EVTOL aircraft and flight control electronic system thereof

Abstract

The invention discloses an EVTOL aircraft and a flight control electronic system thereof, and relates to the technical field of aircrafts. The flight control electronic system comprises a plurality of cockpit interface modules and a flight control computer; the inputs of the plurality of cockpit interfaces are respectively in communication connection with the airborne driving control system; the outputs of the plurality of cockpit interfaces are respectively in communication connection with at least one flight control computer; the input of each flight control computer is in communication connection with the airborne avionics system and / or the air-ground data link system, and the output of each flight control computer is connected with the actuator; the flight control computer receives instructions from the cockpit interface module and / or the airborne avionics system and / or the air-ground data chain system, outputs control signals through the flight control computer, and controls the actuator to act according to the control signals. The system can be adapted to aircrafts with various safety targets, and is adapted to human driving and unmanned driving configurations, the repeated design of one aircraft and one system is abandoned, the development cost is reduced, and the development period is shortened.

Description

Technical Field

[0001] The present invention relates to the technical field of aircraft, and particularly to an EVTOL aircraft and its flight control electronic system. Background Art

[0002] EVTOL aircraft usually utilize a configuration of distributed power and multiple control surfaces and multiple power systems with aerodynamic redundancy to achieve vertical takeoff and landing and cruising. To control multiple control surfaces and multiple power units, EVTOL aircraft generally adopt a fly-by-light or fly-by-wire flight control system. The fly-by-light / wire flight control system usually consists of a cockpit control interface, flight control electronics, and actuators. The cockpit control interface is usually used for in-flight pilot commands or navigation / auto flight commands or receiving ground station commands; flight control electronics are the core of the system, responsible for the input and management of commands and sensors, control law calculation, output of actuator commands, system redundancy management, and status monitoring and indication; actuators are responsible for executing the commands of the flight control electronics and feeding back their own status to the flight control electronics, and they are usually flap controllers, power units, or ground movement and brake control systems.

[0003] Currently, the safety objectives of civil manned aircraft are determined based on whether it is manned, the number of passengers carried by the aircraft, and whether the operating environment is dense or sparse. The higher the number of passengers carried or the denser the population in the operating area, the higher the safety objective; the lower the number of passengers carried or the sparser the population in the operating area, the lower the safety objective, with the highest being up to 1.0e9 / flying hour (1.0e - 9 / FH) of civil transport aircraft and the lowest being no safety requirements for light sport aircraft.

[0004] However, the current flight control electronic systems of aircraft are usually customized and only meet the safety objectives of specific aircraft models, and cannot meet the requirements of different safety objectives, manned and unmanned, and single - pilot or multi - pilot configurations. Based on this, the present invention proposes a flight control electronic system for an EVTOL aircraft. Summary of the Invention

[0005] The present invention provides a flight control electronic system for an EVTOL aircraft, including: a plurality of cockpit interface modules and a flight control computer; the inputs of the plurality of cockpit interfaces are respectively communicatively connected to the on - board flight control system;

[0006] The outputs of the plurality of cockpit interfaces are respectively communicatively connected to at least one flight control computer;

[0007] The input of each flight control computer is communicatively connected to the on - board avionics system and / or the air - ground data link system, and the output of each flight control computer is connected to an actuator;

[0008] The flight control computer receives instructions from the cockpit interface module and / or the on-board avionics system and / or the air-ground data link system, outputs control signals through the flight control computer, and controls the actuator to act according to the control signals.

[0009] An EVTOL aircraft flight control electronic system as described above, wherein digital bus communication is adopted between multiple flight control computers, and the communication mode is point-to-point communication or broadcast communication.

[0010] An EVTOL aircraft flight control electronic system as described above, wherein multiple flight control computers include a main flight control computer and heterogeneous flight control computers, and information synchronization and cross-monitoring are carried out between the main flight control computer and the heterogeneous flight control computers; the flight control computer receives instructions from the cockpit interface module and / or the on-board avionics system and / or the air-ground data link system, outputs a first control signal through the main flight control computer, and outputs a second control signal through the heterogeneous flight control computer, and controls the actuator to act through the first control signal and / or the second control signal.

