Concept of Non-Ablative Thermal Protection System for Hypersonic Vehicles

This work represents a conceptual stage of the project on development of technology of the combined thermal protection system for hypersonic vehicles heat-stressed surfaces with use of technology of the thermionic power cell and thermal protection system with an external emission of electrons. The relevance of this work is to develop thermal protection system technology for aircraft, enabling prolonged controlled flight at hypersonic speeds, while providing low aerodynamic resistance and relative weight, the consistency of the geometric shape of the hypersonic vehicles leading edge. The various using types of thermal protection system are compared and the necessity to develop a new type of it using the effect of thermionic emission of electrons is proved. The scheme and the possible material composition of thermionic power cell with a reversed geometry of the electrodes are given. The problem of the choice of material for emission surface of the system with external electron emission and its manufacturing technology are discussed. Using cesium intercalated graphite as one of the possible coating materials is reviewed. A sequence of forthcoming studies is formulated at the stage of transition to the design basis for the operation of thermal protection of this type.

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Heat Transfer and Failure Mode Analyses of Ultrahigh-Temperature Ceramic Thermal Protection System of Hypersonic Vehicles

Mathematical Problems in Engineering ◽

10.1155/2014/412718 ◽

2014 ◽

Vol 2014 ◽

pp. 1-11 ◽

Cited By ~ 3

Author(s):

Tianbao Cheng ◽

Weiguo Li ◽

Wei Lu ◽

Yushan Shi

Keyword(s):

Heat Transfer ◽

Tensile Stress ◽

Compressive Stress ◽

Thermal Protection ◽

Lower Surface ◽

Thermal Protection System ◽

Protection System ◽

Hypersonic Vehicles ◽

Middle Plane ◽

Ultrahigh Temperature

The transient temperature distribution of the ultrahigh-temperature ceramic (UHTC) thermal protection system (TPS) of hypersonic vehicles is calculated using finite volume method. Convective cooling enables a balance of heat increment and loss to be achieved. The temperature in the UHTC plate at the balance is approximately proportional to the surface heat flux and is approximately inversely proportional to the convective heat transfer coefficient. The failure modes of the UHTCs are presented by investigating the thermal stress field of the UHTC TPS under different thermal environments. The UHTCs which act as the thermal protection materials of hypersonic vehicles can fail because of the tensile stress at the lower surface, an area above the middle plane, and the upper surface as well as because of the compressive stress at the upper surface. However, the area between the lower surface and the middle plane and a small area near the upper surface are relatively safe. Neither the compressive stress nor the tensile stress will cause failure of these areas.

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A THERMAL PROTECTION SYSTEM FOR LIQUID HYDROGEN FUEL TANKAGE IN HYPERSONIC VEHICLES

Thermophysics of Spacecraft and Planetary Bodies ◽

10.1016/b978-0-12-395737-5.50048-2 ◽

1967 ◽

pp. 849-864

Author(s):

C. Lynn Johnson

Keyword(s):

Thermal Protection ◽

Liquid Hydrogen ◽

Thermal Protection System ◽

Protection System ◽

Hypersonic Vehicles ◽

Hydrogen Fuel

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A thermal protection system for liquid hydrogen fuel tankage in hypersonic vehicles

10.2514/6.1967-297 ◽

1967 ◽

Author(s):

C. JOHNSON

Keyword(s):

Thermal Protection ◽

Liquid Hydrogen ◽

Thermal Protection System ◽

Protection System ◽

Hypersonic Vehicles ◽

Hydrogen Fuel

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Aerothermoelastic Load Calculation for Hypersonic Vehicles Based on Multiphysics Coupled Analysis

Mathematical Problems in Engineering ◽

10.1155/2018/6051924 ◽

2018 ◽

Vol 2018 ◽

pp. 1-15

Author(s):

Hao Chen ◽

Min Xu ◽

Zihua Qiu ◽

Dan Xie ◽

Yabin Wang

Keyword(s):

Thermal Protection ◽

Thermal Protection System ◽

Coupling Method ◽

Protection System ◽

Aerodynamic Heating ◽

Hypersonic Vehicles ◽

High Fidelity ◽

Coupling Analysis ◽

Thermal Dynamics ◽

Load Calculation

To fulfill the design objective of a structure and thermal protection system, accurate load environment prediction is very important, so we present a high-fidelity aerothermoelastic load calculation method based on a partitioned computational fluid dynamics/computational structural dynamics/computational thermal dynamics (CFD/CSD/CTD) coupling analysis. For the data transformation between the CFD/CSD/CTD systems, finite element interpolation (FEI) is explored, and a shape-preserving grid deformation strategy is achieved via radical basis functions (RBFs). Numerical results are presented for validation of the proposed CFD/CSD/CTD coupling analysis. First, a simply supported panel in hypersonic flow is investigated for results comparison of the proposed coupling method and previous work. Second, a hypersonic forebody is investigated to explore the aerothermoelastic effects while considering the feedback between deformation and aerodynamic heating. The results show that the CFD/CSD/CTD coupling method is accurate for analysis of aerothermoelasticity. In addition, considering the aerothermoelastic effect, the shear force and bending movement increase with time before 900s and decrease after 900s, and at 900s increased percentages of 5.7% and 4.1% are observed, respectively. Therefore, it is necessary to adopt high-fidelity CFD/CSD/CTD coupling in the design of a structure and thermal protection system for hypersonic vehicles.

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