CN110991110B - Airplane high-altitude electromagnetic pulse environment risk analysis method and device and computer equipment - Google Patents
Airplane high-altitude electromagnetic pulse environment risk analysis method and device and computer equipment Download PDFInfo
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Abstract
The application relates to a method and a device for analyzing risks of an airplane high-altitude electromagnetic pulse environment and computer equipment. The method comprises the following steps: establishing an airplane exposed antenna model, an airplane exposed cable model and an airplane body electromagnetic shielding model based on an external high-altitude electromagnetic pulse environment; determining the internal electromagnetic pulse environment of the airplane based on the external high-altitude electromagnetic pulse environment and the airplane body electromagnetic shielding model; establishing an internal equipment electromagnetic shielding model and an internal cable electromagnetic shielding model of the airplane based on the internal electromagnetic pulse environment; determining failure types of the aircraft caused by an external high-altitude electromagnetic pulse environment and an internal electromagnetic pulse environment based on the aircraft exposed antenna model, the aircraft exposed cable model, the internal equipment electromagnetic shielding model and the internal cable electromagnetic shielding model; if the failure type is catastrophic failure, outputting analysis report information for changing the design of the airplane, thereby realizing the analysis and the finding of weak links of the airplane in the high-altitude electromagnetic pulse environment at the initial stage of the design of the airplane.
Description
Technical Field
The application relates to the technical field of testing, in particular to a method and a device for analyzing risks of an airplane high-altitude electromagnetic pulse environment and computer equipment.
Background
High altitude electromagnetic pulses are a sudden external threat to aircraft. After the high-altitude electromagnetic pulse acts on airborne electronic equipment of an airplane, communication interruption, navigation failure and runaway of various airborne computers can be caused, and catastrophic accidents of machine damage and death can be caused in severe cases. The safety analysis standard in the field of aviation, SAE ARP 4761, explicitly proposes the concept of a specific risk analysis technique, but does not present specific risk analysis methods and procedures. In the field of electromagnetic pulse protection design, design measures such as filtering, shielding and the like are developed, but a relevant analysis method for judging whether the design measures can prevent the occurrence of failure independence requirement events is lacked.
In combination with the high-altitude electromagnetic pulse environment which may be faced by an aircraft, research needs to be carried out on a specific risk analysis method for the high-altitude electromagnetic pulse of the aircraft to show that the electromagnetic pulse protection design of the aircraft can meet a predetermined safety requirement, but in the implementation process, the inventor finds that at least the following problems exist in the conventional technology: methods for risk analysis of aircraft in electromagnetic pulse environments are lacking in the conventional art.
Disclosure of Invention
In view of the above, there is a need to provide a method, an apparatus and a computer device for analyzing risk of high altitude electromagnetic pulse environment of an aircraft, which can analyze the risk of the aircraft in the high altitude electromagnetic pulse environment.
An airplane high altitude electromagnetic pulse environment risk analysis method comprises the following steps:
acquiring an external high-altitude electromagnetic pulse environment of the airplane, and establishing an airplane exposed antenna model, an airplane exposed cable model and an airplane body electromagnetic shielding model based on the external high-altitude electromagnetic pulse environment;
determining the internal electromagnetic pulse environment of the airplane based on the external high-altitude electromagnetic pulse environment and the airplane body electromagnetic shielding model;
establishing an internal equipment electromagnetic shielding model and an internal cable electromagnetic shielding model of the airplane based on the internal electromagnetic pulse environment;
determining failure types of the aircraft caused by an external high-altitude electromagnetic pulse environment and an internal electromagnetic pulse environment based on the aircraft exposed antenna model, the aircraft exposed cable model, the internal equipment electromagnetic shielding model and the internal cable electromagnetic shielding model;
and if the failure type is catastrophic failure, outputting analysis report information for changing the design of the airplane.
In one embodiment, the method further comprises the following steps:
if the failure type is non-catastrophic failure, judging whether the failure type is dangerous failure or not;
if the failure type is non-dangerous failure, analyzing the failure level and the corresponding probability, and outputting analysis report information of the electromagnetic protection design specification of the airplane;
and if the failure type is dangerous failure, analyzing the occurrence probability, outputting analysis report information of the electromagnetic protection design description of the airplane when the occurrence probability meets the quantitative analysis condition, and outputting analysis report information for changing the airplane design when the occurrence probability does not meet the quantitative analysis condition.