[0011] An EVTOL aircraft flight control electronic system as described above, wherein digital bus communication is adopted between multiple cockpit interfaces and multiple flight control computers, and the communication mode is point-to-point communication or broadcast communication.

[0012] An EVTOL aircraft flight control electronic system as described above, wherein the on-board flight control system includes: cockpit switches and at least one first joystick;

[0013] The inputs of each cockpit interface are respectively communicatively connected to the cockpit switches and at least one first joystick.

[0014] An EVTOL aircraft flight control electronic system as described above, wherein the on-board flight control system further includes: at least one second joystick;

[0015] The inputs of each cockpit interface are respectively communicatively connected to the cockpit switches, at least one first joystick, and at least one second joystick.

[0016] An EVTOL aircraft flight control electronic system as described above, wherein the on-board flight control system further includes: at least one second joystick;

[0017] The inputs of some of the multiple cockpit interfaces are respectively communicatively connected to the first joystick, and the inputs of another part of the multiple cockpit interfaces are respectively communicatively connected to the second joystick.

[0018] An EVTOL aircraft flight control electronic system as described above, wherein the flight control electronic system communicates with the on-board avionics system and / or the air-ground data link system through a flight control computer, and / or communicates with the on-board flight control system through the flight control computer and the cockpit interface module, to implement at least one aircraft flight configuration, and the aircraft flight configuration includes at least one of an unmanned configuration, and / or a single-pilot configuration, and / or a multi-pilot configuration.

[0019] The present invention also provides an EVTOL aircraft, characterized in that the EVTOL aircraft includes an EVTOL aircraft flight control electronic system according to any one of the above.

[0020] The beneficial effects achieved by the present invention are as follows: The flight control electronic system architecture proposed by the present invention can be adapted to aircraft with various safety objectives, and is adapted to manned and unmanned configurations, abandoning the repeated design of one system for one aircraft in the current industry, reducing the development cost, and shortening the project development cycle. BRIEF DESCRIPTION OF THE DRAWINGS

[0021] In order to more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the following will briefly introduce the drawings required for use in the description of the embodiments or the prior art. Obviously, the drawings in the following description are only some embodiments recorded in the present invention, and those of ordinary skill in the art can also obtain other drawings based on these drawings.

[0022] Figure 1 It is a schematic diagram of an EVTOL aircraft flight control electronic system provided in Embodiment 1 of the present application;

[0023] Figure 2 and Figure 3 It is a schematic diagram of the interface topology between flight control computers;

[0024] Figure 4 It is a schematic diagram of the EVTOL flight control electronic system - unmanned configuration;

[0025] Figure 5 It is a schematic diagram of the EVTOL flight control electronic system - single-pilot configuration;

[0026] Figure 6 and Figure 7 It is a schematic diagram of the connection method between the cockpit interface module and the flight control computer;

[0027] Figure 8 and Figure 9 It is a schematic diagram of the EVTOL flight control electronic system - multi-pilot configuration;

[0028] Figure 10It is a schematic diagram of the hybrid configuration of the EVTOL flight control electronic system for single-pilot and unmanned operation;

[0029] Figure 11 It is an example block diagram of the function execution of the flight control electronic system;

[0030] Figure 12 It is Figure 11 a detailed schematic diagram of the input signal selection and output instruction selection in Specific implementation manner

[0031] Next, in combination with the accompanying drawings in the embodiments of the present invention, the technical solutions in the embodiments of the present invention will be clearly and completely described. Obviously, the described embodiments are part of the embodiments of the present invention, rather than all the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative efforts shall fall within the protection scope of the present invention.

