Query: solid propellant rocket engine

title: Determining non stationary state of solid propellant rocket engine model based on numerical conjugate problem solution

title: Theoretical and Experimental Heat Transfer in Solid Propellant Rocket Engine
abstract: Accurate determination of heat flux is an important task not only in the designing aspect, but also in the performance analysis of rocket engines. In this purpose, this work deals with the heat flux determination in a combustion chamber through the inverse method. In this approach, the transient heat flux is determined from the experimental temperature data measured at the outer sidewall of the rocket engine. In this work the physical phenomenon was modeled by the transient one dimensional heat equation in cylindrical coordinates and the material properties of the chamber were considered constant. Furthermore, the model is solved using the inverse heat conduction problem with least squares modified by the addition of Tikhonov regularization term of zero order. Moreover, the sensitivity coefficients were obtained by Duhamel's theorem. Through the regularization parameter, it was able to generate acceptable results even when using data with considerable experimental errors.

title: Numerical Research of Intra Chamber Transient Processes Dynamics during Starting Operation of the Solid Propellant Rocket Engine with Special Arrangement

title: Comparison of Turbulence Models in OpenFOAM for 3D Simulation of Gas Flow in Solid Propellant Rocket Engine
abstract: The aim of this paper is to compare various mathematical models simulating the turbulent flow in a solid propellant rocket engine. For comparison, the most frequently used models were chosen for simulations of flow in the S5 rocket engine. For this type of engine experimental data are available allowing comparison of the simulations with reality. The LES Smagorinsky model provided the best results, while type RANS models appeared to be less suitable for this task.

title: BEHAVIOR ANALYSIS SIMULATION OF SOLID PROPELLANT ROCKET ENGINE.

title: Algorithm for computing kinematic characteristics of a flexible joint controlling a swiveling nozzle in a solid propellant rocket engine

title: Modeling Heat Strength Characteristics of Structural Elements of a Solid Propellant Rocket Engine Manufactured Using Prototyping
abstract: Elementy konstruktsii raketnogo dvigatelia tverdogo topliva kharakterizuiutsia slozhnost'iu izgotovleniia i posleduiushchei sborki. K vozmozhnym tekhnologiiam, obespechivaiushchim snizhenie vremennykh i resursnykh zatrat na proizvodstvo detalei etogo dvigatelia, otnositsia tekhnologiia lazernogo spekaniia poroshkov metallopolimernykh kompozitsii (poroshkovoe 3D prototipirovanie) otlichitel'noi osobennost'iu kotoroi iavliaetsia posloinoe sozdanie detali v protsesse spekaniia poroshka. Odnako vnedrenie tekhnologii poroshkovogo prototipirovaniia pri izgotovlenii vysokootvetstvennykh detalei sopriazheno s riadom problem, v tom chisle s nekotorym snizheniem mekhanicheskikh kharakteristik poluchaemogo materiala. Predlozhena metodika rascheta teploprochnostnykh kharakteristik konstruktivnykh elementov raketnogo dvigatelia tverdogo topliva s ispol'zovaniem algoritmov chislennogo modelirovaniia. Provedena otsenka izmeneniia koeffitsienta zapasa prochnosti elementa, vypolnennogo s pomoshch'iu tekhnologii prototipirovaniia, v zavisimosti ot uslovii raboty dvigatelia (davleniia v kamere sgoraniia, temperatury konstruktsii) V rezul'tate matematicheskogo modelirovaniia teploprochnostnykh kharakteristik silovogo karkasa sopla raketnogo dvigatelia tverdogo topliva pokazana vozmozhnost' primeneniia razrabotannoi metodiki pri vybore parametrov elementov konstruktsii takikh dvigatelei.

title: Rocket and solid propellant rocket engine
abstract: FIELD: engines and pumps.  rocket contains a pulling solid propellant rocket engine and a pushing rocket engine. The pulling solid propellant rocket engine includes a nozzle cluster formed by several inclined nozzles evenly distributed around the circumference, mounted on the rear bottom, as well as a rear joint assembly. A bucket is attached to the solid propellant rocket engine housing, with an inner cylindrical surface of which a pallet with a payload contacts, associated with the pushing rocket engine. The length and mass of the solid propellant rocket engine exceed the length and mass of the pushing rocket engine. Another invention relates to a soild propellant rocket engine comprising a housing with bottoms, a rear joint assembly, a nozzle cluster, and a bucket connected to the front bottom. A pallet with a payload contacts with the inner cylindrical surface of the bucket. The bucket is connected to the rear bottom and has an open rear end. The cross sectional area of the rear joint assembly is determined by the pull bending load equal to the sum of the thrust of the soild propellant rocket engine and flight loads.  group of inventions allows to increase the energy mass efficiency of a rocket and solid propellant rocket engine, to simplify their design and increase reliability, to minimize the dimensions of the rocket in its initial state. 10 cl, 2 dwg

title: The development of an elastomeric material for the internal heat resistant coating of solid propellant rocket engine

title: Dynamics of the composite casing of solid propellant rocket engine under the influence of impulse loads describing the work processes in the engine