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Start Over Author "Takeshi Kanda" Journal transactions of the japan society for aeronautical and space sciences
15 results on '"Takeshi Kanda"'

3. Expander and Coolant-Bleed Cycles of Methane-Fueled Rocket Engines

Author

Hiroya Asakawa, Toshiya Kimura, Takeshi Kanda, and Masaki Sato

Subjects
020301 aerospace & aeronautics, business.product_category, Materials science, business.industry, Nuclear engineering, Aerospace Engineering, 02 engineering and technology, Bleed, 01 natural sciences, Methane, 010305 fluids & plasmas, Coolant, chemistry.chemical_compound, 0203 mechanical engineering, chemistry, Rocket, Space and Planetary Science, 0103 physical sciences, Rocket engine, business
Published
2018
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5. Experimental Study of Heat Flux in the Pseudo-shock Region

Author

Kanenori Kato and Takeshi Kanda

Subjects
020301 aerospace & aeronautics, Materials science, Critical heat flux, Aerospace Engineering, 02 engineering and technology, Heat transfer coefficient, Mechanics, Heat Flux, 01 natural sciences, 010305 fluids & plasmas, Shock (mechanics), 0203 mechanical engineering, Heat flux, Space and Planetary Science, 0103 physical sciences, Pseudo-shock, Nucleate boiling
Abstract

形態: 図版あり, Physical characteristics: Original contains illustrations, Accepted: 2016-04-12, 資料番号: PA1710084000

Published
2016

6. Conceptual Design Model of High-Altitude Test Stand for Rocket Engines

Author

Takeshi Kanda, Daizo Sugimori, Yohei Ogawa, and Makoto Kojima

Subjects
Engineering, business.product_category, Condensation, Rocket engine nozzle, Aerospace Engineering, Rocket Engine, 02 engineering and technology, law.invention, 0203 mechanical engineering, Aeronautics, Conceptual design, law, Ejector, Aerospace engineering, 020301 aerospace & aeronautics, business.industry, Diffuser, Injector, Effects of high altitude on humans, Saturation, Test (assessment), 020303 mechanical engineering & transports, HATS, Rocket, Space and Planetary Science, Rocket engine, business
Abstract

Conceptual design procedures and design models of HATS are revised and renewed. The results calculated using the revised method are compared with the operating conditions of HATS at the JAXA Kakuda Space Center. The previous physical method of test chamber pressure and that of ejector suction are adopted in the present model. The suction model adopts the inviscid momentum exchange mechanism. The deceleration process in the supersonic diffuser is revised using the pseudo-shock model. Physical and thermodynamic models are constructed for condensation and steam saturated flow conditions. The results calculated are in reasonable agreement with the measured values (e.g., pressure of secondary flow at the ejector section and pressure changes during engine shut down). The effect of ejector steam condensation on the operating conditions of HATS is quantitatively presented., 形態: 図版あり, Physical characteristics: Original contains illustrations, 資料番号: PA1610066000

Published
2016

7. Conservation-Law Approach for Transition in Pipe Flows

Author

Takeshi Kanda

Subjects
Conservation law, Engineering, Momentum, Operations research, business.industry, Turbulence, Aerospace Engineering, Laminar flow, Conservation, Mechanics, 01 natural sciences, 010305 fluids & plasmas, Pipe flow, Laminar Flow, Space and Planetary Science, Transition, 0103 physical sciences, Turbulent Flow, 010306 general physics, business, Pipe Flow
Abstract

形態: 図版あり, Physical characteristics: Original contains illustrations, Accepted: 2016-07-20, 資料番号: PA1710080000

Published
2016
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8. Analytical Method for Prediction of Suction Performance of Ejector-Jet

Author

Takeshi Kanda, Shuichi Ueda, Kouichiro Tani, Harunori Nagata, and Susumu Hasegawa

Subjects
Jet (fluid), Suction, Materials science, Space and Planetary Science, law, Ejector-jet, Aerospace Engineering, Thermodynamics, Air-breathing Engine, Combined Cycle, Injector, Mechanics, law.invention
Abstract

To reduce the cost of space transportation, air-breathing engines are considered to be candidates for propulsion. However, to cover a wide range of flight speeds, the propulsion system has to operate in various modes to be efficient under incoming atmospheric-air conditions. The Japan Aerospace Exploration Agency is proposing a rocket-based combined cycle engine for operation under various condition, an ejector-jet mode being adopted for the low-speed regime. The suction performance ejector-jets has long been studied experimentally and numerically at JAXA, and little success has been achieved in explaining the deterioration of suction performance with high-temperature gas or light gas such as helium. In the present study, based on former models, a simple one-dimensional model was introduced incorporating the mixing effects of the primary flow (rocket flow) and secondary flow (induced air flow). The results were compared using several experimental and numerical data to check the plausibility of the model. It was found that if greater mixing occurs, suction performance is degraded, explaining the actual phenomena of the experiments., 形態: カラー図版あり, Physical characteristics: Original contains color illustrations, 資料番号: PA1610077000

Published
2015
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9. ロケットエンジンターボポンプのスロットリング作動について

Author

Takeshi Kanda

Subjects
Engineering, Injection, business.industry, Aerospace Engineering, Rocket Engine, Bandwidth throttling, Conceptual study, Circulation, Throttling, Aeronautics, Space and Planetary Science, Rocket engine, Aerospace engineering, business, Turbopump
Abstract

The 43rt JSASS Annual Meeting (April 12-13, 2012. Sanjo Conference Hall, The University of Tokyo), Tokyo, Japan, 資料番号: PA1210039000

Published
2013

11. Conservation-Law Approach to Prediction of Boundary Layer Transition

Author

Takeshi Kanda

Subjects
Mach number, unit Reynolds number, transition, Aerospace Engineering, Reynolds number, Magnetic Reynolds number, Mechanics, Boundary layer thickness, Reynolds equation, Physics::Fluid Dynamics, Flow separation, symbols.namesake, Boundary layer, Transition point, Space and Planetary Science, bluntness, symbols, Statistical physics, wall cooling, Reynolds-averaged Navier–Stokes equations, Mathematics
Abstract

2010 Asian Joint Conference on Propulsion and Power (March 4-6, 2010.), Miyazaki, Japan, 資料番号: AC1000137000, レポート番号: AJCPP2010-003

Published
2011
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12. Suppression of Combustor-Inlet Interaction in a Scramjet Engine under Mach 4 Flight Conditions

Author

Kan Kobayashi, Noboru Sakuranaka, Tohru Mitani, Takeshi Kanda, Sadatake Tomioka, and Kouichiro Tani

Subjects
Engineering, geography, geography.geographical_feature_category, business.industry, Aerospace Engineering, Propulsion, Combustion, Inlet, symbols.namesake, Mach number, Space and Planetary Science, Combustor, symbols, Scramjet, Aerospace engineering, business, Scramjet engine
Abstract

資料番号: ARDS06125000

Published
2007
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13. Staging of Two-Stage-to-Orbit Aerospace Plane

Author

Takeshi Kanda and Kenji Kudo

Subjects
Engineering, Staging, Unstart, business.industry, Plane (geometry), Shutdown, Trajectory, Aerospace Engineering, Aerospace Plane, Space and Planetary Science, Drag, Two-stage-to-orbit, Pitching moment, Pitching Moment, Aerospace engineering, Aerospace, business
Abstract

24th Congress of International Council of the Aeronautical Sciences (August 29-September 3, 2004.), Yokohama, Kanagawa, Japan, 資料番号: AC1000135000, レポート番号: ICAS 2004-1.11.1

Published
2005

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