Aircraft multi-mode switching method and related equipment for full life cycle

Abstract

The disclosed method and related equipment for aircraft multimodal switching throughout its lifecycle, which initializes a ground control system and utilizes a remote interactive computer in the ground control system to receive an upper-layer switching instruction; upon receiving the upper-layer switching instruction, determining whether the aircraft launch preparation time is within a preset time range; if the aircraft launch preparation time is not within the preset time range, controlling the remote interactive computer to enter a standby or dormant state using a power management module (DPM) until the aircraft launch preparation time is within the preset time range; if the aircraft launch preparation time is within the preset time range, responding to the upper-layer switching instruction; and controlling the equipment in the ground control system to execute a specific mode management scheme based on the upper-layer switching instruction, thereby achieving autonomous switching of the aircraft's multimodal modes. This method can effectively achieve switching between aircraft multimodal modes and simultaneously automatically monitor the changing trends of the aircraft's multimodal conversion process in real time.

Description

Technical Field

[0001] The present invention belongs to the technical field of aircraft multi-mode switching, and in particular relates to an aircraft multi-mode switching method for the entire life cycle and related equipment. Background Art

[0002] Aircraft are specialized products designed for long-term storage and single-launch use. Their operational testing and control involve multiple modes. Effectively dividing these modes and effectively switching between them has long been a major challenge for development, production, and operational teams. Due to their complex structure, high price, and small production runs, accelerated lifespan research methods are still immature, making it difficult to develop and implement scientifically sound and practical mode control strategies for optimal health management during development and production. Due to a lack of data supporting actual storage environments and actual aircraft testing, the current international standard is to maintain a single-mode test and control system with long-term power on, which often reduces the aircraft's service life.

[0003] The multimodality (multiple operating modes) of aircraft development primarily aims to meet the mission requirements of the aircraft's equipment systems, sacrificing some performance of the aircraft system platform to achieve the development goals of low-loss and low-cost multimodal management. However, this reduced performance does not affect the normal operation of the entire aircraft system. This is because, as an aircraft system under development, each design mode state does not require long-term use and is generally used for standby. When the aircraft system needs to enter a certain mode or simulation state, the multimodal autonomous system will be able to quickly boot from low-loss mode to normal operating mode, ensuring the normal operation of the aircraft system. However, the process of rapidly booting from low-loss mode to normal operating mode can lead to a degradation trend. Summary of the Invention

[0004] The present invention overcomes one of the shortcomings of the prior art and provides a method and related equipment for aircraft multimodal switching throughout its entire life cycle, which can effectively realize switching between aircraft multimodal modes and at the same time realize real-time automatic monitoring of the changing trend of the control system during the aircraft multimodal conversion process.

[0005] According to one aspect of the present disclosure, a method for multi-mode switching of an aircraft throughout its entire life cycle is proposed, the method comprising:

[0006] Initializing the ground control system and receiving an upper layer switching instruction using a remote interactive computer of the ground control system;

[0007] After receiving the upper layer switching instruction, determining whether the aircraft launch preparation time is within a preset time range;

[0008] When the aircraft launch preparation time is not within the preset time range, the energy management and control module DPM is used to control the remote interactive computer to be in a standby or dormant state until the aircraft launch preparation time is within the preset time range;

[0009] When the aircraft launch preparation time is within a preset time range, responding to the upper layer switching instruction;

[0010] According to the upper layer switching instruction, the equipment in the ground control system is controlled to execute a specific mode management solution to achieve autonomous switching of the aircraft's multi-mode.

[0011] In one possible implementation, the upper-layer switching instructions include: an instruction to control the aircraft to start working in the emergency launch mode, an instruction to control the aircraft to start working in the core mechanism hot backup component mode, an instruction to control the aircraft to start working in all aircraft hot backup modes, an instruction to control the aircraft to jump from the emergency launch mode to the core mechanism hot backup component mode, an instruction to control the aircraft to jump from the emergency launch mode to the aircraft's full hot backup mode, and an instruction to control the aircraft to jump from the core mechanism hot backup component mode to the aircraft's full hot backup mode.

