2.1.2020 Analysis of development trends of design parameters and basic characteristics of missiles for the advanced multiple launch rocket systems

The formalization of the complex task to optimize design parameters, trajectory parameters and motion control programs for the guided missiles capable of flying along the ballistic, [...]

12.1.2024 Hardening of steels modifying their surfaces with ion-plasma nitriding in glow discharge

Heat-resistant MoSi2–NbSi2 and Cr–Ni coatings for rocket engine combustion chambers and respective vacuum-arc deposition technology/ 74th International Astronautical Congress [...]

8.1.2024 Theoretic-experimental evaluation of the solid-propellant grain erosive burning

And in the process of propellant grain combustion, erosive burning often takes place (increase of propellant burning rate depending on combustion products flow rate [...]

5.1.2024 Assessment of risk of toxic damage to people in case of a launch vehicle accident at flight

Using the zone of toxic damage to people during the fall of the failed launch vehicle, which is proposed to be represented by a combination of two figures: a semicircle and a [...]

10.1.2020 Calculation and selection of parameters for a propellant consumption diagram of dual-thrust main SRM

The equations obtained show that the required parameters of diagrams (including consumption-thrust characteristics difference between the starting and cruise modes) can be ensured [...]

3.1.2020 Analysis of the unsteady stress-strain behavior of the launch vehicle hold-down bay at liftoff

Firstly, the unsteady heat fields on the hold-down bay surface are calculated by means of the semi-empirical method, which is based on the simulated results of the combustion [...]

12.1.2017 Static Performance Prediction of Hot-Gas Flapper-Nozzle Actuator

2017 (1); 78-83 Language: Russian Annotation: The basic mathematical relations are considered to construct static characteristics of nozzle-shutter twostage piston pneumatic drive [...]

20.1.2020 Studying the possibility of alternating delivery of rocket propellant wastes to a common thermal neutralization facility

The advantages of thermal neutralization units are considered, their operating principle is described, by the example of high-temperature toxic rocket propellants, the chemical [...]

16.1.2020 Parameters of the supersonic jet of a block propulsion system, flowing into a gas duct, considering chemical kinetics of gas-cycle transformations

The presented work contains simulation of liquid rocket engine combustion products jet flowing into the gas duct at the rocket lift-off, taking into account the following [...]

12.1.2020 Modification of technology as the main course in the military transport aircraft development

the possibility of basing on poorly prepared sites with a runway length of less than 800 m in the short take-off and landing (STL) mode, especially for operational tactical [...]