CN116341116A - Design method, system, equipment and medium for airworthiness induction of landing gear shock absorber - Google Patents
Design method, system, equipment and medium for airworthiness induction of landing gear shock absorber Download PDFInfo
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Abstract
The invention discloses a design method, a system, equipment and a medium for airworthiness induction of a shock absorber of an undercarriage, and relates to the technical field of shock absorbers. The method comprises the following steps: determining the navigability requirement of the shock absorber; according to the navigable requirements and the preset operating environment working conditions, calculating the external load of the shock absorber, and determining the related data of the shock absorption mode; the vibration damping mode related data comprise vibration damping data and vibration damping parts; constructing a three-dimensional solid model of the shock absorber according to the related data of the shock absorption mode; the shock absorber three-dimensional entity model comprises an expansion layer and an application layer which are sequentially connected; the expansion layer is used for storing identification indexes corresponding to the damping mode related data; the application layer is used for updating the model configuration according to the identification index; and carrying out seaworthiness verification according to the three-dimensional solid model of the shock absorber, and determining the seaworthiness standard of the shock absorber. The invention can structure the airworthiness requirement of the shock absorber and improve the airworthiness of the shock absorber.
Description
Technical Field
The invention relates to the technical field of shock absorbers, in particular to a method, a system, equipment and a medium for designing airworthiness induction of a shock absorber of an undercarriage.
Background
Three-dimensional models have become the dominant mode of aviation manufacturing in China as the sole manufacturing basis. The main method of three-dimensional modular definition is model-based engineering definition (Model Based Definition, MBD). MBD is a method of expressing complete product definition information in an integrated three-dimensional solid model. The method can fully utilize the expressive force of the three-dimensional model, and is a product information definition method which is more convenient for users to understand and has higher efficiency. The field of aviation manufacturing utilizes MBD technology to add various manufacturing semantic information such as the size, tolerance, process and the like of a product on a three-dimensional solid model, so that the MBD model of the product is used as a single data source to support the design and manufacturing of the product, however, the product definition mode does not completely contain information required by the product airworthiness in an MBD data set, and the airworthiness is not facilitated to run through the whole life cycle of the product.
The shock absorber is used for absorbing impact energy during landing and taxiing of the navigable aircraft, and is a key part for affecting flight safety. The airworthiness design of the shock absorber includes determining an airworthiness requirement of the shock absorber, driving the design, manufacture and maintenance of the shock absorber with the airworthiness requirement, and indicating compliance with the airworthiness requirement through compliance verification efforts. The process requires the shock absorber developing party to construct a model which can clearly define the airworthiness requirements of the shock absorber and display the airworthiness design and verification process of the shock absorber so as to support airworthiness activities of both the developing party and airworthiness authorities, so that the airworthiness design of the landing gear shock absorber of the airworthiness aircraft is ensured to be successfully completed.
The design of the airworthiness inducibility of the landing gear shock absorber is a complex design process with intensive knowledge, and comprises comprehensive application of airworthiness regulation clause, industry standard, design manual, experience knowledge and the like. In particular, the airworthiness requirements of shock absorbers are spread in part of the Content of Civil Aviation Regulations (CCAR), consultation notices (AC), technical standards regulation (CTSO), industry standards (ASTM, SAE), etc. The designer needs to retrieve, call and merge the corresponding standard document content to form the complete damper airworthiness design and verification requirements. The association relation between the three-dimensional digital analog of the shock absorber and the seaworthiness information is split in the seaworthiness information application mode of the standard document, so that the design efficiency is remarkably reduced, the risk of design errors is increased, and information exchange between seaworthiness office staff and design staff is seriously hindered. In addition, the damper airworthiness design case through airworthiness approval is a crystal of intellectual resources of aircrafts manufacturers, and the core competitiveness is an important embodiment, so that the airworthiness design case representation for accumulating and reusing knowledge of the manufacturers is also of great significance. The strong parametric modeling, information integration and expression capability of the MBD technology enable the navigability requirement of the shock absorber to be fused with the three-dimensional digital-analog, gradually induce and complete the navigability design of the shock absorber, and form a navigability design case which is easy to display and reuse.
