Low-Thrust Transfer Orbit Design Based on Lyapunov Feed Back Control Law

2006 ◽  
Author(s):  
Ren Yuan ◽  
Cui Ping-yuan ◽  
Luan En-jie
Keyword(s):  
Control Law ◽  
Low Thrust ◽  
Orbit Design ◽  
Transfer Orbit

Low-Thrust Geostationary Transfer Orbit (LT2GEO) Radiation Environment and Associated Solar Array Degradation Modeling and Ground Testing

2014 ◽  
Vol 61 (6) ◽  
pp. 3348-3355 ◽  
Author(s):  
Scott R. Messenger ◽  
Frankie Wong ◽  
Bao Hoang ◽  
Cory D. Cress ◽  
Robert J. Walters ◽  
...  
Keyword(s):  
Radiation Environment ◽  
Solar Array ◽  
Low Thrust ◽  
Ground Testing ◽  
Degradation Modeling ◽  
Transfer Orbit

Cooperative Control for Satellite Formation Reconfiguration via Cyclic Pursuit Strategy

2014 ◽  
Vol 875-877 ◽  
pp. 1153-1159 ◽  
Author(s):  
Tao Yang ◽  
Zheng Dong Hu ◽  
Li Bo Yang
Keyword(s):  
Phase Angle ◽  
Cooperative Control ◽  
Movement Control ◽  
Control Law ◽  
Low Thrust ◽  
Orthogonal Direction ◽  
Formation Reconfiguration ◽  
Cyclic Pursuit ◽  
Planar Movement ◽  
Pursuit Strategy

This paper investigates a methodology for group coordination and cooperative control of satellites with the aim to achieve formation reconfiguration such as radius enlargement and phase angle adjustment. The proposed approach separates the control law into two distinct stages: planar movement control and orthogonal displacement suppression. The in plane approach is based on a cyclic pursuit strategy, where satellite i pursues satellite i +1. For phase angle adjustment, a control law that makes use of beacons guidance is synthesized to maintain the circling centre stationary. In the orthogonal direction, a linear feed back control on displacement and velocity is used. Simulation of two missions with low thrust are provided, which high light the over all effectiveness of the proposed approach.

CALCULATION OF SUBOPTIMAL HIGH-ELLIPTICAL ORBIT TO GEOSTATIONARY ORBIT TRAMSFERS FOR SPACECRAFT WITH LOW THRUSTERS

2019 ◽  
pp. 94-108
Author(s):  
V.V. Salmin ◽  
K.V. Petrukhina ◽  
A.A. Kvetkin
Keyword(s):  
Initial Conditions ◽  
Optimization Theory ◽  
Elliptical Orbit ◽  
Geostationary Orbit ◽  
Suboptimal Control ◽  
Control Law ◽  
Trajectory Design ◽  
Low Thrust ◽  
Design Calculations ◽  
Chemical Propulsion

At present the geostationary orbit is where communication satellites are preferably placed. Conventional orbital insertion profiles using chemical propulsion are insufficiently effective and require the use of heavy launch vehicles. Combining electric thrusters with chemical propulsion increases the mass of payload. On the other hand, orbital injection of a spacecraft using electrical propulsion brings up the problem of looking for an optimal control law. The paper discusses the transfer of a spacecraft with low-thrust electrical thruster from a high elliptical orbit to geostationary orbit. It proposes a suboptimal control law for the thrust vector. It provides examples of simulations of the transfer using the control law for various initial conditions. Parameters of intermediate high-elliptical orbits were selected to minimize the time of transfer to the final orbit, and estimates were made of the effects of the residual atmospheric drag during flight in the vicinity of the perigee of the orbit. Considering the low level of error, simplicity and high computational speed the proposed method can be used for trajectory design calculations. Key words: Suboptimal control law, local optimization theory, electric thruster, high-elliptical orbit, geostationary orbit, math model of controlled motion, Pontryagin's maximum principle.

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