CN110844062B

CN110844062B - Modular multipurpose unmanned aerial vehicle with composite wing layout

Info

Publication number: CN110844062B
Application number: CN201910978225.7A
Authority: CN
Inventors: 马超; 姚天; 梅柯; 袁正明; 慈宬嶂; 钟宏
Original assignee: Civil Aviation University of China
Current assignee: Civil Aviation University of China
Priority date: 2019-10-15
Filing date: 2019-10-15
Publication date: 2023-01-17
Anticipated expiration: 2039-10-15
Also published as: CN110844062A

Abstract

The invention provides a modularized multipurpose unmanned aerial vehicle with a composite wing layout, which comprises a rack platform, wherein a machine shell is installed at the top of the rack platform, wings are installed on two sides of the rack platform, a flying wing steering engine is installed on each wing, an undercarriage and a horn are respectively installed on two sides of the bottom of the rack platform, a tail horn is installed in the middle of the rack platform, the two undercarriages and the two horns are symmetrical about the center of the tail horn, one end of the tail horn is connected to a vector power device, the other end of the tail horn is connected to the rack platform through a folding piece, and each vector power device comprises a tilting mechanism and a motor. The modularized multipurpose unmanned aerial vehicle with the composite wing layout can be used for executing special tasks by independently using the rotor wing units, can be connected with the rotor wing units in parallel to form the dual-mode unmanned aerial vehicle with the composite wing layout, and carries different devices to execute diversified tasks according to task requirements.

Description

Modular multipurpose unmanned aerial vehicle with composite wing layout

Technical Field

The invention belongs to the technical field of design and application of unmanned aerial vehicles, and particularly relates to a modularized multipurpose unmanned aerial vehicle with a composite wing layout.

Background

Under the current environment of the big development of unmanned aerial vehicles, a large number of unmanned aerial vehicles with different subdivision tasks and large overlapping occur, and a unit needs to purchase different unmanned aerial vehicles aiming at different subdivision tasks, so that the problems of high use cost, high maintenance cost, resource waste and the like exist; when carrying out different tasks, rotor overall arrangement unmanned aerial vehicle respectively has unique advantage but opposite with fixed wing overall arrangement unmanned aerial vehicle, and the technical scheme that combines together the two has many rotors fixed wing composite configuration and verts two kinds of rotor fixed wing composite configuration at present. The two configurations have the advantages of vertical take-off and landing, strong cruising ability and wide cruising range, but the traditional multi-rotor fixed wing composite configuration rotor unit and the fixed wing unit have serious pneumatic interference, obvious structural waste and low efficiency of a power system; and its tilting mechanism structure of rotor fixed wing composite configuration that verts is complicated, and the wing can cause serious start-up to disturb under the VTOL mode. A better solution has not yet emerged for composite wing configurations.

Disclosure of Invention

In view of this, the present invention provides a modular multi-purpose unmanned aerial vehicle with a composite wing layout, so as to solve the problems of serious pneumatic interference between a rotor unit and a fixed wing unit and serious structural waste of the conventional unmanned aerial vehicle with composite wings.

In order to achieve the purpose, the technical scheme of the invention is realized as follows:

the cross section of the rack platform is of a central symmetrical structure, a machine shell is installed at the top of the rack platform, wings are installed on two sides of the rack platform, the wings comprise wing middle sections and wing outer sections, the wing outer sections are fixedly connected to the wing middle sections through the wing folding pieces, each wing is provided with a flying wing steering engine, two sides of the bottom of the rack platform are respectively provided with one landing gear and one arm, the tail wings are installed in the middle, the two landing gears and the two arms are symmetrical about the tail wing center, the first tilting steering engine SE3 and the first motor M1 are installed on the tail wings, one end of each arm is connected to the motor seat, the other end of each arm is connected to the rack platform through the folding pieces, a motor and a tilting steering engine are installed in each motor seat, a control is installed inside the rack platform, a flying control power module BEC, the first electronic speed regulator ESC1, the second electronic speed regulator ESC2, the third electronic speed regulator ESC3 and a remote control receiver RC are connected to the first electronic speed regulator ESC1, the second electronic speed regulator ESC2, the third electronic speed regulator BEC, the first tilting steering engine is connected to the first remote control motor, and the first remote control receiver, and the first tilting steering engine remote control module.

