UNSTART

作品数：7被引量：21H指数：4
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相关领域：航空宇航科学技术更多>>
相关机构：南京航空航天大学更多>>
相关期刊：《Journal of Systems Engineering and Electronics》《Transactions of Nanjing University of Aeronautics and Astronautics》《Chinese Journal of Aeronautics》更多>>
相关基金：国家自然科学基金中国博士后科学基金更多>>
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Experimental investigation on unstart-restart hysteresis of a supersonic inlet during throat regulation被引量：1
《Chinese Journal of Aeronautics》2023年第11期135-152,共18页Yi JIN Huijun TAN Hao ZHANG Gaojie ZHENG Shu SUN Yue ZHANG 
This work was co-funded by the National Natural Science Foundation of China(Nos.U20A2070,12025202,and 12172175);the National Science and Technology Major Project,China(No.J2019-II-0014-0035).
The hysteresis during the throat regulation process of a supersonic variable inlet is unconducive to restart.Hence,detailed experimental studies of such a hysteresis and its control are necessary.A throat variable sup...
关键词：Supersonic inlet Unstart-restart hysteresis Bleed control Throat regulation process Wind tunnel test 
Numerical Investigation of an Active Jet Control Method for Hypersonic Inlet Restart
《Transactions of Nanjing University of Aeronautics and Astronautics》2022年第6期651-662,共12页JIN Yichao YAO Wei 
supported by the National Key Research and Development Program of China (No.2021YFA0719204);the National Natural Science Foundation of China (No.12272387)。
A flow control method based on an active jet is developed to restart hypersonic inlets. The dynamic restarting process is numerically reproduced by unsteady Reynolds averaged Navier-Stokes(RANS) modeling to verify the...
关键词：hypersonic inlet UNSTART RESTART active jet flow control 
Flow response hysteresis of throat regulation process of a two-dimensional mixed-compression supersonic inlet被引量：3
《Chinese Journal of Aeronautics》2022年第3期112-127,共16页Yi JIN Shu SUN Huijun TAN Yue ZHANG Hexia HUANG 
co-supported by the National Natural Science Foundation of China(Nos.U20A2070,12025202,11772156,51806102,and 51906104)。
The variable geometry supersonic inlet tends to decrease the throat area to reduce the Mach number upstream of the terminal shock,so as to reduce the flow loss.However,excessive Internal Contraction Ratio(ICR)exposes ...
关键词：HYSTERESIS RESTART Supersonic inlet Throat regulation process UNSTART Unsteady numerical simulation 
Robust adaptive control of hypersonic vehicle considering inlet unstart被引量：6
《Journal of Systems Engineering and Electronics》2022年第1期188-196,共9页WANG Fan FAN Pengfei FAN Yonghua XU Bin YAN Jie 
supported by the Foundation of Shanghai Aerospace Science and Technology(SAST2016077)。
In this paper,a model reference adaptive control(MRAC)augmentation method of a linear controller is proposed for air-breathing hypersonic vehicle(AHV)during inlet unstart.With the development of hypersonic flight tech...
关键词：air-breathing hypersonic vehicle(AHV) inlet unstart model reference adaptive control augmentation(MRAC) radial basis function(RBF)neural network 
Performance of wavecatcher intakes at angles of attack and sideslip被引量：4
《Chinese Journal of Aeronautics》2021年第7期244-256,共13页Fengyuan ZUO Sannu MO LDER Gang CHEN 
National Natural Science Foundation of China(No.:12002261);National Postdoctoral Program for Innovative Talents of China(No.:BX20200267);Young Talent fund of University Association for Science and Technology in Shaanxi of China(No.:20200501);China Postdoctoral Science Foundation(No.:2020M673411);the Fundamental Research Funds for the Central Universities of China(No.:xzy012020096).G.Chen are grateful for the support of National Natural Science Foundation of China(No.:11872293).
A wavecatcher type scramjet intake,that reduces the Mach number number from 4 to 1.552,is used as the basis for a study of flow starting/unstarting as affected by freestream angles of attack and sideslip.The intake de...
关键词：Angle of attack Sideslip angle UNSTART Wavecatcher intake 
Effects of trips on the oscillatory flow of an axisymmetric hypersonic inlet with downstream throttle被引量：4
《Chinese Journal of Aeronautics》2018年第2期225-236,共12页Wenzhi GAO Zhufei LI Jiming YANG Yishan ZENG 
co-supported by the China Postdoctoral Science Foundation (No. 2017M612059);the Fundamental Research Funds for the Central Universities of China (JZ2015HGBZ0471);the National Natural Science Foundation of China (Nos. 11402263 and 11132010)
Experimental investigations are conducted on an axisymmetric hypersonic inlet to evaluate the effects of trips on oscillatory flows. The model exit is throttled with a fixed block to generate oscillatory flows at a fr...
关键词：Backpressure Flow separations Hypersonic inlets Inlet unstart Oscillatory flow TRIPS 
The Full Flowpath Analysis of a Hypersonic Vehicle被引量：5
《Chinese Journal of Aeronautics》2007年第5期385-393,共9页孙姝 
National Nature Science Foundation of China (5060601)
A numerical study has been carried out to investigate the full flow path and aerodynamic characteristics of a hypersonic vehicle at a 7.0 free stream Mach number. Results indicate that the inlet started and unstarted ...
关键词：hypersonic vehicle full flow path inlet start inlet unstart UNSTEADY lift-drag ratio 
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