[0012] In a possible implementation, the preset range is t0-5t0, where t0 is the preset unit working time;

[0013] When the aircraft launch preparation time is within a preset time range, responding to the upper layer switching instruction includes:

[0014] When the launch preparation time of the aircraft is 3t0, responding to the instruction to control the aircraft to start working in the emergency launch mode;

[0015] When the launch preparation time of the aircraft is 4t0, responding to the instruction to control the aircraft to start working in the core mechanism hot backup component mode;

[0016] When the launch preparation time of the aircraft is 5t0, responding to the control aircraft to start working in all hot backup instructions of the aircraft;

[0017] When the launch preparation time of the aircraft is t0, the response control aircraft jumps from the emergency launch mode to the core mechanism hot backup component mode instruction or the response control aircraft jumps from the core mechanism hot backup component mode to the core mechanism hot backup component mode instruction

[0018] When the aircraft launch preparation time is 2t0, the aircraft is controlled to jump from the emergency launch mode to the aircraft full hot backup mode instruction in response.

[0019] In a possible implementation, the equipment of the ground control system includes: a fire control box, a small power supply, a measurement and control processing unit, a power supply system, a command and control system, a processor, an emergency processing device, and a mains power supply.

[0020] In a possible implementation, controlling the device in the ground control system to execute a specific mode management solution according to the upper layer switching instruction includes:

[0021] When the upper layer switching instruction is an instruction to control the aircraft to start working in the emergency launch mode, a specific mode management scheme is provided for controlling the fire control box and the small power supply in the ground control system to be in the working state and other devices to be in the dormant state;

[0022] When the upper layer switching instruction is an instruction to control the aircraft to start working in the core mechanism hot backup component mode, a specific mode management scheme is used to control the measurement and control processing unit and the power supply system in the ground control system to be in working state and other devices to be in dormant state;

[0023] When the upper-layer switching instruction is an instruction to control the aircraft to start working in the aircraft's full hot backup mode, a specific mode management scheme is provided to control the command and control system, processor, emergency processing device, and mains power in the ground control system to be in working state and other equipment to be in dormant state.

[0024] In a possible implementation, controlling the devices in the ground control system to execute a specific mode management solution according to the upper layer switching instruction further includes:

[0025] When the upper layer switching instruction is an instruction to control the aircraft to jump from the emergency launch mode to the core mechanism hot backup component mode, the fire control box and the small power supply are turned off, and the measurement and control processing unit and the power supply system are awakened to work.

[0026] In a possible implementation, the energy management and control module DPM includes: a normal state, an idle state, and a sleep state; the idle state is converted to the normal state or the sleep state, and the normal state and the sleep state are converted to each other.

[0027] According to another aspect of the present disclosure, a multi-modal switching system for an aircraft throughout its entire life cycle is provided, the system comprising:

[0028] An initialization module, configured to initialize a ground control system and receive an upper layer switching instruction using a remote interactive computer of the ground control system;

[0029] A judgment module, configured to determine whether the aircraft launch preparation time is within a preset time range after receiving the upper layer switching instruction;

[0030] a sleep module, configured to, when the aircraft launch preparation time is not within a preset time range, control the remote interactive computer to be in a sleep state using the energy management and control module DPM until the aircraft launch preparation time is within the preset time range;

[0031] A response module, configured to respond to the upper layer switching instruction when the aircraft launch preparation time is within a preset time range;

[0032] The switching module is used to control the equipment in the ground control system to execute a specific mode management solution according to the upper-layer switching instruction, so as to realize the autonomous switching of the aircraft's multi-mode.

[0033] According to another aspect of the present disclosure, an electronic device is provided. The device includes a memory, a processor, and a computer program stored in the memory and executable on the processor. When the processor executes the program, the method described above is implemented.

[0034] According to another aspect of the present disclosure, a computer-readable storage medium is provided, wherein the computer-readable storage medium stores a computer program, and when the computer program is executed by a processor, the method described above is implemented.