Furthermore, the wing comprises a left wing and a right wing, a first all-wing steering engine SE1 is installed on the left wing, a second all-wing steering engine SE2 is installed on the right wing, and the first all-wing steering engine SE1 and the second all-wing steering engine SE2 are in signal connection with the flight control.

Further, the models of the first electronic speed regulator ESC1, the second electronic speed regulator ESC2 and the third electronic speed regulator ESC3 are the same and are all brushless electric regulation.

Furthermore, the motor cabinet comprises left frame and right frame, and left frame internally mounted is No. two tilting steering wheel SE4 and No. two motor M2, and right frame internally mounted is No. three tilting steering wheel SE5 and No. three motor M3.

Further, vector power system includes tilting mechanism and brushless motor, and tilting mechanism includes the horn clamping piece, the gasket, the base that verts, the vector steering wheel that verts, turn to the piece and motor gasket, and tilting base bottom is through gasket fixed mounting horn clamping piece, and the steering wheel that verts is installed to the top vector, and the vector steering wheel that verts passes through steering piece fixed connection to brushless motor, is equipped with the motor gasket between brushless motor and the piece that turns to, and vector steering wheel signal connection that verts flies to accuse.

Further, install vector power system on two horn respectively, the steering wheel that corresponds the installation is No. four tilting steering wheel SE6 and No. five tilting steering wheel SE7 respectively, and No. four tilting steering wheel SE6 and No. five tilting steering wheel SE7 are signal connection to respectively flies to control.

Furthermore, the models of a first tilting steering engine SE3, a second tilting steering engine SE4, a third tilting steering engine SE5, a fourth tilting steering engine SE6 and a fifth tilting steering engine SE7 are the same and are LOBOT robot steering engines.

Furthermore, the model of the flight control is thunder pixhawk2, a port GND of the flight control is connected to a GND1 interface of a flight control power supply module BEC, an interface IN of the flight control power supply module BEC is connected to a pin 1 of a voltage stabilizer U1, the model of the voltage stabilizer U1 is LM2596S-ADJ, a third pin and a fifth pin of the voltage stabilizer U1 are both grounded, the first pin grounds the capacitor C2, the capacitor C2 is connected IN parallel with a capacitor C1, a second pin of the voltage stabilizer U1 is grounded through a diode D1, the second pin is grounded through a resistor R1 and a resistor R2, the resistor R1 is connected IN parallel with a capacitor CF, a fourth pin of the voltage stabilizer U1 is connected to a node between the resistor R1 and the resistor R2, a second pin of the voltage stabilizer U1 is grounded through a capacitor C3, the capacitor C3 is connected IN parallel with a capacitor C4, a second pin of the voltage stabilizer U1 is grounded through a resistor R3 and a diode D2, a second pin of the voltage stabilizer U1 is connected to a VCC interface of a first tilting steering engine SE3, a VCC interface of a second tilting steering engine SE4 and a tilting steering engine SE 5; a first pin of the voltage stabilizer U1 is respectively connected to an IN pin of a flight control power supply control module BEC, a VCC port of a first electronic speed regulator ESC1, a VCC port of a second electronic speed regulator ESC2 and a VCC port of a third electronic speed regulator ESC3, the first electronic speed regulator ESC1 is electrically connected to a first motor M1, the second electronic speed regulator ESC2 is electrically connected to a second motor M2, the third electronic speed regulator ESC3 is electrically connected to a third motor M3, a pin GND1 of the flight control power supply control module BEC is grounded, and a pin GND is respectively connected with a GND interface of a first tilting steering engine SE3, a GND interface of a second tilting steering engine SE4, a GND interface of a fourth tilting steering engine SE6 and a GND interface of a fifth tilting steering engine SE 7; a pin OUT of the flight control POWER supply control module BEC is respectively connected to a POWER port of a flight control pixhawk2, a VCC interface of a first flying wing steering engine SE1, a VCC interface of a second flying wing steering engine SE2, a VCC interface of a fourth tilting steering engine SE6 and a VCC interface of a fifth tilting steering engine SE 7; a port RCIN of the flight control pixhawk2 is connected to a remote control receiver RC through an SUBS bus, an output port OUT1 of the flight control pixhawk2 is connected to a SIGNAL port of a first flying wing steering engine SE1, an output port OUT2 is connected to a SIGNAL port of a second flying wing steering engine SE2, an output port OUT3 is connected to a SIGNAL port of a first electronic speed regulator ESC1, an output port OUT4 is connected to a SIGNAL port of a second electronic speed regulator ESC2, an output port OUT5 is connected to a SIGNAL port of a third electronic speed regulator ESC3, an output port OUT6 is connected to a SIGNAL port of a first tilting steering engine SE3, an output port OUT7 is connected to a SIGNAL port of a second tilting steering engine SE4, and an output port OUT8 is connected to a SIGNAL port of a third tilting steering engine SE 5; an output port AUX1 of the flight control pixhawk2 is connected to a SIGNAL port of a four-number tilting steering engine SE6, and an output port AUX2 is connected to a SIGNAL port of a five-number tilting steering engine SE 7.

