CN101986318A - Design method of concept prototype of flight control system - Google Patents
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Abstract
The invention discloses a design method of a concept prototype of a flight control system, which belongs to the technical field of design of the control systems. The method comprises the following steps: step 1) carrying out demand analysis, management and confirmation on the flight control system; step 2) carrying out system analysis and confirmation on the flight control system, and carrying out structural and functional division on the system; step 3) designing all member simulators of the flight control system; and step 4) carrying out system level design and simulation on the flight control system, and establishing the concept prototype of the flight control system. The seamless butt joint between Rhapsody software and Matlab software can be realized by utilizing the point-to-point way, and design data in the two types of software can be organically combined. Compared with the prior art, by adopting the method, the correctness of the design of the flight control system from a top layer can be ensured, and the design efficiency of the whole flight control system can be greatly improved.
Description
Technical field
The present invention relates to the Design of Flight Control method, be specifically related to a kind of flight control system notion model machine method for designing.
Background technology
Flight control system is the complex reaction formula system of a quasi-representative, tradition Design of Flight Control method is a kind of document driven design method, its exemplary shortcomings is that the designer can't move assessment to design proposal before the manufacturing of systems engineering physical prototyping, cause the ambiguity and the mistake that exist in the design proposal, and the cost that these ambiguities and mistake etc. were just found and revised when integrated to system's later stage is huge.
Design of digital be solve traditional documents driven design method deficiency one sharp sword.Its technical connotation is ambiguity and a mistake of eliminating design proposal and decision-making by the first tectonic system virtual prototype before the manufacturing of gongwu model machine and the mode of carrying out simulating, verifying, avoids later stage gongwu prototype design to occur repeatedly.The core of flight control system Design of digital is a structure flight control system virtual prototype.
Than fields such as mechanical systems, flight control system is a kind of multi-field complex reaction formula systems such as machinery, electronics, computing machine, control and software that relate to, and there are a lot of difficulties in its virtual Prototype.Lot of domestic and international research institution had all once carried out research and had attempted, studied a kind of Virtual Prototype Technique (" multidisciplinary virtual prototype collaborative modeling and emulation platform and gordian technique research thereof ") as people such as uncle Li of space flight Second Academy tigers based on single field realistic model, by structure before the manufacturing of gongwu model machine by the integrated virtual prototype of each single domain model and carry out simulating, verifying, eliminate ambiguity and mistake in the design proposal, avoid later stage gongwu prototype design to go wrong.This deficiency that exists in the traditional documents driven design method that solved to a certain extent based on the integrated virtual Prototype technology of single domain model.But still there is a great deficiency in this method itself, promptly this virtual Prototype level is lower, to designing the support that the stages such as early stage demand analysis, conceptual design and assessment can not provide, therefore cause early stage demand analysis, conceptual design and assessment to remain the document drive-type.
Summary of the invention
Technical matters to be solved by this invention is the deficiency at flight control system traditional documents driven design method and present virtual Prototype, a kind of digitalized design method of constructing the hierarchical virtual model machine is proposed, and be that the notion model machine designs and simulating, verifying to the upper strata virtual prototype, guarantee the correctness of flight control system in structure, function, performance and behavior, for lower floor's virtual prototype is that (realization model machine) provides data input and design standards.Realization is to the complete support of every work such as demand analysis before the manufacturing of flight control system gongwu model machine, conceptual design, engineering development.
The present invention is by the following technical solutions:
A kind of flight control system notion model machine method for designing may further comprise the steps:
The demand analysis of step 1, flight control system, management and affirmation;
The systematic analysis of step 2, flight control system and affirmation are carried out system architecture and function and are divided;
Step 3, each flight control system member simulator design;
Flight control system notion model machine is set up in the system level design of step 4, flight control system and emulation.
Wherein, step 1 comprises following each step:
Step 101, user's request is analyzed, decomposed and refines, obtain system requirements;
Step 102, set up related between association between the system requirements and system requirements and the user's request, obtain System Requirement Models;
Step 103, according to System Requirement Models, set up system's use-case model.
Step 2 comprises following each step:
Step 201, carry out system architecture and function according to system's use-case model and divide;
Step 202, constructing system can be carried out use-case model;
Step 203, merge each use-case model and obtain system's top layer model.
