CN105677991A - Reliability design optimization method for avionic device - Google Patents
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Abstract
The invention provides a reliability design optimization method for an avionic device. By means of the reliability design optimization method for the avionic device, the reliability index of the device can be practically and effectively promoted in the design stage. According to the technical scheme, the method comprises the following steps that three-dimensional digital prototype modeling is conducted according to an avionic device design scheme; on the basis of a three-dimensional digital prototype, environmental stress digital prototype modeling is conducted according to a device working load, an environmental load and design information relevant to device characteristics, and a model is corrected and verified; thermal environment stress, mechanical environment stress and the like of the avionic device are analyzed by referring to environmental conditions, environmental stress weak links of the device are searched, and corresponding avionic device design optimization is conducted; a fault physical digital prototype model is built, environmental stress analysis results are introduced to conduct device fault risk prediction, avionic device design optimization is conducted aiming at the reliability weak links occurring in the analysis process, and the reliability level of the avionic device is evaluated according to the optimized fault risk distribution situation.
Description
Technical field
The present invention relates to and be mainly used in avionic device design, be a kind of utilize fail-safe analysis to complete avionic device design optimization the method for lifting means reliability.
Background technology
Avionic device technical difficulty is big, and systematicness is strong. Residing natural environment and mechanical environment inclement condition, simultaneously that reliability requirement is also more and more higher, how improving equipment reliability in the presence of a harsh environment has become a necessary problems faced. Along with the development of science and technology, the functional requirement of synthetic aviation electronic equipment is more and more higher, and structure is day by day complicated, makes the fault diagnosis of electronic equipment become sufficiently complex, and reliability is affected. Have employed a large amount of new technique in current avionic device, integrated level is high, and systematicness is strong, and product structure is complicated, uses environment harsh, and technique assembling degree is intensive; Requirement maintenance cost reduces, and reliability engineering steps into new field. Following avionic device to synthesization, modularity, miniaturization, multifunction, high reliability direction develop, this will necessarily cause such as the appearance of the problems such as heat radiation, electromagnetic compatibility and interface inter-link. Meanwhile, the function of electronic equipment, volume, weight, reliability and the adaptability etc. to various environment are included into the category of design, and this has higher requirement to design. The reliability of avionic device is by the impact of many factors, and the reliability design general by the past can not meet requirement. In the reliability theory in past, do not describe affecting the vital human factors of equipment dependability comprehensively, be even rarely mentioned. In Reliability Engineering, only the effect of people is confined to maintenance and management aspect. Can the basis of product reliability design being stability Design, have left stability Design, the temporal continuity of product quality cannot ensure. Design factor product reliability designs. Design the reliability on equipment and have very important impact. If designer is when product design, reliability being lacked due attention, unsuitable design will bring potential defect into, these defects will make defect sample reach to lose efficacy when stress orders about, and product runs the significant trouble that will appear from being difficult to expect.A large amount of statistics show, the inefficacy that in component failure, software affects the factors of reliability, incorrect use components and parts cause accounts for 1/3. According to statistics, the equipment fault caused because of anthropic factor accounts for the 30%～50% of equipment total failare number, and typical statistic value is 30.6%. The method that the Reliability Engineering of current domestic air mail electronic equipment also relies primarily on the post-project evaluating such as reliability determination, reliability growth test, there is cycle length, costly, and all defect in design can not being completely exposed and producing is likely to come into operation problems such as causing heavy losses to follow-up equipment. A large amount of statistics show, the inefficacy that in component failure, software affects the factors of reliability, incorrect use components and parts cause accounts for 1/3. Current hardware reliability improves constantly, and software reliability issue seems more prominent. Application software is day by day complicated, and the various software products of software business man's exploitation often have ten hundreds of even millions of source program statement. When carrying out abundant in content, structure is sufficiently complex software design, it is desirable to mistake do not occur or the number of mistake is limited in below extremely low limit, it is necessary to having a whole set of to improve the technology of software reliability and instrument. Software is the product designed by human brain, and by manually producing. If some requirement of user is neglected one's supervisory duties by designer, or during design, ignore some external environment condition rule, or designer and user's contact are not freely likely to make a mistake. The software of mistake can form running software mistake under certain input environment. If software itself does not comprise suitable fault-toleranr technique, software faults will cause software fault.