In summary, the landing gear shock absorber airworthiness inducibility design has the following problems: 1) The complete damper airworthiness requirements are distributed in all levels of standards, and an effective structural airworthiness requirement information organization mode is lacked; 2) The navigability design of the shock absorber does not fully utilize the information integration and expression capability of the MBD technology; 3) Shock absorber navigability design case representations that are easy to knowledge accumulate and reuse are lacking. Therefore, there is no design solution capable of improving the navigability of the shock absorber in the current prior art.
Disclosure of Invention
The invention aims to provide a landing gear shock absorber airworthiness induction design method, system, equipment and medium, which can structure the airworthiness requirement of the shock absorber and improve the airworthiness of the shock absorber.
In order to achieve the above object, the present invention provides the following solutions:
a landing gear shock absorber seaworthiness inducing design method, comprising:
determining the navigability requirement of the shock absorber;
calculating the external load of the shock absorber according to the navigable requirements and the preset operating environment working conditions, and determining the related data of the shock absorption mode; the vibration reduction mode related data comprise vibration reduction data and vibration reduction parts; the damping data comprises a damper design load spectrum, damper travel and efficiency, piston size, safety targets and allocations; the damping parts comprise strength, rigidity, durability, materials and processes;
constructing a three-dimensional solid model of the shock absorber according to the related data of the shock absorption mode; the three-dimensional physical model of the shock absorber comprises a shock absorber overall design model and a shock absorber part design model; the shock absorber three-dimensional entity model comprises an expansion layer and an application layer which are sequentially connected; the expansion layer is used for storing an identification index corresponding to the damping mode related data; the application layer is used for updating model configuration according to the identification index;
and carrying out seaworthiness verification according to the three-dimensional solid model of the shock absorber, and determining the seaworthiness standard of the shock absorber.
Optionally, the determining the airworthiness requirement of the shock absorber specifically includes:
and determining the airworthiness requirement according to the external load, performance and function of the shock absorber, system design requirements, part design requirements, process requirements and airworthiness verification test requirements.
Optionally, the constructing a three-dimensional physical model of the shock absorber according to the related data of the shock absorption mode specifically includes:
constructing a general parameterized feature model of the shock absorber;
index identification is carried out on the damping mode related data, and an identification index corresponding to the damping mode related data is obtained;
and configuring the general parameterized feature model of the shock absorber according to the identification index corresponding to the related data of the shock absorption mode, and determining the three-dimensional entity model of the shock absorber.
Optionally, the constructing a general parameterized feature model of the shock absorber specifically includes:
determining a composition architecture of the shock absorber; the composition framework comprises parts and corresponding constraint relations;
and constructing a general parameterized feature model of the shock absorber according to the composition framework.
Optionally, after constructing the three-dimensional solid model of the shock absorber according to the shock absorption mode related data, the method further comprises:
and correlating and storing the construction flow corresponding to the shock absorber three-dimensional entity model to generate a shock absorber navigability design case.
The invention also provides a landing gear shock absorber airworthiness induction design system, which comprises:
the airworthiness requirement determining module is used for determining the airworthiness requirement of the shock absorber;
the external load calculation module is used for calculating the external load of the shock absorber according to the navigable requirements and the preset operation environment working conditions, and determining relevant data of a shock absorption mode; the vibration reduction mode related data comprise vibration reduction data and vibration reduction parts; the damping data comprises a damper design load spectrum, damper travel and efficiency, piston size, safety targets and allocations; the damping parts comprise strength, rigidity, durability, materials and processes;
the shock absorber model construction module is used for constructing a shock absorber three-dimensional entity model according to the shock absorption mode related data; the three-dimensional physical model of the shock absorber comprises a shock absorber overall design model and a shock absorber part design model; the shock absorber three-dimensional entity model comprises an expansion layer and an application layer which are sequentially connected; the expansion layer is used for storing an identification index corresponding to the damping mode related data; the application layer is used for updating model configuration according to the identification index;
and the seaworthiness verification module is used for performing seaworthiness verification according to the shock absorber three-dimensional solid model and determining the seaworthiness standard of the shock absorber.