Furthermore, the left wing comprises a main wing and a side wing, one side of the main wing is fixedly connected to the side wing through a wing folding piece, the other side of the main wing is fixedly connected to a front edge side plate, the front edge side plate is fixedly connected to a rear edge reinforcing piece of the machine shell through a main beam side plate, a middle section side plate and a machine shell reinforcing piece, the front edge side plate, the main beam side plate and the middle section side plate are all fixedly connected to the rack platform, and the machine shell reinforcing piece and the rear edge reinforcing piece of the machine shell are all fixedly connected to the machine shell.

Further, the rack platform comprises an upper rack plate and a lower rack plate, the undercarriage and the tilting steering engine are both mounted at the bottom of the lower rack plate, the top of the folding piece of the machine arm and the top of the tail machine arm are both fixedly connected to the upper rack plate, and the bottom of the folding piece of the machine arm and the bottom of the tail machine arm are both fixedly connected to the lower rack plate.

Compared with the prior art, the modular multipurpose unmanned aerial vehicle with the composite wing layout has the following advantages:

(1) The modularized multipurpose composite wing layout unmanned aerial vehicle is divided into the three-axis vector rotor wing unit and the modularized flying wing unit, the advantage of large internal space of the flying wing layout is reasonably utilized, the rotor wing frame is skillfully embedded into the wing body, two flying platforms are more thoroughly compounded, the problems of serious pneumatic interference and serious structural waste between the rotor wing unit and the fixed wing unit in the traditional composite wing structure are solved, the two sub-units are completely independent, and the task adaptability and diversity of the unmanned aerial vehicle are greatly improved.

(2) The modularized multipurpose unmanned aerial vehicle with the composite wing layout can be used for executing special tasks by independently using the rotor wing units, can be connected with the rotor wing units in parallel to form the dual-mode unmanned aerial vehicle with the composite wing layout, and carries different devices to execute diversified tasks according to task requirements.

(3) The modularized multipurpose composite wing layout unmanned aerial vehicle disclosed by the invention selects the sub-flight units or the parallel sub-units to execute tasks according to different task requirements through a modularized unit concept, so that the task adaptability of the unmanned aerial vehicle is improved, the use cost is reduced, and the combat efficiency and the use consumption ratio are improved.

Drawings

The accompanying drawings, which are incorporated in and constitute a part of this specification, illustrate an embodiment of the invention and, together with the description, serve to explain the invention and not to limit the invention. In the drawings:

fig. 1 is a schematic structural diagram of an unmanned aerial vehicle according to an embodiment of the present invention;

fig. 2 is a top view of an unmanned aerial vehicle according to an embodiment of the present invention;

fig. 3 is a schematic structural view of a rotor unit according to an embodiment of the present invention;

FIG. 4 is a schematic structural view of an airfoil according to an embodiment of the invention;

fig. 5 is a schematic structural diagram of a rack according to an embodiment of the present invention;

FIG. 6 is a schematic structural diagram of a vector power system according to an embodiment of the present invention;

fig. 7 is a schematic circuit diagram of a modular multipurpose composite wing layout drone according to an embodiment of the invention.

Description of reference numerals:

1-a rack upper plate; 2-a frame lower plate; 3-a tilt steering engine; 4-a landing gear; 5-vector power unit installation; 6-a machine arm; 7-a horn fold; 8-a rack platform; 9-tail boom; 10-a housing; 11-right wing; 12-left wing; 13-leading edge side panel; 14-main beam side panels; 15-middle section side plate; 16-a chassis reinforcement panel; 17-a casing trailing edge stiffener; 18-a main wing; 19-wing 19; 20-a folding member; 21-a frame; 22-longitudinal ribs; 23-transverse ribs; 24-a diverter blade; 25-vector tilting steering engine; 26-a tilt base; 27-a horn clip; 28-a brushless motor; 29-motor shim; 30-pad.

