Oct 25 1978
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(New page: NASA announced launch of Nimbus-G (Nimbus 7 in orbit) on Oct. 24, 1978, at 4:14am EDT (08:14:00.72Z). Orbital values were: apogee, 954.6km; perigee, 953.6km; inclination, 99.2°; and perio...)
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NASA announced launch of Nimbus-G (Nimbus 7 in orbit) on Oct. 24, 1978, at 4:14am EDT (08:14:00.72Z). Orbital values were: apogee, 954.6km; perigee, 953.6km; inclination, 99.2°; and period, 104.1 min.
Onboard recorded data dumped during the first Madrid pass showed an apparent reduction in indicated telemetry level, starting at approximately "plus 4 min" and continuing for 30min, at which time the telemetry levels returned to normal. Analysis was under way. Solar arrays had extended, and were normal to and tracking the sun; spacecraft attitude was stable. All spacecraft systems parameters were normal, and activation of the experiment systems had begun. (MOR E-604-78-08 [postlaunch], Oct 25/78)
LaRC announced selection of the Riggins Company, Inc., Hampton, Va., for negotiations leading to award of a contract to provide materials and services for construction of the Nad. Transonic Facility (NTF) at LaRC. The NTF would embody a unique wind-tunnel concept permitting use of temperatures as low as - 300°F to improve simulation of airflow over planes in full-scale flight conditions. The contract, to be managed by LaRC, would include provision of liquid nitrogen, gaseous nitrogen, cooling water, and air and vacuum piping systems required for the wind-tunnel test environment. Riggins Co. estimated the contract value at $2.9 million, with work to be completed by late 1981. (LaRC Release 78-64)
The third of four Space Shuttle solid-propellant booster motors (DM-3) to be tested during the development phase had been fired successfully the previous week at Thiokol Corp.'s Wasatch Division in Brigham City, Utah, the Marshall Star reported. First of a prototype solid-fuel rocket motor (SRM) to be tested in flight configuration, the DM-3 included several features not tested in earlier firings: The motor aft skirt, containing a thrust-vector (directional) control-actuation system for the nozzle was on the motor for the first time. Also part of the overall test was recording data on the pressure inside the exhaust plume (flame), showing how much force would impact the launch platform at liftoff, that JSC and KSC would use in launch-facility studies. An onboard hydraulic system powered the thrust-vector control, moving the nozzle to change vehicle direction, for the first time in an SRM development test. Final event was a test of the linear-shaped explosive charge that would sever the nozzle aft-exit cone from the motor about 25mi above earth during Space Shuttle flights. (Marshall Star, Oct 25/78, 2; JSC Roundup, Oct 27/78, 1)
The Marshall Star reported that MSFC had begun ground-vibration tests of the Space Shuttle in its liftoff configuration in the dynamic-test stand, first test of the Space Shuttle with all elements mated in flight configuration. The test phase would run through November. Test preparation crews from Bendix worked around the clock to prepare the stand, the Shuttle, and the shaker systems for the second phase of ground-vibration testing. The Space Shuttle's weight rested on the aft skirts of the two solid-fuel rocket boosters bolted to hydrodynamic support systems at the base of the test tower. When pressurized, the support systems would allow adequate vertical, lateral, and rotational movement of the entire Space Shuttle.
Test engineers had predetermined a total of 83 shaker positions for the combination of Space Shuttle elements; using a spacecraft computers system to drive the shakers, the engineers could select different positions to determine vehicle response. The computerized system would automatically control up to 24 shaker channels from the 61 that were available, rated at 10001b, 1501b, and 501b force. (Marshall Star, Oct 25/78, 1)
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