CN218848701U

CN218848701U - Flight control and built-in on-board computer

Info

Publication number: CN218848701U
Application number: CN202222698868.6U
Authority: CN
Inventors: 胡爱华; 刘哲宁; 刘一
Original assignee: Jiangsu Blue Whale Intelligent Space Research Institute Co ltd
Current assignee: Jiangsu Blue Whale Intelligent Space Research Institute Co ltd
Priority date: 2022-10-13
Filing date: 2022-10-13
Publication date: 2023-04-11
Anticipated expiration: 2032-10-13

Abstract

The utility model discloses a fly accuse and built-in machine-borne computer, including machine-borne computer, fly accuse mainboard and turbofan, the bottom of machine-borne computer has been installed and has been flown the accuse mainboard, it is the integral structure with machine-borne computer to fly the accuse mainboard, fly accuse mainboard bottom and install the bottom, turbofan establishes in advance the bottom. The flight control and the built-in airborne computer combine the flight control and the airborne computer, and accidents and problems caused by complex wiring are avoided. The interference of the airborne computer signals and heat on the flight control is reduced to the minimum. The traditional flight control system has high-level control capability and complex operation capability, provides more abundant and simple peripheral equipment access capability, has the advantages of no interference of airborne computer signals and flight control, simple wiring, stability and reliability, has high-level control and complex operation capability, is convenient for sensor access and flight control and thermal isolation built in the airborne computer, and has no influence on the flight control due to the heat productivity of the airborne computer.

Description

Flight control and built-in on-board computer

Technical Field

The utility model relates to an unmanned aerial vehicle flies to control technical field, specifically is to fly accuse and built-in airborne computer.

Background

The flying control of the unmanned aerial vehicle is a flying control system of the unmanned aerial vehicle,

the traditional flight control system mainly comprises a gyroscope (sensing flight attitude), an accelerometer, geomagnetic induction, an air pressure sensor (roughly controlling hovering height), an ultrasonic sensor (precisely controlling low altitude height or avoiding obstacles), an optical flow sensor (precisely determining hovering horizontal position), a GPS module (roughly positioning horizontal position height), and a control circuit. The main function is to automatically maintain the normal flying attitude of the airplane.

The traditional flight control system can only automatically keep the normal flight attitude of the airplane and carry out simple navigation control, and the flight control cannot realize a more complex visual algorithm or a navigation control function because corresponding PWM (pulse-width modulation) waveforms need to be generated and the real-time requirement is met, so that high-level flight tasks and actions cannot be finished.

SUMMERY OF THE UTILITY MODEL

An object of the utility model is to provide a fly accuse and built-in airborne computer to propose in solving above-mentioned background art and can't realize more for complicated visual algorithm or navigation control function, the event can't accomplish the problem of senior flight task and action.

In order to achieve the above object, the utility model provides a following technical scheme: flight control and built-in airborne computer, including airborne computer, flight control mainboard and turbofan, the bottom of airborne computer has been installed and has been flown the accuse mainboard, it is the integral structure with airborne computer to fly the accuse mainboard, it installs the bottom to fly accuse mainboard bottom, turbofan predetermine the bottom.

As the utility model discloses an optimized technical scheme, the top laminating of bottom is connected with the casing, casing and bottom are connected for the laminating with the flight control mainboard.

By adopting the technical scheme, the bottom cover and the shell are used for installing the flight control mainboard, the internal space of the bottom cover is completely attached to the flight control mainboard, and the occupied volume of the airborne computer and the flight control is reduced.

As the utility model discloses an optimized technical scheme, casing and bottom one end symmetry are provided with the locking buckle.

By adopting the technical scheme, the shell and the bottom cover are in limited installation through the locking buckle, and the attaching degree of the flight control mainboard and the shell and the bottom cover can be increased.

As the preferred technical scheme of the utility model, bottom one end surface is equipped with the heating panel, the heating panel is connected for the laminating with turbofan.

Adopt above-mentioned technical scheme, the heating panel setting is at the back of bottom, and the other end surface of bottom and the laminating of flying to control the mainboard end that generates heat absorb the heat of airborne computer through the mode of heat conduction to dispel the heat by turbofan.

As the preferred technical scheme of the utility model, turbofan is located same vertical line with the on-board computer.

By adopting the technical scheme, the tail end of the turbofan is attached to the onboard computer, so that the onboard computer can be subjected to heat dissipation treatment with the highest efficiency.

As the preferred technical scheme of the utility model, the casing top is equipped with the protecting crust, protecting crust internal surface and airborne computer sliding connection.

By adopting the technical scheme, the protective shell protects the airborne computer, and simultaneously reduces the occupied volume, thereby increasing the overall practicability.

Compared with the prior art, the beneficial effects of the utility model are that: the flight control and built-in on-board computer:

1. according to the invention, flight control and an onboard computer are combined, and complex thermal design is carried out, so that the larger heat productivity of the onboard computer is quickly and effectively discharged, and the normal work of a flight control sensor system is not influenced;

2. flight control and an airborne computer are combined, and accidents and problems caused by complex wiring are avoided. The interference of the airborne computer signals and heat on the flight control is reduced to the minimum. The traditional flight control system has high-level control capability and complex operation capability, provides more abundant and simple peripheral equipment access capability, has no interference between an onboard computer signal and flight control, is simple in wiring, stable and reliable, has high-level control and complex operation capability, has a USB interface, facilitates sensor access and flight control and thermal isolation built in the onboard computer, and has no influence on flight control due to heat productivity of the onboard computer.