Step 3 comprises following each step:
The design of step 301, each sensor model;
Step 302, each steering wheel Model Design;
Step 303, aircraft dynamics Model Design;
Step 304, carry out the design of the design of flight control computer logical gate and control law part respectively, and with both in conjunction with as a whole flight control computer.
Step 4 comprises following each step:
Step 401, define system Core Feature are carried out the system architecture analysis;
The top layer model that obtains in step 402, the result who utilizes the framework analysis and the systematic analysis carries out the architecture design of system;
Step 403, carry out detailed architecture design can carry out the emulation of subsystem and total system different stage.
Compared to existing technology, flight control system virtual Prototype method of the present invention has the following advantages:
1,, can strengthen checking dynamics, thereby effectively guarantee the design objective of system flight control system by the function of each level simulating, verifying of virtual prototype.Virtual prototype at all levels carried out independent emulation and checking when the design philosophy of hierarchical virtual model machine both can have been carried out the flight control system virtual Prototype, can also carry out hardware in the system-level overall process in loop, full task, totally digitilized emulation and checking;
2, the design of notion model machine can guarantee the correctness of Design of Flight Control from top layer, can allow the deviser just carry out system-level analysis and design from the design beginning, locate errors as early as possible and eliminate mistake with the means of emulation and checking, avoid subsequent design repeatedly, improve design efficiency;
3, the design output data result of notion model machine is as the input data of lower floor's virtual prototype (promptly realizing model machine), for realizing that model machine provides the raw data material, simultaneously also for the design that realizes model machine by the divide into groups purpose of carrying out the collaborative design of branch group of the difference in field to reach, improve Design of Flight Control efficient.
Description of drawings
Accompanying drawing 1 is the hierarchy of flight control system described in the embodiment, and the upper strata is the flight control system virtual prototype, and lower floor is the flight control system physical prototyping; Wherein the virtual prototype layer is divided into the flight control system notion model machine described based on SysML and Simulink again, realizes model machine based on the integrated flight control system of each single domain model of flexible bus technology;
Accompanying drawing 2 be described in the embodiment based on the flight control system notion model machine design cycle of SysML, whole flow process is divided into demand analysis, systematic analysis, system design three phases from top to bottom; The arrow in each design phase left side is represented input and the output of this design phase; System model/the database of goods is designed in the leftmost side for saved system;
Accompanying drawing 3 is the demand analysis of flight control system described in embodiment process flow diagrams;
Accompanying drawing 4 is the systematic analysis of flight control system described in embodiment process flow diagrams;
Accompanying drawing 5 is the seamless link synoptic diagram between MATLAB described in the embodiment and the Rhapsody;
Accompanying drawing 6 is the system design of flight control system described in embodiment process flow diagrams.
Embodiment
Below in conjunction with accompanying drawing technical scheme of the present invention is elaborated:
Accompanying drawing 1 upper strata is the flight control system virtual prototype, and lower floor is the flight control system physical prototyping; Wherein the virtual prototype layer is divided into the flight control system notion model machine described based on SysML and Simulink again, realizes that based on the integrated flight control system of each single domain model of flexible bus technology model machine is two-layer.As can be seen from the figure, full design cycle virtual prototype has been erected the bridge block between design requirement/idea and the final physical model machine, thus between the two synchronous and consistent of assurance.
The notion model machine is the upper strata of complete period virtual prototype, corresponding to the systems engineering design phase.It casts aside domain restrictions, from the crosslinked equal angles modeling of system architecture, function, behavior and data system to be designed, is a kind of PIM model therefore.Notion model machine in the technical program adopts SysML and Simulink to describe with object-oriented way.Wherein the former represents the crosslinked and discrete state behavior of architecture, data of system, the continuous dynamic behaviour in latter's descriptive system.Can carry out the collaborative simulation of notion model machine after the design of notion model machine is finished, whether the crosslinked relation of structure, function, performance, behavior and data of checking flight control system satisfies the demands.
Realizing model machine based on the notion model machine, from characteristics such as the structure that realizes the angle expression system, functions, is a kind of PSM model, and its each form that existence dynamically associates relation between the piece of module and notion model machine.The OO modeling mechanism of notion model machine provides good support for this corresponding relation clearly.Each subsystem module of accompanying drawing 1 demonstration notion model machine layer all can be worked in coordination with realization by the fields such as electronics, machinery, hydraulic pressure and software of realizing model machine; On the other hand, it is integrated to pass through the flexible bus mode between the domain model (module) of realization model machine, forms the realization model machine of flight control system jointly.Realizing that the model machine design can the system-level collaborative simulation that carries out whole flight control system virtual prototype after finishing, the a certain parts that also real physical unit can be replaced virtual prototype, carry out the collaborative simulation of hardware in the loop, whether corresponding one by one with the checking virtual prototype with real physical prototyping.
