Design of Rocket Engine for Spacecraft Using CFD-Modeling

Zubanov, Vasilii; Egorychev, Vitaliy; Shabliy, L. S.

doi:10.1016/j.proeng.2015.04.093

Cited by 13 publications

(3 citation statements)

References 2 publications

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“…where the index ĵ refers to the position that, along the trajectory, corresponds to the maximum value of the P rs batt . In view of ( 5), (6), and (7), and by recalling that at cruising speed the capsule acceleration is null, the second term of the objective function, say T 2 in (15), can be written as in (17).…”

Section: Optimal Assessment Of the Scaling Factormentioning

confidence: 99%

Design of a Hyperloop System MockUp

Tudor

Govoni

Leipold

et al. 2022

2022 IEEE 25th International Conference on Intelligent Transportation Systems (ITSC)

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The thorough development of the hyperloop system does require the availability of reduced-scale models. They can be used for the fast prototyping of various components, as well as for studying critical phenomena that takes place in this peculiar transportation system without the need to develop complex and expensive full-scale setups. In this respect, in this paper, we present a process for the optimal assessment of the scaling factor; it is to be used for the development of a reduced-scale hyperloop model, starting from the knowledge of the technical characteristics of its full-scale counterpart.The objective of the proposed process is the minimisation of the difference between the normalized power profiles associated with the reduced-scale and full-scale models of a hyperloop capsule traveling along a pre-defined trajectory with a predetermined speed profile. By considering the hyperloop fullscale model as a reference, we propose a set of equations that link the above-mentioned metric with the constraints dictated by the kinematics of the hyperloop capsule, the capsule's battery-energy storage and propulsion systems, the capsule's aerodynamics, and the operating environmental conditions. We then derive a closed-form expression for the assessment of the optimal scaling factor and eventually use it to study the scaleddown version of an application example of a realistic hyperloop system.

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Section: Optimal Assessment Of the Scaling Factormentioning

confidence: 99%

Design of a Hyperloop System MockUp

Tudor

Govoni

Leipold

et al. 2022

2022 IEEE 25th International Conference on Intelligent Transportation Systems (ITSC)

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“…In addition, they can facilitate the understanding of test results, since every relevant physical field is accessible. Consequently, CFD is an integral part of the design process of combustion chambers [6][7][8][9]. Traditionally, Reynolds Averaged Navier-Stokes (RANS) solvers have been extensively used in industry due to their low computational cost.…”

Section: Introductionmentioning

confidence: 99%

Subgrid Turbulent Flux Models for Large Eddy Simulations of Diffusion Flames in Space Propulsion

Martinez-Sanchis,

Sternin,

Banik

et al. 2024

Fluids

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Subgrid scale models for unresolved turbulent fluxes are investigated, with a focus on combustion for space propulsion applications. An extension to the gradient model is proposed, introducing a dependency on the local burning regimen. The dynamic behaviors of the model’s coefficients are investigated, and scaling laws are studied. The discussed models are validated using a DNS database of a high-pressure, turbulent, fuel-rich methane–oxygen diffusion flame. The operating point and turbulence characteristics are selected to resemble those of modern combustors for space propulsion applications to support the future usage of the devised model in this context.

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“…The calculated prediction of the nature and characteristics of the fluxes in the engine elements allows to identify possible design errors even before the product is embodied in the metal, and find ways to improve existing engines which much lower costs in comparison with the experimental study. However, using of popular in recent years CFD-simulation technologies of hydrodynamic processes of liquid rocket engines [1,2], allows to perform even optimization researches on high-level models (in fact, virtual prototypes), but in the domestic rocket-engines industry it is still not widespread. Therefore, at the present time, young specialists are faced with the task of developing and mastering CFD-simulation technologies, which in the conditions of modern re-equipment of computational tools (the emergence of cluster computing technologies, supercomputers), will provide a fast pace of designing, manufacturing and testing LPRE aggregates [3,4,5].…”

Section: Introductionmentioning

confidence: 99%

The Technique for CFD-Simulation of Fuel Valve from Pneumatic-Hydraulic System of Liquid-Propellant Rocket Engine

Shabliy

Malov

Bratchinin

2018

IOP Conf. Ser.: Mater. Sci. Eng.

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Abstract. In the article the description of technique for simulation of valves for pneumatichydraulic system of liquid-propellant rocket engine (LPRE) is given. Technique is based on approach of computational hydrodynamics (Computational Fluid Dynamics -CFD). The simulation of a differential valve used in closed circuit LPRE supply pipes of fuel components is performed to show technique abilities. A schematic and operation algorithm of this valve type is described in detail. Also assumptions made in the construction of the geometric model of the hydraulic path of the valve are described in detail. The calculation procedure for determining valve hydraulic characteristics is given. Based on these calculations certain hydraulic characteristics of the valve are given. Some ways of usage of the described simulation technique for research the static and dynamic characteristics of the elements of the pneumatic-hydraulic system of LPRE are proposed.

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Design of Rocket Engine for Spacecraft Using CFD-Modeling

Cited by 13 publications

References 2 publications

Design of a Hyperloop System MockUp

Design of a Hyperloop System MockUp

Subgrid Turbulent Flux Models for Large Eddy Simulations of Diffusion Flames in Space Propulsion

The Technique for CFD-Simulation of Fuel Valve from Pneumatic-Hydraulic System of Liquid-Propellant Rocket Engine

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