CN222522873U - Flight Control Systems and Drones - Google Patents

Abstract

The utility model discloses a flight control system and an unmanned aerial vehicle, and relates to the technical field of unmanned aerial vehicles, wherein the flight control system comprises a main control board, a flight controller and an electronic speed regulator, the flight controller is arranged on one side of the main control board, the flight controller is provided with a first socket, the electronic speed regulator is arranged on one side of the main control board, which is opposite to the flight controller, the electronic speed regulator is provided with a second socket, the first socket is electrically connected with the second socket through a flexible flat cable, in the technical scheme provided by the utility model, the flight controller and the electronic speed regulator work cooperatively to ensure the flight safety and efficiency of the unmanned aerial vehicle together, and the flight controller and the electronic speed regulator are respectively arranged on two sides of the main control board and are electrically connected through the flexible flat cable.

Description

Flight control system and unmanned aerial vehicle

Technical Field

The utility model relates to the technical field of unmanned aerial vehicles, in particular to a flight control system and an unmanned aerial vehicle.

Background

Unmanned aerial vehicles are an aircraft that is capable of autonomous flight or by remote control. It is typically equipped with a plurality of motors and propellers to provide the required lift and thrust. Unmanned aerial vehicle's design can be very various, and small-size four-axis aircraft to large-scale fixed wing aircraft, and they all have wide application in many fields such as military reconnaissance, take photo by plane, commodity circulation transportation, environmental monitoring. The flight control system ensures that the unmanned aerial vehicle can safely and reliably perform the flight mission, whether in a simple teleoperated or complex automatic flight mode.

The electronic speed regulator and the flight controller are the most core components on the unmanned aerial vehicle, and together form a flight control system of the unmanned aerial vehicle, the types of unmanned aerial vehicles in related industries are more and more, especially, the unmanned aerial vehicle of racing type, the whole machine size is smaller and smaller, the internal space is smaller and smaller, and the space available for installing and placing equipment is smaller and smaller, so that the installation of the electronic speed regulator and the flight controller is difficult.

Disclosure of utility model

The utility model mainly aims to provide a flight control system and an unmanned aerial vehicle, and aims to provide the flight control system with higher internal integration degree and smaller occupied space.

In order to achieve the above object, the present utility model provides a flight control system, comprising:

A main control board;

the flight controller is arranged on one side of the main control board and is provided with a first socket, and

The electronic speed regulator is arranged on one side of the main control board, which is opposite to the flight controller, and is provided with a second socket, and the first socket is electrically connected with the second socket through a flexible flat cable.

In an embodiment, a buffer part is arranged at one side of the main control board, and the flight controller is arranged at the buffer part and is movably arranged at intervals with the main control board.

In an embodiment, the buffer portion includes four elastic connection columns, one end of each elastic connection column is disposed on the main control board, and the other end of each elastic connection column is clamped to the flight controller.

In an embodiment, four clamping holes are formed at four corners of the flight controller, clamping ring grooves are formed on the elastic connecting columns, and the outer peripheral walls of the clamping ring grooves are abutted against the inner peripheral walls of the clamping holes.

In an embodiment, the elastic connection column is formed with a through hole, the flight control system further comprises four bolts, the four bolts are respectively arranged on the four elastic connection columns, and the bolts penetrate through the main control board, the elastic connection columns and the flight controller.

In an embodiment, the elastic connection column is made of silica gel.

In an embodiment, the first receptacle and the second receptacle are disposed facing the same side.

In an embodiment, the main control board further comprises a micro control unit.

In one embodiment, the length of the main control board is 44mm, and the width of the main control board is 36mm.

The utility model also provides an unmanned aerial vehicle, which comprises a flight control system, wherein the flight control system comprises:

A main control board;

the flight controller is arranged on one side of the main control board and is provided with a first socket, and

The electronic speed regulator is arranged on one side of the main control board, which is opposite to the flight controller, and is provided with a second socket, and the first socket is electrically connected with the second socket through a flexible flat cable.

According to the technical scheme, the flight control system and the unmanned aerial vehicle are provided, wherein the flight control system comprises a main control board, a flight controller and an electronic speed regulator, the flight controller monitors the flight state of the unmanned aerial vehicle through sensors, such as the gesture, the position and the speed, and then calculates necessary control signals according to the data and a preset flight plan or a remote control instruction so as to ensure the stable flight of the unmanned aerial vehicle and execute a preset task, and the electronic speed regulator is used for executing the decisions of the flight controller to control a power system of the unmanned aerial vehicle and ensure that the unmanned aerial vehicle can perform accurate flight actions according to the instructions of the flight controller. The two work cooperatively to jointly ensure the flight safety and efficiency of the unmanned aerial vehicle. The flight controller and the electronic speed regulator are respectively arranged on two sides of the main control board and are electrically connected through the flexible flat cable, so that the space required by installation of the flight control system can be greatly saved, the integration degree is improved by adopting a stacking arrangement mode, and the unmanned aerial vehicle is miniaturized.

