CN110160742B - Method for determining position of wind tunnel model connecting mechanism - Google Patents
Method for determining position of wind tunnel model connecting mechanism Download PDFInfo
- Publication number
- CN110160742B CN110160742B CN201910259183.1A CN201910259183A CN110160742B CN 110160742 B CN110160742 B CN 110160742B CN 201910259183 A CN201910259183 A CN 201910259183A CN 110160742 B CN110160742 B CN 110160742B
- Authority
- CN
- China
- Prior art keywords
- flutter
- wind tunnel
- range
- speed
- connecting mechanism
- 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.)
- Active
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
- G01M9/00—Aerodynamic testing; Arrangements in or on wind tunnels
- G01M9/08—Aerodynamic models
Landscapes
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- General Physics & Mathematics (AREA)
- Aerodynamic Tests, Hydrodynamic Tests, Wind Tunnels, And Water Tanks (AREA)
Abstract
The invention relates to the technical field of aeroelasticity of aircrafts, and discloses a method for determining a position of a wind tunnel model connecting mechanism. The method comprises the following steps: establishing a structure finite element model of the aircraft object and a structure finite element model of the wind tunnel model connecting mechanism; connecting the wind tunnel model connecting mechanism structure finite element model with the aircraft object structure finite element model within a preset connecting mechanism motion range; respectively carrying out conventional flutter calculation and body freedom degree flutter calculation considering rigid-elastic coupling effect on the connected models; determining an effective speed range of a flutter suppression wind tunnel test and an effective speed range of a gust alleviation wind tunnel test; determining a common speed range of a flutter suppression wind tunnel test and a gust alleviation wind tunnel test; and determining the target position range of the wind tunnel model connecting mechanism from the preset connecting mechanism motion range based on the common speed range. Therefore, the position of the wind tunnel model connecting mechanism with the flutter suppression and gust alleviation functions can be determined.
Description
Technical Field
The invention relates to the technical field of aeroelasticity of aircrafts, in particular to a method for determining the position of a wind tunnel model connecting mechanism.
Background
As aircraft designs are developing towards high speed, great flexibility, and high maneuverability, the excavation requirements for various professional design margins are continuously increasing. The aeroelasticity active control technology is an advanced aircraft design technology which is praised as 'subverting the design concept of the traditional aircraft' and 'fully excavating various potential of the aircraft'. The technology actively and reasonably utilizes the deformation of the wing surface, changes the airflow distribution and the structural characteristics of the wing surface, enhances the control capability of the aircraft, realizes the optimal pneumatic performance in various flight states, and achieves the purposes of reducing the pneumatic resistance and the structural weight of the aircraft, improving the flutter critical speed, slowing down gust response and the like.
The research on the aeroelasticity active control technology is developed by means of a wind tunnel test means. The flutter active suppression technology and the gust active mitigation control technology are two key technologies with the strongest design requirements of the aircraft, and the two technologies have different requirements on wind tunnel test models. Carrying out a flutter suppression test, wherein the flutter speed of the wind tunnel model is required not to be too high, and the flutter is required to be generated at a lower speed, and then the flutter critical speed is improved by an active control means; the gust alleviation test is carried out, the flutter speed of the wind tunnel model is required to be not too low, and the risk of flutter does not occur in the open-close ring test process of gust response. Therefore, in the traditional model design, different wind tunnel models can be designed only aiming at two types of tests, and the tests are respectively carried out, so that the test cost is increased and the test resources are wasted.
Disclosure of Invention
The invention aims to overcome the defects of the prior art and provides a method for determining the position of a wind tunnel model connecting mechanism, which can solve the problems in the prior art.
