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propellants
An experimental method for determination of critical conditions of condensation of metal propellants of electric jet engines (EJEs) on the surfaces of materials of spacecraft thermoregulating covers is presented.
      
Mechanism of combustion of fire-extinguishing propellants based on potassium nitrate
      
A study is made of one-dimensional nonstationary problems of the combustion and detonation of aerosuspensions of unitary fuels or propellants, which contain the oxidant as well as the combustible material (gunpowder, high explosives).
      
The temperature of attainable superheating of rocket propellants is also calculated by the theory of homogeneous nucleation.
      
It is demonstrated that the employed kinetic model of thermochemical processes provides an adequate description of the available experimental data on the rate of combustion of AP- and PBR-based solid propellants.
      
Physical and chemical models are treated which are employed for numerical analysis of the processes of combustion of nonmetallized sandwich heterogeneous propellants on the basis of ammonium perchlorate and hydroxyl-terminated polybutadiene.
      
New approaches to the development of high-performance hydrocarbon propellants
      
An approach to express screening of promising hydrocarbon propellants, based on the calculation of the specific impulse of an engine from the results of quantum-chemical calculation of their heats of combustion, was suggested.
      
Polycyclic and framework hydrocarbons with small rings were suggested as promising propellants.
      
Effect of carbon fiber on the burning rate of model propellants
      
The use of fractal for prediction of burning rate of composite solid propellants
      
By using the fractal geometry it is possible to calculate the actual AP (Ammonium Perchlorate) surface area and oxidizer-binder interface fractal dimension in the prediction of burning rate of composite solid propellants.
      
Cavitation is one of the troublesome problems in rocket turbo pumps, and since most of high-efficiency rocket propellants are cryogenic fluids, so called "thermodynamic effect" becomes more evident than in water.
      
The most commonly used fully halogenated CFC propellants in aerosol cans were found to be CFC11, CFC12 and CFC114.
      
Capillary gas chromatography of double-base propellants
      
Determination of diphenylamine and its mono-derivatives in single-base gun propellants during aging by high performance liquid c
      
The separation and quantitative determination of diphenylamine and its mono-derivatives in single-base gun propellants during aging was investigated by High Performance Liquid Chromatography (HPLC).
      
Composite propellants are considered as major sources of chemical energy for rocket propellants.
      
Cu-Cr-O nanocomposites that can be used as additives for the catalytic combustion of AP(ammonium perchlorate)-based solid-state propellants were synthesized via a citric acid(CA) complexing approach.
      
Addition of the as-synthesized Cu-Cr-O nanocomposites as catalysts enhances the burning rate as well as lowers the pressure exponent of the AP-based solid-state propellants considerably.
      
 

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