CN107697268B - Express delivery unmanned aerial vehicle - Google Patents
Express delivery unmanned aerial vehicle Download PDFInfo
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- CN107697268B CN107697268B CN201710604628.6A CN201710604628A CN107697268B CN 107697268 B CN107697268 B CN 107697268B CN 201710604628 A CN201710604628 A CN 201710604628A CN 107697268 B CN107697268 B CN 107697268B
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- 230000005484 gravity Effects 0.000 claims abstract description 10
- 239000006261 foam material Substances 0.000 claims abstract description 5
- 230000008093 supporting effect Effects 0.000 claims abstract description 5
- 230000000712 assembly Effects 0.000 claims description 13
- 238000000429 assembly Methods 0.000 claims description 13
- 230000003014 reinforcing effect Effects 0.000 claims description 10
- 238000009434 installation Methods 0.000 claims description 7
- 230000003139 buffering effect Effects 0.000 claims description 3
- 230000000694 effects Effects 0.000 abstract description 2
- RZVHIXYEVGDQDX-UHFFFAOYSA-N 9,10-anthraquinone Chemical compound C1=CC=C2C(=O)C3=CC=CC=C3C(=O)C2=C1 RZVHIXYEVGDQDX-UHFFFAOYSA-N 0.000 description 6
- 229920000049 Carbon (fiber) Polymers 0.000 description 2
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/10—Shape of wings
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/22—Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft
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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
- B64D27/24—Aircraft characterised by the type or position of power plants using steam or spring force
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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
- B64D45/00—Aircraft indicators or protectors not otherwise provided for
- B64D45/04—Landing aids; Safety measures to prevent collision with earth's surface
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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
- B64D9/00—Equipment for handling freight; Equipment for facilitating passenger embarkation or the like
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U10/00—Type of UAV
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U50/00—Propulsion; Power supply
- B64U50/10—Propulsion
- B64U50/19—Propulsion using electrically powered motors
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U2101/00—UAVs specially adapted for particular uses or applications
- B64U2101/60—UAVs specially adapted for particular uses or applications for transporting passengers; for transporting goods other than weapons
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Abstract
The utility model provides an express delivery unmanned aerial vehicle, fixed wing power component installs in the fuselage front end. The two groups of rotors are respectively arranged on the lower surfaces of the left wing and the right wing. The express delivery cabin is hung below the machine body through an express delivery cabin hanging frame arranged on the lower surface of the gravity center part of the machine body. The fuselage is in the level state in the vertical take-off and landing stage, changes the angle of attack of cruising stage and is 3.5. When different express delivery cabins are selected, the distance between pulleys on two sides of the express delivery cabin body is adjusted by adjusting the screwing quantity of screws on two ends of the express delivery cabin body, and the cooperation between the pulleys on two sides and the guide rail is met. Four landing buffer strips made of rigid foam materials are uniformly distributed on the bottom surface of the express delivery cabin, so that a buffer effect is achieved when the unmanned aerial vehicle lands, and a supporting effect is achieved when the unmanned aerial vehicle takes off. According to the utility model, different express delivery cabins can be selected for different types of express delivery packages, so that a plurality of express delivery packages can be transported at one time, and the remote quick dispatch can be realized, and the dispatch economy is improved.
Description
Technical Field
The utility model belongs to the technical field of unmanned aerial vehicle application, and particularly relates to a compound layout express unmanned aerial vehicle.
Background
With the rapid development of internet technology, online shopping becomes an increasingly popular choice, and rapid development of express business follows. The conventional express delivery mode has a plurality of problems which are difficult to solve, the bottleneck of logistics delivery of the last kilometer is a common problem faced by express enterprises, and in addition, the delivery timeliness and the terminal user experience are also main problems faced by the express enterprises.
In the research of online shopping commodities, most packages are light-weight small packages, the small packages are not heavy medium packages, the large-size packages with heavy weight are few, and how to quickly and safely send the medium and small packages to customers is achieved, so that satisfaction of vast customers is achieved, and the technical problem to be solved is needed at present. And (3) promoting new operation modes of the express packages according to new market demands of the express packages.
At present, most of express delivery unmanned aerial vehicles are multiaxial rotor unmanned aerial vehicles, carry nonstandard storage tank, generally only can carry an express delivery, and availability factor is very low, and the dismantlement mode is not simple and convenient. Moreover, as the multi-rotor unmanned aerial vehicle has short endurance time and low flying speed, the unmanned aerial vehicle can only make ultra-short distance transportation, and the radius of activity is very small.
