CN218112961U

CN218112961U - Miniature fixed wing unmanned aerial vehicle

Info

Publication number: CN218112961U
Application number: CN202222595705.5U
Authority: CN
Inventors: 胥子彦; 陈俊池; 黄鹏程
Original assignee: Hunan Haozhou Intelligent Technology Co ltd
Current assignee: Hunan Haozhou Intelligent Technology Co ltd
Priority date: 2022-09-29
Filing date: 2022-09-29
Publication date: 2022-12-23
Anticipated expiration: 2032-09-29

Abstract

The utility model belongs to the technical field of unmanned aerial vehicle, a miniature fixed wing unmanned aerial vehicle is disclosed, last fuselage and lower fuselage of connection including splicing each other, go up the fuselage and install preceding wing, the back wing is installed to the fuselage down, the power is installed to the fuselage down, the fuselage is located down the receiver is installed to one side of power, four aluminium posts, four aluminium post tip is installed in the lump by the power carries out the flight control circuit board that supplies power, four install between the aluminium post with the electricity that flies control circuit board signal connection is transferred, the electricity is transferred and is connected with the motor, the motor output is connected with the screw that is located the organism outside, the back wing is articulated with the mode of symmetry and installs left aileron and right aileron, down the fuselage both sides install with left aileron with the steering wheel that right aileron connects respectively, steering wheel control left aileron with right aileron motion is used for adjusting the unmanned aerial vehicle gesture.

Description

Miniature fixed wing unmanned aerial vehicle

Technical Field

The utility model belongs to the technical field of unmanned aerial vehicle, concretely relates to miniature fixed wing unmanned aerial vehicle.

Background

The pilotless plane is called unmanned plane for short, and is a pilotless plane controlled by radio remote control equipment and a self-contained program control device.

The applicant finds that the unmanned aerial vehicle in the prior art has the following technical problems:

1. the existing micro unmanned aerial vehicle system has the carrier mainly comprising four-shaft propeller aircrafts, and has the disadvantages of low aerodynamic efficiency, miniaturization (good portability, concealment and flexibility), no consideration of endurance time and cruising speed;

2. the existing unmanned aerial vehicle control system lacks an efficient control logic for the micro fixed-wing unmanned aerial vehicle, does not support task diversification and self-definition, and is difficult to match variable application scenes.

SUMMERY OF THE UTILITY MODEL

To the problem that the above-mentioned background art provided, the utility model aims at: aims to provide a micro fixed wing unmanned aerial vehicle.

In order to realize the technical purpose, the utility model discloses a technical scheme as follows:

the utility model provides a miniature fixed wing unmanned aerial vehicle, includes last fuselage and lower fuselage of concatenation connection each other, go up the fuselage and install preceding wing, back wing is installed to lower fuselage, the power is installed to lower fuselage, the fuselage is located down the receiver is installed to one side of power, four aluminium posts are installed to lower fuselage, four the aluminium post tip install in the lump by the power carries out the flight control circuit board that supplies power, four install between the aluminium post with flight control circuit board signal connection's electricity is transferred, electricity is transferred and is connected with the motor, the motor output is connected with the screw that is located the organism outside, back wing articulates with the mode of symmetry and installs left aileron and right aileron, down the fuselage both sides install with left aileron with the steering wheel that right aileron is connected respectively, steering wheel control left aileron with right aileron motion is used for adjusting the unmanned aerial vehicle gesture.

Further, the upper fuselage is filled with a foam plate at the installation position of the front wing, and the design is anti-falling.

The wing span length difference size of the front wing and the rear wing is the diameter length size of two wing tip sockets at cruising speed, and the design can weaken the wing tip sockets generated by the front wing and the rear wing to a certain extent, so that the resistance is reduced, and the cruising range is increased.

Further, the upper machine body and the lower machine body are integrally formed by glass fiber reinforced plastics, and the design ensures the strength and lower weight of the machine body.

Further, the power supply is a 2s1000mah battery, and the design ensures the endurance and the volume of the 1000mah battery is most suitable for the micro requirement.

Adopt the beneficial effects of the utility model:

1. the utility model discloses use the material design of high strength low density to go out compact fuselage for minimizing product size under the prerequisite that unmanned aerial vehicle operation ability obtained the assurance, the comprehensive performance of miniaturization, duration, cruise speed improves and makes unmanned aerial vehicle can carry out many current unmanned aerial vehicle and be difficult to competent tasks, if high-speed reconnaissance task.

2. The utility model discloses a wing tandem wing formula overall arrangement design that preceding wing and back wing formed makes the aircraft obviously be stronger than usual four shaft propeller aircraft at the comprehensive performance of miniaturization, time of endurance and cruise speed.

3. The utility model discloses can realize solving the diversified demand of operation task through adopting cluster formula task management software system development, and then promote task efficiency, increased the operation stability.

Drawings

The present invention can be further illustrated by the non-limiting examples given in the accompanying drawings;

fig. 1 is a schematic structural view of an embodiment of a micro fixed-wing drone of the present invention;

fig. 2 is a schematic view of a lower body and an internal structure of a micro fixed-wing drone according to an embodiment of the present invention;

the main element symbols are as follows:

an upper body 1; a lower body 2; a front wing 3; a rear wing 4; a power supply 5; a receiver 6; an aluminum column 7; a flight control circuit board 8; electrically adjusting 9; a motor 10; a left flap 11; a right aileron 12; a steering engine 13; a foam board 14.