The technical solution of the invention is as follows: a method for determining the position of a wind tunnel model connecting mechanism comprises the following steps:
s100, establishing a structure finite element model of the aircraft object and a structure finite element model of the wind tunnel model connecting mechanism;
s102, connecting the wind tunnel model connecting mechanism structure finite element model with the aircraft object structure finite element model in a preset connecting mechanism motion range;
s104, respectively carrying out conventional flutter calculation and body freedom flutter calculation considering rigid-elastic coupling effect on the connected models to obtain a variation relation curve of conventional flutter characteristics along with the position of the connecting mechanism and a variation relation curve of the aircraft body freedom flutter characteristics along with the position of the connecting mechanism;
s106, determining an effective speed range of a flutter suppression wind tunnel test and an effective speed range of a gust alleviation wind tunnel test according to a flutter calculation result;
s108, determining a common speed range of the flutter suppression wind tunnel test and the gust alleviation wind tunnel test based on the effective speed range of the flutter suppression wind tunnel test and the effective speed range of the gust alleviation wind tunnel test;
and S110, determining a target position range of the wind tunnel model connecting mechanism from a preset connecting mechanism motion range based on the common speed range.
Preferably, determining the effective speed range of the flutter suppression wind tunnel test and the effective speed range of the gust alleviation wind tunnel test according to the flutter calculation result comprises:
determining a speed interval which is smaller than the conventional flutter speed and larger than the body freedom degree flutter speed by a first preset amount in the flutter calculation result as an effective speed range of the flutter suppression wind tunnel test;
and determining a speed interval which is smaller than the body freedom degree flutter speed by a second preset amount when the conventional flutter speed is larger than the body freedom degree flutter speed and a speed interval which is smaller than the conventional flutter speed by the second preset amount when the conventional flutter speed is larger than the body freedom degree flutter speed in the flutter calculation result as an effective speed range of the gust alleviation wind tunnel test.
Preferably, determining the common speed range of the flutter suppression wind tunnel test and the gust alleviation wind tunnel test based on the effective speed range of the flutter suppression wind tunnel test and the effective speed range of the gust alleviation wind tunnel test includes:
and determining the intersection of the effective speed range of the flutter suppression wind tunnel test and the effective speed range of the gust alleviation wind tunnel test as the common speed range.
Preferably, determining the wind tunnel model attachment destination location range from the predetermined attachment motion range based on the common velocity range comprises:
determining the target position range of the wind tunnel model connecting mechanism under the gust alleviation wind tunnel test from the preset connecting mechanism motion range based on the common speed range;
and determining the target position range of the wind tunnel model connecting mechanism under the flutter suppression wind tunnel test from the preset connecting mechanism motion range based on the common speed range.
Preferably, determining the target position range of the wind tunnel model connecting mechanism under the wind gust alleviation wind tunnel test from the preset connecting mechanism motion range based on the common speed range comprises:
and determining the corresponding position range when the conventional flutter speed and the body freedom degree flutter speed in the flutter calculation result are higher than the upper limit value of the common speed range as the target position range of the wind tunnel model connecting mechanism under the wind gust alleviation wind tunnel test.
Preferably, determining the target position range of the wind tunnel model connecting mechanism under the flutter suppression wind tunnel test from the preset connecting mechanism motion range based on the common speed range comprises:
and determining the position range corresponding to the conventional flutter speed higher than the upper limit value of the common speed range and the body degree of freedom flutter speed lower than the lower limit value of the common speed range in the flutter calculation result as the target position range of the wind tunnel model connecting mechanism under the flutter suppression wind tunnel test.
Preferably, the method further comprises:
carrying out flutter characteristic check calculation on a wind tunnel model connecting mechanism structure finite element model which is connected in a wind tunnel model connecting mechanism target position range under the gust alleviation wind tunnel test or in a wind tunnel model connecting mechanism target position range under the flutter suppression wind tunnel test;
judging whether the flutter characteristic check calculation results under the two tests meet respective flutter conditions or not;
in the case where any one of the chattering conditions is not satisfied, the steps S100 to S110 are repeatedly performed until both of the chattering conditions are satisfied.
