A flight controller suitable for electric, oil-driven multi-model unmanned aerial vehicles

Abstract

The application relates to a flight controller suitable for electric and oil-driven multi-model unmanned aerial vehicles, which comprises a main control module and a power driving module, the power driving module comprises a group of electronic speed controller signal output interfaces, the electronic speed controller signal output interfaces are used for directly connecting electronic speed controllers and outputting standard PWM or OneShot electronic speed controller control signals; a group of rudder signal output interfaces are used for connecting rudders, including rudders for controlling unmanned aerial vehicle rudders and throttle rudders specially used for controlling oil-driven engine air doors; a power mode switching switch and a power management module, wherein the main control module is electrically connected with the power driving module and the power management module; and the controller can be simultaneously adapted to electric control and oil control.

Description

Technical Field

[0001] This application relates to the field of unmanned aerial vehicle (UAV) flight control technology, and in particular to a flight controller applicable to electric and gasoline-powered multi-model UAVs. Background Technology

[0002] Currently, most drone flight controllers (flight controllers) on the market are designed for specific power types and aircraft structures. The most common existing technology solutions are:

[0003] Dedicated electric flight controllers: These flight controllers are primarily designed for electric drones such as multi-rotor and fixed-wing drones. Their core is an integrated electronic speed controller (ESC) control signal output (such as a PWM signal), which directly drives the ESC via the main processor, thereby controlling the brushless motor. Their power module is typically designed to handle the voltage of the lithium battery pack (e.g., 12V-52V) and is equipped with a corresponding BEC (battery cancellation circuit) to power the flight controller itself and servos. The installation and algorithms of the sensor suite (IMU, barometer, etc.) are also optimized for the vibration environment and flight modes of electric drones.

[0004] Dedicated nitro-powered flight controllers: These flight controllers are designed for nitro-powered unmanned aerial vehicles (UAVs), typically fixed-wing or helicopters. Their core features include independent servo control channels and servo outputs for controlling the engine throttle. Since nitro-powered engines (such as methanol or gasoline engines) cannot be directly driven by electrical signals, servos are needed to mechanically adjust the throttle. Furthermore, the power system of nitro-powered flight controllers typically needs to draw power from a separate receiver battery and incorporate additional shielding and filtering designs to cope with the strong vibrations and electromagnetic interference from the nitro-powered engine.

[0005] Therefore, in existing technologies, users must purchase dedicated products when choosing flight controllers for electric or gasoline-powered drones. If a user or company owns both electric and gasoline-powered drones, or needs to test different configurations (such as switching from a quadcopter to a V-tail fixed-wing), they need to purchase and become familiar with multiple different flight control systems and perform complex installation and parameter configuration. This results in the following drawbacks:

[0006] Poor versatility: Electric flight controllers cannot be directly used to control the throttle of gasoline-powered engines, and gasoline-powered flight controllers cannot efficiently and accurately drive brushless motors; the two are incompatible. Users are forced to equip drones with different flight controllers for different power sources, increasing purchase and learning costs.

[0007] Poor adaptability: Existing flight controllers are usually strongly bound to specific aircraft structures (such as "X" type quadrotors, "+" type quadrotors, conventional fixed wings, flying wings, etc.) in terms of hardware interfaces and software configurations. When changing aircraft models, it is often necessary to re-solder cables, change hardware connections, or perform complex and error-prone channel mapping and mixed control settings in the software, resulting in extremely poor flexibility.

[0008] Complex system integration: For gasoline-powered drones, users need to configure additional servos, throttle servos, receiver batteries, etc. The connection between the flight controller and these devices is complex, increasing the system failure points and installation difficulty. While electric flight controllers have a high degree of integration, their closed nature also limits their application in hybrid power or special configurations.

[0009] Reliability challenges: Although dedicated nitro-powered flight controllers are designed to withstand vibration and interference, their hardware architecture is often fixed. When applied to nitro-powered engines of different power levels, their anti-interference capabilities may be insufficient. The vibration adaptability and electromagnetic compatibility of electric flight controllers in nitro-powered environments are usually unverified, and direct reuse carries risks. Utility Model Content

[0010] To address or partially address the problems existing in related technologies, this application provides a flight controller applicable to both electric and gasoline-powered UAVs, capable of simultaneously adapting to both electric and gasoline-powered systems.

[0011] This application discloses a flight controller applicable to electric and gasoline-powered multi-model unmanned aerial vehicles, including:

[0012] The main control module consists of a main processor and a memory;

[0013] The power drive module includes:

[0014] A set of electronic speed controller (ESC) signal output interfaces, which are used to directly connect to the electronic speed controller and output standard ESC control signals such as PWM or OneShot.

