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propellant
Analysis and operational results show that the control system can meet all technical requirements for high energy composite solid propellant manufacturing.
      
Comprehensive Substantiation of the Structure and Parameters of a Power-Propellant System for a Spacecraft
      
The conceptual and methodological principles, as well as some results of the comprehensive substantiation of a technical approach at early stages of design of power-propellant systems (PPS), are presented.
      
The time of turn is minimized, as well as the functional having a meaning of the propellant consumption.
      
The estimations of the propellant consumption for a realization of the programmed turn are made.
      
The coplanar problem of minimizing propellant consumption in impulsive transfer between circular boundary orbits is investigated.
      
The feasibility of organization of a system of controlling this spacecraft with a small consumption of propellant mass is briefly investigated.
      
A numerical example is considered, in which the propellant consumption is analyzed for the cases of transfers with and without constraints.
      
Studying it is of practical interest, particularly for the optimization of the ignition of a liquid propellant and the development of granulating apparatus in the chemical industry [2].
      
Quasi-One-Dimensional Model of Combustion of Sandwich Heterogeneous Solid Propellant
      
This model includes the heat- and mass-transfer and kinetic-gasdynamic processes in the gas phase above the surface of burning solid propellant, as well as the heat-transfer processes in solid material.
      
Computational Models of Combustion of Nonmetallized Heterogeneous Propellant
      
Monte Carlo simulation algorithms are given which are intended for the calculation of the spectral emissivity of jets of combustion products of solid-propellant rocket motors (SRM).
      
The Outflow of a Two-Phase Gas-Liquid Mixture from the Mixing Head of a Gas Generator when Starting a Liquid-Propellant Rocket E
      
This paper deals with the problems of mathematical simulation of the start-up of a liquid-propellant rocket engine (LPRE), which are associated with two-phase flows in the mixing heads (MH) of combustors and gas generators.
      
Results are given of calculation of spectral directional emissivity of model jet of a solid-propellant engine.
      
A cryogenic piston made from solid carbon dioxide was first used to compress and heat the propellant gas in the second gun stage.
      
The strategy of biological reclamation of ecosystems in the zones of chemical pollution with asymmetrical dimethylhydrazine (ADMH), a highly toxic propellant, is proposed.
      
"Sakhalin" pulsed MHD 500 MW power system based on solid-propellant fuel
      
The instability of the working process in the combustion chamber of a solid-propellant rocket engine
      
 

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