Preferably, the judging whether the calculation results of checking the flutter characteristics under the two tests meet respective flutter conditions includes:
under the condition that the conventional flutter speed and the body degree of freedom flutter speed in the flutter characteristic checking calculation result under the gust wind tunnel test are both higher than the upper limit value of the common speed range, judging that the flutter characteristic checking calculation result under the gust wind tunnel test meets the corresponding flutter condition, and otherwise, judging that the corresponding flutter condition is not met;
and under the condition that the conventional flutter speed in the flutter suppression wind tunnel test flutter characteristic checking calculation result is higher than the upper limit value of the common speed range and the body degree of freedom flutter speed is lower than the lower limit value of the common speed range, judging that the flutter characteristic checking calculation result under the flutter suppression wind tunnel test meets the corresponding flutter condition, and otherwise, judging that the corresponding flutter condition is not met.
Through the technical scheme, the full-area flutter characteristic analysis and evaluation of the position parameter change of the connecting mechanism (such as a rotating shaft) can be established, so that the determination of the position of the wind tunnel model connecting mechanism with the flutter suppression and gust alleviation functions can be realized, and the model of the flutter suppression and gust alleviation test can be shared. Therefore, the application range of the test model is expanded, the test cost is reduced, the design period is prolonged, and the engineering application is facilitated.
Drawings
The accompanying drawings, which are included to provide a further understanding of the embodiments of the invention and are incorporated in and constitute a part of this specification, illustrate embodiments of the invention and together with the description serve to explain the principles of the invention. It is obvious that the drawings in the following description are only some embodiments of the invention, and that for a person skilled in the art, other drawings can be derived from them without inventive effort.
Fig. 1 is a flowchart of a method for determining a position of a wind tunnel model connecting mechanism according to an embodiment of the present invention;
FIG. 2 is a schematic diagram of a positional relationship between a model and a connection mechanism according to an embodiment of the present invention;
FIG. 3 is a diagram illustrating the flutter calculation results according to an embodiment of the present invention;
FIG. 4 is a schematic view of wind speed ranges for two types of tests in an embodiment of the present invention;
fig. 5 is a schematic diagram of a target position range of the connection structure (rotation shaft) in the embodiment of the present invention.
Detailed Description
Specific embodiments of the present invention will be described in detail below with reference to the accompanying drawings. In the following description, for purposes of explanation and not limitation, specific details are set forth in order to provide a thorough understanding of the present invention. However, it will be apparent to one skilled in the art that the present invention may be practiced in other embodiments that depart from these specific details.
It should be noted that, in order to avoid obscuring the present invention with unnecessary details, only the device structures and/or processing steps that are closely related to the scheme according to the present invention are shown in the drawings, and other details that are not so relevant to the present invention are omitted.
Fig. 1 is a flowchart of a method for determining a position of a wind tunnel model connecting mechanism according to an embodiment of the present invention.
Fig. 2 is a schematic diagram of a positional relationship between a model and a connecting mechanism according to an embodiment of the present invention.
FIG. 3 is a diagram illustrating the flutter calculation result according to an embodiment of the present invention.
As shown in fig. 1 to 3, an embodiment of the present invention provides a method for determining a position of a wind tunnel model connection mechanism, where the method includes:
s100, establishing a structural finite element model (shown by the reference numeral 2 in the figure 2) of the aircraft object and a structural finite element model (shown by the reference numeral 3 in the figure 2) of a wind tunnel model connecting mechanism (such as a rotating shaft part);
s102, connecting the wind tunnel model connecting mechanism structure finite element model with the aircraft object structure finite element model within a preset connecting mechanism motion range (the distance contained in a dashed line frame indicated by a reference number 1 in figure 2);
for example, the wind tunnel model connection mechanism structure finite element model can be moved within a predetermined connection mechanism movement range, and after the position is determined, the position can be fixed by the first connection hole 4 on the wind tunnel model connection mechanism structure finite element model 3 and the second connection hole 5 on the aircraft object structure finite element model 2.
