Coupled CFD and rigid body dynamics analysis for the launch vehicle stage separation

Wang, J.

doi:10.2514/6.1997-2944

Cited by 6 publications

(3 citation statements)

References 1 publication

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“…The pressure and heating loads in the interstage region were emphatically explored. Wang 7 conducted the staging analysis of launch vehicle using the method of coupled axisymmetric CFD and one-dimensional separation dynamics. More recently, Li et al.…”

Section: Introductionmentioning

confidence: 99%

Numerical analysis of flow separation and side loads of a conical nozzle during staging

Jia

Jiang

Zhang

2015

Proceedings of the Institution of Mechanical Engineers, Part G:

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The objective of this effort is to numerically investigate the effect of the fire-in-the-hole staging event on the start-up flow separation and side loads of a conical nozzle during flight. The axisymmetric transient flow structure in nozzle was examined by time-accurate numerical method with time-varying chamber pressure and separation gap width. Three-dimensional time-accurate computations to examine the side loads due to non-nominal staging movement were conducted for two particular cases: misalignment between two stages and the angle of the nozzle thrust vector direction. Each asymmetry case comprised several specific staging state points which determined the corresponding chamber pressure and staging gap width. As presented by the simulation results, the flow separation in nozzle is significantly prolonged and intensified by the obstruction of the lower stage dome. When the flow separation location moves close to the nozzle exit, a strenuously axial oscillation of the separation shock appears and lasts for a period of time. In the three-dimensional asymmetric computations, in spite of strenuous oscillation, the time-average of nozzle side loads indicate that the asymmetric staging situation could lead to large sustained lateral disturbance forces. An essential ingredient driving the flow unsteadiness and asymmetry is related to the deflected and reversed supersonic flow by the dome and interstage wall corner of lower stage.

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Section: Introductionmentioning

confidence: 99%

Numerical analysis of flow separation and side loads of a conical nozzle during staging

Jia

Jiang

Zhang

2015

Proceedings of the Institution of Mechanical Engineers, Part G:

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“…A perfect gas with constant specific heat ( p C ) of 2433 J/(kgK) and constant specific heat ratio (  ) of 1.14 is assumed, which is adequate for the simulation (Wang, 1997;Buning et al, 2001 and. The conservation equations of mass, momentum and energy are expressed in tensor form as…”

Section: Flow Field Governing Equationsmentioning

confidence: 99%

“…However, stage separation in reality is at least a coupled problem between the fluid flow induced by the upper stage jet and rigid body motions of the two separating stages. With the advances in computing power and CFD techniques, coupled CFD and rigid body dynamics simulations can now be performed by means of dynamic grid (Wang, 1997) and Chimera grid method (Zhang and Zhao, 2007). In this work, a coupled CFD and rigid body dynamics analysis of a multistage rocket stage separation was carried out with the Chimera grid approach which is able to simulate moving-grid problems for arbitrary motions.…”

Section: Introductionmentioning

confidence: 99%

Intermittent Gas Resonance in Stage Separation Flow Field of Multistage Rocket

Gao¹,

Fu²

2012

Engineering Applications of Computational Fluid Mechanics

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ABSTRACT:The aerodynamic-dynamic coupled simulation was performed to investigate the interstage flow characteristics of a multistage rocket in the course of stage separation. Results show that the stage separation exhibits five phases, i.e., the initial transient phase, the smooth gas leakage phase, the gas resonance phase, the suspension phase of gas resonance and the resumed gas resonance phase. There is a striking contrast between stage separation flow of a rocket and that of a gas resonance tube, which shows iso-magnitude and iso-period oscillation. The present analysis shows that shock wave structures of the interstage and relative distance between the two stages are the main conditions which lead to this interesting phenomenon.

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Modeling of 3-DOF Launch Dynamics in Transonic and Supersonic Regime Using Navier-Stokes Equation

Purwar

Jagadeesh

2019

31st International Symposium on Shock Waves 2

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Coupled CFD and rigid body dynamics analysis for the launch vehicle stage separation

Cited by 6 publications

References 1 publication

Numerical analysis of flow separation and side loads of a conical nozzle during staging

Numerical analysis of flow separation and side loads of a conical nozzle during staging

Intermittent Gas Resonance in Stage Separation Flow Field of Multistage Rocket

Modeling of 3-DOF Launch Dynamics in Transonic and Supersonic Regime Using Navier-Stokes Equation

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