[0015] A set of servo signal output interfaces, the servo signal output interfaces being used to connect servos, including servos for controlling the control surfaces of the UAV and throttle servos specifically for controlling the throttle of the nitro engine;

[0016] The power mode switching switch is a hardware DIP switch or an electronic switch that can be triggered by software commands; its input end is connected to the core main control module, and its output end is connected to the servo signal output interface and the servo signal output interface, used to set the current power mode of the flight controller to "electric mode" or "hydraulic mode".

[0017] A power management module, which has a wide voltage input capability and includes multiple independent voltage regulation and filtering circuits;

[0018] The main control module is electrically connected to the power drive module and the power management module.

[0019] Optionally, a sensor module is also included, which includes an inertial measurement unit, a barometer, and a magnetometer, and is mounted on a base with a vibration damping structure and electrically connected to the main control module.

[0020] Optionally, the voltage regulation and filtering circuitry includes an enhanced EMI filter and surge protection circuitry.

[0021] Optionally, a communication module may also be included, which includes wireless and wired communication interfaces and is electrically connected to the main control module.

[0022] Optionally, the ESC signal output interface, servo signal output interface, and power mode switching switch of the power drive module can be integrated into a single hardware circuit board.

[0023] Optionally, the main control module, power drive module, power mode switching switch, and power management module are centrally located in a container, and the interfaces of each module and power module, as well as the power mode switching switch, are fixedly installed on the container wall.

[0024] The technical solution provided in this application may include the following beneficial effects:

[0025] This device employs a power drive module hardware structure that integrates the ESC signal output interface, servo signal output interface, and power mode switching switch into a single integrated hardware unit. This hardware / electronic switch enables dynamic routing of throttle commands between the ESC channel and the throttle servo channel. A power management module protects against wide voltage inputs, provides multiple independent outputs, and features enhanced EMI filtering and surge protection specifically for hydraulic environments. The overall design comprises a core control module, a power drive module, and a power management module, along with their collaborative operation to achieve electric / hydraulic compatibility and multi-model adaptation. Ultimately, a single flight control hardware setup can meet the control needs of drones with two completely different power sources: electric and gasoline. This significantly reduces equipment and storage costs for users. Furthermore, through hardware switches and graphical configuration software, users can switch between power modes or aircraft types within minutes without altering hardware wiring or gaining a deep understanding of the underlying hybrid control logic, greatly lowering the technical barrier and ease of use. Integrated power management and targeted anti-interference design ensure stable operation of the flight control system even in the harsh operating environment of gasoline engines. The modular design also reduces external wiring and connectors, lowering the risk of failures caused by loose connectors or corrosion. It also facilitates rapid development and testing. For drone R&D companies and enthusiasts, this flight control system serves as an ideal testing platform, allowing for quick switching between electric and gasoline prototypes, or testing the flight performance of different configurations on the same platform, accelerating the product development and iteration process.

[0026] It should be understood that the above general description and the following detailed description are exemplary and explanatory only, and do not limit this application. Attached Figure Description

[0027] The above and other objects, features and advantages of this application will become more apparent from the more detailed description of exemplary embodiments thereof in conjunction with the accompanying drawings, wherein the same reference numerals generally represent the same components in the exemplary embodiments thereof.

[0028] Figure 1 This is a schematic diagram of the structure shown in the embodiments of this application;

[0029] Figure label:

[0030] 1. Main control module; 2. Power drive module; 3. Power management module; 4. Sensor module; 5. Communication module. Detailed Implementation

[0031] Embodiments of this application will now be described in more detail with reference to the accompanying drawings. While embodiments of this application are shown in the drawings, it should be understood that this application may be implemented in various forms and should not be limited to the embodiments set forth herein. Rather, these embodiments are provided to make this application more thorough and complete, and to fully convey the scope of this application to those skilled in the art.

[0032] It should be understood that although the terms "first," "second," "third," etc., may be used in this application to describe various information, this information should not be limited to these terms. These terms are only used to distinguish information of the same type from one another. For example, without departing from the scope of this application, first information may also be referred to as second information, and similarly, second information may also be referred to as first information. Thus, a feature defined as "first" or "second" may explicitly or implicitly include one or more of that feature. In the description of this application, "multiple" means two or more, unless otherwise explicitly specified.

[0033] In the description of this application, it should be understood that the terms "length", "width", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings, and are only for the convenience of describing this application and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation, and therefore should not be construed as a limitation of this application.

[0034] Unless otherwise expressly specified and limited, the terms "installation," "connection," "linking," and "fixing," etc., should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral part; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium; they can refer to the internal communication of two components or the interaction between two components. Those skilled in the art can understand the specific meaning of the above terms in this application according to the specific circumstances.

[0035] To address the aforementioned issues, this application provides a flight controller applicable to electric and gasoline-powered multi-model unmanned aerial vehicles (UAVs). The technical solution of this application embodiment is described in detail below with reference to the accompanying drawings.

