Development and Validation of Fluid/Thermodynamic Models for Spacecraft Propulsion Systems

Hearn, H. C.

doi:10.2514/2.5807

Cited by 10 publications

(9 citation statements)

References 5 publications

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“…Pressure increase in the pressurization process is linear, as prescribed by Eq. (14), and the tank pressure is found to fall continuously in the readiness check period due to the cooling of ullage gas by the convective heat loss to the liquid oxygen surface as well as the evaporation of liquid oxygen. It is found that the pressure drop after the end of the pressurization period is approximately 7 and 13% of pressurization level at 100 and 200 s into the readiness check period.…”

Section: Resultsmentioning

confidence: 98%

“…Heat transfer between the liquid and the gas is generally characterized as the natural convection due to the relatively low gas movement and mixing intensity [14]. The heat transfer coefficient on the gas side is evaluated using the following correlation of the Nusselt number for natural convection on the horizontal surface [15]:…”

Section: Heat Transfer At the Liquid-gas Interfacementioning

confidence: 99%

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Transient thermal analysis of a cryogenic oxidizer tank in the liquid rocket propulsion system during the prelaunch helium gas pressurization

Kim

et al. 2012

J. Engin. Thermophys.

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The transient thermal behavior in the cryogenic oxidizer tank for the liquid propulsion system of the KSLV-I satellite launching space vehicle is theoretically investigated for the pressurization process by gaseous helium injection followed by the readiness check stage. The numerical model is established using the transient mass and energy conservation of oxygen/helium mixtures both in ullage and liquid regions. At the liquid-gas interface, various modes of heat and mass transfer are considered, including the liquid evaporation and the helium absorption. The present study focuses on the effects of the increasing pressurization level on some of important properties that should be considered in the propulsion system design, such as tank pressure, ullage gas temperature, and evaporation of liquid oxygen. Particularly, the tank pressure drop after the pressurization is investigated in the proposed design of propulsion system. Also, the effect of the initial loading of liquid oxygen in the oxidizer tank is studied and discussed. As for the helium absorption into the liquid region, its mass is negligibly small and it should not be the concern in design and operation of the oxidizer tank system.

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Section: Resultsmentioning

confidence: 98%

Section: Heat Transfer At the Liquid-gas Interfacementioning

confidence: 99%

Transient thermal analysis of a cryogenic oxidizer tank in the liquid rocket propulsion system during the prelaunch helium gas pressurization

Kim

et al. 2012

J. Engin. Thermophys.

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“…Besides, several numerical models have been developed to predict the pressurization performances. Majumdar , Hearn , and Karimi et al . applied a thermodynamic equilibrium model to investigate the pressurization behaviors of a discharge process.…”

Section: Introductionmentioning

confidence: 99%

“…Besides, several numerical models have been developed to predict the pressurization performances. Majumdar [28] , Hearn [29] , and Karimi et al [30] applied a thermodynamic equilibrium model to investigate the pressurization behaviors of a discharge process. Roudebush [31] and Masters [32] developed a onedimensional model to take into consideration the formation of thermal stratification in the ullage during discharge.…”

Section: Introductionmentioning

confidence: 99%

Numerical investigation of pressurization performance in cryogenic tank of new‐style launch vehicle

Wang

Zhao

et al. 2013

Asia-Pacific J Chem Eng

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The pressurization performance of cryogenic tanks during discharge is investigated by a computational fluid dynamic approach. A series of cases accounting for the effects of various influence factors such as inlet gas temperature, ramp time of inlet gas temperature, wall thickness, outflow rate, injector structure, and liquid supercooling on pressurization behaviors are computed and analyzed successively. Several valuable conclusions have been drawn as follows: (1) Increasing inlet gas temperature, applying a thin wall to construct the tank, and increasing the outflow rate are beneficial to the reduction of gas requirements, (2) Ramp process and use of a straight pipe injector may lead to an excessive pressure drop at the beginning of discharge, (3) Use of straight pipe injector can remarkably reduce the gas requirement but lead to a large loss of liquid propellant as well as a large weight of final ullage gas, and (4) The mode of mass transfer within the tank is close related to the injector structure and liquid supercooling. A trend of mass transfer toward evaporation can be observed by increasing the liquid temperature, especially for the straight pipe injector case. Generally, the results of this paper might be beneficial to the design and optimization of a pressurization system. © 2013 Curtin University of Technology and John Wiley & Sons, Ltd.

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“…Pressure reducing regulator (PRR) and check valve (CV) are two types of components widely applied to various liquid propulsion systems and energy systems [1][2][3][4][5][6][7][8][9]. The former is used to reduce the pressure of inlet high-pressure fluid to the defined value and stabilize it within a certain range; the latter is used to prevent reverse flow.…”

Section: Introductionmentioning

confidence: 99%

Dynamic modeling and simulation of an integral bipropellant propulsion double-valve combined test system

Yang

Wang

Xia³

et al. 2017

Acta Astronautica

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For the pressure reducing regulator and check valve double-valve combined test system in an integral bipropellant propulsion system, a system model is established with modular models of various typical components. The simulation research is conducted on the whole working process of an experiment of 9MPa working condition from startup to rated working condition and finally to shutdown. Comparison of simulation results with test data shows: five working conditions including standby, startup, rated pressurization, shutdown and halt and nine stages of the combined test system are comprehensively disclosed; valve-spool opening and closing details of the regulator and two check valves are accurately revealed; the simulation also clarifies two phenomena which test data are unable to clarify, one is the critical opening state in which the check valve spools slightly open and close alternately in their own fully closed positions, the other is the obvious effects of flow-field temperature drop and temperature rise in pipeline network with helium gas flowing. Moreover, simulation results with consideration of component wall heat transfer are closer to the test data than those under the adiabatic-wall condition, and more able to reveal the dynamic characteristics of the system in various working stages.

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Development and Validation of Fluid/Thermodynamic Models for Spacecraft Propulsion Systems

Cited by 10 publications

References 5 publications

Transient thermal analysis of a cryogenic oxidizer tank in the liquid rocket propulsion system during the prelaunch helium gas pressurization

Transient thermal analysis of a cryogenic oxidizer tank in the liquid rocket propulsion system during the prelaunch helium gas pressurization

Numerical investigation of pressurization performance in cryogenic tank of new‐style launch vehicle

Dynamic modeling and simulation of an integral bipropellant propulsion double-valve combined test system

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