Prediction of a propellant tank pressure history using state space methods

Estey, Paul N.; Lewis, David H.; Connor, Maureen

doi:10.2514/3.28355

Cited by 22 publications

(18 citation statements)

References 3 publications

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“…It is treated as saturated hydrogen vapor, whose temperature is equal to that of the liquid/vapor interface, where [1,4,7] T…”

Section: Tank Modelingmentioning

confidence: 99%

“…If the film layer is considered negligibly thin so that one can ignore its mass [1], then the energy balance equation for the CV (f ) can be written aṡ…”

Section: Tank Modelingmentioning

confidence: 99%

“…The wall temperature T w is governed by the heat flow passing through the walls from the environment [1][2][3].…”

Section: Tank Modelingmentioning

confidence: 99%

“…Here, the heat transfer coefficients describe natural convection inside and outside the tank walls [1,10].…”

Section: Tank Modelingmentioning

confidence: 99%

“…The loading of cryogenic spacecraft propellants is an inherently risky and unsafe operation, especially in the case of hydrogen [1][2][3][4]. Therefore, diagnostic solutions are necessary to quickly identify when a fault occurs, so that recovery ac-tions can be taken or an abort procedure can be initiated before system safety is compromised.…”

Section: Introductionmentioning

confidence: 99%

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Model-based diagnostics for propellant loading systems

Daigle

Foygel

Smelyanskiy

2011

2011 Aerospace Conference

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Abstract-The loading of spacecraft propellants is a complex, risky operation. Therefore, diagnostic solutions are necessary to quickly identify when a fault occurs, so that recovery actions can be taken or an abort procedure can be initiated. Model-based diagnosis solutions, established using an in-depth analysis and understanding of the underlying physical processes, offer the advanced capability to quickly detect and isolate faults, identify their severity, and predict their effects on system performance. We develop a physics-based model of a cryogenic propellant loading system, which describes the complex dynamics of liquid hydrogen filling from a storage tank to an external vehicle tank, as well as the influence of different faults on this process. The model takes into account the main physical processes such as highly nonequilibrium condensation and evaporation of the hydrogen vapor, pressurization, and also the dynamics of liquid hydrogen and vapor flows inside the system in the presence of helium gas. Since the model incorporates multiple faults in the system, it provides a suitable framework for model-based diagnostics and prognostics algorithms. Using this model, we analyze the effects of faults on the system, derive symbolic fault signatures for the purposes of fault isolation, and perform fault identification using a particle filter approach. We demonstrate the detection, isolation, and identification of a number of faults using simulation-based experiments.

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“…It is treated as saturated hydrogen vapor, whose temperature is equal to that of the liquid/vapor interface, where [1,4,7] T…”

Section: Tank Modelingmentioning

confidence: 99%

“…If the film layer is considered negligibly thin so that one can ignore its mass [1], then the energy balance equation for the CV (f ) can be written aṡ…”

Section: Tank Modelingmentioning

confidence: 99%

“…The wall temperature T w is governed by the heat flow passing through the walls from the environment [1][2][3].…”

Section: Tank Modelingmentioning

confidence: 99%

“…Here, the heat transfer coefficients describe natural convection inside and outside the tank walls [1,10].…”

Section: Tank Modelingmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

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Model-based diagnostics for propellant loading systems

Daigle

Foygel

Smelyanskiy

2011

2011 Aerospace Conference

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Simulation Research of Vaporization and Pressure Variation in a Cryogenic Propellant Tank at the Launch Site

Chen

Liang

2013

Microgravity Sci. Technol.

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Liquid hydrogen storage design trades for a short-range aircraft concept

Burschyk,

Cabac,

Silberhorn

et al. 2023

CEAS Aeronaut J

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Preliminary design trades for the liquid hydrogen storage system of a short-range aircraft are presented. Two promising insulation methods, namely rigid foam and multilayer insulation, are identified as main design drivers. In addition, the maximal pressure and the shape of the hydrogen storage tank influence the aircraft performance and the insulation efficiency. In this study, the hydrogen storage tanks are integrated in wing pods. The main effects driven by the design parameters are addressed using conceptual and preliminary methods: models are carried out for the storage mass, additional drag, propeller efficiency loss and the dynamical thermodynamic behavior of the liquid hydrogen storage. These effects are coupled making an integrated design method necessary. For the sizing of the liquid hydrogen storage, a multidisciplinary workflow is set up including the aircraft sensitivities on the design mission block fuel. The trade-off study reveals the opposing trend between insulation efficiency and aircraft performance. For the insulation architecture based on rigid foam, the penalties implied by the storage tank on aircraft level and the penalties due to vented hydrogen can be balanced and result in minimal block fuel for the design mission. The application of multilayer insulation avoids venting during the design mission, but has an increased penalty on the aircraft performance compared to rigid foam insulation. Besides the criterion of minimal block fuel, the dormancy time is compared, indicating the thermal efficiency. Applying multilayer insulation, the dormancy time can be increased significantly calling for a discussion of operational requirements for hydrogen-powered aircraft.

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Prediction of a propellant tank pressure history using state space methods

Cited by 22 publications

References 3 publications

Model-based diagnostics for propellant loading systems

Model-based diagnostics for propellant loading systems

Simulation Research of Vaporization and Pressure Variation in a Cryogenic Propellant Tank at the Launch Site

Liquid hydrogen storage design trades for a short-range aircraft concept

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