[0035] The disclosed method for aircraft multimodal switching throughout its lifecycle includes initializing a ground control system and utilizing a remote interactive computer of the ground control system to receive an upper-layer switching instruction. Upon receiving the upper-layer switching instruction, the method determines whether the aircraft launch preparation time is within a preset time range. If the aircraft launch preparation time is not within the preset time range, the remote interactive computer is controlled by an energy management and control module (DPM) to enter a standby or dormant state until the aircraft launch preparation time is within the preset time range. If the aircraft launch preparation time is within the preset time range, the remote interactive computer responds to the upper-layer switching instruction. Based on the upper-layer switching instruction, the device in the ground control system is controlled to execute a specific mode management scheme to achieve autonomous switching of the aircraft's multimodal modes. The method effectively achieves switching between aircraft multimodal modes and simultaneously automatically monitors the changing trends of the control system during the aircraft multimodal conversion process in real time. BRIEF DESCRIPTION OF THE DRAWINGS

[0036] The accompanying drawings are used to provide a further understanding of the technical solution of this application or the prior art and constitute a part of the specification. Among them, the drawings that express the embodiments of this application are used together with the embodiments of this application to explain the technical solution of this application, but do not constitute a limitation of the technical solution of this application.

[0037] Figure 1 A flowchart of a multi-mode switching method for an aircraft throughout its life cycle according to an embodiment of the present disclosure is shown;

[0038] Figure 2 A flow chart of a multi-mode switching method for an aircraft throughout its life cycle according to another embodiment of the present disclosure is shown;

[0039] Figure 3 A schematic diagram of the energy management and control module DPM state according to an embodiment of the present disclosure is shown;

[0040] Figure 4 A block diagram of a multi-mode switching system for an aircraft throughout its life cycle according to an embodiment of the present disclosure is shown;

[0041] Figure 5 FIG. 4 shows a structural diagram of an electronic device 3 according to an embodiment of the present disclosure. DETAILED DESCRIPTION

[0042] The following will describe the implementation methods of the present invention in detail with reference to the accompanying drawings and embodiments, so that the implementation process of how the present invention applies technical means to solve technical problems and achieve corresponding technical effects can be fully understood and implemented accordingly. The various features in the examples and embodiments of this application can be combined with each other without conflict, and the resulting technical solutions are all within the scope of protection of the present invention.

[0043] In addition, the steps shown in the flowchart of the accompanying drawings can be executed in a computer such as a set of computer-executable instructions. Also, although a logical order is shown in the flowchart, in some cases, the steps shown or described can be performed in a different order than here.

[0044] Figure 1 and Figure 2 The following are respectively shown: a method for multi-mode switching of an aircraft for the entire life cycle according to an embodiment of the present disclosure. The method is applied to a ground control system for multi-mode switching of an aircraft, such as Figure 1 As shown, the method may include:

[0045] Step S1: Initialize the ground control system and use the remote interactive computer of the ground control system to receive an upper-layer switching instruction.

[0046] like Figure 2 As shown, initializing the ground control system involves powering on various devices in the ground control system, initializing the ground control system software, and starting the ground control system. In addition to the remote interactive computer, the various devices in the ground control system also include a fire control box, a small power supply, a measurement and control processing unit, a power supply system, a command and control system, a processor, an emergency response device, and a mains power supply.

[0047] The upper-level switching instructions include: instructions for controlling the aircraft to start working in emergency launch mode, instructions for controlling the aircraft to start working in core mechanism hot backup component mode, instructions for controlling the aircraft to start working in all aircraft hot backup mode, instructions for controlling the aircraft to jump from emergency launch mode to core mechanism hot backup component mode, instructions for controlling the aircraft to jump from emergency launch mode to all aircraft hot backup mode, and instructions for controlling the aircraft to jump from core mechanism hot backup component mode to all aircraft hot backup mode.

[0048] Step S2: After receiving the upper layer switching instruction, determine whether the aircraft launch preparation time is within a preset time range.

[0049] Among them, upper-layer switching commands have the highest priority, allowing the aircraft to interrupt the current operating mode at any time. For example, after receiving an upper-layer switching command, the aircraft responds to the upper computer's mode switching program flow based on its own health status and determines whether the aircraft's launch preparation time is within the preset time range. For example, if the preset time range is t0-5t0, where t0 is the preset unit operating time, the aircraft will determine whether the launch preparation time is within t0-5t0.

[0050] Step S3: When the aircraft launch preparation time is not within the preset time range, the energy management and control module DPM is used to control the remote interactive computer to be in a standby or dormant state until the aircraft launch preparation time is within the preset time range.

[0051] The energy management and control module DPM includes: a normal state, an idle state and a sleep state; the idle state is converted to the normal state or the sleep state, and the normal state and the sleep state are converted to each other.

