Flight control system and unmanned aerial vehicle
By designing a flight control system in the drone, and using stacking settings to tightly integrate the flight controller and the electronic speed controller, the problem of small internal space of racing drones is solved, and the installation problem is difficult to achieve, and the more High integration and smaller footprint.
Patent Information
- Application Number
- CN202421403872.8
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- Filing Date
- 2024-06-18
- Publication Date
- 2025-02-25
- Estimated Expiration
- 2034-06-18
AI Technical Summary
The entire size of racing drones is getting smaller and smaller, and the internal space is getting smaller, making it difficult to install electronic speed regulators and flight controllers.
A flight control system is designed, in which the flight controller and the electronic speed governor are respectively arranged on both sides of the main control board and are electrically connected through soft cables. The degree of integration is improved by stacking and installation space is saved.
It realizes higher internal integration of the flight control system and smaller footprint, solves the problem of installation difficulties, and promotes the miniaturization of drones.
Smart Images
Figure CN222522873U_ABST
Abstract
Description
Technical Field
[0001] 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 Art
[0002] A drone is an aircraft that can fly autonomously or by remote control. It is usually equipped with multiple motors and propellers to provide the required lift and thrust. The design of drones can be very diverse, from small quadcopters to large fixed-wing aircraft, and they are widely used in many fields such as military reconnaissance, aerial photography, logistics and transportation, and environmental monitoring. The flight control system ensures that the drone can perform flight missions safely and reliably, whether in simple remote control operation or in complex automatic flight mode.
[0003] The electronic speed regulator and flight controller are the core components of drones, and together they form the flight control system of drones. There are more and more types of drones in related industries, especially racing drones. The size of the whole machine is getting smaller and smaller, and the internal space is getting smaller and smaller. The space available for installing and placing equipment is also getting smaller and smaller, which makes it difficult to install the electronic speed regulator and flight controller. Utility Model Content
[0004] The main purpose of the utility model is to provide a flight control system and an unmanned aerial vehicle, aiming to provide a flight control system with a higher degree of internal integration and a smaller occupied space.
[0005] To achieve the above-mentioned purpose, the flight control system proposed by the utility model includes:
[0006] Main control board;
[0007] A flight controller, the flight controller is arranged at one side of the main control board, and the flight controller is provided with a first socket; and
[0008] An electronic speed regulator is arranged on a side of the main control board facing away from the flight controller. The electronic speed regulator is provided with a second socket, and the first socket is electrically connected to the second socket through a flexible flat cable.
[0009] In one embodiment, a buffer portion is provided on one side of the main control board, and the flight controller is disposed on the buffer portion and is spaced apart from the main control board.
[0010] In one embodiment, the buffer portion includes four elastic connecting columns, one end of each elastic connecting column is disposed on the main control board, and the other end is clamped on the flight controller.
[0011] In one embodiment, four snap-in holes are formed at four corners of the flight controller, and the elastic connecting column is formed with a snap-in ring groove, and the outer peripheral wall of the snap-in ring groove abuts against the inner peripheral wall of the snap-in hole.
[0012] In one embodiment, the elastic connecting column is formed with a through hole, and the flight control system further includes four bolts, and the four bolts are respectively arranged on the four elastic connecting columns, and the bolts pass through the main control board, the elastic connecting column and the flight controller.
[0013] In one embodiment, the elastic connecting column is made of silicone.
[0014] In one embodiment, the first socket and the second socket are arranged facing the same side.
[0015] In one embodiment, the main control board further includes a micro control unit.
[0016] In one implementation, the length of the main control board is 44 mm, and the width of the main control board is 36 mm.
[0017] The utility model also provides an unmanned aerial vehicle, the unmanned aerial vehicle includes a flight control system, and the flight control system includes:
[0018] Main control board;
[0019] A flight controller, the flight controller is arranged at one side of the main control board, and the flight controller is provided with a first socket; and
[0020] An electronic speed regulator is arranged on a side of the main control board facing away from the flight controller. The electronic speed regulator is provided with a second socket, and the first socket is electrically connected to the second socket through a flexible flat cable.