The invention also provides electronic equipment, which comprises a memory and a processor, wherein the memory is used for storing a computer program, and the processor runs the computer program to enable the electronic equipment to execute the landing gear shock absorber airworthiness induction design method.
The invention also provides a computer readable storage medium storing a computer program which when executed by a processor implements a landing gear shock absorber airworthiness inducing design method as described above.
According to the specific embodiment provided by the invention, the invention discloses the following technical effects:
the invention discloses a landing gear shock absorber airworthiness induction design method, a system, equipment and a medium, wherein the method comprises the steps of determining the airworthiness requirement of a shock absorber, calculating the external load of the shock absorber on the airworthiness requirement, obtaining shock absorption mode related data, constructing a shock absorber three-dimensional solid model based on the shock absorption related data, displaying an identification index corresponding to the shock absorption mode related data in the shock absorber three-dimensional solid model through an expansion layer, displaying the three-dimensional model after the model configuration is updated according to the identification index through an application layer, and further obtaining the airworthiness result of the shock absorber through airworthiness verification, so that the airworthiness requirement of the structural shock absorber is realized, and the airworthiness of the shock absorber is improved.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions of the prior art, the drawings that are needed in the embodiments will be briefly described below, it being obvious that the drawings in the following description are only some embodiments of the present invention, and that other drawings may be obtained according to these drawings without inventive effort for a person skilled in the art.
FIG. 1 is a flow chart of a landing gear shock absorber airworthiness induction design method of the present invention;
FIG. 2 is a schematic diagram of the design flow of the airworthiness of the shock absorber according to the present embodiment;
FIG. 3 is a schematic diagram of the design process of the airworthiness of the shock absorber and the MBD model construction in this embodiment;
fig. 4 is a block diagram of the airworthiness inducing design system of the landing gear shock absorber of the present invention.
Detailed Description
The following description of the embodiments of the present invention will be made clearly and completely with reference to the accompanying drawings, in which it is apparent that the embodiments described are only some embodiments of the present invention, but not all embodiments. All other embodiments, which can be made by those skilled in the art based on the embodiments of the invention without making any inventive effort, are intended to be within the scope of the invention.
The invention aims to provide a landing gear shock absorber airworthiness induction design method, system, equipment and medium, which can structure the airworthiness requirement of the shock absorber and improve the airworthiness of the shock absorber.
In order that the above-recited objects, features and advantages of the present invention will become more readily apparent, a more particular description of the invention will be rendered by reference to the appended drawings and appended detailed description.
As shown in FIG. 1, the invention provides a landing gear shock absorber airworthiness induction design method, system, equipment and medium, comprising the following steps:
step 100: the airworthiness requirements of the shock absorber are determined.
Step 200: calculating the external load of the shock absorber according to the navigable requirements and the preset operating environment working conditions, and determining the related data of the shock absorption mode; the vibration reduction mode related data comprise vibration reduction data and vibration reduction parts; the damping data comprises a damper design load spectrum, damper travel and efficiency, piston size, safety targets and allocations; the shock absorbing components include strength, stiffness, durability, materials and processes.
Step 300: constructing a three-dimensional solid model of the shock absorber according to the related data of the shock absorption mode; the three-dimensional physical model of the shock absorber comprises a shock absorber overall design model and a shock absorber part design model; the shock absorber three-dimensional entity model comprises an expansion layer and an application layer which are sequentially connected; the expansion layer is used for storing an identification index corresponding to the damping mode related data; the application layer is used for updating the model configuration according to the identification index.