[0052] Figure 3 A schematic diagram of the energy management and control module DPM state according to an embodiment of the present disclosure is shown.

[0053] The energy management module DPM (Dynamic Power Management) is a method that supports dynamic configuration of power consumption modes. Figure 3 As shown, the autonomous switching program (DPM) may include: a normal state NMAL, an idle state IDLE and a sleep state SLEEP; the idle state IDLE switches to the normal state NMAL or the sleep state SLEEP, and the normal state NMAL and the sleep state SLEEP switch to each other.

[0054] like Figure 3As shown, it takes t1 time to switch from the idle state IDLE to the normal state NMAL, t2 time to switch from the idle state IDLE to the SLEEP state, t3 time to switch from the normal state NMAL to the sleep state SLEEP, and t4 time to switch from the sleep state SLEEP to the normal state NMAL. At this time, it is necessary to determine whether it is worthwhile to enter the sleep state SLEEP (low power mode) in the idle state IDLE according to the onboard control system. When the idle time is short, the energy consumption of the die-cutting switch will be greater than the energy savings of the low power mode to the normal mode in the same time. In this case, it is not suitable to switch the energy. That is, the state switching of the corresponding mode of the equipment is performed through the energy management and control module DPM unit. Under the premise of achieving functional requirements, the power consumption of the ground control system can be controlled to the lowest possible level to run, including the realization of switching between different power consumption modes.

[0055] Step S4: When the aircraft launch preparation time is within the preset time range, respond to the upper layer switching instruction.

[0056] When it is determined that the aircraft launch preparation time is within t0-5t0, different upper layer switching instructions are responded to according to the aircraft launch preparation time, which may be:

[0057] When the aircraft launch preparation time is 3t0, the aircraft is controlled to start operating in emergency launch mode. That is, when the aircraft launch preparation time is greater than 3t0, all equipment in the ground control system is dormant until 3t0 and then restarted. When the aircraft launch preparation time is less than 3t0, the ground control system enters a standby state, waiting for new instructions from the remote interactive computer sent by the person in the loop. The waiting process does not respond to the mode switch.

[0058] When the launch preparation time of the aircraft is 4t0, the aircraft is controlled to start operating in the core mechanism hot backup component mode. That is, when the launch preparation time of the aircraft is greater than 4t0, all equipment in the ground control system will be dormant until 3t0 and then restarted. When the launch preparation time of the aircraft is less than 4t0, the ground control system will enter a standby state, waiting for new instructions from the remote interactive computer sent by the person in the loop. The waiting process does not respond to this mode switch.

[0059] When the aircraft launch preparation time is 5t0, the aircraft is controlled to start operating in full hot standby mode. That is, when the aircraft launch preparation time is greater than 5t0, all devices in the ground control system are put into hibernation until 5t0 and then restarted. That is, when the aircraft launch preparation time is less than 5t0, the ground control system enters a standby state, waiting for new remote interactive computer commands sent by the person in the loop. The waiting process does not respond to this mode switch.

[0060] When the aircraft launch preparation time is t0, the aircraft is controlled to switch from the emergency launch mode to the core mechanism hot backup component mode, or to switch from the core mechanism hot backup component mode to the core mechanism hot backup component mode. That is, when the aircraft launch preparation time is greater than t0, all devices in the ground control system are put into hibernation until time 3t0 and then restarted. That is, when the aircraft launch preparation time is less than t0, the ground control system enters a standby state, waiting for new remote interactive computer instructions sent by the person in the loop, and the waiting process does not respond to the mode switch.

[0061] When the aircraft launch preparation time is 2t0, the aircraft is controlled to switch from emergency launch mode to full hot standby mode. Specifically, when the aircraft launch preparation time is greater than 2t0, all devices in the ground control system are put into hibernation until 2t0 and then restarted. Specifically, when the aircraft launch preparation time is less than 2t0, the ground control system enters a standby state, awaiting new commands from the remote interactive computer sent by the person in the loop. The waiting process does not respond to the mode switch.

[0062] Step S5: Controlling the equipment in the ground control system to execute a specific mode management solution according to the upper layer switching instruction, so as to realize the autonomous switching of the aircraft's multi-mode.

