Development Study on Atrex Engine

Satô, Tetsuya; Tanatsugu, Nobuhiro; Kobayashi, Hiroaki; Hatta, Hiroshi; Sawai, Shujiro; Maru, Yusuke

doi:10.1016/s0094-5765(00)00129-6

Cited by 47 publications

(7 citation statements)

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“…On the other hand the M in values of the highest Q = 2000 kW/m 2 case of α = 3 • , 6 • and 9• nozzles are lower than that of the α = 0 • task by 34•74%, 56•39% and 72•01% respectively These proportions imply that α causes logarithmic decreases in M in ; moreover the higher decrease rates in M in due to convergence half angle put forward that α is more effective on M in than surface heat flux. These findings are similar to those ofLear et al's (1997) numerical andSato et al's (2000) experimental determinations. Application of the constant surface temperature condition on the nozzle wall(Lear et al 1997) caused flow velocities, thus M, to decrease, whereas the cooling of the nozzle surface(Sato et al 2000), which is the counter operation of the present work-focus, resulted in higher mass flow rates.…”

supporting

confidence: 92%

“…These findings are similar to those ofLear et al's (1997) numerical andSato et al's (2000) experimental determinations. Application of the constant surface temperature condition on the nozzle wall(Lear et al 1997) caused flow velocities, thus M, to decrease, whereas the cooling of the nozzle surface(Sato et al 2000), which is the counter operation of the present work-focus, resulted in higher mass flow rates. For α = 0 • case the heat flux of Q = 2000 kW/m 2 results in a decrease in M in of 23•1% when compared with the isentropic flow.…”

supporting

confidence: 92%

“…Massier et al (1970) conducted experiments in a 10 • convergence half angle nozzle with different working fluids and with a wide range of inlet stagnation pressures and recorded lower discharge coefficients with the decrease of inlet stagnation pressure. Sato et al (2000) presented the recent data of a real-time propulsion engine, which is equipped with the air-cooling system and Back et al (1996) performed an experimental investigation of flow and heat transfer in a choked nozzle with cooling.…”

Section: Introductionmentioning

confidence: 99%

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Numerical analysis of choked converging nozzle flows with surface roughness and heat flux conditions

Ozalp

2006

Sadhana

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Choked converging nozzle flow and heat transfer characteristics are numerically investigated by means of a recent computational model that integrates the axisymmetric continuity, state, momentum and energy equations. To predict the combined effects of nozzle geometry, friction and heat transfer rates, analyses are conducted with sufficiently wide ranges of covergence half angle, surface roughness and heat flux conditions. Numerical findings show that inlet Mach and Nusselt numbers decrease up to 23.1% and 15.8% with surface heat flux and by 15.13% and 4.8% due to surface roughness. Considering each convergence half angle case individually results in a linear relation between nozzle discharge coefficients and exit Reynolds numbers with similar slopes. Heat flux implementation, by decreasing the shear stress values, lowers the risks due to wear hazards at upstream sections of flow walls; however the final 10% downstream nozzle portion is determined to be quite critical, where shear stress attains the highest magnitudes. Heat transfer rates are seen to increase in the streamwise direction up to 2.7 times; however high convergence half angles, heat flux and surface roughness conditions lower inlet Nusselt numbers by 70%, 15.8% and 4.8% respectively.

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supporting

confidence: 92%

supporting

confidence: 92%

Section: Introductionmentioning

confidence: 99%

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Numerical analysis of choked converging nozzle flows with surface roughness and heat flux conditions

Ozalp

2006

Sadhana

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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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“…1. The booster is powered by airbreathing engines, ATREX engines 2 , which have been developed in the Institute of Space and Astronautical Science (ISAS) of Japan. The orbiter has reusable LOX/LH 2 rocket engines.…”

Section: Introductionmentioning

confidence: 99%

An integrated optimization for conceptual designs of airbreathing launch TSTO vehicle

Tsuchiya¹,

Mori²,

Maita³

2001

10th AIAA/NAL-NASDA-ISAS International Space Planes and Hypersonic Systems and Technologies Conference

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This paper presents the application of an optimization method to conceptual designs of fully reusable TSTO (Two-Stage-To-Orbit) spaceplanes. TSTO spaceplane is under consideration for the future space transportation vehicle Japan aims to develop and realize in the near future. Technical fields for vehicle designs in this paper are aerodynamic analysis, engine analysis, weight analysis, and trajectory analysis, which are integrated and optimized simultaneously by an optimization method proposed herein. A payload weight is defined as an index of the feasibility of spaceplanes, and the best shape and trajectories maximizing the payload weight are indicated. The results show the effectiveness of the proposed numerical methods and necessity of the further weight reduction to realize future space transportation vehicles.

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Development Study on Atrex Engine

Cited by 47 publications

References 0 publications

Numerical analysis of choked converging nozzle flows with surface roughness and heat flux conditions

Numerical analysis of choked converging nozzle flows with surface roughness and heat flux conditions

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

An integrated optimization for conceptual designs of airbreathing launch TSTO vehicle

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