In this embodiment, the demand management of flight control system is the demand management of carrying out user's request in DOORS software; The demand of utilizing Gateway to be done in DOORS software imports to carries out demand analysis in the Rhapsody software, obtain System Requirement Models, and the use-case model of modelling system according to demand.
Described each flight control system member simulator design, be to utilize SYSML that each parts of flight control system and the coupled relation between them are analyzed and developed, and under Simulink and Rhapsody software environment, carry out the design of each several part respectively, be specially: in Simulink, carry out each Design of Sensor; In Simulink, carry out the design of each steering wheel; In Simulink, carry out the aircraft dynamics Model Design; Carry out the design of flight control computer logical gate in Rhapsody, carry out the design of control law part in Simulink, both are in conjunction with as a whole flight control computer.
The system level design of described flight control system and emulation are the piece definition figure, the home block figure that provide based on SysML in Rhapsody software, constitutional diagram etc., in conjunction with the Simulink module in the Matlab software flight control system is carried out Design ﹠ Analysis of System, set up and describe flight control system notion model machine from structure, function, behavior and performance equal angles; Wherein the definition of the piece among the SysML figure, home block figure etc. describe notion model machine static structure; The dynamic behaviour of notion model machine is described in constitutional diagrams etc.
As shown in Figure 2, the inventive method comprises:
The demand analysis of step 1, flight control system, management and affirmation; As shown in Figure 3, be specially: the input data of this step come from user's request (relating to many demands) knowledge base; Output data is the demand that flight control system is confirmed, one of imports as the systematic analysis of flight control system system.At first, refine, analyze and decompose, obtain system requirements relating to many demands, set up simultaneously relate between many demands, system requirements and relate between many demands, relate to the incidence relation between many demands, obtain System Requirement Models; Then, based on system requirements guiding system use-case and participant, the system's of foundation illustration, and set up related between functional system demand and the use-case, obtain system's use-case model.The output of demand analysis stage is System Requirement Models and system's use-case model.Wherein the demand management of flight control system is the demand management of carrying out user's request in DOORS software, the demand of utilizing Gateway to be done in DOORS software imports to carries out demand analysis in the Rhapsody software, obtain System Requirement Models, and the use-case model of modelling system according to demand.
The systematic analysis of step 2, flight control system and affirmation are carried out system architecture and function and are divided; As shown in Figure 4, be specially: the input data of this step come from the flight control system demand that the demand analysis of flight control system is confirmed; Output data is the top layer model of flight control system, as one of each flight control system member simulator design input of flight control system.At first, but set up use-case execution model (black box) one by one at each use-case in system's use-case model, comprising mutual scene precedence diagram between the activity diagram of describing use-case and participant behavior, constitutional diagram and description use-case (representative system) and the participant.Can be to carrying out detailed design alternately between participant and the system by three kinds of behavior figure, and by the simulation analysis checking case behind system requirements and relate to many demands.In the process of adding behavior figure, be that use-case and participant add essential attribute, operation, event/reception to, characteristics such as Port, Interface and various associations, obtain black box thus and can carry out use-case model according to behavior description needs and non-functional system requirements.Then, but the use-case execution model that a last sub is set up carries out consistency check, guarantee in each different use-cases description unanimity to the same system characteristic, the characteristic that can merge each use-case after finishing through consistency check obtains the complete characteristic that complex control system should possess, i.e. system's top layer model.To set up related between each system performance and the system requirements (comprising functional and non-functional) simultaneously, and guarantee that each characteristic and system requirements all are capped.The output in systematic analysis stage is executable system use-case model (black box) and system's top layer model.