S104, respectively carrying out conventional flutter calculation and body freedom flutter calculation considering rigid-elastic coupling effect on the connected models to obtain a variation relation curve 7 of conventional flutter characteristics along with the position of the connecting mechanism and a variation relation curve 6 of the body freedom flutter characteristics along with the position of the connecting mechanism;
s106, determining an effective speed range of a flutter suppression wind tunnel test and an effective speed range of a gust alleviation wind tunnel test according to a flutter calculation result;
s108, determining a common speed range of the flutter suppression wind tunnel test and the gust alleviation wind tunnel test based on the effective speed range of the flutter suppression wind tunnel test and the effective speed range of the gust alleviation wind tunnel test;
and S110, determining a target position range of the wind tunnel model connecting mechanism from a preset connecting mechanism motion range based on the common speed range.
Through the technical scheme, the full-area flutter characteristic analysis and evaluation of the position parameter change of the connecting mechanism (such as a rotating shaft) can be established, so that the determination of the position of the wind tunnel model connecting mechanism with the flutter suppression and gust alleviation functions can be realized, and the model of the flutter suppression and gust alleviation test can be shared. Therefore, the application range of the test model is expanded, the test cost is reduced, the design period is prolonged, and the engineering application is facilitated.
FIG. 4 is a schematic view of wind speed ranges for two types of tests in an embodiment of the present invention.
According to one embodiment of the invention, the effective speed range of the flutter suppression wind tunnel test and the effective speed range of the gust alleviation wind tunnel test determined according to the flutter calculation result comprises:
determining a speed interval which is smaller than the conventional flutter speed and larger than the body freedom flutter speed by a first preset amount (for example, 5% of body freedom flutter speed allowance) in the flutter calculation result as an effective speed range 8 of the flutter suppression wind tunnel test;
and determining a speed interval which is smaller than the body freedom degree flutter speed by a second predetermined amount (for example, 10% of the body freedom degree flutter speed allowance) when the conventional flutter speed is larger than the body freedom degree flutter speed and a speed interval which is smaller than the conventional flutter speed by the second predetermined amount when the conventional flutter speed is larger than the body freedom degree flutter speed in the flutter calculation result as an effective speed range 9 of the gust slowing wind tunnel test.
For example, as shown in fig. 4, the upper and lower limits of the effective speed range 8 of the flutter suppression wind tunnel test may be Vf _ max (test maximum wind speed) and Vf _ min (test minimum wind speed), respectively; the upper and lower limits of the effective speed range 9 of the gust alleviation wind tunnel test may be Vw _ max (test highest wind speed) and 0 (test lowest wind speed), respectively.
In other words, the normal flutter speed in the case where it is smaller than the normal flutter speed and larger than the body degree of freedom flutter speed by the first predetermined amount may be regarded as Vf _ max, and the speed larger than the body degree of freedom flutter speed by the first predetermined amount may be regarded as Vf _ min.
According to an embodiment of the present invention, determining the common speed range of the flutter suppression wind tunnel test and the gust alleviation wind tunnel test based on the effective speed range of the flutter suppression wind tunnel test and the effective speed range of the gust alleviation wind tunnel test includes:
and determining the intersection of the effective speed range of the flutter suppression wind tunnel test and the effective speed range of the gust alleviation wind tunnel test as the common speed range.
For example, as shown in fig. 4, the effective velocity range 8 for the flutter suppression wind tunnel test is approximately (24, 31.5), and the effective velocity range 9 for the gust alleviation wind tunnel test is approximately (0, 29). Thus, a common speed range (24, 29) can be obtained by intersecting the two.
Fig. 5 is a schematic diagram of the target position range of the connection (rotation shaft) structure in the embodiment of the present invention.
