Development of method for selecting motion control laws of space optical system on based diffractive membranes during transfer into geostationary orbit

The article presents a formulation of a problem of trajectory optimization using low-thrust engines for an optical space system based on diffractive membranes. A methodology, where first stage nominal trajectories and control programs are selected and then corrected at the longrange guidance, has been developed for solving the problem of optimizing the trajectories of a flight to a geostationary orbit. At the final stage, algorithms for terminal control are formed, which allows to deliver a cosmic optical system based on diffraction membranes to a given point in the geostationary orbit. The end result is acquisition of Pareto-optimal solutions in the coordinates "characteristic speed-duration of the flight", where each point of the set of solutions has a corresponding a measure of accuracy of payload delivery to a geostationary orbit at a given set of coordinates.

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Low-Thrust Trajectory Optimization Using Orbital Averaging and Control Parameterization

Spacecraft Trajectory Optimization ◽

10.1017/cbo9780511778025.006 ◽

2011 ◽

pp. 112-138 ◽

Cited By ~ 12

Author(s):

Craig A. Kluever

Keyword(s):

Trajectory Optimization ◽

Low Thrust ◽

Control Parameterization ◽

And Control

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An Auto-Landing Solution for a Drop Test RLV Demonstrator

Modern Applied Science ◽

10.5539/mas.v8n5p204 ◽

2014 ◽

Vol 8 (5) ◽

pp. 204 ◽

Cited By ~ 1

Author(s):

Peng Yong-Tao ◽

Wang Yue-Ping ◽

Wei Wen-Ling ◽

Wang Xiao-Ting

Keyword(s):

Trajectory Optimization ◽

Technology Development ◽

Trajectory Generation ◽

Drop Test ◽

Design Parameters ◽

Trajectory Design ◽

Schedule Control ◽

Control Laws ◽

Gain Schedule ◽

And Control

Unpowered drop test is very important for reusable launch vehicle (RLV) autolanding technology development. One of the challenges is to design an autolanding trajectory with enough robustness against uncertainties of drop conditions, aerodynamic characteristic and disturbances from control system and environment. In this paper, a solution including trajectory generation and control design is proposed for a drop test RLV demonstrator. Firstly, the drop test and vertical flight trajectory are introduced. Also, parts of the drop flight, segments of landing trajecory and trajectory design parameters in groups are shown. Secondly, an online trajectory generation method including self-adapted capture segment plan and landing trajectory optimization following UAV auto-landing experience are illustrated in detail by designing groups of parameters. Then, simple but practical gain schedule control laws are presented. Finally, mathematic simulation and analysis based on both RSS and Monte Carlo methods indicate that the solution proposed has shown an acceptable robustness and can provide enough capability for the demonstrator to land saftly.

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