Simulation of Supersonic Stage Separation of Capsule-Shaped Abort System by Aerodynamic Interaction

Wang, Yunpeng; Ozawa, Hiroshi; Koyama, Hiroto; Nakamura, Yoshiaki

doi:10.2514/6.2011-3064

Cited by 3 publications

(5 citation statements)

References 7 publications

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“…The CFL number is fixed and equals 0.5. As the accuracy of results obtained by the present in-house code has already been confirmed from the previous study [Ozawa et al, 2009], [Wang et al, 2011], it is applied to predict unsteady flow fields in this study. Additionally, the calculations were carried out by an eight-processor Linux cluster, and the MPI (Message Passing Interface) was used for parallelization.…”

Section: Governing Equations Algorithm and Gridsupporting

confidence: 70%

“…No turbulence model is employed here to show the case for laminar flow. Ozawa [2009] and Wang [2011] have already performed the numerical simulation in the case without the clearance at α = 0 • using a laminar case, where those results obtained by calculations are in agreement with experimental data. Therefore, the same conditions are employed in this paper, include a similar mesh.…”

Section: Governing Equations Algorithm and Gridsupporting

confidence: 64%

“…Detailed analysis of the pulsation shock during one cycle has been made by Ozawa, H. et al, [2009] in the case of α = 0 • , where the flow oscillations were explained from the unsteady flow fields with aerodynamic interference at four moments: t = T/4, T/2, 3T/4, T during one period T. Wang, Y. et al, [2011] further analyzed the mechanism of oscillating flow, which is focused on the fluidfluid and fluid-body interactions. In order to avoid unnecessary duplication, only variations of the flow field at an angle of attack are shown and explained in detail in this study.…”

Section: Unsteady Flow With Self-sustained Oscillationmentioning

confidence: 99%

“…The very strong aerodynamic interaction can be used for the abort system. Wang, Y. et al, [2011] simulated the abort separation of this system using a series of static and dynamic models, and analyzed the effect of Mach number on self-sustained flow oscillations in the case without separation distance.…”

Section: Introductionmentioning

confidence: 99%

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Supersonic Unsteady Flow Around a Capsule-Shaped Abort System with Angle of Attack

Wang¹,

Nakamura²

2011

International Journal of Aerospace and Lightweight Structures (

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Supersonic flow over a capsule-shaped abort system with angle of attack (AoA) of α, which is boosted by supersonic aerodynamic interference, is investigated numerically through the 3D simulation. The objective of this study is to examine the effects of AoA on aerodynamic stability. In the previous study, the flowfield around this system at α = 0 • is unsteady and has a strong periodic flow oscillation in the case without the clearance between the capsule and rocket. In the present study, this system has the angle of attack and a disk is installed to enhance the abort separation. The self-sustaining flow oscillation in the case with AoA is described and is visualized using the phase-averaged analysis of simulated results. With increasing AoA, the oscillating flow is divided into two parts, which correspond to the lower and upper surfaces of the cone. These two flows have a phase difference which becomes larger with increasing AoA. The present findings show it is about 0.28π and 0.4π, respectively. At the same time, the lower flow oscillation is out of step with the upper one, and an inharmonic flow oscillation occurs because of strong aerodynamic interaction in the lower flow. This unstable flow will lead to a risky abort separation and this phenomenon is analyzed in detail in this paper.

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Section: Governing Equations Algorithm and Gridsupporting

confidence: 70%

Section: Governing Equations Algorithm and Gridsupporting

confidence: 64%

Section: Unsteady Flow With Self-sustained Oscillationmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

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Supersonic Unsteady Flow Around a Capsule-Shaped Abort System with Angle of Attack

Wang¹,

Nakamura²

2011

International Journal of Aerospace and Lightweight Structures (

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“…Статья [5] посвящена экспериментальному исследованию структуры и распределения давления по дну осесимметричной выемки при ее сверхзвуковом (М ∞ = 2,84) обтекании в зависимости от длины (глубина была постоянно равной 0,7 диаметра цилиндра). Авторами работы [6] выполнено экспериментальное и численное в осесимметричной постановке изучение влияния аэродинамической интерференции на процесс отделения капсулы от ракеты при М ∞ от 1,6 до 5. Изучено влияние параметров выемки на распределение давления и аэродинамическое сопротивление.…”

Section: Introductionunclassified

Multimode Pulsations in the Axisymmetric Cavern at Supersonic Flow

Gubanov

Zapryagaev

2017

SJPhys

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Представлены результаты экспериментального исследования структуры течения и спектральных характеристик пульсаций давления в осесимметричной полости, омываемой сверхзвуковым потоком при числе Маха 2. Выявлено наличие многомодовых пульсаций, характеризующихся тем, что в различные моменты времени доминируют различные моды колебаний. Максимальная амплитуда пульсаций давления одной моды соответствует минимальному значению другой. Зарегистрирован случайный характер перестройки режима колебаний с одной моды на другую с временем существования колебаний отдельной моды существенно больше ее периода. Установлено, что моды колебаний существуют в виде тороидальных и спиральных возмущений. Результаты численного моделирования качественно воспроизводят многомодовый характер пульсаций, наблюдаемый в эксперименте. Ключевые слова: осесимметричная выемка, сверхзвуковое обтекание, многомодовые пульсации.

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Numerical Simulation of Stage Jettisoning of a Two-Stage Rocket with Different Separation Distances

Balasubramanian

Anandhanarayanan

Krishnamurthy

et al. 2012

J. Inst. Eng. India Ser. C

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Simulation of Supersonic Stage Separation of Capsule-Shaped Abort System by Aerodynamic Interaction

Cited by 3 publications

References 7 publications

Supersonic Unsteady Flow Around a Capsule-Shaped Abort System with Angle of Attack

Supersonic Unsteady Flow Around a Capsule-Shaped Abort System with Angle of Attack

Multimode Pulsations in the Axisymmetric Cavern at Supersonic Flow

Numerical Simulation of Stage Jettisoning of a Two-Stage Rocket with Different Separation Distances

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