The Secretary of the Army approved the transfer of the Ordnance Research and Development Division, Sub-Office (Rocket) at Fort Bliss, Texas, to Redstone Arsenal. Among those transferred were Dr. Wernher von Braun and his team of German scientists and t
100-foot-diameter inflatable sphere launched on a suborbital test flight from NASA Wallops Station, Va., to an altitude of 250 miles by a first Sergeant-Delta rocket; aluminum-coated Mylar-plastic sphere to be used as passive electronic reflector in Echo was developed by NASA Langley's Space Vehicle Group under the direction of William J. O'Sullivan. References: 17 .
Key staff members of NASA Headquarters and the Commander, U.S. Air Force Research and Development Command, met at the Air Force Ballistic Missile Division, Los Angeles, Calif., to attend briefings and discuss matters of mutual concern.
At an executive session, Air Force and NASA programs of orbital rendezvous, refueling, and descent from orbit were discussed. Long-range Air Force studies on a lunar base were in progress as well as research on more immediate missions, such as rendezvous by an unmanned satellite interceptor for inspection purposes, manned maintenance satellites, and reentry methods. NASA plans for the manned lunar landing mission included the possible use of the Saturn booster in an orbital staging operation employing orbital refueling. Reentry studies beyond Mercury were concentrated on reentry at escape speeds and on a spacecraft configuration capable of aerodynamic maneuvering during reentry. References: 16 .
Military-Industrial Commission (VPK) Decree 'On assignment of lunar programs to OKB-52 and OKB-1' was issued. References: 474 .
Testing of the first flight-weight 15-cell stack of the LEM fuel cell assembly began. Although the voltage was three percent below design, the unit had a 980-watt capability. Earlier, the unit completed 150 hours of operation, and single cell life had reached 662 hours. References: 16 .
ASPO's Operations Planning Division defined the current Apollo mission programming as envisioned by MSC. The overall Apollo flight program was described in terms of its major phases: Little Joe II flights (unmanned Little Joe II development and launch escape vehicle development); Saturn IB flights (unmanned Saturn IB and Block I CSM development, Block I CSM earth orbital operations, unmanned LEM development, and manned Block II CSM/LEM earth orbital operations); and Saturn V flights (unmanned Saturn V and Block II CSM development, manned Block II CSM/LEM earth orbital operations, and manned lunar missions). References: 16 .
The original Gemini VI mission had been canceled when its target vehicle failed catastrophically on October 25. In a memorandum to the President, NASA Administrator James E. Webb indicated the possibility that Gemini VI spacecraft and launch vehicle could be reerected shortly after the launch of Gemini VII. Since much of the prelaunch checkout of Gemini VI would not need repeating, it could be launched in time to rendezvous with Gemini VII (a mission scheduled for 14 days) if launching Gemini VII did not excessively damage the launch pad. NASA officials, spurred by suggestions from Walter F. Burke and John F. Yardley of McDonnell, began discussing the possibility of a dual mission immediately after the failure October 25, drawing on some six months of discussion and preliminary planning by NASA, Air Force, Martin, and McDonnell personnel for a rapid manned flight launch demonstration.
Moscow Oblast Executive Committee Decree 'On renaming of Zeleniy as Zvezdniy gorodok' was issued. References: 474 .
A lunar roving vehicle (LRV) cost-plus-incentive-fee contract was awarded to the Boeing Co. LRV-1 was scheduled for delivery on April 1, 1971, leaving only 17 months for vehicle development, production, and tests. The LRV project was managed at MSFC by Saverio F. Morea as a project within the Saturn Program Office. The Boeing Company would manage the LRV project in Huntsville, Ala., under Henry Kudish. General Motors Corp. AC Electronics Defense Research Laboratories in Santa Barbara, Calif., would furnish the mobility system (wheels, motors, and suspension). The Boeing Go. in Seattle, Wash., would furnish the electronics and navigation system. Vehicle testing would take place at the Boeing facility in Kent, Wash., and the chassis manufacturing and overall assembly would take place at the Boeing facility in Huntsville, Ala. References: 16 .
To test in space equipment for future satellites and to conduct a scientific experiment to measure the incidence of micro-meteoroids. Launch time 0409 GMT, injection point 13.7 deg S, 137.9 deg E. Anticipated life 100 years. References: 1 , 2 , 5 , 6 .
Failed lunar soil return mission. After successfully entering earth orbit, flying to the moon, entering lunar orbit, and descending toward the surface, the spacecraft was damaged during landing in Mare Crisium (Sea of Crises). The sample collecting apparatus could not operate and no samples were returned. The lander continued transmissions for three days after landing. In 1976, Luna 24 landed several hundred meters away and successfully returned samples. Parameters are for lunar orbit. References: 1 , 2 , 5 , 6 , 67 , 274 , 296 .
Continued operation of the long-range telephone and telegraph radio-communication system; transmission of USSR central television programmes to stations in the Orbita network and international cooperation. References: 1 , 2 , 5 , 6 .
Replaced Molniya 1-56. Operation of the long-range telephone and telegraph radio communications system in the USSR; transmission of USSR Central Television programmes to stations in the Orbita network. References: 1 , 2 , 5 , 6 .
Satellite was originally built as a backup for Argentina's Nahuelsat. This allowed Dornier and Alcatel to deliver the satellite in a record twelve months. Dry mass of GE 5 was 769 kg - it carried 950 kg of propellant at launch. Geostationary at 36.4 degrees W.
Afristar was the first WorldSpace satellite. Afristar was to broadcast digital radio over Africa and the Middle East. Small hand-held radios could pick up the 24 to 96 radio channels available on the three L-band beams. Dry mass of Afristar was 1205 kg; it carried 1534 kg of propellant at launch. Geostationary at 21.0 degrees E.