Redistribution of Energy during Interaction of a Shock Wave with a Temperature Layered Plasma Region at Hypersonic Speeds

The paper is devoted to the problem of the interaction between a shock wave and a thermally stratified energy source for the purpose of supersonic/hypersonic flow control realization. The effect of the thermally stratified energy source on a shock wave with the Mach number in the range of 6–12 is researched numerically based on the Navier-Stokes system of equations. Redistribution of specific internal energy and volume density of kinetic energy behind the wave front is investigated. Multiple manifestations of the Richtmyer-Meshkov instability has been obtained which has caused the blurring and disappearance of shock wave and contact discontinuity fronts in density fields. A study of the efficiency of using a stratified energy source instead of a homogeneous one with the same value of the full energy is carried out. The agreement with the available experimental data for the shock wave Mach number 6 has been obtained.

FLOW SIMULATION OVER REENTRY CAPSULE AT SUPERSONIC AND HYPERSONIC SPEEDS. THE COMPARE BETWEEN TWO REENTRY CAPSULES. PART 1

This study presents flow simulation over the reentry capsule at supersonic and hypersonic speeds. Numerical algorithms solve for the CFD method, which is produced using help ANSYS Fluent 19.2. The using GPU core to get a solution faster. The main purpose – flow simulation and numerical analysis reentry capsule; understand the behavior of supersonic and hypersonic flow and its effect on the reentry capsule; compare temperature results for the range Mach numbers equals 2–6. This study showed results on velocity counters, on temperature counters and vector of velocity for range Mach numbers equals 2–6. This study demonstrates the importance of understanding the effects of shock waves and illustrates how the shock wave changes as the Mach number increases. For every solves, the mesh had adapted for pressure gradient and velocity gradient to get the exact solution. As a result of the obtained solution, it is found that a curved shock wave appears in front of the reentry capsule. The central part of which is a forward shock. An angular expansion process is observed, which is a modified picture of the Prandtl- Mayer flow that occurs in a supersonic flow near the sharp edge of the expanding region. It is revealed that with an increase in the Mach number, the shock wave approaches the bottom of the reentry capsule, and there is also a slope of the shock to the flow direction, with an increase in the Mach number. The relevance and significance of this problem for the design of new and modernization of old reentry capsules.

Применение индукционных датчиков в исследованиях быстропротекающих процессов

When testing on a rocket track, one of the most difficult problems is the system for controlling and launching pyrotechnic devices at a given coordinate. The way of start-up and device for its implementation, is intended to provide actuation of pyrotechnic means during acceleration of the rocket trains on the rails rocket catapult track to hypersonic speeds with ejection test subject in free flight. The method is based on the principle of generating current pulses for triggering pyrotechnic devices of moving stages of a rocket train using induction sensors. The same principle makes it possible to implement a non-contact method for starting recording systems and a device for measuring the average speed of a thrown object in continuous media. The method is based on the principle of generating triggering signals (rectangular pulses of positive polarity) for starting the recording equipment with synchronization of the launch along the path in a given coordinate and measuring the speed of the object being thrown at the time of its passage through the measuring section. The methods of starting recording systems and the results obtained as a result of hydrodynamic and terradynamic experiments are presented.

FLOW SIMULATION OVER REENTRY CAPSULE AT SUPERSONIC AND HYPERSONIC SPEEDS. THE COMPARE BETWEEN TWO REENTRY CAPSULES. PART 2

This study is a continuation of the first part “Flow simulation over reentry capsule at supersonic and hypersonic speeds. The comparison between two reentry capsules. Part 1”. This study presents a comparison between two reentry capsules, which are made in Russia. Numerical algorithms solve for the CFD method, which is produced using help ANSYS Fluent 19.2. The using GPU core to get a solution faster. The main purpose – flow simulation and numerical analysis two tips reentry capsule understand the behavior of supersonic and hypersonic flow and its effect on the reentry capsule; compare temperature results and compare drag coefficient for the range Mach numbers equals 2–6. This study showed results on velocity counters, on temperature counters and drag coefficient for range Mach numbers equals 2–6. This study demonstrates the importance of understanding the effects of shock waves and illustrates how the shock wave changes as the Mach number increases. For every solves, the mesh had adapted for pressure gradient and velocity gradient to get the exact solution. As a result of the obtained solution, it is found that the “Prototype 2” reentry vehicle has a lower temperature a lateral surface, than the “Prototype 1”, but a higher temperature over the frontal segment at Mach number M = 6. A general trend has been observed, which is that the resistance drag coefficient decreases with increasing Mach number, which is associated with high height and low density and pressure values. The relevance and significance of this problem for the design of new and modernization of old reentry capsules.