The utility model patent with application number 2016205131.1 provides an express unmanned aerial vehicle, and the unmanned aerial vehicle adopts a conventional fixed wing and four-rotor tilting rotor mode, and a cargo hold is connected with a beam through lugs. The disadvantage is that the existing tilting rotor technology is not mature, and the flying state is unsafe; in addition, this connection of the cargo compartment to the girder is inconvenient.
The utility model patent with the application number of 201620697179.5 provides a small-sized vertical take-off and landing express unmanned aerial vehicle, wherein the unmanned aerial vehicle adopts a tilting wing mode, and a power system adopts a three-rotor wing model. The three-rotor-wing type helicopter has the defects that the three-rotor-wing mode is unstable in heading at the vertical take-off and landing stage, the tilting mechanism is complex, the tilting wing control mode is immature, and great potential safety hazards exist.
Today, when delivering timeliness and end user experience are taught, in the face of express demands of massive packages, a novel express delivery mode with high timeliness, large delivery capacity, wide coverage range and convenience in taking and placing of express packages is provided.
Disclosure of Invention
In order to overcome the defects of potential safety hazard and low delivery efficiency in the prior art, the utility model provides an express unmanned aerial vehicle
The utility model comprises a fuselage, wings, tail wings, a fixed wing power assembly, a front left rotor assembly, a front right rotor assembly, a rear left rotor assembly, an express cabin and an express cabin hanging frame. Wherein: the fixed wing power assembly is arranged at the front end of the machine body. The two groups of rotors are respectively arranged on the lower surfaces of the left wing and the right wing, and the spreading position on each wing is 16% of the spreading length of the wing root of the wing. Two rotor wing assemblies are respectively arranged in the two groups of rotor wings; the two rotor wing assemblies are respectively arranged at two ends of the horn, and a left front rotor wing assembly and a left rear rotor wing assembly are formed at one side of the left wing; a right front rotor assembly and a right rear rotor assembly are formed on one side of the right wing. The express delivery cabin is hung below the machine body through an express delivery cabin hanging frame arranged on the lower surface of the gravity center part of the machine body. The fuselage is in a horizontal state in the vertical take-off and landing stage, and the attack angle for turning into the cruising stage is 3.5 degrees. The fuselage includes a fuselage head, a fuselage middle, and a fuselage tail. The installation angle alpha of the wing and the tail wing is 2.5-5 degrees.
The left wing and the right wing are fixedly connected with a main beam positioned at the position 26% away from the front end of the main body through wing main beams respectively; the wing girder is positioned at the 1/4 chord length of the wing. The left wing and the right wing are rectangular flat wings, the aspect ratio is 8, and the wing area is 1.84m 2 。
The distance between the inner end face and the outer end face of the left wing aileron and the wing root is 27.5% and 47.5% of the span length respectively. The distance between the inner end face and the outer end face of the right wing aileron and the wing root is 27.5% and 47.5% of the span length respectively. The chord width of each aileron is 1/4 chord length.
And the vertical tail wing of the tail wing is connected with the tail part of the machine body through a main beam positioned at the 1/4 chord length of the root of the vertical tail wing. The vertical tail plane is trapezoidal in shape. Vertical tail area 0.13m 2 The root-to-tip ratio was 1.6. The chord direction width of the rudder at the tail end of the vertical tail wing is 1/4 chord length of the vertical tail wing, and the height is equal to the vertical tail height; the plane shape of the horizontal tail fin is trapezoid, the aspect ratio is 3.5, and the area of the horizontal tail fin is 0.337m 2 The root to tip ratio was 1.45. The extension length of the elevator positioned at the rear edge of the horizontal tail wing is the same as that of the horizontal tail wing; the maximum chord-wise width of the elevator is positioned at the root of the horizontal tail wing and is 32.1% of the chord length of the root of the horizontal tail wing; the chord-wise minimum width is located at the horizontal tail wing tip and is 31.7% of the horizontal tail wing tip chord length.
The left rotor arm is installed at a span length of 16% from the wing root in the wingspan direction of the left machine and is fixed on the lower surface of the left wing. The right rotor arm is installed at the extension position of 16% of the wing root in the wingspan direction of the right machine and is fixed on the lower surface of the right wing. The 1/2 part of the length of the left rotor arm and the right rotor arm after installation corresponds to the gravity center position of the express unmanned aerial vehicle.