[0063] When the ground control system receives a switching instruction from the upper layer, each device controlling the ground control system implements a specific mode management solution.

[0064] In one example, controlling the equipment in the ground control system to execute a specific mode management solution according to the upper layer switching instruction includes:

[0065] When the upper-layer switching instruction is to control the aircraft to start operating in emergency launch mode, a specific mode management scheme is used to control the fire control box and small power supply in the ground control system to be in an active state, while other equipment in the ground control system is in a dormant state. This is the simplest and fastest way to switch the aircraft to start operating in emergency launch mode. Clock gating can be used to drive the underlying chip, operating the embedded, highly real-time measurement and control equipment in the ground control system: the fire control box, small power supply. Other ground control system equipment (measurement and control processing unit, power supply system, command and control system, processor, emergency response device, and mains power) is in a dormant state. This effectively meets the basic measurement and control requirements of the aircraft and enables ground test control in emergency launch mode.

[0066] When the upper-layer switching instruction is an instruction to control the aircraft to start working in the core mechanism hot backup component mode, a specific mode management scheme is provided to control the measurement and control processing unit and the power supply system in the ground control system to be in working state and other equipment to be in dormant state.

[0067] In such situations, every component of the ground control system must switch states. When the remote interactive computer responds to a human-in-the-loop intervention command, the state switch is completed first. Then, the measurement and control processing unit and the power supply system are awakened from their dormant state, returning them to an operational state while simultaneously shutting down the embedded devices. The measurement and control processing unit, compared to the fire control box, has more complex system operation capabilities and supports multi-threaded online scheduling. Compared to the small power supply used in emergency launch mode, the power supply system can achieve high-power, variable-frequency, and high-voltage output, supporting the testing and control requirements of the hot-backup mode of the aircraft's core mechanisms.

[0068] When the upper-layer switching instruction is to control the aircraft to start working in the aircraft's full hot backup mode, a specific mode management solution is provided to control the command and control system, processor, emergency processing device, and mains power in the ground control system to be in working state and other equipment to be in dormant state.

[0069] The aircraft's startup control operates under hot backup mode for all ground equipment. The remote interactive computer switches to full-speed operation and wakes up all command and control systems, processors, emergency response devices, and mains power, ensuring the redundant fault tolerance and robustness of the ground control system. The command and control system is used for information-assisted decision-making, the processor enhances the equipment's backend processing capabilities, and the emergency response device provides redundant processing capabilities in emergency situations.

[0070] In addition, when the upper layer switching instruction is an instruction to control the aircraft to jump from the emergency launch mode to the core mechanism hot backup component mode, the fire control box and the small power supply are turned off, and the measurement and control processing unit and the power supply system are awakened.

[0071] For example, in emergency launch mode, the fire control box and small power supply of the aircraft's ground control system act as real-time response core devices. When the emergency launch mode is switched to core mechanism hot backup component mode, the remote interactive computer responds to human-in-the-loop commands and executes the mode switching control program, while meeting the space switching time.

[0072] During the transition from emergency launch mode to core mechanism hot backup component mode, the system first awakens the measurement and control processing unit and power supply system to an operational state, simultaneously turning on the analog circuit power of the measurement and control processing unit and the power supply system. Fault diagnosis of the measurement and control processing unit and the power supply system's data acquisition system is then completed. After completing the fault diagnosis of the measurement and control processing unit and the power supply system's data acquisition system, if no new upper-layer switching instructions are received after a preset idle time, the measurement and control processing unit and the power supply system are switched to shutdown mode, and the ground control system is controlled to switch back to emergency launch mode, protecting the reliability of the core actuator.

[0073] The disclosed method for aircraft multimodal switching throughout its lifecycle includes initializing a ground control system and utilizing a remote interactive computer of the ground control system to receive an upper-layer switching instruction. Upon receiving the upper-layer switching instruction, the method determines whether the aircraft launch preparation time is within a preset time range. If the aircraft launch preparation time is not within the preset time range, the remote interactive computer is controlled by an energy management and control module (DPM) to enter a standby or dormant state until the aircraft launch preparation time is within the preset time range. If the aircraft launch preparation time is within the preset time range, the remote interactive computer responds to the upper-layer switching instruction. Based on the upper-layer switching instruction, the device in the ground control system is controlled to execute a specific mode management scheme to achieve autonomous switching of the aircraft's multimodal modes. The method effectively achieves switching between aircraft multimodal modes and simultaneously automatically monitors the changing trends of the control system during the aircraft multimodal conversion process in real time.

