A5015010920- Aerospace Engineering and Control Systems
- Space Satellite Systems and Control
- Spacecraft Dynamics and Control
- Plasma Diagnostics and Applications
- Rocket and propulsion systems research
- Astro and Planetary Science
- Solar and Space Plasma Dynamics
- Field-Flow Fractionation Techniques
- Electrohydrodynamics and Fluid Dynamics
- Aerospace, Electronics, Mathematical Modeling
- Spacecraft Design and Technology
- Ionosphere and magnetosphere dynamics
- Heat Transfer and Mathematical Modeling
- Mechanics and Biomechanics Studies
- Advanced Research in Science and Engineering
- Gas Dynamics and Kinetic Theory
- Material Science and Thermodynamics
- Mechanical Systems and Engineering
- Photocathodes and Microchannel Plates
- Technical Engine Diagnostics and Monitoring
- Spacecraft and Cryogenic Technologies
- Gas Sensing Nanomaterials and Sensors
- Geodetic Measurements and Engineering Structures
- Advanced Theoretical and Applied Studies in Material Sciences and Geometry
- Numerical methods for differential equations
Moscow State University
2022-2024
Lomonosov Moscow State University
2021-2024
Moscow Aviation Institute
2022-2023
Central Aerohydrodynamic Institute
2001-2020
The problem of the optimal control spacecraft (SC) with an electric ramjet (ER) to change orbital parameters is considered. ER uses air as a fuel. Optimal determined by solving on conditional maximum local (at current point orbit) impact perturbing acceleration functional, assuming perturbations' smallness compared gravity. An approximate synthesis thrust vector obtained in view power limitation. Parametric investigations apogee's changes, depending SC parameters, were carried out....
Improving the thruster efficiency is a crucial challenge for development of space electric propulsion systems, especially advanced air-breathing thrusters utilizing surrounding rarefied atmosphere as fuel. A significant reduction in power consumption can be achieved by using field emission (FE) cathodes that do not require heating and have highest energy efficiency. In this work, we study FE from nano-graphite thin films, consisting carbon nanostructures with high aspect ratio, demonstrate...
A problem of through optimization fail-safe branched trajectories launchers in view aerodynamic load constraints and restrictions on ground impact areas separated parts (SP) is considered. The failsafety regarded to the possibility a recoverable vehicle (RV) return from any point ascent trajectory landing points without excess allowable g-loads. So, purpose determination launcher optimal control all branches: main, corresponding an active injection leg, side branches, SP fall imaginary RV...
Abstract The attention to specific problems of guarantee sub-orbital flight safety is accented. It displayed, that physical limitations on ascent and reentry segments form conflict requirements configurations the launcher vehicle. algorithm construction permissible parameter ranges determining a shape such vehicles their critical regimes offered. developed technique demonstrated as an application analyze possibility use Angara-1 for space tourism purposes.
The problem of changing the apogee altitude orbits with ultralow perigee (altitude 120–250 km) is considered. To compensate for aerodynamic drag spacecraft, an air-breathing electric propulsion (ABEP) used, fuel which gases outboard atmosphere. decrease in efficiency ABEP increase angle attack and possibility operation only at a sufficient gas concentration ionization chamber are taken into account. solved on basis Pontryagin maximum principle under assumption that thrust small compared to...
The problem of spacecraft stabilization in ultra-low (120–250 km for the Earth) orbits with help air-breathing electric propulsion (ABEP), which uses gases surrounding atmosphere as a propellant, is considered. Qualitative differences ABEP from traditional are emphasized and, on basis fundamental laws mechanics and electrodynamics, necessary conditions existence closed substantiated.