CN104765927A - Plane lift-enhancing device high-velocity and high-velocity comprehensive optimum design method based on multiple subjects - Google Patents
Plane lift-enhancing device high-velocity and high-velocity comprehensive optimum design method based on multiple subjects Download PDFInfo
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Abstract
The invention belongs to the field of plane design, and provides a plane lift-enhancing device high-velocity and high-velocity comprehensive optimum design method based on multiple subjects for solving the problems that in an existing lift-enhancing device design process, by means of a mechanism and pneumatic reciprocated iteration, consumed time is long, expenses are high, and plane performance can hardly be improved through a cruiser wing variable camber. Take-off performance, landing performance, cruising performance and the mechanism weight serve as optimization targets, parameterized control points of lift-enhancing device multi-section wing types, mechanism design parameters of the lift-enhancing device drive mechanism, required take-off configuration deflection angles, required landing configuration deflection angles and cruising stage variable camber deflection angles are optimized so that the configuration of the optimal comprehensive performance can be obtained. The method has the advantages that the requirement for the weight of the drive mechanism, the requirement for trajectory kinematics, the requirement for the high-velocity cruise variable camber and the requirement for low-velocity take-off and landing are all met while the system is optimized, and the method is suitable for various mechanism types, free of specific trajectory formulas and high in flexibility.
Description
Technical field
The invention belongs to field of airplane design, be specially a kind of based on multi-disciplinary high-lift device of airplane height low speed Synthetical Optimization method.
Background technology
In recent years, country greatly develops large transport airplane, and high lift device system, as an important system of aircraft, has very important impact for the security and economy improving aircraft.For the current and following long-range jumbo jet, utilize high lift device to realize cruising phase variable camber and can realize reducing resistance as a new technology, reduce oil consumption, this has higher requirement to high lift device design.
In current high lift device design process, pneumatic design and mechanism design are different and separate and carry out according to subject, and do not consider to utilize high lift device to realize cruising phase wing variable camber.In actual design process, the high lift device configuration often meeting pneumatic design requirement cannot be realized by mechanism.Such design, needs on the one hand repeatedly to design between aeroperformance and mechanism's realizability, can extend the design cycle, improve design cost; Cause to realize good take-off and landing flap configuration on the other hand, the driving mechanism of wing flap is often very complicated, and construction weight is large.The driving mechanism that this complexity is heavy again can reduce the mission payload of aircraft, is not also suitable for wing simultaneously and cruises variable camber.
From domestic disclosed patent, had the high lift device Optimization Design considering movement locus, it mainly carries out single subject optimization of high lift device aeroperformance using movement locus as constraint.Only ensure that the realizability of takeoff and anding position, and the mechanism performance such as weight of mechanism is not done to consider, mechanism's preponderance of designing may be caused like this and need to redesign, truly not solving the pneumatic and inter-agency problem needing repeatedly to design.In addition, current method for designing is not considered to utilize high lift device mechanism to realize cruising phase variable camber.
Summary of the invention
The object of the invention is to solve in existing high lift device design process, mechanism and pneumatic repeatedly design cause length consuming time, spend high, and do not consider that the utilization wing variable camber that cruises promotes the shortcoming such as aeroplane performance, provide a kind of based on multi-disciplinary high-lift device of airplane height low speed Synthetical Optimization method.