[0074] The following are device embodiments of the present application, which can be used to implement the method embodiments of the present application. For details not disclosed in the device embodiments of the present application, please refer to the method embodiments of the present application.

[0075] Figure 4 FIG. 1 shows a block diagram of a multi-mode switching system for an aircraft throughout its life cycle according to an embodiment of the present disclosure; FIG. Figure 4 As shown, the system may include:

[0076] Initialization module 401 is used to initialize the ground control system and receive upper layer switching instructions using the remote interactive computer of the ground control system;

[0077] The judgment module 402 is used to judge whether the aircraft launch preparation time is within a preset time range after receiving the upper layer switching instruction;

[0078] The sleep module 403 is configured to control the remote interactive computer to be in a sleep state by using the energy management and control module DPM when the aircraft launch preparation time is not within the preset time range, until the aircraft launch preparation time is within the preset time range;

[0079] A response module 404 is configured to respond to the upper layer switching instruction when the aircraft launch preparation time is within a preset time range;

[0080] The switching module 405 is used to control the equipment in the ground control system to execute a specific mode management solution according to the upper layer switching instruction, so as to realize the autonomous switching of the aircraft's multi-mode.

[0081] It should be understood that the size of the serial numbers of the steps in the above embodiments does not mean the order of execution. The execution order of each process should be determined by its function and internal logic, and should not constitute any limitation on the implementation process of the embodiments of this application.

[0082] Figure 5 Schematic diagram of the structure of the electronic device 3 provided in the embodiment of the present application. Figure 5 As shown, the electronic device 3 of this embodiment includes: a processor 301, a memory 302, and a computer program 303 stored in the memory 302 and executable on the processor 301. When the processor 301 executes the computer program 303, the steps of the above-mentioned method embodiments are implemented. Alternatively, when the processor 301 executes the computer program 303, the functions of the modules / units in the above-mentioned device embodiments are implemented.

[0083] For example, computer program 303 may be divided into one or more modules / units, which are stored in memory 302 and executed by processor 301 to implement the present application. One or more modules / units may be a series of computer program instruction segments capable of performing specific functions, and the instruction segments are used to describe the execution process of computer program 303 in electronic device 3.

[0084] The electronic device 3 may be a desktop computer, a notebook, a PDA, a cloud server or other electronic device. The electronic device 3 may include but is not limited to a processor 301 and a memory 302. Those skilled in the art will understand that Figure 3 It is only an example of electronic device 3 and does not constitute a limitation of electronic device 3. It may include more or fewer components than shown in the figure, or a combination of certain components, or different components. For example, the electronic device may also include input and output devices, network access devices, buses, etc.

[0085] The processor 301 may be a central processing unit (CPU), or other general-purpose processors, digital signal processors (DSP), application-specific integrated circuits (ASIC), field-programmable gate arrays (FPGA), or other programmable logic devices, discrete gate or transistor logic devices, discrete hardware components, etc. The general-purpose processor may be a microprocessor or any conventional processor.

[0086] The memory 302 can be an internal storage unit of the electronic device 3, such as a hard drive or memory of the electronic device 3. The memory 302 can also be an external storage device of the electronic device 3, such as a plug-in hard drive, a Smart Media Card (SMC), a Secure Digital (SD) card, a flash memory card, etc. equipped on the electronic device 3. Furthermore, the memory 302 can include both an internal storage unit of the electronic device 3 and an external storage device. The memory 302 is used to store computer programs and other programs and data required by the electronic device. The memory 302 can also be used to temporarily store data that has been output or is about to be output.

[0087] Those skilled in the art can clearly understand that, for the convenience and brevity of description, only the division of the above-mentioned functional units and modules is used as an example for illustration. In actual applications, the above-mentioned functions can be distributed and completed by different functional units and modules as needed, that is, the internal structure of the device can be divided into different functional units or modules to complete all or part of the functions described above. The functional units and modules in the embodiment can be integrated into one processing unit, or each unit can exist physically alone, or two or more units can be integrated into one unit. The above-mentioned integrated unit can be implemented in the form of hardware or in the form of software functional units. In addition, the specific names of the functional units and modules are only for the convenience of distinguishing each other, and are not used to limit the scope of protection of this application. The specific working process of the units and modules in the above-mentioned system can refer to the corresponding process in the aforementioned method embodiment, and will not be repeated here.