The distance between the front end of the left rotor arm and the front edge of the left wing and the distance between the rear end of the left rotor arm and the rear edge of the left wing are both larger than the radius of the propeller; the distance between the front end of the right rotor arm and the front edge of the right wing and the distance between the rear end of the right rotor arm and the rear edge of the right wing are both larger than the radius of the propeller.
The express cabin hanging frame is of a plate frame structure and comprises a plurality of cross beams and a pair of guide rails which are parallel to each other. The pair of guide rails are respectively fixed on the lower surfaces of the two ends of the plurality of cross beams; a slideway matched with a pulley on the express cabin is arranged on the corresponding surface between the pair of guide rails; and positioning bolts are arranged on the slide ways to prevent the express cabin from sliding back and forth on the slide ways.
The express delivery cabin comprises an express delivery cabin body, two groups of pulley assemblies and landing buffer strips. The middle part of the upper cover of the express cabin body is provided with a split cabin door. Reinforcing ribs are respectively fixed at two ends of the inner surface of the upper cover of the express cabin body; the reinforcing rib is provided with a through hole with internal threads. The two groups of pulley assemblies are symmetrically arranged on two sides of the express cabin body through fixing plates, and mounting holes at two ends of the fixing plates are concentric with the internal thread through holes on the reinforcing ribs respectively. A plurality of pulleys in each pulley assembly are arranged on the surface of the fixed plate through wheel shafts;
the wheel shaft is a screw, the root of the screw is a polished rod, the fixed plate is fixedly connected with the express cabin body through the screw, and the polished rod at the root is used as the wheel shaft of the pulley. The length of the two screws used for connecting the two ends of the fixing plate is the sum of the width of the express cabin body and the thickness of the fixing plate. When the overall dimension of the selected express cabin is smaller, the distance between pulleys on two sides of the express cabin body is adjusted by adjusting the screwing quantity of the two screws which are connected with the fixing plate and the two ends of the express cabin body, so that the cooperation between the pulleys on two sides and the guide rail is satisfied.
The express delivery cabin is 0.5-1 m long, 0.3-0.5 m wide and 0.25-0.4 m high. The length of the express cabin pulley assembly is 0.2-0.35 m.
Four landing buffer strips made of rigid foam materials are uniformly distributed on the bottom surface of the express cabin; the landing buffer strips are arranged on the bottom surface of the express delivery cabin in parallel, and 0.1 meter is arranged between two adjacent landing buffer strips. The landing buffer strip plays a role in buffering when being used for unmanned aerial vehicle landing, and plays a role in supporting when unmanned aerial vehicle takes off simultaneously.
According to the utility model, different express delivery cabins can be selected for different types of express delivery packages, so that a plurality of express delivery packages can be transported at one time, and the remote rapid dispatch can be realized.
Compared with the prior art, the utility model has the following advantages:
the express delivery cabin is fast and convenient to disassemble and assemble. Express delivery cabin pulley assembly is installed to express delivery cabin body both sides, installs the roller pulley on the express delivery cabin pulley assembly, and express delivery cabin pulley assembly is connected with express delivery cabin guide rail on the organism, rolls at the inside express delivery cabin guide rail through the roller pulley and realizes dismouting express delivery cabin, carries out spacingly to the express delivery cabin pulley through the bolt at the express delivery cabin guide rail end.
The express delivery cabin can be used in various modes. The requirements of different types of express packages on the conveying environment are different, and the utility model improves the dispatching economy by selecting different express cabin bodies.
The landing buffer strip and the express cabin are integrated, so that the landing gear is simplified, and the weight of the aircraft structure is reduced. The aircraft has simple requirements on taking off and landing environments, so that landing gears are not specially designed for the aircraft, but the bottom of the cabin body of the express cabin is provided with the buffer structure made of hard foam materials, and the buffer structure and the express cabin play a supporting role on the aircraft, so that the structural weight of the aircraft is reduced.
The utility model has the characteristic of wide effective coverage range. The aircraft takes off and land in a rotor wing mode, cruises and flies in a fixed wing mode, and the rotor wing takes off and land in a mode with less time and lower energy; most of energy is used for the fixed-wing cruising mode, and the fixed-wing cruising mode cruises fast, and low in power consumption and long in duration, so that the effective coverage area of the aircraft is large, remote express delivery can be carried out, and the safety of unmanned aerial vehicle delivery is improved.
