A5065348066- Spacecraft Dynamics and Control
- Space Satellite Systems and Control
- Inertial Sensor and Navigation
- Astro and Planetary Science
- Satellite Communication Systems
- Spacecraft Design and Technology
- Geophysics and Gravity Measurements
- Magnetic Bearings and Levitation Dynamics
- Aerospace Engineering and Energy Systems
- Muscle activation and electromyography studies
- Aerospace Engineering and Control Systems
- Geophysics and Sensor Technology
- Lightning and Electromagnetic Phenomena
- Earthquake Detection and Analysis
- Sports Performance and Training
- Cardiovascular and exercise physiology
- Adaptive Control of Nonlinear Systems
- Ionosphere and magnetosphere dynamics
Keldysh Institute of Applied Mathematics
2019-2024
Moscow Center For Continuous Mathematical Education
2021
The paper presents a study of decentralized control for satellite formation flying mission that uses differential lift and drag to enforce the relative positioning requirements. All spacecraft are equipped with large sunlight reflectors so that, given appropriate lighting conditions, as whole can be made visible from Earth configurable pixel image in sky. analyzes possibility achieving pre-defined lineup by implementing aerodynamic-based through orientation incoming airflow. required...
A servicing spacecraft motion control approach for the problem of on-orbit truss structure assembly is developed in this paper. It considered that a cargo container with rod set and are orbit initially. The procedure based on free-flight between structure’s specified points. equipped two robotic manipulators capable attaching to holding rods. In addition, can repulse from given relative velocity using manipulator, so receive impulses. repulsion vector calculated order reach target point...
A decentralized control algorithm for the construction of a tetrahedral configuration using differential lift and drag forces is proposed in this paper. Four 3U CubeSats launched LEO are considered. Satellite attitude-controlled motion relative to incoming airflow provides required order change translational motion. The developed allows one track reference trajectories satellites at vertices tetrahedron shape size. influence initial launch conditions on controlled studied
In this article, five feedback magnetic attitude control algorithms are compared in terms of stabilization accuracy and implementation problems. The strategies classic Lyapunov with scalar gain; the same strategy matrix gain a specific gain-tuning procedure; sliding variable surface; linear quadratic regulator constructed for special time-invariant system higher degree than initial time-varying system; controllable trajectory developed using particle swarm optimization. A new surface...
О р д е н а Л и ИНСТИТУТ ПРИКЛАДНОЙ МАТЕМАТИКИ имени М.В.Келдыша Р о с й к м у У.В.Монахова, Д.С.Иванов Формирование роя наноспутников помощью децентрализованного аэродинамического управления учетом коммуникационных ограничений Москва -2018 Монахова У.В., Иванов Д
Предложено управление движением роя малых космических аппаратов после кластерного запуска для удержания в заданной области и обеспечения межспутниковой связи. Целью алгоритма управления является устранение среднего параметра дрейфа достижение требуемого сдвига относительной траектории вдоль трансверсали. На основе линейной модели относительного движения проведено аналитическое исследование предложенного движения. С помощью численного моделирования орбитального спутников рое была проведена...
The paper proposes an algorithm for angular motion control of a dynamically elongated spacecraft. is based on the direct Lyapunov method using matrix coefficients. calculated mechanical torque implemented magnetic attitude system. Control parameters are selected Floquet theory to ensure convergence trajectory required one. A numerical study controlled achieve gravitational equilibrium 3U CubeSat carried out.
The paper considers the dynamic aspects of possibility carrying out a space mission to study gamma-ray flares terrestrial origin. We propose an approach selection reference orbits that allows satellites form equilateral triangle in near-equatorial zone. In addition, algorithm for phasing by latitude argument using aerodynamic drag forces is proposed.
The problem of joining a formation flying small satellites up immediately after their separation from the launch vehicle is considered in paper. A distributed control based on aerodynamic drag to eliminate relative drift between proposed attitude satellite performed by magnetic coils.
Algorithms for small satellite's attitude determination and control system are studied. ADCS consists of sun sensor, angular velocity magnetometer, reaction wheels magnetorquers. In order to determine current satellite a set Kalman Filters developed Lyapunov-based controller is implemented. The capabilities validated using computer simulation different mission scenarios including orbital inertial stabilization.