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be a descrption or the propulsion systems available, the available from each, and the required for abort.
d.
The significant characteristics of abort trajectories will also be disscussed. Included will be (illegible text) thing as orientation with respect to the earth and moon, relation between return time required, and delay time
The major constraints which shape all abort trajectories are as follows:
a.
Reentry corridor - In other words a velocity/flight path angle relation at the beginning of the atmosphere (400,000 feet). For the purposes of this paper, only abort trajectories targeted to the center of the entry corridor will be considered.
b.
Maximum reentry speed (less than 36,000 fps.) - This constraint is due to heat shield limitations.
c.
Return inclination (less than 40°) - This constraint assures landings in temperate zones even in the presence of large reentry dispersions and also reduces heat shield requirements
d.
available - In other words, the required for an abort must be within the capability of the spacecraft. This value will probably be set at some amount less than the total available allow a pad for midcourse and possible contingencies.
e.
2
The mission phases considered in this discussion will be (1) launch—to—earth parking orbit, (2) earth parking orbit coast, (3) translunar injection, (4) translunar coast, (5) lunar orbit insertion, (6) lunar orbit cost (7) transearth injection, and (8) transearth coast. Note that aborts during LM maneuvers are not considered (illegible text) would be to rendezvous.
2.0
ABORTS DURING LAUNCH PHASE
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