The Experts below are selected from a list of 213 Experts worldwide ranked by ideXlab platform

Jia-ling Yang - One of the best experts on this subject based on the ideXlab platform.

  • Insulation Performance of Heat-Resistant Material for High-Speed Aircraft Under Thermal Environments
    Journal of Materials Engineering and Performance, 2015
    Co-Authors: Dafang Wu, Yue Wu Wang, Jia-ling Yang
    Abstract:

    Lightweight insulation materials are widely used to thermally protect High-Speed Aircraft, such as missiles. Thermal conductivity is an important parameter used to evaluate the efficiency of a material’s thermal insulation performance. Since thermal conductivities provided from material handbooks or manufacturers are discrete data for different temperature ranges, there is a deviation between those and actual parameters in terms of continuous nonlinear variations. Therefore, this study measures the thermal conductivities of lightweight thermal insulation materials at high temperatures, and the relationship between the thermal conductivity and temperature is obtained. A finite element model of the thermal insulation materials is also established and applied to numerically calculate the thermal insulation properties for high-temperature ceramic fiber insulation materials using the experimentally obtained nonlinear relationship between thermal conductivity and temperature. Additionally, a transient aerodynamic heating experiment simulation system is used to thermally test the same materials; the calculated and experimental results for the same materials are compared, which exhibit good consistency that demonstrates that accurate results can be obtained from the numerical computation using the relationship established from the experimentally measured conductivity and temperature.

  • Fast and High Precision Thermoelectric Potential – Temperature Conversion Method for Aerodynamic Heating Control Systems
    Advanced Materials Research, 2013
    Co-Authors: Da Fang Wu, Yue Wu Wang, Shuang Wu, Jia-ling Yang
    Abstract:

    A fast and high-precision ‘thermoelectric potential - temperature (E-T)’ sensor conversion method for the transient aerodynamic heating control systems of High-Speed Aircraft is proposed. The developed method has the advantages of easy calculation, rapid conversion speed and high calibration precision, and can thus be employed for fast non-linear dynamic control of rapidly-changing temperature fields in the aerodynamic heating process of High-Speed Aircraft.

  • Research on Control of Heat Flux Environment Simulation for High-Speed Aircraft
    Advanced Materials Research, 2013
    Co-Authors: Da Fang Wu, Yue Wu Wang, Jia-ling Yang, Zhen Tong Gao
    Abstract:

    The characteristics of the transient heating control process of aerodynamic simulation experiments are complicated, transient, highly nonlinear, and strongly coupled, which make it difficult or impossible to develop a mathematical model. By using the fuzzy control method, many good qualities (such as robustness, high adaptability to changing parameters, and a short transition process time) can be obtained. Based on the fuzzy control method, a transient aerodynamic heating simulation control system for missiles was established. It was demonstrated that quick dynamic control of the aerodynamic simulation heating process according to the transient and continual change in heat flow on the surface of High-Speed Aircrafts can be completed by using this control system.

Dafang Wu - One of the best experts on this subject based on the ideXlab platform.

  • Insulation Performance of Heat-Resistant Material for High-Speed Aircraft Under Thermal Environments
    Journal of Materials Engineering and Performance, 2015
    Co-Authors: Dafang Wu, Yue Wu Wang, Jia-ling Yang
    Abstract:

    Lightweight insulation materials are widely used to thermally protect High-Speed Aircraft, such as missiles. Thermal conductivity is an important parameter used to evaluate the efficiency of a material’s thermal insulation performance. Since thermal conductivities provided from material handbooks or manufacturers are discrete data for different temperature ranges, there is a deviation between those and actual parameters in terms of continuous nonlinear variations. Therefore, this study measures the thermal conductivities of lightweight thermal insulation materials at high temperatures, and the relationship between the thermal conductivity and temperature is obtained. A finite element model of the thermal insulation materials is also established and applied to numerically calculate the thermal insulation properties for high-temperature ceramic fiber insulation materials using the experimentally obtained nonlinear relationship between thermal conductivity and temperature. Additionally, a transient aerodynamic heating experiment simulation system is used to thermally test the same materials; the calculated and experimental results for the same materials are compared, which exhibit good consistency that demonstrates that accurate results can be obtained from the numerical computation using the relationship established from the experimentally measured conductivity and temperature.

Rimas Vaicaitis - One of the best experts on this subject based on the ideXlab platform.

  • Nonlinear response of composite panels of high speed Aircraft
    Composites Engineering, 1993
    Co-Authors: P. Kavallieratos, Rimas Vaicaitis
    Abstract:

    Abstract The surface thermal protection systems of advanced high speed Aircraft such as the National Aerospace Plane (N.A.S.P.) will be constructed from high temperature resistant composite and intermetallic materials. The various dynamic response studies indicate that under severe aerodynamic, acoustic and thermal loads the response of these surface panels is nonlinear. The equations of motion for nonlinear response of composite surface panels are developed in the space-time domain. A time domain Monte Carlo type approach is used to determine the nonlinear deflection and stress response solutions. The formulation includes surface loads due to nonsteady aerodynamic flow, turbulent boundary layer and engine exhaust noise, oscillating surface shocks and aerodynamic heating. Numerical results are presented for a simply supported laminated composite panel.