Step 400: and carrying out seaworthiness verification according to the three-dimensional solid model of the shock absorber, and determining the seaworthiness standard of the shock absorber.
One embodiment of step 100 includes:
and determining the airworthiness requirement according to the external load, performance and function of the shock absorber, system design requirements, part design requirements, process requirements and airworthiness verification test requirements.
One embodiment of step 300 includes:
constructing a general parameterized feature model of the shock absorber; index identification is carried out on the damping mode related data, and an identification index corresponding to the damping mode related data is obtained; and configuring the general parameterized feature model of the shock absorber according to the identification index corresponding to the related data of the shock absorption mode, and determining the three-dimensional entity model of the shock absorber.
The method for constructing the general parameterized feature model of the shock absorber specifically comprises the following steps:
determining a composition architecture of the shock absorber; the composition framework comprises parts and corresponding constraint relations; and constructing a general parameterized feature model of the shock absorber according to the composition framework.
After step 300, further comprising:
and correlating and storing the construction flow corresponding to the shock absorber three-dimensional entity model to generate a shock absorber navigability design case.
Based on the above scheme, embodiments as shown in fig. 2-3 are provided:
step 1: general parameterized feature model construction for shock absorber
From the shock absorber landing gear model: the general composition and the structure of the shock absorber system are obtained by combing HB6176-1988, GB/T38918-2020, HB8449-2014, GJB3063A-2008 and HB/Z4-1995 and the technical manual (AMM manual) of the main-flow navigation aircraft, the constraint relation is matched importantly, and the general parametric characteristic model of the shock absorber is built by using main-flow CAD software such as CATIA, NX, solidWorks and the like. The characteristic parameterized model contains the parts that make up the shock absorber and their associated constraints. Wherein, the bumper shock absorber part includes: an inner cylinder and an outer cylinder; a piston, a piston rod, a dynamic and static sealing ring, a structure, a bolt and the like; constraints include geometric constraints of coaxiality, parallelism, end runout, and sealing structure.
Step 2: definition of airworthiness requirements for shock absorbers
The complete damper airworthiness requirement is combed from civil aviation regulations, corresponding consultation notices and industry standards. The airworthiness requirements of the shock absorber are organized according to the angles of external load, performance and function, system design requirements, part design requirements, process requirements and airworthiness verification test requirements, the airworthiness requirements which can be traced to specific design work are obtained through a standard hierarchical structure and a mutual supporting relation, and unique identification indexes of the airworthiness requirements are defined.
Step 3: defining a model of the design process of the navigability of a shock absorber
As shown in fig. 2, the respective conditions of the shock absorber are defined from corresponding terms of civil aviation regulations according to the model in which the shock absorber is to be installed and the expected operating environment, and the shock absorber external load calculation is performed in combination with the extreme environmental conditions. And selecting a damping mode according to the external load of the damper, and performing damping performance calculation and simulation. The external load is the load of the undercarriage calculated under each working condition, and the load is determined to be transmitted to the shock absorber according to the structural connection mode of the shock absorber and other systems of the undercarriage; the damping mode is divided into: oil and gas type shock absorption (mainstream); spring damping (especially for small aircraft). On this basis, the overall design of the shock absorber, including the shock absorber design load spectrum, shock absorber travel and efficiency, piston size, safety goals and allocations, etc., and the shock absorber component design, including strength, stiffness, durability, materials and processes, etc., and manufacturing verification are developed. And finally, verifying the assembled shock absorber by a system-level test which meets the navigable requirements.
Step 4: MBD model defining damper navigability design
As shown in fig. 3, for the airworthiness design process of step 3, an association relationship between the damper design process and the airworthiness requirement is established, the identification index of the airworthiness requirement is displayed by using the 3D annotation of the extension layer of the MBD model, and the specific content corresponding to the identification index is configured to the application layer of the MBD model. Therefore, the multi-view model expression of associating the extension layer with the application layer by taking the 3D geometric model as a carrier is realized, and design requirements, materials, processes and airworthiness verification test standards become organic compositions of the MBD data set.