Step 3, each flight control system member simulator design; This step is specially: the discrete portions of sensor and flight-control computer (being logical gate) all utilizes the SysML language to design in Rhapsody software, and the design of the continuous part of flight-control computer (being the control law part), vehicle dynamics model and steering wheel group all utilizes Simulink to design in Matlab software; Utilize the seamless link mechanism between Rhapsody software and the Matlab/Simulink software, piece definition figure, home block figure, the constitutional diagram that provides with SysML in Rhapsody software waits the discrete portions (being logical gate) that designs flight-control computer, is combined in the complete flight control computer model of the common formation of Flight Control Law part that designs among the Simulink.
In order to realize the seamless link between Rhapsody software and the Matlab software, the present invention adopts point-to-point mode, to utilize the designed flight control system each several part of SysML language and Simulink to couple together, carry out system-level collaborative simulation, from function, performance and behavior three aspects checking flight control system notion model machine.Concrete seamless connecting method as shown in Figure 5.It is the Software tool of real-time or non real-time program that MATLAB provides the Simulink model conversation: Real-time Workshop(RTW), it is based on the code Core Generator of Simulink, can be the C language codes or the C++ code of standard with the Simulink model conversation, the model running framework that the system of adding provides, they constitute a complete C/C++ language program.These program codes can break away from MATLAB environment independent operating after compiling connects the generation executable file.Steering wheel model that will design in Simulink and vehicle dynamics model utilize RTW to generate executable code, and these two kinds of models are encapsulated, and the model after the encapsulation utilizes flowport to carry out exchanges data.In Rhapsody software, utilize expansion profile mechanism, will be in the Simulink packaged model and the code of generation import the point-to-point seamless link of promptly finishing among the Rhapsody between Matlab and the Rhapsody simultaneously, both satisfied all models of being set up are all in the Rhapsody software environment, and integrated complete flight control computer lays the first stone for the system-level collaborative simulation of realizing flight control system again.
Flight control system notion model machine is set up in the system level design of step 4, flight control system and emulation; The input data of this step come from the output of each flight control system member simulator design; Output data is the model of notion model machine, promptly realizes the input data of model machine as flight control system virtual prototype lower floor.This design phase can be divided into two subs.First sub is system architecture analysis and architecture design.This stage is all system operations in the analytic system top layer model at first, and it is carried out grouping and classifying obtain some groups of critical system functions, and the principle of grouping is that all operations in this group can provide (realization) by same physical unit; Then, determine each critical system function structure one by one, obtain the system architecture of subsystem irrespective of size based on the WOM method; At last, system performance (comprising attribute, operation, event/reception) is distributed to each subsystem.The distribution of system performance can manually also can be carried out use-case model based on white box and carry out.It is can be carried out by black box to obtain after activity diagram in the use-case model and precedence diagram decompose that white box can be carried out use-case model.The former is meant and the activity diagram of use-case (representative system) is decomposed into some swimming lanes (Swimlane) according to system architecture and the activity of activity diagram is assigned in each swimming lane, the event/reception during the latter is meant the use-case in the precedence diagram is decomposed into the plurality of sub system and redistributes in the former precedence diagram according to system architecture to and operation.The decomposition of system architecture level can be carried out according to actual needs, and the minimum unit rank in framework satisfies model machine design needs.The second sub work is the detailed structure design.At first be set up between each level subsystem, port, interface and flowport between subsystem and the system, realize instruction stream and description of data stream between the subsystem; Secondly, add behavior figure for subsystem (unit) module.The output of system design is that white box can be carried out use-case model, system architecture analytical model and system concept model.Wherein the system concept model is the system concept model machine.Piece definition figure, the home block figure that in Rhapsody software, provides, constitutional diagram etc. based on SysML, in conjunction with the Simulink module in the Matlab software flight control system is carried out system design, foundation is described flight control system notion model machine from structure, function, behavior and performance equal angles, wherein notion model machine discrete state partly utilizes piece definition figure, home block figure etc. among the SysML to describe its static structure, utilizes precedence diagram, constitutional diagram etc. to describe its dynamic behaviour; Notion model machine continuous part then is described in Simulink.The whole process of this step as shown in Figure 6.
Claims (7)
1. a flight control system notion model machine method for designing is characterized in that, may further comprise the steps:
The demand analysis of step 1, flight control system, management and affirmation;
The systematic analysis of step 2, flight control system and affirmation are carried out system architecture and function and are divided;
Step 3, each flight control system member simulator design;
Flight control system notion model machine is set up in the system level design of step 4, flight control system and emulation.
