CN115877699A - Multi-modal aircraft switching method for full life cycle and related equipment thereof - Google Patents
Multi-modal aircraft switching method for full life cycle and related equipment thereof Download PDFInfo
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Abstract
The multi-mode switching method and the relevant equipment for the aircraft with the whole life cycle receive an upper switching instruction by initializing a ground control system and utilizing a remote interactive computer of the ground control system; after receiving an upper layer switching instruction, judging whether the aircraft launching preparation time is within a preset time range; when the aircraft emission preparation time is not within a preset time range, controlling the remote interactive computer to be in a standby or dormant state by using the DPM until the aircraft emission preparation time is within the preset time range; responding to an upper layer switching instruction when the aircraft launching preparation time is within a preset time range; and controlling equipment in the ground control system to execute a specific mode management scheme according to an upper layer switching instruction, so as to realize multi-mode autonomous switching of the aircraft. The switching among the multiple modes of the aircraft can be effectively realized, and the change trend of the aircraft in the multi-mode conversion process can be automatically monitored in real time.
Description
Technical Field
The invention belongs to the technical field of multi-mode switching of aircrafts, and particularly relates to a multi-mode switching method for an aircraft in a full life cycle and relevant equipment thereof.
Background
The aircraft belongs to a special product which is stored for a long time and is used by one-time launching, the test control during the use period of the aircraft relates to a plurality of modes, how to effectively divide the multiple modes and effectively switch the multiple modes, and the problem is always a great problem which troubles the research, production and use departments. The aircraft has complex structure, high price, less batch and immature accelerated life research method, and scientific and practical mode control strategies are difficult to provide during development and production so as to realize optimal health state management. Due to the lack of support for actual stored environmental data and actual test data for an aircraft, the current international common approach is to employ long-term power-up, continuous single-mode test control, which generally reduces the service life of the aircraft.
The multiple modes (multiple operating modes) of aircraft development are mainly based on the premise of meeting the task requirements of aircraft equipment systems, and the development targets of loss and cost in low-multiple mode management are realized at the expense of part of the performance of an aircraft system platform, but the reduced performance does not influence the normal operation of the whole aircraft system, because each design mode state does not need to be used for a long time as the aircraft system is developed, and generally the standby mode is mainly used. When the aircraft system needs to enter a certain mode or a simulation state, the multi-mode autonomous system can be quickly started from a low-loss mode to enter a normal working mode, and normal work of the aircraft system is guaranteed. But the multi-mode autonomous system can be started from the low-loss mode to the normal operation mode quickly, and the problem of the change trend of the degradation can occur.
Disclosure of Invention
The invention overcomes one of the defects of the prior art, provides the multi-mode switching method of the aircraft for the whole life cycle and the related equipment, can effectively realize the multi-mode switching of the aircraft, and simultaneously realizes the real-time automatic monitoring of the change trend of the control system in the multi-mode switching process of the aircraft.
According to an aspect of the present disclosure, there is provided a method for multi-modal handoff of an aircraft for a full life cycle, the method comprising:
initializing a ground control system, and receiving an upper layer switching instruction by using a remote interactive computer of the ground control system;
after receiving the upper layer switching instruction, judging whether the aircraft launching preparation time is within a preset time range;
when the aircraft launching preparation time is not within a preset time range, controlling the remote interactive computer to be in a standby or dormant state by using an energy management and control module (DPM) until the aircraft launching preparation time is within the preset time range;
responding to the upper layer switching instruction when the aircraft launching preparation time is within a preset time range;
and controlling equipment in the ground control system to execute a specific mode management scheme according to the upper layer switching instruction, so as to realize multi-mode autonomous switching of the aircraft.
In one possible implementation, the upper layer switching instruction includes: the method comprises the steps of controlling an aircraft to start to work in an emergency emission mode, controlling the aircraft to start to work in a core mechanism hot backup component mode, controlling the aircraft to start to work in an aircraft all hot backup mode, controlling the aircraft to jump from the emergency emission mode to the core mechanism hot backup component mode, controlling the aircraft to jump from the emergency emission mode to the aircraft all hot backup mode, and controlling the aircraft to jump from the core mechanism hot backup component mode to the aircraft all hot backup mode.