[0032] Embodiment 1

[0033] Embodiment 1 of the present invention provides an EVTOL aircraft flight control electronic system, including: a plurality of cockpit interface modules, and a flight control computer; the inputs of the plurality of cockpit interfaces are respectively communicatively connected to the on-board flight control system; the outputs of the plurality of cockpit interfaces are respectively communicatively connected to at least one flight control computer; the input of each flight control computer is communicatively connected to the on-board avionics system and / or the air-ground data link system, and the output of each flight control computer is connected to an actuator; the flight control computer receives instructions from the cockpit interface module and / or the on-board avionics system and / or the air-ground data link system, outputs a control signal through the flight control computer, and controls the actuator to act according to the control signal.

[0034] The flight control electronic system includes N flight control computers, and the N flight control computers include N-1 main flight control computers (FCC) and 1 heterogeneous flight control computer (BFCC). Information is synchronized and cross-monitored between the main flight control computer and the heterogeneous flight control computer; the flight control computer receives instructions from the cockpit interface module and / or the on-board avionics system and / or the air-ground data link system, outputs a first control signal through the main flight control computer, and outputs a second control signal through the heterogeneous flight control computer, and controls the actuator to act through the first control signal and / or the second control signal.

[0035] In the embodiments of the present application, the heterogeneous computer is designed dissimilarly to the main flight control computer to mitigate the common mode risk of the main flight control computer. Its functions can be the same as those of the main flight control computer or a subset of the functions of the main flight control computer to simplify the development cost. The flight control computer is responsible for receiving instructions and sensor inputs and management, control law calculation, outputting actuator instructions, system redundancy management, and status monitoring and indication. The working modes between the redundancies of the main flight control computer can be in the form of'main-main-main' or'main-backup-backup', and the output instruction selection can adopt strategies such as 'preset priority' or'majority voting', and the specific strategy depends on the integrity of the output instructions of a single flight control computer. The heterogeneous flight control computer is in the backup mode and is automatically activated through the system fault logic or actively selected by the pilot.

[0036] Digital bus communication is adopted between flight control computers, and the communication methods include one-to-one communication or one-to-many communication. Depending on the synchronization method between flight control computers and the implementation form of cross-monitoring, necessary analog quantities also need to be set to ensure that the states of the flight control computers are synchronized (it can be tight synchronization or loose synchronization) and the information is consistent (it refers to within a time period, not instantaneously).

[0037] As Figure 2 shown, the one-to-one communication method is point-to-point communication, and each master vehicle communicates with other vehicles through an independent bus. For example, the flight control electronic system includes three main flight control computers and one heterogeneous flight control computer. After the main flight control computer 1# sends a signal, it is transmitted to the main flight control computer 2# through the independent bus 1-2, the main flight control computer 1# sends a signal and is transmitted to the main flight control computer 3# through the independent bus 1-3, and the main flight control computer 1# sends a signal and is transmitted to the heterogeneous flight control computer through the independent bus 1-Y. The communication between other flight control vehicles is similar to that of the main flight control computer 1#.

[0038] As Figure 3 shown, the one-to-many communication method is broadcast communication. After each master vehicle sends a signal, all other flight control computers can receive the signal. For example, the flight control electronic system includes three main flight control computers and one heterogeneous flight control computer. All flight control computers are connected to multiple buses. When the main flight control computer 1# sends a signal, the main flight control computers 2#, 3# and the heterogeneous flight control computer can all receive the signal through the multiple connected buses. The communication of other flight control vehicles is similar to that of the main flight control computer 1#.

[0039] The cockpit interface modules are independent of each other and have no communication requirements. Multiple cockpit interfaces communicate with multiple flight control computers through a digital bus, and the communication method is point-to-point communication or broadcast communication.

[0040] The cockpit interface module is used for data acquisition and transmission, including receiving cockpit aircraft control instructions (specifically, control sticks such as control wheel, pedals, side stick and throttle lever) and cockpit switch instructions (such as mode switch, function activation switch, etc.), and sending the instructions to the flight control computer.

[0041] One end of each cockpit interface module is connected to the on-board flight control system outside the flight control electronic system to receive the on-board flight control system instructions, and the other end is connected to each flight control computer inside the flight control electronic system to send the aircraft operating system instructions to the flight control computer.