[0088] In the above embodiments, the description of each embodiment has its own focus. For parts that are not described or recorded in detail in a certain embodiment, reference can be made to the relevant description of other embodiments.

[0089] Those skilled in the art will appreciate that the units and algorithm steps of each example described in conjunction with the embodiments applied for herein can be implemented in electronic hardware, or a combination of computer software and electronic hardware. Whether these functions are performed in hardware or software depends on the specific application and design constraints of the technical solution. Professional and technical personnel can use different methods to implement the described functions for each specific application, but such implementation should not be considered beyond the scope of this application.

[0090] In the embodiments provided in this application, it should be understood that the disclosed apparatus / computer equipment and methods can be implemented in other ways. For example, the apparatus / computer equipment embodiments described above are merely schematic. For example, the division of modules or units is merely a logical function division. In actual implementation, there may be other division methods. Multiple units or components may be combined or integrated into another system, or some features may be ignored or not executed. Another point is that the mutual coupling or direct coupling or communication connection shown or discussed may be through some interfaces, indirect coupling or communication connection of the apparatus or unit, which may be electrical, mechanical or other forms.

[0091] Units described as separate components may or may not be physically separate, and 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 these units may be selected to achieve the purpose of this embodiment according to actual needs.

[0092] In addition, the functional units in the various embodiments of the present application may be integrated into a single processing unit, or each unit may exist physically separately, or two or more units may be integrated into a single unit. The aforementioned integrated units may be implemented in the form of hardware or software functional units.

[0093] If the integrated module / unit is implemented in the form of a software functional unit and sold or used as an independent product, it can be stored in a computer-readable storage medium. Based on this understanding, the present application implements all or part of the process in the above-mentioned embodiment method, and can also be completed by instructing the relevant hardware through a computer program. The computer program can be stored in a computer-readable storage medium, and when the computer program is executed by the processor, it can implement the steps of the above-mentioned various method embodiments. The computer program may include computer program code, which may be in source code form, object code form, executable file or some intermediate form. The computer-readable medium may include: any entity or device capable of carrying computer program code, recording medium, USB flash drive, mobile hard disk, magnetic disk, optical disk, computer memory, read-only memory (ROM), random access memory (RAM), electric carrier signal, telecommunication signal and software distribution medium. It should be noted that the content contained in the computer-readable medium can be appropriately increased or decreased according to the requirements of legislation and patent practice in the jurisdiction. For example, in some jurisdictions, according to legislation and patent practice, computer-readable media do not include electric carrier signals and telecommunication signals.

[0094] The above embodiments are only used to illustrate the technical solutions of the present application, rather than to limit them. Although the present application has been described in detail with reference to the aforementioned embodiments, those skilled in the art should understand that they can still modify the technical solutions described in the aforementioned embodiments, or make equivalent replacements for some of the technical features therein. These modifications or replacements do not deviate the essence of the corresponding technical solutions from the spirit and scope of the technical solutions of the various embodiments of the present application, and should all be included in the scope of protection of the present application.

Claims

1. A multi-mode switching method for an aircraft throughout its life cycle, characterized in that: The method comprises: Initializing the ground control system and receiving an upper layer switching instruction using a remote interactive computer of the ground control system; After receiving the upper layer switching instruction, determining whether the aircraft launch preparation time is within a preset time range; When the aircraft launch preparation time is not within the preset time range, the energy management and control module DPM is used to control the remote interactive computer to be in a dormant state until the aircraft launch preparation time is within the preset time range; When the aircraft launch preparation time is within a preset time range, responding to the upper layer switching instruction; According to the upper layer switching instruction, the equipment in the ground control system is controlled to execute a specific mode management solution to achieve autonomous switching of the aircraft's multi-mode.