Technical scheme of the present invention is:
Described one, based on multi-disciplinary high-lift device of airplane height low speed Synthetical Optimization method, is characterized in that: comprise the following steps:
Step 1: adopt parametric method to carry out the Design of Aerodynamic Configuration of high lift device Airfoils, obtain the original shape of high lift device;
Step 2: the high lift device original shape obtained according to step 1 and the initial mechanism design parameter of high lift device driving mechanism, carries out Mechanism Modeling, obtains the motion model of high lift device and driving mechanism; The movement locus of high lift device wing flap is obtained by the motion simulation of the motion model to high lift device and driving mechanism; And the movement locus of the wing flap obtained with this step enters step 3;
Step 3: according to the movement locus of wing flap entering this step, calculate the wing flap sail angle that this movement locus can realize, if wing flap sail angle is less than the landing configuration drift angle of requirement, then enter step 5, otherwise judge whether wing flap interferes with main wing in motion process, if interfere, then enter step 5, otherwise with the mechanism design parameter of the parametric control point of the high lift device Airfoils corresponding to the movement locus of the wing flap entering this step and high lift device driving mechanism, and the takeoff configuration drift angle required, landing configuration drift angle and cruising phase become curved drift angle into a sample point,
Step 4: sample point step 3 obtained is put into and optimized population; Judge to optimize sample point number in population, enter step 6 when sample point number reaches when number requires, otherwise enter step 5;
Step 5: the parametric control point of amendment high lift device Airfoils and the mechanism design parameter of high lift device driving mechanism, obtained the movement locus of high lift device wing flap by amended parametric control point and mechanism design parameter, and the movement locus of the wing flap obtained with this step returns step 3;
Step 6: adopt multi-objective optimization algorithm to be optimized process to optimization population, maximum with takeoff configuration lift-drag ratio, that landing configuration maximum lift coefficient is maximum, cruising phase becomes curved configuration lift-drag ratio is maximum, mechanism's bar in high lift device driving mechanism long minimum be optimization aim, curved drift angle is become to the takeoff configuration drift angle of the mechanism design parameter of the parametric control point of high lift device Airfoils, high lift device driving mechanism, requirement, landing configuration drift angle and cruising phase and carries out optimizing; In described optimization process, judge obtaining sample point through multi-objective optimization algorithm amendment: if amendment obtains the landing configuration drift angle that the attainable wing flap sail angle of flap kinematics track corresponding to sample point is less than requirement, then reject the sample point that this amendment obtains, otherwise judge whether wing flap interferes with main wing in motion process, if interfere, then reject the sample point that this amendment obtains.
Further preferred version, described one, based on multi-disciplinary high-lift device of airplane height low speed Synthetical Optimization method, is characterized in that: the lift-drag ratio that takeoff configuration lift-drag ratio in step 6, landing configuration maximum lift coefficient, cruising phase become curved configuration is obtained by following process:
According to the parametric control point of high lift device Airfoils and the mechanism design parameter of high lift device driving mechanism, and the takeoff configuration drift angle required, landing configuration drift angle and cruising phase become curved drift angle, obtain corresponding takeoff configuration, landing configuration and cruising phase and become curved configuration; Dynamic Mesh is adopted to set up the computing grid that takeoff configuration, landing configuration and cruising phase become curved configuration respectively, become the aerodynamic force of curved configuration by RANS equation solution takeoff configuration, landing configuration and cruising phase, obtain takeoff configuration lift-drag ratio, lift-drag ratio that landing configuration maximum lift coefficient, cruising phase become curved configuration.
Further preferred version, described one is based on multi-disciplinary high-lift device of airplane height low speed Synthetical Optimization method, it is characterized in that: high lift device driving mechanism adopts four-bar mechanism, and the design parameter of four-bar mechanism is the coordinate of two movable axis points in four-bar mechanism.
Further preferred version, described one, based on multi-disciplinary high-lift device of airplane height low speed Synthetical Optimization method, is characterized in that: high lift device driving mechanism adopts System of Rotating about Fixed Axis mechanism, and the design parameter of System of Rotating about Fixed Axis mechanism is the coordinate of dead axle point.
Further preferred version, described one is based on multi-disciplinary high-lift device of airplane height low speed Synthetical Optimization method, it is characterized in that: high lift device driving mechanism adopts connecting rod sliding track mechanism, and the design parameter of connecting rod sliding track mechanism is the coordinate of two movable axis points and the angle of slide rail and coordinate axis in connecting rod sliding track mechanism.
Further preferred version, described one is based on multi-disciplinary high-lift device of airplane height low speed Synthetical Optimization method, and it is characterized in that: in step 1, the parametric method of employing is B-spline method.
Further preferred version, described one is based on multi-disciplinary high-lift device of airplane height low speed Synthetical Optimization method, it is characterized in that: the Pareto forward position of the target that is optimized by multi-objective optimization algorithm in step 6, according to the requirement of different aircraft to performance, select the result of combination property optimum in Pareto forward position.
