Three flight tests were made between February and April in a He-112 equipped with a 300 kgf liquid fuel rocket engine by Flight-Captain Erich Warsitz from Neuhardenberg near Berlin. On the final flight Warstiz smelled something burning, and made an emergency belly landing. He survived but the aircraft had to be written off. Engine exhaust had flowed back into the space between the engine and fuselage and burnt cables. Work on this engine continued at Area 4 at Peenemuende. The planned application was a 1000 kgf JATO pod, with a burn time of 30 seconds, to boost bombers into the air.

Russian cosmonaut 1962-1997. First woman in space, aboard Vostok 6. But the flight was propaganda and future spaceflight opportunities did not develop. Was married to cosmonaut Andrian Nikolayev. Later a leading Communist politician. 1 spaceflight, 3.0 days in space. Flew to orbit on Vostok 6 (1963).

Joint German Army-Air Force rocket research station opened at Peenemünde on the Baltic Sea. The Army Ordnance rocket program under Capt. Walter Dornberger moved 90 of its staff from Kummersdorf. Thiel and five staff working on V-2 rocket engine development remained at Kummersdorf until the summer of 1940, when the test stands at Peenemuende were finally completed..

Rocket was equipped with streamline retractable air vanes and wire-wound pressure storage tank; length 17 ft 8 in.; diameter 9 in.; altitude 3250 ft; duration 29.5 sec; much-improved stabilisation. Final results of Section B of L Series, from November 1936-May 1937, showed two proving-stand tests, and six flight test attempts, all of which resulted in flights. Average interval between tests 22 days

Theodore von Kármán, Director of the Guggenheim Aeronautical Laboratory at the California Institute of Technology at Pasadena, founded group which began experiments in design fundamentals of high-altitude sounding rocket. The group, named the Cal Tech Rocket Research Project, consisted of Frank J. Malina, Tsien Hsue-sen, A. M. O. Smith, John W. Parsons, Edward Forman, and Weld Arnold. This was the origin of the Jet Propulsion Laboratory.

These would run through August 9, 1938 (L16-L30). Section C rockets included light tank construction, movable-tailpiece (i.e. gimbal) steering, catapult launching, and further development of liquid nitrogen tank pressure method. Lengths varied from 17 ft 4.25 in. to 18 ft 5.75 in.; diameter 9 in., weight empty varied from 80 to 1091b; loaded weight about 170 lb or more; lift of static tests varied from 228 lb to 477 lb; jet velocities from 3960 to 5340 ft/sec. These tests indicated extremely high temperatures for the jet: pebbles of the cement gas deflector were fused and thrown out, starting fires more than 50 ft from the tower.

Rocket was equipped with movable-tailpiece or gimbal steering, with wire-wound tanks and barograph; length 18 ft 5.5 in.; diameter 9 in.; weight empty 95 lb 5 oz; loaded 162 lb 5 oz; 39 lb liquid oxygen, 28 lb gasoline; altitude 2055 ft; duration 28 sec; parachute opened near ground, checked speed; coasted one-eighth of ascent; landed 1000 ft from tower.

First launch of an A3 rocket. New facilites being built at Peenemuende were not ready, so the A3 launches were made from the offshore island of Greifswalder Oie. The A3 launched on this day was 6.5 m long and 70 cm in diameter. The engine occupied the first 2 m of the fuselage. The missile had a 750 kg lift-off mass, including 450 kg of propellant, which was pressurised to 20 atmospheres. The 1.5 tonne thrust engine had a 1900 m/s exhaust velocity and a 45 second burn time. The parachute deployed 3 seconds after launch, and the engine cutoff at 6.5 seconds. The rocket impacted and exploded 300 m from the launch point.

Final launch of the A3. The rocket is fired without the parachute that ruined the first two attempts, but in heavy fog. It is more successful than earlier shots, but at 800 to 1000 m altitude it also veers over and thrusts its way downward into the ocean. Analysis showed that the fins steering the rocket could not overcome the 8 m/s wind blowing at the time of the launch. Further study shows that at the low speed of initial rocket acceleration, a wind as little as 4 m/s would be enough to topple the rocket. A rudder area ten times greater than is needed to control the rocket at low speeds. This result leads to the decision to abandon the A3 configuration and build the A5 to support development of the A4 missile.