Little Joe 1-A (LJ-1A) was launched in a test for a planned abort under high aerodynamic load conditions. This flight was a repeat of the Little Joe (LJ-1) that had been planned for August 21, 1959 (escape rocket fired 31 min before the intended launch of the Little Joe launch vehicle). After lift-off, the pressure sensing system was to supply a signal when the intended abort dynamic pressure was reached (about 30 sec after launch). An electrical impulse was then sent to the explosive bolts to separate the spacecraft from the launch vehicle. Up to this point, the operation went as planned, but the impulse was also designed to start the igniter in the escape motor. The igniter activated, but pressure failed to build up in the motor until a number of seconds had elapsed. Thus the abort maneuver, the prime mission of the flight, was accomplished at a dynamic pressure that was too low. For this reason a repeat of the test was planned. All other events from the launch through recovery occurred without incident. The flight attained an altitude of 9 statute miles, a range of 11.5 statute miles, and a speed of 2,021.6 miles per hour.

Enos, the 6-year-old chimpanzee who made a two-orbit flight around the earth aboard the Mercury-Atlas 5 (MA-5) spacecraft (November 29, 1961, entry) died at Holloman Air Force Base, New Mexico. The chimpanzee had been under night and day observation and treatment for 2 months before his death. He was afflicted with shigella dysentary, a type resistant to antibiotics, and this caused his death. Officials at the Air Medical Research Laboratory stated that his illness and death were in no way related to his orbital flight the year before.

Mars probe intended to make a soft landing on Mars. Although the escape stage and payload reached orbit, the strong third stage vibrations shook a fuse loose from its mount in the main nozzle of the escape stage Block L's engine. The engine could not be ignited and remained in Earth orbit. It decayed about two months after insertion.

NASA announced an Apollo mission schedule calling for six flights in 1968 and five in 1969. NASA Associate Administrator for Manned Space Flight George E. Mueller said the schedule and alternative plans provided a schedule under which a limited number of Apollo command and service modules and lunar landing modules, configured for lunar landing might be launched on test flights toward the moon by the end of the decade. Apollo/uprated Saturn I flights were identified with a 200 series number; Saturn V flights were identified with a 500 series number. Additional Details: here....

The rockets achieved expected performance, solar pointing systems functioned properly, payloads were successfully recovered, and preliminary results appeared excellent. The information obtained by the rocket flights on solar emission intensity, filter performance, film response, and exposure time would be available in time to provide a useful and effective feedback into the ATM instruments development program.

Venera 13 and 14 were identical spacecraft built to take advantage of the 1981 Venus launch opportunity and launched 5 days apart. After launch and a four month cruise to Venus, the descent vehicle separated and plunged into the Venus atmosphere on 5 March 1982. As it flew by Venus the bus acted as a data relay for the brief life of the descent vehicle, and then continued on into a heliocentric orbit. The parachute of the descent vehicle opened after the lander reached subsonic speed. At an altitude of about 50 km the parachute was released and simple airbraking was used the rest of the way to the surface. Venera 14 landed about 950 km southwest of Venera 13 near the eastern flank of Phoebe Regio at 13 deg 15 min S by 310 E on a basaltic plain. After landing an imaging panorama was started It has been reported that the surface analysis arm accidentally landed on one of the ejected camera covers and therefore didn't send back any data on the Venusian soil. This is visible in photographs sent back. On the other hand, the official account very specifically states that the mechanical drilling arm obtained a sample, which was deposited in a hermetically sealed chamber, maintained at 30 degrees C and a pressure of about .05 atmospheres. The composition of the sample was determined by the X-ray flourescence spectrometer, showing it to be similar to oceanic tholeiitic basalts. The lander survived for 57 minutes (the planned design life was 32 minutes) in an environment with a temperature of 465 degrees C and a pressure of 94 Earth atmospheres.

Studied natural resources. It carried the German Safir-R1 communications experiment as a secondary attached payload. Expected life 3 to 5 years. The spacecraft mass of 1,907 kg was slightly higher than earlier models. The principal Earth observation sensors were MSU-SK and MSU-E instruments along with an experimental PVM-E local vertical sensor .

Soyuz TM-19 undocked from Mir with the crew of Malenchenko, Merbold and Musabayev aboard at 07:29 GMT on November 4. The Soyuz instrument module (PAO, priborno-agregatniy otsek) fired its deorbit engine, and was jettisoned together with the orbital module (BO, bitovoy otsek) at 10:51 GMT, with entry interface for the descent module (SA, spuskaemiy apparat) at 10:54. It landed 170 km north-east of Arkalyk in Kazakhstan on 1994 November 4 at 11:18 GMT.

The High Energy Transient Experiment (HETE) was an international mission led by The Massachusetts Institute of Technology (MIT). Its prime objective was to carry out the first multiwavelength study of gamma ray bursts (GRBs) with UV, X-ray, and gamma ray instruments. A unique feature of the mission was its capability to localise bursts with several arcsecond accuracy, in near real-time aboard the spacecraft. These positions were to be transmitted to the ground, and picked up by a global network of primary and secondary ground stations (SGS), enabling sensitive follow-up studies. However the satellite was never released from its payload fitting. Although signals were received, the solar panels could not deploy, and it went silent after a few days when its batteries ran down. Air dropped in Wallops Island DZ.

The Proton launch vehicles Block DM3 fourth stage put the Panamsat PAS 8 into a 6784 km x 35941 km x 17.3 degree transfer orbit. PAS 8 had 24 C-band and 24 Ku-band transponders and was to be located over the Pacific after its R-4D apogee engine manoeuvred the orbit to geostationary altitude and inclination. Geostationary at 166.1 degrees E. Positioned in geosynchronous orbit at 166 deg E in 1998-1999 As of 4 September 2001 located at 166.05 deg E drifting at 0.003 deg W per day. As of 2007 Mar 9 located at 165.96E drifting at 0.002E degrees per day.

Defense Meteorological Satellite Program satellite with the Operational Linescan System camera, a microwave imager-sounder, ultraviolet spectrometers, particle detectors, a magnetometer, and a laser threat warning sensor. Reportedly went for a time into safe mode due to software problems after launch. The booster upper stage was conducted a maneuver to deorbit itself after placing the satellite in orbit. After the burn an explosion evidently occurred aboard the stage - dozens of objects were tracked in various orbits with perigees down to 670 km and apogees up to 851 km.

Launched from the Kauai Test Facility's Kokole Point pad; went out of control during first stage burn and was destroyed. The University of Hawaii's Hiakasat and 12 cubesats were aboard. The vehicle had three solid stages (LEO-46, LEO-7 and LEO-1) developed by Aerojet.