[0021] In the technical solution of the utility model, a flight control system and a UAV are proposed, wherein the flight control system includes a main control board, a flight controller and an electronic speed regulator. The flight controller monitors the flight status of the UAV, such as attitude, position, speed, etc., through sensors, and then calculates the necessary control signals based on these data and the preset flight plan or remote control instructions to ensure the stable flight of the UAV and the execution of the predetermined tasks. The electronic speed regulator is used to execute these decisions of the flight controller, control the power system of the UAV, and ensure that the UAV can perform precise flight actions according to the instructions of the flight controller. The two work together to ensure the flight safety and efficiency of the UAV. The flight controller and the electronic speed regulator are respectively arranged on both sides of the main control board and are electrically connected through a flexible flat cable. Such an arrangement can greatly save the space required for the installation of the flight control system, and the stacking arrangement is adopted to improve the degree of integration, thereby realizing the miniaturization of the UAV. BRIEF DESCRIPTION OF THE DRAWINGS
[0022] In order to more clearly illustrate the embodiments of the utility model or the technical solutions in the prior art, the drawings required for use in the embodiments or the description of the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the utility model. For ordinary technicians in this field, other drawings can be obtained based on the structures shown in these drawings without paying creative work.
[0023] Figure 1 A schematic structural diagram of an embodiment of a flight control system provided by the utility model;
[0024] Figure 2 for Figure 1 Schematic diagram of the structure of the elastic connecting column;
[0025] Figure 3 This is a schematic diagram of the exploded structure of the flight control system provided by the utility model;
[0026] Figure 4 for Figure 1 Schematic diagram of the medium soft cable.
[0027] Description of Figure Numbers:
[0028] 1000, flight control system; 1, main control board; 11, mounting hole; 2, flight controller; 21, first socket; 211, flexible flat cable; 22, snap-in hole; 221, notch; 3, electronic speed regulator; 31, second socket; 4, buffer; 41, elastic connecting column; 411, snap-in ring groove; 412, through hole; 5, bolt.
[0029] The realization of the purpose, functional features and advantages of the utility model will be further explained in conjunction with embodiments and with reference to the accompanying drawings. DETAILED DESCRIPTION
[0030] The following will be combined with the drawings in the embodiments of the utility model to clearly and completely describe the technical solutions in the embodiments of the utility model. Obviously, the described embodiments are only part of the embodiments of the utility model, not all of the embodiments. Based on the embodiments of the utility model, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the utility model.
[0031] It should be noted that if the embodiments of the present invention involve directional indications (such as up, down, left, right, front, back...), the directional indications are only used to explain the relative position relationship, movement status, etc. between the components in a certain specific posture. If the specific posture changes, the directional indications will also change accordingly.
[0032] In addition, if there are descriptions involving "first", "second", etc. in the embodiments of the utility model, the descriptions of "first", "second", etc. are only used for descriptive purposes and cannot be understood as indicating or implying their relative importance or implicitly indicating the number of technical features indicated. Therefore, the features limited to "first" and "second" may explicitly or implicitly include at least one of the features. In addition, if "and / or" or "and / or" appears in the full text, its meaning includes three parallel solutions. Taking "A and / or B" as an example, it includes solution A, solution B, or solutions that satisfy both A and B. In addition, the technical solutions between the various embodiments can be combined with each other, but it must be based on the ability of ordinary technicians in this field to implement. When the combination of technical solutions is contradictory or cannot be implemented, it should be deemed that such combination of technical solutions does not exist and is not within the scope of protection required by the utility model.
[0033] A drone is an aircraft that can fly autonomously or by remote control. It is usually equipped with multiple motors and propellers to provide the required lift and thrust. The design of drones can be very diverse, from small quadcopters to large fixed-wing aircraft, and they are widely used in many fields such as military reconnaissance, aerial photography, logistics and transportation, and environmental monitoring. The flight control system ensures that the drone can perform flight missions safely and reliably, whether in simple remote control operation or in complex automatic flight mode.
[0034] The electronic speed regulator and flight controller are the core components of drones, and together they form the flight control system of drones. There are more and more types of drones in related industries, especially racing drones. The size of the whole machine is getting smaller and smaller, and the internal space is getting smaller and smaller. The space available for installing and placing equipment is also getting smaller and smaller, which makes it difficult to install the electronic speed regulator and flight controller.
