CN105740525A - Aerodynamic data processing method and aerodynamic data processing system for aircraft - Google Patents
Aerodynamic data processing method and aerodynamic data processing system for aircraft Download PDFInfo
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Abstract
The invention discloses an aerodynamic data processing method for an aircraft. The method comprises the following steps: S1, performing classification according to control surfaces, establishing hierarchical relationship names for aerodynamic data of each control surface according to the height, a Mach number, a yaw angle and a rudder deviation, and establishing a data object by using an object-oriented thought; S2, reading original aerodynamic data through an original aerodynamic data reading module, establishing a data structure body, and performing primary analysis on original data through an aerodynamic primary analysis module; S3, according to data processing process and method, establishing a process-oriented data computing process; and S4, generating a universal database through an aerodynamic data processing system for the aircraft. The invention furthermore provides the aerodynamic data processing system used for implementing the aerodynamic data processing method. The method and system have the beneficial effects that the post-processing burden is reduced, the error rate is low, the computing process work can be reused in data processing of different stages, and lots of working time is saved.
Description
Technical field
The present invention relates to wind-tunnel technique field, the aerodynamic data processing method and the aerodynamic data that are specifically related to a kind of aircraft process system.
Background technology
Wind tunnel test is to obtain the aerodynamic performance of aircraft and aerodynamic loading data.Aerodynamic loading data need, through processing, just to can be used for the analysis of aerodynamic characteristic, and be supplied to performance/behaviour steady/fly the professional uses such as control.Aerodynamic data amount is huge and numerous and diverse, thus Data Post process be one uninteresting, repeat, the process of labor intensive, for this we need a kind of can the technology of fast automatic post processing wind tunnel test data, to processing large batch of aerodynamic data fast and accurately.
Summary of the invention
It is an object of the invention to provide the aerodynamic data processing method of a kind of aircraft and aerodynamic data processes system, to process large batch of aerodynamic data fast and accurately.
The technical solution used in the present invention is: provide the aerodynamic data processing method of a kind of aircraft, comprise the steps of S1, classify according to rudder face, the aerodynamic data of each rudder face is set up hierarchical relationship name partially according to height, Mach number, yaw angle, rudder, use OO thought, set up data object；S2, reads in module by aerodynamic force initial data and reads original aerodynamic data, set up data structure body, and by aerodynamic force preliminary analysis module, initial data is carried out preliminary analysis；S3, according to flow chart of data processing and method, sets up processor-oriented data calculation process；S4, processes system by the aerodynamic data of aircraft and generates unitized data storehouse.
Preferably, OO processing method in described step S1 is not specifically, differentiate between concrete rudder partially or configuration, and all of rudder is partially or the input that is just as of the data of configuration and object output.
Preferably, initial data is carried out preliminary analysis by described step S2 specifically, reject noise, the preliminary effectiveness confirmed for the data calculated.
Preferably, described initial data is carried out preliminary analysis also comprise the train number data that completion is default.
Preferably, described step S3 uses the thought analysis of bivector traction, particularly as follows: S31, be derived by known data according to available data；S32, data derive the data that the need of needs are known according to demand；S33, can obtain, in primary data, the data that need to know；S34, sets up, according to front 3 steps, flow process and the method that data process.
Preferably, described flow chart of data processing and method, particularly as follows: the key word of Criterion is corresponding with key word in a program calculating function, are expressed by processor-oriented data calculation process in described step S3 by key word, set up and calculate input file.
Preferably, in described step S4, the generation of data base adopts unitized data management, to be configured as node, sets up unitized data storehouse by aircraft type.
Preferably, in described step S4, unitized data call tool storage room refers to the function library set up by the method for forward retrieval, reverse interpolation；It is specially, " forward retrieval " is according to input variable order, two values that forward retrieval first order input variable is nearest in corresponding Variables Sequence, then retrieves two fingers nearest from current layer variable in the next stage Variables Sequence that the two value is corresponding, the like, until last layer；" reverse interpolation " refers to the result according to " forward retrieval ", starts interpolation from afterbody, and interpolation goes out the result of last layer, goes out the result at last layer with the result interpolation of output, until the last result needed.
