CN113504064A - Online simulation driven aircraft structure thermodynamic combined test system and method - Google Patents
Online simulation driven aircraft structure thermodynamic combined test system and method Download PDFInfo
- Publication number
- CN113504064A CN113504064A CN202110777454.XA CN202110777454A CN113504064A CN 113504064 A CN113504064 A CN 113504064A CN 202110777454 A CN202110777454 A CN 202110777454A CN 113504064 A CN113504064 A CN 113504064A
- Authority
- CN
- China
- Prior art keywords
- module
- test
- control system
- loading
- thermal
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
Images
Classifications
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M99/00—Subject matter not provided for in other groups of this subclass
- G01M99/002—Thermal testing
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
- B64F5/60—Testing or inspecting aircraft components or systems
Landscapes
- Engineering & Computer Science (AREA)
- Manufacturing & Machinery (AREA)
- Transportation (AREA)
- Aviation & Aerospace Engineering (AREA)
- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Management, Administration, Business Operations System, And Electronic Commerce (AREA)
- Investigating Or Analyzing Materials Using Thermal Means (AREA)
Abstract
The invention provides an aircraft structure test system and method for online simulation driven thermal and force load combined loading, which can realize dynamic thermal and force load real-time prediction and loading depending on the structure state. The test system includes: the device comprises a thermal loading module, a force loading module, a data acquisition module, a high-performance calculation module and a test control system, wherein all the systems are connected with each other through bidirectional data. In the test method, a simulation model which runs on line in a high-performance computing module is adopted, the thermal and force response data of the structure in the actual loading process are combined, the future thermal and force loading load is predicted, and the load data is fed back to a thermal and force loading module through a test control system, so that dynamic loading is realized.
Description
Technical Field
The invention belongs to the technical field of testing devices, and particularly relates to an on-line simulation driven aircraft structure thermodynamic combined test system and method.
Background
High speed aircraft experience significant aerodynamic thermal and mechanical loads during flight. In order to verify the reliability of the structural design of the high-speed aircraft, the verification and the assessment of the heat resistance and the mechanical bearing performance of a key structure are required to be carried out under typical combined heat and force loads in the development of the aircraft. The thermal and force load loading curves adopted by the test are determined in advance according to the established flight mission and the flight trajectory. In the test, the response and the integrity of the structure are mainly observed, and the heat and force loading curves are kept unchanged.
Intelligent high-speed aircraft are an important trend in future development. Dynamic and autonomous flight path planning is one of the main characteristics of an intelligent aircraft. The flight path is driven by the autonomous situational awareness of the environment and structure and needs to be completed by the swinging of thermal structures such as control surfaces. In this process, the structure's motion couples with the surrounding flow field, determining the thermal and force loads to which it is subjected. With the change of the flight path, the aerodynamic heat and force load born by the structure of the intelligent aircraft also changes dynamically. Therefore, it is difficult to fully determine the thermal and force loads of the smart aircraft structure during the design phase of the aircraft. This presents significant difficulties in determining the thermal and force combined loading and assessment test curves for aircraft structures.
Therefore, in order to meet the requirement of the thermodynamic joint test assessment of the intelligent high-speed aircraft, it is important to develop a thermal and force joint loading test system and method capable of determining a loading curve in real time according to the state of a thermal structure in the test process.
Disclosure of Invention
The invention aims to solve the problem that the thermal/force check load cannot be determined in advance due to the autonomous mission planning of an intelligent high-speed aircraft, and provides an online simulation-driven aircraft structure thermodynamic combined test system and method.
In order to achieve the purpose, the technical scheme adopted by the invention is as follows:
an online simulation driven aircraft structure thermodynamic combined test system comprises a thermal loading module, a mechanical loading module, a data acquisition module, a high-performance calculation module and a test control system;
the thermal loading module, the mechanical loading module, the data acquisition module and the high-performance calculation module are all in bidirectional data connection with the test control system.