Beneficial effect
Optimization method of the present invention has taken into account the requirement that driving mechanism is lightweight, meet orbiting motion requirement, meet high-performance cruise variable camber and low speed takeoff and anding characteristic, makes it have the advantage of following several respects compared to prior art:
Because high lift device aeroperformance and mechanism are Synchronous fluorimetry designs, make the high lift device configuration of acquisition by path implementation, avoid and repeatedly design, greatly can shorten the design cycle of high lift device;
Using mechanism's weight as optimization aim, the mechanism designed is made to meet lightweight requirement;
Consider high low speed pneumatic design, be applicable to long-range expanded letter class passenger plane and utilize trailing edge flap to realize mechanism design and the optimization of cruising phase variable camber, be beneficial to and alleviate cruise drag, ensure low speed airfield performance simultaneously;
Be applicable to various mechanism form.Mechanism adopts 3 d modeling software to generate, generate track by motion simulation, do not need the kinematics formula for specific driving mechanism, robustness is good, flexibility ratio is high, can be used for cruise the System of Rotating about Fixed Axis mechanism form of wing variable camber, traditional double leval jib, connecting rod sliding track mechanism etc.
Accompanying drawing explanation
Fig. 1 is optimal design flow process.
Fig. 2 is four-bar mechanism sketch.
Fig. 3 is System of Rotating about Fixed Axis schematic diagram of mechanism.
Fig. 4 is connecting rod sliding track mechanism sketch.
Embodiment
Below in conjunction with specific embodiment, the present invention is described:
High lift device is generally made up of leading edge slat, main wing, trailing edge flap.Current most airplane in transportation category leading edge slat adopts the driving mechanism of slide rail form, and its movement locus is fairly simple, is typical arc track form.Trailing edge flap driving mechanism is various informative, wherein in the majority with four-bar mechanism, connecting rod sliding track mechanism and the application of System of Rotating about Fixed Axis mechanism.Trailing edge flap and driving mechanism design thereof are the key components of high lift device design.
The present invention proposes driving mechanism and the aeroperformance Synchronous fluorimetry method of high lift device, using takeoff data, landing data, cruise performance and organ length information as optimization aim, this is because rod member length and mechanism's weight closely related, so adopt rod member length as optimization aim.
Driving mechanism below in conjunction with trailing edge flap is described in detail to this method.
Step 1: adopt parametric method to carry out the Design of Aerodynamic Configuration of high lift device Airfoils, obtain the original shape of high lift device.
According to constraints such as wing flap chord length, main wing posterior border positions in the present embodiment, carried out the Design of Aerodynamic Configuration of two-dimentional high lift device by B-spline curves parametric method, obtain high lift device profile, B-spline may be defined as:
And arrange 0/0=0.In formula, k represents the power of B-spline, and t is node, and subscript i is the sequence number of B-spline.
B-spline method has good local pillar character, can carry out intense adjustment by encryption curve control point to curved profile.
Step 2: the high lift device original shape obtained according to step 1 and the initial mechanism design parameter of high lift device driving mechanism, carries out Mechanism Modeling, obtains the motion model of high lift device and driving mechanism; The movement locus of high lift device wing flap is obtained by the motion simulation of the motion model to high lift device and driving mechanism; And the movement locus of the wing flap obtained with this step enters step 3.
According to the initial mechanism design parameter of two-dimentional high lift device aerodynamic configuration and high lift device driving mechanism in the present embodiment, Simulation of Mechanism Movement software Adams is utilized to carry out Mechanism Modeling, obtain the motion model of high lift device and driving mechanism, and obtain length information corresponding to organ.Obtain by motion simulation the position that on wing flap, any two points can arrive, and export the movement locus of these two points.Utilize this process of Adams macro document record, the position of wing flap can be obtained by the movement locus of two points on wing flap in conjunction with given wing flap drift angle.
For four-bar mechanism, it simplifies the internal structure of an organization as shown in Figure 2.Main member is made up of driving stem, connecting rod, follower lever.Its king-rod 1 is driving stem, and bar 2 is connecting rod, bar 3 is follower lever.Driving stem counterclockwise movement, can drive wing flap to takeoff and anding position, and the clockwise or counterclockwise small angle deflection of driving stem, can make wing flap carry out small angle deflection, thus realizes cruising and become curved.
Adams can be adopted equally to carry out the modeling work of System of Rotating about Fixed Axis mechanism (Fig. 3), connecting rod sliding track mechanism (Fig. 4) etc., obtained the movement locus of mechanism by motion simulation.
