Optimal electric propulsion orbit transfer vehicle design and operational effectiveness

1985 ◽  
Author(s):  
L. MADDOX ◽  
M. MEKARU ◽  
W. ELROD ◽  
W. WIESEL
Keyword(s):  
Electric Propulsion ◽  
Vehicle Design ◽  
Orbit Transfer ◽  
Operational Effectiveness

Closed-Loop Orbit Transfer Using Solar Electric Propulsion

2016 ◽  
Vol 39 (11) ◽  
pp. 2563-2569 ◽  
Author(s):  
Mauricio M. Guelman ◽  
Alexander Shiryaev
Keyword(s):  
Electric Propulsion ◽  
Closed Loop ◽  
Orbit Transfer ◽  
Solar Electric Propulsion

Electric Propulsion Development

1969 ◽  
Vol 73 (708) ◽  
pp. 1071-1075
Author(s):  
P. R. Openshaw
Keyword(s):  
Attitude Control ◽  
Electric Propulsion ◽  
Control Problems ◽  
Orbital Elements ◽  
Orbit Transfer ◽  
Expansion Phase ◽  
Ion Thrusters ◽  
Black Arrow ◽  
Orbit Eccentricity ◽  
Orbit Inclination

Parts I and II of this series of papers have dealt with the development of ion thrusters for use in an orbit transfer manoeuvre, and of various types of micro thruster for position and attitude control. The present paper deals with the actual satellite electric propulsion system and configuration needed for expansion manoeuvres. The control problems both during the expansion phase and subsequently in the required orbit are discussed. Short analyses for two specific cases (ELDO launcher and Black Arrow) are presented in which payloads and missions are defined. Burt has shown that all the orbital elements of a spacecraft can be changed by means of a small continuous thrust. He gave particular attention to the problem of expanding from a low orbit to a synchronous one, and the change of orbit inclination and orbit eccentricity was also considered. Such a type of manoeuvre is eminently suitable to electric propulsion because the high exhaust velocities possible lead to a small propellant mass; this mass saving is achieved at the expense of the time taken for the manoeuvre.

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