scholarly journals Fluid Dynamics of Thrust Vectorable Submerged Nozzle

Fluids ◽  
2021 ◽  
Vol 6 (8) ◽  
pp. 278
Author(s):  
Sergey Denisikhin ◽  
Vladislav Emelyanov ◽  
Konstantin Volkov
Keyword(s):  
Cylindrical Channel ◽  
Geometric Model ◽  
Combustion Products ◽  
Vortical Flow ◽  
Solid Rocket Motor ◽  
Time Step ◽  
Gas Dynamic ◽  
Computational Mesh ◽  
Nozzle Block ◽  
Solid Rocket

A numerical simulation of the gas-dynamic processes in the thrust vectorable nozzle of the solid rocket motor is considered. Construction of a geometric model and a generation of computational mesh, and reconstruction of model and mesh at each time step are discussed. Calculations of the flowfield of combustion products in the pre-nozzle chamber and nozzle block are carried out for various angles of nozzle rotation. The distributions of the gas dynamic quantities in the pre-nozzle volume corresponding to the outflow of the combustion products from the cylindrical channel and star-shaped channel are compared, as well as the solutions of the problem obtained with quasi-stationary and unsteady formulations. The effects of the channel shape on the distribution of flow quantities and formation of a vortical flow structure in the nozzle block are discussed.

NON-STATIONARY BEHAVIOR OF A SOLID PROPELLANT CHARGE FOR NOZZLELESS SOLID ROCKET MOTORS UNDER GAS-DYNAMIC LOAD

2021 ◽  
pp. 48-59
Author(s):  
I.G. Voropaeva ◽  
◽  
A.A. Kozulin ◽  
L.L. Min’kov ◽  
E.R. Shrager ◽  
...  
Keyword(s):  
Burning Rate ◽  
Solid Propellant ◽  
Solid Mechanics ◽  
Stokes Equations ◽  
Combustion Products ◽  
Conjugate Problem ◽  
Navier Stokes ◽  
Solid Rocket Motor ◽  
Propellant Charge ◽  
Solid Rocket

The numerical solution to a conjugate problem of an unsteady flow of combustion products in a flow path of the nozzleless solid rocket motor (SRM) and the oscillation of a solid propellant charge under the action of the forces directed from combustion products is considered. The Navier-Stokes equations for a compressible viscous gas are used to mathematically describe the flow of the combustion products. To model the charge oscillations, the equations of solid mechanics are applied, which take into account the propellant hyperelasticity. Pressure distributions and the propellant burning rate along the charge channel are presented for different models of the propellant burning rate. It is revealed that at the stage of SRM design, the use of the burning rate law, determined by pressure in the head of the combustion chamber, is more preferable in order to assess the internal ballistic characteristics. The solution to the conjugate problem shows that in the nozzleless SRM with the propellant having low Young's modulus, resonance can occur, which causes uncontrolled charge oscillations.

Gas-dynamic flow in a spinning, coning solid rocket motor

1993 ◽  
Vol 9 (1) ◽  
pp. 35-42 ◽  
Author(s):  
D. L. Misterek ◽  
J. W. Murdock ◽  
S. Koshigoe
Keyword(s):  
Rocket Motor ◽  
Solid Rocket Motor ◽  
Dynamic Flow ◽  
Gas Dynamic ◽  
Solid Rocket

Optimization of Solid Rocket Motor Quenching in Gas Dynamic Tunnels during Firing Bench Tests

2017 ◽  
Vol 743 ◽  
pp. 269-272
Author(s):  
Galina Ivanovna Shaidurova ◽  
Sergey Vladimirovich Patrulin ◽  
Aleksandr Aleksandrovich Nazartsev
Keyword(s):  
Environmental Safety ◽  
Design Parameters ◽  
Solid Rocket Motor ◽  
Solid Rocket Motors ◽  
Rocket Motors ◽  
Bench Tests ◽  
Gaseous Products ◽  
Gas Dynamic ◽  
Solid Rocket ◽  
Fuel Components

The paper presents the experimental results that allow determining optimum quenching conditions for solid rocket motors (SRM) at the stage of firing bench tests (FBT) in gas dynamic tunnels (GDT) with altitude simulation. The work describes main design approaches for quenching unit enabling reduced thermal insulation (TI) destruction by 15-20% after finish of SRM operation due to aftereffect decrease, as well as reduced values of scattering of TI undamaged layer thickness up to 10% owing to uniform cooling.If necessary, drying accompanied with emissions of TI gaseous products and remnants of k-phase fuel components is run in GDT, which allows improving environmental safety of working facilities and shortening the time for evaluation of SRM design parameters.

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