[0042] Among them, the on-board flight control system includes: cockpit switches and at least one first control stick (such as at least one of control wheel, pedals, side stick and throttle lever), and the inputs of each cockpit interface are respectively communicatively connected to the cockpit switches and at least one first control stick.

[0043] In addition, the on-board flight control system further includes: at least one second control stick (such as at least one of control wheel, pedals, side stick and throttle lever) for dual-pilot operation; the inputs of each cockpit interface are respectively communicatively connected to the cockpit switches, at least one first control stick, and at least one second control stick; or the inputs of some of the multiple cockpit interfaces are respectively communicatively connected to the first control stick, and the inputs of another part of the multiple cockpit interfaces are respectively communicatively connected to the second control stick.

[0044] Embodiment 2

[0045] In the embodiment of the present application, the flight control electronic system communicates with the on-board avionics system and / or the air-ground data link system through the flight control computer, and / or communicates with the on-board flight control system through the flight control computer and the cockpit interface module to implement at least one aircraft flight configuration. Different EVTOL aircraft can select a single flight configuration according to actual needs, or can select to implement different aircraft flight configurations by designing control methods.

[0046] The aircraft flight configurations include an unmanned configuration and a manned configuration. The manned configuration includes a single-pilot configuration and / or a multi-pilot configuration, and can also be controlled by fusing different flight configurations. Among them:

[0047] (1) Unmanned configuration:

[0048] As Figure 4 shown, in the unmanned configuration, the on-board avionics system and the air-ground data link system are the main inputs of the flight control electronic system.

[0049] The unmanned configuration includes an avionics control configuration and a remote control configuration:

[0050] For the avionics control configuration, the flight control electronic system includes multiple flight control computers, which are divided into multiple primary flight control computers and heterogeneous flight control computers. The number of heterogeneous flight control computers is not limited, generally set to one, and the number of primary flight control computers is set accordingly according to the flight control processing performance. The multiple flight control computers receive aircraft motion information and navigation / guidance instructions from the airborne avionics system, execute the control laws and send them to the actuators to control the aircraft to fly according to the airborne navigation / guidance instructions;

[0051] For the remote control configuration, the flight control electronic system includes multiple flight control computers, which are divided into multiple primary flight control computers and heterogeneous flight control computers. The multiple flight control computers communicate with the ground station through the air-ground data link system and execute the control instructions sent by the ground station.

[0052] (2) Single-pilot configuration:

[0053] As Figure 5 shown, in the single-pilot configuration, the airborne avionics system and the airborne flight control system are the main inputs of the flight control electronic system.

[0054] For the single-pilot configuration, the flight control electronic system includes N flight control computers and M cockpit interface modules. The numbers of N and M depend on the safety objectives of the aircraft. The communication method between the flight control computers and the cockpit interface modules can be a one-to-one communication method or a one-to-many communication method. Figure 6 Figure 16 is a schematic diagram of the one-to-one communication method between the cockpit interface module and the flight control computer. In the figure, each cockpit interface module is connected to a corresponding flight control computer, and each flight control computer is connected through a bus. The information of each cockpit interface module can be obtained by the connected flight control computer, and all flight control computers can also obtain the information of the cockpit interface module through the bus. Figure 7 Figure 18 is a schematic diagram of the one-to-many communication method between the cockpit interface module and the flight control computer. In the figure, each cockpit interface module is connected to all flight control computers through a bus, and each flight control computer is connected through a bus, so as to ensure that the information of each cockpit interface module can be obtained by all flight control computers after being broadcast.

[0055] Each cockpit interface module remains independent and has no communication requirements. One end of each cockpit interface module is connected to the airborne flight control system outside the flight control electronic system to receive the instructions of the airborne flight control system, and the other end is connected to each flight control computer inside the flight control electronic system to send the aircraft operating system instructions to the flight control computer. The cockpit interface module is used for data acquisition and transmission, including receiving the flight vehicle control instructions in the cockpit (specifically referring to the control stick, such as the joystick, foot pedal, side stick and throttle lever) and the cockpit switch instructions (such as the mode switch, function activation switch, etc.), and sending the instructions to the flight control computer.

