CN116448189B - Test equipment of supporting facility of flight command system - Google Patents
Test equipment of supporting facility of flight command system Download PDFInfo
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- CN116448189B CN116448189B CN202310693531.2A CN202310693531A CN116448189B CN 116448189 B CN116448189 B CN 116448189B CN 202310693531 A CN202310693531 A CN 202310693531A CN 116448189 B CN116448189 B CN 116448189B
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Classifications
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- G—PHYSICS
- G08—SIGNALLING
- G08G—TRAFFIC CONTROL SYSTEMS
- G08G5/00—Traffic control systems for aircraft, e.g. air-traffic control [ATC]
- G08G5/06—Traffic control systems for aircraft, e.g. air-traffic control [ATC] for control when on the ground
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01D—MEASURING NOT SPECIALLY ADAPTED FOR A SPECIFIC VARIABLE; ARRANGEMENTS FOR MEASURING TWO OR MORE VARIABLES NOT COVERED IN A SINGLE OTHER SUBCLASS; TARIFF METERING APPARATUS; MEASURING OR TESTING NOT OTHERWISE PROVIDED FOR
- G01D21/00—Measuring or testing not otherwise provided for
- G01D21/02—Measuring two or more variables by means not covered by a single other subclass
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- G—PHYSICS
- G08—SIGNALLING
- G08B—SIGNALLING OR CALLING SYSTEMS; ORDER TELEGRAPHS; ALARM SYSTEMS
- G08B21/00—Alarms responsive to a single specified undesired or abnormal condition and not otherwise provided for
- G08B21/18—Status alarms
- G08B21/185—Electrical failure alarms
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02A—TECHNOLOGIES FOR ADAPTATION TO CLIMATE CHANGE
- Y02A90/00—Technologies having an indirect contribution to adaptation to climate change
- Y02A90/10—Information and communication technologies [ICT] supporting adaptation to climate change, e.g. for weather forecasting or climate simulation
Abstract
The application discloses test equipment of a flight command system supporting facility, which relates to the technical field of test equipment. The application sends out the early warning signal before the flight command system supporting facility breaks down, so that the pilot can return to the flight before the flight command system supporting facility breaks down, and the safe flight of the aircraft is effectively ensured.
Description
Technical Field
The application relates to the technical field of test equipment, in particular to test equipment of a flight command system supporting facility.
Background
The flight command system is a comprehensive software system for aviation transportation and flight control, aims to provide planning, monitoring and coordination of flight tasks, is an important technical support tool in the aviation industry, helps ensure that an aircraft takes off, flies and lands safely, can trace back to the early stage of aviation industry development, and needs a system to manage and coordinate each flight task along with the introduction of the aircraft and the growth of aviation transportation;
the supporting facilities of the flight command system comprise a series of ground facilities and equipment, which are used for supporting the operation and the function realization of the flight command system, the facilities play a vital role in the aviation industry, and the facilities provide the infrastructure for data collection, processing, transmission and display, so that the smooth proceeding of the flight tasks is ensured.
The prior art has the following defects:
in the prior art, a pilot is remotely commanded through a flight command system, the flight command system acquires weather of a flight environment and predicts some possible abnormal conditions, and then a flight route of an aircraft is planned again, however, as the flight command system supports running through a series of ground facilities and equipment, when the ground facilities and the equipment fail, the flight command system is caused to command errors or command failures, so that the safe flight of the aircraft is not guaranteed;
based on the above, the application provides the test equipment of the supporting facilities of the flight command system, and the test equipment predicts the faults of the supporting facilities in the use process of the flight command system, so that the flight command system can make command strategies in advance, and the safe flight of an airplane is ensured.
Disclosure of Invention
The application aims to provide test equipment of a flight command system supporting facility, which aims to solve the defects in the background technology.