Drawings
FIG. 1 is a schematic diagram of the structure of the present utility model;
fig. 2 is a schematic structural view of an express delivery cabin;
FIG. 3 is a bottom view of FIG. 2;
fig. 4 is a schematic structural view of the express delivery cabin guide rail;
fig. 5 is a schematic structural view of the express cabin pulley assembly.
In the figure: 1. a body; 2. a wing; 3. a tail wing; 4. a left rotor arm; 5. a right rotor arm; 6. a fixed wing power assembly; 7. a left front rotor assembly; 8. a right front rotor assembly; 9. a right rear rotor assembly; 10. a left rear rotor assembly; 11. a flight control system; 12. a battery compartment; 13. express cabin hanging rack; 14. express delivery cabin guide rail beam; 15. a guide rail; 16. express delivery cabin; 17. express cabin pulley assembly; 18. pulley assembly fixed plate; 19. a pulley; 20. landing buffer bars;
Detailed Description
The embodiment is a compound overall arrangement express delivery unmanned aerial vehicle, include: fuselage 1, wing 2, fin 3, left rotor arm 4, right rotor arm 5, fixed wing power pack 6, left front rotor assembly 7, right front rotor assembly 8, right back rotor assembly 9, left back rotor assembly 10, flight control system 11, battery compartment 12, express delivery cabin 16 and express delivery cabin stores pylon 13.
Wherein: a fixed wing power assembly 6 is mounted at the forward end of the fuselage 1. The two groups of rotors are respectively arranged on the lower surfaces of the left wing and the right wing, and the spreading position on each wing is 16% of the spreading length of the wing root of the wing. Two rotor assemblies are respectively arranged in the two groups of rotors. The two rotor wing assemblies are respectively arranged at two ends of the horn, and a left front rotor wing assembly 7 and a left rear rotor wing assembly 10 are formed at one side of the left wing; a right front rotor assembly 8 and a right rear rotor assembly 9 are formed on one side of the right wing. The express delivery cabin 16 is suspended below the fuselage by an express delivery cabin hanger 13 mounted on the lower surface of the center of gravity of the fuselage.
The fuselage 1 is in a horizontal state in the vertical take-off and landing phase, and the attack angle for turning into the cruising phase is 3.5 degrees. The machine body 1 comprises a machine body head part, a machine body middle part and a machine body tail part; wherein:
the wing 2 comprises a left wing and a right wing; the left wing and the right wing are fixedly connected with a main beam positioned at the position 26% away from the front end of the main body through wing main beams respectively; the wing girder is positioned at the 1/4 chord length of the wing. The wing 2 is a rectangular flat wing, the aspect ratio is 8, and the wing area is 1.84m 2 . Ailerons are respectively arranged at the rear edges of the left wing and the right wing; the extension of the inner side end surface of each aileron from the wing root is 27.5%, and the extension of the outer side end surface of each aileron from the wing root is 47.5%; the chord width of each aileron is 1/4 chord length.
The tail 3 includes a vertical tail and a horizontal tail. The vertical tail wing is connected with the tail of the machine body through a main beam positioned at the 1/4 chord length of the root of the vertical tail wing, and is limited through bolts. The horizontal tail fin is fixedly arranged at the upper end of the vertical tail fin; the plane shape of the horizontal tail fin is trapezoid, the aspect ratio is 3.5, and the area of the horizontal tail fin is 0.337m 2 The root to tip ratio was 1.45. The extension length of the elevator positioned at the rear edge of the horizontal tail wing is the same as that of the horizontal tail wing; the maximum chord-wise width of the elevator is positioned at the root of the horizontal tail wing and is 32.1% of the chord length of the root of the horizontal tail wing; the chord-wise minimum width is located at the horizontal tail wing tip and is 31.7% of the horizontal tail wing tip chord length. Elevators are used to adjust the longitudinal attitude of an aircraft during flight.
The vertical tail plane is trapezoidal in shape. Vertical tail area 0.13m 2 The root-to-tip ratio was 1.6. The tail end of the vertical tail fin is provided with a rudder. The chord direction width of the rudder is 1/4 chord length of the vertical tail, and the height is equal to the vertical tail height; rudders are used to adjust the attitude of a heading during the flight of an aircraft.
