Full-Scale Firing Tests of Variable Flow Ducted Rocket Engines Employing Gap Solid Fuel Gas Generator

Nakayama, Hisahiro; Ikegami, Yoshiyuki; Yoshida, Akihiko; Koori, Kenji; Watanabe, Kiyoyuki; Tokunaga, Hidenori; Shimizu, Haruo; Kanaizumi, Shigeyuki

doi:10.2514/6.2009-5121

Cited by 9 publications

(4 citation statements)

References 6 publications

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“…When the throat area is decreased, dA t ðÞ d 5 0, the gas pressure increases, dP g ðÞ d 4 0, and vice versa. So, the two terms in the square brackets of equation (4) are in the opposite sign, and the trend of the gas flow in the VMS is determined by the term whose absolute value is relatively greater. If the absolute value of the relative changing rate of the throat area, 1…”

Section: Theoretical Analysesmentioning

confidence: 98%

“…Equation (4) suggests that the variation of gas flow is determined together by the variation of throat area, A t ðÞ, and gas pressure, P g ðÞ, when the throat area is changing; and only by the variation of the gas pressure when the throat area throttling valve stops moving. Based on this, the process of gas flow regulation can be divided into two stages: the valve motion stage (VMS) and the parameter responding stage (PRS).…”

Section: Theoretical Analysesmentioning

confidence: 99%

“…To guarantee the safety and high performance of ducted rocket over wider ranges of Mach number (2-4) and attitude (5-25 km), the gas flow, which is generated by the gas generator and reacts with the air in the secondary combustor to produce thrust, should be controllable. [4][5][6] There are two main approaches to control the gas flow of ducted rocket: approach of modulating the throat area of gas generator and approach of self-adaptive adjusting of unchoked ducted rocket. The widely used one is the former.…”

Section: Introductionmentioning

confidence: 99%

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Investigation on the anti-regulation characteristic of variable flow ducted rocket

Xia

et al. 2012

Proceedings of the Institution of Mechanical Engineers, Part G:

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A so-called 'anti-regulation' characteristic was detected to exist in the gas flow regulation process of variable flow ducted rocket. Anti-regulation of gas flow is harmful to the performance enhancement of variable flow ducted rocket and also increases difficulties in the control system design. This article focuses on the anti-regulation characteristic of variable flow ducted rocket, and aims at revealing the physical mechanism of this phenomenon. Some basic concerns, such as the definition, the reason and the termination condition of anti-regulation, were theoretically analysed. A concept of critical changing rate of throat area was introduced and defined to analytically explain the anti-regulation phenomenon. Based on this, the critical regulation process was defined and demonstrated to be the best compromise between the rapid response and stability of variable flow ducted rocket. Programming calculations and direct-connected variable flow ducted rocket tests were conducted to validate the conclusions obtained in this article. The results demonstrated that the appearance of the gas flow anti-regulation during the regulation process can be precisely predicted by the relationship between the critical changing rate of throat area and the actual changing rate of the throat area.

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Section: Theoretical Analysesmentioning

confidence: 98%

Section: Theoretical Analysesmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

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Investigation on the anti-regulation characteristic of variable flow ducted rocket

Xia

et al. 2012

Proceedings of the Institution of Mechanical Engineers, Part G:

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“…Furthermore, it can be decomposed rapidly under the low combustion temperature and fuel-rich decomposition products are produced during combustion [16]. The GAP-based propellants have demonstrated a signi¦cant capability as e¨ective fuels for the gas generator in several research groups [5,12,16]. Thus, such a propellant was chosen for the gas generator in the present study.…”

Section: Simulant Fuel Mixture For the Gas Generatormentioning

confidence: 99%

Experimental investigation of the effect of the air inlet angle and the combustion pressure in a ducted rocket combustor

Laguzzi

Molinaro

Natan

2019

Progress in Propulsion Physics – Volume 11

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The scope of the study is to evaluate the combustion efficiency of a ducted rocket combustor operating at different conditions, using a connected-pipe testing setup. An experimental parametric investigation was conducted to evaluate the effect of the inlet air-injection angles and the effect of the combustion pressure for different fuel-to-air ratios. The experimental results indicate that best energetic performance was obtained for an injection angle of 120°, i. e., against the main flow direction. The reason is that this way better mixing was obtained and the residence time increased. Characteristic velocity was found to decrease with decreasing the combustion pressure.

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An LES for the Effects of Particle Size and Velocity Ratio on the Flow Structure in the Secondary Combustor

Kim

Choi

Sung

2020

Int. J. Aeronaut. Space Sci.

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Full-Scale Firing Tests of Variable Flow Ducted Rocket Engines Employing Gap Solid Fuel Gas Generator

Cited by 9 publications

References 6 publications

Investigation on the anti-regulation characteristic of variable flow ducted rocket

Investigation on the anti-regulation characteristic of variable flow ducted rocket

Experimental investigation of the effect of the air inlet angle and the combustion pressure in a ducted rocket combustor

An LES for the Effects of Particle Size and Velocity Ratio on the Flow Structure in the Secondary Combustor

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