In order to achieve the above object, the present application provides the following technical solutions: the test equipment of the flight command system supporting facility comprises an acquisition unit, a judging unit, a prediction unit, a control unit and an early warning unit;
the acquisition unit: after multi-source data of test operation and operation of supporting facilities of the flight command system are collected, the multi-source data are preprocessed;
a judging unit: after receiving multi-source data of test operation of the matched facilities, comprehensively analyzing the multi-source data and generating an evaluation model, judging whether the matched facilities support the operation of the flight command system according to the evaluation model, if the matched facilities do not support the operation of the flight command system, sending a warning signal by a judging unit, and if the matched facilities support the operation of the flight command system, sending a wake-up signal by the judging unit to a control unit;
and a control unit: after receiving the wake-up signal, sending a starting instruction to the prediction unit;
prediction unit: the method comprises the steps of acquiring multi-source data of supporting facility operation from an acquisition unit at regular time, comprehensively analyzing the multi-source data, generating an early warning model, and predicting whether future use of the supporting facility of the flight command system can be failed according to the early warning model;
an early warning unit: if the future use of the facilities matched with the flight command system is predicted to be faulty, the early warning unit sends an early warning signal to the flight command system.
In a preferred embodiment, the acquisition unit acquires multi-source data of the ground radar system, the communication device and the meteorological device, wherein the multi-source data comprises device parameters and power parameters, the device parameters comprise ground radar transmitting power amplitude, communication device data transmission accuracy rate and meteorological sensor numerical change rate, and the power parameters comprise power supply voltage fluctuation values.
In a preferred embodiment, the determining unit removes the dimensions of the ground radar transmitting power amplitude, the communication device data transmission accuracy, the weather sensor value change rate and the supply voltage fluctuation value, and then the method comprises the following steps of:calculating to obtain facility coefficient->Wherein->For the data transmission accuracy of the communication device, +.>Transmit power amplitude for ground radar, < >>For the rate of change of the value of the meteorological sensor,for supply voltage ripple value +.>、/>、/>、/>The data transmission accuracy of the communication equipment, the ground radar transmitting power amplitude, the change rate of the meteorological sensor value and the proportional coefficient of the fluctuation value of the power supply voltage are respectively +.>、/>、/>、/>Are all greater than 0;
acquiring facility coefficientsAfter that, facility coefficient->And a preset evaluation threshold->And comparing to generate an evaluation model.
In a preferred embodiment, the prediction unit obtains the ground radar transmitting power amplitude, the data transmission accuracy of the communication device, the numerical change rate of the meteorological sensor and the power supply voltage fluctuation value removal dimension at regular time, and then the method is as follows:calculating to obtain facility coefficient->Wherein->For the data transmission accuracy of the communication device, +.>Transmit power amplitude for ground radar, < >>For the rate of change of the value of the meteorological sensor,for supply voltage ripple value +.>、/>、/>、/>The data transmission accuracy of the communication equipment, the ground radar transmitting power amplitude, the change rate of the meteorological sensor value and the proportional coefficient of the fluctuation value of the power supply voltage are respectively +.>、/>、/>、/>Are all greater than 0;
acquiring facility coefficientsAfter that, the facility coefficient is calculated/>And preset prediction threshold->And comparing to generate an early warning model.
In a preferred embodiment, the judging unit analyzes the test running state of the supporting facilities of the flight command system according to the evaluation model;
if the analysis result is that the facility coefficient< evaluation threshold->The judging unit analyzes that the supporting facilities do not support the operation of the flight command system and sends out a warning signal;
if the analysis result is that the facility coefficientEvaluate threshold ∈>The judging unit analyzes the supporting facilities to support the operation of the flight command system.
In a preferred embodiment, the prediction unit predicts whether future use of the flight command system supporting facility will fail according to the early warning model;
if the prediction result is that the facility coefficient< prediction threshold->The prediction unit analyzes that the matched facilities are about to have faults;
if the analysis result is that the facility coefficientNot less than prediction threshold->The prediction unit analyzes that the matched facilities run stably.
In a preferred embodiment, the method is characterized by: the processing logic of the ground radar transmitting power amplitude is as follows: marking the stable operating range of ground radar transmitting power asThe current monitored in real time is marked +.>When->At the time, the ground radar transmitting power amplitude value +.>The method comprises the steps of carrying out a first treatment on the surface of the When->At the time, the ground radar transmitting power amplitude value +.>；
The calculation expression of the ground radar transmitting power is as follows:the method comprises the steps of carrying out a first treatment on the surface of the In (1) the->Transmit power for ground radar, < >>Is the gain of the radar antenna, < >>Is radar wavelength, < >>Is the effective radiating area of the radar antenna, +.>Is the power of the radar transmitter, +.>Is a power density factor in free space propagation, +.>Take a value of 0.5.