In one embodiment, in the step of determining the internal electromagnetic pulse environment of the aircraft based on the external high altitude electromagnetic pulse environment and the aircraft body electromagnetic shielding model, the aircraft body electromagnetic shielding model is established by:
processing an external high-altitude electromagnetic pulse environment, material characteristics, pore size and lap joint impedance by a time domain finite difference method to obtain an aircraft body electromagnetic shielding model; the material characteristics, the size of the pore and the lap joint impedance are obtained through a three-dimensional digital prototype model of the airplane body.
In one embodiment, the step of determining the failure type of the aircraft caused by the external high-altitude electromagnetic pulse environment and the internal electromagnetic pulse environment based on the aircraft exposed antenna model, the aircraft exposed cable model, the internal equipment electromagnetic shielding model and the internal cable electromagnetic shielding model comprises the following steps:
based on the airplane exposed antenna model and the receiving gain of the airplane exposed antenna, the voltage peak value, the peak value power and the rise time of the coupling waveform in the airplane exposed antenna are obtained through a time domain finite difference method.
In one embodiment, the step of determining the failure type of the aircraft caused by the external high-altitude electromagnetic pulse environment and the internal electromagnetic pulse environment based on the aircraft exposed antenna model, the aircraft exposed cable model, the internal equipment electromagnetic shielding model and the internal cable electromagnetic shielding model comprises the following steps:
based on the airplane exposed cable model and the material characteristics of the airplane exposed cable, the voltage peak value, the peak value power and the rise time of the coupling waveform in the airplane exposed cable are obtained through a time domain finite difference method.
In one embodiment, the step of determining the failure type of the aircraft caused by the external high-altitude electromagnetic pulse environment and the internal electromagnetic pulse environment based on the aircraft exposed antenna model, the aircraft exposed cable model, the internal equipment electromagnetic shielding model and the internal cable electromagnetic shielding model comprises the following steps:
based on an internal equipment electromagnetic shielding model, the voltage peak value, the peak power and the rise time of the coupling waveform in the internal equipment of the airplane are obtained through a time domain finite difference method.
In one embodiment, the step of determining the failure type of the aircraft caused by the external high-altitude electromagnetic pulse environment and the internal electromagnetic pulse environment based on the aircraft exposed antenna model, the aircraft exposed cable model, the internal equipment electromagnetic shielding model and the internal cable electromagnetic shielding model comprises the following steps:
based on the internal cable electromagnetic shielding model, the voltage peak value, the peak power and the rise time of the coupling waveform in the internal cable of the airplane are obtained through a time domain finite difference method.
An aircraft high altitude electromagnetic pulse environment risk analysis device, comprising:
the first model building module is used for obtaining an external high-altitude electromagnetic pulse environment of the airplane and building an airplane exposed antenna model, an airplane exposed cable model and an airplane body electromagnetic shielding model based on the external high-altitude electromagnetic pulse environment;
the internal electromagnetic pulse environment determining module is used for determining the internal electromagnetic pulse environment of the airplane based on the external high-altitude electromagnetic pulse environment and the airplane body electromagnetic shielding model;
the second model establishing module is used for establishing an internal equipment electromagnetic shielding model and an internal cable electromagnetic shielding model of the airplane based on the internal electromagnetic pulse environment;
the failure type determining module is used for determining failure types of the airplane caused by an external high-altitude electromagnetic pulse environment and an internal electromagnetic pulse environment based on the airplane exposed antenna model, the airplane exposed cable model, the internal equipment electromagnetic shielding model and the internal cable electromagnetic shielding model;
and the report output module is used for outputting analysis report information for changing the design of the airplane if the failure type is catastrophic failure.
A computer device comprising a memory storing a computer program and a processor implementing the steps of the method when the processor executes the computer program.
A computer-readable storage medium, on which a computer program is stored which, when being executed by a processor, carries out the steps of the above-mentioned method.