Detailed Description

In order to make the technical solution of the present invention better understood, the following description is provided for the purpose of illustrating the present invention with reference to the accompanying drawings and embodiments.

As fig. 1, fig. 2 shows, the utility model discloses a miniature fixed wing unmanned aerial vehicle, last fuselage 1 and lower fuselage 2 including concatenation connection each other, go up fuselage 1 and install preceding wing 3, lower fuselage 2 installs rear wing 4, lower fuselage 2 installs power 5, receiver 6 is installed to one side that lower fuselage 2 is located power 5, lower fuselage 2 installs four aluminium columns 7, four aluminium columns 7 tip install the flight control circuit board 8 that supplies power by power 5 in the lump, install the electricity 9 of being connected with flight control circuit board 8 signal between four aluminium columns 7, electricity 9 is connected with motor 10, the motor 10 output is connected with the screw that is located the organism outside, rear wing 4 articulates with the mode of symmetry and installs left aileron 11 and right aileron 12, the steering wheel 13 of being connected respectively with left aileron 11 and right aileron 12 is installed to lower fuselage 2 both sides, steering wheel 13 control left aileron 11 and right aileron 12 motion are used for adjusting the gesture.

In this embodiment, when a micro fixed wing drone is used, an operator sets a common/cluster task through ground station software, the ground station software generates a real-time control command in real time through dynamic calculation, the command is transmitted to a drone/drone cluster through a radio transmitting station after being encrypted, the drone/drone cluster receives a signal through a receiver 6, a flight control circuit board 8 analyzes a radio signal to execute corresponding real-time action, the continuous real-time action forms an operation task, a power supply 5 continuously supplies power to the flight control circuit board 8 and an electric controller 9, the flight control circuit board 8 controls a steering engine 13 to achieve the purpose of controlling the movement of a left aileron 11 and a right aileron 12 to adjust the attitude of the drone, an installation mode of supporting the flight control circuit board 8 by an aluminum column 7 enables components to be installed on the lower side of the flight control circuit board 8, an installation space is saved, the volume can be reduced to the maximum, the miniaturization requirement is met, and compared with a common propeller, the comprehensive performance of the miniaturization, the cluster task management software system is developed to further improve the diversified requirements of operation and the cruise stability of the operation task.

The upper fuselage 1 is preferably filled with the foam board 14 at the installation position of the front wing 3, and such a design is anti-falling, and in fact, the specification and the size of the foam board 14 can be considered according to specific situations.

Preferably, the span length difference size of the front wing 3 and the rear wing 4 is the diameter length size of the two wing tip sockets at cruising speed, and by the design, the wing tip sockets generated by the front wing and the rear wing can be weakened to a certain extent, so that the resistance is reduced, the cruising is increased, and in fact, the span length difference size of the front wing 3 and the rear wing 4 can be considered according to specific conditions.

The upper machine body 1 and the lower machine body 2 are preferably integrally formed by glass fiber reinforced plastics, and by adopting the design, the strength and the lower weight of the machine body are ensured, and actually, the forming mode of the upper machine body 1 and the lower machine body 2 can be considered according to specific conditions.

The power supply 5 is preferably a 2s1000mah battery, and such a design ensures endurance, and the volume of the 1000mah battery is most suitable for the micro requirements, and actually, the selection of the power supply 5 can be considered according to specific situations.

The above embodiments are merely illustrative of the principles and effects of the present invention, and are not to be construed as limiting the invention. Modifications and variations can be made to the above-described embodiments by those skilled in the art without departing from the spirit and scope of the present invention. Accordingly, it is intended that all equivalent modifications or changes which may be made by those skilled in the art without departing from the spirit and technical spirit of the present invention be covered by the claims of the present invention.

Claims

1. The utility model provides a miniature fixed wing unmanned aerial vehicle, includes upper fuselage (1) and lower fuselage (2) of concatenation connection each other, its characterized in that: go up fuselage (1) and install preceding wing (3), back wing (4) are installed in fuselage (2) down, power (5) are installed in fuselage (2) down, fuselage (2) are located down receiver (6) are installed to one side of power (5), four aluminium post (7) tip are installed in the lump by power (5) carry out the flight control circuit board (8) of supplying power, four install between aluminium post (7) with flight control circuit board (8) signal connection's electricity accent (9), electricity accent (9) are connected with motor (10), motor (10) output is connected with the screw that is located the organism outside, back wing (4) are articulated with the mode of symmetry install left aileron (11) and right aileron (12), down fuselage (2) both sides install with left aileron (11) with steering wheel (13) that right aileron (12) are connected respectively, control left aileron (13) with right aileron (12) move for the adjustment gesture.

2. The micro fixed-wing drone of claim 1, wherein: and a foam plate (14) is filled and installed at the installation position of the front wing (3) of the upper fuselage (1).

3. A micro fixed-wing drone according to claim 2, characterized in that: the span length difference size of the front wing (3) and the rear wing (4) is the diameter length size of two wing tip sockets at cruising speed.

4. A micro fixed-wing drone according to claim 3, characterized in that: the upper machine body (1) and the lower machine body (2) are integrally formed by glass fiber reinforced plastics.

5. The micro fixed-wing drone of claim 4, wherein: the power supply (5) is a 2s1000mah battery.