In a preferred embodiment, the calculation expression of the data transmission accuracy of the communication device is:the method comprises the steps of carrying out a first treatment on the surface of the In (1) the->Is the number of bits in error>Is the total number of bits transmitted.
In a preferred embodiment, the rate of change of the meteorological sensor values: i is a numbered library of different sensors, and i= {1, 2, 3..the., n }, n is a positive integer greater than 0, =>For the ith sensor value change rate, the weather sensor includes a temperature sensor, a humidity sensor, an air pressure sensor, and a wind speed sensor, n=4, then，/>For the rate of change of the temperature sensor value, +.>For the rate of change of the humidity sensor value, +.>Is the rate of change of the value of the air pressure sensor,is the rate of change of the wind speed sensor value.
In a preferred embodiment, the rate of change of the temperature sensor value，/>Temperature values at two time points are respectively indicated, the rate of change of the humidity sensor value is +.>，/>Humidity values at two time points are respectively represented, and the change rate of the value of the air pressure sensor is +.>，/>Air pressure values at two time points are respectively represented, and the numerical change rate of the air speed sensor is +.>，/>Wind speed values for two points in time, < >>Respectively, representing the corresponding points in time.
In the technical scheme, the application has the technical effects and advantages that:
1. according to the application, the state evaluation is carried out on the matched facilities of the flight command system before the aircraft takes off, when the matched facilities are found to be insufficient to support the operation of the flight command system, the flight is stopped and a warning signal is sent out to remind an maintainer of the need of overhauling the matched facilities of the flight command system, so that the situation that the aircraft directly returns to the air after the aircraft is lifted due to the fact that the matched facilities of the flight command system do not support the operation is avoided, useless flight is caused, and the flight cost is increased is avoided;
2. according to the application, the facility coefficient is obtained through comprehensive calculation through a formula after the dimensions of the ground radar transmitting power amplitude, the communication equipment data transmission accuracy, the meteorological sensor numerical value change rate and the power supply voltage fluctuation value are removed, the data processing efficiency is effectively improved, the analysis is more comprehensive, an evaluation model is generated through comparison of the facility coefficient and an evaluation threshold value, the test running state of the matched facility is evaluated according to the evaluation model before the aircraft takes off, an early warning model is generated through comparison of the facility coefficient and a prediction threshold value, the running state of the matched facility is predicted through the prediction model at fixed time after the aircraft takes off, and the decision and management are convenient to make in time.
Drawings
In order to more clearly illustrate the embodiments of the present application or the technical solutions in the prior art, the drawings required for the embodiments will be briefly described below, and it is apparent that the drawings in the following description are only some embodiments described in the present application, and other drawings may be obtained according to these drawings for a person having ordinary skill in the art.
Fig. 1 is a system unit diagram of the present application.
Detailed Description
For the purpose of making the objects, technical solutions and advantages of the embodiments of the present application more apparent, the technical solutions of the embodiments of the present application will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present application, and it is apparent that the described embodiments are some embodiments of the present application, but not all embodiments of the present application. All other embodiments, which can be made by those skilled in the art based on the embodiments of the application without making any inventive effort, are intended to be within the scope of the application.
Example 1: referring to fig. 1, the test device of the supporting facility of the flight command system according to the embodiment includes an acquisition unit, a judgment unit, a prediction unit, a control unit and an early warning unit;
the method comprises the steps that after a flight command system tries to run before an aircraft takes off, an acquisition unit acquires multisource data of a supporting facility, the multisource data are preprocessed and sent to a judgment unit and a prediction unit, after the judgment unit receives the multisource data, the multisource data are comprehensively analyzed and an evaluation model is generated, whether the supporting facility supports the flight command system to run is judged according to the evaluation model, if the supporting facility does not support the flight command system to run, the judgment unit sends out a warning signal, if the supporting facility supports the flight command system to run, the flight command system enters an operating state, a pilot drives the aircraft to lift off, the judgment unit sends out a wake-up signal to a control unit, after the control unit receives the wake-up signal, a starting instruction is sent out to the prediction unit, after the prediction unit is started, the multisource data are acquired from the acquisition unit at regular time, the multisource data are comprehensively analyzed and an early warning model is generated, whether future use of the supporting facility of the flight command system is faulty or not is predicted according to the early warning model, if the supporting facility of the predicted to be faulty in future, the flight command system sends out an early warning signal to the flight command system, and after the pilot receives the pilot return command, the pilot return command is needed.