In a possible implementation, the range between the presets is t 0 -5t 0 Wherein, t 0 Is preset unit working time;
when the aircraft launching preparation time is within a preset time range, responding to the upper layer switching instruction, and the method comprises the following steps:
when the aircraft launching preparation time is 3t 0 Responding to an instruction for controlling the aircraft to start to work in an emergency launching mode;
when the aircraft launching preparation time is 4t 0 Responding to a command for controlling the aircraft to start to work in a hot backup component mode of a core mechanism;
when the aircraft is ready for launching at 5t 0 Responding to a command for controlling the aircraft to start to work on all the hot backup of the aircraft;
when the aircraft launching preparation time is t 0 When the emergency transmission mode of the aircraft is controlled to jump to the core mechanism hot backup component mode, responding to an instruction of controlling the aircraft to jump to the core mechanism hot backup component mode from the emergency transmission mode or responding to an instruction of controlling the aircraft to jump to the core mechanism hot backup component mode from the core mechanism hot backup component mode
When the aircraft launching preparation time is 2t 0 And responding to an instruction for controlling the aircraft to jump from the emergency transmission mode to the all-hot-backup mode of the aircraft.
In one possible implementation, the apparatus of the ground control system comprises: fire control box, little power, observing and controling processing unit, electrical power generating system, finger control system, treater, emergency treatment device, commercial power.
In one possible implementation, controlling the device in the ground control system to execute a specific mode management scheme according to the upper layer switching instruction includes:
when the upper layer switching instruction is an instruction for controlling the aircraft to start to work in an emergency launching mode, controlling a fire control box and a small power supply in the ground control system to be in a working state, and controlling other equipment to be in a dormant state;
when the upper layer switching instruction is an instruction for controlling an aircraft to start working in a hot backup component mode of a core mechanism, controlling a measurement and control processing unit and a power supply system in the ground control system to be in a working state, and controlling other equipment to be in a dormant state;
and when the upper layer switching instruction is an instruction for controlling the aircraft to start to work in a full hot backup mode of the aircraft, controlling a command control system, a processor, an emergency processing device and the commercial power in the ground control system to be in a working state, and controlling other equipment to be in a specific mode management scheme in a dormant state.
In one possible implementation manner, controlling the device in the ground control system to execute a specific mode management scheme according to the upper layer switching instruction further includes:
and when the upper layer switching instruction is an instruction for controlling the aircraft to jump to the core mechanism hot backup component mode from the emergency transmission mode, closing the fire control box and the small power supply, and waking up the measurement and control processing unit and the power supply system to work.
In one possible implementation, the DPM includes: a normal state, an idle state, and a sleep state; and the idle state is transited to the normal state or the sleep state, and the normal state and the sleep state are transited mutually.
According to another aspect of the present disclosure, there is provided a multi-modal switching system for an aircraft for a full life cycle, the system comprising:
the system comprises an initialization module, a switching module and a switching module, wherein the initialization module is used for initializing a ground control system and receiving an upper layer switching instruction by using a remote interactive computer of the ground control system;
the judging module is used for judging whether the aircraft launching preparation time is within a preset time range after receiving the upper layer switching instruction;
the sleep module is used for controlling the remote interactive computer to be in a sleep state by utilizing the DPM when the aircraft transmission preparation time is not within a preset time range until the aircraft transmission preparation time is within the preset time range;
the response module is used for responding to the upper layer switching instruction when the aircraft launching preparation time is within a preset time range;
and the switching module is used for controlling equipment in the ground control system to execute a specific mode management scheme according to the upper switching instruction so as to realize multi-mode autonomous switching of the aircraft.
According to another aspect of the present disclosure, an electronic device is proposed, the device comprising a memory, a processor and a computer program stored on the memory and executable on the processor, the processor implementing the method as described above when executing the program.
According to another aspect of the present disclosure, a computer-readable storage medium is proposed, which stores a computer program, which when executed by a processor implements the method as described above.
According to the multi-mode switching method for the aircraft with the full life cycle, the ground control system is initialized, and the remote interactive computer of the ground control system is used for receiving the upper layer switching instruction; after receiving the upper layer switching instruction, judging whether the aircraft launching preparation time is within a preset time range; when the aircraft emission preparation time is not within a preset time range, controlling the remote interactive computer to be in a standby or dormant state by using an energy management and control module (DPM) until the aircraft emission preparation time is within the preset time range; responding to the upper layer switching instruction when the aircraft launching preparation time is within a preset time range; and controlling equipment in the ground control system to execute a specific mode management scheme according to the upper layer switching instruction, so as to realize multi-mode autonomous switching of the aircraft. The switching among the multiple modes of the aircraft can be effectively realized, and the change trend of a control system in the multi-mode switching process of the aircraft can be automatically monitored in real time.
