Numerical Simulation of Missile Jet Deflector

Basu, Souraseni; Saha, S.; Chakraborty, Debasis

doi:10.2514/1.a33761

Cited by 4 publications

(2 citation statements)

References 16 publications

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“…The results showed that the Mach disk moves closer to the nozzle exit plane with decreasing pressure ratio, and the length of the first shock cell decreases. Threedimensional Navier-Stokes equations [3] were solved to estimate the heat flux on a jet deflector caused due to impingement of the rocket exhaust of a canisterized missile. Based on the theory of computational fluid dynamics [4], the flow field of a rocket engine plume is simulated and analyzed by numerical method.…”

Section: Introductionmentioning

confidence: 99%

Analysis of supersonic free jets and impinging supersonic jets on deflector

Mehta

2023

Simulation Modeling - Recent Advances, New Perspectives, and Applications [Working Title]

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The computational fluid dynamics analysis is carried out to analyze the shock and flow characteristics of under- and over expanded supersonic free jets emanating from convergent-divergent nozzles. Influence of exit Mach number on shock cell lengths are analyzed with the help of density contours and schlieren images. A parameter based on an exit Mach number is obtained to characterize the pressure variation along the jet axis which shows them independent of the exit to ambient pressure ratio. Impingement flow fields over axisymmetric and wedge deflector are investigated employing numerically and compared with experimental results. Effects of jet expansion ratio and distance between the nozzle to deflector apex has been studied at various expansion ratios and distances. Impingement load is computed at various conditions. Pressure distributions over a surface of wedge and axisymmetric jet deflector are computed and compared between them. Pressure load on a diaphragm of a solid motor during lift-off of a satellite launch vehicle having four liquid engines is numerically simulated.

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Section: Introductionmentioning

confidence: 99%

Analysis of supersonic free jets and impinging supersonic jets on deflector

Mehta

2023

Simulation Modeling - Recent Advances, New Perspectives, and Applications [Working Title]

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“…The accumulation and reflection of high temperature gas has an influence on the stability of the flame deflector, as well as the security of the launch process. An efficacious design for the flame deflector structure integral for building a solid foundation for successful launch can reduce adverse effects caused by the recirculation or backdraft of rocket exhaust gas inside the deflector (Basu et al, 2017;Prasad et al, 1994;Sakurai et al, 2017). However, it must be noted that deflection efficiency of the flame deflector is influenced by many geometric parameters (Ignatius et al, 2015;Panda et al, 2014), not least including the jet impingement angle, the separation distance, the exit radius between the deflector surface and floor, and the uplift angle between the deflector floor and horizontal as shown in Figure 1 (Phillips, 1980).…”

Section: Introductionmentioning

confidence: 99%

Numerical study for the flame deflector design of four-engine liquid rockets

Zhou

Zhang²,

2020

Engineering Applications of Computational Fluid Mechanics

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The thermal environment of four-engine liquid rocket exhaust plume impinging on the flame deflector with different impingement and uplift angles is analysed. The supersonic exhaust gas impinging model was established by using the compressible, multi-component, Reynolds-Averaged Navier-Stokes (RANS) equations with the finite volume method. A comparison between the numerical results and experimental data in the literature is made, which verified the validity and accuracy of the numerical model. Additionally, the flow fields of the four-engine rocket impinging on the flame deflector under different impingement and uplift angles are simulated. The results show that high temperatures on the deflector surface mainly occur on the impingement point or the cambered surface. A large impingement angle causes the reverse flow intensity to increase whilst a small angle causes the exhaust gas to deflect a little, a suitable uplift angle can smoothly guide the exhaust gas away from the deflector that the best thermal environment of the deflector channel appears at an impingement angle of 25°and an uplift angle of 5°. This study demonstrates that our model can effectively simulate the impinging flow field, and can be of use for the design of the flame deflector under the multi-engine rocket exhaust gas impact.

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Effect of uplift angle on thermal environment of flame deflector during rocket launch

Zhou

Wang

et al. 2023

Advances in Space Research

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Numerical Simulation of Missile Jet Deflector

Cited by 4 publications

References 16 publications

Analysis of supersonic free jets and impinging supersonic jets on deflector

Analysis of supersonic free jets and impinging supersonic jets on deflector

Numerical study for the flame deflector design of four-engine liquid rockets

Effect of uplift angle on thermal environment of flame deflector during rocket launch

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