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 PowerPropellant 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 powerpropellant 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].


QuasiOneDimensional Model of Combustion of Sandwich Heterogeneous Solid Propellant


This model includes the heat and masstransfer and kineticgasdynamic processes in the gas phase above the surface of burning solid propellant, as well as the heattransfer 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 solidpropellant rocket motors (SRM).


The Outflow of a TwoPhase GasLiquid Mixture from the Mixing Head of a Gas Generator when Starting a LiquidPropellant Rocket E


This paper deals with the problems of mathematical simulation of the startup of a liquidpropellant rocket engine (LPRE), which are associated with twophase 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 solidpropellant 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 solidpropellant fuel


The instability of the working process in the combustion chamber of a solidpropellant rocket engine

