CN112761818B - State monitoring system of reusable ramjet engine - Google Patents
State monitoring system of reusable ramjet engine Download PDFInfo
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- CN112761818B CN112761818B CN202110053871.XA CN202110053871A CN112761818B CN 112761818 B CN112761818 B CN 112761818B CN 202110053871 A CN202110053871 A CN 202110053871A CN 112761818 B CN112761818 B CN 112761818B
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- 238000012544 monitoring process Methods 0.000 title claims abstract description 37
- 238000004088 simulation Methods 0.000 claims abstract description 17
- 238000003745 diagnosis Methods 0.000 claims abstract description 12
- 238000012795 verification Methods 0.000 claims abstract description 11
- 238000000034 method Methods 0.000 claims description 30
- 238000004458 analytical method Methods 0.000 claims description 15
- 230000015556 catabolic process Effects 0.000 claims description 15
- 238000006731 degradation reaction Methods 0.000 claims description 15
- 238000012360 testing method Methods 0.000 claims description 15
- 230000036541 health Effects 0.000 claims description 11
- 238000004364 calculation method Methods 0.000 claims description 9
- 238000007405 data analysis Methods 0.000 claims description 8
- 238000011156 evaluation Methods 0.000 claims description 8
- 230000002159 abnormal effect Effects 0.000 claims description 3
- 238000012937 correction Methods 0.000 claims description 3
- 238000001514 detection method Methods 0.000 claims description 3
- 230000007246 mechanism Effects 0.000 claims description 3
- 238000004080 punching Methods 0.000 abstract description 14
- 206010063385 Intellectualisation Diseases 0.000 abstract description 4
- 238000012423 maintenance Methods 0.000 abstract description 2
- 238000005516 engineering process Methods 0.000 description 5
- 238000011160 research Methods 0.000 description 5
- 238000009825 accumulation Methods 0.000 description 4
- 238000011161 development Methods 0.000 description 3
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000008859 change Effects 0.000 description 1
- 230000007812 deficiency Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000006872 improvement Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
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Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K7/00—Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof
- F02K7/10—Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof characterised by having ram-action compression, i.e. aero-thermo-dynamic-ducts or ram-jet engines
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C9/00—Controlling gas-turbine plants; Controlling fuel supply in air- breathing jet-propulsion plants
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K7/00—Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof
- F02K7/10—Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof characterised by having ram-action compression, i.e. aero-thermo-dynamic-ducts or ram-jet engines
- F02K7/16—Composite ram-jet/turbo-jet engines
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- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F30/00—Computer-aided design [CAD]
- G06F30/20—Design optimisation, verification or simulation
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- General Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Physics & Mathematics (AREA)
- Theoretical Computer Science (AREA)
- Computer Hardware Design (AREA)
- Evolutionary Computation (AREA)
- Geometry (AREA)
- General Physics & Mathematics (AREA)
- Testing Of Engines (AREA)
Abstract
The invention discloses a state monitoring system of a reusable ramjet, which comprises a fault diagnosis standard module, a fault state identification module, a controller, a fault knowledge base and a simulation verification platform, wherein the fault diagnosis standard module is used for detecting the fault state of the ramjet; the invention can be applied to the power device of the near space aircraft such as the punching stage of a reusable punching engine and a turbine punching combined engine, can find the fault of the reusable punching engine in time, determine the availability and the maintenance requirement of the punching engine, greatly improve the safety, the reliability and the maintainability of the reusable punching engine, has scientific, simple and convenient system, can realize intellectualization and miniaturization, and greatly improve the informatization and intellectualization level of the reusable punching engine.
Description
Technical Field
The invention relates to the technical field of spaceflight reusable ramjet engines, in particular to a state monitoring system of a reusable ramjet engine.