Drawings
The accompanying drawings are included to provide a further understanding of the technology or prior art of the present application and are incorporated in and constitute a part of this specification. The drawings for illustrating the embodiments of the present application together with the embodiments of the present application serve to explain the technical solutions of the present application, but do not limit the technical solutions of the present application.
FIG. 1 illustrates a flow diagram of a method for multi-modal handoff of an aircraft for a full life cycle in accordance with an embodiment of the present disclosure;
FIG. 2 illustrates a flow diagram of a method for multi-modal handoff of an aircraft for a full life cycle in accordance with another embodiment of the disclosure;
fig. 3 shows a diagram of a state of an energy management module DPM according to an embodiment of the present disclosure;
FIG. 4 illustrates a block diagram of a multi-modal switching system for a full lifecycle aircraft, in accordance with an embodiment of the present disclosure;
fig. 5 shows a schematic structural diagram of the electronic device 3 according to an embodiment of the present disclosure.
Detailed Description
The following detailed description of the embodiments of the present invention will be provided with reference to the accompanying drawings and examples, so that how to apply the technical means to solve the technical problems and achieve the corresponding technical effects can be fully understood and implemented. The features of the embodiments and examples may be combined without conflict, and the technical solutions formed are all within the scope of the present invention.
Additionally, the steps illustrated in the flow charts of the figures may be performed in a computer such as a set of computer-executable instructions. Also, while a logical order is shown in the flow diagrams, in some cases, the steps shown or described may be performed in an order different than here.
Fig. 1 and 2 respectively illustrate a multi-modal handoff method for an aircraft for a full life cycle in accordance with an embodiment of the present disclosure. The method is applied to a ground control system for multi-mode switching of the aircraft, and as shown in fig. 1, the method can comprise the following steps:
step S1: initializing a ground control system, and receiving an upper layer switching instruction by using a remote interactive computer of the ground control system.
As shown in fig. 2, initializing the surface control system may be to power on various devices of the surface control system, initialize a software program of the surface control system, and start the surface control system. Each device of the ground control system comprises a fire control box, a small power supply, a measurement and control processing unit, a power supply system, a finger control system, a processor, an emergency processing device, a commercial power and the like besides a remote interactive computer.
The upper layer switching instruction comprises the following steps: the method comprises the steps of controlling an aircraft to start to work in an emergency emission mode, controlling the aircraft to start to work in a core mechanism hot backup component mode, controlling the aircraft to start to work in an aircraft all hot backup mode, controlling the aircraft to jump from the emergency emission mode to the core mechanism hot backup component mode, controlling the aircraft to jump from the emergency emission mode to the aircraft all hot backup mode, and controlling the aircraft to jump from the core mechanism hot backup component mode to the aircraft all hot backup mode.
Step S2: and after receiving the upper layer switching instruction, judging whether the aircraft launching preparation time is within a preset time range.
The priority of the upper layer switching instruction is the highest, and the operating mode of the aircraft in execution is allowed to be broken at any time. For example, after receiving the upper layer switching instruction, the aircraft responds to the program flow of the mode switching of the upper computer according to the self health state, and judges whether the aircraft launching preparation time is within the preset time range. For example, assume that the predetermined time range is t 0 -5t 0 Wherein, t 0 Is a preset unit operating time. Judging whether the aircraft launching preparation time is at t 0 -5t 0 Within.
And step S3: and when the aircraft launching preparation time is not within a preset time range, controlling the remote interactive computer to be in a standby or dormant state by using an energy management and control module (DPM) until the aircraft launching preparation time is within the preset time range.
Wherein, energy management and control module DPM includes: a normal state, an idle state, and a sleep state; and the idle state is transited to the normal state or the sleep state, and the normal state and the sleep state are transited mutually.
Fig. 3 shows a schematic diagram of a DPM state of an energy management module according to an embodiment of the present disclosure.
An energy Management and control module (DPM) is a method for supporting Dynamic configuration of Power consumption modes. As shown in fig. 3, the autonomous handover procedure (DPM) may include: normal state NMAL, IDLE state IDLE and SLEEP state SLEEP; the IDLE state IDLE is transited to the normal state NMAL or the SLEEP state SLEEP, and the normal state NMAL and the SLEEP state SLEEP are transited to each other.
