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JournalISSN: 0549-3811

Transactions of The Japan Society for Aeronautical and Space Sciences 

About: Transactions of The Japan Society for Aeronautical and Space Sciences is an academic journal. The journal publishes majorly in the area(s): Aerodynamics & Airfoil. It has an ISSN identifier of 0549-3811. It is also open access. Over the lifetime, 980 publications have been published receiving 4991 citations. The journal is also known as: Transactions of the Japan Society of Aeronautical Engineering.


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Journal ArticleDOI
TL;DR: In this article, a pulse detonation engine was modeled as a straight tube, one end of the tube was closed and the other was open, and a detonation wave was ignited at the closed end.
Abstract: The performance of pulse detonation engines was analytically estimated by using a simple model. A pulse detonation engine was modeled as a straight tube. One end of the tube was closed and the other was open, and a detonation wave was ignited at the closed end. One cycle of the pulse-detonation-engine operation was divided into three phases: combustion, exhaust, and filling phases. The combustion and exhaust phases were theoretically analyzed with some simplifications, using the Hugoniot relation for the Chapman-Jouguet detonation wave and flow relations for self-similar rarefaction waves. Based on the simplified theoretical analysis, useful formulas for impulse density per one-cycle operation and time-averaged thrust density were derived.

85 citations

Journal ArticleDOI
TL;DR: In this paper, the effect of turbulence models on numerical simulation of the vortical flow over a wingbody configuration at low speed and high angles of attack was investigated using Reynolds-Averaged Navier-Stokes equations with three popular turbulence models.
Abstract: This paper investigates the effect of turbulence models on numerical simulation of the vortical flow over a wingbody configuration at low speed and high angles of attack. Numerical simulations are conducted using Reynolds-Averaged Navier-Stokes equations with three popular turbulence models: the Spalart-Allmaras model, the Menter’s shear stress transport model, and the Launder-Sharma k–" model. Computational results are compared with experiments. The original Spalart-Allmaras model shows excessively large dissipation in the vortical flow away from the surface, but the rotation correction indicates significant improvement in computational results. The Menter’s model predicts reasonable agreement with the experiment in details and capture vortex structures well. The Launder-Sharma k–" model performs provides results close to those of the Menter’s model at high angles of attack. Although details of the flowfield have been simulated with large differences by different turbulence models, the choice of turbulence models is not important for prediction of aerodynamic forces.

78 citations

Journal ArticleDOI
TL;DR: The proposed constraint-handling method is demonstrated to be remarkably more robust than the dynamic penalty approach and other dominance-based approaches through the optimal design of a welded beam and conceptual design optimization of a two-stage-to-orbit spaceplane.
Abstract: A new constraint-handling method based on Pareto-optimality and niching concepts for multi-objective multi-constraint evolutionary optimization is proposed. The proposed method does not require any constants to be tuned for constraint-handling. In addition, the present method does not use the weighted-sum of constraints and thus does not require tuning of weight coefficients and is efficient even when all individuals in the initial population are infeasible or the amount of violation of each constraint is significantly different. The proposed approach is demonstrated to be remarkably more robust than the dynamic penalty approach and other dominance-based approaches through the optimal design of a welded beam and conceptual design optimization of a two-stage-to-orbit spaceplane.

66 citations

Journal ArticleDOI
TL;DR: In this paper, the prototype of a solid propellant rocket array thruster for simple attitude control of a 10 kg class micro-spacecraft was completed and tested, and the prototype has 10×10 φ0.8 mm solid-rockets arrayed at a pitch of 1.2 mm on a 20×22 mm substrate.
Abstract: The prototype of a solid propellant rocket array thruster for simple attitude control of a 10 kg class micro-spacecraft was completed and tested. The prototype has 10×10 φ0.8 mm solid propellant micro-rockets arrayed at a pitch of 1.2 mm on a 20×22 mm substrate. To realize such a dense array of micro-rockets, each ignition heater is powered from the backside of the thruster through an electrical feedthrough which passes along a propellant cylinder wall. Boron/potassium nitrate propellant (NAB) is used with/without lead rhodanide/potassium chlorate/nitrocellulose ignition aid (RK). Impulse thrust was measured by a pendulum method in air. Ignition required electric power of at least 3–4 W with RK and 4–6 W without RK. Measured impulse thrusts were from 2×10−5 Ns to 3×10−4 Ns after the calculation of compensation for air dumping.

60 citations

Journal Article
TL;DR: The wake characteristic of groups of normal flat plates, consisting of two, three, or four plates placed side by side with slits in between, have been investigated experimentally as mentioned in this paper.
Abstract: The wake characteristic of groups of normal flat plates, consisting of two, three, or four plates placed side by side with slits in between, have been investigated experimentally. When the ratio of the slit width to the plate width (slit ratio) was small, the gap flows were observed to be biased either upward or downward in a stable way, leading to multiple, stable flow patterns for a single slit-ratio value. Some regularities were recognized in the gap-flow directions and the appearance of the flow patterns. The plates on the biased side showed high drag and regular vortex shedding, while those on the unbiased side showed the opposite. The origin of the biased flow has also been investigated with water-tank experiments, numerical calculations and wind-tunnel experiments. The-results showed that the origin of biasing is strongly related to the vortex shedding of each plate of a row.

59 citations

Performance
Metrics
No. of papers from the Journal in previous years
YearPapers
202318
202237
202123
202030
201934
201828