One of the above technical solutions has the following advantages and beneficial effects:
the method for analyzing the risk of the high-altitude electromagnetic pulse environment of the airplane provided by each embodiment of the application comprises the following steps: acquiring an external high-altitude electromagnetic pulse environment of the airplane, and establishing an airplane exposed antenna model, an airplane exposed cable model and an airplane body electromagnetic shielding model based on the external high-altitude electromagnetic pulse environment; determining the internal electromagnetic pulse environment of the airplane based on the external high-altitude electromagnetic pulse environment and the airplane body electromagnetic shielding model; establishing an internal equipment electromagnetic shielding model and an internal cable electromagnetic shielding model of the airplane based on the internal electromagnetic pulse environment; determining failure types of the aircraft caused by an external high-altitude electromagnetic pulse environment and an internal electromagnetic pulse environment based on the aircraft exposed antenna model, the aircraft exposed cable model, the internal equipment electromagnetic shielding model and the internal cable electromagnetic shielding model; if the failure type is catastrophic failure, analysis report information for changing the design of the airplane is output, so that risk analysis of the airplane in a high-altitude electromagnetic pulse environment is realized, weak links of the airplane in the high-altitude electromagnetic pulse environment are analyzed and found out at the initial stage of the airplane design, on one hand, the direction can be indicated for the electromagnetic pulse protection design, the design can be changed to improve the safety level of the airplane, and on the other hand, the problem that the design change cost is too high when relevant test verification is carried out at the later stage of airplane development is solved.
Drawings
FIG. 1 is a schematic flow chart of a risk analysis method for an aircraft high altitude electromagnetic pulse environment in one embodiment;
FIG. 2 is a schematic flow chart of a risk analysis method for an aircraft high altitude electromagnetic pulse environment in another embodiment;
FIG. 3 is a block diagram of an apparatus for risk analysis of an aircraft high altitude electromagnetic pulse environment according to an embodiment;
FIG. 4 is a diagram illustrating an internal structure of a computer device according to an embodiment.
Detailed Description
In order to make the objects, technical solutions and advantages of the present application more apparent, the present application is described in further detail below with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are merely illustrative of the present application and are not intended to limit the present application.
In order to solve the problem of the lack of a method for risk analysis of an aircraft in a high-altitude electromagnetic pulse environment in the conventional technology, in one embodiment, as shown in fig. 1, there is provided a method for risk analysis of an aircraft high-altitude electromagnetic pulse environment, comprising the following steps:
step S110, obtaining an external high-altitude electromagnetic pulse environment of the airplane, and establishing an airplane exposed antenna model, an airplane exposed cable model and an airplane body electromagnetic shielding model based on the external high-altitude electromagnetic pulse environment.
It should be noted that the external high-altitude electromagnetic pulse environment is obtained from an electromagnetic pulse waveform in the GJB 151B-2013 standard. The exposed antennas and cables of an aircraft are the primary means of electromagnetic pulse effect "front door" coupling. And establishing an aircraft exposed antenna model for determining the voltage peak value, the peak power and the rise time of the coupling waveform in the aircraft exposed antenna. And establishing an aircraft exposed cable model for the voltage peak value, the peak power and the rise time of the coupling waveform in the aircraft exposed cable.
The hole seam in the airplane body is a coupling way of electromagnetic pulse effect 'back door', and the airplane body electromagnetic shielding model is used for determining the new electromagnetic field distribution condition in the airplane. In one example, an aircraft body electromagnetic shielding model is established by:
processing an external high-altitude electromagnetic pulse environment, material characteristics, pore size and lap joint impedance by a time domain finite difference method to obtain an aircraft body electromagnetic shielding model; the material characteristics, the size of the pore and the lap joint impedance are obtained through a three-dimensional digital prototype model of the airplane body.
It should be noted that the material characteristics refer to characteristics of the material that forms the body, including permeability, dielectric constant, and resistivity. The size of the hole seam refers to the size of the seam at the joint of each part of the machine body. The lap impedance refers to impedance formed by connecting all parts of the machine body. In the actual analysis process, according to the electromagnetic topological method, the rest parts of the machine body are not influenced mutually except the mutual action of the hole and the seam.
And step S120, determining the internal electromagnetic pulse environment of the airplane based on the external high-altitude electromagnetic pulse environment and the airplane body electromagnetic shielding model.