Background
In recent years, the strategic value of the aerospace shuttle vehicle is emphasized by all countries in the world, and military developed countries such as the United states and the Russia invest a great deal of funds, so that the research on the technology and the application of the aerospace shuttle vehicle is actively carried out, and the research and the development of the aerospace shuttle vehicle are gradually carried out in China. The ramjet has the characteristic of high specific impulse under the supersonic flight condition, and is ideal power for long-distance, high-altitude and high-speed cruising aircrafts. With the development of technology and the change of demand, the application demand of the ramjet engine to and from the aircraft in the field of novel near space aircraft and even aerospace is increasing. Compared with the traditional one-time elastic ramjet, the ramjet is developed from one-time use to repeated reuse, the function and performance requirements of the repeated reusable ramjet are greatly improved, and the system complexity is increased. In order to improve the comprehensive performances of the reusable ramjet such as safety, reliability, availability and the like and adapt to the information and intelligent technical development trend of advanced engines, the research on the monitoring technology of the ramjet state is urgently needed. However, in the field of the ramjet, the ramjet is mainly used for disposable bullets at home and abroad, at present, a technology for monitoring the state of the reusable ramjet is hardly available, specific theoretical research and method deficiency on the aspect of discrimination standards are involved, no specific application and engineering research is carried out on the implementation method level, the method accumulation is less, and no relevant experience and data accumulation exist.
Disclosure of Invention
In view of this, the present invention provides a state monitoring system for a reusable ramjet engine, which can find out the fault of the reusable ramjet engine in time, and greatly improve the safety, reliability and maintainability of the reusable ramjet engine.
The technical scheme adopted by the invention is as follows:
a state monitoring system of a reusable ramjet engine comprises a fault diagnosis standard module, a fault state identification module, a controller, a fault knowledge base and a simulation verification platform;
the fault diagnosis standard module is used for establishing a criterion of the normal state, the abnormal state or the fault state of the ramjet;
the fault state identification module is used for comparing the collected technical state parameters of the ramjet with the judgment criteria to obtain the technical state of the ramjet, obtaining a health evaluation result by using a ramjet gas circuit performance monitoring method and a key component service life monitoring method, and generating a fault data analysis report; the health assessment results include engine performance degradation levels and available capacity, critical component life consumption, and estimated remaining life;
the controller takes the technical state and the health evaluation result of the ramjet sent by the fault state identification module as input, takes the collected technical state parameters of the ramjet as feedback, carries out self-adaptive control or fault-tolerant control according to the control rule parameters calculated by the simulation verification platform, outputs a correction signal, and adjusts the ramjet in real time by an external execution mechanism to ensure that the technical state of the ramjet is in a normal state;
the fault knowledge base is used for forming a monitoring method for the performance of a gas circuit of the ramjet engine and a monitoring method for the service life of a key component, and perfecting the judgment criterion of the fault diagnosis standard module according to the fault data analysis report;
and the simulation verification platform establishes a simulation model by combining the state monitoring data of the ground test and the flight test of the ramjet, and calculates the control rule parameters according to the simulation model.
Further, the ramjet gas circuit performance monitoring method obtains the performance degradation level and the available capacity of the engine through ramjet performance reduced parameter analysis, a degradation and degradation trend identification method, performance degradation model analysis and a performance parameter identification threshold value method.
Further, the method for monitoring the service life of the key component calculates the service life consumption and the estimated residual service life of the key component of the stamping engine according to the service life loss calculation model, the load magnitude of the key component and the self-strength condition.
Further, the fault knowledge base aims at the thermodynamic cycle characteristics of the ramjet, and establishes a similar analysis method of the ramjet under different incoming flow conditions through pneumatic and thermodynamic theoretical analysis to form a monitoring method of the performance of the gas circuit of the ramjet.
Further, the fault knowledge base carries out load data accumulation through a ground test and a flight test of the ramjet aiming at the structure and the load characteristics of the ramjet, establishes a life loss calculation model, and corrects the life loss calculation model of the ramjet by combining the detection and analysis of the damage degree of the engine obtained in the test.