An aircraft structure thermodynamic combination test method driven by online simulation of the system comprises the following steps:
step 1: according to a specific test purpose, setting an online simulation model on the high-performance computing module;
step 2: installing a test piece, setting an initial loading curve by using a test control system, and loading the test piece by using a thermal loading module and a mechanical loading module;
and step 3: acquiring structural heat and force responses acquired by a sensor arranged on a test piece by using a data acquisition module, and acquiring actually loaded heat and mechanical loads by using a test control system;
and 4, step 4: transmitting the actual heat and force response of the test piece and the heat and force load actually loaded by the test control system to the high-performance computing module by adopting the test control system, and sending a starting computing instruction to the high-performance computing module;
and 5: the high-performance calculation module adopts the actually loaded heat and force load data in the step 4 to simulate the structure thermal coupling model and correct the parameters of the structure thermal coupling model;
step 6: determining a dynamic flight path by adopting a flight path planning model according to the calculation result of the structural thermodynamic coupling model in the step 5 and the actual structural deformation data in the step 4;
and 7: determining the thermal load and the force load at the future time t according to the flight path and the flight load calculation model in the step 6;
and 8: the high-performance computing module transmits the thermal and force load data of the future t time to the test control system;
and step 9: the test control system outputs loading instruction data to the thermal loading module and the mechanical loading module;
step 10: and the thermal loading module and the mechanical loading module complete thermal and force combined load loading according to a loading instruction of the test control system.
Compared with the prior art, the invention has the beneficial effects that: by integrating the heat/force loading module, the data acquisition module and the online simulation model, the future load is predicted by fusing the structural real-time response acquired data and the online simulation model, and a set of thermodynamic combined loading method and an examination and verification platform are provided for the intelligent high-speed aircraft to dynamically change the thermodynamic load based on the state and the autonomous planning flight path.
Drawings
FIG. 1 is a block diagram of a test system according to the present invention;
the system comprises a test piece 1, a thermal loading module 2, a mechanical loading module 3, a data loading module 4, a test control system 5, a high-performance computing module 6, data chains 7, 8, 9 and 10 and a sensor 11.
Detailed Description
The technical solutions of the present invention are further described below with reference to the drawings and the embodiments, but the present invention is not limited thereto, and modifications or equivalent substitutions may be made to the technical solutions of the present invention without departing from the spirit and scope of the technical solutions of the present invention.
The invention can realize the dynamic thermal and force load real-time prediction and loading depending on the structure state. The test system includes: the device comprises a thermal loading module, a force loading module, a data acquisition module, a high-performance calculation module and a test control system, wherein all the systems are connected with each other through bidirectional data. In the test method, a simulation model which runs on line in a high-performance computing module is adopted, the thermal and force response data of the structure in the actual loading process are combined, the future thermal and force loading load is predicted, and the load data is fed back to a thermal and force loading module through a test control system, so that dynamic loading is realized.
The first embodiment is as follows: the embodiment describes an online simulation driven aircraft structure thermodynamic combined test system, which comprises a thermal loading module 2, a mechanical loading module 3, a data acquisition module 4, a high-performance calculation module 6 and a test control system 5;
the thermal loading module 2, the mechanical loading module 3, the data acquisition module 4 and the high-performance calculation module 6 are all in bidirectional data connection with the test control system 5.
The second embodiment is as follows: in a first specific embodiment, the test control system 5 is composed of quartz lamp loading module control software, mechanical loading module control software, data acquisition instrument control software and high-performance computing cluster interface software which are run on a computer, and performs periodic test loading process control by taking specific time t0 as a unit.
The third concrete implementation mode: in a first specific embodiment of the system for testing the aircraft structure thermodynamic combination under the drive of online simulation, the high performance computing module 6 performs online computation on an online simulation model.
The fourth concrete implementation mode: in a third specific embodiment, the online simulation-driven aircraft structure thermodynamic combined test system includes an online calculation of a structure thermodynamic coupling analysis model under thermal and force loads, a flight path planning model, and a flight aerodynamic thermal and flight structure load calculation model.
The fifth concrete implementation mode: in a first specific embodiment of the online simulation-driven aircraft structure thermodynamic joint test system, the bidirectional data connection between the thermal loading module 2 and the test control system 5 means that the thermal loading module 2 transmits actual loading process data to the test control system 5, and the test control system 5 outputs loading power at a future time t to the thermal loading module 2.
The sixth specific implementation mode: in a specific embodiment of the online simulation-driven aircraft structure thermodynamic joint test system, the bidirectional data connection between the mechanical loading module 3 and the test control system 5 means that the mechanical loading module 3 transfers the loaded mechanical load to the test control system 5, and the test control system 5 sends the mechanical load at the future time t to the mechanical loading module 3.