It should be noted that the electromagnetic pulse environment inside the airplane is analyzed by using the external high-altitude electromagnetic pulse environment and the electromagnetic shielding model of the airplane body after the external high-altitude electromagnetic pulse environment and the electromagnetic shielding model of the airplane body are obtained.
Step S130, establishing an internal equipment electromagnetic shielding model and an internal cable electromagnetic shielding model of the airplane based on the internal electromagnetic pulse environment.
It should be noted that, under the effect of the internal electromagnetic pulse environment, parameters such as structural materials of the aircraft equipment, the size of the hole seam, the lap joint impedance, the cable materials and the material length are integrated, the damage of the internal electromagnetic pulse environment to the aircraft internal equipment and the cable is analyzed, and an internal equipment electromagnetic shielding model and an internal cable electromagnetic shielding model are respectively established.
And S140, determining failure types of the aircraft caused by the external high-altitude electromagnetic pulse environment and the internal electromagnetic pulse environment based on the aircraft exposed antenna model, the aircraft exposed cable model, the internal equipment electromagnetic shielding model and the internal cable electromagnetic shielding model.
After the airplane exposed antenna model, the airplane exposed cable model, the internal equipment electromagnetic shielding model and the internal cable electromagnetic shielding model are established, the airplane exposed antenna model, the airplane exposed cable model, the internal equipment electromagnetic shielding model and the internal cable electromagnetic shielding model are used for analyzing the damage of an external high-altitude electromagnetic pulse environment and the damage of an internal electromagnetic pulse environment to the airplane together, and failure classification is carried out according to failure grades caused by the damage to obtain failure types.
Specifically, in one example, based on the model of the aircraft exposed antenna and the receiving gain of the aircraft exposed antenna, the voltage peak value, the peak power and the rise time of the coupling waveform in the aircraft exposed antenna are obtained by a time-domain finite difference method.
Based on the airplane exposed cable model and the material characteristics of the airplane exposed cable, the voltage peak value, the peak value power and the rise time of the coupling waveform in the airplane exposed cable are obtained through a time domain finite difference method.
Based on an internal equipment electromagnetic shielding model, the voltage peak value, the peak power and the rise time of the coupling waveform in the internal equipment of the airplane are obtained through a time domain finite difference method.
Based on the internal cable electromagnetic shielding model, the voltage peak value, the peak power and the rise time of the coupling waveform in the internal cable of the airplane are obtained through a time domain finite difference method.
Based on the obtained voltage peak values, peak power and rise time, the damage of the internal electromagnetic pulse environment and the external high-altitude electromagnetic pulse environment to the airplane is analyzed, and the danger type is obtained.
And step S150, if the failure type is catastrophic failure, outputting analysis report information for changing the design of the airplane.
Further, if the failure type is non-catastrophic failure, whether the failure type is dangerous failure is judged;
if the failure type is non-dangerous failure, analyzing the failure level and the corresponding probability, and outputting analysis report information of the electromagnetic protection design specification of the airplane;
and if the failure type is dangerous failure, analyzing the occurrence probability, outputting analysis report information of the electromagnetic protection design description of the airplane when the occurrence probability meets the quantitative analysis condition, and outputting analysis report information for changing the airplane design when the occurrence probability does not meet the quantitative analysis condition.
It should be noted that when it is analyzed that catastrophic failure of the flying in the electromagnetic pulse environment occurs, analysis report information for changing the design of the aircraft is output, and the analysis report information indicates a part of the aircraft which needs to be improved. The improved means can be as follows: the method comprises the following steps of carrying out protection design on an exposed antenna of the airplane, or carrying out electromagnetic pulse reinforcement design on an airplane body structure of the airplane, or carrying out electromagnetic pulse reinforcement design on airplane equipment and cables thereof, or carrying out design change by integrating the three. Wherein, the analysis report information can be presented in the form of a table, a document or a picture.
When the dangerous failure of the flight in the electromagnetic pulse environment is analyzed, the occurrence probability of the dangerous failure is analyzed, for example, in the preliminary system safety evaluation work, the occurrence probability can be calculated by utilizing a fault tree, a correlation diagram or a Markov chain. Further, if the occurrence probability meets the quantitative analysis conditions (the requirements of the occurrence probability on catastrophic and dangerous failure states in the operation of evaluating the functional dangers of the airplane and the system), the analysis report information of the electromagnetic protection design description of the airplane is output, and the analysis report information for changing the airplane design is output if the occurrence probability does not meet the quantitative analysis conditions. The analysis report information of the electromagnetic protection design description is used for carrying out detailed analysis description on dangerous failure states meeting quantitative analysis conditions or failure states of other levels and occurrence probability thereof.