Detailed Description

It should be noted that the embodiments and features of the embodiments may be combined with each other without conflict.

In the description of the present invention, it is to be understood that the terms "central," "longitudinal," "lateral," "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," "outer," and the like are used in the orientations and positional relationships indicated in the drawings, which are based on the orientations and positional relationships indicated in the drawings, and are used for convenience in describing the present invention and for simplicity in description, but do not indicate or imply that the device or element so referred to must have a particular orientation, be constructed in a particular orientation, and be operated, and thus should not be construed as limiting the present invention. Furthermore, the terms "first", "second", etc. are used for descriptive purposes only and are not to be construed as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defined as "first," "second," etc. may explicitly or implicitly include one or more of that feature. In the description of the present invention, "a plurality" means two or more unless otherwise specified.

In the description of the present invention, it should be noted that, unless otherwise explicitly specified or limited, the terms "mounted," "connected," and "connected" are to be construed broadly and may be, for example, fixedly connected, detachably connected, or integrally connected; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meanings of the above terms in the present invention can be understood by those of ordinary skill in the art through specific situations.

The present invention will be described in detail below with reference to the accompanying drawings in conjunction with embodiments.

The noun explains:

a flight controller: referred to as flight control.

A modularized multipurpose unmanned plane with a composite wing layout comprises a rotor wing unit and a flying wing unit, wherein the rotor wing unit comprises a rack platform 8, tilting steering engines 3, landing gears 4, vector power device installation parts 5, arms 6 and arm folding parts 7, the cross section of the rack platform 8 is of a central symmetry structure, the landing gears 4 and the tilting steering engines 3 are respectively installed on two sides of the bottom of a lower plate 2 of the rack platform 8, one arm 6 is respectively installed on two sides of the rack platform 8 through one arm folding part 7, the vector power device installation part 5 is arranged at the other end of each arm 6 and used for installing a vector power system, a tail arm 9 is installed at the tail part of the rack platform 8, the two landing gears 4 and the two arms 6 are respectively symmetrical about the center of the tail arm 9, a first tilting steering engine SE3 and a first tilting motor M1 are installed on the tail arm 9,

the flying wing unit comprises a right wing 11, a left wing 12 and a machine shell 10, the machine shell 10 is installed at the top of the rack platform 8, the right wing 11 and the left wing 12 are installed on two sides of the rack platform 8 respectively, the structures of the right wing 11 and the left wing 12 are completely the same, a flying wing steering engine is installed on the right wing 11 and the left wing 12 respectively, a flying control power supply module BEC, a first electronic speed regulator ESC1, a second electronic speed regulator ESC2, a third electronic speed regulator ESC3 and a remote control receiver RC are installed inside the rack platform 8, the flying control is connected to the first electronic speed regulator ESC1, the second electronic speed regulator ESC2, the third electronic speed regulator ESC3, the remote control receiver RC, a tilting steering engine 3, the flying wing steering engine, the first tilting steering engine SE3, a first motor M1 and a motor of a vector power system through signals respectively, the flying control power supply module BEC is electrically connected to the remote control, and the remote control receiver RC signals are connected to a remote controller.

No. one all-wing aircraft steering engine SE1 is installed on the left wing 12, no. two all-wing aircraft steering engines SE2 are installed on the right wing 11, and the No. one all-wing aircraft steering engine SE1 and the No. two all-wing aircraft steering engines SE2 are in signal connection with flight control and are used for controlling the unmanned aerial vehicle to roll around the Y axis and keeping stability balance. Vector driving system is including tilting mechanism and brushless motor 28, tilting mechanism includes horn clamping piece 27, the gasket 30, tilt base 26, the vector steering wheel 25 that verts, turn to piece 24 and motor gasket, tilt base 26 bottom is through gasket 30 fixed mounting horn clamping piece 27, the steering wheel 25 that verts is installed to the top vector, the vector steering wheel 25 that verts is through turning to piece 24 fixed connection to brushless motor 28, brushless motor 28 and turning to be equipped with motor gasket 29 between the piece 24, vector steering wheel 25 signal connection to that verts flies to control.

The cross section of the steering sheet 24 is of a U-shaped structure, and two sides of the steering sheet 24 are respectively connected with two sides of the vector tilting steering engine 25.

