PLANECHG: Earth orbit to lunar orbit delta V estimation program. User and technical documentation

Details PLANECHG: Earth orbit to lunar orbit delta V estimation program. User and technical documentation PLANECHG: Earth orbit to lunar orbit delta V estimation program. User and technical documentation

Sep 1988

adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=1988stin...8913442.&link_type=abstract

Unknown

Mathematics

Earth-Moon Trajectories, Midcourse Guidance, Orbital Launching, Velocity, Altitude, Circular Orbits, Earth Orbits, Inclination, Longitude, Lunar Orbits, Matrices (Mathematics)

Scientific paper

The PLANECNG computer program calculates velocities for Earth-to-Mooon and Moon-to-Earth trajectories. The flight to be analyzed originates in a circular orbit of any inclination and altitude about one of the bodies, and culminates in a circular orbit of any inclination and altitude about the other body. An intermedate delta V and plane change occurs at the Lunar Sphere of Influence (SOI), the region where the vehicle is near its lowest velocity in the trajectory, and therefore where it is able to make the plane change with the lowest delta V. A given flight may penetrate the SOI at a number of points. Each point has associated with it a unique set of delta V's and total velocity. The program displays the velocities, in matrix form, for a representative set of SOI penetration points. An SOI point is identified by projecting Lunar latitude and longitude onto the SOI. The points recorded for a given flight are defined by the user, who provides a starting longitude and latitude, and an increment for each. A matrix is built with 10 longitudes forming the columns and 19 latitudes forming the rows. This matrix is presented in six reports, each containing different velocity or node information in the body of the matrix.

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