When analyzing that neither catastrophic failure nor dangerous failure occurs in the flying electromagnetic pulse environment, analyzing the failure level and giving corresponding probability.
The specific process is as follows (as shown in fig. 2): judging whether the failure type or the failure type combination can cause catastrophic failure or not according to the identified failure type or the failure type combination which is harmful to the airplane equipment, and if so, changing the design; if the catastrophic failure state cannot be caused, further judging whether the failure type or the failure type combination can cause dangerous failure; if the dangerous failure cannot be caused, carrying out detailed analysis and explanation on the failure level and the probability thereof caused by the current design; if the dangerous failure is caused, further analyzing and calculating the occurrence probability of the dangerous failure state and judging whether the quantitative analysis condition is met; if the occurrence probability of the dangerous failure state meets the quantitative analysis condition, carrying out detailed analysis explanation on the occurrence probability of the dangerous failure state; and if the occurrence probability of the dangerous failure state does not meet the quantitative analysis condition, changing the design.
According to the embodiments of the method for analyzing the risk of the high-altitude electromagnetic pulse environment of the airplane, the external high-altitude electromagnetic pulse environment of the airplane is obtained, and an airplane exposed antenna model, an airplane exposed cable model and an airplane body electromagnetic shielding model are established based on the external high-altitude electromagnetic pulse environment; determining the internal electromagnetic pulse environment of the airplane based on the external high-altitude electromagnetic pulse environment and the airplane body electromagnetic shielding model; establishing an internal equipment electromagnetic shielding model and an internal cable electromagnetic shielding model of the airplane based on the internal electromagnetic pulse environment; determining failure types of the aircraft caused by an external high-altitude electromagnetic pulse environment and an internal electromagnetic pulse environment based on the aircraft exposed antenna model, the aircraft exposed cable model, the internal equipment electromagnetic shielding model and the internal cable electromagnetic shielding model; if the failure type is catastrophic failure, analysis report information for changing the design of the airplane is output, so that risk analysis of the airplane in a high-altitude electromagnetic pulse environment is realized, weak links of the airplane in the high-altitude electromagnetic pulse environment are analyzed and found out at the initial stage of the airplane design, on one hand, the direction can be indicated for the electromagnetic pulse protection design, the design can be changed to improve the safety level of the airplane, and on the other hand, the problem that the design change cost is too high when relevant test verification is carried out at the later stage of airplane development is solved.
It should be understood that although the various steps in the flowcharts of fig. 1 and 2 are shown in order as indicated by the arrows, the steps are not necessarily performed in order as indicated by the arrows. The steps are not performed in the exact order shown and described, and may be performed in other orders, unless explicitly stated otherwise. Moreover, at least some of the steps in fig. 1 and 2 may include multiple sub-steps or multiple stages that are not necessarily performed at the same time, but may be performed at different times, and the order of performing the sub-steps or stages is not necessarily sequential, but may be performed in turn or alternately with other steps or at least some of the sub-steps or stages of other steps.
In one embodiment, as shown in fig. 3, there is provided an aircraft high altitude electromagnetic pulse environment risk analysis device, including:
the first model establishing module 310 is used for acquiring an external high-altitude electromagnetic pulse environment of the airplane and establishing an airplane exposed antenna model, an airplane exposed cable model and an airplane body electromagnetic shielding model based on the external high-altitude electromagnetic pulse environment;
an internal electromagnetic pulse environment determination module 320, configured to determine an internal electromagnetic pulse environment of the aircraft based on the external high altitude electromagnetic pulse environment and the aircraft body electromagnetic shielding model;
a second model establishing module 330, configured to establish an internal device electromagnetic shielding model and an internal cable electromagnetic shielding model of the aircraft based on the internal electromagnetic pulse environment;
the failure type determining module 340 is configured to determine a failure type of the aircraft caused by an external high-altitude electromagnetic pulse environment and an internal electromagnetic pulse environment based on the aircraft exposed antenna model, the aircraft exposed cable model, the internal equipment electromagnetic shielding model and the internal cable electromagnetic shielding model;
and a report output module 350, configured to output analysis report information for changing the aircraft design if the failure type is a catastrophic failure.
