Analysis of the Radio Astronomy Explorer lunar orbit mission.The second Radio Astronomy Explorer spacecraft (RAE-B) is planned to be inserted into lunar orbit in 1973. The transfer trajectory design, lunar orbit selection and launch opportunities are developed in relation to the spacecraft mass properties, propulsion capability and the scientific, environmental and engineering constraints. Alternative midcourse guidance and lunar orbit trim strategies are analyzed and compared. A means of achieving a launch window without varying launch azimuth and park orbit coast time is described. The resulting mission design is characterized by near-minimum energy lunar transfer trajectories and low eccentricity, retrograde critical inclination lunar orbits. Acceptable launch periods are shown to exist for six consecutive months and for two to four consecutive days per month.
Document ID
19720061771
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Groves, R. T. (NASA Goddard Space Flight Center Flight Mission Analysis Branch, Greenbelt, Md., United States)