[0056] In the embodiment of the present application, the cockpit interface module is designed in an extremely simplified manner and only undertakes the functions of data acquisition and transmission. Assurance levels and testing are developed as methods to mitigate common mode risks. If more confidence is needed, a dissimilar design strategy similar to that of heterogeneous computers can also be adopted as a method to mitigate common mode sharing.

[0057] In addition, the flight control electronic system is also connected to the airborne avionics system, receives aircraft motion information and navigation instructions from the airborne avionics system, calculates control laws according to the instructions of the airborne flight control system and the airborne avionics system, and sends them to the actuator to control the flight of the aircraft.

[0058] (3) Multi-pilot configuration:

[0059] As Figure 8 shown, in the multi-pilot configuration, the airborne avionics system and the airborne flight control systems of multiple pilots are the main inputs to the flight control electronic system.

[0060] For the multi-pilot configuration, the flight control electronic system includes N flight control computers and M cockpit interface modules. The numbers of N and M depend on the safety objectives of the aircraft. The communication mode between the flight control computer and the cockpit interface module can be a one-to-one communication mode or a one-to-many communication mode.

[0061] One end of each cockpit interface module is connected to the airborne flight control systems of multiple pilots outside the flight control electronic system to receive the instructions of the airborne flight control system, and the other end is connected to each flight control computer within the flight control electronic system to send the aircraft operating system instructions to the flight control computer. In addition, the flight control electronic system is also connected to the airborne avionics system, receives the instructions from the airborne avionics system, calculates control laws according to the instructions of the airborne flight control system and the airborne avionics system, and sends them to the actuator to control the flight of the aircraft.

[0062] Among them, in the multi-pilot configuration, the instructions of the airborne flight control systems of multiple pilots received by each cockpit interface module include the pilot control authority instructions negotiated between the airborne flight control systems, as well as the multi-channel pilot operation instructions and cockpit switch instructions.

[0063] Figure 8Taking the dual-pilot configuration as an example, the main inputs of the flight control electronic system are two pilot control authority commands, airborne avionics system commands, and pilot operation commands. The dual-pilot configuration needs to solve the competition situation of simultaneous input of commands by two pilots. For passive side sticks, the control authority is usually allocated and declared through priority switches, priority logic, and priority indicator lights; for active side sticks, double input is avoided through linkage and tactile indication. Optionally, each sensor of the control sticks of the two pilots shares a cockpit interface module, that is, 4 cockpit interface modules are configured; in addition, as Figure 9 shown, dedicated cockpit interface modules can also be configured for the control sticks of the two pilots, that is, 8 cockpit interface modules are configured.

[0064] (4) Hybrid configuration:

[0065] The EVTOL aircraft provided by this application can support any two or more non-exclusive flight configurations, such as the hybrid configuration of single-pilot and unmanned, the hybrid configuration of multi-pilot and unmanned, the hybrid configuration of single-pilot and multi-pilot, the hybrid configuration of single-pilot, unmanned, and multi-pilot, etc.

[0066] Figure 10 Taking the hybrid configuration of single-pilot and unmanned as an example, the flight control system, airborne avionics system, and air-ground data link system are the main inputs of the flight control electronic system.

[0067] The flight control electronic system includes N flight control computers and M cockpit interface modules. The numbers of N and M depend on the safety objectives of the aircraft. The communication method between the flight control computers and the cockpit interface modules can be one-to-one communication or one-to-many communication. One end of each cockpit interface module is connected to the airborne flight control system outside the flight control electronic system to receive the airborne flight control system commands, and the other end is connected to each flight control computer inside the flight control electronic system to send the aircraft operating system commands to the flight control computer. The flight control electronic system is also connected to the airborne avionics system to receive the airborne avionics system commands (including aircraft motion information and navigation information) from the airborne avionics system. The flight control electronic system is also connected to the air-ground data link system, and multiple flight control computers communicate with the ground station through the air-ground data link system to receive the control commands sent by the ground station.