The wing 2 and the tail wing 3 both have a mounting angle alpha; the installation angle alpha is 2.5-5 degrees. The mounting angle α described in this embodiment is 3 °
The left rotor arm 4 is installed at the extension position of 16% of the wing root from the wingspan direction of the left machine, and is connected with the lower surface of the left wing through bolts. The rotor assemblies are respectively installed at two ends of the left rotor arm, the left front rotor assembly 7 is installed at one end of the head of the left rotor arm, and the left rear rotor assembly 10 is installed at one end of the tail of the left rotor arm.
The right rotor arm 5 is installed at the extension position of 16% of the wing root from the wing span direction of the right machine, and is connected with the lower surface of the right wing through bolts. The rotor assembly is installed respectively at the both ends of right rotor arm, installs the front right rotor assembly 8 for right rotor arm aircraft nose one end, installs the rear right rotor assembly 9 for right rotor arm tail one end.
The lengths of the left rotor arm 4 and the right rotor arm 5 need to meet the following requirements: the 1/2 part of the length of the left rotor arm and the length of the right rotor arm after installation corresponds to the gravity center position of the express unmanned aerial vehicle, and the left rotor arm and the right rotor arm after installation enable
The distance between the front end of the left rotor arm and the front edge of the left wing and the distance between the rear end of the left rotor arm and the rear edge of the left wing are both larger than the radius of the propeller; the distance between the front end of the right rotor arm and the front edge of the right wing and the distance between the rear end of the right rotor arm and the rear edge of the right wing are both larger than the radius of the propeller.
The front left rotor assembly 7, the front right rotor assembly 8, the rear right rotor assembly 9 and the rear left rotor assembly 10 all comprise driving motors and propellers. The left front rotor wing assembly 7 and the left rear rotor wing assembly 10 are fixedly connected with the motor base of the left rotor wing arm 4; the propellers are fixedly connected with the output shafts of the corresponding driving motors respectively, and the propellers are all JXF3095 carbon fiber propellers. The right front rotor wing assembly 8 and the right rear rotor wing assembly 9 are respectively and fixedly connected with a motor base of the right rotor wing arm; the screw is fixedly connected with the output shaft of the corresponding driving motor respectively. The four propellers are positioned on the same plane to form a propeller plane; in the vertical take-off, landing and plane flight stages, the plane of the propeller is in a horizontal state.
The fixed wing power assembly 6 includes a drive motor and a propeller. The driving motor is fixedly connected with the machine body through a motor base; the propeller is fixedly connected with an output shaft of a driving motor in the fixed wing power assembly. The fixed wing power assembly 6 provides power for the unmanned aerial vehicle in the flying stage of the fixed wing, and the propeller is a JXF2310 carbon fiber propeller.
The flight control system 11 comprises a flight control board; the flight control board is arranged at the gravity center position of the machine body 1; and the flight control plate is always parallel to the plane of the propeller.
The express cabin hanging frame 13 is of a plate frame structure and comprises a plurality of cross beams 14 and a pair of guide rails 15 which are parallel to each other. The pair of guide rails are respectively fixed on the lower surfaces of the two ends of the plurality of cross beams. And a slideway is arranged on the corresponding surface between the pair of guide rails 15 and is used for placing a pulley on the express cabin 16 and positioning the pulley by bolts so as to prevent the express cabin from sliding back and forth on the slideway.
The express delivery cabin 16 comprises an express delivery cabin body, two groups of pulley assemblies 17 and a landing buffer strip 20. The middle part of the upper cover of the express cabin body is provided with a split cabin door, so that articles can be conveniently taken and placed. Reinforcing ribs are respectively fixed at two ends of the inner surface of the upper cover of the express cabin body, and the length of each reinforcing rib is slightly smaller than the width of the express cabin body; the reinforcing rib is provided with a through hole with internal threads. The two groups of pulley assemblies are symmetrically arranged on two sides of the express cabin body through fixing plates 18, and mounting holes at two ends of the fixing plates are concentric with the internal thread through holes on the reinforcing ribs respectively. A plurality of pulleys in each pulley assembly are arranged on the surface of the fixed plate through wheel shafts; the wheel shaft is a screw, the root of the screw is a polish rod, the end of the screw is a threaded rod, the fixing plate 18 is fixedly connected with the express cabin body through the screw, and the polish rod at the root is used as the wheel shaft of the pulley. The length of the two screws used for connecting the two ends of the fixing plate is the sum of the width of the express cabin body and the thickness of the fixing plate.