As shown in fig. 3, t is required for the IDLE state IDLE to switch to the normal state NMAL 1 Time, t is required to switch from IDLE state IDLE to SLEEP state 2 Time, t is required from normal state NMAL to SLEEP state SLEEP 3 Time, t is required to switch from SLEEP state SLEEP to normal state NMAL 4 Time. At this time, it is necessary to determine whether it is worth to enter a SLEEP state SLEEP (low power consumption mode) in the IDLE state IDLE according to the rocket control system, and when the IDLE time is small, the energy consumption of die cutting switching will be greater than the energy saving amount of the low power consumption mode to the normal mode in the same time, in this case, the energy switching is not suitable. The state switching of the corresponding modes of the equipment is carried out through the DPM unit, the power consumption of the ground control system can be controlled to be the lowest as possible to operate on the premise of realizing the functional requirements, and the switching among different power consumption modes is realized.
And step S4: and responding to the upper layer switching instruction when the aircraft transmission preparation time is within a preset time range.
When judging that the aircraft is ready for launching at t 0 -5t 0 When the method is used, different upper layer switching instructions are responded according to the aircraft launching preparation time, and the method specifically comprises the following steps:
when the aircraft launching preparation time is 3t 0 And responding to the command for controlling the aircraft to start working in the emergency launching mode. I.e. when the aircraft launch preparation time is greater than 3t 0 All devices of the ground control system are dormant to 3t 0 Restarting at any moment; when the aircraft launching preparation time is less than 3t 0 And when the ground control system enters a standby state, the ground control system waits for a new remote interactive computer instruction sent by a person in a loop, and the waiting process does not respond to the mode switching.
When the aircraft launching preparation time is 4t 0 In time, response control aircraft starterAnd a hot backup component mode command of the core mechanism is made. I.e. when the aircraft launch preparation time is greater than 4t 0 When the system is in use, all the equipment in the system of the ground control system sleeps to 3t 0 Restarting at any moment; when the aircraft launching preparation time is less than 4t 0 And when the system is in the standby state, the ground control system waits for a new remote interactive computer command sent by a person in the loop, and the waiting process does not respond to the mode switching.
When the aircraft is ready for launching at 5t 0 And responding to a command for controlling the aircraft to start to work on all the hot backup of the aircraft. I.e. when the aircraft launch preparation time is greater than 5t 0 Then all the devices of the ground control system sleep to 5t 0 Restarting at any moment; namely, when the aircraft launching preparation time is less than 5t0, the ground control system enters a standby state, namely, a new remote interactive computer instruction sent by a person in a loop is waited, and the waiting process does not respond to the mode switching.
When the aircraft launching preparation time is t 0 And responding to a command that the aircraft is controlled to jump to the core mechanism hot backup component mode from the emergency transmission mode or responding to a command that the aircraft jumps to the core mechanism hot backup component mode from the core mechanism hot backup component mode. I.e. when the aircraft launch preparation time is greater than t 0 Then all the devices of the ground control system sleep to 3t 0 Restarting at any moment; i.e. when the aircraft launch preparation time is less than t 0 And when the ground control system enters a standby state, the ground control system waits for a new remote interactive computer instruction sent by a person in a loop, and the waiting process does not respond to the mode switching.
When the aircraft launching preparation time is 2t 0 And responding to an instruction for controlling the aircraft to jump from the emergency transmission mode to the all-hot-backup mode of the aircraft. I.e. when the aircraft launch preparation time is greater than 2t 0 Then all the devices of the ground control system sleep to 2t 0 Restarting at any moment; i.e. when the aircraft launch preparation time is less than 2t 0 And when the ground control system enters a standby state, the ground control system waits for a new remote interactive computer instruction sent by a person in a loop, and the waiting process does not respond to the mode switching.
Step S5: and controlling equipment in the ground control system to execute a specific mode management scheme according to an upper layer switching instruction, so as to realize the multi-mode autonomous switching of the aircraft.
And when the ground control system receives the upper layer switching instruction, controlling each device of the ground control system to implement a specific mode management scheme.