For specific limitations of the aircraft high altitude electromagnetic pulse environment risk analysis device, reference may be made to the above limitations of the aircraft high altitude electromagnetic pulse environment risk analysis method, and details are not repeated here. All or part of each module in the high-altitude electromagnetic pulse environment risk analysis device for the airplane can be realized by software, hardware and a combination thereof. The modules can be embedded in a hardware form or independent from a processor in the computer device, and can also be stored in a memory in the computer device in a software form, so that the processor can call and execute operations corresponding to the modules.
In one embodiment, a computer device is provided, which may be a server, the internal structure of which may be as shown in fig. 4. The computer device includes a processor, a memory, a network interface, and a database connected by a system bus. Wherein the processor of the computer device is configured to provide computing and control capabilities. The memory of the computer device comprises a nonvolatile storage medium and an internal memory. The non-volatile storage medium stores an operating system, a computer program, and a database. The internal memory provides an environment for the operation of an operating system and computer programs in the non-volatile storage medium. The database of the computer device is used for storing data. The network interface of the computer device is used for communicating with an external terminal through a network connection. The computer program is executed by a processor to realize the risk analysis method for the airplane high altitude electromagnetic pulse environment.
Those skilled in the art will appreciate that the architecture shown in fig. 4 is merely a block diagram of some of the structures associated with the disclosed aspects and is not intended to limit the computing devices to which the disclosed aspects apply, as particular computing devices may include more or less components than those shown, or may combine certain components, or have a different arrangement of components.
In one embodiment, a computer device is provided, comprising a memory and a processor, the memory having a computer program stored therein, the processor implementing the following steps when executing the computer program:
acquiring an external high-altitude electromagnetic pulse environment of the airplane, and establishing an airplane exposed antenna model, an airplane exposed cable model and an airplane body electromagnetic shielding model based on the external high-altitude electromagnetic pulse environment;
determining the internal electromagnetic pulse environment of the airplane based on the external high-altitude electromagnetic pulse environment and the airplane body electromagnetic shielding model;
establishing an internal equipment electromagnetic shielding model and an internal cable electromagnetic shielding model of the airplane based on the internal electromagnetic pulse environment;
determining failure types of the aircraft caused by an external high-altitude electromagnetic pulse environment and an internal electromagnetic pulse environment based on the aircraft exposed antenna model, the aircraft exposed cable model, the internal equipment electromagnetic shielding model and the internal cable electromagnetic shielding model;
and if the failure type is catastrophic failure, outputting analysis report information for changing the design of the airplane.
In one embodiment, a computer-readable storage medium is provided, having a computer program stored thereon, which when executed by a processor, performs the steps of:
acquiring an external high-altitude electromagnetic pulse environment of the airplane, and establishing an airplane exposed antenna model, an airplane exposed cable model and an airplane body electromagnetic shielding model based on the external high-altitude electromagnetic pulse environment;
determining the internal electromagnetic pulse environment of the airplane based on the external high-altitude electromagnetic pulse environment and the airplane body electromagnetic shielding model;
establishing an internal equipment electromagnetic shielding model and an internal cable electromagnetic shielding model of the airplane based on the internal electromagnetic pulse environment;
determining failure types of the aircraft caused by an external high-altitude electromagnetic pulse environment and an internal electromagnetic pulse environment based on the aircraft exposed antenna model, the aircraft exposed cable model, the internal equipment electromagnetic shielding model and the internal cable electromagnetic shielding model;
and if the failure type is catastrophic failure, outputting analysis report information for changing the design of the airplane.