Tilting steering engine 3 includes left frame and right frame, and No. two tilting steering engine SE4 of left frame internally mounted and No. two motor M2, no. three tilting steering engine SE5 of right frame internally mounted and No. three motor M3, no. two tilting steering engine SE4, no. two motor M2, no. three tilting steering engine SE5 and No. three equal signal connection of motor M3 to the flight control for keep unmanned aerial vehicle flight balance.

Install respectively on two horn 6 vector driving system, the steering wheel that corresponds the installation is four numbers steering wheel SE6 that verts and five numbers steering wheel SE7 that verts respectively, and four numbers steering wheel SE6 that verts and five numbers steering wheel SE7 that verts signal connection respectively fly to control for control unmanned aerial vehicle's flight direction.

No. one vert steering wheel SE3, no. two vert steering wheel SE4, no. three vert steering wheel SE5, no. four vert steering wheel SE6 and No. five model of verting steering wheel SE7 are the same, are LOBOT robot steering wheel.

The left wing 12 comprises a main wing 18 and a side wing 19, one side of the main wing 18 is fixedly connected to the side wing 19 through a wing folding piece 20, the other side of the main wing is fixedly connected to a front edge side plate 13, the front edge side plate 13 is fixedly connected to a casing rear edge reinforcing piece 17 through a main beam side plate 14, a middle section side plate 15 and a casing reinforcing piece 16, the front edge side plate 13, the main beam side plate 14 and the middle section side plate 15 are all fixedly connected to the rack platform 8, and the casing reinforcing piece 16 and the casing rear edge reinforcing piece 17 are all fixedly connected to the casing 10.

The wing folding piece 20 comprises a gasket, a steering connecting piece and a lock catch, the gasket is composed of an upper gasket and a lower gasket which correspond to each other in position, the upper gasket is installed above a wing keel, the steering connecting piece is installed at the bottom of the upper gasket, the lower gasket is installed below the wing keel, the lower gasket is used for installing the lock catch, and the lock catch is connected with the end portion of the steering connecting piece in a clamped mode.

The machine shell 10 is internally provided with a machine frame 21, the machine shell 10 adopts a hollow design and is formed by mutually intersecting and matching seven longitudinal ribs 22 and seven transverse ribs 23, and the machine frame 21 is of a central symmetrical structure.

The rack platform 8 comprises a rack upper plate 1 and a rack lower plate 2, the undercarriage 4 and the tilting steering engine 3 are both installed at the bottom of the rack lower plate 2, the top of the arm folding piece 7 and the top of the tail arm 9 are both fixedly connected to the rack upper plate 1, and the bottom of the arm folding piece 7 and the bottom of the tail arm 9 are both fixedly connected to the rack lower plate 2.

The models of the first electronic speed regulator ESC1, the second electronic speed regulator ESC2 and the third electronic speed regulator ESC3 are the same and are brushless electric regulation of Happy XRotor paradise series.

The frame platform 8 is the main body of the rotor unit and is cut by adopting a CNC integrated forming process.

A distribution board is arranged on the rack platform 8 and is a Matek distribution board, and the distribution board divides a signal circuit and a power supply circuit into two paths.

The model of the remote controller is FUTABA T14SG, and the remote control receiver RC is a FUTABA compatible receiver.