  • Nonlinear response and sonic fatigue of high speed Aircraft
    Computational Stochastic Mechanics, 1991
    Co-Authors: Rimas Vaicaitis, P. Kavallieratos
    Abstract:

    The surface thermal protection systems of advanced high speed Aircraft such as the National Aerospace Plane (NASP) will be constructed from high temperature resistant composite and intermetallic materials. The various dynamic response studies indicate that under severe aerodynamic, acoustic and thermal loads the response of these surface panels is nonlinear. The equations of motion for nonlinear response of composite surface panels are developed in space-time domain. A time domain Monte Carlo type approach is used to determine solutions and fatigue live predictions. The formulation includes surface loads due to nonsteady aerodynamic flow, cavity and static pressure, parametric excitations, turbulent boundary layer and engine exhaust noise, oscillating surface shocks and aerodynamic heating. Numerical results are presented for a simplified laminated composite panel.

Yue Wu Wang - One of the best experts on this subject based on the ideXlab platform.

  • Insulation Performance of Heat-Resistant Material for High-Speed Aircraft Under Thermal Environments
    Journal of Materials Engineering and Performance, 2015
    Co-Authors: Dafang Wu, Yue Wu Wang, Jia-ling Yang
    Abstract:

    Lightweight insulation materials are widely used to thermally protect High-Speed Aircraft, such as missiles. Thermal conductivity is an important parameter used to evaluate the efficiency of a material’s thermal insulation performance. Since thermal conductivities provided from material handbooks or manufacturers are discrete data for different temperature ranges, there is a deviation between those and actual parameters in terms of continuous nonlinear variations. Therefore, this study measures the thermal conductivities of lightweight thermal insulation materials at high temperatures, and the relationship between the thermal conductivity and temperature is obtained. A finite element model of the thermal insulation materials is also established and applied to numerically calculate the thermal insulation properties for high-temperature ceramic fiber insulation materials using the experimentally obtained nonlinear relationship between thermal conductivity and temperature. Additionally, a transient aerodynamic heating experiment simulation system is used to thermally test the same materials; the calculated and experimental results for the same materials are compared, which exhibit good consistency that demonstrates that accurate results can be obtained from the numerical computation using the relationship established from the experimentally measured conductivity and temperature.

  • Fast and High Precision Thermoelectric Potential – Temperature Conversion Method for Aerodynamic Heating Control Systems
    Advanced Materials Research, 2013
    Co-Authors: Da Fang Wu, Yue Wu Wang, Shuang Wu, Jia-ling Yang
    Abstract:

    A fast and high-precision ‘thermoelectric potential - temperature (E-T)’ sensor conversion method for the transient aerodynamic heating control systems of High-Speed Aircraft is proposed. The developed method has the advantages of easy calculation, rapid conversion speed and high calibration precision, and can thus be employed for fast non-linear dynamic control of rapidly-changing temperature fields in the aerodynamic heating process of High-Speed Aircraft.

  • Research on Control of Heat Flux Environment Simulation for High-Speed Aircraft
    Advanced Materials Research, 2013
    Co-Authors: Da Fang Wu, Yue Wu Wang, Jia-ling Yang, Zhen Tong Gao
    Abstract:

    The characteristics of the transient heating control process of aerodynamic simulation experiments are complicated, transient, highly nonlinear, and strongly coupled, which make it difficult or impossible to develop a mathematical model. By using the fuzzy control method, many good qualities (such as robustness, high adaptability to changing parameters, and a short transition process time) can be obtained. Based on the fuzzy control method, a transient aerodynamic heating simulation control system for missiles was established. It was demonstrated that quick dynamic control of the aerodynamic simulation heating process according to the transient and continual change in heat flow on the surface of High-Speed Aircrafts can be completed by using this control system.

Omar Khan - One of the best experts on this subject based on the ideXlab platform.

  • Computed Effect of Wing Tip Configuration on Wing Load Characteristics of a High Speed Aircraft
    53rd AIAA Aerospace Sciences Meeting, 2015
    Co-Authors: Jehanzeb Masud, Omar Khan
    Abstract:

    The wing tip configuration of an Aircraft is important structurally and aerodynamically. The formation of wing tip vortices not only add to the induced drag but also decrease the lift produced by the wing. This aspect becomes significantly important for high speed Aircraft that have low aspect ratio wings. In this paper effect of wing tip configurations of a high speed Aircraft equipped with wingtip missile on its wing load characteristics is presented. Normal force coefficient has been computed for the wing panel of the Aircraft for both with and without wingtip missile in transonic fight regime and a wide range of angle of attack. It is observed that the wing tip missile considerably alters the strength and structure of the wingtip vortices. It has also observed that as much as 20% increase in normal force coefficient occurs when the wingtip missile is mounted. This difference between the wing loads of clean wing and missile mounted wing diminishes as the angle of attack is increased, this is due the shifting low pressure region on the wing upper surface from wing tip towards wing root as the root strake becomes effective.