According to one embodiment of the invention, determining a wind tunnel model attachment mechanism destination location range from a predetermined attachment mechanism range of motion based on a common velocity range comprises:
determining a target position range 11 of a wind tunnel model connecting mechanism under a gust alleviation wind tunnel test from a predetermined connecting mechanism motion range based on a common speed range;
and determining a target position range 10 of the wind tunnel model connecting mechanism under the flutter suppression wind tunnel test from a preset connecting mechanism motion range based on the common speed range.
According to an embodiment of the present invention, determining a wind tunnel model connection mechanism target position range 11 under a gust alleviation wind tunnel test from a predetermined connection mechanism movement range based on a common speed range includes:
and determining the corresponding position range when the conventional flutter speed and the body freedom degree flutter speed in the flutter calculation result are higher than the upper limit value of the common speed range as a target position range 11 of the wind tunnel model connecting mechanism under the wind gust alleviation wind tunnel test.
For example, as shown in FIG. 5, the wind tunnel model attachment destination location range 11 under the wind tunnel test for gust alleviation may be approximately 160 to 200.
According to one embodiment of the present invention, determining a wind tunnel model connection mechanism destination location range 10 under a flutter suppression wind tunnel test from a predetermined connection mechanism motion range based on a common speed range comprises:
and determining a position range corresponding to the conventional flutter speed higher than the upper limit value of the common speed range and the body degree of freedom flutter speed lower than the lower limit value of the common speed range in the flutter calculation result as a wind tunnel model connecting mechanism target position range 10 under the flutter suppression wind tunnel test.
For example, as shown in FIG. 5, the wind tunnel model attachment destination location range 10 under flutter suppression wind tunnel testing may be approximately 45 to 50.
According to an embodiment of the invention, the method further comprises:
carrying out flutter characteristic check calculation on a wind tunnel model connecting mechanism structure finite element model which is connected in a wind tunnel model connecting mechanism target position range under the gust alleviation wind tunnel test or in a wind tunnel model connecting mechanism target position range under the flutter suppression wind tunnel test;
judging whether the flutter characteristic check calculation results under the two tests meet respective flutter conditions or not;
in the case where any one of the chattering conditions is not satisfied, the steps S100 to S110 are repeatedly performed until both of the chattering conditions are satisfied.
Therefore, the target position range of the wind tunnel model connecting mechanism in the two types of tests can be verified, and the target position range can be optimized.
According to an embodiment of the present invention, determining whether the flutter characteristic check calculation results under the two tests satisfy respective flutter conditions includes:
under the condition that the conventional flutter speed and the body degree of freedom flutter speed in the flutter characteristic checking calculation result under the gust wind tunnel test are both higher than the upper limit value of the common speed range, judging that the flutter characteristic checking calculation result under the gust wind tunnel test meets the corresponding flutter condition, and otherwise, judging that the corresponding flutter condition is not met;
and under the condition that the conventional flutter speed in the flutter suppression wind tunnel test flutter characteristic checking calculation result is higher than the upper limit value of the common speed range and the body degree of freedom flutter speed is lower than the lower limit value of the common speed range, judging that the flutter characteristic checking calculation result under the flutter suppression wind tunnel test meets the corresponding flutter condition, and otherwise, judging that the corresponding flutter condition is not met.
It will be understood by those skilled in the art that the numerical values shown in the drawings are exemplary only and are not intended to limit the present invention.
Features that are described and/or illustrated above with respect to one embodiment may be used in the same way or in a similar way in one or more other embodiments and/or in combination with or instead of the features of the other embodiments.
It should be emphasized that the term "comprises/comprising" when used herein, is taken to specify the presence of stated features, integers, steps or components but does not preclude the presence or addition of one or more other features, integers, steps, components or groups thereof.