The seventh embodiment: in a first specific embodiment, the two-way data connection between the data acquisition module 4 and the test control system 5 means that the data acquisition module 4 acquires structural heat and force response data acquired by the sensors 11 arranged on the loaded structure and transmits the structural heat and force response data to the test control system 5, and the test control system 5 sends an acquisition instruction to the data acquisition module 4, that is, an instruction for starting and stopping data acquisition.
The specific implementation mode is eight: in a first specific embodiment of the online simulation-driven aircraft structure thermodynamic joint test system, the high performance calculation module 6 is in bidirectional data connection with the test control system 5, which means that the high performance calculation module 6 transmits the thermal load and mechanical load data at the future time t, which are predicted by the flight structure load calculation model in the online simulation model, to the test control system 5, and the test control system 5 transmits the thermal response, force response and loading curve data in the actual loading of the test piece to the high performance calculation module 6.
The specific implementation method nine: an aircraft structure thermodynamic combination test method driven by online simulation of the system according to any one of the first to eighth embodiments, the method comprising the steps of:
step 1: according to a specific test purpose, an online simulation model is arranged on the high-performance computing module 6;
step 2: installing a test piece 1, setting an initial loading curve by using a test control system 5, and loading the test piece 1 by using a thermal loading module 2 and a mechanical loading module 3;
and step 3: the data acquisition module 4 is adopted to acquire structural heat and force responses acquired by a sensor 11 arranged on the test piece 1, and the test control system 5 is adopted to acquire actually loaded heat and mechanical loads;
and 4, step 4: the test control system 5 is adopted to transmit the actual heat and force responses of the test piece 1 and the heat and force loads actually loaded by the test control system to the high-performance computing module 6 and send a starting computing instruction to the high-performance computing module 6;
and 5: the high-performance calculation module 6 adopts the actually loaded heat and force load data in the step 4 to simulate the structure thermodynamic coupling model and correct the parameters of the structure thermodynamic coupling model;
step 6: determining a dynamic flight path by adopting a flight path planning model according to the calculation result of the structural thermodynamic coupling model in the step 5 and the actual structural deformation data in the step 4;
and 7: determining the thermal load and the force load at the future time t according to the flight path and the flight load calculation model in the step 6;
and 8: the high-performance calculation module 6 transmits the thermal and force load data of the future time t to the test control system 5;
and step 9: the test control system 5 outputs loading instruction data to the thermal loading module 2 and the mechanical loading module 3;
step 10: the thermal loading module 2 and the mechanical loading module 3 complete thermal and force combined load loading according to the loading instruction of the test control system 5.
The detailed implementation mode is ten: in a ninth specific embodiment, the method for the thermodynamic combination test of the aircraft structure driven by the online simulation, in the whole test period, with the time t as an increment step, executes the steps 3 to 10 in a circulating manner until the test is completed.
Example 1:
FIG. 1 is a schematic diagram of the composition of the test system of the present invention. As shown in FIG. 1, the online simulation-driven thermal-force combined loading test system disclosed by the invention is composed of a thermal loading module 2, a mechanical loading module 3, a data acquisition module 4, a high-performance calculation module 6 and a test control system 5, and is used for performing thermal-force combined test on a high-speed aircraft structure test piece 1.
The heat loading module 2 can be composed of one or more quartz lamp array heating modules.
The force loading module 3 can be composed of an electric cylinder or a hydraulic actuating rod.
The data acquisition module 4 can adopt a data acquisition instrument.
The high-performance computing module 6 may adopt a high-performance computing cluster with multiple computing nodes, and is configured to deploy a simulation model and perform online computing.
The simulation model comprises: structural thermodynamic coupling analysis models under thermal and force loads, such as calculation models for developing temperature, deformation and structural safety margins; a flight path planning model for actively planning a flight path, for example, based on a structural safety margin constraint, a task time minimum target constraint, a task reliability constraint and the like; computational models of aerodynamic heating, flight structure loading, for example, to compute overload of a structure. And based on the current deformation of the structure, carrying out computational fluid mechanics analysis and calculating the aerodynamic heat and aerodynamic force born by the structure.
The test control system 5 consists of quartz lamp loading module control software, mechanical loading module control software, data acquisition instrument control software and high-performance computing cluster interface software which run on a computer.
The quartz lamp heat loading module 2, the actuating rod mechanics loading module 3, the data acquisition module 4 and the high-performance calculation module 6 are all in bidirectional data connection with the test control system 5.
