A5047756916- Spacecraft Dynamics and Control
- Space Satellite Systems and Control
- Astro and Planetary Science
- Aerospace Engineering and Control Systems
- Diamond and Carbon-based Materials Research
- Guidance and Control Systems
- Advanced Surface Polishing Techniques
- Robotic Path Planning Algorithms
- Rocket and propulsion systems research
- Space Science and Extraterrestrial Life
- Computational Fluid Dynamics and Aerodynamics
- Space exploration and regulation
- Spacecraft and Cryogenic Technologies
- Advanced materials and composites
- Combustion and flame dynamics
- Advanced Control Systems Optimization
- Technology Assessment and Management
- Systems Engineering Methodologies and Applications
- Planetary Science and Exploration
- Spacecraft Design and Technology
- Aerodynamics and Acoustics in Jet Flows
- Product Development and Customization
- Bone Tissue Engineering Materials
- Robotics and Sensor-Based Localization
- Minerals Flotation and Separation Techniques
China Astronaut Research and Training Center
2013-2024
National University of Defense Technology
2011-2013
The problem of synchronous flying-around control for uncontrolled tumbling target spacecraft is investigated in the paper. Firstly, relative motion equations chaser and established based on line sight (LOS) coordinate system, scenario analyzed. Secondly, attitude model established, described by Modified Rodriguez Parameters (MRPs). transformed into a two-dimensional instantaneous rotation plane LOS (IRPL). sliding mode controller designed to direction vertical IRPL, stability In order verify...
System-of-systems (SoS) architecture is crucial in managing complex and interconnected systems. However, the description modeling of SoS pose significant challenges require a structured organized approach. In this study, metamodel for that considers both structural behavioral perspectives defined. The then mapped to ontologies are enhanced with flow-based extension characterize views. On basis, an capability ontology (SoSCO) operational (SoSOO) built factors, relationships, flows. A...
We propose two approaches based on feedforward control and model-predictive control, respectively, to solve the station-keeping problem of an electric-propulsion geostationary Earth orbit (GEO) satellite, whose thrusters are mounted robotic arms its anti-nadir face. This novel configuration enables a wider range thrust direction, making it possible regard direction as variables. To this problem, we present quick controller (QFFC) fuel-optimal model predictive (FOMPC). The QFFC is developed...
The optimization of lunar soft landing trajectory is an control problem with non-linear free terminal time and constrained.. application the Chebyshev pseudospectral described on optimal problems. This method employs Nth Lagrange polynomial approximations for state variables to transform differential equations algebraic equations. Finally transformed a nonlinear programming problem. In process solving using matlab, flying are used as variables. Simulation results demonstrate methodology...
The lunar landing stage can be divided into three phases: de-orbit, powered descent and terminal approach. Most fuel is consumed during the phase. Therefore, optimization problem of minimum energy typically focused on this In paper, a highly precise three-dimensional dynamics model derived, main constraints for manned mission are presented. To solve complex with strict constraints, hybrid method which combines collocation method-Gauss pseudospectral (GPM) shooting proposed. approach GPM used...
Spacecraft science missions to planets or asteroids have historically visited only one several celestial bodies per mission. The research goal of this paper is create a trajectory design algorithm that generates allowing spacecraft visit significant number during single For the problem global optimization, even with recent advances in low-thrust full enumeration not possible. This work presents an traverse searching space practical fashion and generate solutions. flight sequence determined...
The exploration of the Moon has always been a hot topic. determination Moon-to-Earth transfer opportunity and design precise trajectory play important roles in manned missions. It is still difficult problem to determine return for accurate atmospheric re-entry landing, through which actual can be easily obtained later. This paper proposes an efficient integrated method window searching optimization considering constraints Earth landing. First, analytical geometry-based proposed state point...