The above methods of the present invention may be implemented by hardware, or may be implemented by hardware in combination with software. The present invention relates to a computer-readable program which, when executed by a logic section, enables the logic section to realize the above-described apparatus or constituent section, or to realize the above-described various methods or steps. The present invention also relates to a storage medium such as a hard disk, a magnetic disk, an optical disk, a DVD, a flash memory, or the like, for storing the above program.
The many features and advantages of these embodiments are apparent from the detailed specification, and thus, it is intended by the appended claims to cover all such features and advantages of these embodiments which fall within the true spirit and scope thereof. Further, since numerous modifications and changes will readily occur to those skilled in the art, it is not desired to limit the embodiments of the invention to the exact construction and operation illustrated and described, and accordingly, all suitable modifications and equivalents may be resorted to, falling within the scope thereof.
The invention has not been described in detail and is in part known to those of skill in the art.
Claims (8)
1. A method for determining the position of a wind tunnel model connecting mechanism is characterized by comprising the following steps:
s100, establishing a structure finite element model of the aircraft object and a structure finite element model of the wind tunnel model connecting mechanism;
s102, connecting the wind tunnel model connecting mechanism structure finite element model with the aircraft object structure finite element model in a preset connecting mechanism motion range to obtain a connected model;
s104, respectively carrying out conventional flutter calculation and body freedom flutter calculation considering the rigid-elastic coupling effect on the connected models to obtain a variation relation curve of the conventional flutter characteristic along with the position of the connecting mechanism and a variation relation curve of the aircraft body freedom flutter characteristic along with the position of the connecting mechanism;
s106, determining an effective speed range of a flutter suppression wind tunnel test and an effective speed range of a gust alleviation wind tunnel test according to a conventional flutter calculation result and a body freedom flutter calculation result considering a rigid-elastic coupling effect;
s108, determining a common speed range of the flutter suppression wind tunnel test and the gust alleviation wind tunnel test based on the effective speed range of the flutter suppression wind tunnel test and the effective speed range of the gust alleviation wind tunnel test;
and S110, determining a target position range of the wind tunnel model connecting mechanism from a preset connecting mechanism motion range based on the common speed range.
2. The method of claim 1, wherein determining the effective velocity range for a flutter suppression wind tunnel test and the effective velocity range for a gust alleviation wind tunnel test based on conventional flutter calculation results and body-freedom flutter calculation results taking into account the rigid-elastic coupling effect comprises:
determining a speed interval which is smaller than the conventional flutter speed and larger than the body freedom degree flutter speed by a first preset amount in the flutter calculation result as an effective speed range of the flutter suppression wind tunnel test;
and determining a speed interval which is smaller than the body freedom degree flutter speed by a second preset amount when the conventional flutter speed is larger than the body freedom degree flutter speed and a speed interval which is smaller than the conventional flutter speed by the second preset amount when the conventional flutter speed is larger than the body freedom degree flutter speed in the flutter calculation result as an effective speed range of the gust alleviation wind tunnel test.
3. The method of claim 2, wherein determining the common speed range for the flutter suppression wind tunnel test and the gust alleviation wind tunnel test based on the effective speed range for the flutter suppression wind tunnel test and the effective speed range for the gust alleviation wind tunnel test comprises:
and determining the intersection of the effective speed range of the flutter suppression wind tunnel test and the effective speed range of the gust alleviation wind tunnel test as the common speed range.
4. The method of claim 1, wherein determining a wind tunnel model attachment destination location range from a predetermined attachment motion range based on the common velocity range comprises:
determining the target position range of the wind tunnel model connecting mechanism under the gust alleviation wind tunnel test from the preset connecting mechanism motion range based on the common speed range;
and determining the target position range of the wind tunnel model connecting mechanism under the flutter suppression wind tunnel test from the preset connecting mechanism motion range based on the common speed range.
5. The method of claim 4, wherein determining a range of wind tunnel model attachment mechanism destination locations under a gust alleviation wind tunnel test from a predetermined range of attachment mechanism motions based on a common velocity range comprises:
and determining the corresponding position range when the conventional flutter speed and the body freedom degree flutter speed in the flutter calculation result are higher than the upper limit value of the common speed range as the target position range of the wind tunnel model connecting mechanism under the wind gust alleviation wind tunnel test.
