Assessment of Using Electric Pumps on Hybrid Rockets

Gegeoglu, Kaan; Kahraman, Mehmet; Üçler, Çağlar; Karabeyoğlu, Arif

doi:10.2514/6.2019-4124

Cited by 5 publications

(2 citation statements)

References 3 publications

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“…For the small thrust size of an HPRM, a gas-pressurized system is enough to feed the oxidizer or fuel to the combustion chamber, which is filled with solid fuel or oxidizer [100,106,109,110]. However, in the case of large thrust and deep throttling, there is a limit to using the gas pressure method, so a pump is required [160,161]. For this reason, the three or four governing equations are needed depending on the size of the system.…”

Section: Mathematical Modeling Of Chemical Propulsion Systemsmentioning

confidence: 99%

Numerical Simulation of Chemical Propulsion Systems: Survey and Fundamental Mathematical Modeling Approach

Cha

2023

Aerospace

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This study deals with the mathematical modeling and numerical simulation of chemical propulsion systems (CPSs). For this, we investigate and summarize a comprehensive collection of the simulation modeling developments of CPSs in academic works, applications, and industrial fields. Then, we organize and analyze the simulation modeling approaches in several ways. After that, we organize differential-algebraic Equations (DAEs) for fundamental mathematical modeling consisting of the governing Equations (ordinary differential equations, ODEs) for the components and other equations derived from several physical rules or characteristics (algebraic equations or phenomenological equations, AEs) and then synthesize and summarize the fundamental structures of analytic mathematical modeling by types (liquid-propellant rocket engines, solid-propellant rocket motors, and hybrid-propellant rocket motors) of CPSs.

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Section: Mathematical Modeling Of Chemical Propulsion Systemsmentioning

confidence: 99%

Numerical Simulation of Chemical Propulsion Systems: Survey and Fundamental Mathematical Modeling Approach

Cha

2023

Aerospace

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“…After that, Solda, Waxenegger-Wilfing, Rachov and Kwak evaluated the total mass of engines with different supply systems, which aroused greater interest in electric pump supply system [7][8][9][10]. Casalino et al researched the improvement of upper-stage hybrid rocket motor performance by using hydrogen peroxide electric pump [11][12][13]. The result shows that using an electric pump system can reduce the pressure of storage tank and greatly reduce the mass of storage tank and gas cylinder.…”

Section: Introductionmentioning

confidence: 99%

The effect of reflux schemes in hydrogen peroxide electric pump on anti-cavitation of inducer

Tian

et al. 2023

J. Phys.: Conf. Ser.

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Hydrogen peroxide electric pump supply system can provide an improvement to hybrid rocket motor performance. Due to the physical and chemical properties of hydrogen peroxide, a canned pump scheme is more suitable to be used in hybrid rocket motor. The high-temperature liquid between the rotor and stator of the electric pump, returning to the inlet of the inducer, has a considerable influence on the anti-cavitation performance. The numerical simulation results show that the optimal reflux scheme is different when the inlet pressure range of the inducer is different. When the inlet pressure of the inducer is 0.4 MPa, the performance of the inducer is less affected by the reflux schemes, and the optimal scheme is the axial scheme in the simulation. When the inlet pressure is 0.12 MPa and there is a large cavitation area in the inducer, the radial reflux scheme is better than the axial and mixed reflux. When the inlet pressure is 0.1 MPa and the cavitation areas almost extend to the whole blade passage, the radial reflux scheme is much better than the axial and mixed reflux.

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Conceptual Design and Optimization of Hybrid Rockets

Messinger¹

2021

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Assessment of Using Electric Pumps on Hybrid Rockets

Cited by 5 publications

References 3 publications

Numerical Simulation of Chemical Propulsion Systems: Survey and Fundamental Mathematical Modeling Approach

Numerical Simulation of Chemical Propulsion Systems: Survey and Fundamental Mathematical Modeling Approach

The effect of reflux schemes in hydrogen peroxide electric pump on anti-cavitation of inducer

Conceptual Design and Optimization of Hybrid Rockets

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