Progress in research on composite cryogenic propellant tank for large aerospace vehicles

Liu, Geoffrey; Ma, Bin; Feng, Liqiang; Huang, Wenxuan; Xu, Baosheng; Qu, Lijie; Yang, Yusen

doi:10.1016/j.compositesa.2021.106297

Cited by 48 publications

(17 citation statements)

References 86 publications

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“…The development of large cryogenic composite tanks with all-composite materials without metal lining has also become an important direction for lightweight arrow structures. 1,2 Compatibility between the polymer matrix and liquid oxygen (LOX) must be solved to develop a composite tank. Epoxy resins (EPs) have found a wide range of applications in low temperature fields due to their excellent mechanical properties, low shrinkage, strong adhesion, moisture resistance, solvent resistance, chemical resistance and corrosion resistance.…”

Section: Introductionmentioning

confidence: 99%

A phosphorus-containing imidazole derivative towards the liquid oxygen compatibility and toughness of epoxy resin

Wang

Hou

et al. 2022

RSC Adv.

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Section: Introductionmentioning

confidence: 99%

A phosphorus-containing imidazole derivative towards the liquid oxygen compatibility and toughness of epoxy resin

Wang

Hou

et al. 2022

RSC Adv.

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“…When formulating the problem statement, it was assumed that a sample of gel fuel is located on the side of a metal cylinder heated to high temperatures (Figure 1). The cylinder temperature was 203 K (a typical cryogenic storage temperature for gel fuels [25]). When a fuel is used at low temperatures, its initial temperature is one of the main factors affecting the inertia of the combustion process [26,27].…”

Section: Dominance Of Conductive Heat Flux On the Surface Of A Gel Fuel Samplementioning

confidence: 99%

Critical Conditions for the Ignition of a Gel Fuel under Different Heating Schemes

Gaidukova

Стрижак

2021

Energies

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A model was developed to research the critical conditions and time characteristics of the ignition of gel fuels in the course of conductive, convective, radiant and mixed heat transfer. MATLAB was used for numerical modeling. Original MATLAB code was established pursuant to the developed mathematical model. For gel fuel ignition at initial temperatures corresponding to cryogenic storage conditions with different heating schemes, a numerical analysis of interconnected processes of heat and mass transfer in the chemical reaction conditions and exothermic and endothermic phase transitions was conducted. The model was tested by comparing the theoretical results with the experimental data. Dependencies were established between the key process characteristic (i.e., the ignition delay time) and the ambient temperature when the following parameters were varied: emissivity, heat emission coefficient, activation energy and pre-exponential factor of the fuel vapor oxidation reaction. The critical values of the main parameters of the energy source were determined. For these values, gel fuel ignition conditions were consistently realized for each heating scheme. The critical heat fluxes necessary and sufficient for the ignition of typical gel fuels were determined.

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“…Solid rocket motors are devices powered by burning chemical propellant, mainly composed of combustion chamber, propellant grain, ignition torch and nozzle, which have the advantages of high energy density, simple structure and low cost, and have long been widely used in the power system of rockets, missiles and sounding rockets and other equipment [1]. Solid propellant is the power source of solid rocket motor, which is composed of polymer matrix and solid particles, and has a specific geometric configuration to ensure that the propellant column can be burned according to the predetermined initial combustion surface and the law of combustion surface retreat.…”

Section: Introductionmentioning

confidence: 99%

Research progress on crack propagation behavior of solid propellant

Wu¹,

Fu²,

Li³

2023

AETR

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Crack sprouting will lead to the mechanical properties of propellant degradation, and the additional combustion surface formed by crack propagation may cause over-pressurization, resulting in uneven combustion of propellant, significantly changing the thrust characteristics of the engine, reducing the range of the vehicle, and may even cause catastrophic accidents such as explosions. Therefore, the study of crack propagation law of solid rocket propellant pillar is an important basis to ensure the structural integrity and safety of the engine. In order to study the crack propagation pattern of propellant pillar under different working conditions, three aspects of propellant crack initiation criterion, crack propagation model, and crack propagation influencing factors are systematically reviewed. On this basis, the next research focus is sorted out, and it is considered that the construction of crack propagation model by establishing a multi-scale model, the characterization of crack propagation by using various test characterization means, and the analysis of damage evolution under the coupling of multiple working conditions will be the next research focus.

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Progress in research on composite cryogenic propellant tank for large aerospace vehicles

Cited by 48 publications

References 86 publications

A phosphorus-containing imidazole derivative towards the liquid oxygen compatibility and toughness of epoxy resin

A phosphorus-containing imidazole derivative towards the liquid oxygen compatibility and toughness of epoxy resin

Critical Conditions for the Ignition of a Gel Fuel under Different Heating Schemes

Research progress on crack propagation behavior of solid propellant

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