Slow and steady wins the race!
Graduated from Moscow Aviation Institute (MAI). Specialty “Aircraft”. Qualification of mechanical engineer for aircraft was awarded.
Studied and graduated from Lomonosov Moscow State University. Specialty “Mathematics”. Qualified as a mathematician.
Engineer, senior engineer, senior researcher at the Department of Aircraft Design of Moscow Aviation Institute.
Correspondence postgraduate course at Moscow Aviation Institute.
Candidate thesis for the degree of Candidate of Technical Sciences in the specialty “Aircraft design and construction” was defended.
Assistant, senior lecturer, associate professor of the Department №601 “Aircraft Design” of Moscow Aviation Institute.
Academic title of Associate Professor at the Department of “Aircraft Design” was awarded.
Doctoral thesis for the degree of Doctor of Technical Sciences in the specialty 05.07.02 “Aircraft design and construction” was defended.
Professor of the Department of Space systems and rocket engineering at Moscow Aviation Institute.
Academic title of Professor at the Department of “Aircraft Design” was awarded.
Senior researcher, leading researcher, chief researcher of the Research Institute of Applied Mechanics and Electrodynamics of MAI.
Chief specialist and leading specialist of the Federal State company “Lavochkin Research and Production Association”
Academician of International Academy of Astronautics (IAA).
Professor of the Department of “Space Flight Mechanics” of the Institute of Applied Technical and Economic Research and Expertise of RUDN University.
Professor of the Department of Mechanics and Mechatronics of the Institute of Space Technologies of RUDN University.
Gives a course of lectures to RUDN University students: “Interplanetary Flight Path design”.
- Analyzed the required perfection of a nuclear electric rocket propulsion system (specific mass of the installation) for the implementation of a manned Mars expedition. Analyzed this required perfection as a function of the time of the expedition and the mass of the space complex being put into the base earth orbit.
- Analyzed the influence of the characteristics of the power plant when using an electric propulsion system in the mercury research project.
- Analyzed the rational characteristics of the solar power plant of a spacecraft (SC) with an electric rocket propulsion system for the Solar research project. Considered the direct (without gravitational maneuvers) launch of the SC into a low heliocentric orbit with a large inclination to the plane of the solar equator.
- Showed that at the beginning of an energetically complex interplanetary flight, it is advisable to use a heliocentric Earth - to - Earth flight with a gravitational maneuver near the Earth. The trajectory of the heliocentric flight is implemented using an electric propulsion system. This maneuver allows us to significantly increase the hyperbolic excess speed and expands the transport capabilities of the SC. It was shown how the transport capabilities of space systems based on medium-sized (Soyuz-2) and heavy-class (Soyuz-2) launch vehicles expand when using such a flight scheme and a solar electric propulsion system with an electric power of 5 kW.
- Analyzed the change in the optimal thrust profile of an electric rocket propulsion system (the law of engine on - off) as a function of the characteristics of the transport system for space transport tasks.
- Developed a method for optimizing complex interplanetary flight schemes (flights with a chain of gravitational maneuvers) of the SC with an electric propulsion system. The method uses three stages. At the first stage, the problem of optimizing the flight path to the destination planet using gravitational maneuvers and additional speed pulses in deep space was analyzed. Used the method of evolutionary strategy with adaptation of the covariance matrix. At the second stage, each of the heliocentric sections (planet-planet) of the route under consideration was optimized separately. At the third stage, the multipoint boundary value problem of end-to-end optimization was solved. The entire set of necessary optimality conditions for gravity maneuvers were met.
- Analyzed several schemes for launching the SC into heliocentric orbits to study the Sun (project “INTERHELIO-PROBE”). Showed that the use of an electric rocket propulsion system at the initial stage of a heliocentric flight and a system of gravitational maneuvers makes it possible to bring a sufficiently large mass to the final working orbit of the SC in a relatively short time (for example, 5 years). Analyzed a number of chains of gravitational maneuvers that ensure the launch of the SC into working orbits and identified flight patterns that can be recommended for use.
- Studied the problem of parrying trajectory disturbances that may occur during an interplanetary flight of the SC with an electric rocket propulsion system due to the temporary impossibility of regular use of the engine. Showed that an abnormal engine shutdown should be provided for when designing the interplanetary trajectory of the SC. Proposed a new approach, taking into account the need to parry the trajectory perturbation associated with the emergency shutdown of the electric propulsion system. Concluded that it is advisable to adjust the nominal trajectories to increase the maximum permissible time for an abnormal engine shutdown. It was shown that optimization of the characteristics of additional passive sections (their position on the trajectory and duration) leads to an increase in the maximum permissible time of emergency engine shutdown to a level that can satisfy the transport system designer.
- Design and ballistic analysis of space transportation systems;
- Space flight mechanics of a spacecraft with low-thrust engines;
- Design of trajectories in the implementation of complex schemes of interorbital and interplanetary flights.