with a modular canard layout, and the vertical take-off and landing fixed wing unmanned aerial vehicle includes a body 1, a nose 2 and wings, wherein the wings include a middle wing section 3, two ends of the middle wing section 3 are respectively connected with outer wing sections 4, the bottom of the body 1 near the rear end of the body 1 is connected with the top center 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 sections 4, and the wing body driving mechanism is used for driving the outer wing sections 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 aircraft nose 2 is installed at the front end of the aircraft nose 1, duck wings 7 are respectively arranged on two sides of the aircraft nose 2, the vertical rods 8 are respectively arranged on two sides of the aircraft nose 1, the front ends of the vertical rods 8 are connected with the duck wings 7, the tops of the vertical rods 8 close to the rear ends of the vertical rods 8 are connected with the middle wing section 3, and a plurality of rotor wing power systems 9 are symmetrically arranged on the two vertical rods 8; the bottom of the vertical rod 8 close to the rear end of the vertical rod 8 is connected with a vertical tail 10, and the bottom of the vertical rod 8 close to the front end of the vertical rod 8 is connected with an undercarriage 14.
In the embodiment, three rotor power systems 9 are arranged at the top of each vertical rod 8, wherein two rotor power systems 9 are arranged at the top of the vertical rod 8 between the middle wing section 3 and the canard 7, and the other rotor power system 9 is arranged at the top of the rear end of the vertical rod 8; the six rotor wing power systems 9 are arranged on the vertical rods 8 on the two sides of the fuselage 1, the rotor wing power systems 9 arranged on the two vertical rods 8 are symmetrically arranged, and the wings, the vertical rods 8 and the fuselage 1 adopt a lifting structure, so that the structural reliability is improved; this embodiment unmanned aerial vehicle's rotor mechanism overall arrangement adopts six rotor mechanism's overall arrangement modes, and for traditional four rotor mechanism overall arrangement, six rotor mechanism's overall arrangement modes make unmanned aerial vehicle stability under the strong wind condition stronger, still can normally descend when the 9 troubles of certain rotor driving system, have improved unmanned aerial vehicle's reliability greatly.
In this embodiment, the rotor power system 9 is an electric rotor power system, the tail thrust engine 5 is a fuel oil type tail thrust engine, an oil tank and a battery pack for supplying power are arranged inside the airframe 1, and an oil tank cover 15 is arranged at the top of the airframe 1; the driving system of the unmanned aerial vehicle adopts oil-electricity hybrid power, adopts different driving systems under different flight states, adopts an electric rotor driving system in the vertical take-off and landing process, and adopts a fuel type tail thrust engine driving system in the cruise flight process of the fixed wing, so that the voyage and the voyage of the vertical take-off and landing fixed wing unmanned aerial vehicle are greatly improved.
In the embodiment, a plurality of through holes I11 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 through holes II 12 correspondingly matched with the through holes I11 are formed in the bottom of the fuselage 1, and the fuselage 1 and the middle wing section 3 are detachably connected through bolts and nut assemblies 13 penetrating through the corresponding through holes II 12 and the through holes I11; a rear machine body cover 16 is arranged at the top of the machine body 1 corresponding to the plurality of second through holes 12; the bolt and nut assembly 13 can be operated by opening the rear body cover 16 at the top of the body 1, so that the body 1 and the middle wing section 3 can be quickly disassembled and assembled; in practical application, the middle wing metal reinforcing frame can be embedded into the middle wing section 3, the through hole I11 is formed in the middle wing metal reinforcing frame, the machine body metal reinforcing piece is embedded into the machine body 1 corresponding to the middle wing metal reinforcing frame, and the through hole II 12 is formed in the machine body metal reinforcing piece so as to improve the strength of a connecting structure between the two.
In the embodiment, the outer side surfaces of the middle wing section main beam 17 and the middle wing section auxiliary beam 18 are respectively provided with a middle wing metal piece 19, the top of the 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 piece 19 and the self-locking nut 20 are detachably connected through a bolt 21; an opening through which a 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 and disassembly between the middle wing panel 3 and the vertical rod 8 are realized.
