The need to control extra-terrestrial vehicles such as manned and unmanned satellites and space vehicles has created a requirement for a low thrust propulsion systems. It has been proposed that a thrustor system of this type could operate using cryogenic liquid as propellant, employing some type of heat exchange unit to raise the enthalpy of the propellant. The system mentioned above would also provide a possible low thrust unit for interplanetary space travel since the fuel for such a system would be stored in a highly concentrated form thus permitting long periods of fuel consumption. This paper presents an analytical and experimental study of one possible type heat exchange unit for such a thrustor system. It will be shown that such an evaporator may be designed in a manner so that all necessary thermal energy for changing the state of the propellant from liquid to gas can be obtained from the evaporator structure and its surroundings. (Author)
Heat Transfer Characteristics of a Low Thrust Attitude Control System Evaporator
1969
29 pages
Report
Keine Angabe
Englisch
Mathematics of attitude-constrained optimal low-thrust orbit transfer
Online Contents | 2017
|Mathematics of attitude-constrained optimal low-thrust orbit transfer
Springer Verlag | 2017
|Constant-attitude thrust program optimization.
NTRS | 1965
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