[0068] The airborne avionics system communicates with the flight control computer via a data bus and is responsible for providing the aircraft's motion information (speed, attitude, altitude, heading), navigation information. For manned aircraft, it also provides crew indication and warning, air-ground communication, and for unmanned aircraft, it provides guidance functions. The air-ground data link system (a digital data link system that transmits short messages between the aircraft and the ground station via radio or satellite) communicates with the flight control computer via a data bus. When it comes to unmanned aircraft, the air-ground data link system refers to the ground station's monitoring and control of the aircraft's state to achieve remote control. The airborne flight control system is used in the manned configuration and communicates with the flight control computer through the cockpit interface module. The airborne flight control system includes various airborne flight control devices, including but not limited to the pitch axis side stick, roll axis side stick, yaw axis side stick, throttle lever, and cockpit switches, etc.

[0069] The flight control electronic system performs control law calculations based on the instructions of the airborne flight control system, and / or the airborne avionics system, and / or the ground station control instructions, and sends them to the actuators to control the flight of the aircraft.

[0070] Embodiment 3

[0071] In the flight control electronic system of the EVTOL aircraft provided by this application, the flight control computer needs to meet the requirements of aircraft with different safety requirements and can, through configuration, meet safety objectives equivalent to or lower than those of civil transport aircraft.

[0072] There are two architectures for the flight control computer:

[0073] One is the high-integrity "control monitor compare pair" dual-branch form. The failure rate of incorrect instructions output by a single flight control computer is less than the "safety objective for catastrophic events", that is, a single computer can perform flight control functions.

[0074] The other is the single-branch form. The failure rate of incorrect instructions output by a single flight control computer usually depends on the reliability MTBF (mean time between failures) of computer components. Conservatively, the basic failure rate (1 / MTBF) is regarded as the failure rate of equipment function failure and function error for preliminary design, and subsequent optimization verification can be carried out according to the in-depth design. If the incorrect instructions output by the single branch will cause catastrophic effects and the occurrence probability is higher than the overall catastrophic safety objective, additional monitoring devices (usually adding redundancy and then using a voter to select instructions) need to be configured to improve the integrity of the instructions. (The computer working mode and output instruction selection need to be considered.)

[0075] The following is an example of adapting to different safety objectives:

[0076] The MTBF of the flight control computer and the MTBF of the cockpit interface module are 5,000 hours, and their failure rates are conservatively considered to be 2.0E-4 / FH; one-to-many communication is adopted between the flight control computer and the cockpit interface module; the flight control computers share flight control commands through point-to-point cross-transmission; the flight control computer architecture selects the form of comparison and monitoring pairs, and the probability of a single flight control computer outputting incorrect commands is less than the safety target of a single catastrophic event; the backup computer has the ability to support the safe flight and landing of the aircraft.

[0077] After the following test analysis, the above example meets the safety target:

[0078] ① For a flight control electronic system including 3 flight control computers and 4 cockpit interface modules, the loss of 3 cockpit module units or the loss of 3 flight control computers may lead to a catastrophic event, and the probability of its occurrence is 4.0e-11 / FH, which is less than 1.0e-9 / FH. Moreover, heterogeneous computers mitigate the common mode risk. Therefore, this architecture can meet the requirements of EASA SC-VTOL Category Enhanced and basic, CCAR 25 transport category aircraft, CCAR 23 part 4 / 3 level, and CCAR 29 transport category helicopters for safety.

[0079] ② For a flight control electronic system including 2 flight control computers and 4 cockpit interface modules, the loss of any 3 cockpit module units or the loss of 2 flight control computers may lead to a catastrophic event, and the probability of its occurrence is 4e-8 / FH, which is less than 1.0e-7 / FH. Moreover, heterogeneous computers mitigate the common mode risk. Therefore, this architecture can meet the safety requirements of CCAR 23 part 2 level and CCAR 27 normal category helicopters.