Present invention also offers the aerodynamic data of a kind of aircraft and process system, it is characterised in that: comprise aerodynamic force initial data and read in module, for reading in the initial data of wind tunnel test unit output；Aerodynamic force preliminary analysis module, for checking and the initial data of wind tunnel test described in graphic software platform；Aerodynamic data processes design module, for design input processing computing formula；Aerodynamic data computing module, calculates according to the process computing formula of the initial data read in and design input, and stores the result in data base；Aerodynamic force labor module, calls the data in data base, result of the test is analysed in depth；Aerodynamic force calling module, for the demand of different majors, designs different calculating instruments, for each specialty；Interface module, for being packaged with upper module, it is provided that interface, it is simple to staff uses.
Preferably, described aerodynamic force labor module analysing in depth specifically, the aerodynamic force curve drawn under various configuration result of the test, detailed comparisons analyzes the aerodynamic data under various configuration, lift curve, resistance curve and polar.
The beneficial effects of the present invention is: the process of existing wind tunnel test data adopts scattered small routine, each is processed respectively from data block, then splices, expend energy, error rate is high.And the present invention can independently, efficiently, be rapidly performed by data and process, alleviate the burden of post processing, and error rate be low, simultaneously, set up calculation process be operated in different phase Data processing can multiplexing, save a lot of working times, it is to avoid error that different disposal method is brought introduces.
Accompanying drawing explanation
Fig. 1 is the flow chart of the aerodynamic data processing method of a kind of aircraft of the present invention.
Fig. 2 is the unitized data structure schematic diagram of the aerodynamic data processing method of a kind of aircraft of the present invention.
Fig. 3 is the rudder face aerodynamic data prototype structure schematic diagram of the aerodynamic data processing method of a kind of aircraft of the present invention.
Fig. 4 is the output data calculation expression of the aerodynamic data processing method of a kind of aircraft of the present invention.
Fig. 5 is the lift coefficient calculation expression formula of the aerodynamic data processing method of a kind of aircraft of the present invention.
Fig. 6 is " forward retrieval " example of the aerodynamic data processing method of a kind of aircraft of the present invention.
Fig. 7 is " reverse interpolation " example of the aerodynamic data processing method of a kind of aircraft of the present invention.
Fig. 8 is the Operate process chart of the aerodynamic data processing method of a kind of aircraft of the present invention.
Detailed description of the invention
For making purpose of the invention process, technical scheme and advantage clearly, below in conjunction with the accompanying drawing in the embodiment of the present invention, the technical scheme in the embodiment of the present invention is further described in more detail.In the accompanying drawings, same or similar label represents same or similar element or has the element of same or like function from start to finish.Described embodiment is a part of embodiment of the present invention, rather than whole embodiments.The embodiment described below with reference to accompanying drawing is illustrative of, it is intended to is used for explaining the present invention, and is not considered as limiting the invention.Based on the embodiment in the present invention, the every other embodiment that those of ordinary skill in the art obtain under not making creative work premise, broadly fall into the scope of protection of the invention.Below in conjunction with accompanying drawing, embodiments of the invention are described in detail.
In describing the invention; it will be appreciated that; term " orientation or the position relationship of the instruction such as " center ", " longitudinal direction ", " transverse direction ", "front", "rear", "left", "right", " vertically ", " level ", " top ", " end " " interior ", " outward " be based on orientation shown in the drawings or position relationship; be for only for ease of the description present invention and simplifying and describe; rather than instruction or imply indication device or element must have specific orientation, with specific azimuth configuration and operation, therefore it is not intended that limiting the scope of the invention.
Configuration described in the present embodiment refers to the principal character of aircraft geometric shape and the general name of the various loading arrangement of aircraft.Generally distinguish aircraft configuration and be primarily referred to as according to the profile of parts, quantity and relative position: the number of empennage and the relative position with wing, fuselage thereof；The flat shape of wing and the installation site on fuselage thereof；Electromotor (air intake duct) number and installation site；The pattern of undercarriage and its stored position.
As shown in Figures 1 to 8, the aerodynamic data processing method of a kind of aircraft, comprise the steps of S1, classify according to rudder face, the aerodynamic data of each rudder face is set up hierarchical relationship name partially according to height, Mach number, yaw angle, rudder, uses OO thought, set up data object.