Step 5: gradually pushing MBD models of each design link according to the navigability design process models
Pushing an MBD model of a shock absorber system in the overall design stage of the shock absorber; in the design stage of the shock absorber parts, the part MBD model is pushed, and in the seaworthiness verification stage of the shock absorber, the system MBD model is pushed. The shock absorber seaworthiness verification stage mainly comprises shock absorber drop test, static strength, dynamic strength, fatigue test, sealing test and the like according to relevant seaworthiness standards. The process is secondarily developed through CAD software to form a solidified design flow, after the design process of the airworthiness of the shock absorber is completed, the MBD-based airworthiness design case representation of the special navigation aircraft type landing gear shock absorber is formed, and the accumulation and reuse of the airworthiness design knowledge are realized by storing and calling the case.
Thus, take the design of induction of fixed wing landing gear shock absorber seaworthiness induction design as an example:
1) And (3) constructing a general parameterized characteristic model of the shock absorber: the general composition and the framework of a shock absorber system are obtained by combing the conventional oil-gas shock absorbers of the navigation aircraft landing gear with HB6176-1988, GB/T38918-2020, HB8449-2014, GJB3063A-2008, HB/Z4-1995 and an aircraft AMM manual, and the general composition and the framework of the shock absorber system are matched with the important constraint relation. And constructing a general parametric characteristic model of the shock absorber by utilizing SolidWorks software. The characteristic parameterized model comprises an inner cylinder, an outer cylinder, a dynamic and static sealing structure, an O-shaped sealing ring, a square sealing ring, an inflation valve, a cover plate, a connector, a sleeve, a central bolt, a locking nut and the like.
2) Definition of airworthiness requirements of shock absorbers: the airworthiness terms of the shock absorber are extracted from CCAR23 department of aircraft airworthiness regulations of normal class, and the complete airworthiness requirement of the shock absorber is established by combining AC-23 normal class aircraft airworthiness approval and ASTM standards. The airworthiness requirements of the shock absorber are organized according to the angles of external load, performance and function, system design requirements, part design requirements, process requirements and airworthiness verification test requirements, the airworthiness requirements for realizing development of specific design work are obtained, and unique identification indexes of the airworthiness requirements are defined.
3) MBD model is designed to bumper shock absorber navigability: defining a design process model of the shock absorber according to the step 3, and defining MBD models of all design stages according to the step 4. MBD model construction function provided by SolidWorks software is utilized to express geometric features and assembly relations of a model by utilizing a three-dimensional model, identification indexes of airworthiness requirements are displayed by utilizing 3D annotations on the three-dimensional model, the identification indexes are directly embedded into a PDF file, and specific contents corresponding to the airworthiness requirement identification indexes in the 3D annotations are configured in a text region of the PDF file. Therefore, the multi-view model expression of associating the extension layer with the application layer by taking the 3D geometric model as a carrier is realized by using the PDF file, so that design requirements, materials, processes and airworthiness verification test standards become organic compositions of the MBD data set.
4) MBD model-based damper navigability induction design: pushing the MBD model to each design stage according to the step 5, and updating the design result to the parameterized MBD model to form a damper navigability design case with specific fixed wing model and operation characteristics.
The embodiment has the following beneficial effects:
the structural information representation based on MBD of the landing gear shock absorber airworthiness induction design requirement is realized, and the airworthiness approval planning and airworthiness approval efficiency are remarkably improved; the MBD model of the design of the airworthiness of the shock absorber reflects the design process and the association of the design process and the airworthiness requirement, the expressive force of the 3D model is fully utilized, the design process of the airworthiness can be clearly and intuitively displayed, and the MBD model has an important supporting effect on rapidly and high-quality completion of airworthiness approval work of the shock absorber. MBD-based damper navigability design case representation is beneficial to knowledge accumulation and reuse, and the difficulty of navigability design is remarkably reduced.
