Third launch of A3 subscale V-2 missile. No parachute deployment and the engine cut-off early. The rocket impacted into the Baltic Sea and sank. References: 394 .

First successful powered (RMI XLR-11 rocket engine) flight of an XS-1, flown by Chalmers Goodlin, Bell test pilot, reached a speed of 550 mph. This was first U.S. aircraft designed for supersonic speeds. References: 17 .

Launched 14:42 local time. Reached 104.8 km. Carried pressure, temperature, solar radiation, sky brightness, ionosphere, photo experiments for Air Research and Development Command.

Launched 12:14 local time. Reached 130.6 km. Carried Composition, ionosphere, meteorites, solar radiation, sky brightness experiments for Air Research and Development Command. Last monkey, Albert IV, launched in V-2 series. The successful flight indicated no ill effects on monkey until impact of V-2.

AF flight 3. First high-mach flight attempt by X-1A. Mach 1.9 attained at 18300 m during slight climb. References: 49 , 97 .

First Vanguard test; re-entry studies; not a vertical firing. Launched at 0103 local time. First test rocket in the IGY-U.S. satellite program, a one-stage NRL Viking, attained an altitude of 176 km and a speed of 6,400 kph. Viking No. 13 carried a "minitrack" radio transmitter which was ejected at 80 km and tracked.

The Space Task Group indicated that nine Atlas launch vehicles were required in support of the Project Mercury manned and unmanned flights and these were ordered from the Air Force Ballistic Missile Division. References: 483 .

KH-2; film capsule recovered 3.1 days later. First successful mission employing KH-2 camera system. References: 1 , 2 , 5 , 6 .

A single main parachute was drop-tested at El Centro, Calif., to verify the ultimate strength. The parachute was designed for a disreef load of 11,703 kg (25,800 lbs) and a 1.35 safety factor. The test conditions were to achieve a disreef load of 15,876 kg (35,000 lbs. Preliminary information indicated the parachute deployed normally to the reefed shape (78,017 kg (17,200 lbs) force), disreefed after the programmed three seconds, and achieved an inflated load of 16,193 kg (35,700 lbs), after which the canopy failed. Additional Details: Apollo main parachute drop-tested. References: 16 .

Boilerplate 23, Mission A-002, was successfully launched from WSMR by a Little Joe II launch vehicle. The test was to demonstrate satisfactory launch escape vehicle performance utilizing the canard subsystem and boost protective cover, and to verify the abort capability in the maximum dynamic pressure region with conditions approximating emergency detection subsystem limits. References: 16 .

Suborbital test of subscale model of X-20 Dynasoar. Aero-environmental test vehicle (AEV) to test aerodynamic properties of flexing outer skin with corrugated columbium panel. Reached 4,000 m/s at 53.2 km altitude before being released from launch vehicle. Telemetry received for 900 seconds until spaceplane had reached Mach 2 1200 km downrange. It then became unstable and crashed into the Atlantic. Recovery was not planned. References: 48 .

An 889-kilonewton (200,000-lb) thrust J-2 engine was captive-fired for 388 sec on a new test stand at MSFC. The J-2 engine would be used to power the Saturn S-IVB stage for the Saturn V. Ten tests of the liquid hydrogen-liquid oxygen powered rocket engine had been conducted at MSFC since the J-2 engine test facility was put into use in August 1965. References: 16 .

An Apollo drop test failed at El Centro, Calif. The two-drogue verification test had been planned to provide confidence in the drogue chute design (using a weighted bomb) before repeating the parachute test vehicle (PTV) test. Preliminary information indicated that in the test one drogue entangled with the other during deployment and that only one drogue inflated. The failure appeared to be related to a test deployment method rather than to drogue design. The test vehicle was successfully recovered by a USAF recovery parachute-intact and reusable. References: 16 .