According to the application, the state evaluation is carried out on the matched facilities of the flight command system before the aircraft takes off, when the matched facilities are found to be insufficient to support the operation of the flight command system, the flight is stopped and a warning signal is sent out to remind an maintainer of the need of overhauling the matched facilities of the flight command system, so that the situation that the aircraft directly returns to the air after the aircraft is lifted due to the fact that the matched facilities of the flight command system do not support the operation is avoided, useless flight is caused, the flight cost is increased, and in the aircraft flight process, whether the future use of the matched facilities of the flight command system can fail or not is predicted by a prediction unit in a timing manner, so that a warning signal is sent out before the matched facilities of the flight command system fail, and a pilot can return to the air before the matched facilities of the flight command system fail, thereby effectively guaranteeing the safe flight of the aircraft.
The improved flight command system supporting facilities comprise the following facilities:
A. ground radar system: the ground radar system is used for monitoring and tracking the position and dynamic information of the aircraft, detecting the position of the aircraft through radar signals, and transmitting data to a related system for flight monitoring and conflict resolution;
B. communication apparatus: the supporting facilities of the flight command system comprise communication equipment, which is used for communication between the ground and the air, wherein the equipment comprises a radio station, satellite communication equipment, communication navigation equipment and the like, so that real-time communication and data transmission in a flight task are ensured;
C. weather equipment: the meteorological equipment is used for collecting and providing meteorological data and providing accurate meteorological information for a flight mission, and comprises a meteorological radar, a meteorological satellite receiver, a meteorological sensor and the like, so that a flight command system and a pilot can be helped to know current and predicted weather conditions;
D. flight data recording and analyzing device: the equipment is used for recording and analyzing flight data to support subsequent flight analysis and improvement, can record key data such as flight parameters, communication records, flight tracks and the like, and provides data support for performance evaluation and improvement of a flight command system;
E. data center and server facility: the flight command system requires powerful computing and storage capabilities to process and manage large amounts of data, and data centers and server facilities provide high performance computing and storage devices supporting the operation and data management of the flight command system.
In the actual situation, the facilities which play a main role in the safety command of the flight command system are a ground radar system, communication equipment and meteorological equipment;
when the ground radar system fails, the position data of the aircraft cannot be accurately acquired, so that the flight command system is difficult to know the position and the motion state of the aircraft in real time;
when the communication equipment fails, the flight plan, the route information and the instruction cannot be transmitted in time, so that communication between the aircraft and the ground command center is blocked, and the data transmission delay or loss can be caused by the failed communication equipment. This can lead to inaccuracy or loss of flight data, thereby affecting the flight director's knowledge and decisions about the aircraft's state;
when meteorological equipment fails, the flight command system cannot provide accurate weather navigation and flight limitation information. This will have an adverse effect on flight planning and flight decisions, increasing flight safety risks.
In summary, the acquisition unit mainly acquires multi-source data from a ground radar system, communication equipment and meteorological equipment;
the acquired multi-source data comprise equipment parameters and power parameters, wherein the equipment parameters comprise ground radar transmitting power amplitude, communication equipment data transmission accuracy and meteorological sensor numerical value change rate, and the power parameters comprise power supply voltage fluctuation values.