The model of flight control is Raffinxhawk 2, a port GND of the flight control is connected to a GND1 interface of a flight control power supply module BEC, an interface IN of the flight control power supply module BEC is connected to a pin 1 of a voltage stabilizer U1, the model of the voltage stabilizer U1 is LM2596S-ADJ, a third pin and a fifth pin of the voltage stabilizer U1 are both grounded, the first pin grounds the capacitor C2, the capacitor C2 is connected IN parallel with the capacitor C1, a second pin of the voltage stabilizer U1 is grounded through a diode D1, the second pin is grounded through a resistor R1 and a resistor R2, the resistor R1 is connected IN parallel with a capacitor CF, a fourth pin of the voltage stabilizer U1 is connected to a node between the resistor R1 and the resistor R2, a second pin of the voltage stabilizer U1 is grounded through a capacitor C3, the capacitor C3 is connected IN parallel with a capacitor C4, a second pin of the voltage stabilizer U1 is grounded through the resistor R3 and the diode D2, and a second pin of the SE1 is respectively connected to a VCC interface of a first tilting steering engine SE3, a VCC 4 interface of a third tilting steering engine 5; a first pin of the voltage stabilizer U1 is respectively connected to an IN pin of a flight control power supply control module BEC, a VCC port of a first electronic speed regulator ESC1, a VCC port of a second electronic speed regulator ESC2 and a VCC port of a third electronic speed regulator ESC3, the first electronic speed regulator ESC1 is electrically connected to a first motor M1, the second electronic speed regulator ESC2 is electrically connected to a second motor M2, the third electronic speed regulator ESC3 is electrically connected to a third motor M3, a pin GND1 of the flight control power supply control module BEC is grounded, and a pin GND is respectively connected with a GND interface of a first tilting steering engine SE3, a GND interface of a second tilting steering engine SE4, a GND interface of a fourth tilting steering engine SE6 and a GND interface of a fifth tilting steering engine SE 7; a pin OUT of the flight control POWER supply control module BEC is respectively connected to a port POWER of a flight control pixhawk2, a VCC interface of a first flying wing steering engine SE1, a VCC interface of a second flying wing steering engine SE2, a VCC interface of a fourth tilting steering engine SE6 and a VCC interface of a fifth tilting steering engine SE 7; a port RCIN of the flight control pixhawk2 is connected to a remote control receiver RC through an SUBS bus, an output port OUT1 of the flight control pixhawk2 is connected to a SIGNAL port of a first flying wing steering engine SE1, an output port OUT2 is connected to a SIGNAL port of a second flying wing steering engine SE2, an output port OUT3 is connected to a SIGNAL port of a first electronic speed regulator ESC1, an output port OUT4 is connected to a SIGNAL port of a second electronic speed regulator ESC2, an output port OUT5 is connected to a SIGNAL port of a third electronic speed regulator ESC3, an output port OUT6 is connected to a SIGNAL port of a first tilting steering engine SE3, an output port OUT7 is connected to a SIGNAL port of a second tilting steering engine SE4, and an output port OUT8 is connected to a SIGNAL port of a third tilting steering engine SE 5; an output port AUX1 of the flight control pixhawk2 is connected to a SIGNAL port of a four-number tilting steering engine SE6, and an output port AUX2 is connected to a SIGNAL port of a five-number tilting steering engine SE 7.

Flight control is used as a control unit of the whole machine, a remote controller FUTABA T14SG (2.4 GHz) signal is received by a remote control receiver RC through an RSFSB/SBUS FUTABA compatible receiver, meanwhile, the remote control unit has the capability of automatically controlling flight, a signal circuit and a power supply circuit are carried out in two paths, the signal is received by the receiver, is transmitted to a tilting steering engine and an electric regulator after being processed by the flight control, the electric regulator converts a PWM signal into an electric signal, and the electric signal is transmitted to a motor after the voltage is regulated to a proper voltage. The power supply of the machine consists of a 13000mah battery, and one path of the power supply supplies power for flight control and electric regulation through a distribution board. And the other path of the power supply is used for reducing the voltage and conveying the tilting steering engine and the landing gear through the flight control power supply module BEC.

The assembly process of the modularized multipurpose composite wing layout unmanned aerial vehicle comprises the following steps:

firstly, unfolding and fixing a rotor wing arm 6 to a specified position, installing electronic elements such as a battery and a flight control on a rack platform 8, and routing related wires to complete rotor wing platform assembly; secondly, splicing and fixing the outer wing section 9 and the middle wing section 7 in sequence through the wing folding pieces 7; and thirdly, taking the rotor flight platform 9 as a center, sequentially installing a machine shell 10 on the upper part of the rotor flight platform, installing a right wing 12 on the right side of the rotor flight platform, and installing a left wing 11 on the left side of the rotor flight platform to finish the composite wing configuration assembly.

When the unmanned aerial vehicle only has a rotor wing unit, the flight control controls the speed of the unmanned aerial vehicle in three directions by respectively controlling a first tilting steering engine SE3, a second tilting steering engine SE4, a third tilting steering engine SE5, a first electronic speed regulator ESC1, a second electronic speed regulator ESC2 and a third electronic speed regulator ESC3, so that the flight direction of the unmanned aerial vehicle is adjusted; when unmanned aerial vehicle carries on or delivers more article as required, assemble rotor unit and flying wing unit, the remote controller cooperation of flight control and ground, through control tilting steering wheel SE3, no. two tilting steering wheel SE4, no. three tilting steering wheel SE5, no. four tilting steering wheel SE6, no. five tilting steering wheel SE7, an electronic governor ESC1, no. two electronic governor ESC2, no. three electronic governor ESC3 come control unmanned aerial vehicle at the speed of three direction, thereby adjust unmanned aerial vehicle's flight direction, wherein No. four tilting steering wheel SE6 and No. five tilting steering wheel SE7 are used for controlling the direction of horn 6, make unmanned aerial vehicle complete machine flight direction's adjustment more nimble.