[0035] In order to solve the above problems, the utility model proposes a flight control system and an unmanned aerial vehicle, aiming to provide a flight control system with a higher degree of internal integration and a smaller occupied space. Figures 1 to 4 The present invention is a schematic structural diagram of an embodiment of a flight control system provided by the present invention.
[0036] Please refer to Figures 1 to 4 The utility model proposes a flight control system 1000, including a main control board 1, a flight controller 2 and an electronic speed regulator 3, 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, the electronic speed regulator 3 is arranged on a 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 to the second socket 31 through a flexible flat cable 211.
[0037] In the technical solution of the utility model, a flight control system 1000 and a UAV are proposed, wherein the flight control system 1000 includes a main control board 1, a flight controller 2 and an electronic speed regulator 3. The flight controller 2 monitors the flight status of the UAV, such as attitude, position, speed, etc., through sensors, and then calculates the necessary control signals according to these data and the preset flight plan or remote control instructions to ensure the stable flight of the UAV and the execution of the predetermined task. The electronic speed regulator 3 is used to execute these decisions of the flight controller 2, control the power system of the UAV, and ensure that the UAV can perform precise flight actions according to the instructions of the flight controller 2. The two work together to ensure the flight safety and efficiency of the UAV. The flight controller 2 and the electronic speed regulator 3 are respectively arranged on both sides of the main control board 1 and are electrically connected through a flexible flat cable 211. Such an arrangement can greatly save the space required for the installation of the flight control system 1000, and the stacking arrangement is adopted to improve the degree of integration, thereby realizing the miniaturization of the UAV.
[0038] The flight controller 2 is the core component of the drone, equivalent to the "brain" of the drone. It integrates a microcontroller, sensors and algorithms, and is responsible for real-time monitoring and processing of the drone's flight status, such as attitude, position, speed, etc. By receiving sensor data, the flight controller 2 can accurately calculate and adjust the flight path and attitude of the drone to achieve stable flight and perform complex flight missions. In addition, the flight controller 2 is also responsible for communicating with other components such as the remote control, GPS system, camera, etc. to ensure that the drone can operate according to the 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 operation accuracy of the drone. Since the drone may vibrate or crash due to improper operation during flight, in order to protect the flight controller 2, a buffer part 4 is provided on one side of the main control board 1. The flight controller 2 is arranged in the buffer part 4 and is spaced from the main control board 1. When the drone is subjected to a large acceleration, the buffer part 4 will be quickly compressed or stretched, thereby preventing the flight controller 2 from being broken due to a large force at the connection between the fuselage and the flight controller 2. It should be noted that the buffer part 4 can be a spring or an elastic connecting column 41. The utility model does not limit this. In one embodiment of the utility model, the buffer part 4 is composed of four elastic connecting columns 41. The material of the elastic connecting column 41 is silicone. The silicone material has good elasticity and flexibility, and can absorb vibration and impact during the flight of the drone, reducing physical damage to the flight controller 2. Secondly, the silicone connecting column can provide stable fixing and insulation performance to prevent the flight controller 2 from malfunctioning due to poor contact or short circuit. In addition, the silicone connecting column is easy to install and disassemble, which is convenient for maintaining and upgrading the flight controller 2. Finally, the excellent temperature resistance and aging resistance of silicone can help extend the service life of the flight controller 2 and ensure that the drone can operate stably under various environmental conditions.
[0039] In order to facilitate the installation and removal of the flight controller 2, four snap-in holes 22 are formed at the four corners of the flight controller 2, and four elastic connecting columns 41 are snap-fitted into the four snap-in holes 22. Four notches 221 are respectively provided at the four corners of the flight controller 2. Such a configuration can improve the elastic deformation capacity of the four snap-in holes 22, thereby making it easier to assemble the flight controller 2. In order to prevent the flight controller 2 from escaping from the four elastic connecting columns 41 during intense flight of the drone, a snap-in ring groove 411 is formed on each elastic connecting column 41. For details, please refer to Figure 2 The outer wall of the snap ring groove 411 abuts against the inner wall of the snap hole 22 , so that the flight controller 2 is partially embedded in the elastic connecting column 41 , which can limit the flight controller 2 .