On 13 October 1967 Mishin began his efforts to kill the VI program. From the point of view of the 'Podpliki Mafia', Kozlov had insulted them by redesigning the Soyuz VI in light of the defects of their 7K-OK design. They were also fundamentally opposed to the use of radio-isotope power sources, and raised doubts about the 800 mm hatch cut into the heat shield (as they did in the case of Chelomei�s VA). Mishin wrote a letter to Afanasyev and Smirnov, urging them to cancel the 7K-VI program. In the place of Kozlov's VI Mishin proposed his own project for an Soyuz-derived OIS orbital station. In a November 1967 meeting between Mishin and Kozlov Mishin demanded the abandonment of Kozlov�s 7K-VI project. Kozlov rejected this and subsequently appealed to Kamanin. Through various complex machinations Mishin seized control of the project on 8 December 1967 and promised that the first OIS would be launched in 1969. Mishin�s revised project was reaffirmed in May 1968. Having won the battle, Mishin lost interest. OKB-1 would pursue it at a desultory pace until it was finally cancelled in 1969. In the place of Kozlov's VI Mishin proposed his own project for an orbital station 11F730 Soyuz VI. This would consist of on orbital block 11F731 OB-VI and a transport spacecraft 11F732 7K-S. Through various complex machinations Mishin seized control of the project on 8 December 1967. The new Soyuz VI was designated the OIS 11F730. It would be launched into a lower-inclination 51.6 degree orbit at 250 x 270 km, and would use solar panels in the place of the nuclear power sources.

During a routine flight of lunar landing training vehicle (LLTV) No. 1, MSC test pilot Joseph S. Algranti was forced to eject from the craft when it became unstable and he could no longer control the vehicle. The LLTV crashed and burned. A flight readiness review at MSC on November 26 had found the LLTV ready for use in astronaut training, and 10 flight tests had been made before the accident. Additional Details: Apollo lunar landing training vehicle No 1 crashed and burned at Ellington AFB. References: 16 .

Released 24 Romb radar calibration subsatellites. References: 1 , 2 , 5 , 6 .

Deployed from NOSS 2. References: 1 , 2 , 5 , 6 , 278 .

Deployed from NOSS 2. References: 1 , 2 , 5 , 6 , 278 .

Deployed from NOSS 2. References: 1 , 2 , 5 , 6 , 278 .

Ocean surveillance; aka White Cloud type spacecraft; Navy Ocean Surveillance Satellite; PARCAE. References: 1 , 2 , 5 , 6 , 172 , 278 .

Area survey photo reconnaissance satellite; returned film capsule. References: 1 , 2 , 6 .

Intended to replace Molniya 1-48; failed. Investigation of the upper atmosphere and outer space. References: 1 , 2 , 5 , 6 , 64 , 65 .

Military navigation satellite. Replaced Cosmos 1417. References: 1 , 2 , 5 , 6 .

Military cartographic satellite; returned film capsule. References: 1 , 2 , 6 .

Glonass. Testing components and apparatus from the space navigation system being set up to determine the position of Soviet civil aircraft and vessels in the Soviet merchant marine and fishing fleet. Three satellites launched by a single rocket. References: 1 , 2 , 5 , 6 , 67 , 274 .

Glonass. Testing components and apparatus from the space navigation system being set up to determine the position of Soviet civil aircraft and vessels in the Soviet merchant marine and fishing fleet. Three satellites launched by a single rocket. References: 1 , 2 , 5 , 6 , 67 , 274 .

Glonass. Testing components and apparatus from the space navigation system being set up to determine the position of Soviet civil aircraft and vessels in the Soviet merchant marine and fishing fleet. Three satellites launched by a single rocket. References: 1 , 2 , 5 , 6 , 67 , 274 .

Hubble Space Telescope Servicing Mission 1 - solar array drive replacement. References: 66 .

NATO encrypted communications relay. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C). References: 1 , 2 , 5 , 6 .

CSAR II (Canadian materials processing payload)

Repositioned docking adapter. References: 66 .

Plane 6. Ascending node 325.8 degrees. References: 4 .

Plane 6. Ascending node 325.8 degrees. Not in service. References: 4 .

Geosynchronous. Stationed over 79.2W Launch vehicle put payload into geosynchronous transfer orbit with MRS trajectory option. Used HS-601 XIPS ion engine for station keeping. References: 4 , 278 .