The above description is only for the purpose of illustrating the preferred embodiments of the present invention and should not be taken as limiting the scope of the present invention, which is intended to cover any modifications, equivalents, improvements, etc. within the spirit and scope of the present invention.

Claims

1. The utility model provides a compound wing overall arrangement unmanned aerial vehicle of modularization multipurpose which characterized in that: the aircraft comprises a motor base, machine arms, folding pieces, a rack platform, landing gears and a remote controller, wherein the cross section of the rack platform is of a centrosymmetric structure, a machine shell is installed at the top of the rack platform, wings are installed on two sides of the rack platform and comprise a wing middle section and a wing outer section, the wing outer section is fixedly connected to the wing middle section through the wing folding pieces, a flying wing steering engine is installed on each wing, the landing gears and one arm are respectively installed on two sides of the bottom of the rack platform, a tail arm is installed in the middle of the rack platform, the two landing gears and the two arms are both centrosymmetric about the tail arm, a first tilting steering engine SE3 and a first motor M1 are installed on the tail arm, one end of each arm is connected to a vector power device, the other end of each arm is connected to the rack platform through the folding pieces, each vector power device consists of a tilting mechanism and a motor, a rack platform is internally provided with a flight control, a power module BEC, a first electronic speed regulator 1, a second electronic speed regulator 2, a third electronic speed regulator 3 and a remote control receiver RC, the first tilting steering engine controller RC is electrically connected to a remote control signal receiver, and a remote control receiver RC are respectively connected to the first tilting steering engine controller SE1, a second electronic speed regulator 2, a third electronic speed regulator ESC3, a remote controller RC receiver and a remote controller RC receiver; the wing comprises left wing and right wing, installs No. one all-wing aircraft steering wheel SE1 on the left wing, installs No. two all-wing aircraft steering wheel SE2 on the right wing, no. one all-wing aircraft steering wheel SE1 and No. two all-wing aircraft steering wheel SE2 signal connection to the flight accuse.

2. The modular multi-purpose compound wing layout drone of claim 1, characterized in that: the models of the first electronic speed regulator ESC1, the second electronic speed regulator ESC2 and the third electronic speed regulator ESC3 are the same and are brushless electric regulation.

3. The modular multi-purpose compound wing layout drone of claim 1, characterized in that: the motor cabinet comprises left frame and right frame, and No. two tilting steering wheel SE4 and No. two motor M2 of left frame internally mounted, no. three tilting steering wheel SE5 and No. three motor M3 of right frame internally mounted.

4. The modular multi-purpose compound wing layout drone of claim 1, characterized in that: vector driving system is including tilting mechanism and brushless motor, tilting mechanism includes the horn clamping piece, the gasket, the base that verts, the steering wheel is verted to the vector, turn to piece and motor gasket, tilting base bottom is through gasket fixed mounting horn clamping piece, the steering wheel is verted to the top installation vector, the steering wheel is verted through turning to piece fixed connection to brushless motor to the vector, brushless motor with turn to and be equipped with the motor gasket between the piece, the steering wheel signal connection that verts to the vector flies to control.

5. The modular multi-purpose compound wing layout drone of claim 1, characterized in that: install vector power system on two horn respectively, the vector tilting steering wheel that corresponds the installation is No. four tilting steering wheel SE6 and No. five tilting steering wheel SE7 respectively, and No. four tilting steering wheel SE6 and No. five tilting steering wheel SE7 are signal connection to respectively flies to control.

6. The modular multi-purpose compound wing layout drone of claim 1, characterized in that: no. one vert steering wheel SE3, no. two vert steering wheel SE4, no. three vert steering wheel SE5, no. four vert steering wheel SE6 and No. five model of verting steering wheel SE7 are the same, are LOBOT robot steering wheel.