In this embodiment, a sleeve 22 is arranged at one end of the duck wing 7 away from the machine head 2, a carbon tube 23 is arranged at the front end of the vertical rod 8, and the carbon tube 23 at the front end of the vertical rod 8 is inserted into the sleeve 22 of the duck wing 7 and is detachably connected with the duck wing 7 through a plurality of screws; the vertical rod 8 and the duck wing 7 can be quickly disassembled and assembled; the end face of the front end 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 end of the machine head 2 connected with the machine body 1 is provided with a machine head end plate, and the machine body end plate is detachably connected with the machine head end plate through a plurality of screws; a front machine body cover 25 at the top of the machine body 1 is opened, so that a plurality of screws for connecting the machine body end plate and the machine head end plate can be operated, and the quick assembly and disassembly between the machine body 1 and the machine head 2 are realized; in this embodiment, the duck wing 7 and the machine head 2 are in an integrated forming structure.
In the embodiment, the vertical fin 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 fin 10 and the landing gear 14 respectively; quick assembly and disassembly between the tag 10 and the landing gear 14 and the drop rod 8 is facilitated, and the two tags 10 can be used as the landing gear 14, avoiding the extra weight and air resistance of the separate arrangement of the landing gear 14.
In the embodiment, the wing body driving mechanism comprises a driving rotating mechanism and a driven rotating mechanism, the driving rotating mechanism comprises a girder middle wing lug 31 and a girder outer wing lug 32, the girder middle wing lug 31 is installed on the inner side surface of a middle wing section girder 17, the girder outer wing lug 32 is installed on the inner side surface of an outer wing section girder 27, the girder outer wing lug 32 is rotatably connected with the top of the girder middle wing lug 31 through a hinge 29, an arc-shaped sliding limiting hole 30 is formed in the bottom of the girder middle wing lug 31, a linear steering engine 33 is arranged between the girder middle wing lug 31 and the girder outer wing lug 32, the tail end of the linear steering engine 33 is rotatably connected with the top of the girder outer wing lug 32, and the end part of an actuating rod 34 of the linear steering engine 33 is slidably connected in the sliding limiting hole 30; the driven rotating mechanism comprises a aileron middle wing lug 41 and an aileron outer wing lug 42, the aileron middle wing lug 41 is arranged on the inner side surface of the middle wing section aileron 18, the aileron outer wing lug 42 is arranged on the inner side surface of the outer wing section aileron 28, and the aileron outer wing lug 42 is rotatably connected with the top of the aileron middle wing lug 41 through a hinge 29.
When the outer wing section 4 is in an unfolded state, 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 execution rod 34 to extend, the outer wing section 4 starts to be folded upwards in a turnover mode under the thrust of the tail end of the linear steering engine 33 along with the gradual extension of the execution rod 34 of the linear steering engine 33, the end portion of the execution rod 34 of the linear steering engine 33 slides along the arc-shaped limit stroke of the sliding limit hole 30, when the extended exposed length of the execution rod 34 of the linear steering engine 33 reaches the longest state, the upward turnover folding angle of the outer wing section 4 reaches the maximum value, at the moment, the end portion of the execution rod 34 of the linear steering engine 33 slides to the arc-shaped limit stroke end position of the sliding limit hole 30 from the arc-shaped limit stroke initial position of the sliding limit hole 30, and the outer wing section 4 is in a folded state; the outer wing sections 4 of the wings of the vertical take-off and landing fixed-wing unmanned aerial vehicle are parked in a folded state, so that the size of a machine position or the space of a warehouse required by the unmanned aerial vehicle can be reduced; moreover, the fatigue problem of the wing structure in the ground transportation process is relieved, the service life is prolonged, and the wing structure and adjacent parts are convenient to disassemble and install; in the process that the outer wing panel 4 of the vertical take-off and landing fixed wing unmanned aerial vehicle wings takes off and lands in a folded state, normal take-off and landing can be realized under the condition of insufficient space of a take-off and landing field, and the requirements of relevant geometric indexes of a carrier-based aircraft are easily met; make VTOL fixed wing unmanned aerial vehicle possess bigger aspect ratio, when improving the time spent performance, satisfy the relevant restriction requirement in airport.