Example 2: after receiving the multi-source data, the judging unit comprehensively analyzes the multi-source data and generates an evaluation model, judges whether the matched facilities support the operation of the flight command system according to the evaluation model, and if the matched facilities do not support the operation of the flight command system, the judging unit sends out a warning signal;
after receiving the multi-source data, the judging unit comprehensively analyzes the multi-source data and generates an evaluation model, wherein the generation of the evaluation model comprises the following steps:
the judgment unit removes the dimensions of the ground radar transmitting power amplitude, the data transmission accuracy of the communication equipment, the numerical change rate of the meteorological sensor and the fluctuation value of the power supply voltage, and then the data transmission accuracy, the numerical change rate and the power supply voltage fluctuation value are calculated by the following formula:calculating to obtain facility coefficient->Wherein->For the data transmission accuracy of the communication device, +.>Transmit power amplitude for ground radar, < >>For the rate of change of the value of the meteorological sensor, +.>For supply voltage ripple value +.>、/>、/>、/>The data transmission accuracy of the communication equipment, the ground radar transmitting power amplitude, the change rate of the meteorological sensor value and the proportional coefficient of the fluctuation value of the power supply voltage are respectively +.>、/>、/>、/>Are all greater than 0.
In the application, the acquisition logic of the ground radar transmitting power amplitude is as follows: the ground radar transmitting power needs to be in a stable range, when the ground radar transmitting power is not in the stable rangeThe ground radar energy consumption can be increased, the generated heat causes faults and reduces the performance and accuracy of the radar system, so that the processing logic of the ground radar transmitting power amplitude is as follows: marking the stable operating range of ground radar transmitting power asThe current monitored in real time is marked +.>When->At the time, the ground radar transmitting power amplitude value +.>The method comprises the steps of carrying out a first treatment on the surface of the When->At the time, the ground radar transmitting power amplitude value +.>The larger the amplitude of the ground radar transmitting power is, the more unstable the ground radar transmitting power is, and the stable use of the matched facilities is affected;
the calculation expression of the ground radar transmitting power is as follows:the method comprises the steps of carrying out a first treatment on the surface of the In (1) the->Transmit power for ground radar, < >>Is the gain of the radar antenna, < >>Is radar wavelength, < >>Is the effective radiating area of the radar antenna, +.>Is the power of the radar transmitter, +.>Is a power density factor in free space propagation, +.>Take a value of 0.5.
The calculation expression of the data transmission accuracy rate of the communication equipment is as follows:the method comprises the steps of carrying out a first treatment on the surface of the In (1) the->Is the number of bits in error>For the total number of bits transmitted, the number of bits in error is the number of bits in error in the transmission process, the total number of bits transmitted is the total number of bits transmitted, and the greater the data transmission accuracy of the communication equipment is, the more stable the communication transmission of the communication equipment is, and the better the operation stability of the supporting facilities is.
The processing logic of the supply voltage fluctuation value is as follows: marking the voltage stable operating range of the matched facility asThe current monitored in real time is marked +.>When->At the time of supply voltage fluctuation valueThe method comprises the steps of carrying out a first treatment on the surface of the When->At this time, the supply voltage fluctuation value +.>The larger the fluctuation value of the power supply voltage is, the larger the fluctuation amplitude of the power supply voltage is, thereby affecting the stable use of the matched facilities.
Meteorological sensor rate of change of value: i is a numbered library of different sensors, and i= {1, 2, 3..the., n }, n is a positive integer greater than 0, =>For the ith sensor value change rate, the weather sensor typically includes a temperature sensor, a humidity sensor, an air pressure sensor, and a wind speed sensor, so n=4, then，/>For the rate of change of the temperature sensor value, +.>For the rate of change of the humidity sensor value, +.>Is the rate of change of the value of the air pressure sensor,for the numerical change rate of the wind speed sensor, the larger the numerical change rate of the meteorological sensor is, the more unstable the meteorological equipment operates, and the stable use of the whole supporting facility is affected.
Rate of change of temperature sensor value，/>Temperature values for two time points, +.>Respectively representing corresponding time points;
rate of change of humidity sensor value，/>Humidity values of two time points, < ->Respectively representing corresponding time points;
rate of change of barometric sensor value，/>Air pressure values, respectively representing two time points, +.>Respectively representing corresponding time points;
speed of change of value of wind speed sensor，/>Wind speed values for two points in time, < >>Respectively, representing the corresponding points in time.
Acquiring facility coefficientsAfter that, facility coefficient->And a preset evaluation threshold->And comparing to generate an evaluation model.