Wind tunnel test side provides wind tunnel test data (such as Fig. 2) according to the form of software requirement, then use aerodynamic data to read in module and read in initial data, generate the data structure of level, set up the back end of various configuration, use OO thought, set up the generalization aerodynamic data storehouse (such as Fig. 3) of initial data.
S2, reads in module by aerodynamic force initial data and reads original aerodynamic data, set up data structure body, and by aerodynamic force preliminary analysis module, initial data is carried out preliminary analysis.
Initial data is carried out preliminary analysis, use preliminary analysis module, display primary aerodynamic data, data under relative analysis different conditions, processing mode: 1) and completion train number (as: yaw angle test test data only has positive yaw angle data, negative yaw angle requires over mirror image operation and obtains, example: (yaw angle is 5 °, the angle of attack is aerodynamic data when 0 ° is [0.20.020.002-0.002-0.0020.002]), yaw angle can be obtained and be-5 °, when the angle of attack is 0 °, aerodynamic data is [0.20.020.0020.0020.002-0.002])；2) the part angle of attack interpolation arithmetic (as: for the test of control surface deflection, angle of attack sequence is thinner, it is necessary to encrypted by interpolation).After preliminary analysis, form new wind tunnel test data base.
S3, according to flow chart of data processing and method, sets up processor-oriented data calculation process.
Use the thought of " bivector traction ", set up data and process chain, and with using the Feature Words of definition in software, define data processing method.First, according to original aerodynamic data, decomposite the fundamental quantity under various configuration, increment, correction factor, and express (forward traction) with key word.Then, the calculation expression mode (Fig. 4) according to output data, use key word to express (reversely traction).Finally expression of results xml document is write out.
S4, processes system by the aerodynamic data of aircraft and generates unitized data storehouse, for each specialty, and provides corresponding data call tool storage room.
Use aerodynamic data to process design module and read in xml document, call aerodynamic data computing module, aerodynamic data handling process according to xml input, calculate aerodynamic data (the calculation process citing: in Fig. 5 of required output, calculate the increment dElevator of elevator deflection, operate='-' in operator Operta (1), variable name aeroName=' j_Elevator ', path source=' path/j_Elevator ', operate='-' in operator Operta (2), variable name aeroName=' d_Elevator ', path source=' path/d_Elevator '.In actual operation, program can be automatically obtained d_Elevator and deduct the data of j_Elevator, and difference is exactly dElevator), and set up unitized result output database.
Data labor method.Call data base's labor module, it is possible to drawing the aerodynamic force curve under various configuration, detailed comparisons analyzes the aerodynamic data under various configuration, lift curve, resistance curve and polar.
Data structure using method.In aerodynamic force calling module, provide the user aerodynamics evaluation instrument, user can obtain the aerodynamic parameter of a certain state point.(Fig. 5,6) is calculated by " forward retrieval, reverse interpolation " method." forward retrieval ": according to variable hierarchical relationship, from top to bottom, retrieve step by step.Assume the pneumatic efficiency (speed Ma, aileron movement deflection, yaw angle beta, the lift coefficient that the different angles of attack are corresponding) needing to calculate aileron.1 > retrieval Ma sequence, first finds Ma1 and Ma2, Ma1 less than Ma, Ma2 more than Ma；2 > aileron movement deflection corresponding under rope Ma1 and Ma2, retrieves deflection1, deflection2, deflection3 and deflection4；3 > the like, until last layer." reversely retrieval ": according to variable hierarchical relationship, from the bottom to top, interpolation step by step.Equally for the aerodynamic force efficiency of aileron.1 > first interpolation goes out different aerodynamic data corresponding for beta；2 > go out aerodynamic data corresponding to deflection1 according to beta1, beta2 interpolation, go out aerodynamic data corresponding to deflection2 according to beta3, beta4 interpolation ...；3 > data corresponding to Ma1 are gone out according to deflection1, deflection2 interpolation ...；4 > the like, until interpolation goes out required aerodynamic data.
Interface module.The mainly encapsulation to function above, it is simple to those familiar is not as programming and uses.
In the present embodiment, in described step S1, OO processing method is specially, for certain aircraft type, the result of wind tunnel test data be about configuration, highly, the inclined data splitting of Ma, yaw angle, the angle of attack, rudder, output data are lift, resistance, side force, pitching moment, yawing, rolling moment, thus, data can be set up and process object, and do not differentiate between concrete rudder partially or configuration, so, all of rudder is partially or the input that is just as of the data of configuration and object output.
