CN110844062A

CN110844062A - Modular multipurpose unmanned aerial vehicle with composite wing layout

Info

Publication number: CN110844062A
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: 2020-02-28
Anticipated expiration: 2039-10-15
Also published as: CN110844062B

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:

a modularized multipurpose unmanned aerial vehicle with a composite wing layout comprises a motor base, a machine arm, folding pieces, a rack platform, landing gears and a remote controller, wherein the cross section of the rack platform is of a central symmetry 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 wing middle sections and wing outer sections, the wing outer sections are fixedly connected to the wing middle sections through the wing folding pieces, a flying wing steering engine is installed on each wing, the landing gears, the machine arm and the tail wings are installed on two sides of the bottom of the rack platform respectively, the two landing gears and the two machine arms are symmetrical about the center of the tail wings, a first tilting steering engine SE3 and a first motor M1 are installed on the tail wings, one end of each machine arm is connected to the motor base, the other end of each machine arm is connected to the rack platform through the folding pieces, a motor and a tilting steering engine, The flight control system comprises a flight control power 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, wherein flight control is respectively 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 motor, a tilting steering engine, a flying wing steering engine, a first tilting steering engine SE3 and a first motor in a signal mode, the flight control power module BEC is electrically connected to the flight control power module BEC, and the remote control receiver RC is connected to a remote controller in a signal mode.

Furthermore, the wing comprises a left wing and a right wing, a first flying wing steering engine SE1 is installed on the left wing, a second flying wing steering engine SE2 is installed on the right wing, and the first flying wing steering engine SE1 and the second flying wing steering engine SE2 are connected to the flying control in a signal mode.

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 and adjustable.

Furthermore, the motor cabinet comprises left frame and right frame, and left frame internally mounted inclines steering engine SE4 and No. two motor M2 for two numbers, and right frame internally mounted inclines steering engine SE5 and No. three motor M3 for three numbers.

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.

Furthermore, the vector power systems are respectively installed on the two machine arms, the correspondingly installed steering engines are respectively a fourth tilting steering engine SE6 and a fifth tilting steering engine SE7, and the fourth tilting steering engine SE6 and the fifth tilting steering engine SE7 are respectively in signal connection with flight control.

Furthermore, the first tilting steering engine SE3, the second tilting steering engine SE4, the third tilting steering engine SE5, the fourth tilting steering engine SE6 and the fifth tilting steering engine SE7 are the same in model 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 regulator U1, the model of the voltage regulator U1 is LM2596S-ADJ, a third pin and a fifth pin of the voltage regulator U1 are both grounded, the first pin connects the capacitor C2 to ground, the capacitor C2 is connected IN parallel with a capacitor C1, a second pin of the voltage regulator U1 is connected to ground through a diode D1, the third pin and the fifth pin are 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 regulator U1 is connected to a node between a resistor R1 and a resistor R2, a second pin of the voltage regulator U1 is connected to ground through a capacitor C3, the capacitor C3 is connected IN parallel with a capacitor C4, a second pin of the voltage regulator U1 is connected to ground, a second pin of the voltage stabilizer U1 is respectively connected to a VCC interface of the first tilting steering engine SE3, a VCC interface of the second tilting steering engine SE4 and a VCC interface of the third 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, a second electronic speed regulator ESC2 is electrically connected to a second motor M2, a 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 the 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 the 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 shell through a main beam side plate, a middle section side plate and a shell reinforcing piece, the front edge side plate, the main beam side plate and the middle section side plate are fixedly connected to the rack platform, and the shell reinforcing piece and the rear edge reinforcing piece of the shell are fixedly connected to the.

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 space inside 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 traditional composite wing configuration rotor wing unit and the fixed wing unit 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 multi-purpose unmanned aerial vehicle with the composite wing layout has the advantages that the sub-flight units or the parallel sub-units are selected to execute tasks according to different task requirements through the 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-girder side panels; 15-middle section side plate; 16-a chassis reinforcing sheet; 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 "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 only 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 "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, e.g., as meaning either a fixed connection, a removable connection, or an integral connection; 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 meaning 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 embodiments with reference to the attached drawings.

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 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 each of the right wing 11 and the left wing 12, 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, the tilting steering engine 3, the flying wing steering engine, the first steering engine SE3, the first motor M1 and a motor of the vector power system through signals, the flying control power supply module BEC is electrically connected to a remote.

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

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 motors M2, No. three tilting steering engine SE5 of right frame internally mounted and No. three motors M3, No. two tilting steering engine SE4, No. two motors M2, No. three tilting steering engine SE5 and No. three motors M3 all signal connection to fly the accuse for keep unmanned aerial vehicle flight balance.

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

No. one tilting steering engine SE3, No. two tilting steering engines SE4, No. three tilting steering engines SE5, No. four tilting steering engines SE6 and No. five tilting steering engines SE7 are the same in model and are LOBOT robot steering engines.

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.

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 Letian series.

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

The rack platform 8 is provided with a distribution board which is a Matek distribution board, and the distribution board divides a signal circuit and a power supply circuit into two paths.

The remote control is of the type FUTABA T14SG and the remote control receiver RC is a FUTABA compatible receiver.