Has the beneficial effects that:
the invention can be applied to the power device of the near space aircraft such as the punching stage of a reusable punching engine and a turbine punching combined engine, can find the fault of the reusable punching engine in time, determines the availability and the maintenance requirement of the punching engine, greatly improves the safety, the reliability and the maintainability of the reusable punching engine, has scientific, simple and convenient system, can realize intellectualization and miniaturization, and greatly improves the informatization and intellectualization level of the reusable punching engine.
Drawings
FIG. 1 is a schematic diagram of the system of the present invention.
Detailed Description
The invention is described in detail below by way of example with reference to the accompanying drawings.
The invention provides a state monitoring system of a reusable ramjet engine, which comprises a fault diagnosis standard module, a fault state identification module, a controller, a fault knowledge base and a simulation verification platform, as shown in figure 1.
The fault diagnosis standard module is used for analyzing and establishing a judgment criterion of the technical state of the ramjet according to the function and the characteristic of monitoring the ramjet, wherein the technical state comprises a normal state, an abnormal state and a fault state, and the judgment criterion comprises a threshold value for identifying the pneumatic parameters of the ramjet and the like.
The fault state identification module is used for comparing the collected technical state parameters of the ramjet with the judgment criteria to obtain the technical state of the ramjet, and utilizing a ramjet gas circuit performance monitoring method and a key component service life monitoring method to obtain a health evaluation result and generate a fault data analysis report. Health assessment results include engine performance degradation levels and available capacity, critical component life consumption, and estimated remaining life. The ramjet engine state of technology parameters include engine temperature, pressure, altitude, and flight mach number.
The controller takes the technical state and the health evaluation result of the ramjet sent by the fault state identification module as input, takes the acquired technical state parameters of the ramjet as feedback, carries out self-adaptive control or fault-tolerant control according to the control rule parameters calculated by the simulation verification platform, outputs a correction signal, and adjusts the ramjet in real time by an external execution mechanism so that the technical state of the ramjet is in a normal state.
The fault knowledge base is used for forming a ramjet gas circuit performance monitoring method and a key component service life monitoring method, and perfecting the judgment criterion of the fault diagnosis standard module according to the fault data analysis report transmitted by the fault state recognition module.
And the simulation verification platform establishes a simulation model by combining the state monitoring data of the ground test and the flight test of the ramjet, and calculates the control rule parameters according to the simulation model.
The fault diagnosis standard module is connected with the fault state identification module, the fault state identification module generates a health evaluation result and a fault data analysis report and respectively transmits the health evaluation result and the fault data analysis report to the controller and the fault knowledge base, and the fault knowledge base is connected with the simulation verification platform.
The monitoring method of the ramjet gas circuit performance obtains the performance degradation level and the available capacity of the engine through ramjet performance reduced parameter analysis, a degradation and degradation trend identification method, performance degradation model analysis and a performance parameter identification threshold value method.
The method for monitoring the service life of the key component calculates the service life consumption and the estimated residual service life of the key component of the stamping engine according to the service life loss calculation model, the load magnitude of the key component and the strength condition of the key component.
Aiming at the thermodynamic cycle characteristics of the ramjet, the fault knowledge base establishes a similar analysis method of the ramjet under different incoming flow conditions through pneumatic and thermodynamic theoretical analysis to form a monitoring method of the performance of the gas circuit of the ramjet.
Aiming at the structure and load characteristics of the ramjet, the fault knowledge base carries out load data accumulation through a ground test and a flight test of the ramjet, establishes a life loss calculation model, and corrects the life loss calculation model of the ramjet by combining detection and analysis of the damage degree of the engine obtained in the test.
Therefore, the faults of the reusable ramjet can be found in time, the safety, reliability and maintainability of the reusable ramjet are greatly improved, and the informatization and intelligentization levels of the reusable ramjet are greatly improved.