In one example, controlling devices in the ground control system to execute a particular mode management scheme according to the upper layer switching instructions includes:
and when the upper layer switching instruction is an instruction for controlling the aircraft to start to work in an emergency launching mode, controlling a fire control box and a small power supply in the ground control system to be in a working state, and controlling other equipment to be in a dormant state. The switching of the starting work of the aircraft in the emergency launching mode is the simplest and the fastest. The bottom chip can be driven by a clock gating method, and embedded measurement and control equipment with extremely high real-time performance in the ground control system is operated: the fire control box, the small power supply and other equipment (a measurement and control processing unit, a power supply system, a finger control system, a processor, an emergency processing device and commercial power) of the ground control system are in a dormant state, so that the measurement and control requirements of basic functions of the aircraft can be met, and the ground test control in an emergency launching mode is realized.
And when the upper layer switching instruction is an instruction for controlling the aircraft to start to work in a core mechanism hot backup component mode, controlling a measurement and control processing unit and a power supply system in the ground control system to be in a working state, and controlling other equipment to be in a dormant state.
In such cases, each part of the ground control system switches state. Firstly, completing state switching when responding to a command of human intervention in a loop to a remote interactive computer; then awakening the dormant states of the measurement and control processing unit and the power system to enable the measurement and control processing unit and the power system to be in working states, and simultaneously turning off the embedded equipment. The measurement and control processing unit is added with a complex system operation function compared with a fire control box and supports the multithreading online scheduling capability; compared with a small power supply in an emergency emission mode, the power supply system can realize high-power, variable-frequency and high-voltage power supply output and support the mode test and control requirements of a hot backup component assembly of a core mechanism of an aircraft.
And when the upper layer switching instruction is an instruction for controlling the aircraft to start to work in a full hot backup mode of the aircraft, controlling a command control system, a processor, an emergency processing device and the commercial power in the ground control system to be in a working state, and controlling other equipment to be in a specific mode management scheme in a dormant state.
The remote interactive computer is switched to a full-speed working mode under the condition that the starting of the aircraft is controlled to work in a full hot backup mode of aircraft ground equipment, and awakens equipment such as a full finger control system, a processor, an emergency processing device and a mains supply to be in a working state, so that the redundant fault-tolerant capability and robustness of the ground control system can be ensured and the equipment used in the full hot backup mode can be ensured. The system comprises a command control system, a processor and an emergency processing device, wherein the command control system is a system for information aid decision, the processor is equipment for improving the background processing capacity of the equipment, and the emergency processing device is a device with a set of redundant guaranteed processing capacity under emergency conditions.
In addition, when the upper layer switching instruction is an instruction for controlling the aircraft to jump to the core mechanism hot backup component mode from an emergency transmission mode, the fire control box and the small power supply are closed, and the measurement and control processing unit and the power supply system are awakened to work.
For example, in the emergency transmission mode, the fire control box and the small power supply device of the aircraft ground control system are used as devices for responding to the operation of the kernel in real time. When the core mechanism hot backup component module mode is switched in the emergency emission mode, the remote interactive computer is used for responding to a human-in-loop instruction, and the switching mode control program is operated on the premise of meeting the space switching time.
In the process of jumping to the core mechanism hot backup component mode in the emergency transmission mode, firstly, the measurement and control processing unit and the power supply system are awakened to be in a working state, meanwhile, the analog circuit power supplies of the measurement and control processing unit and the power supply system are turned on, and then fault diagnosis of the data acquisition system of the measurement and control processing unit and the power supply system is completed. After the fault diagnosis of the data acquisition systems of the measurement and control processing unit and the power supply system is completed, if no new upper layer switching instruction exists after the preset idle time is exceeded, the measurement and control processing unit and the power supply system are switched to a turn-off mode, the ground control system is controlled to be switched back to the emergency transmission mode again, and the reliability state of the core execution mechanism is protected.
According to the multi-mode switching method for the aircraft with the full life cycle, the ground control system is initialized, and the remote interactive computer of the ground control system is used for receiving the upper layer switching instruction; after receiving the upper layer switching instruction, judging whether the aircraft launching preparation time is within a preset time range; when the aircraft launching preparation time is not within a preset time range, controlling the remote interactive computer to be in a standby or dormant state by using an energy management and control module (DPM) until the aircraft launching preparation time is within the preset time range; responding to the upper layer switching instruction when the aircraft launching preparation time is within a preset time range; and controlling equipment in the ground control system to execute a specific mode management scheme according to the upper layer switching instruction, so as to realize multi-mode autonomous switching of the aircraft. The switching among the multiple modes of the aircraft can be effectively realized, and the change trend of a control system in the multi-mode conversion process of the aircraft can be automatically monitored in real time.