In the prior art, the work in series pattern of the lifting of avionic device reliability level commonly used " test of equipment performance designed reliability designed reliability improves and improves reliability test ". This pattern usually, after equipment has designed, carrys out the reliability prediction to equipment by the crash rate based on empirically determined element constant failure model. This reliability prediction can calculate the fault rate value of equipment, but how predicted data comprehensively to be analyzed, and finds out the reliability optimization direction of equipment, and then in the reliability level of design phase raising equipment, this method for predicting reliability does not provide. The reliability optimization making equipment cannot be completed by this in the design phase, causes the successive ignition of design process, it could even be possible to there is being unsatisfactory in test the situation of reliability index, causes the iteration of production process. Owing to synthetic aviation electronic equipment becomes increasingly complex, reliability requirement is more and more higher, and reliability, by the restriction of various factors, is difficult to ensure that by current method for designing and control method. Synthetic aviation electronic equipment.
Summary of the invention
In order to overcome prior art avionic device reliability method above shortcomings, the present invention provides one can shorten the lead time, reduce R&D costs, and can prevent fault from occurring, the lifting avionic device reliability design optimization method of lifting means reliability level
The above-mentioned purpose of the present invention can be reached by following measures: a kind of avionic device reliability design optimization method is characterized in that comprising the steps: in the design phase, carries out 3-dimensional digital Prototype Modeling according to avionic device design, based on 3-dimensional digital model machine, according to the temperature in plant life cycle, vibration environment load, power consumption, electric current, voltage, frequency and other service load, the relevant design information of relevant parameter dynamic range, carry out hot feature, mechanical characteristics environmental stress digital prototype modeling and modelling verification, require to carry out equipment heat, mechanical environment stress analysis with reference to avionic device environmental suitability, the environmental stress weak link of location equipment, comparison foundation avionic device standard design criteria, determine the weak link being unsatisfactory for environmental suitability, return 3-dimensional digital Prototype Design step to be designed optimizing, and be recirculated to stress analysis step, until meet environmental suitability requirement, to meeting environmental suitability, then enter failure risk prediction and reliability assessment, set up faulty physical PM prototype model, according to stress analysis result, analysis failure risk is distributed, the weak links of reliability of location equipment, according to failure risk distribution situation, the reliability level of assessment avionic device, with reference to reliability index requirements, meet reliability index requirements, then enter detailed Engineering Design, it is unsatisfactory for reliability index requirements, 3-dimensional digital Prototype Design optimization is re-started for the weak links of reliability occurred in analyzing, and it is recycled to failure risk prediction and reliability assessment, until entering detailed Engineering Design after meeting reliability index requirements.
The present invention has the advantages that compared to prior art
Shorten the equipment development cycle, reduce equipment R&D costs.The present invention is with reference to avionic device environmental condition, analyze the environmental stress of the hot feature of avionic device, mechanics spy, find the environmental stress weak link of described equipment, carry out corresponding design optimization, analyze the failure risk of described equipment, the weak links of reliability of location equipment, the reliability level of assessment avionic device, and carry out specific aim optimization, until meet reliability index requirements; The deficiency of the work in series pattern of convectional reliability " test of equipment performance designed reliability designed reliability improves and improves reliability test " can be overcome, reliability index at design phase practical lifting means, reduce in reliability test, occur that equipment is unsatisfactory for the situation of reliability index, reduce the probability of amendment model machine in kind, thus shortening the lead time, reduce R&D costs.
Reduce R&D costs, and can prevent fault from occurring. The failure mechanism affecting equipment dependability index is analyzed by the present invention, rely on analysis means, find weak links of reliability, it is designed optimizing for the weak links of reliability occurred in analyzing and with corresponding failure risk information, the reliability assessment value making equipment meets requirement, prevent fault from occurring by equipment 3-dimensional digital model machine is carried out further design optimization, it is possible in the reliability index of the design phase efficiently and effectively lifting means of equipment. R&D costs are reduced while the reliability level of lifting means.
Reliability index promotes. Failure risk prediction has been incorporated in the design cycle of avionic device by the present invention with reliability assessment, predicted by failure risk, the weak links of reliability of location avionic device, and optimize digital mockup design according to weak links of reliability, reliability requirement has been designed in avionic device, realize fusion and the Synchronous fluorimetry of reliability and performance, improve the reliability level of equipment design phase.
Accompanying drawing explanation
Below in conjunction with drawings and Examples, invention is further illustrated.
Fig. 1 is the schematic flow sheet that avionic device reliability design of the present invention optimizes.