Four landing buffer strips 20 made of rigid foam materials are uniformly distributed on the bottom surface of the express delivery cabin 16; the landing buffers are arranged on the bottom surface of the express delivery cabin 16 in parallel, and 0.1 meter is arranged between two adjacent landing buffers. The landing buffer strip plays a role in buffering when being used for unmanned aerial vehicle landing, and plays a role in supporting when unmanned aerial vehicle takes off simultaneously.
In this embodiment, different sizes of express cabins are selected according to different transported cargoes. When the overall dimension of the selected express cabin is smaller, the distance between pulleys on two sides of the express cabin body is adjusted by adjusting the screwing quantity of the two screws which are connected with the fixing plate and the two ends of the express cabin body, and the cooperation between the pulleys on two sides and the guide rail 15 is met.
The express delivery cabin 16 has a length of 0.5-1 meter, a width of 0.3-0.5 meter and a height of 0.25-0.4 meter.
The length of the express cabin pulley assembly 17 is 0.2-0.35 m.
The battery compartment 12 is disposed at the center of gravity of the machine body 1, and is used for installing a power battery and adjusting the center of gravity of the whole machine.
Claims (6)
1. The express unmanned aerial vehicle is characterized by comprising a fuselage, wings, tail wings, a fixed wing power assembly, a front left rotor assembly, a front right rotor assembly, a rear left rotor assembly, an express cabin and an express cabin hanging frame; wherein: the fixed wing power assembly is arranged at the front end of the machine body; the two groups of rotors are respectively arranged on the lower surfaces of the left wing and the right wing, and the spreading position distance on each wing is 16% of the spreading length of the wing root of the wing; two rotor wing assemblies are respectively arranged in the two groups of rotor wings; the two rotor wing assemblies are respectively arranged at two ends of the horn, and a left front rotor wing assembly and a left rear rotor wing assembly are formed at one side of the left wing; a right front rotor assembly and a right rear rotor assembly are formed on one side of the right wing; the express cabin is hung below the machine body through an express cabin hanging frame arranged on the lower surface of the gravity center part of the machine body; the fuselage is in a horizontal state in a vertical take-off and landing stage, and the attack angle of the fuselage is 3.5 degrees in a cruise stage; the machine body comprises a machine body head part, a machine body middle part and a machine body tail part; the installation angle alpha of the wing and the tail wing is 2.5-5 degrees;
the left wing and the right wing are fixedly connected with a main beam positioned at the position 26% away from the front end of the main body through wing main beams respectively; the wing girder is positioned at the 1/4 chord length of the wing; the left wing and the right wing are rectangular flat wings, the aspect ratio is 8, and the wing areaAre all 1.84m 2 ；
The distance between the inner end face and the outer end face of the left wing aileron and the wing root is 27.5% and 47.5% of the span length respectively; the distance between the inner end face and the outer end face of the right wing aileron and the wing root is 27.5% and 47.5% of the span length respectively; the chord width of each aileron is 1/4 chord length;
the vertical tail wing of the tail wing is connected with the tail part of the machine body through a main beam positioned at the 1/4 chord length of the root of the vertical tail wing; the plane shape of the vertical tail fin is trapezoid; vertical tail area 0.13m 2 The root-tip ratio is 1.6; the chord direction width of the rudder at the tail end of the vertical tail wing is 1/4 chord length of the vertical tail wing, and the height is equal to the vertical tail height; the plane shape of the horizontal tail fin is trapezoid, the aspect ratio is 3.5, and the area of the horizontal tail fin is 0.337m 2 The root-tip ratio is 1.45; the extension length of the elevator positioned at the rear edge of the horizontal tail wing is the same as that of the horizontal tail wing; the maximum chord-wise width of the elevator is positioned at the root of the horizontal tail wing and is 32.1% of the chord length of the root of the horizontal tail wing; the chord-wise minimum width is positioned at the wing tip of the horizontal tail wing and is 31.7 percent of the chord length of the wing tip of the horizontal tail wing;
the left rotor wing arm is arranged at the extension position of 16% of the wing root in the wingspan direction of the left machine and is fixed on the lower surface of the left wing; the right rotor wing arm is arranged at the extension position of 16% of the wing root in the wingspan direction of the right machine and is fixed on the lower surface of the right wing; the 1/2 part of the length of the left rotor wing arm and the length of the right rotor wing arm after installation corresponds to the gravity center position of the express unmanned aerial vehicle;
the distance between the front end of the left rotor arm and the front edge of the left wing and the distance between the rear end of the left rotor arm and the rear edge of the left wing are both larger than the radius of the propeller; the distance between the front end of the right rotor arm and the front edge of the right wing and the distance between the rear end of the right rotor arm and the rear edge of the right wing are all larger than the radius of the propeller.