When the flight command system supporting facilities are in trial operation, the judging unit substitutes the multi-source data acquired by the acquisition unit into the evaluation model, and analyzes the trial operation state of the flight command system supporting facilities according to the evaluation model;
if the analysis result is that the facility coefficient< evaluation threshold->The judging unit analyzes that the supporting facilities do not support the operation of the flight command system, sends out a warning signal, stops the flight when a manager receives the warning signal, sends out an overhaul instruction to an overhaul personnel, and overhauls the supporting facilities of the flight command system after the overhaul personnel receives the overhaul instruction;
if the analysis result is that the facility coefficientEvaluate threshold ∈>The judging unit analyzes the supporting facilities to support the operation of the flight command system, and the manager approves the flight.
After the prediction unit is started, multi-source data are acquired from the acquisition unit at regular time, the multi-source data are comprehensively analyzed and an early warning model is generated, whether future use of the matched facilities of the flight command system is faulty or not is predicted according to the early warning model, a prediction result is sent to the early warning unit, if the future use of the matched facilities of the flight command system is predicted to be faulty, the early warning unit sends an early warning signal to the flight command system, after the early warning signal is received by the flight command system, a return instruction is directly sent to a pilot, and the pilot needs to drive the aircraft to return in time when receiving the return instruction;
after the prediction unit is started, multi-source data are acquired from the acquisition unit at regular time, and the multi-source data are comprehensively analyzed to generate an early warning model.
The prediction unit obtains the ground radar transmitting power amplitude, the data transmission accuracy of the communication equipment, the numerical value change rate of the meteorological sensor and the power supply voltage fluctuation value after removing the dimension by the formula:calculating to obtain facility coefficient->Wherein->For the data transmission accuracy of the communication device, +.>Transmit power amplitude for ground radar, < >>For the rate of change of the value of the meteorological sensor,for supply voltage ripple value +.>、/>、/>、/>The data transmission accuracy of the communication equipment, the ground radar transmitting power amplitude, the change rate of the meteorological sensor value and the proportional coefficient of the fluctuation value of the power supply voltage are respectively +.>、/>、/>、/>Are all greater than 0.
Acquiring facility coefficientsAfter that, facility coefficient->And preset prediction threshold->And comparing to generate an early warning model.
When the flight command system supporting facilities run, the prediction unit substitutes the multi-source data acquired by the acquisition unit into a prediction model, and predicts whether the future use of the flight command system supporting facilities can be failed according to the early warning model;
if the prediction result is that the facility coefficient< prediction threshold->The prediction unit analyzes that the matched facilities are about to have faults;
if the analysis result is that the facility coefficientNot less than prediction threshold->The prediction unit analyzes that the matched facilities run stably.
When the prediction result is that the analysis supporting facilities are about to fail, the early warning unit sends an early warning signal to the flight command system, the flight command system directly sends a return instruction to the pilot after receiving the early warning signal, and the pilot needs to drive the aircraft to return in time when receiving the return instruction.
According to the application, the facility coefficient is obtained through comprehensive calculation through a formula after the dimensions of the ground radar transmitting power amplitude, the communication equipment data transmission accuracy, the meteorological sensor numerical value change rate and the power supply voltage fluctuation value are removed, the data processing efficiency is effectively improved, the analysis is more comprehensive, an evaluation model is generated through comparison of the facility coefficient and an evaluation threshold value, the test running state of the matched facility is evaluated according to the evaluation model before the aircraft takes off, an early warning model is generated through comparison of the facility coefficient and a prediction threshold value, the running state of the matched facility is predicted through the prediction model at fixed time after the aircraft takes off, and the decision and management are convenient to make in time.
