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heat shield
Use of sensitivity functions in the problem of designing a multilayer heat shield
      
An approach is proposed for solving the problem of designing a multilayer heat shield with a prescribed structure from the restrictions on its temperature.
      
Investigation of the Serviceability of the Heat Shield of the Orbital Aircraft "Buran" under the Conditions of Radiant Heating o
      
This paper gives the mathematical model of three-dimensional transpiration cooling control system in heat shield.
      
Two re-entry type heat shield geometries were then tested with the experimental drag forces being compared with a Modified-Newtonian prediction.
      
The actual problem in a nuclear reactor involves a volumetric heat generation in the debris falling over the heat shield plate under failed conditions of the reactor and heat is removed by a decay heat exchanger serving as a sink.
      
In this study we have reduced this transient problem to a quasi-steady problem with a prescribed temperature on the heat shield plate.
      
A simple but comprehensive distributed parameter integral model has been developed for predicting the temperature distribution of the shield and the protected component for a variety of heat shield systems.
      
Aerothermodynamic Aspects of Entry Probe Heat Shield Design
      
The telescope axis is oriented normal to the spherical surface of the Probe's rear heat shield which is needed for heat protection of the scientific payload during the Probe's entry into the Jovian atmosphere.
      
The material thickness of the heat shield determines the lower energy threshold of the particle species investigated during the Probe's pre-entry phase.
      
The people who did much of the test work in the search for a suitable heat shield material for the Apollo spacecraft have turned their attention toward fire protection through materials.
      
It is known [1-3] that in order to provide heat shield or to improve the aerodynamics of the body strong injection of cooling gas into the supersonic stream is utilized.
      
During the atmospheric re-entry of space shuttles, the thermal constraints due to the hypersonic velocity can lead to very extensive damage on materials of the protective heat shield (oxidation, thermal shock, etc.).
      
In this study, samples of an IN939 alloy heat shield with both a metal bond coat and a ceramic thermal barrier coating have been heated in air at high temperature for up to 2000 hours to assess the long term stability of the metal bond coat.
      
Technique for investigation of heat transfer boundary conditions during study of heat shield layer breakdown processes
      
The finite-element method was applied to calculate the thermal state and the state of stress and strain of a wedge-shaped model with a heat-resistant coating (heat shield) subjected to heat cycling by a gas stream.
      
We obtained data on the influence of the technological factors and of the thickness of the heat shield on the kinetics of the state of thermal stress of the material of the models.
      
Transient thermal strains at temperatures up to 2000°F were measured with a water-cooled Tuckerman optical strain gage shielded from heat transfer by a cooled radiant-heat shield.
      
Wall pressure fluctuations over a bulbous heat shield of a satellite launch vehicle
      
 

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