6. The method of claim 4, wherein determining a range of wind tunnel model attachment destination locations under a flutter suppression wind tunnel test from within a predetermined attachment motion range based on a common velocity range comprises:
and determining the position range corresponding to the conventional flutter speed higher than the upper limit value of the common speed range and the body degree of freedom flutter speed lower than the lower limit value of the common speed range in the flutter calculation result as the target position range of the wind tunnel model connecting mechanism under the flutter suppression wind tunnel test.
7. The method of claim 1, further comprising:
carrying out flutter characteristic check calculation on a wind tunnel model connecting mechanism structure finite element model which is connected in a wind tunnel model connecting mechanism target position range under the gust alleviation wind tunnel test or in a wind tunnel model connecting mechanism target position range under the flutter suppression wind tunnel test;
judging whether the flutter characteristic check calculation results under the two tests meet respective flutter conditions or not;
in the case where any one of the chattering conditions is not satisfied, the steps S100 to S110 are repeatedly performed until both of the chattering conditions are satisfied.
8. The method of claim 7, wherein determining whether the flutter characteristics check computation results under two tests satisfy respective flutter conditions comprises:
under the condition that the conventional flutter speed and the body degree of freedom flutter speed in the flutter characteristic checking calculation result under the gust wind tunnel test are both higher than the upper limit value of the common speed range, judging that the flutter characteristic checking calculation result under the gust wind tunnel test meets the corresponding flutter condition, and otherwise, judging that the corresponding flutter condition is not met;
and under the condition that the conventional flutter speed in the flutter suppression wind tunnel test flutter characteristic checking calculation result is higher than the upper limit value of the common speed range and the body degree of freedom flutter speed is lower than the lower limit value of the common speed range, judging that the flutter characteristic checking calculation result under the flutter suppression wind tunnel test meets the corresponding flutter condition, and otherwise, judging that the corresponding flutter condition is not met.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910259183.1A CN110160742B (en) | 2019-04-02 | 2019-04-02 | Method for determining position of wind tunnel model connecting mechanism |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910259183.1A CN110160742B (en) | 2019-04-02 | 2019-04-02 | Method for determining position of wind tunnel model connecting mechanism |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN110160742A CN110160742A (en) | 2019-08-23 |
| CN110160742B true CN110160742B (en) | 2020-12-08 |
Family
ID=67638444
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201910259183.1A Active CN110160742B (en) | 2019-04-02 | 2019-04-02 | Method for determining position of wind tunnel model connecting mechanism |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN110160742B (en) |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113916489B (en) * | 2021-09-30 | 2023-12-26 | 中国航空工业集团公司哈尔滨空气动力研究所 | Model supporting device for releasing five rigid body degrees of freedom of wind tunnel test model |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101419117A (en) * | 2008-11-28 | 2009-04-29 | 北京航空航天大学 | Aeroelastic flutter generating device |
| CN102305699A (en) * | 2011-05-19 | 2012-01-04 | 北京航空航天大学 | Wind tunnel experiment system for free flight model |
| CN105954000A (en) * | 2016-05-31 | 2016-09-21 | 中国航空工业集团公司西安飞机设计研究所 | Flight flutter model |
| CN107436221A (en) * | 2017-09-12 | 2017-12-05 | 西北工业大学 | The hanging method and suspension arrangement of extreme span all-wing aircraft body free degree flutter wind tunnel test model |
