CHEMICAL ROCKET PROPULSION: A COMPREHENSIVE SURVEY OF ENERGETIC MATERIALS 545-575 2017年 [査読有り]
The demand for the economic and dedicated space launchers for vast amount of lightweight, so-called nano-/microsatellites, is now growing rapidly. There is a strong rationale for the usage of the hybrid propulsion for economic space launch as sugg...
Numerical analysis on the instability of liquid/dense fluid films under supercritical operating conditions is performed on methane fuel. A numerical code for compressible fluid flows, accommodated for the van der Waals equation of state, is develo...
TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, AEROSPACE TECHNOLOGY JAPAN 8(ists27) Pa_29-Pa_37-Pa_37 2010年 [査読有り]
In this paper, described is the development of a numerical simulation system, what we call "Advanced Computer Science on SRM Internal Ballistics (ACSSIB)", for the purpose of improvement of performance and reliability of solid rocket motors (SRM)....
For the last 50 years solid propulsion has successfully created a multitude of small launchers and many first stages or boosters for heavy launchers with low risk, high performance. competitive cost, superb storability, and "instant" readiness in ...
JOURNAL OF PROPULSION AND POWER 25(6) 1300-1310 2009年11月 [査読有り]
To understand the mechanism of the generation of large roll torque in an operating solid rocket motor with axially slotted propellant grain and a narrow nozzle-submergence region, fully three-dimensional Navier-Stokes numerical simulations are con...
Proceedings of the International Astronautical Congress, IAC 13 8624-8628 2017年
A new hybrid rocket combustion method which can improve the fuel regression rate more than that of conventional method. The new method is named as Multi-Section Swirl Injection Method, which generates swirling flows at some cross-sections in combu...
A computational model of a hybrid rocket motor has been developed for the purpose of simulation of internal ballistics and transient behavior such as combustion instabilities. The numerical model consists of four sub-components: i) a quasi 1D gas ...
The primary objective of this study is to reveal the effect of oxidizer mass flow control for extinction-reignition, which is one of the useful points of hybrid rocket, for extending downrange and duration in the lower thermosphere. Swirling-flow ...
Impacts of various types of O/F shifts on flight performances of a single stage sounding rocket with a scale of S-520 sounding rocket series were comprehensively evaluated by flight simulations of O/F controlled and uncontrolled hybrid rockets. Be...
61st International Astronautical Congress 2010, IAC 2010 2010年9月27日
This paper describes the development of a numerical simulation system, "Advanced Computer Science on Solid-Rocket-Motor (SRM) Internal Ballistics (ACSSIB)". The objectives of this technology development consist of development of composite-propella...