References

MSFC Flight Mission Directive, Apollo-Saturn 202 Mission, June 22, 1965 (U). 2. MSFC SA-202 Saturn Vehicle Data Book, May 15, 1965 (C). 3. Memorandum, R-P& VE-VAW-66-49, Saturn IB AS-202 Final Predicted Mass Characteristics, June 6, 1966 (U). 4. Memorandum, R-P& VE-PPE-66-M-96, AS-202 S-IB & S-IVB Final Flight Propulsion Prediction, May 18, 1966 (U). 5. Memorandum, R-P& VE-PPE-66-M-102, Douglas Aircraft Final S-IVB 202 Propulsion Flight Prediction, June 2, 1966 (U). 6....

Mass

Shown in Appendix A are the mass characteristics used to generate the AS-202 launch vehicle operational flight trajectory. These data were extracted from reference 3. The propulsion characteristics used to generate the data presented . in this report were obtained from references 4 and 5. Plots of thrust, flow rates, and specific impulse for both flight stages will be published at a later date for flight evaluation purposes. The inertial Saturn IB guidance system performs navigation...

Ballistic Portion

Retro-rockets are ignited at separation of the S-IB S-IVB to decelerate the S-IB stage. This portion of the trajectory, with subsequent ballistic flight to impact, is presented in tables 15 through 18. Two motion picture cameras, recording S-IB S-IVB separation, S-IVB ullage burn, and 3-2 engine ignition are ejected from the S-IB stage after separation. The S-IB and camera capsule impact footprint is presented in figure 10. The nominal camera capsule trajectory is. presented in table 23....

As Launch Vehicle Operational Flight Trajectory

The information in this report has been reviewed for security classification. Review of any information concerning Department of Defense or Atomic Energy Commission programs has been made by the MSFC Security Classification Officer. This report, in its entirety, has been determined to be unclassified. This document has also been reviewed and approved for technical accuracy. Chief, Tracking & Orbital Analysis Br Chief, Tracking & Orbital Analysis Br Lewis L. McNair Chief, Projects Office...

Configuration

The launch vehicle, consisting of four major vehicle assemblies, the S-IB stage, S-IVB stage, IU, and payload, is shown in figure 1. A weight breakdown is given in appendix A. Hie S-IB booster stage of the multistage Saturn IB vehicle develops the thrust necessary for the vehicle to achieve the altitude and velocity required by the upper stages to perform the mission and accomplish objectives. Eight H-l engines, uprated to 890,000 Newtons 200,000 lbf , supplied Oy four each LOX and fuel RP-1...

Section Iv Trajectory Description A Powered Portion

Shown in table 1 is the nominal sequence of events for AS-202, and in table 2, a trajectory and orbit fact sheet. Table 3 gives some significant parameters for certain events. The above tables serve as a summary of the following description. Guidance Reference Release GRR signal occurs approximately five seconds before launch commit, at which time the LVDC begins its computations and the platform becomes inertial. Vehicle first motion occurs approximately 0.2 seconds before Instrument Unit IU...