Dec 3 1967
From The Space Library
U.S.S.R. launched Cosmos CXCIV into orbit with 333-km (207-mi) apogee, 205-km (127-mi) perigee, 89.7-min period, end 65.7° inclination. Equipment and instruments functioned satisfactorily, and spacecraft was successfully recovered Dec. 11. (W Post, 12/6/67, B2; Interavia Air Letter, 12/14/67,6; GSFC SSR, 12/15/67)
"Evaluation of Apollo 4 mission data . . . continues to confirm initial reports that Spacecraft 017 met all flight objectives without problems," NASA announced. Detailed systems analyses were still in process, but evidence to date indicated spacecraft systems operated properly during Nov. 9 mission and met all specifications. First Service Propulsion System (SPS) burn had occurred as scheduled; second SPS burn, however, was 13 sec longer than planned, because of a switchover to ground control after burn was started by onboard guidance and navigation system. Although review of the burn was still being conducted, NASA had already determined that there had been no failure in onboard systems involved. Because of the longer-than-planned SPS burn, spacecraft's reentry velocity was 0.0058% higher than expected; actual velocity was 24,913 mph, compared with nominal 24,772 mph. Increased velocity caused higher Command Module (CM) maximum heat rate-620 BTUs per sq ft per sec instead of planned 586 BTUs. Maximum rate expected on lunar return was 480 BTUs. Maximum g on reentry was 7.3, compared with expected 8.33 g, because of a shallower reentry flight-path angle. Cabin pressure remained between 5.6 and 5.8 psi during entire mission, indicating negligible leakage rate. Cabin air temperature remained stable at 60° F during orbit and increased to 70° F during reentry. Structural performance of the spacecraft and Lunar Test Article 10-R (a simulated lunar module) during launch and boost phase was satisfactory. Earth landing system functioned as planned; all parachutes inflated properly, and recovery aids deployed and operated normally. Heat shield performance was good; maximum char thickness was 3/4 in, and charring of crew compartment heat shield was less than expected. Fuel cell and cryogenic subsystems functioned normally, with fuel cells producing potable sterile water and demonstrating excellent load-sharing and thermal-control capability. CM and SM reaction-control systems, electrical power subsystem, and spacecraft sequential devices operated normally, with all functions occurring at scheduled times. Guidance and control system and the mission control programmer performed properly. Range-to-go at drogue parachute deployment calculated was 2.2 nm. Comparisons with measured landing point indicated better than predicted performance. All communications objectives were accomplished. Each MSFN station, Apollo tracking ship Vanguard, and at least two of the Apollo/Range Instrumentation Aircraft established two-way communications with the spacecraft as planned. (NASA Release 67-294; Hines, W Star, 12/3/67, A20; SBD, 12/5/67, 172-3)
As of Nov. 15, US. had dropped 1,630,500 bombs on North and South Vietnam since July 1965-twice the tonnage dropped during the Korean War, and three times that dropped in the Pacific Theater during World War II. (Wilson, W Post, 1/5/68, 4)
William Littlewood, a former vice president of American Airlines and developer of the DC-3 aircraft, died at age 69. Recipient of numerous awards-including Wright Brothers Medal, Flight Safety Foundation Medal, and Guggenheim Medal-Littlewood had been a member of NACA, Flight Safety Foundation, Cornell Aeronautical Laboratory board of directors, U.K. Royal Aeronautical Society, and Canadian Aeronautics and Space Institute. (NYT, 12/5/67, 45; W Star, 12/5/67, B4)
1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18 19 20 21 22 23 24 25 26 27 28 29 30 31