Step 3: according to the movement locus of wing flap entering this step, calculate the wing flap sail angle that this movement locus can realize, if wing flap sail angle is less than the landing configuration drift angle of requirement, then enter step 5, otherwise judge whether wing flap interferes with main wing in motion process, if interfere, then enter step 5, otherwise with the mechanism design parameter of the parametric control point of the high lift device Airfoils corresponding to the movement locus of the wing flap entering this step and high lift device driving mechanism, and the takeoff configuration drift angle required, landing configuration drift angle and cruising phase become curved drift angle into a sample point.Judge that the method whether wing flap interferes with main wing in motion process is: within landing angle range, obtain the flap configuration that each tracing point is corresponding, judge whether it interferes with main wing.
Step 4: sample point step 3 obtained is put into and optimized population; Judge to optimize sample point number in population, enter step 6 when sample point number reaches when number requires, otherwise enter step 5.
Step 5: the parametric control point of amendment high lift device Airfoils and the mechanism design parameter of high lift device driving mechanism, obtained the movement locus of high lift device wing flap by amended parametric control point and mechanism design parameter, and the movement locus of the wing flap obtained with this step returns step 3.
In the present embodiment, adopt design parameter, the movement locus of call macro file output new mechanism and the length information of organ of mechanism in amendment macro document.
The design parameter of four-bar mechanism major effect mechanism path is the coordinate of A point in Fig. 2 and B point, by the coordinate of A point and B point in amendment macro document, new four-bar mechanism can be obtained, and then obtain the movement locus of new mechanism, and the length sum of rod member 1,2,3.
The design parameter of System of Rotating about Fixed Axis mechanism major effect mechanism path is the coordinate of the A point in Fig. 3, by the coordinate of A point in amendment macro document, can obtain new System of Rotating about Fixed Axis mechanism, and then obtain the movement locus of new mechanism, and rod member 1 length sum.
The design parameter of connecting rod sliding track mechanism major effect mechanism path is coordinate and the slide rail bias angle theta of the A point B point in Fig. 4, by coordinate and the slide rail bias angle theta of A point B point in amendment macro document, new connecting rod slide rail machine can be obtained, and then obtain the movement locus of new mechanism, and rod member 1, rod member 2 and slide rail 3 length sum.
Step 6: adopt multi-objective optimization algorithm to be optimized process to optimization population, maximum with takeoff configuration lift-drag ratio, that landing configuration maximum lift coefficient is maximum, cruising phase becomes curved configuration lift-drag ratio is maximum, mechanism's bar in high lift device driving mechanism long minimum be optimization aim, curved drift angle is become to the takeoff configuration drift angle of the mechanism design parameter of the parametric control point of high lift device Airfoils, high lift device driving mechanism, requirement, landing configuration drift angle and cruising phase and carries out optimizing.In described optimization process, judge obtaining sample point through multi-objective optimization algorithm amendment: if amendment obtains the landing configuration drift angle that the attainable wing flap sail angle of flap kinematics track corresponding to sample point is less than requirement, then reject the sample point that this amendment obtains, otherwise judge whether wing flap interferes with main wing in motion process, if interfere, then reject the sample point that this amendment obtains.
The lift-drag ratio that takeoff configuration lift-drag ratio in optimization aim, landing configuration maximum lift coefficient, cruising phase become curved configuration is obtained by following process:
According to the parametric control point of high lift device Airfoils and the mechanism design parameter of high lift device driving mechanism, and the takeoff configuration drift angle required, landing configuration drift angle and cruising phase become curved drift angle, obtain corresponding takeoff configuration, landing configuration and cruising phase and become curved configuration; Dynamic Mesh is adopted to set up the computing grid that takeoff configuration, landing configuration and cruising phase become curved configuration respectively, become the aerodynamic force of curved configuration by RANS equation solution takeoff configuration, landing configuration and cruising phase, obtain takeoff configuration lift-drag ratio, lift-drag ratio that landing configuration maximum lift coefficient, cruising phase become curved configuration.
The Pareto forward position of the target that can be optimized by above-mentioned multi-objective optimization algorithm, thus according to the requirement of different aircraft to performance, the result of combination property optimum can be selected in Pareto forward position.