In the present application, the prediction threshold valueLess than the evaluation threshold->Because the evaluation model evaluates the running state of the flight command system auxiliary facilities before the aircraft takes off, the evaluation threshold value +.>The acquisition logic of (1) is:
when the data transmission accuracy of the communication device is at a minimum accuracy (when the data transmission accuracy of the communication device is lower than the minimum accuracy, the data of the communication device cannot be accurately transmitted, so that normal communication is affected), the ground radar transmission power amplitude is at a maximum power amplitude (when the ground radar transmission power amplitude exceeds the maximum power amplitude, the radar device generates excessive heat and stress, the service life of the device is shortened, or parts are damaged, the radar detection range is shortened, a long-distance target or a weak echo signal cannot be detected, etc.), the change rate of the value of the weather sensor is at a maximum change rate (when the change rate of the value of the weather sensor exceeds the maximum change rate, the weather sensor may have damage, the monitoring accuracy is reduced or cannot be monitored), and the power supply voltage fluctuation value has a maximum fluctuation value (for useWhen the fluctuation value of the electric voltage is higher than the maximum fluctuation value, the condition that the power supply voltage is too large or too small can lead to unstable operation of the electric equipment is indicated, and therefore, the electric equipment is in a proportion coefficient、/>、/>、/>After the determination, the minimum accuracy, the high power amplitude, the maximum change rate and the maximum fluctuation value are brought into a facility coefficient calculation formula to be calculated, so that a determined facility coefficient is obtained, and the facility coefficient is used as an evaluation threshold value;
after the aircraft is lifted off, a fault is required to be predicted in advance, so that 80% of the evaluation threshold value is taken as a prediction threshold value, and the effect of predicting in advance is achieved.
The above formulas are all formulas with dimensions removed and numerical values calculated, the formulas are formulas with a large amount of data collected for software simulation to obtain the latest real situation, and preset parameters in the formulas are set by those skilled in the art according to the actual situation.
In the description of the present specification, the descriptions of the terms "one embodiment," "example," "specific example," and the like, mean that a particular feature, structure, material, or characteristic described in connection with the embodiment or example is included in at least one embodiment or example of the present application. In this specification, schematic representations of the above terms do not necessarily refer to the same embodiments or examples. Furthermore, the particular features, structures, materials, or characteristics described may be combined in any suitable manner in any one or more embodiments or examples.
The preferred embodiments of the application disclosed above are intended only to assist in the explanation of the application. The preferred embodiments are not intended to be exhaustive or to limit the application to the precise form disclosed. Obviously, many modifications and variations are possible in light of the above teaching. The embodiments were chosen and described in order to best explain the principles of the application and the practical application, to thereby enable others skilled in the art to best understand and utilize the application. The application is limited only by the claims and the full scope and equivalents thereof.
Claims (6)
1. The utility model provides a test equipment of flight command system supporting facility which characterized in that: the system comprises an acquisition unit, a judging unit, a prediction unit, a control unit and an early warning unit;
the acquisition unit: after multi-source data of test operation and operation of supporting facilities of the flight command system are collected, the multi-source data are preprocessed;
a judging unit: after receiving multi-source data of test operation of the matched facilities, comprehensively analyzing the multi-source data and generating an evaluation model, judging whether the matched facilities support the operation of the flight command system according to the evaluation model, if the matched facilities do not support the operation of the flight command system, sending a warning signal by a judging unit, and if the matched facilities support the operation of the flight command system, sending a wake-up signal by the judging unit to a control unit;
and a control unit: after receiving the wake-up signal, sending a starting instruction to the prediction unit;
prediction unit: the method comprises the steps of acquiring multi-source data of supporting facility operation from an acquisition unit at regular time, comprehensively analyzing the multi-source data, generating an early warning model, and predicting whether future use of the supporting facility of the flight command system can be failed according to the early warning model;
an early warning unit: if the future use of the matched facilities of the flight command system is predicted to be faulty, the early warning unit sends an early warning signal to the flight command system;