In the present embodiment, initial data is carried out preliminary analysis by described step S2 specifically, reject noise, the preliminary effectiveness confirmed for the data calculated.
In the present embodiment, described initial data is carried out preliminary analysis also comprise the default train number data of completion (as: interpolation goes out the aerodynamic data under the required angle of attack and yaw angle).
In the present embodiment, described step S3 uses the thought analysis of bivector traction, particularly as follows: S31, be derived by known data according to available data；S32, data derive the data that the need of needs are known according to demand；S33, can obtain, in primary data, the data that need to know；S34, sets up, according to front 3 steps, flow process and the method that data process.
In the present embodiment, processor-oriented data calculation process in described step S3 is particularly as follows: the key word of Criterion is corresponding with key word in a program calculating function, by key word, described flow chart of data processing and method are expressed, set up and calculate input file.
In the present embodiment, in described step S4, the generation of data base adopts unitized data management, for node, sets up unitized data storehouse by aircraft type with configuration (band undercarriage, without undercarriage, carry etc.).
In the present embodiment, in described step S4, unitized data call tool storage room refers to the function library set up by the method for forward retrieval, reverse interpolation.It is specially, " forward retrieval " is according to input variable order (highly, Ma, yaw angle, the angle of attack etc.), two values that forward retrieval first order input variable (such as height) is nearest in corresponding Variables Sequence, then in next stage (such as the Ma) Variables Sequence that the two value is corresponding, retrieve two fingers nearest from current layer variable, the like, until last layer；" reverse interpolation " refers to the result according to " forward retrieval ", starts interpolation from afterbody, and interpolation goes out the result of last layer, goes out the result at last layer with the result interpolation of output, until the last result needed.
The aerodynamic data of a kind of aircraft processes system, comprises aerodynamic force initial data and reads in module, for reading in the initial data of wind tunnel test unit output；Aerodynamic force preliminary analysis module, for checking and the initial data of wind tunnel test described in graphic software platform；Aerodynamic data processes design module, for design input processing computing formula；Aerodynamic data computing module, calculates according to the process computing formula of the initial data read in and design input, and stores the result in data base；Aerodynamic force labor module, calls the data in data base, result of the test is analysed in depth；Aerodynamic force calling module, for the demand of different majors, designs different calculating instruments, for each specialty；Interface module, for being packaged with upper module, it is provided that interface, it is simple to staff uses.
In the present embodiment, described aerodynamic force labor module analysing in depth specifically, the aerodynamic force curve drawn under various configuration result of the test, detailed comparisons analyzes the aerodynamic data under various configuration, lift coefficient, resistance coefficient and polar.
Last it is noted that above example is only in order to illustrate technical scheme, it is not intended to limit.Although the present invention being described in detail with reference to previous embodiment, it will be understood by those within the art that: the technical scheme described in foregoing embodiments still can be modified by it, or wherein portion of techniques feature is carried out equivalent replacement；And these amendments or replacement, do not make the essence of appropriate technical solution depart from the spirit and scope of various embodiments of the present invention technical scheme.
Claims (10)
1. the aerodynamic data processing method of an aircraft, it is characterised in that comprise the steps of
S1, classifies according to rudder face, according to height, Mach number, yaw angle, rudder, the aerodynamic data of each rudder face is set up hierarchical relationship name partially, uses OO thought, set up data object；
S2, reads in module by aerodynamic force initial data and reads original aerodynamic data, set up data structure body, and by aerodynamic force preliminary analysis module, initial data is carried out preliminary analysis；
S3, according to flow chart of data processing and method, sets up processor-oriented data calculation process；
S4, processes system by the aerodynamic data of aircraft and generates unitized data storehouse.
2. aerodynamic data processing method as claimed in claim 1, it is characterised in that: OO processing method in described step S1 is not specifically, differentiate between concrete rudder partially or configuration, and all of rudder is partially or the input that is just as of the data of configuration and object output.
3. aerodynamic data processing method as claimed in claim 1, it is characterised in that: initial data is carried out preliminary analysis by described step S2 specifically, reject noise, the preliminary effectiveness confirmed for the data calculated.