As shown in fig. 4, the present invention provides a landing gear shock absorber seaworthiness inducing design system, comprising:
and the airworthiness requirement determining module is used for determining the airworthiness requirement of the shock absorber.
The external load calculation module is used for calculating the external load of the shock absorber according to the navigable requirements and the preset operation environment working conditions, and determining relevant data of a shock absorption mode; the vibration reduction mode related data comprise vibration reduction data and vibration reduction parts; the damping data comprises a damper design load spectrum, damper travel and efficiency, piston size, safety targets and allocations; the shock absorbing components include strength, stiffness, durability, materials and processes.
The shock absorber model construction module is used for constructing a shock absorber three-dimensional entity model according to the shock absorption mode related data; the three-dimensional physical model of the shock absorber comprises a shock absorber overall design model and a shock absorber part design model; the shock absorber three-dimensional entity model comprises an expansion layer and an application layer which are sequentially connected; the expansion layer is used for storing an identification index corresponding to the damping mode related data; the application layer is used for updating the model configuration according to the identification index.
And the seaworthiness verification module is used for performing seaworthiness verification according to the shock absorber three-dimensional solid model and determining the seaworthiness standard of the shock absorber.
The invention also provides electronic equipment, which comprises a memory and a processor, wherein the memory is used for storing a computer program, and the processor runs the computer program to enable the electronic equipment to execute the landing gear shock absorber airworthiness induction design method.
The invention also provides a computer readable storage medium storing a computer program which when executed by a processor implements a landing gear shock absorber airworthiness inducing design method as described above.
In the present specification, each embodiment is described in a progressive manner, and each embodiment is mainly described in a different point from other embodiments, and identical and similar parts between the embodiments are all enough to refer to each other.
The principles and embodiments of the present invention have been described herein with reference to specific examples, the description of which is intended only to assist in understanding the core concept of the invention; also, it is within the scope of the present invention to be modified by those of ordinary skill in the art in light of the present teachings. In view of the foregoing, this description should not be construed as limiting the invention.
Claims (8)
1. A landing gear shock absorber seaworthiness inducing design method, comprising:
determining the navigability requirement of the shock absorber;
calculating the external load of the shock absorber according to the navigable requirements and the preset operating environment working conditions, and determining the related data of the shock absorption mode; the vibration reduction mode related data comprise vibration reduction data and vibration reduction parts; the damping data comprises a damper design load spectrum, damper travel and efficiency, piston size, safety targets and allocations; the damping parts comprise strength, rigidity, durability, materials and processes;
constructing a three-dimensional solid model of the shock absorber according to the related data of the shock absorption mode; the three-dimensional physical model of the shock absorber comprises a shock absorber overall design model and a shock absorber part design model; the shock absorber three-dimensional entity model comprises an expansion layer and an application layer which are sequentially connected; the expansion layer is used for storing an identification index corresponding to the damping mode related data; the application layer is used for updating model configuration according to the identification index;
and carrying out seaworthiness verification according to the three-dimensional solid model of the shock absorber, and determining the seaworthiness standard of the shock absorber.
2. The landing gear shock absorber airworthiness induction design method of claim 1, wherein the determining the airworthiness requirements of the shock absorber specifically comprises:
and determining the airworthiness requirement according to the external load, performance and function of the shock absorber, system design requirements, part design requirements, process requirements and airworthiness verification test requirements.
3. The landing gear shock absorber airworthiness induction design method of claim 1, wherein the constructing a shock absorber three-dimensional solid model according to the shock absorption mode related data specifically includes:
constructing a general parameterized feature model of the shock absorber;
index identification is carried out on the damping mode related data, and an identification index corresponding to the damping mode related data is obtained;
and configuring the general parameterized feature model of the shock absorber according to the identification index corresponding to the related data of the shock absorption mode, and determining the three-dimensional entity model of the shock absorber.