In this embodiment, the end of the main beam middle wing tab 31 facing the main beam outer wing tab 32 is provided with two side walls, the main beam outer wing tab 32 is rotatably connected between the two side walls at the top of the main beam middle wing tab 31 through a hinge 29, the two side walls at the bottom of the main beam middle wing tab 31 are respectively provided with arc-shaped sliding limiting holes 30 corresponding to each other, and the end of the actuating rod 34 of the linear steering engine 33 is positioned 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 execution rod 34 of the linear steering engine 33 in the sliding limiting hole 30 is improved, and the structural stress uniformity of the wing lug 31 in the main beam is guaranteed.
In this embodiment, a pipe body 35 is arranged at an end of an execution rod 34 of the linear steering engine 33, an axis of the pipe body 35 is perpendicular to an axis of the execution rod 34, the pipe body 35 is located between sliding limiting holes 30 of two side walls, the length of the pipe body 35 is smaller than the distance between the two side walls, a rotating shaft 36 is arranged in the sliding limiting holes 30 of the two side walls in a sliding manner, the rotating shaft 36 movably penetrates through the pipe body 35 at the end of the execution rod 34 of the linear steering engine 33, a limiting piece 37 is arranged at one end of the rotating shaft 36, a threaded hole is formed in the end face of the other end of the rotating shaft 36, a limiting bolt 38 is connected in the threaded hole in a threaded manner, a locking piece 39 is movably sleeved on a screw rod of the limiting bolt 38, and the limiting piece 37 and the locking piece 39 are respectively located on outer side faces of two side walls of the wing tab 31 in the main beam; make the executive rod 34 tip of straight line steering wheel 33 through pivot 36 sliding connection in the spacing hole 30 that slides, when pivot 36 appeared wearing and tearing, can in time change pivot 36 for guarantee the normal work of straight line steering wheel 33, simultaneously, can also make the executive rod 34 tip of straight line steering wheel 33 break away from between two lateral walls when daily maintenance.
The unmanned aerial vehicle adopts the front-mounted duck wing layout, so that the lift-drag ratio and the pneumatic efficiency of the unmanned aerial vehicle are improved, and the unmanned aerial vehicle has better maneuverability; the modular design is adopted, so that the integral detachability of the unmanned aerial vehicle is realized, and the replaceability of each module of the unmanned aerial vehicle is realized, thereby facilitating daily maintenance, storage and transportation; the six rotor wing power systems are arranged on the two vertical rods on the two sides of the fuselage, the rotor wing power systems arranged on the two vertical rods are mutually symmetrically arranged, and the wings, the vertical rods and the fuselage are in a lifting structure, so that the structural reliability is improved; the layout of the rotor mechanism of the unmanned aerial vehicle adopts a layout mode of six rotor mechanisms, and compared with the layout of the traditional four rotor mechanisms, the layout mode of the six rotor mechanisms enables the unmanned aerial vehicle to have stronger stability under the strong wind condition and still normally land when a certain rotor power system fails, so that the reliability of the unmanned aerial vehicle is greatly improved, and the strong wind interference resistance is strong; the driving system of the unmanned aerial vehicle adopts oil-electricity hybrid power, adopts different driving systems under different flight states, adopts an electric rotor driving system in the vertical take-off and landing process, and adopts a fuel type tail thrust engine driving system in the cruise flight process of the fixed wing, so that the voyage and the voyage of the vertical take-off and landing fixed wing unmanned aerial vehicle are greatly improved.