The following are embodiments of the apparatus of the present application that may be used to perform embodiments of the method of the present application. For details which are not disclosed in the embodiments of the apparatus of the present application, reference is made to the embodiments of the method of the present application.
FIG. 4 illustrates a block diagram of a multi-modal switching system for a full life cycle aircraft in accordance with an embodiment of the present disclosure; as shown in fig. 4, the system may include:
the initialization module 401 is configured to initialize a ground control system, and receive an upper layer switching instruction by using a remote interactive computer of the ground control system;
a judging module 402, configured to judge whether aircraft launch preparation time is within a preset time range after receiving the upper layer switching instruction;
a sleep module 403, configured to, when the aircraft transmission preparation time is not within a preset time range, control the remote interactive computer to be in a sleep state by using an energy management and control module DPM until the aircraft transmission preparation time is within the preset time range;
a response module 404, configured to respond to the upper layer switching instruction when the aircraft launch preparation time is within a preset time range;
and a switching module 405, configured to control, according to the upper layer switching instruction, a device in the ground control system to execute a specific mode management scheme, so as to implement multi-mode autonomous switching of the aircraft.
It should be understood that, the sequence numbers of the steps in the foregoing embodiments do not imply an execution sequence, and the execution sequence of each process should be determined by its function and inherent logic, and should not constitute any limitation to the implementation process of the embodiments of the present application.
Fig. 5 is a schematic structural diagram of an electronic device 3 provided in an embodiment of the present application. As shown in fig. 5, the electronic apparatus 3 of this embodiment includes: a processor 301, a memory 302, and a computer program 303 stored in the memory 302 and operable on the processor 301. The steps in the various method embodiments described above are implemented when the processor 301 executes the computer program 303. Alternatively, the processor 301 implements the functions of the modules/units in the above-described device embodiments when executing the computer program 303.
Illustratively, the computer program 303 may be partitioned into one or more modules/units, which are stored in the memory 302 and executed by the processor 301 to accomplish the present application. One or more modules/units may be a series of computer program instruction segments capable of performing specific functions, which are used to describe the execution of the computer program 303 in the electronic device 3.
The electronic device 3 may be a desktop computer, a notebook, a palm computer, a cloud server, or other electronic devices. The electronic device 3 may include, but is not limited to, a processor 301 and a memory 302. Those skilled in the art will appreciate that fig. 3 is merely an example of the electronic device 3, and does not constitute a limitation of the electronic device 3, and may include more or less components than those shown, or combine certain components, or different components, for example, the electronic device may also include input-output devices, network access devices, buses, etc.
The Processor 301 may be a Central Processing Unit (CPU), other general purpose Processor, a Digital Signal Processor (DSP), an Application Specific Integrated Circuit (ASIC), a Field Programmable Gate Array (FPGA) or other Programmable logic device, discrete Gate or transistor logic device, discrete hardware component, or the like. A general purpose processor may be a microprocessor or the processor may be any conventional processor or the like.
The storage 302 may be an internal storage unit of the electronic device 3, for example, a hard disk or a memory of the electronic device 3. The memory 302 may also be an external storage device of the electronic device 3, such as a plug-in hard disk provided on the electronic device 3, a Smart Media Card (SMC), a Secure Digital (SD) Card, a Flash memory Card (Flash Card), and the like. Further, the memory 302 may also include both an internal storage unit of the electronic device 3 and an external storage device. The memory 302 is used for storing computer programs and other programs and data required by the electronic device. The memory 302 may also be used to temporarily store data that has been output or is to be output.
It will be apparent to those skilled in the art that, for convenience and brevity of description, only the above-mentioned division of the functional units and modules is illustrated, and in practical applications, the above-mentioned function distribution may be performed by different functional units and modules according to needs, that is, the internal structure of the apparatus is divided into different functional units or modules, so as to perform all or part of the functions described above. Each functional unit and module in the embodiments may be integrated in one processing unit, or each unit may exist alone physically, or two or more units are integrated in one unit, and the integrated unit may be implemented in a form of hardware, or in a form of software functional unit. In addition, specific names of the functional units and modules are only used for distinguishing one functional unit from another, and are not used for limiting the protection scope of the present application. The specific working processes of the units and modules in the system may refer to the corresponding processes in the foregoing method embodiments, and are not described herein again.
In the above embodiments, the descriptions of the respective embodiments have respective emphasis, and reference may be made to the related descriptions of other embodiments for parts that are not described or illustrated in a certain embodiment.