| CN108116657A (en) * | 2017-11-27 | 2018-06-05 | 西北工业大学 | A kind of wing damper mechanism based on shape memory spring distressed structure |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US8651813B2 (en) * | 2009-05-29 | 2014-02-18 | Donald James Long | Fluid dynamic body having escapelet openings for reducing induced and interference drag, and energizing stagnant flow |
-
2019
- 2019-04-02 CN CN201910259183.1A patent/CN110160742B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101419117A (en) * | 2008-11-28 | 2009-04-29 | 北京航空航天大学 | Aeroelastic flutter generating device |
| CN102305699A (en) * | 2011-05-19 | 2012-01-04 | 北京航空航天大学 | Wind tunnel experiment system for free flight model |
| CN105954000A (en) * | 2016-05-31 | 2016-09-21 | 中国航空工业集团公司西安飞机设计研究所 | Flight flutter model |
| CN107436221A (en) * | 2017-09-12 | 2017-12-05 | 西北工业大学 | The hanging method and suspension arrangement of extreme span all-wing aircraft body free degree flutter wind tunnel test model |
| CN108116657A (en) * | 2017-11-27 | 2018-06-05 | 西北工业大学 | A kind of wing damper mechanism based on shape memory spring distressed structure |
Non-Patent Citations (2)
| Title |
|---|
| 主动气动弹性机翼的颤振主动抑制与阵风减缓研究;吴志刚 等;《机械强度》;20030228;第25卷(第1期);第32-35页 * |
| 飞行器气动弹性风洞试验技术综述;杨希明 等;《空气动力学学报》;20181231;第36卷(第6期);第995-1006页 * |
Also Published As
| Publication number | Publication date |
|---|---|
| CN110160742A (en) | 2019-08-23 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN110160742B (en) | Method for determining position of wind tunnel model connecting mechanism | |
| JP6689231B2 (en) | Intake design method, intake design program, and intake design device | |
| CN107238177A (en) | A kind of control method and device of air conditioner silent mode | |
| CN113742845B (en) | Method for correcting transition model by hypersonic flow field temperature | |
| CA2583468A1 (en) | Method for designing a flight vehicle | |
| CN108984862B (en) | Pneumatic characteristic CFD calculation result correction method | |
| CN110953178A (en) | Stall early warning method and system for parallel running fans | |
| CN106708065A (en) | Unmanned aerial vehicle landing control method, device and unmanned aerial vehicle | |
| CN112506218A (en) | Reentry aircraft any no-fly-off area fly-around method based on intelligent trajectory prediction | |
| CN115328191A (en) | Method, system, equipment and storage medium for controlling cruise of grazing cruise target | |
| CN105404310B (en) | UAV Flight Control method and device | |
| CN115750103A (en) | Anti-surge control method and device, electronic equipment and storage medium | |
| JP7014472B2 (en) | How to divide the wing fork point cloud based on the 3D feature descriptor | |
| WO2023045301A1 (en) | Unmanned device control | |
| CN114139282B (en) | Water inlet impact load modeling method for cross-medium aircraft | |
| BR112021003681A2 (en) | method of precomputing a recovery trajectory for an aircraft autopilot and apparatus for precomputing a recovery trajectory for an aircraft autopilot system | |
| CN112560174B (en) | Static aeroelasticity low dynamic test data extraction method, device, medium and equipment | |
| JPWO2020121664A1 (en) | Information processing device | |
| BR112021003696A2 (en) | non-binary collaborative recovery system and method | |
| CN113815859B (en) | Unmanned equipment take-off control method, unmanned equipment take-off control device, unmanned equipment take-off control equipment and storage medium | |
| KR102408423B1 (en) | Apparatus and method for generating drevice command for control wing of flight vehicle | |
| KR102617794B1 (en) | Learning method for aircraft control and electronic apparatus therefor | |
| CN113158347A (en) | Method for rapidly determining position of flow direction vortex in high-speed three-dimensional boundary layer | |
| CN114061042A (en) | Air conditioner energy-saving control method, air conditioner and computer readable storage medium | |
| CN112182754B (en) | Method for calculating aerodynamic resistance of surface projection of helicopter body |
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 | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |