Section Trajectory

The Skylab-3 vehicle was launched at 7 10 50 a.m. Eastern Daylight Time, July 28, 1973, from Pad 39B at Kennedy Space Center. The vehicle was launched on an azimuth of 90 degrees east of north. A roll maneuver was initiated at approximately 10 seconds that placed the vehicle on a flight azimuth of 45.003 degrees east of north. The down range pitch program was also initiated at this time. The reconstructed flight trajectory (actual) was very close to the Post Launch Operational Trajectory...

Digital Command System Evaluation

The DCS performed satisfactorily throughout this mission. Fifteen conmands were initiated by MCC-H and all but one were accepted by the onboard equipment. Table 15-6 lists the commands transmitted to the IU. The deorbit dump command transmitted from HAW at 15,906 seconds (4 25 06) did not produce the desired memory data display at MCC-H and the same command was retransmitted at 16,049 seconds (4 27 29). The second transmission als iiled to produce the desired display although telemetry data...

Figure Ascent Trajectory Cfynamic Pressure and Nach Number Comparison

Standard Reference Atmosphere was used. A theoretical free flight trajectory was computed for the spent S-IB stage, using initial conditions fron the actual trajectory at S-IB S-IVB separation signal. Three trajectories were integrated from that point to impact using nominal retro-motor performance and outboard engine decay data. The three trajectories incorporate three different drag conditions for 1) stabilized at zero angle of attack (nose forward), 2) tumbling stage,...

Sib Base Heating

The thermal environment measured in the SA-207 S-IB base region has been compared with corresponding data from flights SA-203 through SA-206. With the exception of the flame shield radiation heating data measurement C0603-006 , these conparisons show excellent agreement. In all areas the measured thermal environments in the base region of SA-207 were well below the S-IB stage design level. There were seven base region thermal environment measurements flown on SA-207. Heat shield thermal...

REMARKS

Event-Oxid Turbine Bypass Valve - Open Event-Oxid Turbine Bypass Valve - Closed Measurement lost because of failure in the telemetry system. See paragraph 15.3. System performance analysis verified that the basic events properly occurred. NOTE There were no partial failures. Tabl 15-4. SA-207 Launch Vehicle Telemetry Links Performance Surrmary Tabl 15-4. SA-207 Launch Vehicle Telemetry Links Performance Surrmary

Figure Sivb Lox Dunp

Fuel dump was initiated at 19,702 seconds 5 28 22 and was satisfactorily accomplished. Fuel dump impulse, flowrate, mass remaining in fuel tank, and ullage pressure are shown in Figure 7-11. Only GH remained in the tank at dump start. The LH2 completely boiled off during orbital coast. A reconstruction of dump indicates the dump impulse, 31,800 lfb-sec, was in good agreement with the real time nominal predicted value of 31,500 lbf-sec. The ullage mass at the start of the dump was 343 lbm....

Tvb

DEGREES MEST OF GREENWICH Figure 4-5. Launch Vehicle Ground Track LONGITUDE. DEGREES MEST OF GREENWICH Figure 4-5. Launch Vehicle Ground Track SECTION 5 S-IVB IU DEORBIT TRAJECTORY All aspects of the S-IVB IU deorbit were accomplished successfully. The propellant dump was modified during real time to establish a reentry traj-jectory that would enable observation by Kwajalein. This modified plan was accomplished. The velocity change obtained for deorbit was very close to the real-time...

Info

It is now more apparent that the established trend of high flight thrust than ground thrust is valid for the 205 klbf engines and that the SA-206 lower flight thrust was probably due to the inconsistencies in the different ground tests and the subsequent effect of these inconsistencies on the predicted flight levels. The lower than predicted propel1ant flowrates caused IECO to be 0.76 second later than predict d. The lower flowrates and a greater than predicted differential between the center...