4. aerodynamic data processing method as claimed in claim 3, it is characterised in that: described initial data is carried out preliminary analysis also comprise the train number data that completion is default.
5. aerodynamic data processing method as claimed in claim 1, it is characterised in that: described step S3 uses the thought analysis of bivector traction, particularly as follows: S31, is derived by known data according to available data；S32, data derive the data that the need of needs are known according to demand；S33, can obtain, in primary data, the data that need to know；S34, sets up, according to front 3 steps, flow process and the method that data process.
6. aerodynamic data processing method as claimed in claim 5, it is characterized in that: processor-oriented data calculation process in described step S3 is particularly as follows: the key word of Criterion is corresponding with key word in a program calculating function, by key word, described flow chart of data processing and method are expressed, set up and calculate input file.
7. aerodynamic data processing method as claimed in claim 1, it is characterised in that: in described step S4, the generation of data base adopts unitized data management, to be configured as node, sets up unitized data storehouse by aircraft type.
8. aerodynamic data processing method as claimed in claim 1, it is characterised in that: in described step S4, unitized data call tool storage room refers to by the function library that the method for " forward retrieval ", " reverse interpolation " is set up；It is specially, " forward retrieval " is according to input variable order, two values that " forward retrieval " first order input variable is nearest in corresponding Variables Sequence, then retrieves two fingers nearest from current layer variable in the next stage Variables Sequence that the two value is corresponding, the like, until last layer；" reverse interpolation " refers to the result according to " forward retrieval ", starts interpolation from afterbody, and interpolation goes out the result of last layer, goes out the result at last layer with the result interpolation of output, until the last result needed.
9. the aerodynamic data of an aircraft processes system, it is characterised in that: comprise
Aerodynamic force initial data reads in module, for reading in the initial data of wind tunnel test unit output；
Aerodynamic force preliminary analysis module, for checking and the initial data of wind tunnel test described in graphic software platform；
Aerodynamic data processes design module, for design input processing computing formula；
Aerodynamic data computing module, calculates according to the process computing formula of the initial data read in and design input, and stores the result in data base；
Aerodynamic force labor module, calls the data in data base, result of the test is analysed in depth；
Aerodynamic force calling module, for the demand of different majors, designs different calculating instruments, for each specialty；
Interface module, for being packaged with upper module, it is provided that interface, it is simple to staff uses.
10. aerodynamic data as claimed in claim 9 processes system, it is characterized in that: the in-depth analysis of result of the test is specially by described aerodynamic force labor module, drawing the aerodynamic force curve under various configuration, detailed comparisons analyzes the aerodynamic data under various configuration, lift curve, resistance curve and polar.
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Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106446424A (en) * | 2016-09-29 | 2017-02-22 | 西北工业大学 | Unsteady aerodynamic model parameter prediction method |
| CN106649909A (en) * | 2016-08-29 | 2017-05-10 | 成都飞机工业（集团）有限责任公司 | Dual-redundancy compensation type empennage control plane fault state control method |
| CN111581726A (en) * | 2020-05-11 | 2020-08-25 | 中国空气动力研究与发展中心 | Online integrated aircraft aerodynamic modeling system |
| CN111897854A (en) * | 2020-07-15 | 2020-11-06 | 清华大学 | Aerodynamic force and flow field correlation data analysis method, device, system and computer readable storage medium |
| CN114861334A (en) * | 2022-07-06 | 2022-08-05 | 航空航天工业沈阳六0一科技装备制造有限公司 | Low-cost pneumatic model construction method for influence of outer hanging objects on elevon |