In summary, the above description is only a preferred embodiment of the present invention, and is not intended to limit the scope of the present invention. Any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (3)
1. A condition monitoring system of a reusable ramjet engine is characterized by comprising a fault diagnosis standard module, a fault condition identification module, a controller, a fault knowledge base and a simulation verification platform;
the fault diagnosis standard module is used for establishing the discrimination criteria of the normal state, the abnormal state and the fault state of the ramjet;
the fault state identification module is used for comparing the collected technical state parameters of the ramjet with the judgment criteria to obtain the technical state of the ramjet, and obtaining a health evaluation result by utilizing a ramjet gas circuit performance monitoring method and a key component service life monitoring method to generate a fault data analysis report; the health assessment results include engine performance degradation levels and available capacity, critical component life consumption, and estimated remaining life;
the controller takes the technical state and the health evaluation result of the ramjet sent by the fault state identification module as input, takes the collected technical state parameters of the ramjet as feedback, carries out self-adaptive control or fault-tolerant control according to the control rule parameters calculated by the simulation verification platform, outputs a correction signal, and adjusts the ramjet in real time by an external execution mechanism to ensure that the technical state of the ramjet is in a normal state;
the fault knowledge base is used for forming a monitoring method for the gas circuit performance of the ramjet and a monitoring method for the service life of a key component, and perfecting the judgment criterion of the fault diagnosis standard module according to the fault data analysis report;
the simulation verification platform is combined with the state monitoring data of the ramjet ground test and the flight test to establish a simulation model, and control rule parameters are calculated according to the simulation model;
the ramjet gas circuit performance monitoring method obtains the performance degradation level and the available capacity of the engine through ramjet performance reduced parameter analysis, a degradation and degradation trend identification method, performance degradation model analysis and a performance parameter identification threshold value method;
the fault knowledge base aims at the thermodynamic cycle characteristics of the ramjet, and establishes a similar analysis method of the ramjet under different incoming flow conditions through pneumatic and thermodynamic theoretical analysis to form a monitoring method of the performance of the gas circuit of the ramjet.
2. The system for monitoring the condition of a reusable ramjet as set forth in claim 1, wherein the method for monitoring the life of critical components calculates the life consumption and estimated remaining life of critical components of the ramjet based on the life loss calculation model, the load level of the critical components and the strength of the critical components.
3. The system for monitoring the state of a reusable ramjet according to claim 1, wherein the failure knowledge base is used for accumulating load data by carrying out a ground test and a flight test of the ramjet according to the structural and load characteristics of the ramjet, establishing a life loss calculation model, and correcting the life loss calculation model of the ramjet by combining detection and analysis of the damage degree of the engine obtained in the test.
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| CN202110053871.XA CN112761818B (en) | 2021-01-15 | 2021-01-15 | State monitoring system of reusable ramjet engine |
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| CN112761818B true CN112761818B (en) | 2023-01-31 |
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Family Cites Families (7)
| Publication number | Priority date | Publication date | Assignee | Title |
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| FR2972025B1 (en) * | 2011-02-25 | 2016-03-04 | Snecma | PREDICTION OF MAINTENANCE OPERATIONS ON AN AIRCRAFT ENGINE |
| FR3028067B1 (en) * | 2014-11-05 | 2016-12-30 | Snecma | VALIDATION TOOL FOR A SYSTEM FOR MONITORING AN AIRCRAFT ENGINE |
| CN107719699B (en) * | 2017-09-25 | 2020-12-01 | 中国航空工业集团公司西安飞机设计研究所 | A test comprehensive control management system and method |
| CN108256173B (en) * | 2017-12-27 | 2021-06-22 | 南京航空航天大学 | Gas circuit fault diagnosis method and system for dynamic process of aircraft engine |
| CN111581763B (en) * | 2019-02-15 | 2023-10-17 | 中国航发商用航空发动机有限责任公司 | Method for evaluating air path fault diagnosis result of aero-engine |
| CN110991024B (en) * | 2019-11-27 | 2025-01-21 | 南京航空航天大学 | A method for monitoring sudden changes in gas path components under concurrent failures of an aircraft engine control system |
| CN111259515B (en) * | 2020-01-07 | 2023-11-21 | 珠海欧比特宇航科技股份有限公司 | Aircraft health management method and system |
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