2. flight control system notion model machine method for designing according to claim 1 is characterized in that described step 1 comprises following each step:
Step 101, user's request is analyzed, decomposed and refines, obtain system requirements;
Step 102, set up related between association between the system requirements and system requirements and the user's request, obtain System Requirement Models;
Step 103, according to System Requirement Models, set up system's use-case model.
3. flight control system notion model machine method for designing according to claim 1 is characterized in that described step 2 comprises
Below each step:
Step 201, carry out system architecture and function according to system's use-case model and divide;
Step 202, constructing system can be carried out use-case model;
Step 203, merge each use-case model and obtain system's top layer model.
4. flight control system notion model machine method for designing according to claim 1 is characterized in that described step 3 comprises following each step:
The design of step 301, each sensor model;
Step 302, each steering wheel Model Design;
Step 303, aircraft dynamics Model Design;
Step 304, carry out the design of the design of flight control computer logical gate and control law part respectively, and with both in conjunction with as a whole flight control computer.
5. as flight control system notion model machine method for designing as described in the claim 4, it is characterized in that, step 3 is to utilize SYSML that each parts of flight control system and the coupled relation between them are analyzed and developed, and carries out the design of each several part respectively under Simulink and Rhapsody software environment.
6. flight control system notion model machine method for designing according to claim 1 is characterized in that described step 4 comprises following each step:
Step 401, define system Core Feature are carried out the system architecture analysis;
The top layer model that obtains in step 402, the result who utilizes the framework analysis and the systematic analysis carries out the architecture design of system;
Step 403, carry out detailed architecture design can carry out the emulation of subsystem and total system different stage.
7. as capable control system notion model machine method for designing as described in the claim 6, it is characterized in that, described step 4 is the piece definition figure, the home block figure that provide based on SysML in Rhapsody software, constitutional diagram etc., in conjunction with the Simulink module in the Matlab software flight control system is carried out Design ﹠ Analysis of System, set up and describe flight control system notion model machine from structure, function, behavior and performance equal angles; Wherein notion model machine discrete state partly utilizes piece definition figure, home block figure etc. among the SysML to describe its static structure, utilizes precedence diagram, constitutional diagram etc. to describe its dynamic behaviour; Notion model machine continuous part then is described in Simulink.
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Citations (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101750978A (en) * | 2009-10-23 | 2010-06-23 | 北京航空航天大学 | Open platform for supporting design, verification and validation of telex flight control system |
-
2010
- 2010-11-26 CN CN 201010560848 patent/CN101986318A/en active Pending
Patent Citations (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101750978A (en) * | 2009-10-23 | 2010-06-23 | 北京航空航天大学 | Open platform for supporting design, verification and validation of telex flight control system |
Non-Patent Citations (2)
| Title |
|---|
| 《应用科学学报》 20091130 何火军等 无人机飞行控制系统虚拟样机平台 第637-643页 1-7 第27卷, 第6期 2 * |
| 《系统仿真学报》 20090731 刘兴华等 模型驱动的复杂反应式系统顶层设计与验证 第4284-4287页 1-7 第21卷, 第14期 2 * |
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| CN102253877A (en) * | 2011-06-29 | 2011-11-23 | 南京航空航天大学 | Airborne system digital design verification system and method |
| CN103294843A (en) * | 2012-03-01 | 2013-09-11 | 波音公司 | System and method for structural analysis |
| US11030362B2 (en) | 2012-06-25 | 2021-06-08 | International Business Machines Corporation | Modeling and cooperative simulation of systems with interdependent discrete and continuous elements |