4. A landing gear shock absorber airworthiness induction design method according to claim 3, wherein the constructing of the shock absorber generic parameterized feature model specifically comprises:
determining a composition architecture of the shock absorber; the composition framework comprises parts and corresponding constraint relations;
and constructing a general parameterized feature model of the shock absorber according to the composition framework.
5. The landing gear shock absorber airworthiness induction design method of claim 1, further comprising, after constructing a shock absorber three-dimensional solid model from the shock absorption manner related data:
and correlating and storing the construction flow corresponding to the shock absorber three-dimensional entity model to generate a shock absorber navigability design case.
6. A landing gear shock absorber seaworthiness inducing design system, comprising:
the airworthiness requirement determining module is used for determining the airworthiness requirement of the shock absorber;
the external load calculation module is used for calculating the external load of the shock absorber according to the navigable requirements and the preset operation environment working conditions, and determining relevant data of a shock absorption mode; the vibration reduction mode related data comprise vibration reduction data and vibration reduction parts; the damping data comprises a damper design load spectrum, damper travel and efficiency, piston size, safety targets and allocations; the damping parts comprise strength, rigidity, durability, materials and processes;
the shock absorber model construction module is used for constructing a shock absorber three-dimensional entity model according to the shock absorption mode related data; the three-dimensional physical model of the shock absorber comprises a shock absorber overall design model and a shock absorber part design model; the shock absorber three-dimensional entity model comprises an expansion layer and an application layer which are sequentially connected; the expansion layer is used for storing an identification index corresponding to the damping mode related data; the application layer is used for updating model configuration according to the identification index;
and the seaworthiness verification module is used for performing seaworthiness verification according to the shock absorber three-dimensional solid model and determining the seaworthiness standard of the shock absorber.
7. An electronic device comprising a memory for storing a computer program and a processor that runs the computer program to cause the electronic device to perform the landing gear shock absorber airworthiness inducing design method of claims 1-5.
8. A computer-readable storage medium, characterized in that it stores a computer program which, when executed by a processor, implements a landing gear shock absorber airworthiness inducing design method as claimed in claims 1-5.
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Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20110178725A1 (en) * | 2010-01-20 | 2011-07-21 | Airbus | Method of assisting decision-taking concerning the airworthiness of an aircraft |
| CN104200107A (en) * | 2014-09-09 | 2014-12-10 | 北京航空航天大学 | Airworthiness certification method for influences of different flying angles on stall/surge characteristics of aero-engine |
| CN106777579A (en) * | 2016-11-30 | 2017-05-31 | 中国直升机设计研究所 | A kind of helicopter fits the dynamic design approach of pendant seat |
-
2023
- 2023-03-30 CN CN202310327597.XA patent/CN116341116B/en active Active
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20110178725A1 (en) * | 2010-01-20 | 2011-07-21 | Airbus | Method of assisting decision-taking concerning the airworthiness of an aircraft |
| CN104200107A (en) * | 2014-09-09 | 2014-12-10 | 北京航空航天大学 | Airworthiness certification method for influences of different flying angles on stall/surge characteristics of aero-engine |
| CN106777579A (en) * | 2016-11-30 | 2017-05-31 | 中国直升机设计研究所 | A kind of helicopter fits the dynamic design approach of pendant seat |
Non-Patent Citations (4)
| Title |
|---|
| TUĞBA SARAÇ: "Certification Aspects of Model Based Development for Airborne Software", IEEE XPLORE * |
| 刘泽林 等: "基于模型的民机适航要求自动捕获方法", 科技导报, no. 07 * |
| 杨晓强 等: "基于系统理论过程分析的定检维修疲劳致因分析与控制", 科学技术与工程 * |
| 田宪伟 等: "材料信息在MBD数据集中的表达与集成应用研究", 航空制造技术 * |
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