The model of the 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 a voltage stabilizer U1 is LM2596S-ADJ, a third pin and a fifth pin of the voltage stabilizer U1 are both grounded, a first pin grounds a capacitor C2, a 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 third pin and the fifth pin are grounded through a resistor R1 and a resistor R2, a resistor R1 is connected IN parallel with a capacitor CF, a fourth pin of the voltage stabilizer U1 is connected to a node between a resistor R1 and a resistor R2, a second pin of the voltage stabilizer U1 is grounded through a capacitor C3, a capacitor C3 is connected IN parallel with a capacitor C4, a second pin of an 82U 56 is grounded through a resistor R84, a second pin of the voltage stabilizer U1 is respectively connected to a VCC interface of the first tilting steering engine SE3, a VCC interface of the second tilting steering engine SE4 and a VCC interface of the third 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, a second electronic speed regulator ESC2 is electrically connected to a second motor M2, a 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 the 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 the 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 (2.4GHz) signal is received by a remote control receiver RC through an RSFSB/SBUS FUTABA compatible receiver, meanwhile, the flight control device 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 through 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 transmission line is used for reducing the voltage and transmitting 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 speeds 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 the unmanned aerial vehicle carries on or delivers more articles as required, assemble rotor unit and flying wing unit, the remote controller cooperation of flight control and ground, through control tilting steering wheel SE3, tilting steering wheel SE4 No. two, tilting steering wheel SE5 No. three, tilting steering wheel SE6 No. four, tilting steering wheel SE7 No. five, electronic governor ESC1 No. two, electronic governor ESC2, the speed of unmanned aerial vehicle in three direction is controlled to electronic governor ESC3, thereby adjust unmanned aerial vehicle's flight direction, wherein tilting steering wheel SE6 No. four and tilting steering wheel SE7 No. five are used for the direction of control horn 6, make the adjustment of unmanned aerial vehicle complete machine flight direction more nimble.

The above description is only for the purpose of illustrating the preferred embodiments of the present invention and is not to be construed as limiting the invention, and any modifications, equivalents, improvements and the like that fall within the spirit and principle of the present invention are intended to be included therein.

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 machine arm are respectively installed on two sides of the bottom of the rack platform, a tail machine arm is installed in the middle of the rack platform, the two landing gears and the two machine arms are both centrosymmetric about the tail machine arm, a first tilting steering engine SE3 and a first motor M1 are installed on the tail machine arm, one end of each machine arm is connected to a vector power device, the other end of each vector power device is connected to the rack platform through the folding pieces, each vector power device is composed of, The flight control system comprises a first electronic speed regulator ESC1, a second electronic speed regulator ESC2, a third electronic speed regulator ESC3 and a remote control receiver RC, wherein flight control signals are respectively 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 motor, a tilting steering engine, a flying wing steering engine, a first tilting steering engine SE3 and a first motor, the flight control system is electrically connected to a flight control power module BEC, and the remote control receiver RC is connected to a remote controller in a signal mode.

2. The modular multi-purpose compound wing layout drone of claim 1, characterized in that: the wing comprises left wing and right wing, installs No. one all wing steering wheel SE1 on the left wing, installs No. two all wing steering wheel SE2 on the right wing, No. one all wing steering wheel SE1 and No. two all signal connection to fly accuse to the all wing steering wheel SE 2.

3. The modular multi-purpose compound wing layout drone of claim 2, 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.

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

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

6. The modular multi-purpose compound wing layout drone of claim 5, characterized in that: vector power systems are respectively installed on the two machine arms, the vector tilting steering engines correspondingly installed are a fourth tilting steering engine SE6 and a fifth tilting steering engine SE7 respectively, and the fourth tilting steering engine SE6 and the fifth tilting steering engine SE7 are respectively in signal connection with flight control.

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

8. The modular multi-purpose compound wing layout drone of claim 7, characterized in that: the model of the 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 a voltage stabilizer U1 is LM2596S-ADJ, a third pin and a fifth pin of the voltage stabilizer U1 are both grounded, a first pin grounds a capacitor C2, a 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 third pin and the fifth pin are grounded through a resistor R1 and a resistor R2, a resistor R1 is connected IN parallel with a capacitor CF, a fourth pin of the voltage stabilizer U1 is connected to a node between a resistor R1 and a resistor R2, a second pin of the voltage stabilizer U1 is grounded through a capacitor C3, a capacitor C3 is connected IN parallel with a capacitor C4, a second pin of an 82U 56 is grounded through a resistor R84, a second pin of the voltage stabilizer U1 is respectively connected to a VCC interface of the first tilting steering engine SE3, a VCC interface of the second tilting steering engine SE4 and a VCC interface of the third 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, a second electronic speed regulator ESC2 is electrically connected to a second motor M2, a 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 the 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 the 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.

9. 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 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.

10. The modular multi-purpose compound wing layout drone of claim 1, characterized in that: the rack platform comprises an upper rack plate and a lower rack plate, the landing gear and the tilting steering engine are both mounted at the bottom of the lower rack plate, the top of the folding part 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 part of the machine arm and the bottom of the tail machine arm are both fixedly connected to the lower rack plate.