Minimum-energy attitude control for a class of electric propulsion devices

1964 ◽  
Vol 9 (3) ◽  
pp. 287-290 ◽  
Author(s):  
L. Schwartz
Keyword(s):  
Attitude Control ◽  
Electric Propulsion ◽  
Minimum Energy

Modified LADRC Method Applied to Attitude Control of Distributed Electric Propulsion UAV

2020 ◽  
Author(s):  
Yuelong Ma ◽  
Wei Zhang ◽  
Meng Li ◽  
Ruyue Wei ◽  
Yuying Liu ◽  
...  
Keyword(s):  
Attitude Control ◽  
Electric Propulsion

Four-Wheeled Hopping Robot with Attitude Control

2004 ◽  
Vol 16 (3) ◽  
pp. 319-326
Author(s):  
Shingo Shimoda ◽  
◽  
Takashi Kubota ◽  
Ichiro Nakatani ◽  
Keyword(s):  
Simulation Study ◽  
Attitude Control ◽  
Minimum Energy ◽  
Free Fall ◽  
Control Mechanisms ◽  
Hopping Robot

Because a hopping robot moves long distances at minimum energy and can observe its surrounding from high points when it jumps, it is expected to explore microgravity environments effectively. Despite the importance of attitude control in such exploratory robots, few attitude control mechanisms have been proposed. This paper proposes a four-wheeled hopping robot that hops horizontally and lands without bouncing. Its wheels are applied to attitude control in the air. A simulation study and free-fall experiments verified the feasibility of the proposed mobility and the applicability of the robot.

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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