It will be understood by those skilled in the art that all or part of the processes of the methods of the embodiments described above can be implemented by hardware instructions of a computer program, which can be stored in a non-volatile computer-readable storage medium, and when executed, can include the processes of the embodiments of the methods described above. Any reference to memory, storage, database, or other medium used in the embodiments provided herein may include non-volatile and/or volatile memory, among others. Non-volatile memory can include read-only memory (ROM), Programmable ROM (PROM), Electrically Programmable ROM (EPROM), Electrically Erasable Programmable ROM (EEPROM), or flash memory. Volatile memory can include Random Access Memory (RAM) or external cache memory. By way of illustration and not limitation, RAM is available in a variety of forms such as Static RAM (SRAM), Dynamic RAM (DRAM), Synchronous DRAM (SDRAM), Double Data Rate SDRAM (DDRSDRAM), Enhanced SDRAM (ESDRAM), Synchronous Link DRAM (SLDRAM), Rambus Direct RAM (RDRAM), direct bus dynamic RAM (DRDRAM), and memory bus dynamic RAM (RDRAM).
The technical features of the above embodiments can be arbitrarily combined, and for the sake of brevity, all possible combinations of the technical features in the above embodiments are not described, but should be considered as the scope of the present specification as long as there is no contradiction between the combinations of the technical features.
The above-mentioned embodiments only express several embodiments of the present application, and the description thereof is more specific and detailed, but not construed as limiting the claims. It should be noted that, for a person skilled in the art, several variations and modifications can be made without departing from the concept of the present application, which falls within the scope of protection of the present application. Therefore, the protection scope of the present patent shall be subject to the appended claims.
Claims (10)
1. An airplane high altitude electromagnetic pulse environment risk analysis method is characterized by comprising the following steps:
acquiring an external high-altitude electromagnetic pulse environment of the airplane, and establishing an airplane exposed antenna model, an airplane exposed cable model and an airplane body electromagnetic shielding model based on the external high-altitude electromagnetic pulse environment;
determining an internal electromagnetic pulse environment of the aircraft based on the external high-altitude electromagnetic pulse environment and the aircraft body electromagnetic shielding model; in the step of determining the internal electromagnetic pulse environment of the aircraft based on the external high-altitude electromagnetic pulse environment and the aircraft body electromagnetic shielding model, the aircraft body electromagnetic shielding model is established through the following steps: processing the external high-altitude electromagnetic pulse environment, the material characteristics, the pore size and the lap joint impedance by a time domain finite difference method to obtain the aircraft body electromagnetic shielding model; the material characteristics, the size of the hole seam and the lap joint impedance are obtained through a three-dimensional digital prototype model of an airplane body;
establishing an internal equipment electromagnetic shielding model and an internal cable electromagnetic shielding model of the airplane based on the internal electromagnetic pulse environment;
determining failure types of the aircraft caused by the external high-altitude electromagnetic pulse environment and the internal electromagnetic pulse environment based on the aircraft exposed antenna model, the aircraft exposed cable model, the internal equipment electromagnetic shielding model and the internal cable electromagnetic shielding model;
if the failure type is catastrophic failure, outputting analysis report information for changing the design of the airplane; wherein the analysis report information is used for indicating the part of the airplane needing improvement.
2. The aircraft high altitude electromagnetic pulse environment risk analysis method according to claim 1, further comprising the steps of:
if the failure type is non-catastrophic failure, judging whether the failure type is dangerous failure or not;
if the failure type is non-dangerous failure, analyzing the failure level and the corresponding probability, and outputting analysis report information of the electromagnetic protection design specification of the airplane;
and if the failure type is dangerous failure, analyzing the occurrence probability, outputting analysis report information of the electromagnetic protection design description of the airplane when the occurrence probability meets the quantitative analysis condition, and outputting analysis report information for changing the design of the airplane when the occurrence probability does not meet the quantitative analysis condition.
3. The aircraft high altitude electromagnetic pulse environment risk analysis method according to claim 1, wherein the step of establishing an aircraft interior equipment electromagnetic shielding model and an aircraft interior cable electromagnetic shielding model comprises:
and (4) integrating the structural material, the size of the hole seam, the lap joint impedance, the cable material and the length parameter of the material of the airplane equipment, and establishing an internal equipment electromagnetic shielding model and an internal cable electromagnetic shielding model.