Drawings

FIG. 1 is a schematic view of the overall front three-dimensional structure of the present invention;

FIG. 2 is a schematic view of the overall back side three-dimensional structure of the present invention;

fig. 3 is the schematic view of the whole split three-dimensional structure of the present invention.

In the figure: 1. an onboard computer; 2. a flight control main board; 3. a housing; 4. a bottom cover; 5. a protective shell; 6. locking a buckle; 7. a heat dissipation plate; 8. a turbofan.

Detailed Description

The technical solutions in the embodiments of the present invention will be described clearly and completely with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only some embodiments of the present invention, not all embodiments. Based on the embodiments in the present invention, all other embodiments obtained by a person skilled in the art without creative efforts all belong to the protection scope of the present invention.

Referring to fig. 1-3, the present invention provides a technical solution: flight control and built-in airborne computer, including airborne computer 1, flight control mainboard 2 and turbofan 8, flight control mainboard 2 has been installed to airborne computer 1's bottom, and flight control mainboard 2 and airborne computer 1 are the integral structure, and bottom 4 is installed to flight control mainboard 2 bottom, and turbofan 8 predetermines in bottom 4 bottoms.

The top end laminating of bottom 4 is connected with casing 3, casing 3 and bottom 4 are connected for laminating with flying to control mainboard 2, bottom 4 and casing 3 are installed flying to control mainboard 2, and its inner space laminates flying to control mainboard 2 completely, reduce the volume that takes up of airborne computer 1 and flying to control, casing 3 and bottom 4 one end symmetry are provided with locking buckle 6, casing 3 and bottom 4 carry out spacing installation through locking buckle 6, can increase the laminating degree of flying to control mainboard 2 and casing 3 and bottom 4, bottom 4 one end surface is equipped with heating panel 7, heating panel 7 is for laminating the connection with turbofan 8, heating panel 7 sets up the back at bottom 4, the other end surface of bottom 4 laminates with flying to control mainboard 2 heating end, absorb the heat of airborne computer 1 through the mode of heat conduction, and dispel the heat by turbofan 8, turbofan 8 is located the same perpendicular line with airborne computer 1, the end of turbofan 8 laminates with airborne computer 1, can carry out the heat dissipation processing to airborne computer 1 the utmost, casing 3 top is equipped with protecting crust 5, protecting crust 5 and airborne efficient computer 1 sliding connection, thereby the whole volume that takes up the reduction simultaneously.

The working principle is as follows: the flight control mainboard 2 is provided with an RK3399 on-board computer 1, a Linux system is built in, and the flight control mainboard has greater advantages for vision and advanced control operation compared with flight control. The flight control system is connected with the airborne computer 1 through a data interface, the airborne computer 1 unpacks data acquired by a binocular sensor, operation, correction, after complex operations such as path analysis and the like, basic control data are sent to the flight control system, the aircraft is controlled again by flight control to complete complex control, wherein the bottom cover 4 and the shell 3 are used for installing the flight control mainboard 2, the internal space of the bottom cover is completely attached to the flight control mainboard 2, the occupied volume of the airborne computer 1 and flight control is reduced, the shell 3 and the bottom cover 4 are installed in a limiting mode through the locking buckle 6, the attaching degree of the flight control mainboard 2 to the shell 3 and the bottom cover 4 can be increased, the heat dissipation plate 7 is arranged on the back face of the bottom cover 4, the other end face of the bottom cover 4 is attached to the heating end of the flight control mainboard 2, heat of the airborne computer 1 is absorbed in a heat conduction mode, heat dissipation is carried out through the turbofan 8, the tail end of the turbofan 8 is attached to the airborne computer 1, heat dissipation processing can be carried out on the airborne computer 1 at the highest efficiency, the protective shell 5 is carried out on the airborne computer 1, the protective volume is reduced, and the whole practicability is increased.

Although embodiments of the present invention have been shown and described, it will be appreciated by those skilled in the art that changes, modifications, substitutions and alterations can be made in these embodiments without departing from the principles and spirit of the invention, the scope of which is defined in the appended claims and their equivalents.

Claims

1. Flight control and built-in airborne computer, its characterized in that includes airborne computer (1), flies accuse mainboard (2) and turbofan (8), flight control mainboard (2) have been installed to the bottom of airborne computer (1), it is the integrated structure with airborne computer (1) to fly accuse mainboard (2), bottom (4) are installed to flight control mainboard (2) bottom, turbofan (8) predetermine bottom (4) bottom.

2. The flight control and on-board computer of claim 1, wherein: the top end laminating of bottom (4) is connected with casing (3), casing (3) and bottom (4) are connected for laminating with flight control mainboard (2).

3. The flight control and on-board computer of claim 2, wherein: and locking buckles (6) are symmetrically arranged at one ends of the shell (3) and the bottom cover (4).

4. The flight control and on-board computer of claim 1, wherein: the outer surface of one end of the bottom cover (4) is provided with a heat dissipation plate (7), and the heat dissipation plate (7) is connected with the turbofan (8) in a fitting manner.

5. The flight and embedded on-board computer of claim 1, wherein: the turbofan (8) and the onboard computer (1) are positioned on the same vertical line.

6. The flight control and on-board computer of claim 2, wherein: the top end of the shell (3) is provided with a protective shell (5), and the inner surface of the protective shell (5) is connected with the airborne computer (1) in a sliding manner.