Analytical study of pre-cooled turbojet engine for TSTO Spaceplane

Pre-cooled turbojet engine is investigated to realize Mach 5 class hypersonic transport aircraft. The engine has been demonstrated under sea level static and Mach 2 flight conditions using hydrogen as fuel. Presently, Mach 5 propulsion wind tunnel test using liquid hydrogen is planned and the engine components such as pre-cooler, core engine, afterburner and exhaust nozzle are under development. The engine components were tested under Mach 4 simulating condition by connecting the pre-cooler inlet to an air supply facility. The engine was tested in a propulsion wind tunnel with Mach 4 flight condition. Liquid nitrogen was supplied to the pre-cooler as a coolant in place of liquid hydrogen. Gaseous hydrogen was supplied to the main burner to drive the turbine with the combustion gas. As a result, high temperature structure and cooling system was proved to endure Mach 4 high temperature airstream. Wind-mill starting sequence of the core engine under Mach 4 flight condition was confirmed. Gross thrust of the core engine was obtained as an initial evaluation of elemental performance. Nomenclature GH2= gaseous hydrogen GN2 = gaseous nitrogen LH2 = liquid hydrogen LN2 = liquid nitrogen TIO = Intake outlet (pre-cooler inlet) air temperature TFDI = flow duct inlet (pre-cooler outlet) air temperature TPCIN = pre-cooler inlet coolant temperature TPCOUT = pre-cooler outlet coolant temperature TEIN = evaporator inlet fuel temperature TEOUT = evaporator outlet fuel temperature PTIO = intake outlet air total pressure POUT = compressor outlet air total pressure

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“…The design and fabrication of pre-cooled turbojet 5,6 has been conducted in JAXA. The engine operates from take-off to Mach 5, continuously.…”

Section: Figure 1 Hypersonic Technology Experimental Aircraft (Hytex)mentioning

confidence: 99%

Mach 4 Wind Tunnel Experiment of Hypersonic Pre-Cooled Turbojet Engine

Taguchi

Harada

Kobayashi

et al. 2014

19th AIAA International Space Planes and Hypersonic Systems and Technologies Conference

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“…Furthermore, we make a table of the thrust of the PCTJ engine in response to the Mach number and altitude. 3,4) This study optimizes the trajectory after the end of the micro-gravity experiment. The initial condition at t ¼ 0 in the optimal trajectory is related to the state of the vehicle that completes the micro-gravity experiment in 40 sec from an altitude of 40 km.…”

Section: Optimization Problemmentioning

confidence: 99%

“…2,3) A promising candidate for such engines is a precooled turbojet (PCTJ) engine. We have studied the components of the PCTJ engine, 3,4) and our next step is to examine the engine in an actual flight environment.…”

Section: Introductionmentioning

confidence: 99%

Trajectory Optimization and Conceptual Study of Small Test Vehicles for a Hypersonic Engine Using a High-Altitude Balloon

Tsuchiya¹,

Takenaka²,

Taguchi³

et al. 2007

Trans. Japan Soc. Aero. S Sci.

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The Japan Aerospace Exploration Agency, JAXA, announced a long-term vision recently. In the vision, JAXA aims to develop hypersonic aircrafts. A pre-cooled turbojet engine has great potential as one of newly developed hypersonic airbreathing engines. We also expect the engine to be installed in space transportation vehicles in the future. For combustion test in the real flight conditions of the engines, JAXA has an experimental plan where a small test vehicle is released from a high-altitude balloon. This paper applies numerical analysis and optimization techniques to conceptual designs of the test vehicle in order to obtain the best configuration and trajectory for the flight test. The results show helpful knowledge for designing prototype vehicles.

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“…Various types of engines have also been studied. 2,3 In June 2000, the Committee on Future Space Transportation Systems, established within Japan's Science and Technology Agency, defined a new direction for Japan's space transportation systems in the 21st century: an incremental research and development program whose final goal is a single-stage-toorbit space plane, with an interim fully reusable two-stage-to-orbit (TSTO) space plane to be developed within a few decades. 4 On the basis of that directive, Japan has begun conceptual studies of TSTO systems.…”

Section: Introductionmentioning

confidence: 99%

Optimal Design of Two-Stage-To-Orbit Space Planes with Airbreathing Engines

Tsuchiya

Mori

2005

Journal of Spacecraft and Rockets

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Many candidate concepts of reusable space transportation vehicles have been proposed around the world. Our aim in this study is to apply an optimization method for conceptual designs of two-stage-to-orbit (TSTO) space planes with airbreathing engines on the first-stage boosters and to obtain necessary vehicle sizes and their optimal flight trajectories. First, we integrate analysis methods into the optimization problem, the solution of which yield the minimized total dry mass of the first-stage booster and the second-stage orbiter. This information allows us to determine the optimal vehicle configuration and flight trajectory for a highly feasible TSTO space plane. The optimal solutions show that TSTO space planes with boosters powered by rocket engines added to the airbreathing engines are lighter in total dry mass than vehicles with boosters propelled by only airbreathing engines. However, it is necessary to lighten and miniaturize vehicle components to achieve greater feasibility. In addition, the trajectory optimizations enable the booster to glide back to a launch site using little propellant, despite the long downrange path from the staging point of the ascent trajectory. This study confirms that the analysis and optimization method proposed are effective.

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Analytical study of pre-cooled turbojet engine for TSTO Spaceplane

Cited by 14 publications

References 3 publications

Mach 4 Wind Tunnel Experiment of Hypersonic Pre-Cooled Turbojet Engine

Mach 4 Wind Tunnel Experiment of Hypersonic Pre-Cooled Turbojet Engine

Trajectory Optimization and Conceptual Study of Small Test Vehicles for a Hypersonic Engine Using a High-Altitude Balloon

Optimal Design of Two-Stage-To-Orbit Space Planes with Airbreathing Engines

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