[0036] like Figure 1 The invention relates to a flight controller for electric and gasoline-powered multi-model UAVs, comprising a main control module 1, which consists of a main processor and a memory. The memory contains pre-stored mixed control logic programs for various UAV layouts, such as quadcopter "X" mode, hexacopter "Y" mode, fixed-wing conventional mode, and V-tail mixed control mode.

[0037] Power drive module 2, the power drive module includes:

[0038] A set of at least 6 ESC signal output interfaces are provided. These interfaces are used to directly connect to an electronic speed controller and output standard ESC control signals such as PWM or OneShot to drive the brushless motor.

[0039] A set of servo signal output interfaces has at least 6 servo signals output interfaces for connecting servos, including servos for controlling the control surfaces of the UAV, such as ailerons, elevators, and rudders, as well as throttle servos specifically for controlling the throttle of the gasoline engine.

[0040] A power mode switching switch, which can be a hardware DIP switch or an electronic switch triggered by software commands, is connected to the core control module and is used to set the current power mode of the flight controller to "electric mode" or "hydraulic mode". When switching to "electric mode", the core control module will map the throttle control command to the ESC signal output interface according to the selected aircraft model's hybrid control logic; when switching to "hydraulic mode", the core control module will map the throttle control command to the designated throttle servo signal output interface, while the remaining servo output interfaces are used for flight attitude control.

[0041] The power management module 3 has a wide voltage input capability to be compatible with the high-voltage lithium battery packs of electric drones and the 2S-4S lithium-ion receiver batteries commonly used in gasoline-powered drones, such as 5V-60V DC. It includes multiple independent voltage regulation and filtering circuits to provide clean and stable operating voltages for the core control module, sensor module, servo output interface, and ESC signal output interface. For gasoline-powered mode, the power input path is designed with an enhanced EMI filter and surge protection circuit to resist the strong electromagnetic interference generated by the engine ignition system.

[0042] The main control module is electrically connected to the power drive module and the power management module to form a whole.

[0043] This application also includes a sensor module 4, which comprises an inertial measurement unit, a barometer, and a magnetometer. It is mounted on a base with a vibration-damping structure and electrically connected to the main control module. This vibration-damping base effectively isolates high-frequency vibrations from the electric motor and low-frequency, large-amplitude vibrations from the gasoline engine. A communication module 5 is also included, comprising wireless and wired communication interfaces. This communication module is electrically connected to the main control module for remote communication or programming the controller. Furthermore, the ESC signal output interface, servo signal output interface, and power mode switching switch of the power drive module 2 are integrated onto a single hardware circuit board. A management module is configured within the main control module 1. This module is a graphical user configuration software. After connecting to the flight controller via a ground station computer or mobile app, users can select the power mode (as a supplement or replacement for the hardware switch) and choose the aircraft model (such as "Quadcopter X" or "Fixed Wing") from the preset library. The main control module will automatically load the corresponding mixing logic and channel mapping based on the user's selection, eliminating the need for users to manually write complex mixing scripts. Ultimately, the main control module, power drive module, power mode switch, and power management module are all housed in a single container. The interfaces of each module and the power module, as well as the power mode switch, are fixedly mounted on the container wall.

[0044] Thus, this application employs a hardware structure that integrates the ESC signal output interface, servo signal output interface, and power mode switching switch into a single integrated hardware unit. This hardware / electronic switch enables dynamic routing of throttle commands between the ESC channel and the servo channel. A power management module is configured to protect against wide voltage inputs, provide multiple independent outputs, and specifically enhance EMI filtering and surge protection for hydraulic environments. The overall structure comprises a core control module, a power drive module, and a power management module, along with their collaborative working mechanism to achieve electric / hydraulic compatibility and multi-model adaptation. Ultimately, a single flight control hardware setup can meet the control needs of drones with two completely different power sources: electric and gasoline. This significantly reduces equipment and storage costs for users. Furthermore, through hardware switches and graphical configuration software, users can switch between power modes or aircraft types within minutes without altering hardware wiring or gaining a deep understanding of the underlying hybrid control logic, greatly lowering the technical barrier and ease of use. Integrated power management and targeted anti-interference design ensure stable operation of the flight control system even in the harsh operating environment of gasoline engines. The modular design also reduces external wiring and connectors, lowering the risk of failures caused by loose connectors or corrosion. It also facilitates rapid development and testing. For drone R&D companies and enthusiasts, this flight control system serves as an ideal testing platform, allowing for quick switching between electric and gasoline prototypes, or testing the flight performance of different configurations on the same platform, accelerating the product development and iteration process.

