Air Bearing Supply

The purpose of the air bearing supply was to provide clean gaseous nitrogen at a predetermined flow, temperature, and pressure to the air bearings of the ST-90 and ST-124P stabilized platforms. Blockhouse records show that theair bearing high pressure supplywas maintained prior to launch at approximately 210kg cm2 ( 2990 psi gauge) for the ST-90 and 209 kg cm2 (2970 psi gauge) for the ST-124P, which was within the redline limits of 220 kg cm2 (3200 psi gauge) maximum and 183 kg cm2 (2600 psi...

Angleofattack Meters

Four active control local angle-of-attack meters (U. S. Science) were used on SA-3. A Q-ball angle-of-attack device, similar to the one used on SA-2, was used for measuring purposes. The U. S. Science meters were mounted radially 90 degrees apart in the payload body surface at station 1841. Two of these meters measure in the pitch plane and two in the yaw plane. The average of the two pitch measurements and the two yaw measurements are shown in Figure 7-11. Since these meters are located on the...

Figure Center Lox Tank Telemetered Sloshing Amplitudes After Seconds

The fluid surface went below the slosh probe and the measurement ended. The dashed lines in Figure 7-16 show the envelope of the slosh amplitude observed in the center tank on SA-2. This has been referenced to the location at the end of the baffles, since the time history of the two flights was different due to the pro-pellant loading differences. The sloshing in the center tank was similar in magnitude on SA-2 and SA-3. However, it appeared that sloshing started somewhat earlier on SA-3. Also,...

For C With A Typical Decay

At this time, no explanation as to the cause of this rapid temperature decay is available, but preliminary evaluation indicates the following possibilities 1) a difference in the heating and cooling cycles possibly exists, whereby the correction factor obtained after cutoff is possibly not valid for the entire flight, 2) possible conduction losses during flight higher than indicated by the laboratory calibration method, and 3) a possibility of a convective cooling source hitting the calorimeter...

Actuators

The operation of the hydraulic actuators was satisfactory. An investigation of actuator loading cluring the flight was made by analyzing the actuator differential pressure measurements. Thrust vector misalignments andinertial loads were determined for all actuators. An investigation of curtain and gimbal friction torques was not made since reliable data was not available lor periods when these torques could be isolated. Thrust misalignment forces, as determined from the differential pressure...

Telemetry System Analysis

Data transmission for flight testing Saturn vehicle SA-3 was effected by eight radio telemetry system links, and a TM auxiliary equipment assembly. In addition, two experimental systems, a PCM system link 6 and a UHF RF assembly Link 9 , were flight tested for the first time. All systems operated satisfactorily. The overall performance of link 6 was found to be excellent, and indications are that the PCM FM system will provide very accurate data. The signal strength from this link was very...

Figure Bending Moment And Normal Load Factor

Because five of the eight stud gauges of the 1. 8 m 70 inch LOX tanks station 869 were lost, no bending moments about the pitch and yaw axes could be calculated at that station. However, the three gauges which functioned properly gave some check on the bending moment at station 979. These three gauges were found to be in agreement with predicted values. The vehicle bending moment about the pitch axis at station 979 is shown in the 75 to 85 seconds range time interval in Figure 10-2. Also shown...

Figure Picture Sequence Of Project Highwater Experiment

Film from the long range camera at Vero Beach showed that the S-l booster remained intact after destruct of the upper dummy stages. The tumbling 66 a. M-31 Heat Shield Panel Block II Type h. S-IV Stage Temperature and Pressure Meas. i. Block II Swing Arm j. Retro Rockets 13. 3 VIII Paragraph 8. 2. 2 Xin Paragraph 13. 3 1. M-AERO-PO-3-62 Saturn C-l Vehicle SA-3 Test Flight Trajectory Corridor To Be Flown By SA-3 U by Hardage, O. M. dated November 2, 1962. 2. MPR-SAT-WF-61-8 Saturn SA-1 Flight...

Project Highwater

A water cloud experiment similar to the experiment conducted on SA-2 was accomplished successfully on SA-3. At 292 seconds range time the upper stages' water ballasts were ruptured with primacord, injecting 86. 7 m3 22, 900 gal of water into the upper atmosphere. At the time of Project Highwater, the vehicle was at an altitude of 167. 22 km 0.45 km higher than predicted and at a range of 211.41 km 3. 76 km above predicted . The Saturn water release experiment was con-ductedonthe SA-3 flightin...