加減速環境下における超音速軸対称型インテークの制御に関する実験的研究
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- Material Type
- 記事
- Author/Editor
- 小島 孝之佐藤 哲也棚次 亘弘 他
- Periodical title
- 日本航空宇宙学会論文集 = Journal of the Japan Society for Aeronautical and Space Sciences
- No. or year of volume/issue
- 51(596) 2003.9
- Volume
- 51
- Issue
- 596
- Pages
- 459～468
- Publication date of volume/issue (W3CDTF)
- 2003-09
- ISSN (Periodical Title)
- 1344-6460
- ISSN-L (Periodical Title)
- 1344-6460
- Publication (Periodical Title)
- 東京 : 日本航空宇宙学会
- Place of Publication (Country Code)
- JP
- Text Language Code
- jpn
- NDLC
- Target Audience
- 一般
- Holding library
- 国立国会図書館
- Call No.
- Z74-B503
- Data Provider (Database)
- 国立国会図書館 : 国立国会図書館雑誌記事索引
- Bibliographic ID (NDL)
- 6703623
- Bibliographic Record Category (NDL)
- 632
- Summary, etc.
- A control system of variable geometry mixed compression axisymmetric intake is experimentally studied at ONERA S3 supersonic wind tunnel. The acceleration/deceleration of the space plane is simulated by changing the free stream velocity. The intake is successfully controlled with 90% of the maximum total pressure recovery and mass capture ratio. In this experiment, two subjects about control of axisymmetric intake are also cleared. First, the effect of the trapping of the terminal shock by bleed holes causes the disturbances in the terminal shock control system. Second, a special compression form change operation is necessary when the intake compression form change from all external compression to mixed compression.
- DOI
- 10.2322/jjsass.51.459
- Access Restrictions
- インターネット公開
- Data Provider (Database)
- 科学技術振興機構 : J-STAGE
- Summary, etc.
- A control system of variable geometry mixed compression axisymmetric intake is experimentally studied at ONERA S3 supersonic wind tunnel. The acceleration/deceleration of the space plane is simulated by changing the free stream velocity. The intake is successfully controlled with 90% of the maximum total pressure recovery and mass capture ratio. In this experiment, two subjects about control of axisymmetric intake are also cleared. First, the effect of the trapping of the terminal shock by bleed holes causes the disturbances in the terminal shock control system. Second, a special compression form change operation is necessary when the intake compression form change from all external compression to mixed compression.
- DOI
- 10.2322/jjsass.51.459
- Related Material
- 加減速環境下における超音速軸対称型インテークの制御に関する実験的研究
- Related Material (URI)
- Is Referenced By
- 矩形形状可変インテークのマッハ５空力特性
- References
- Control of the intake shock-position in the test rig for ramjet engineTowards the ultimate conservative difference scheme. V. A second-order sequel to Godunov's methodApproximate Riemann solvers, parameter vectors, and difference schemesInvestigations of High-Speed Civil Transport Inlet Unstart at Angle of AttackIn situ Examination of Segregation and Wear Processes of Precious Metal Electrical Contact AlloysPractical applications of new LU-ADI scheme for the three-dimensional Navier-Stokes computation of transonic viscous flows
- Data Provider (Database)
- 国立情報学研究所 : CiNii Research
- Original Data Provider (Database)
- Japan Link Center雑誌記事索引データベースCrossrefCiNii Articles学術機関リポジトリデータベースCrossref
- Bibliographic ID (NDL)
- 6703623
- NAID
- 10011725820