[0045] The present invention will be further described below with reference to a specific embodiment:

[0046] Application Scenario: An agricultural plant protection company owns electric hexacopter drones for routine operations and large gasoline-powered fixed-wing drones for large-scale mapping. They want to use the same flight control system to manage the entire fleet.

[0047] Implementation process:

[0048] For use in electric hexacopter:

[0049] Switch the flight controller's power mode switch to "electric mode".

[0050] Connect the flight controller and computer via USB communication module, open the configuration software in the main control module, and select the "Hexacopter Y6" model from the model library.

[0051] Connect the ESC signal wires of the six brushless motors to the six ESC signal output interfaces of the flight controller. Connect the power input wire of the flight controller to the 6S lithium battery.

[0052] The main control module automatically allocates output logic to 6 channels. After completing the calibration of other sensors, it is ready for flight.

[0053] For use in nitro-powered fixed-wing aircraft:

[0054] Switch the power mode switch on the same flight controller to "Noctilinear mode".

[0055] Select the "Fixed Wing" model in the main control module.

[0056] Connect the throttle servo of the nitro engine to the servo signal output interface marked "Throttle" on the flight controller. Connect the aileron and elevator servos to the other servo interfaces respectively.

[0057] Connect a 2S lithium-ion battery (receiver battery) to the power input port of the flight controller.

[0058] The main control module automatically maps the remote controller's throttle channel to the throttle servo output and sets up logic such as elevator-throttle hybrid control for fixed-wing aircraft. Enhanced power filtering in the flight controller ensures uninterrupted system power supply during engine ignition and operation.

[0059] As can be seen from this embodiment, this utility model achieves seamless switching between UAVs with different power sources and configurations through simple physical switching combined with existing software configuration, fully demonstrating its advantages of versatility, flexibility and reliability.

[0060] Finally, it should be noted that in this document, relationships such as "first" and "second" are used merely to distinguish one entity or operation from another, and do not necessarily require or imply any such actual relationship or order between these entities or operations. Furthermore, the terms "include," "contain," or any other variations are intended to cover non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements includes not only those elements but also other elements not expressly listed, or elements inherent to such a process, method, article, or apparatus.

[0061] The units described as separate components may or may not be physically separate. The components shown as units may or may not be physical units; that is, they may be located in one place or distributed across multiple network units. Some or all of the units can be selected to achieve the purpose of this embodiment according to actual needs.

[0062] The various embodiments of this application have been described above. These descriptions are exemplary and not exhaustive, nor are they limited to the disclosed embodiments. Many modifications and variations will be apparent to those skilled in the art without departing from the scope and spirit of the described embodiments. The terminology used herein is chosen to best explain the principles, practical application, or improvement of the technology in the market, or to enable others skilled in the art to understand the embodiments disclosed herein.

Claims

1. A flight controller suitable for electric and gasoline-powered multi-model unmanned aerial vehicles (UAVs), characterized in that, include: The main control module consists of a main processor and a memory; The power drive module includes: A set of electronic speed controller (ESC) signal output interfaces, which are used to directly connect to the electronic speed controller and output standard PWM or OneShot ESC control signals. A set of servo signal output interfaces, the servo signal output interfaces being used to connect servos, including servos for controlling the control surfaces of the UAV and throttle servos specifically for controlling the throttle of the nitro engine; A power mode switching switch, which is a hardware DIP switch or an electronic switch that can be triggered by software commands, is used to set the current power mode of the flight controller to "electric mode" or "hydropower mode". A power management module, which has a wide voltage input capability and includes multiple independent voltage regulation and filtering circuits; The main control module is electrically connected to the power drive module and the power management module.

2. The flight controller for electric and gasoline-powered multi-model unmanned aerial vehicles according to claim 1, characterized in that: It also includes a sensor module, which comprises an inertial measurement unit, a barometer, and a magnetometer, and is mounted on a base with a vibration damping structure and electrically connected to the main control module.

3. A flight controller for electric and gasoline-powered multi-model unmanned aerial vehicles according to claim 1, characterized in that: The voltage regulation and filtering circuit is an enhanced EMI filter and surge protection circuit.

4. A flight controller for electric and gasoline-powered multi-model unmanned aerial vehicles according to claim 1, characterized in that: It also includes a communication module, which includes wireless and wired communication interfaces and is electrically connected to the main control module.

5. A flight controller for electric and gasoline-powered multi-model unmanned aerial vehicles according to claim 1, characterized in that: The power drive module's ESC signal output interface, servo signal output interface, and power mode switching switch are all integrated onto a single hardware circuit board.

6. A flight controller for electric and gasoline-powered multi-model unmanned aerial vehicles according to claim 1, characterized in that: The main control module, power drive module, power mode switching switch, and power management module are centrally located in a container, and the interfaces of each module and power module, as well as the power mode switching switch, are fixedly installed on the container wall.

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