[0080] ③ For a flight control electronic system including 2 flight control computers and 3 cockpit interface modules, the loss of any 2 cockpit module units or the loss of 2 flight control computers may lead to a catastrophic event, and the probability of its occurrence is 1.6e-7 / FH, which is less than 1.0e-6 / FH. Moreover, heterogeneous computers mitigate the common mode risk. Therefore, this architecture can meet the safety requirements of CCAR 23 part 1 level aircraft.

[0081] Embodiment 4

[0082] Figure 11 It is an example block diagram of the function execution of the flight control electronic system. The flight control electronic system specifically performs the following operations:

[0083] Step 1110: The flight control electronic system receives flight control commands, which include the commands of the on-board flight control system (PIU) manipulated by the pilot, and / or the commands of the on-board avionics system, and / or the ground station control commands;

[0084] Step 1120: Judge the validity of the input flight control command. If it is valid, execute Step 1130; otherwise, give an instruction error prompt.

[0085] Step 1130: Select the input flight control command according to the selection strategy and output the command selection.

[0086] Among them, the selection strategy can be the instruction selection requirements set in the system. For example Figure 12 is an example diagram of input signal selection. The command for flight control can be selected from the commands of the on-board flight control system, the on-board avionics system, and the ground station control command through the majority voting method, or can be selected according to the command priority, etc. The selection method can be set by oneself and is not limited here. Figure 12 The function of 'validity judgment of instruction input' in [] generally resides in the flight control computer. For the manned configuration, it can also be selected to reside in the PIU.

[0087] Step 1140: Execute control law calculation on the selected flight control command, send the control law to the actuator, and control the flight of the aircraft.

[0088] The actuator includes but is not limited to a rudder surface controller (main control surface and control surface controller), a distributed power unit system, and a ground movement and braking control system.

[0089] Optionally, 'command selection' and 'control law calculation' reside in the flight control computer, and 'output command selection' can reside in the flight control computer or in the actuator.

[0090] Corresponding to the above embodiments, an embodiment of the present invention provides a computer storage medium, including: at least one memory and at least one processor; the memory is used to store one or more program instructions; the processor is used to run one or more program instructions.

[0091] In the embodiment of the present invention, the processor can be an integrated circuit chip with signal processing capabilities. The processor can be a general-purpose processor, a digital signal processor (DSP for short), an application specific integrated circuit (ASIC for short), a field programmable gate array (FPGA for short), or other programmable logic devices, discrete gate or transistor logic devices, discrete hardware components.

[0092] The various methods, steps, and logic block diagrams disclosed in the embodiments of the present invention can be implemented or executed. The general-purpose processor can be a microprocessor, or the processor can also be any conventional processor, etc. The steps of the method disclosed in combination with the embodiments of the present invention can be directly embodied as being executed and completed by a hardware decoding processor, or can be executed and completed by a combination of hardware and software modules in the decoding processor. The software module can be located in a mature storage medium in the art such as random access memory, flash memory, read-only memory, programmable read-only memory, or electrically erasable programmable memory, register, etc. The processor reads the information in the storage medium and combines its hardware to complete the steps of the above method.

[0093] The storage medium can be a memory, for example, it can be a volatile memory or a non-volatile memory, or can include both volatile and non-volatile memories.

[0094] Among them, the non-volatile memory can be read-only memory (ROM for short), programmable read-only memory (PROM for short), erasable programmable read-only memory (EPROM for short), electrically erasable programmable read-only memory (EEPROM for short), or flash memory.

[0095] The volatile memory can be random access memory (RAM for short), which is used as an external cache. By way of example but not limitation, many forms of RAM are available, such as static random access memory (SRAM for short), dynamic random access memory (DRAM for short), synchronous dynamic random access memory (SDRAM for short), double data rate synchronous dynamic random access memory (DDR SDRAM for short), enhanced synchronous dynamic random access memory (ESDRAM for short), synchlink dynamic random access memory (SLDRAM for short), and direct rambus random access memory (DRRAM for short).