The fixed wing wings of the unmanned aerial vehicle can be folded or unfolded, so that the requirement on the area of a take-off and landing site is reduced, and the unmanned aerial vehicle can take off and land vertically on the ground or a deck with a smaller site; under the unfolding state of the outer wing section, the end part of an actuating rod of the linear steering engine is positioned at the initial position of the arc 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 linear steering engine drives the execution rod to extend, the outer wing section starts to be turned upwards and folded under the thrust of the tail end of the linear steering engine along with the gradual extension of the execution rod of the linear steering engine, the end part of the execution rod of the linear steering engine slides along the arc limiting stroke of the sliding limiting hole, when the extended exposed length of the execution rod of the linear steering engine reaches the longest state, the upward turning and folding angle of the outer wing section reaches the maximum value, and at the moment, the end part of the execution rod of the linear steering engine slides from the initial position of the arc limiting stroke of the sliding limiting hole to the end position of the arc 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 unfolded state, the linear steering engine drives the executing rod to be shortened, the outer wing section starts to turn downwards and unfold under the pulling force of the tail end of the linear steering engine along the arc limiting stroke of the sliding limiting hole along with the gradual shortening of the executing rod of the linear steering engine, when the executing rod of the linear steering engine is shortened to the shortest exposed length, the outer wing section is turned downwards and unfolded, at the moment, the end part of the executing rod of the linear steering engine slides to the initial position of the arc limiting stroke of the sliding limiting hole from the end position of the arc limiting stroke of the sliding limiting hole, and the outer wing section is restored to the unfolded state; the outer wing sections of the wings of the vertical take-off and landing fixed wing unmanned aerial vehicle are parked in a folded state, so that the size of a machine position or the space of a warehouse required by the unmanned aerial vehicle can be reduced; moreover, the fatigue problem of the wing structure in the ground transportation process is relieved, the service life is prolonged, and the wing structure and adjacent parts are convenient to disassemble and install; in the process of taking off and landing the outer wing sections of the wings of the vertical take-off and landing fixed-wing unmanned aerial vehicle in a folded state, normal taking off and landing can be realized under the condition of insufficient space of a take-off and landing field, and the requirements of relevant geometric indexes of a carrier-based aircraft are easily met; make VTOL fixed wing unmanned aerial vehicle possess bigger aspect ratio, when improving the time spent performance, satisfy the relevant restriction requirement in airport.
In the description of the present invention, it is to be understood that the terms "center", "longitudinal", "lateral", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", and the like, indicate orientations or positional relationships based on those shown in the drawings, and are used merely for convenience in describing the present invention and for simplicity in description, and do not indicate or imply that the referenced devices or elements must have a particular orientation, be constructed and operated in a particular orientation, and thus, are not to be construed as limiting the present invention; furthermore, the terms "a" and "an" 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 the terms "mounted," "connected," and "disposed" are to be construed broadly and may be, for example, fixedly connected, disposed, detachably connected, disposed, or integrally connected and disposed unless otherwise explicitly stated or limited; can be mechanically or electrically connected; the two elements can be directly connected, indirectly connected through an intermediate medium, or communicated with each other inside; the specific meanings of the above terms in the present invention can be understood by those skilled in the art according to specific situations.
The foregoing shows and describes the general principles, principal features and advantages of the invention; it should be understood by those skilled in the art that the above embodiments do not limit the present invention in any way, and all technical solutions obtained by using equivalent alternatives or equivalent variations fall within the scope of the present invention.
Claims (10)
1. A modularized canard layout vertical take-off and landing fixed wing unmanned aerial vehicle is characterized by comprising a body, 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 body close to the rear end of the body is connected with the center 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 used for driving the outer wing sections to fold or unfold; a tail pushing engine is arranged at the rear end of the machine body, and a tail pushing propeller is mounted on an output shaft of the tail pushing engine; the aircraft nose is arranged at the front end of the aircraft body, duck wings are respectively arranged on two sides of the aircraft nose, the two sides of the aircraft body are respectively provided with a vertical rod, the front end of the vertical rod is connected with the duck wings, the top of the vertical rod close to the rear end of the vertical rod is connected with the middle wing section, and a plurality of rotor wing power systems are symmetrically arranged on the two vertical 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 an undercarriage.
2. A modular canard configuration VTOL fixed wing UAV according to claim 1, wherein there are three rotor power systems on top of each droop mast, two of them being located at the top of the droop mast between the midspan and the canard, the other being located at the top of the rear end of the droop mast.
3. The modular canard configuration VTOL fixed-wing UAV according to claim 1 or 2, wherein the rotor power system is an electric rotor power system, the tail-push engine is a fuel-oil tail-push engine, an oil tank and a battery pack for supplying power are arranged inside the fuselage, and an oil tank cover is arranged on the top of the fuselage.
4. The vertical take-off and landing fixed-wing unmanned aerial vehicle with the modular canard layout is characterized in that a first plurality of 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 second plurality of through holes correspondingly matched with the first plurality of through holes are formed in the bottom of the unmanned aerial vehicle body, and the unmanned aerial vehicle body and the middle wing section are detachably connected through bolt and nut assemblies penetrating through the 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 plurality of second through holes.