2. The express unmanned aerial vehicle of claim 1, wherein the express cabin hanger has a plate frame structure and comprises a plurality of cross beams and a pair of guide rails which are parallel to each other; the pair of guide rails are respectively fixed on the lower surfaces of the two ends of the plurality of cross beams; a slideway matched with a pulley on the express cabin is arranged on the corresponding surface between the pair of guide rails; and positioning bolts are arranged on the slide ways to prevent the express cabin from sliding back and forth on the slide ways.
3. The express delivery unmanned aerial vehicle of claim 1, wherein the express delivery cabin comprises an express delivery cabin body, two groups of pulley assemblies and a landing buffer strip; the middle part of the upper cover of the express cabin body is provided with a split cabin door; reinforcing ribs are respectively fixed at two ends of the inner surface of the upper cover of the express cabin body; the reinforcing rib is provided with a through hole with internal threads; the two groups of pulley assemblies are symmetrically arranged on two sides of the express cabin body through fixing plates, and mounting holes at two ends of the fixing plates are concentric with the internal thread through holes on the reinforcing ribs respectively; a plurality of pulleys in each pulley assembly are arranged on the surface of the fixed plate through wheel shafts.
4. The express unmanned aerial vehicle according to claim 3, wherein the wheel shaft is a screw, the root of the screw is a polished rod, the fixed plate is fixedly connected with the express cabin body through the screw, and the polished rod at the root is used as the wheel shaft of the pulley; the length of the two screws used for connecting the two ends of the fixing plate is the sum of the width of the express cabin body and the thickness of the fixing plate; when the overall dimension of the selected express cabin is smaller, the distance between pulleys on two sides of the express cabin body is adjusted by adjusting the screwing quantity of the two screws which are connected with the fixing plate and the two ends of the express cabin body, so that the cooperation between the pulleys on two sides and the guide rail is satisfied.
5. The express unmanned aerial vehicle of claim 3, wherein the express cabin has a length of 0.5-1 meter, a width of 0.3-0.5 meter, and a height of 0.25-0.4 meter; the length of the express cabin pulley component is 0.2-0.35 m.
6. The express unmanned aerial vehicle of claim 3, wherein four landing buffer strips made of rigid foam materials are uniformly distributed on the bottom surface of the express cabin; the landing buffer strips are arranged on the bottom surface of the express cabin in parallel, and 0.1 meter is arranged between two adjacent landing buffer strips; the landing buffer strip plays a role in buffering when being used for unmanned aerial vehicle landing, and plays a role in supporting when unmanned aerial vehicle takes off simultaneously.
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| CN108725787B (en) * | 2018-07-19 | 2024-01-16 | 广州天狼航空科技发展有限公司 | Unmanned aerial vehicle for carrying express delivery |
| CN108791868A (en) * | 2018-07-31 | 2018-11-13 | 刘浩然 | A kind of new transport unmanned plane of safety and stability |
| CN109178301A (en) * | 2018-09-04 | 2019-01-11 | 西北工业大学 | A kind of fixed-wing rotor mixing unmanned plane |
| CN109552638A (en) * | 2018-11-29 | 2019-04-02 | 江苏鸿鹄无人机应用科技有限公司 | A kind of balancing device of unmanned plane |
| CN111509153B (en) * | 2019-01-31 | 2022-12-16 | 深圳市卓派自动化技术有限公司 | Battery, parcel case, unmanned aerial vehicle, transportation center and automatic access cabinet |
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| CN206068150U (en) * | 2016-09-23 | 2017-04-05 | 西北工业大学 | Combined type layout vertically taking off and landing flyer |
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| FR2802893B1 (en) * | 1999-12-22 | 2002-05-03 | Inst Rech Developpement Ird | REDUCED-SIZE RADIO-CONTROLLED FLYING APPARATUS |
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| US20160355259A1 (en) * | 2015-06-03 | 2016-12-08 | Google Inc. | Hardpoint Strain Reliefs |
| CN105923163B (en) * | 2016-06-01 | 2018-05-08 | 北京小米移动软件有限公司 | Transport shelf and unmanned plane |
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