Drawings

In order to more clearly illustrate the embodiments of the present utility model or the technical solutions in the prior art, the drawings that are required in the embodiments or the description of the prior art will be briefly described, and it is obvious that the drawings in the following description are only some embodiments of the present utility model, and other drawings may be obtained according to the structures shown in these drawings without inventive effort for a person skilled in the art.

FIG. 1 is a schematic diagram of a flight control system according to an embodiment of the present utility model;

FIG. 2 is a schematic view of the elastic connection column in FIG. 1;

FIG. 3 is a schematic diagram of an exploded configuration of the flight control system provided by the present utility model;

Fig. 4 is a schematic view of the flexible flat cable of fig. 1.

Reference numerals illustrate:

1000. The device comprises a flight control system, a main control board, 11 parts of mounting holes, 2 parts of flight controllers, 21 parts of first sockets, 211 parts of flexible flat cables, 22 parts of clamping holes, 221 parts of notches, 3 parts of electronic speed regulators, 31 parts of second sockets, 4 parts of buffer parts, 41 parts of elastic connecting columns, 411 parts of clamping ring grooves, 412 parts of through holes, 5 parts of bolts.

The achievement of the objects, functional features and advantages of the present utility model will be further described with reference to the accompanying drawings, in conjunction with the embodiments.

Detailed Description

The following description of the embodiments of the present utility model will be made clearly and fully with reference to the accompanying drawings, in which it is evident that the embodiments described are only some, but not all embodiments of the utility model. All other embodiments, which can be made by those skilled in the art based on the embodiments of the utility model without making any inventive effort, are intended to be within the scope of the utility model.

It should be noted that, if directional indications (such as up, down, left, right, front, and rear are referred to in the embodiments of the present utility model), the directional indications are merely used to explain the relative positional relationship, movement conditions, and the like between the components in a specific posture, and if the specific posture is changed, the directional indications are correspondingly changed.

In addition, if there is a description of "first", "second", etc. in the embodiments of the present utility model, the description of "first", "second", etc. is for descriptive purposes only and is not to be construed as indicating or implying a relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defining "a first" or "a second" may explicitly or implicitly include at least one such feature. In addition, if "and/or" and/or "are used throughout, the meaning includes three parallel schemes, for example," a and/or B "including a scheme, or B scheme, or a scheme where a and B are satisfied simultaneously. In addition, the technical solutions of the embodiments may be combined with each other, but it is necessary to base that the technical solutions can be realized by those skilled in the art, and when the technical solutions are contradictory or cannot be realized, the combination of the technical solutions should be considered to be absent and not within the scope of protection claimed in the present utility model.

Unmanned aerial vehicles are an aircraft that is capable of autonomous flight or by remote control. It is typically equipped with a plurality of motors and propellers to provide the required lift and thrust. Unmanned aerial vehicle's design can be very various, and small-size four-axis aircraft to large-scale fixed wing aircraft, and they all have wide application in many fields such as military reconnaissance, take photo by plane, commodity circulation transportation, environmental monitoring. The flight control system ensures that the unmanned aerial vehicle can safely and reliably perform the flight mission, whether in a simple teleoperated or complex automatic flight mode.

The electronic speed regulator and the flight controller are the most core components on the unmanned aerial vehicle, and together form a flight control system of the unmanned aerial vehicle, the types of unmanned aerial vehicles in related industries are more and more, especially, the unmanned aerial vehicle of racing type, the whole machine size is smaller and smaller, the internal space is smaller and smaller, and the space available for installing and placing equipment is smaller and smaller, so that the installation of the electronic speed regulator and the flight controller is difficult.

In order to solve the above problems, the present utility model provides a flight control system and an unmanned aerial vehicle, and is aimed at providing a flight control system with higher internal integration and smaller occupied space, and fig. 1 to 4 are schematic structural diagrams of an embodiment of the flight control system according to the present utility model.

Referring to fig. 1 to 4, the present utility model provides a flight control system 1000, which includes a main control board 1, a flight controller 2 and an electronic speed regulator 3, wherein the flight controller 2 is disposed on one side of the main control board 1, the flight controller 2 is provided with a first socket 21, the electronic speed regulator 3 is disposed on one side of the main control board 1 facing away from the flight controller 2, the electronic speed regulator 3 is provided with a second socket 31, and the first socket 21 is electrically connected with the second socket 31 through a flexible flat cable 211.