Those of ordinary skill in the art would appreciate that the various illustrative elements and algorithm steps described in connection with the embodiments disclosed herein may be implemented as electronic hardware or combinations of computer software and electronic hardware. Whether such functionality is implemented as hardware or software depends upon the particular application and design constraints imposed on the implementation. Skilled artisans may implement the described functionality in varying ways for each particular application, but such implementation decisions should not be interpreted as causing a departure from the scope of the present application.
In the embodiments provided in the present application, it should be understood that the disclosed apparatus/computer device and method may be implemented in other ways. For example, the above-described apparatus/computer device embodiments are merely illustrative, and for example, a division of modules or units, a division of logical functions only, an additional division may be made in actual implementation, multiple units or components may be combined or integrated with another system, or some features may be omitted, or not implemented. In addition, the shown or discussed mutual coupling or direct coupling or communication connection may be through some interfaces, indirect coupling or communication connection of devices or units, and may be in an electrical, mechanical or other form.
Units described as separate parts may or may not be physically separate, and parts displayed as units may or may not be physical units, may be located in one place, or may be distributed on a plurality of network units. Some or all of the units can be selected according to actual needs to achieve the purpose of the solution of the embodiment.
In addition, functional units in the embodiments of the present application may be integrated into one processing unit, or each unit may exist alone physically, or two or more units are integrated into one unit. The integrated unit can be realized in a form of hardware, and can also be realized in a form of a software functional unit.
The integrated modules/units, if implemented in the form of software functional units and sold or used as separate products, may be stored in a computer readable storage medium. Based on such understanding, all or part of the flow in the method of the foregoing embodiments may be implemented by a computer program, which may be stored in a computer readable storage medium and instructs related hardware to implement the steps of the foregoing method embodiments when executed by a processor. The computer program may comprise computer program code, which may be in the form of source code, object code, an executable file or some intermediate form, etc. The computer readable medium may include: any entity or device capable of carrying computer program code, recording medium, U.S. disk, removable hard disk, magnetic disk, optical disk, computer Memory, read-Only Memory (ROM), random Access Memory (RAM), electrical carrier wave signals, telecommunications signals, software distribution media, and the like. It should be noted that the computer readable medium may contain suitable additions or additions that may be required in accordance with legislative and patent practices within the jurisdiction, for example, in some jurisdictions, computer readable media may not include electrical carrier signals or telecommunications signals in accordance with legislative and patent practices.
The above embodiments are only used to illustrate the technical solutions of the present application, and not to limit the same; although the present application has been described in detail with reference to the foregoing embodiments, it should be understood by those of ordinary skill in the art that: the technical solutions described in the foregoing embodiments may still be modified, or some technical features may be equivalently replaced; such modifications and substitutions do not substantially depart from the spirit and scope of the embodiments of the present application and are intended to be included within the scope of the present application.
Claims (10)
1. A method for multi-modal handoff of an aircraft for a full life cycle, the method comprising:
initializing a ground control system, and receiving an upper layer switching instruction by using a remote interactive computer of the ground control system;
after the upper layer switching instruction is received, judging whether the aircraft launching preparation time is within a preset time range;
when the aircraft launching preparation time is not within a preset time range, controlling the remote interactive computer to be in a dormant state by using an energy management and control module (DPM) until the aircraft launching preparation time is within the preset time range;
responding to the upper layer switching instruction when the aircraft launching preparation time is within a preset time range;
and controlling equipment in the ground control system to execute a specific mode management scheme according to the upper layer switching instruction, so as to realize multi-mode autonomous switching of the aircraft.
2. The aircraft multimodal switching method according to claim 1, characterized in that the upper layer switching instructions comprise: the method comprises the steps of controlling an aircraft to start to work in an emergency emission mode, controlling the aircraft to start to work in a core mechanism hot backup component mode, controlling the aircraft to start to work in an aircraft all hot backup mode, controlling the aircraft to jump from the emergency emission mode to the core mechanism hot backup component mode, controlling the aircraft to jump from the emergency emission mode to the aircraft all hot backup mode, and controlling the aircraft to jump from the core mechanism hot backup component mode to the aircraft all hot backup mode.