the acquisition unit acquires multi-source data of a ground radar system, communication equipment and meteorological equipment, wherein the multi-source data comprises equipment parameters and power parameters, the equipment parameters comprise a ground radar transmitting power amplitude, communication equipment data transmission accuracy and a meteorological sensor numerical value change rate, and the power parameters comprise a power supply voltage fluctuation value; the judging unit transmits the ground radar transmitting power amplitude and the ground radar transmitting powerAfter the data transmission accuracy of the communication equipment, the numerical change rate of the meteorological sensor and the fluctuation value of the power supply voltage are removed, the dimension is removed through the formula:calculating to obtain facility coefficient->Wherein->For the data transmission accuracy of the communication device, +.>Transmit power amplitude for ground radar, < >>For the rate of change of the value of the meteorological sensor, +.>For supply voltage ripple value +.>、/>、/>、/>The data transmission accuracy of the communication equipment, the ground radar transmitting power amplitude, the change rate of the meteorological sensor value and the proportional coefficient of the fluctuation value of the power supply voltage are respectively +.>、/>、/>、/>Are all greater than 0;
acquiring facility coefficientsAfter that, facility coefficient->And a preset evaluation threshold->Comparing to generate an evaluation model;
the prediction unit is used for regularly obtaining the ground radar transmitting power amplitude, the data transmission accuracy of communication equipment, the numerical value change rate of a meteorological sensor and the power supply voltage fluctuation value, and removing the dimension, and then the method is characterized by comprising the following steps of:calculating to obtain facility coefficient->Wherein->For the data transmission accuracy of the communication device, +.>Transmit power amplitude for ground radar, < >>For the rate of change of the value of the meteorological sensor,for supplying voltageFluctuation value->、/>、/>、/>The data transmission accuracy of the communication equipment, the ground radar transmitting power amplitude, the change rate of the meteorological sensor value and the proportional coefficient of the fluctuation value of the power supply voltage are respectively +.>、/>、/>、/>Are all greater than 0;
acquiring facility coefficientsAfter that, facility coefficient->And preset prediction threshold->Comparing to generate an early warning model;
the change rate of the numerical value of the meteorological sensor: i is a library of numbers for different sensors,and i= {1, 2, 3..and n }, n is a positive integer greater than 0,/and n>For the ith sensor value change rate, the weather sensor includes a temperature sensor, a humidity sensor, an air pressure sensor, and a wind speed sensor, n=4, then，/>For the rate of change of the temperature sensor value, +.>For the rate of change of the humidity sensor value, +.>Is the rate of change of the value of the air pressure sensor,is the rate of change of the wind speed sensor value.
2. A test apparatus for a flight command system kit as recited in claim 1, wherein: the judging unit analyzes the test running state of the supporting facilities of the flight command system according to the evaluation model;
if the analysis result is that the facility coefficient< evaluation threshold->The judging unit analyzes that the supporting facilities do not support the operation of the flight command system and sends out a warning signal;
if the analysis result is that the facility coefficientEvaluate threshold ∈>The judging unit analyzes the supporting facilities to support the operation of the flight command system.
3. A test apparatus for a flight command system kit as recited in claim 2, wherein: the prediction unit predicts whether future use of the supporting facilities of the flight command system will fail according to the early warning model;
if the prediction result is that the facility coefficient< prediction threshold->The prediction unit analyzes that the matched facilities are about to have faults;
if the analysis result is that the facility coefficientNot less than prediction threshold->The prediction unit analyzes that the matched facilities run stably.
4. A test apparatus for a flight command system kit as recited in claim 1, wherein: the processing logic of the ground radar transmitting power amplitude is as follows: marking the stable operating range of ground radar transmitting power asThe current monitored in real time is marked +.>When->When the ground radar transmits power amplitudeThe method comprises the steps of carrying out a first treatment on the surface of the When->At the time, the ground radar transmitting power amplitude value +.>；
The calculation expression of the ground radar transmitting power is as follows:the method comprises the steps of carrying out a first treatment on the surface of the In (1) the->Transmit power for ground radar, < >>Is the gain of the radar antenna, < >>Is radar wavelength, < >>Is the effective radiating area of the radar antenna, +.>Is the power of the radar transmitter, +.>Is a power density factor in free space propagation, +.>Take a value of 0.5.
5. A flight command system kit as claimed in claim 4A test apparatus, characterized in that: the calculation expression of the data transmission accuracy rate of the communication equipment is as follows:the method comprises the steps of carrying out a first treatment on the surface of the In (1) the->As the number of bits in error,is the total number of bits transmitted.
6. The test equipment for a flight command system kit as recited in claim 5, wherein: the rate of change of the temperature sensor value，/>Temperature values at two time points are respectively indicated, the rate of change of the humidity sensor value is +.>，/>Humidity values at two time points are respectively represented, and the change rate of the value of the air pressure sensor is +.>，/>Air pressure values at two time points are respectively represented, and the numerical change rate of the air speed sensor is +.>，Wind speed values for two points in time, < >>Respectively, representing the corresponding points in time.
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