The Influence of Configuration on the Range of a Hypersonic Flight Vehicle under Space Limitations

2019 ◽  
pp. 77-86
Author(s):  
S.V. Presnyakov ◽  
V.A. Usachev ◽  
V.V. Koryanov ◽  
N.V. Kudryavtseva
Keyword(s):  
Solid Propellant ◽  
Rocket Engine ◽  
Flight Vehicle ◽  
Hypersonic Flight Vehicle ◽  
Hypersonic Flight ◽  
Solid Propellant Rocket ◽  
Solid Propellant Rocket Engine ◽  
The Russian Federation ◽  
Cruise Flight ◽  
Propellant Rocket

The article examines the influence of the configuration of a hypersonic flight vehicle with a hori-zontal cruise flight section on the maximum flight range under the conditions of limiting dimen-sions. The ram jet and the solid propellant rocket engine were chosen as the cruise engine, and re-spective calculations were performed. The hypersonic flight vehicle was configured based on the design patented in the Russian Federation, under the condition of launch using the 3S14 universal launcher. Dependencies of the maximum range on the ratio between the launch mass to the payload were analysed. The mass efficiency indicator for a two-stage ballistic missile was chosen as a crite-rion for a comparison with other available alternatives.

scholarly journals ROCKET-PROPELLED ANTI-PERSONNEL GRENADE LAUNCHERS EQUIPPED WITH DIFFERENT WARHEADS

2020 ◽  
pp. 93-104
Author(s):  
V. Khailov ◽  
V. Chebotar ◽  
V. Kuzmenko
Keyword(s):  
Russian Federation ◽  
Solid Propellant ◽  
Rocket Engine ◽  
State Tests ◽  
Joint Forces ◽  
Solid Propellant Rocket ◽  
Solid Propellant Rocket Engine ◽  
The Russian Federation ◽  
Propellant Rocket

At present, the issue of creating means of destruction of domestic production in Ukraine, including rocket- propelled anti-personnel grenade launchers equipped with different warheads (thermobaric, assault, fragmentation and incendiary) is acute. With the advent of new incendiary, thermobaric agents and explosives, the development of multi-purpose rocket-propelled grenade launchers has become one of the promising trends. All of the above is proven by the experience of the Anti-Terrorist Operation/Joint Forces Operation in eastern Ukraine. Analysis of flame troops combat operations during the anti-terrorist operation showed the need to intensify efforts to develop new rocket-propelled anti-personnel grenade launchers with thermobaric, assault, fragmentation and incendiary warheads. Leading specialists from the Russian Federation and Western countries also came to this conclusion. Thus, in recent years in Russia there have been developed, passed state tests and adopted RGSH-1 with a modular warhead in the thermobaric version, RGSH-2 rocket projectile with thermobaric warhead and RPG-32 "Barkas" equipped with thermobaric or tandem cumulative grenade. Nowadays, several enterprises of the defense complex, one of which is the ТОV "Vognyana Varta", are dealing with the creation of a modern domestic rocket-propelled anti-personnel grenade launcher in Ukraine. ТОV "Vognyana Varta" on its own initiative has been developing a rocket-propelled anti-personnel grenade launcher with different warheads using new incendiary, thermobaric mixtures and explosives. The classification of rocket-propelled grenade launchers (flamethrowers) is carried out. The design of modern ammunition to rocket-propelled grenade launchers (flamethrowers) and types of warheads for them are considered. Calculations of a solid-propellant rocket engine for modern rocket-propelled grenade launchers (flamethrowers) are given.

Numerical Computation of Specific Impulse and Internal Flow Parameters in Solid Fuel Rocket Motors with Two-Phase Сombustion Products

2021 ◽  
pp. 98-107
Author(s):  
T.S. Sultanov ◽  
G.A. Glebov
Keyword(s):  
Combustion Chamber ◽  
Condensed Phase ◽  
Solid Fuel ◽  
Solid Propellant ◽  
Rocket Engine ◽  
Specific Impulse ◽  
Two Phase ◽  
Solid Propellant Rocket ◽  
Solid Propellant Rocket Engine ◽  
Propellant Rocket

Eulerian --- Lagrangian method was used in the Fluent computational fluid dynamics system to calculate motion of the two-phase combustion products in the solid fuel rocket motor combustion chamber and nozzle. Condensed phase is assumed to consist of spherical particles with the same diameter, which dimensions are not changing along the motion trajectory. Flows with particle diameters of 3, 5, 7, 9, and 11 μm were investigated. Four versions of the engine combustion chamber configuration were examined: with slotted and smooth cylindrical charge channels, each with external and submerged nozzles. Gas flow and particle trajectories were calculated starting from the solid fuel surface and to the nozzle exit. Volumetric fields of particle concentrations, condensed phase velocities and temperatures, as well as turbulence degree in the solid propellant rocket engine flow duct were obtained. Values of particles velocity and temperature lag from the gas phase along the nozzle length were received. Influence of the charge channel shape, degree of the nozzle submersion and of the condensate particles size on the solid propellant rocket engine specific impulse were determined, and losses were estimated in comparison with the case of ideal flow

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