| US11023627B2 (en) | 2012-06-25 | 2021-06-01 | International Business Machines Corporation | Modeling and cooperative simulation of systems with interdependent discrete and continuous elements |
| CN103886116A (en) * | 2012-12-20 | 2014-06-25 | 北汽福田汽车股份有限公司 | Calculation analysis system and method for vehicle gear shifting system |
| CN103886116B (en) * | 2012-12-20 | 2017-02-15 | 北汽福田汽车股份有限公司 | Calculation analysis system and method for vehicle gear shifting system |
| CN105960652A (en) * | 2013-11-26 | 2016-09-21 | 德国汉莎航空公司 | Method and system for designing aircraft |
| CN105960652B (en) * | 2013-11-26 | 2022-09-20 | 德国汉莎航空公司 | Method and system for designing an aircraft |
| CN103699739A (en) * | 2013-12-20 | 2014-04-02 | 北京宇航系统工程研究所 | Automatic designing and generating system for carrier rocket flight time sequence |
| CN103699739B (en) * | 2013-12-20 | 2016-06-01 | 北京宇航系统工程研究所 | A kind of carrier rocket flight time sequence designs and generation system automatically |
| CN104461882B (en) * | 2014-11-29 | 2017-05-17 | 中国航空工业集团公司第六三一研究所 | Method for model verification of software conforming to DO-178B/C A level |
| CN104461882A (en) * | 2014-11-29 | 2015-03-25 | 中国航空工业集团公司第六三一研究所 | Method for model verification of software conforming to DO-178B/C A level |
| CN105787141A (en) * | 2014-12-25 | 2016-07-20 | 北京仿真中心 | Collaborative simulation method and system for complex weapon system operation process |
| CN105787141B (en) * | 2014-12-25 | 2018-08-24 | 北京仿真中心 | A kind of synergy emulation method and system of Complex Weapon System Campaign Process |
| CN104915507A (en) * | 2015-06-19 | 2015-09-16 | 中国航空无线电电子研究所 | Interlinked simulation verification method based on model dynamic condition |
| CN105528476A (en) * | 2015-11-30 | 2016-04-27 | 上海电机学院 | Digital design method of flight control system |
| CN106599416A (en) * | 2016-11-30 | 2017-04-26 | 中国直升机设计研究所 | Man-machine work efficiency evaluation and optimization design method |
| CN106970795A (en) * | 2017-03-29 | 2017-07-21 | 北京润科通用技术有限公司 | A kind of information interacting method and system |
| CN107193559A (en) * | 2017-05-15 | 2017-09-22 | 上海电机学院 | A kind of complication system virtual Prototype method based on meta-model |
| CN107290978A (en) * | 2017-06-16 | 2017-10-24 | 南京航空航天大学 | A kind of helicopter flight simulation method and system |
| CN107657855A (en) * | 2017-09-04 | 2018-02-02 | 中国航空无线电电子研究所 | Integrated navigation monitoring stimulating and training system based on model |
| CN108974389A (en) * | 2018-07-16 | 2018-12-11 | 上海交通大学 | The intelligent cockpit network system realization authorized for Ci vil Aircraft Design and seaworthiness |
| CN110674588A (en) * | 2019-09-30 | 2020-01-10 | 北京航空航天大学 | MBSE-based modeling simulation method for on-missile electrical system |
| CN111191325A (en) * | 2019-12-24 | 2020-05-22 | 中国航空工业集团公司西安飞机设计研究所 | Aircraft direct flight preparation modeling method based on SysML |
| CN111176614B (en) * | 2019-12-26 | 2021-06-29 | 南京航空航天大学 | Method for generating and analyzing VRM formalized demand model |
| CN111176614A (en) * | 2019-12-26 | 2020-05-19 | 南京航空航天大学 | Method for generating and analyzing VRM formalized demand model |
| CN111596915A (en) * | 2020-05-19 | 2020-08-28 | 西安电子科技大学 | C + + code generation method of unmanned aerial vehicle flight mode based on state machine diagram |
| CN111596915B (en) * | 2020-05-19 | 2022-12-02 | 西安电子科技大学 | C + + code generation method of unmanned aerial vehicle flight mode based on state machine diagram |
| CN111930345A (en) * | 2020-07-06 | 2020-11-13 | 西安电子科技大学 | Unmanned aerial vehicle system modeling method and device based on SysML and readable storage medium |
| CN111930345B (en) * | 2020-07-06 | 2021-10-12 | 西安电子科技大学 | Unmanned aerial vehicle system modeling method and device based on SysML and readable storage medium |
| CN112347649A (en) * | 2020-11-06 | 2021-02-09 | 上海航天控制技术研究所 | Flight control system digital simulation method based on multidisciplinary combination |
| CN113050451A (en) * | 2021-03-24 | 2021-06-29 | 北京航空航天大学 | Modeling method and device of flight control system |
| CN112800124A (en) * | 2021-04-15 | 2021-05-14 | 成都赢瑞科技有限公司 | Computer aided design model integration system and method based on interface control file |
| CN112800124B (en) * | 2021-04-15 | 2021-09-10 | 成都赢瑞科技有限公司 | Computer aided design model integration system and method based on interface control file |
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