4. The method for analyzing risks of high altitude electromagnetic pulse environment of aircraft as claimed in any one of claims 1 to 3, wherein the step of determining the failure types of the external high altitude electromagnetic pulse environment and the internal electromagnetic pulse environment to the aircraft based on the aircraft exposed antenna model, the aircraft exposed cable model, the internal equipment electromagnetic shielding model and the internal cable electromagnetic shielding model comprises the steps of:
and acquiring the voltage peak value, the peak power and the rise time of the coupling waveform in the aircraft exposed antenna by a time domain finite difference method based on the aircraft exposed antenna model and the receiving gain of the aircraft exposed antenna.
5. The method for analyzing risks of high altitude electromagnetic pulse environment of aircraft according to claim 4, wherein the step of determining the failure types of the aircraft caused by the external high altitude electromagnetic pulse environment and the internal electromagnetic pulse environment based on the aircraft exposed antenna model, the aircraft exposed cable model, the internal equipment electromagnetic shielding model and the internal cable electromagnetic shielding model comprises the steps of:
and acquiring the voltage peak value, the peak power and the rise time of the coupling waveform in the airplane exposed cable by a time domain finite difference method based on the airplane exposed cable model and the material characteristics of the airplane exposed cable.
6. The method for analyzing risks of high altitude electromagnetic pulse environment of aircraft according to claim 5, wherein the step of determining the types of failures caused to the aircraft by the external high altitude electromagnetic pulse environment and the internal electromagnetic pulse environment based on the aircraft exposed antenna model, the aircraft exposed cable model, the internal equipment electromagnetic shielding model and the internal cable electromagnetic shielding model comprises the steps of:
and acquiring the voltage peak value, the peak power and the rise time of the coupling waveform in the aircraft internal equipment by a time domain finite difference method based on the internal equipment electromagnetic shielding model.
7. The method for analyzing risks of high altitude electromagnetic pulse environment of aircraft according to claim 5, wherein the step of determining the types of failures caused to the aircraft by the external high altitude electromagnetic pulse environment and the internal electromagnetic pulse environment based on the aircraft exposed antenna model, the aircraft exposed cable model, the internal equipment electromagnetic shielding model and the internal cable electromagnetic shielding model comprises the steps of:
and acquiring the voltage peak value, the peak power and the rise time of the coupling waveform in the internal cable of the airplane by a time domain finite difference method based on the internal cable electromagnetic shielding model.
8. An aircraft high altitude electromagnetic pulse environment risk analysis device, characterized by includes:
the first model building module is used for obtaining an external high-altitude electromagnetic pulse environment of the airplane and building an airplane exposed antenna model, an airplane exposed cable model and an airplane body electromagnetic shielding model based on the external high-altitude electromagnetic pulse environment; the aircraft body electromagnetic shielding model is also used for processing the external high-altitude electromagnetic pulse environment, the material characteristics, the size of the pore and the lap joint impedance by a time domain finite difference method and establishing the aircraft body electromagnetic shielding model; the material characteristics, the size of the hole seam and the lap joint impedance are obtained through a three-dimensional digital prototype model of an airplane body;
the internal electromagnetic pulse environment determining module is used for determining the internal electromagnetic pulse environment of the airplane based on the external high-altitude electromagnetic pulse environment and the airplane body electromagnetic shielding model;
the second model establishing module is used for establishing an internal equipment electromagnetic shielding model and an internal cable electromagnetic shielding model of the airplane based on the internal electromagnetic pulse environment;
the failure type determining module is used for determining failure types of the aircraft caused by the external high-altitude electromagnetic pulse environment and the internal electromagnetic pulse environment based on the aircraft exposed antenna model, the aircraft exposed cable model, the internal equipment electromagnetic shielding model and the internal cable electromagnetic shielding model;
and the report output module is used for outputting analysis report information for changing the design of the airplane if the failure type is catastrophic failure, wherein the analysis report information is used for indicating the part of the airplane needing improvement.
9. A computer device comprising a memory and a processor, the memory storing a computer program, characterized in that the processor realizes the steps of the method of any one of claims 1 to 7 when executing the computer program.
10. A computer-readable storage medium, on which a computer program is stored, which, when being executed by a processor, carries out the steps of the method according to any one of claims 1 to 7.
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| Application Number | Priority Date | Filing Date | Title |
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| CN201911179896.3A CN110991110B (en) | 2019-11-27 | 2019-11-27 | Airplane high-altitude electromagnetic pulse environment risk analysis method and device and computer equipment |
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