| CN114912301A (en) * | 2022-07-18 | 2022-08-16 | 中国空气动力研究与发展中心低速空气动力研究所 | Low-speed wind tunnel full-machine model force measurement test data processing and correcting system |
| CN115017842A (en) * | 2022-08-09 | 2022-09-06 | 北京星途探索科技有限公司 | Pneumatic data interpolation method and device, electronic equipment and storage medium |
| CN115290289A (en) * | 2022-10-08 | 2022-11-04 | 中国航空工业集团公司哈尔滨空气动力研究所 | Optimization method for improving control precision of large-attack-angle tail support test system |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2008056055A1 (en) * | 2006-10-27 | 2008-05-15 | Airbus France | Method and aids for relative positioning of objects during a design phase |
| CN103617324A (en) * | 2013-12-03 | 2014-03-05 | 中国航空无线电电子研究所 | Flight simulation recording analysis system based on FlightGear simulation software |
| CN104914736A (en) * | 2015-05-07 | 2015-09-16 | 南京航空航天大学 | Method for building general simulation model for hypersonic flight vehicles |
| CN105205293A (en) * | 2015-11-05 | 2015-12-30 | 中国商用飞机有限责任公司 | Method and system for acquiring aerodynamic load of aircraft component |
-
2016
- 2016-01-26 CN CN201610052987.0A patent/CN105740525A/en active Pending
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2008056055A1 (en) * | 2006-10-27 | 2008-05-15 | Airbus France | Method and aids for relative positioning of objects during a design phase |
| CN103617324A (en) * | 2013-12-03 | 2014-03-05 | 中国航空无线电电子研究所 | Flight simulation recording analysis system based on FlightGear simulation software |
| CN104914736A (en) * | 2015-05-07 | 2015-09-16 | 南京航空航天大学 | Method for building general simulation model for hypersonic flight vehicles |
| CN105205293A (en) * | 2015-11-05 | 2015-12-30 | 中国商用飞机有限责任公司 | Method and system for acquiring aerodynamic load of aircraft component |
Non-Patent Citations (1)
| Title |
|---|
| 齐志敏: "气动综合数据库管理系统的设计与实现", 《中国优秀硕士学位论文全文数据库工程科技Ⅱ辑》 * |
Cited By (15)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106649909A (en) * | 2016-08-29 | 2017-05-10 | 成都飞机工业（集团）有限责任公司 | Dual-redundancy compensation type empennage control plane fault state control method |
| CN106649909B (en) * | 2016-08-29 | 2020-04-03 | 成都飞机工业（集团）有限责任公司 | Dual-redundancy compensation type empennage control surface fault state control method |
| CN106446424A (en) * | 2016-09-29 | 2017-02-22 | 西北工业大学 | Unsteady aerodynamic model parameter prediction method |
| CN106446424B (en) * | 2016-09-29 | 2019-07-19 | 西北工业大学 | A kind of unsteady aerodynamic force parameter prediction method |
| CN111581726A (en) * | 2020-05-11 | 2020-08-25 | 中国空气动力研究与发展中心 | Online integrated aircraft aerodynamic modeling system |
| CN111581726B (en) * | 2020-05-11 | 2023-07-28 | 中国空气动力研究与发展中心 | Online integrated aircraft aerodynamic modeling system |
| CN111897854B (en) * | 2020-07-15 | 2022-07-08 | 清华大学 | Aerodynamic force and flow field correlation data analysis method, device, system and computer readable storage medium |
| CN111897854A (en) * | 2020-07-15 | 2020-11-06 | 清华大学 | Aerodynamic force and flow field correlation data analysis method, device, system and computer readable storage medium |
| CN114861334A (en) * | 2022-07-06 | 2022-08-05 | 航空航天工业沈阳六0一科技装备制造有限公司 | Low-cost pneumatic model construction method for influence of outer hanging objects on elevon |
| CN114861334B (en) * | 2022-07-06 | 2022-09-02 | 航空航天工业沈阳六0一科技装备制造有限公司 | Low-cost pneumatic model construction method for influence of outer hanging objects on elevon |
| CN114912301A (en) * | 2022-07-18 | 2022-08-16 | 中国空气动力研究与发展中心低速空气动力研究所 | Low-speed wind tunnel full-machine model force measurement test data processing and correcting system |
| CN115017842A (en) * | 2022-08-09 | 2022-09-06 | 北京星途探索科技有限公司 | Pneumatic data interpolation method and device, electronic equipment and storage medium |
| CN115017842B (en) * | 2022-08-09 | 2022-12-02 | 北京星途探索科技有限公司 | Pneumatic data interpolation method and device, electronic equipment and storage medium |
| CN115290289A (en) * | 2022-10-08 | 2022-11-04 | 中国航空工业集团公司哈尔滨空气动力研究所 | Optimization method for improving control precision of large-attack-angle tail support test system |
| CN115290289B (en) * | 2022-10-08 | 2022-12-09 | 中国航空工业集团公司哈尔滨空气动力研究所 | Optimization method for improving control precision of large-incidence-angle tail support test system |
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