[0096] The storage media described in the embodiments of the present invention are intended to include but not be limited to these and any other suitable types of memories.

[0097] Those skilled in the art should be able to realize that in one or more of the above examples, the functions described in the present invention can be implemented by a combination of hardware and software. When applying software, the corresponding functions can be stored in a computer-readable medium or transmitted as one or more instructions or codes on a computer-readable medium. The computer-readable medium includes computer storage media and communication media, where the communication media includes any medium that facilitates the transmission of a computer program from one place to another. The storage media can be any available medium accessible by a general-purpose or special-purpose computer.

[0098] The above specific implementation manners have further elaborated on the purpose, technical solutions, and beneficial effects of the present invention. It should be understood that the above are only specific implementation manners of the present invention and are not used to limit the protection scope of the present invention. Any modifications, equivalent replacements, improvements, etc. made on the basis of the technical solutions of the present invention should be included in the protection scope of the present invention.

Claims

1. An electronic flight control system for an EVTOL aircraft, characterized in that, Comprising: Multiple cockpit interface modules, and a flight control computer; the inputs of the multiple cockpit interfaces are respectively communicatively connected to the airborne flight control system; The outputs of the multiple cockpit interfaces are respectively communicatively connected to at least one flight control computer; The input of each flight control computer is communicatively connected to the airborne avionics system and / or the air-ground data link system, and the output of each flight control computer is connected to an actuator; The flight control computer receives instructions from the cockpit interface module and / or the airborne avionics system and / or the air-ground data link system, outputs a control signal through the flight control computer, and controls the actuator to act according to the control signal.

2. The flight control electronic system of an EVTOL aircraft according to claim 1, characterized in that Digital bus communication is adopted between the multiple flight control computers, and the communication mode is point-to-point communication or broadcast communication.

3. An electronic flight control system for an EVTOL aircraft according to claim 1, characterized in that, The multiple flight control computers include a main flight control computer and heterogeneous flight control computers, and information synchronization and cross-monitoring are carried out between the main flight control computer and the heterogeneous flight control computers; the flight control computer receives instructions from the cockpit interface module and / or the airborne avionics system and / or the air-ground data link system, outputs a first control signal through the main flight control computer, and outputs a second control signal through the heterogeneous flight control computer, and controls the actuator to act through the first control signal and / or the second control signal.

4. The flight control electronic system of an EVTOL aircraft according to claim 1, wherein Digital bus communication is adopted between the multiple cockpit interfaces and the multiple flight control computers, and the communication mode is point-to-point communication or broadcast communication.

5. The flight control electronic system of an EVTOL aircraft according to claim 1, characterized in that, The airborne flight control system includes: cockpit switches and at least one first joystick; The input of each cockpit interface is respectively communicatively connected to the cockpit switch and at least one first joystick.

6. An EVTOL aircraft flight control electronic system as claimed in claim 5, characterized in that, The airborne flight control system further includes: at least one second joystick; The input of each cockpit interface is respectively communicatively connected to the cockpit switch, at least one first joystick, and at least one second joystick.

7. An electronic flight control system for an EVTOL aircraft according to claim 5, characterized in that, The airborne flight control system further includes: at least one second joystick; The inputs of some of the multiple cockpit interfaces are respectively communicatively connected to the first joystick, and the inputs of another part of the multiple cockpit interfaces are respectively communicatively connected to the second joystick.

8. The flight control electronic system of an EVTOL aircraft as claimed in claim 1, wherein, The flight control electronic system communicates with the airborne avionics system and / or the air-ground data link system through the flight control computer, and / or communicates with the airborne flight control system through the flight control computer and the cockpit interface module, so as to implement at least one aircraft flight configuration, and the aircraft flight configuration includes at least one of an unmanned configuration, and / or a single-pilot configuration, and / or a multi-pilot configuration.

9. An EVTOL aircraft, characterized in that, The EVTOL aircraft includes an EVTOL aircraft flight control electronic system according to any one of claims 1-8.

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