In the technical scheme of the utility model, a flight control system 1000 and an unmanned aerial vehicle are provided, wherein the flight control system 1000 comprises a main control board 1, a flight controller 2 and an electronic speed regulator 3, the flight controller 2 monitors the flight state of the unmanned aerial vehicle, such as the attitude, the position, the speed and the like, and then calculates necessary control signals according to the data and a preset flight plan or a remote control instruction to ensure the stable flight of the unmanned aerial vehicle and execute a preset task, and the electronic speed regulator 3 is used for executing the decisions of the flight controller 2 to control the power system of the unmanned aerial vehicle and ensure the unmanned aerial vehicle to perform accurate flight actions according to the instructions of the flight controller 2. The two work cooperatively to jointly ensure the flight safety and efficiency of the unmanned aerial vehicle. The flight controller 2 and the electronic speed regulator 3 are respectively arranged at two sides of the main control board 1 and are electrically connected through the flexible flat cables 211, so that the space required by the installation of the flight control system 1000 can be greatly saved, and the integration degree is improved by adopting a stacking arrangement mode, so that the miniaturization of the unmanned aerial vehicle is realized.

The flight controller 2 is a core component of the unmanned aerial vehicle, corresponding to the "brain" of the unmanned aerial vehicle. The unmanned aerial vehicle flight state monitoring system integrates a microcontroller, a sensor and an algorithm, and is responsible for monitoring and processing the unmanned aerial vehicle flight state such as the attitude, the position, the speed and the like in real time. By receiving the sensor data, the flight controller 2 can accurately calculate and adjust the flight path and attitude of the unmanned aerial vehicle to achieve stable flight and perform complex flight tasks. In addition, the flight controller 2 is also responsible for communication with other components such as a remote controller, a GPS system, a camera, etc., to ensure that the unmanned aerial vehicle can operate according to a preset flight plan or real-time remote control instructions. The performance of the flight controller 2 is directly related to the flight safety, stability and accuracy of operation of the unmanned aerial vehicle. Since the unmanned aerial vehicle may generate vibration or improper operation during the flight process to cause the collision machine, in order to protect the flight controller 2, one side of the main control board 1 is provided with the buffer part 4, the flight controller 2 is arranged on the buffer part 4 and is spaced from the main control board 1, when the unmanned aerial vehicle is subjected to a large acceleration, the buffer part 4 can be rapidly compressed or stretched, so that the connection part of the flight controller 2 and the machine body is prevented from being broken due to large stress, the buffer part 4 can be a spring or an elastic connecting column 41, the utility model is not limited by the spring or the elastic connecting column 41, in one embodiment of the utility model, the buffer part 4 is composed of four elastic connecting columns 41, the elastic connecting columns 41 are all made of silica gel materials, and the silica gel materials have good elasticity and flexibility, can absorb the vibration and the impact during the flight process of the unmanned aerial vehicle, and reduce the physical damage to the flight controller 2. Secondly, the silica gel connection column can provide stable fixing and insulating properties, preventing the flight controller 2 from malfunctioning due to poor contact or short circuit. In addition, the silica gel spliced pole is easy to install and detach, is convenient for maintain and upgrade flight controller 2. Finally, the silica gel has excellent temperature resistance and aging resistance, is beneficial to prolonging the service life of the flight controller 2, and ensures that the unmanned aerial vehicle can stably operate under various environmental conditions.

In order to facilitate the installation and the disassembly of the flight controller 2, four clamping holes 22 are formed in four corners of the flight controller 2, four elastic connecting columns 41 are clamped in the four clamping holes 22, four notches 221 are respectively formed in four corners of the flight controller 2, and thus the elastic deformation capacity of the four clamping holes 22 can be improved, the flight controller 2 can be assembled more conveniently, the flight controller 2 is prevented from being separated from the four elastic connecting columns 41 in the fierce flight process of an unmanned aerial vehicle, and clamping ring grooves 411 are formed in each elastic connecting column 41, specifically, referring to fig. 2, the outer peripheral walls of the clamping ring grooves 411 are abutted against the inner peripheral walls of the clamping holes 22, so that the flight controller 2 is partially embedded into the elastic connecting columns 41, and the flight controller 2 can be limited.