Claims (7)
1., based on a multi-disciplinary high-lift device of airplane height low speed Synthetical Optimization method, it is characterized in that: comprise the following steps:
Step 1: adopt parametric method to carry out the Design of Aerodynamic Configuration of high lift device Airfoils, obtain the original shape of high lift device;
Step 2: the high lift device original shape obtained according to step 1 and the initial mechanism design parameter of high lift device driving mechanism, carries out Mechanism Modeling, obtains the motion model of high lift device and driving mechanism; The movement locus of high lift device wing flap is obtained by the motion simulation of the motion model to high lift device and driving mechanism; And the movement locus of the wing flap obtained with this step enters step 3;
Step 3: according to the movement locus of wing flap entering this step, calculate the wing flap sail angle that this movement locus can realize, if wing flap sail angle is less than the landing configuration drift angle of requirement, then enter step 5, otherwise judge whether wing flap interferes with main wing in motion process, if interfere, then enter step 5, otherwise with the mechanism design parameter of the parametric control point of the high lift device Airfoils corresponding to the movement locus of the wing flap entering this step and high lift device driving mechanism, and the takeoff configuration drift angle required, landing configuration drift angle and cruising phase become curved drift angle into a sample point,
Step 4: sample point step 3 obtained is put into and optimized population; Judge to optimize sample point number in population, enter step 6 when sample point number reaches when number requires, otherwise enter step 5;
Step 5: the parametric control point of amendment high lift device Airfoils and the mechanism design parameter of high lift device driving mechanism, obtained the movement locus of high lift device wing flap by amended parametric control point and mechanism design parameter, and the movement locus of the wing flap obtained with this step returns step 3;
Step 6: adopt multi-objective optimization algorithm to be optimized process to optimization population, maximum with takeoff configuration lift-drag ratio, that landing configuration maximum lift coefficient is maximum, cruising phase becomes curved configuration lift-drag ratio is maximum, mechanism's bar in high lift device driving mechanism long minimum be optimization aim, curved drift angle is become to the takeoff configuration drift angle of the mechanism design parameter of the parametric control point of high lift device Airfoils, high lift device driving mechanism, requirement, landing configuration drift angle and cruising phase and carries out optimizing; In described optimization process, judge obtaining sample point through multi-objective optimization algorithm amendment: if amendment obtains the landing configuration drift angle that the attainable wing flap sail angle of flap kinematics track corresponding to sample point is less than requirement, then reject the sample point that this amendment obtains, otherwise judge whether wing flap interferes with main wing in motion process, if interfere, then reject the sample point that this amendment obtains.
2. a kind of based on multi-disciplinary high-lift device of airplane height low speed Synthetical Optimization method according to claim 1, it is characterized in that: the lift-drag ratio that takeoff configuration lift-drag ratio in step 6, landing configuration maximum lift coefficient, cruising phase become curved configuration is obtained by following process:
According to the parametric control point of high lift device Airfoils and the mechanism design parameter of high lift device driving mechanism, and the takeoff configuration drift angle required, landing configuration drift angle and cruising phase become curved drift angle, obtain corresponding takeoff configuration, landing configuration and cruising phase and become curved configuration; Dynamic Mesh is adopted to set up the computing grid that takeoff configuration, landing configuration and cruising phase become curved configuration respectively, become the aerodynamic force of curved configuration by RANS equation solution takeoff configuration, landing configuration and cruising phase, obtain takeoff configuration lift-drag ratio, lift-drag ratio that landing configuration maximum lift coefficient, cruising phase become curved configuration.
3. a kind of based on multi-disciplinary high-lift device of airplane height low speed Synthetical Optimization method according to claim 2, it is characterized in that: high lift device driving mechanism adopts four-bar mechanism, and the design parameter of four-bar mechanism is the coordinate of two movable axis points in four-bar mechanism.
4. a kind of based on multi-disciplinary high-lift device of airplane height low speed Synthetical Optimization method according to claim 2, it is characterized in that: high lift device driving mechanism adopts System of Rotating about Fixed Axis mechanism, and the design parameter of System of Rotating about Fixed Axis mechanism is the coordinate of dead axle point.
5. a kind of based on multi-disciplinary high-lift device of airplane height low speed Synthetical Optimization method according to claim 2, it is characterized in that: high lift device driving mechanism adopts connecting rod sliding track mechanism, and the design parameter of connecting rod sliding track mechanism is the coordinate of two movable axis points and the angle of slide rail and coordinate axis in connecting rod sliding track mechanism.