[0040] In order to further reliably fix the flight controller 2 and the main control board 1, the elastic connecting column 41 is formed with a through hole 412, and a bolt 5 is arranged in the through hole 412. The bolt 5 passes through the main control board 1, the elastic connecting piece and the flight controller 2 from top to bottom at once, and the three are reliably fixed. If the flight controller 2 is to be disassembled, it is only necessary to unscrew the bolt 5 to achieve disassembly. Since the flight controller 2 and the electronic speed controller 3 adopt an upper and lower stacking design, the two are connected by a flexible flat cable 211. In order 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 speed controller 3 are arranged toward the same side. For details, please refer to Figure 4 Such an arrangement makes the distance between the first socket 21 and the second socket 31 closer, thereby reducing the wiring of the flexible flat cable 211.
[0041] In order to realize the control of the UAV, the main control board 1 is provided with a microcontroller unit, and the microcontroller unit (MCU) is responsible for receiving and processing data from sensors in real time, executing flight control algorithms, and managing various functions of the UAV, such as navigation, attitude stabilization, automatic flight, and execution of remote control commands. The MCU adjusts the speed and direction of the motor by accurately controlling the electronic speed regulator 3 (ESC) to ensure the flight stability and maneuverability of the UAV. In addition, the MCU is also responsible for data exchange and coordination with other systems such as GPS, cameras, and communication modules, so that the UAV can perform complex tasks such as waypoint navigation, target tracking, and real-time image transmission. In one embodiment of the utility model, the length of the main control board 1 is 44mm, the width is 36mm, and the outer dimensions of the flight controller 2 are 29mm*29mm to 36mm*36mm. 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 the installation.
[0042] The utility model also proposes an unmanned aerial vehicle, which includes a flight control system 1000. The specific structure of the flight control system 1000 refers to the above-mentioned embodiment. Since the unmanned aerial vehicle adopts all the technical solutions of all the above-mentioned embodiments, it has at least all the beneficial effects brought by the technical solutions of the above-mentioned embodiments, which will not be described one by one here.
[0043] The above description is only an exemplary embodiment of the present invention, and does not limit the patent scope of the present invention. All equivalent structural changes made by using the contents of the present invention specification and drawings under the technical concept of the present invention, or directly / indirectly applied in other related technical fields are included in the patent protection scope of the present invention.
Claims
1. A flight control system (1000), characterized in that: include: Main control board (1); A flight controller (2), the flight controller (2) being arranged on one side of the main control board (1), the flight controller (2) being provided with a first socket (21); and An electronic speed regulator (3), the electronic speed regulator (3) being arranged on a side of the main control board (1) facing away from the flight controller (2), the electronic speed regulator (3) being provided with a second socket (31), the first socket (21) being electrically connected to the second socket (31) via a flexible flat cable (211).
2. The flight control system (1000) according to claim 1, characterized in that: A buffer portion (4) is provided on one side of the main control panel (1), and the flight controller (2) is arranged on the buffer portion (4) and is arranged at a movable interval from the main control panel (1).
3. The flight control system (1000) according to claim 2, characterized in that: The buffer part (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 is clamped on the flight controller (2).
4. The flight control system (1000) according to claim 3, characterized in that: Four snap-fit holes (22) are formed at the four corners of the flight controller (2), and the elastic connecting column (41) is formed with a snap-fit ring groove (411), and the outer peripheral wall of the snap-fit ring groove (411) abuts against the inner peripheral wall of the snap-fit hole (22).
5. The flight control system (1000) according to claim 3, characterized in that: The elastic connecting column (41) is formed with a through hole (412), and the flight control system (1000) further comprises four bolts (5), wherein the four bolts (5) are respectively arranged on the four elastic connecting columns (41), and the bolts (5) are passed through the main control board (1), the elastic connecting column (41) and the flight controller (2).
6. The flight control system (1000) according to claim 3, characterized in that: The elastic connecting column (41) is made of silicone material.
7. The flight control system (1000) according to any one of claims 1 to 6, characterized in that: 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, characterized in that: The main control board (1) also includes 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 board (1) is 44 mm, and the width of the main control board (1) is 36 mm.
10. A drone, characterized in that: The invention comprises a flight control system (1000) as claimed in any one of claims 1 to 9.