7. The modular multi-purpose compound wing layout drone of claim 1, characterized in that: the model of flight control is Raffinxhawk 2, a port GND of the flight control is connected to a GND1 interface of a flight control power supply module BEC, an interface IN of the flight control power supply module BEC is connected to a pin 1 of a voltage stabilizer U1, the model of the voltage stabilizer U1 is LM2596S-ADJ, a third pin and a fifth pin of the voltage stabilizer U1 are both grounded, the first pin grounds the capacitor C2, the capacitor C2 is connected IN parallel with the capacitor C1, a second pin of the voltage stabilizer U1 is grounded through a diode D1, the second pin is grounded through a resistor R1 and a resistor R2, the resistor R1 is connected IN parallel with a capacitor CF, a fourth pin of the voltage stabilizer U1 is connected to a node between the resistor R1 and the resistor R2, a second pin of the voltage stabilizer U1 is grounded through a capacitor C3, the capacitor C3 is connected IN parallel with a capacitor C4, a second pin of the voltage stabilizer U1 is grounded through the resistor R3 and the diode D2, and a second pin of the SE1 is respectively connected to a VCC interface of a first tilting steering engine SE3, a VCC 4 interface of a third tilting steering engine 5; a first pin of the voltage stabilizer U1 is respectively connected to an IN pin of a flight control power supply control module BEC, a VCC port of a first electronic speed regulator ESC1, a VCC port of a second electronic speed regulator ESC2 and a VCC port of a third electronic speed regulator ESC3, the first electronic speed regulator ESC1 is electrically connected to a first motor M1, the second electronic speed regulator ESC2 is electrically connected to a second motor M2, the third electronic speed regulator ESC3 is electrically connected to a third motor M3, a pin GND1 of the flight control power supply control module BEC is grounded, and a pin GND is respectively connected with a GND interface of a first tilting steering engine SE3, a GND interface of a second tilting steering engine SE4, a GND interface of a fourth tilting steering engine SE6 and a GND interface of a fifth tilting steering engine SE 7; a pin OUT of the flight control POWER supply control module BEC is respectively connected to a port POWER of a flight control pixhawk2, a VCC interface of a first flying wing steering engine SE1, a VCC interface of a second flying wing steering engine SE2, a VCC interface of a fourth tilting steering engine SE6 and a VCC interface of a fifth tilting steering engine SE 7; a port RCIN of the flight control pixhawk2 is connected to a remote control receiver RC through an SUBS bus, an output port OUT1 of the flight control pixhawk2 is connected to a SIGNAL port of a first flying wing steering engine SE1, an output port OUT2 is connected to a SIGNAL port of a second flying wing steering engine SE2, an output port OUT3 is connected to a SIGNAL port of a first electronic speed regulator ESC1, an output port OUT4 is connected to a SIGNAL port of a second electronic speed regulator ESC2, an output port OUT5 is connected to a SIGNAL port of a third electronic speed regulator ESC3, an output port OUT6 is connected to a SIGNAL port of a first tilting steering engine SE3, an output port OUT7 is connected to a SIGNAL port of a second tilting steering engine SE4, and an output port OUT8 is connected to a SIGNAL port of a third tilting steering engine SE 5; an output port AUX1 of the flight control pixhawk2 is connected to a SIGNAL port of a four-number tilting steering engine SE6, and an output port AUX2 is connected to a SIGNAL port of a five-number tilting steering engine SE 7.

8. The modular multi-purpose compound wing layout drone of claim 1, characterized in that: the left wing comprises a main wing and a side wing, one side of the main wing is fixedly connected to the side wing through a wing folding piece, the other side of the main wing is fixedly connected to a front edge side plate, the front edge side plate is fixedly connected to a casing rear edge reinforcing piece through a main beam side plate, a middle section side plate and a casing reinforcing piece, the front edge side plate, the main beam side plate and the middle section side plate are all fixedly connected to the rack platform, and the casing reinforcing piece and the casing rear edge reinforcing piece are all fixedly connected to the casing.

9. The modular multi-purpose compound wing layout drone of claim 1, characterized in that: the frame platform includes frame upper plate and frame hypoplastron, and the undercarriage is all installed in frame hypoplastron bottom with the steering wheel that verts, the equal fixed connection in top of horn folded piece, the equal fixed connection in top of tail horn to frame upper plate, the bottom of horn folded piece, the equal fixed connection in bottom of tail horn to frame hypoplastron.