The bidirectional data connection between the quartz lamp heat loading module 2 and the test control system 5 means that the quartz lamp loading module 2 transmits actual loading process data, such as actually loaded heat flux density data of each partition, to the test control system 5, and the test control system outputs loading power data of the future time t to the heat loading module, such as a future actual target heat flux density of the time t.
The bidirectional data connection of the actuating rod mechanics loading module 3 and the test control system 5 means that the actuating rod mechanics loading module 3 transmits the loaded mechanics load, i.e. the actuating force and displacement of each actuating rod, to the test control system 5, and the test control system 5 transmits the mechanics load, i.e. the actuating force or displacement, of the future t time to the mechanics loading module 3.
The bidirectional data connection between the data acquisition module 4 and the test control system 5 means that the data acquisition module 4 acquires structural heat and force response data, such as temperature, deformation and the like, acquired by the sensor 11 and transmits the data to the test control system 5, and the test control system 5 sends an acquisition instruction, namely an instruction for starting and stopping data acquisition, to the data acquisition module 4.
The bidirectional data connection between the high-performance computing module 6 and the test control system 5 means that the high-performance computing module 6 transmits the thermal load and mechanical load data at the future t time given by the online model prediction to the test control system 5, and the test control system 5 transmits the thermal response, the force response and the loading curve data in the actual loading of the test piece to the high-performance computing module 6.
The online simulation driven aircraft structure thermodynamic combined test and method is an aircraft structure thermodynamic combined test system utilizing the online simulation driven aircraft structure thermodynamic combined test, and comprises the following steps:
step 1: according to a specific test purpose, deploying an online simulation calculation model on the high-performance calculation module 6;
step 2: installing a test piece 1, setting an initial loading curve by using a test control system 5, and loading the test piece 1 by using a thermal loading module 2 and a force loading module 3;
and step 3: acquiring a signal output by a sensor 11 by using a data acquisition module 4, acquiring actual thermal and force responses of a structural part 1, and acquiring actually loaded thermal and mechanical loads by using a test control system 5;
and 4, step 4: the test control system 5 is adopted to transmit the actual heat and response of the structural part and the heat and force load actually loaded by the test system to the high-performance computing module 6 and send a starting computing instruction to the high-performance computing module 6;
and 5: the high-performance calculation module 6 carries out simulation calculation on the structural thermodynamic coupling model, and corrects structural thermodynamic coupling model parameters such as material mechanical property parameters, thermophysical property parameters, constitutive model parameters and the like together with heat and force response data acquired by an actual structure;
step 6: determining a dynamic flight path by adopting a flight path planning model according to a structural thermodynamic coupling model calculation result, such as the bearing capacity of a structure;
and 7: determining thermal and force loads at the future time t according to flight path and flight load calculation models, such as an overload calculation model, an aerodynamic thermal calculation model and an aerodynamic calculation model;
and 8: the high-performance calculation module 6 transmits the thermal and force load data of the future time t to the test control system 5;
and step 9: the test control system 5 outputs loading instruction data including heat flux density and displacement or actuating force of each actuating rod to the heat loading module 2 and the force loading module 3;
step 10: and the thermal loading module 2 and the force loading module 3 complete thermal and force combined load loading according to a loading instruction of the test control system 5.
The simulation online driving heat and force combined loading test method is characterized in that the steps 3 to 10 are executed in a circulating mode by taking t time as an increment step in the whole test period until the test is finished.
Claims (10)
1. The utility model provides an online emulation driven aircraft structure heating power combined test system which characterized in that: the system comprises a thermal loading module (2), a mechanical loading module (3), a data acquisition module (4), a high-performance calculation module (6) and a test control system (5);
the thermal loading module (2), the mechanical loading module (3), the data acquisition module (4) and the high-performance calculation module (6) are all in bidirectional data connection with the test control system (5).
2. The on-line simulation driven aircraft structure thermodynamic combination test system according to claim 1, wherein: the test control system (5) consists of quartz lamp loading module control software, mechanical loading module control software, data acquisition instrument control software and high-performance computing cluster interface software which run on a computer, and performs periodic test loading process control by taking specific time t0 as a unit.
3. The on-line simulation driven aircraft structure thermodynamic combination test system according to claim 1, wherein: and the high-performance calculation module (6) is used for carrying out online calculation on the online simulation model.
