Flutter test of rudder with real servo actuator in continuous transonic wind tunnel
Flutter wind tunnel test is an important approach of investigation of transonic flutter characteristics of flight vehicle. Comparing with the blow-down wind tunnel, the long-running and low dynamic pressure capabilities of continuous transonic wind tunnel are very suitable for flutter test. The flut...
| Main Authors: | , , , , , |
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| Format: | Article |
| Language: | zho |
| Published: |
EDP Sciences
2022-04-01
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| Series: | Xibei Gongye Daxue Xuebao |
| Subjects: | |
| Online Access: | https://www.jnwpu.org/articles/jnwpu/full_html/2022/02/jnwpu2022402p401/jnwpu2022402p401.html |
| _version_ | 1797668875120148480 |
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| author | HAN Jiangxu LIU Nan SHI Xiaoming GUO Jin WANG Song YU Xianpeng |
| author_facet | HAN Jiangxu LIU Nan SHI Xiaoming GUO Jin WANG Song YU Xianpeng |
| author_sort | HAN Jiangxu |
| collection | DOAJ |
| description | Flutter wind tunnel test is an important approach of investigation of transonic flutter characteristics of flight vehicle. Comparing with the blow-down wind tunnel, the long-running and low dynamic pressure capabilities of continuous transonic wind tunnel are very suitable for flutter test. The flutter safety protection and analysis of dynamic signals are developed. The safety protection control software, rapid reduction of Mach number and dynamic pressure, model debris catch screen are integrated, which can provide safety protection of test model and wind tunnel. During the test process, the flutter boundary can be achieved by interpolating the reciprocal of spectrum peak. The flutter tests of rudder are conduct through two methods of step and continuous varying dynamic pressure. It is illustrated that the error of flutter dynamic pressure is relatively small, less than 5% between the two methods. Meanwhile, the feedback effect of the real servo actuator on the flutter characteristics is hard to be obtained via numerical simulation. It is demonstrated that the flutter dynamic pressure has been increased by 10% due to the feedback effect. |
| first_indexed | 2024-03-11T20:35:51Z |
| format | Article |
| id | doaj.art-fd2cb3001a6045b88da7a9a8ce649073 |
| institution | Directory Open Access Journal |
| issn | 1000-2758 2609-7125 |
| language | zho |
| last_indexed | 2024-03-11T20:35:51Z |
| publishDate | 2022-04-01 |
| publisher | EDP Sciences |
| record_format | Article |
| series | Xibei Gongye Daxue Xuebao |
| spelling | doaj.art-fd2cb3001a6045b88da7a9a8ce6490732023-10-02T06:48:49ZzhoEDP SciencesXibei Gongye Daxue Xuebao1000-27582609-71252022-04-0140240140610.1051/jnwpu/20224020401jnwpu2022402p401Flutter test of rudder with real servo actuator in continuous transonic wind tunnelHAN Jiangxu0LIU Nan1SHI Xiaoming2GUO Jin3WANG Song4YU Xianpeng5Beihang UniversityAVIC Aerodynamics Research InstituteShanghai Electro-Mechanical Engineering InstituteAVIC Aerodynamics Research InstituteAVIC Aerodynamics Research InstituteAVIC Aerodynamics Research InstituteFlutter wind tunnel test is an important approach of investigation of transonic flutter characteristics of flight vehicle. Comparing with the blow-down wind tunnel, the long-running and low dynamic pressure capabilities of continuous transonic wind tunnel are very suitable for flutter test. The flutter safety protection and analysis of dynamic signals are developed. The safety protection control software, rapid reduction of Mach number and dynamic pressure, model debris catch screen are integrated, which can provide safety protection of test model and wind tunnel. During the test process, the flutter boundary can be achieved by interpolating the reciprocal of spectrum peak. The flutter tests of rudder are conduct through two methods of step and continuous varying dynamic pressure. It is illustrated that the error of flutter dynamic pressure is relatively small, less than 5% between the two methods. Meanwhile, the feedback effect of the real servo actuator on the flutter characteristics is hard to be obtained via numerical simulation. It is demonstrated that the flutter dynamic pressure has been increased by 10% due to the feedback effect.https://www.jnwpu.org/articles/jnwpu/full_html/2022/02/jnwpu2022402p401/jnwpu2022402p401.htmlflutterwind tunnel testtransonic continuous wind tunnelreal servo actuatorrudder |
| spellingShingle | HAN Jiangxu LIU Nan SHI Xiaoming GUO Jin WANG Song YU Xianpeng Flutter test of rudder with real servo actuator in continuous transonic wind tunnel Xibei Gongye Daxue Xuebao flutter wind tunnel test transonic continuous wind tunnel real servo actuator rudder |
| title | Flutter test of rudder with real servo actuator in continuous transonic wind tunnel |
| title_full | Flutter test of rudder with real servo actuator in continuous transonic wind tunnel |
| title_fullStr | Flutter test of rudder with real servo actuator in continuous transonic wind tunnel |
| title_full_unstemmed | Flutter test of rudder with real servo actuator in continuous transonic wind tunnel |
| title_short | Flutter test of rudder with real servo actuator in continuous transonic wind tunnel |
| title_sort | flutter test of rudder with real servo actuator in continuous transonic wind tunnel |
| topic | flutter wind tunnel test transonic continuous wind tunnel real servo actuator rudder |
| url | https://www.jnwpu.org/articles/jnwpu/full_html/2022/02/jnwpu2022402p401/jnwpu2022402p401.html |
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