Detailed description of the invention
Consult Fig. 1. in the examples below, the design optimization realization promoting avionic device reliability realizes with optimizing by incorporating fail-safe analysis in performance design. in the design phase, carry out 3-dimensional digital Prototype Modeling according to avionic device equipment design, based on 3-dimensional digital model machine, according to the temperature in plant life cycle, temperature cycles, vibration, shock environment load, power consumption, electric current, voltage, frequency and other service load, the relevant design information of version, overall dimensions, annexation and relevant parameter dynamic range, carry out hot feature, mechanical characteristics environmental stress digital prototype modeling and modelling verification, with reference to avionic device environmental suitability requirement, carry out the environmental stress analyses such as the hot feature of equipment, mechanics, the environmental stress weak link of location equipment, the design criteria that comparison establishing criteria specify, determine the weak link being unsatisfactory for environmental suitability, return 3-dimensional digital Prototype Design, be designed optimizing, and be recirculated to stress analysis until meeting environmental suitability requirement, to meeting environmental suitability, then enter failure risk prediction and reliability assessment, set up faulty physical PM prototype model, according to stress analysis result, analysis failure risk is distributed, the weak links of reliability of location equipment, according to failure risk distribution situation, the reliability level of assessment avionic device, with reference to reliability index requirements, meet reliability index requirements, then enter detailed Engineering Design, it is unsatisfactory for reliability index requirements, 3-dimensional digital Prototype Design optimization is re-started for the weak links of reliability occurred in analyzing, and it is recycled to failure risk prediction and reliability assessment, until entering detailed Engineering Design after meeting reliability index requirements. concrete steps include as follows:
(1) according to avionic device design, 3-dimensional digital Prototype Design modeling is carried out;
(2) based on 3-dimensional digital model machine, add the relevant design information of the three below aspect of avionic device: (a) power consumption, electric current, voltage, frequency and other service load, the environmental loads such as temperature in (b) life period of equipment, temperature cycles, vibration, impact, the device characteristics such as (c) annexation and relevant parameter dynamic range, carry out the environmental stress digital prototype modeling of the features such as the heat of avionic device, mechanics, and carried out modelling verification and correction by the method such as Thermal test and kinetic test; Wherein environmental stress digital prototype includes: hot feature digital prototype and mechanical characteristics digital prototype.
(3) with reference to the environmental suitability of avionic device, carry out the environmental stress analyses such as the heat of avionic device, mechanics, the environmental stress weak link of searching equipment, and carry out 3-dimensional digital Prototype Design modeling according to weak link return step (1), carry out corresponding avionic device 3-dimensional digital model machine to improve, and be recirculated to stress analysis until meeting the environmental suitability requirement of equipment;
(4) set up avionics failure physical digital PM prototype model, according to stress analysis result, carry out the failure risk prediction of equipment, according to failure risk distribution situation, the reliability level of assessment avionic device. With reference to reliability index, it is back to step (1) for the weak links of reliability occurred in analyzing and carries out 3-dimensional digital model machine optimization, and it is recycled to failure risk prediction with reliability assessment until meeting reliability index requirements, hence into detailed Engineering Design.
According to avionic device design, adding on the basis of the geometry of avionic device, interconnected relationship and installation site, carry out 3-dimensional digital Prototype Modeling; Add the service load of avionic device, environmental load and device characteristics, 3-dimensional digital model machine is carried out respective handling, obtain hot feature digital prototype and the mechanical characteristics digital prototype of avionic device, and carried out modelling verification and correction by the method such as Thermal test and kinetic test; Environmental load with reference to avionic device, carry out the environmental stress analysis of the aspects such as the heat of avionic device, mechanics, the environmental stress weak link of searching equipment, and carry out the improvement of corresponding avionic device 3-dimensional digital model machine until meeting environmental suitability requirement according to environmental stress weak link; Set up avionics failure physical digital model machine, according to stress analysis result, carry out the failure risk prediction of equipment, according to failure risk distribution situation, the reliability level of assessment avionic device. With reference to reliability index, carry out 3-dimensional digital model machine optimization for the weak links of reliability occurred in analyzing, until meeting reliability index requirements, hence into detailed Engineering Design.
3-dimensional digital model machine needs to accurately reflect the design informations such as the version of this equipment, overall dimensions, mounting means, internal module composition and weight, plate level device layout and weight. 3-dimensional digital Prototype Design is the functional requirement according to avionic device and mounting means, the conceptual design carried out; Based on this, in the way of three-dimensional modeling, carry out the 3-dimensional digital Prototype Design of avionic device.
The modeling of environmental stress digital prototype is on 3-dimensional digital model machine basis, adds the relevant informations such as the material properties of avionic device, device power consumption and device characteristics, carries out the environmental stress digital prototype modeling of the features such as equipment heat, mechanics respectively; This digital prototype should be modified by test method, and correction can be undertaken by validation test, checking modeling accuracy.
For guaranteeing the accuracy that equipment mechanical characteristics digital prototype models, the test of vibration equipment modal response and random response test is carried out by kinetic test, obtain actual modal response and random response curve and the data of whole equipment, according to these random response curves and data and stress analysis obtain emulation modal response and the comparing result of emulation random response curve and data, avionic device mechanical characteristics digital prototype is modified and checking.
For guaranteeing the accuracy that hot feature digital prototype models, adopt the contactless method being combined with contact, application thermal imaging system and temperature sensor carry out the test of device temperature field, some temperature test, according to Thermal test result and the temperature field test in stress analysis, some temperature comparisons's situation, the hot feature digital prototype of avionic device is modified and checking.
Environmental stress analysis is referred to the environmental suitability of avionic device, analyzed by the heat of avionic device, mechanics iso-stress, obtain the response distribution situation under extreme environmental conditions, and the thermal design criterion determined according to standards such as army mark, rowers, Anti-vibration Design criterion, it is indicated that deficiency in design and the environmental stress weak link of requirement can not be met. And carry out the improvement of corresponding avionic device 3-dimensional digital model machine according to design weak link, and it is recirculated to stress analysis until meeting the environmental suitability requirement of equipment.
Failure risk prediction is to add detailed design parameter, technological parameter and electronic devices and components detail parameters on 3-dimensional digital model machine basis to set up avionics failure physical digital model machine, introduce environmental stress and analyze result, carry out the stress-Cumulative Damage of equipment, obtain the failure risk information such as each abort situation of device interior, fault mode, failure mechanism, fault time; And the random fluctuation counter stress that foundation equipment parameters, stress level etc. are within the specific limits damages and the impact of damage accumulation, introduce Monte Carlo method MonteCarlo emulation and carry out parameter discrete and stochastic sampling calculating, to form the failure risk information data of large sample amount. Weak links of reliability and failure risk information thereof is determined according to the principle that fault time is the shortest. MonteCarlo emulation mode is also known as Monte Carlo method, it is a kind of method adopting statistical sampling theory to solve mathematics, physics and engineering problem approx. the basic thought of its solution problem is, initially set up and describe this problem and have the probabilistic model of similarity, then model is carried out stochastic simulation or statistical sampling, the result of recycling gained obtains the statistical value approximate solution as former problem of characteristic quantity, and the precision solved is made some estimation. The main theoretical basis of MonteCarlo emulation mode is the law of large numbers in theory of probability, the sampling analysis Main Means to be stochastic variable. The feature of MonteCarlo emulation mode is as follows: (1) MonteCarlo simulation analysis is by simple sampling with repetition realization in a large number, therefore computational methods and program structure are all very simple; (2) the probability and convergence rate restrained is unrelated with the dimension of problem; (3) strong adaptability, the impact limited by conditions of problems is less.
Reliability assessment is after obtaining the major failure risk information of avionic device, fault density fitting of distribution is carried out by the big-sample data that failure risk prediction is obtained, and by substantial amounts of fault data is picked out the data suited the requirements, the fault density of this partial fault is distributed the fault density distribution adopting emulation mode to be fused to equipment again, finally evaluates the reliability level of equipment.
Comparison avionic device reliability index, such as MTBF MTBF, meet reliability index, then enter detailed Engineering Design; It is unsatisfactory for equipment dependability index, the equipment dependability weak link occurred in predicting for failure risk returns and optimizes 3-dimensional digital model machine, and it is re-circulated to failure risk prediction and reliability assessment, until entering detailed Engineering Design after meeting reliability index requirements.
Above-described is only the preferred embodiments of the present invention.It should be pointed out that, for the person of ordinary skill of the art, under the premise without departing from the principles of the invention, it is also possible to make some deformation and improvement. Such as the kind of counter stress analysis increases and decreases. These alterations and modifications should be regarded as belonging to protection scope of the present invention.
Claims (9)
1. avionic device reliability design optimization method is characterized in that comprising the steps: in a design phase, carries out 3-dimensional digital Prototype Modeling according to avionic device design, based on 3-dimensional digital model machine, according to the temperature in plant life cycle, vibration environment load, power consumption, electric current, voltage, frequency and other service load, the relevant design information of relevant parameter dynamic range, carry out hot feature, mechanical characteristics environmental stress digital prototype modeling and modelling verification, require to carry out equipment heat, mechanical environment stress analysis with reference to avionic device environmental suitability, the environmental stress weak link of location equipment, comparison foundation avionic device standard design criteria, determine the weak link being unsatisfactory for environmental suitability, return 3-dimensional digital Prototype Design step to be designed optimizing, and be recirculated to stress analysis step, until meet environmental suitability requirement, to meeting environmental suitability, then enter failure risk prediction and reliability assessment, set up faulty physical PM prototype model, according to stress analysis result, analysis failure risk is distributed, the weak links of reliability of location equipment, according to failure risk distribution situation, the reliability level of assessment avionic device, with reference to reliability index requirements, meet reliability index requirements, then enter detailed Engineering Design, it is unsatisfactory for reliability index requirements, 3-dimensional digital Prototype Design optimization is re-started for the weak links of reliability occurred in analyzing, and it is recycled to failure risk prediction and reliability assessment, until entering detailed Engineering Design after meeting reliability index requirements.
2. avionic device reliability design optimization method as claimed in claim 1, it is characterized in that, failure risk prediction is incorporated in the design cycle of avionic device with reliability assessment, predicted by failure risk, the weak links of reliability of location avionic device, and optimize avionic device design, the reliability index of assessment equipment according to weak links of reliability, the reliability level of equipment is improved in the design phase of equipment.
3. avionic device reliability design optimization method as claimed in claim 1, it is characterized in that, environmental suitability with reference to avionic device, carry out the heat of avionic device, mechanical stress analysis, the environmental stress weak link of searching equipment, and return 3-dimensional digital Prototype Design modeling procedure according to environmental stress weak link, carry out corresponding avionic device 3-dimensional digital model machine and improve.
4. avionic device reliability design optimization method as claimed in claim 1, it is characterized in that, the modeling of environmental stress digital prototype is on 3-dimensional digital model machine basis, add the service load of avionic device, environmental load and device characteristics relevant information, carry out equipment heat, the modeling of mechanical environment stress digital prototype respectively.
5. avionic device reliability design optimization method as claimed in claim 1, it is characterized in that, for guaranteeing the accuracy that equipment mechanical characteristics digital prototype models, the test of vibration equipment modal response and random response test is carried out by kinetic test, obtain actual modal response and random response curve and the data of whole equipment, according to these random response curves and data and stress analysis obtain emulation modal response and the comparing result of emulation random response curve and data, avionic device mechanical characteristics digital prototype is modified and checking.
6. avionic device reliability design optimization method as claimed in claim 1, it is characterized in that, for guaranteeing the accuracy that hot feature digital prototype models, adopt the contactless method being combined with contact, application thermal imaging system and temperature sensor carry out the test of device temperature field, some temperature test, according to Thermal test result and the temperature field test in stress analysis, some temperature comparisons's situation, the hot feature digital prototype of avionic device is modified and checking.
7. avionic device reliability design optimization method as claimed in claim 1, it is characterized in that, environmental stress analyzes the environmental suitability with reference to avionic device, analyzed by the heat of avionic device, mechanics iso-stress, obtain the response distribution situation under extreme environmental conditions, and the thermal design criterion determined according to industry standard, Anti-vibration Design criterion, it is indicated that deficiency in design and the environmental stress weak link of requirement can not be met.
8. avionic device reliability design optimization method as claimed in claim 1, it is characterized in that, failure risk prediction is to add detailed design parameter, technological parameter and electronic devices and components detail parameters on 3-dimensional digital model machine basis to set up avionics failure physical digital model machine, introduce environmental stress and analyze result, carry out the stress-Cumulative Damage of equipment, obtain the failure risk information such as each abort situation of device interior, fault mode, failure mechanism, fault time; And the random fluctuation counter stress that foundation equipment parameters, stress level are within the specific limits damages and the impact of damage accumulation, introduce statistical analysis method MonteCarlo emulation and carry out parameter discrete and stochastic sampling calculating, form the failure risk information data of large sample amount.
9. avionic device reliability design optimization method as claimed in claim 1, it is characterized in that, reliability assessment is after obtaining the major failure risk information of avionic device, fault density fitting of distribution is carried out by the big-sample data that failure risk prediction is obtained, and by substantial amounts of fault data is picked out the data suited the requirements, the fault density of this partial fault is distributed the fault density distribution adopting emulation mode to be fused to equipment again, finally evaluates the reliability level of equipment.
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