4. The on-line simulation driven aircraft structure thermodynamic combination test system according to claim 3, wherein: the online simulation model comprises a structural thermodynamic coupling analysis model under thermal and force loads, a flight path planning model and a flight aerodynamic thermal and flight structural load calculation model which are calculated online.
5. The on-line simulation driven aircraft structure thermodynamic combination test system according to claim 1, wherein: the bidirectional data connection of the thermal loading module (2) and the test control system (5) means that the thermal loading module (2) transmits actual loading process data to the test control system (5), and the test control system (5) outputs loading power of the future t time to the thermal loading module (2).
6. The on-line simulation driven aircraft structure thermodynamic combination test system according to claim 1, wherein: the mechanical loading module (3) is in bidirectional data connection with the test control system (5), and the mechanical loading module (3) transmits the loaded mechanical load to the test control system (5), and the test control system (5) transmits the mechanical load at the future time t to the mechanical loading module (3).
7. The on-line simulation driven aircraft structure thermodynamic combination test system according to claim 1, wherein: the bidirectional data connection of the data acquisition module (4) and the test control system (5) means that the data acquisition module (4) acquires structural heat and force response data acquired by a sensor (11) arranged on a loaded structure and transmits the structural heat and force response data to the test control system (5), and the test control system (5) sends an acquisition instruction to the data acquisition module (4).
8. The on-line simulation driven aircraft structure thermodynamic combination test system according to claim 1, wherein: the high-performance computing module (6) is in bidirectional data connection with the test control system (5), and means that the high-performance computing module (6) transmits the thermal load and mechanical load data at the future time t, which are predicted by the flight structure load computing model in the online simulation model, to the test control system (5), and the test control system (5) transmits the thermal response, the force response and the loading curve data in the actual loading of the test piece to the high-performance computing module (6).
9. An aircraft structure thermodynamic combination test method driven by the system of any one of claims 1 to 8 through online simulation is characterized in that: the method comprises the following steps:
step 1: according to a specific test purpose, an online simulation model is arranged on the high-performance computing module (6);
step 2: installing a test piece (1), setting an initial loading curve by using a test control system (5), and loading the test piece (1) by using a thermal loading module (2) and a mechanical loading module (3);
and step 3: the method comprises the steps that a data acquisition module (4) is used for acquiring structural heat and force responses acquired by a sensor (11) arranged on a test piece (1), and a test control system (5) is used for acquiring actually loaded heat and mechanical loads;
and 4, step 4: adopting a test control system (5), transmitting the actual heat and force response of the test piece (1) and the heat and force load actually loaded by the test control system to a high-performance computing module (6), and sending a starting computing instruction to the high-performance computing module (6);
and 5: the high-performance calculation module (6) adopts the actually loaded heat and force load data in the step (4) to simulate the structural thermodynamic coupling model and correct the parameters of the structural thermodynamic coupling model;
step 6: determining a dynamic flight path by adopting a flight path planning model according to the calculation result of the structural thermodynamic coupling model in the step 5 and the actual structural deformation data in the step 4;
and 7: determining the thermal load and the force load at the future time t according to the flight path and the flight load calculation model in the step 6;
and 8: the high-performance computing module (6) transmits the heat and force load data of the future t time to the test control system (5);
and step 9: the test control system (5) outputs loading instruction data to the thermal loading module (2) and the mechanical loading module (3);
step 10: and the thermal loading module (2) and the mechanical loading module (3) complete thermal and force combined load loading according to the loading instruction of the test control system (5).