6. a kind of based on multi-disciplinary high-lift device of airplane height low speed Synthetical Optimization method according to claim 1, it is characterized in that: in step 1, the parametric method of employing is B-spline method.
7. a kind of based on multi-disciplinary high-lift device of airplane height low speed Synthetical Optimization method according to claim 1, it is characterized in that: the Pareto forward position of the target that is optimized by multi-objective optimization algorithm in step 6, according to the requirement of different aircraft to performance, select the result of combination property optimum in Pareto forward position.
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Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105260498A (en) * | 2015-10-23 | 2016-01-20 | 中国商用飞机有限责任公司北京民用飞机技术研究中心 | Variable camber design method of large civil aircraft wing |
| CN106599353A (en) * | 2016-11-04 | 2017-04-26 | 上海工程技术大学 | Dynamic numerical simulation method for external flow field of multi-element airfoil of airplane |
| CN107220415A (en) * | 2017-05-08 | 2017-09-29 | 西北工业大学 | A kind of two-dimentional high lift device parameterization design method for meeting Engineering constraint based on nurbs curve |
| CN111159815A (en) * | 2019-12-24 | 2020-05-15 | 中国航空工业集团公司西安飞机设计研究所 | Method for quickly optimizing plane parameters of airplane wings |
| CN113609582A (en) * | 2021-07-30 | 2021-11-05 | 北京航空航天大学 | High-lift device position design method capable of meeting mechanism movement and seam parameter |
Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104176234A (en) * | 2014-08-19 | 2014-12-03 | 西北工业大学 | Imitated pterosaur airfoil profile with high lift-drag ratio gliding characteristic |
| CN104354875A (en) * | 2014-10-31 | 2015-02-18 | 中国航天空气动力技术研究院 | High-lift device optimum design method taking motion locus into account |
-
2015
- 2015-04-16 CN CN201510182441.2A patent/CN104765927B/en active Active
Patent Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104176234A (en) * | 2014-08-19 | 2014-12-03 | 西北工业大学 | Imitated pterosaur airfoil profile with high lift-drag ratio gliding characteristic |
| CN104354875A (en) * | 2014-10-31 | 2015-02-18 | 中国航天空气动力技术研究院 | High-lift device optimum design method taking motion locus into account |
Non-Patent Citations (3)
| Title |
|---|
| BAI JUNQIANG, ET AL.: "An Efficient Surrogate Model Construction Strategy for Large-Scale Output Problems", 《2ND INTERNATIONAL CONFERENCE ON ADVANCES IN COMPUTATIONAL MODELING AND SIMULATION》 * |
| 白俊强，等: "基于RBF动网格方法和改进粒子群优化算法的多段翼型优化", 《航空学报》 * |
| 白俊强，等: "考虑动力影响的大型运输机增升构型气动特性研究", 《空气动力学学报》 * |
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105260498A (en) * | 2015-10-23 | 2016-01-20 | 中国商用飞机有限责任公司北京民用飞机技术研究中心 | Variable camber design method of large civil aircraft wing |
| CN105260498B (en) * | 2015-10-23 | 2018-06-12 | 中国商用飞机有限责任公司北京民用飞机技术研究中心 | A kind of large size civil aircraft wing variable camber design method |
| CN106599353A (en) * | 2016-11-04 | 2017-04-26 | 上海工程技术大学 | Dynamic numerical simulation method for external flow field of multi-element airfoil of airplane |
| CN107220415A (en) * | 2017-05-08 | 2017-09-29 | 西北工业大学 | A kind of two-dimentional high lift device parameterization design method for meeting Engineering constraint based on nurbs curve |
| CN111159815A (en) * | 2019-12-24 | 2020-05-15 | 中国航空工业集团公司西安飞机设计研究所 | Method for quickly optimizing plane parameters of airplane wings |
| CN111159815B (en) * | 2019-12-24 | 2023-05-23 | 中国航空工业集团公司西安飞机设计研究所 | Method for rapidly optimizing plane parameters of aircraft wing |
| CN113609582A (en) * | 2021-07-30 | 2021-11-05 | 北京航空航天大学 | High-lift device position design method capable of meeting mechanism movement and seam parameter |
| CN113609582B (en) * | 2021-07-30 | 2024-02-20 | 北京航空航天大学 | Position design method for high lift device meeting mechanism movement and joint path parameters |
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