In order to further reliably fix the flight controller 2 and the main control board 1, the elastic connecting column 41 is provided with a through hole 412, a bolt 5 is arranged in the through hole 412, the bolt 5 penetrates through the main control board 1, the elastic connecting piece and the flight controller 2 from top to bottom once, the three parts are reliably fixed, and if the flight controller 2 is to be disassembled, the disassembly can be realized only by unscrewing the bolt 5. Because the flight controller 2 and the electronic governor 3 are designed to be stacked up and down, they are connected by the flexible flat cable 211, so as to reduce the length of the flexible flat cable 211 and make the structural layout more reasonable, the first socket 21 of the flight controller 2 and the second socket 31 of the electronic governor 3 are disposed towards the same side, specifically, please refer to fig. 4, so that the distance between the first socket 21 and the second socket 31 is closer, thereby reducing the wiring of the flexible flat cable 211.

In order to realize the control of the unmanned aerial vehicle, the main control board 1 is provided with a Micro Control Unit (MCU) which is responsible for receiving and processing data from the sensor in real time, executing a flight control algorithm and managing various functions of the unmanned aerial vehicle, such as navigation, gesture stabilization, automatic flight and execution of remote control instructions. The MCU adjusts the rotating speed and the rotating direction of the motor by precisely controlling an electronic speed regulator 3 (ESC), so that the flight stability and the maneuverability of the unmanned aerial vehicle are ensured. In addition, the MCU is also responsible for data exchange and coordination with other systems such as a GPS, a camera, a communication module and the like, so that the unmanned aerial vehicle can perform complex tasks such as navigation, target tracking and real-time image transmission. In an embodiment of the present utility model, the length dimension of the main control board 1 is 44mm, the width dimension is 36mm, the external dimension of the flight controller 2 is 29mm by 29mm to 36mm by 36mm, and when the two are stacked, the flight controller 2 is completely located in the area covered by the main control board 1, thereby saving the space occupied by installation.

The utility model also provides an unmanned aerial vehicle, which comprises a flight control system 1000, wherein the specific structure of the flight control system 1000 refers to the embodiment, and as the unmanned aerial vehicle adopts all the technical schemes of all the embodiments, the unmanned aerial vehicle at least has all the beneficial effects brought by the technical schemes of the embodiments, and the detailed description is omitted.

The foregoing description is only exemplary embodiments of the present utility model and is not intended to limit the scope of the utility model, and all equivalent structural changes made by the description of the present utility model and the accompanying drawings or direct/indirect application in other related technical fields are included in the scope of the present utility model.

Claims (10)

1. A flight control system (1000), comprising:

A main control board (1);

The flight controller (2), the flight controller (2) is arranged on one side of the main control board (1), the flight controller (2) is provided with a first socket (21), and

The electronic speed regulator (3), electronic speed regulator (3) are located main control board (1) dorsad flight controller (2) one side, electronic speed regulator (3) are equipped with second socket (31), first socket (21) pass through flexible flat cable (211) with second socket (31) electricity is connected.

2. The flight control system (1000) according to claim 1, wherein a buffer portion (4) is disposed on one side of the main control board (1), and the flight controller (2) is disposed on the buffer portion (4) and is movably spaced from the main control board (1).

3. The flight control system (1000) according to claim 2, wherein the buffer portion (4) comprises four elastic connection columns (41), one end of each elastic connection column (41) is arranged on the main control board (1), and the other end of each elastic connection column is clamped to the flight controller (2).

4. A flight control system (1000) according to claim 3, wherein four clamping holes (22) are formed at four corners of the flight controller (2), the elastic connection column (41) is formed with a clamping ring groove (411), and an outer peripheral wall of the clamping ring groove (411) is abutted with an inner peripheral wall of the clamping hole (22).

5. A flight control system (1000) according to claim 3, wherein the elastic connection column (41) is formed with a through hole (412), the flight control system (1000) further comprises four bolts (5), the four bolts (5) are respectively arranged on the four elastic connection columns (41), and the bolts (5) are arranged on the main control board (1), the elastic connection column (41) and the flight controller (2) in a penetrating manner.

6. A flight control system (1000) according to claim 3, wherein the resilient connecting post (41) is of silicone material.

7. The flight control system (1000) according to any one of claims 1 to 6, wherein the first socket (21) and the second socket (31) are arranged facing the same side.

8. The flight control system (1000) according to any one of claims 1 to 6, wherein the main control board (1) further comprises a micro control unit.

9. The flight control system (1000) according to any one of claims 1 to 6, characterized in that the length of the main control panel (1) is 44mm and the width of the main control panel (1) is 36mm.

10. A drone, characterized by comprising a flight control system (1000) according to any one of claims 1 to 9.