3. Method for multimodal switching of aircraft according to claim 2, characterized in that said preset time is the time of dayIn the interval of t 0 -5t 0 Wherein, t 0 Is preset unit working time;
when the aircraft launching preparation time is within a preset time range, responding to the upper layer switching instruction, and the method comprises the following steps:
when the aircraft launching preparation time is 3t 0 Responding to an instruction for controlling the aircraft to start to work in an emergency launching mode;
when the aircraft launching preparation time is 4t 0 Responding to a command for controlling the aircraft to start to work in a hot backup component mode of a core mechanism;
when the aircraft is ready for launching at 5t 0 Responding to a command for controlling the aircraft to start to work on all the hot backup of the aircraft;
when the aircraft launching preparation time is t 0 When the emergency transmission mode of the aircraft is responded, jumping to a core mechanism hot backup component mode instruction from the emergency transmission mode of the aircraft is responded, or jumping to the core mechanism hot backup component mode instruction from the core mechanism hot backup component mode of the aircraft is responded;
when the aircraft launching preparation time is 2t 0 And responding to an instruction for controlling the aircraft to jump from the emergency transmission mode to the full hot backup mode of the aircraft.
4. A method for multimodal switching of aircraft according to claim 3, characterized in that the devices of the ground control system comprise: fire control box, little power, observe and control processing unit, electrical power generating system, finger control system, treater, emergency treatment device, commercial power.
5. The multi-modal aircraft handoff method of claim 4 wherein controlling devices in the ground control system to execute a mode-specific management scheme in accordance with the upper-level handoff instructions comprises:
when the upper layer switching instruction is an instruction for controlling the aircraft to start to work in an emergency launching mode, controlling a fire control box and a small power supply in the ground control system to be in a working state, and controlling other equipment to be in a dormant state;
when the upper layer switching instruction is an instruction for controlling the aircraft to start working in a core mechanism hot backup component mode, controlling a measurement and control processing unit and a power supply system in the ground control system to be in a working state, and controlling other equipment to be in a dormant state;
and when the upper layer switching instruction is an instruction for controlling the aircraft to start to work in a full hot backup mode of the aircraft, controlling a command control system, a processor, an emergency processing device and the commercial power in the ground control system to be in a working state, and controlling other equipment to be in a specific mode management scheme in a dormant state.
6. The multi-modal aircraft switching method of claim 4, wherein controlling devices in the ground control system to execute a particular mode management scheme in accordance with the upper layer switching instructions further comprises:
and when the upper layer switching instruction is an instruction for controlling the aircraft to jump to the core mechanism hot backup component mode from the emergency transmission mode, closing the fire control box and the small power supply, and waking up the measurement and control processing unit and the power supply system to work.
7. The multi-modal aircraft switching method of claim 1, wherein the energy management module DPM comprises: a normal state, an idle state, and a sleep state; and the idle state is transited to the normal state or the sleep state, and the normal state and the sleep state are transited mutually.
8. A multi-modal switching system for a full life cycle aircraft, the system comprising:
the system comprises an initialization module, a switching module and a switching module, wherein the initialization module is used for initializing a ground control system and receiving an upper layer switching instruction by using a remote interactive computer of the ground control system;
the judging module is used for judging whether the aircraft launching preparation time is within a preset time range after receiving the upper layer switching instruction;
the sleep module is used for controlling the remote interactive computer to be in a sleep state by utilizing the DPM when the aircraft transmission preparation time is not within a preset time range until the aircraft transmission preparation time is within the preset time range;
the response module is used for responding to the upper layer switching instruction when the aircraft launching preparation time is within a preset time range;
and the switching module is used for controlling equipment in the ground control system to execute a specific mode management scheme according to the upper switching instruction so as to realize multi-mode autonomous switching of the aircraft.
9. An electronic device, characterized in that the device comprises a memory, a processor and a computer program stored on the memory and executable on the processor, which when executing the program implements the method according to any of claims 1 to 7.
10. A computer-readable storage medium, in which a computer program is stored which, when being executed by a processor, carries out the method according to any one of claims 1 to 7.
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211599662.6A CN115877699A (en) | 2022-12-12 | 2022-12-12 | Multi-modal aircraft switching method for full life cycle and related equipment thereof |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211599662.6A CN115877699A (en) | 2022-12-12 | 2022-12-12 | Multi-modal aircraft switching method for full life cycle and related equipment thereof |
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| CN115877699A true CN115877699A (en) | 2023-03-31 |
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| CN202211599662.6A Pending CN115877699A (en) | 2022-12-12 | 2022-12-12 | Multi-modal aircraft switching method for full life cycle and related equipment thereof |
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| Country | Link |
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| CN (1) | CN115877699A (en) |
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