5. The vertical take-off and landing fixed-wing unmanned aerial vehicle with the modular duck-type layout as claimed in claim 1, wherein the outer side surfaces of the middle wing section main beam and the middle wing section secondary 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 and the self-locking nuts are detachably connected 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 unmanned aerial vehicle with the modular canard layout and the fixed wings capable of taking off and landing vertically is characterized in that one end, far away from a nose, of each canard wing is provided with a sleeve, a carbon tube is arranged at the front end of each vertical rod, and the carbon tube at the front end of each vertical rod is inserted into the sleeve of each canard wing and is detachably connected with the canard wing through a plurality of screws; the aircraft nose is characterized in that a fuselage end plate is arranged on the end face of the front end of the fuselage, a front fuselage cover is arranged at the top of the fuselage close to the front end of the fuselage, a nose end plate is arranged at the connecting end of the fuselage and the fuselage, and the fuselage end plate and the nose end plate are detachably connected through a plurality of screws.
7. The modular canard configuration vertical take-off and landing fixed wing drone of claim 1, wherein the vertical fin and landing gear are detachably connected to the vertical rod through a plurality of screws, and rubber pads are disposed at bottom ends of the vertical fin and landing gear, respectively.
8. The vertical take-off and landing fixed wing unmanned aerial vehicle with the modular duck type layout as claimed in claim 1, wherein the wing body driving mechanism comprises a driving rotating mechanism and a driven rotating mechanism, the driving rotating mechanism comprises a girder middle wing lug and a girder outer wing lug, the girder middle wing lug is installed on the inner side surface of a middle wing section girder, the girder outer wing lug is installed on the inner side surface of an outer wing section girder, the girder outer wing lug is rotatably connected with the top of the girder middle wing lug through a hinge, an arc-shaped sliding limiting hole is formed in the bottom of the girder middle wing lug, a linear steering engine is arranged between the girder middle wing lug and the girder outer wing lug, the tail end of the linear steering engine is rotatably connected with the top of the girder outer wing lug, and the end part of an actuating rod of the linear steering engine is slidably connected in the sliding limiting hole; the driven rotating mechanism comprises a aileron middle wing lug and an aileron outer wing lug, the aileron middle wing lug is arranged on the inner side surface of the middle wing section aileron, the aileron outer wing lug is arranged on the inner side surface of the outer wing section aileron, and the aileron outer wing lug is rotatably connected with the top of the aileron middle wing lug through a hinge.
9. The vertical take-off and landing fixed-wing unmanned aerial vehicle with the modular duck-type layout as claimed in claim 8, wherein the end of the main beam middle wing tab facing the main beam outer wing tab has two side walls, the main beam outer wing tab is rotatably connected between the two side walls at the top of the main beam middle wing tab through a hinge, the two side walls at the bottom of the main beam middle wing tab are respectively provided with arc-shaped sliding limiting holes corresponding to each other, and the end of the actuating rod of the linear steering engine is located between the two side walls and is slidably connected in the two sliding limiting holes.
10. The VTOL fixed wing UAV of claim 9, wherein the actuator rod end of the linear actuator has a tube, the axis of the tube is perpendicular to the axis of the actuator rod, the tube is located between the sliding limit holes of the two sidewalls and the length of the tube is less than the distance between the two sidewalls, a rotating shaft is arranged in the sliding limit holes of the two sidewalls in a sliding manner, the rotating shaft movably penetrates through the tube at the actuator rod end of the linear actuator rod, one end of the rotating shaft has a limit piece, a threaded hole is arranged on the other end face of the rotating shaft, the threaded hole is connected with a limit bolt, a locking piece is movably sleeved on a screw rod of the limit bolt, and the limit piece and the locking piece are respectively located on the outer side faces of the two sidewalls of the middle wing ear piece of the main beam.
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| CN202111454185.XA CN113955092B (en) | 2021-12-01 | 2021-12-01 | Vertical take-off and landing fixed wing unmanned aerial vehicle with modularized duck-type layout |
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| CN113955092B (en) | 2023-09-26 |
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