10. The method for the thermodynamic combination test of the on-line simulation driven aircraft structure according to claim 1, wherein the method comprises the following steps: and (5) circularly executing the steps 3 to 10 by taking the time t as an increment step in the whole test period until the test is finished.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110777454.XA CN113504064A (en) | 2021-07-09 | 2021-07-09 | Online simulation driven aircraft structure thermodynamic combined test system and method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110777454.XA CN113504064A (en) | 2021-07-09 | 2021-07-09 | Online simulation driven aircraft structure thermodynamic combined test system and method |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN113504064A true CN113504064A (en) | 2021-10-15 |
Family
ID=78011903
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202110777454.XA Pending CN113504064A (en) | 2021-07-09 | 2021-07-09 | Online simulation driven aircraft structure thermodynamic combined test system and method |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN113504064A (en) |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103364170A (en) * | 2013-07-05 | 2013-10-23 | 北京航空航天大学 | Ground simulation predicting method and system for aeroelasticity stability |
| CN103542997A (en) * | 2013-09-30 | 2014-01-29 | 中国人民解放军国防科学技术大学 | Method for dynamically testing rudder system on basis of high-enthalpy wind tunnel force/heat environment |
| CN105416609A (en) * | 2015-12-08 | 2016-03-23 | 中国飞机强度研究所 | Multi-field coupling testing system and method |
| CN108918582A (en) * | 2018-07-05 | 2018-11-30 | 北京强度环境研究所 | A kind of hot external pressure test system and method for aircraft cargo tank structure |
| CN109142085A (en) * | 2018-10-10 | 2019-01-04 | 哈尔滨工业大学 | A kind of thermal protection on-line analysis system and method based on dynamic data driving |
| CN109883660A (en) * | 2017-12-01 | 2019-06-14 | 中国飞机强度研究所 | A kind of thermal modeling test control method |
-
2021
- 2021-07-09 CN CN202110777454.XA patent/CN113504064A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103364170A (en) * | 2013-07-05 | 2013-10-23 | 北京航空航天大学 | Ground simulation predicting method and system for aeroelasticity stability |
| CN103542997A (en) * | 2013-09-30 | 2014-01-29 | 中国人民解放军国防科学技术大学 | Method for dynamically testing rudder system on basis of high-enthalpy wind tunnel force/heat environment |
| CN105416609A (en) * | 2015-12-08 | 2016-03-23 | 中国飞机强度研究所 | Multi-field coupling testing system and method |
| CN109883660A (en) * | 2017-12-01 | 2019-06-14 | 中国飞机强度研究所 | A kind of thermal modeling test control method |
| CN108918582A (en) * | 2018-07-05 | 2018-11-30 | 北京强度环境研究所 | A kind of hot external pressure test system and method for aircraft cargo tank structure |
| CN109142085A (en) * | 2018-10-10 | 2019-01-04 | 哈尔滨工业大学 | A kind of thermal protection on-line analysis system and method based on dynamic data driving |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN111737811B (en) | Helicopter movable part service life management method, device and medium based on digital twin | |
| CN102411313B (en) | Satellite flight control closed loop simulation system based on component simulator | |
| CN103970128A (en) | On-line real-time simulation testing system of wind generating set controller | |
| CN107462425B (en) | A kind of failure prediction method and failure predication platform of car kits system | |
| CN105260581A (en) | Method for virtual vibration and impact tests of electromechanical control equipment of ship | |
| CN110631792B (en) | Seismic hybrid test model updating method based on convolutional neural network | |
| CN103792851A (en) | Wireless ad hoc network-based cluster spacecraft semi-physical simulation system and method | |
| CN109917669A (en) | Device and method are verified in the satellite GNC system integration based on dSPACE real-time simulation machine | |
| KR20170121553A (en) | Flight control law simulation method and apparatus | |
| Roth et al. | Cyber-physical system development environment for energy applications | |
| CN104298823A (en) | Analysis method and system of high- and low-temperature balances | |
| CN113504064A (en) | Online simulation driven aircraft structure thermodynamic combined test system and method | |
| CN111443618B (en) | Multi-mode online real-time autonomous switching simulation system and method for GNC system | |
| Farhat et al. | Towards a dynamic data driven system for structural and material health monitoring | |
| CN111563324A (en) | Flight control system simulation method, flight control system simulation platform, flight control system simulation server and storage medium | |
| Wang et al. | Optimal sensor placement for digital twin based on mutual information and correlation with multi-fidelity data | |
| Nanjundaswamy et al. | Development and calibration of on-board-diagnostic strategies using a micro-HiL approach | |
| Kim et al. | Human-interactive hardware-in-the-loop simulation framework for cyber-physical systems | |
| CN111008118A (en) | Servo system energy consumption evaluation system and evaluation method | |
| CN113793527B (en) | Test verification system for urban traffic active control | |
| Timoshenko et al. | Modeling of thermal processes in transmitting complexes of radar monitoring stations | |
| Levinski et al. | OPERAND: An innovative multi-physics approach to individual aircraft tracking | |
| Sun et al. | Technology of structure damage monitoring based on multi-agent | |
| Chu et al. | A model based approach for digital testbed development supporting virtual experimentation of an unmanned surface vehicle | |
| Zinnecker et al. | A modular framework for modeling hardware elements in distributed engine control systems |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| RJ01 | Rejection of invention patent application after publication | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20211015 |