2. The aircraft multi-mode switching method according to claim 1, characterized in that: The upper-level switching instructions include: instructions for controlling the aircraft to start working in emergency launch mode, instructions for controlling the aircraft to start working in core mechanism hot backup component mode, instructions for controlling the aircraft to start working in all aircraft hot backup mode, instructions for controlling the aircraft to jump from emergency launch mode to core mechanism hot backup component mode, instructions for controlling the aircraft to jump from emergency launch mode to all aircraft hot backup mode, and instructions for controlling the aircraft to jump from core mechanism hot backup component mode to all aircraft hot backup mode.

3. The aircraft multi-mode switching method according to claim 2, characterized in that: The preset time range is t0-5t0, where t0 is the preset unit working time; When the aircraft launch preparation time is within a preset time range, responding to the upper layer switching instruction includes: When the launch preparation time of the aircraft is 3t0, responding to the instruction to control the aircraft to start working in the emergency launch mode; When the launch preparation time of the aircraft is 4t0, responding to the instruction to control the aircraft to start working in the core mechanism hot backup component mode; When the launch preparation time of the aircraft is 5t0, responding to the control aircraft to start working in all hot backup instructions of the aircraft; When the launch preparation time of the aircraft is t0, responding to the control of the aircraft to jump from the emergency launch mode to the core mechanism hot backup component mode instruction or responding to the control of the aircraft to jump from the core mechanism hot backup component mode to the core mechanism hot backup component mode instruction; When the aircraft launch preparation time is 2t0, the aircraft is controlled to jump from the emergency launch mode to the aircraft full hot backup mode instruction in response.

4. The aircraft multi-mode switching method according to claim 3, characterized in that: The equipment of the ground control system includes: a fire control box, a small power supply, a measurement and control processing unit, a power supply system, a command and control system, a processor, an emergency processing device, and a mains power supply.

5. The aircraft multi-mode switching method according to claim 4, characterized in that: Controlling the equipment in the ground control system to execute a specific mode management solution according to the upper layer switching instruction includes: When the upper layer switching instruction is an instruction to control the aircraft to start working in the emergency launch mode, a specific mode management scheme is provided for controlling the fire control box and the small power supply in the ground control system to be in the working state and other devices to be in the dormant state; When the upper layer switching instruction is an instruction to control the aircraft to start working in the core mechanism hot backup component mode, a specific mode management scheme is used to control the measurement and control processing unit and the power supply system in the ground control system to be in working state and other devices to be in dormant state; When the upper-layer switching instruction is an instruction to control the aircraft to start working in the aircraft's full hot backup mode, a specific mode management scheme is provided to control the command and control system, processor, emergency processing device, and mains power in the ground control system to be in working state and other equipment to be in dormant state.

6. The aircraft multi-mode switching method according to claim 4, characterized in that: Controlling the equipment in the ground control system to execute a specific mode management solution according to the upper layer switching instruction also includes: When the upper layer switching instruction is an instruction to control the aircraft to jump from the emergency launch mode to the core mechanism hot backup component mode, the fire control box and the small power supply are turned off, and the measurement and control processing unit and the power supply system are awakened to work.

7. The aircraft multi-mode switching method according to claim 1, characterized in that: The energy management and control module DPM includes: a normal state, an idle state and a sleep state; the idle state switches to the normal state or the sleep state, and the normal state and the sleep state switch to each other.

8. A multi-modal switching system for aircraft throughout its life cycle, characterized in that: The system comprises: An initialization module, configured to initialize a ground control system and receive an upper layer switching instruction using a remote interactive computer of the ground control system; A judgment module, configured to determine whether the aircraft launch preparation time is within a preset time range after receiving the upper layer switching instruction; a sleep module, configured to, when the aircraft launch preparation time is not within a preset time range, control the remote interactive computer to be in a sleep state using the energy management and control module DPM until the aircraft launch preparation time is within the preset time range; A response module, configured to respond to the upper layer switching instruction when the aircraft launch preparation time is within a preset time range; The switching module is used to control the equipment in the ground control system to execute a specific mode management solution according to the upper-layer switching instruction, so as to realize the autonomous switching of the aircraft's multi-mode.

9. An electronic device, characterized in that: The device includes a memory, a processor, and a computer program stored in the memory and executable on the processor. When the processor executes the program, the method according to any one of claims 1 to 7 is implemented.

10. A computer-readable storage medium storing a computer program, characterized in that: When the computer program is executed by a processor, the method according to any one of claims 1 to 7 is implemented.

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