Coenders at Saar Roechling proposed the concept of sequentially electrically activated angled side chambers to provide additional acceleration of a shell during its passage up the barrel of the gun. This allowed a muzzle velocity of over 1500 m/s. A 140 m long cannon using this concept would be capable of delivering a 140 kg shell over a 165 km range. Funding is finally obtained to build a subscale prototype.

Throughout the early 1940's Thiel and his team sought to produce a single chamber 25 tonne thrust engine in place of the kludged prototype engine that used 18 separate 1.5 tf chambers. They managed to demonstrate a 60 second burn time in the 18-chamber design, but the engine itself was considered too complicated to fabricate in production, requiring thousands of hand-assembled tubes to introduce fuel and oxidiser into the chamber. Thiel sought to replace these thousands of tubes with a simpler injection system - rows of simple bored holes on a flat injector plate at the head of the chamber. Beck at the Technische Hochschule in Dresden developed a ring-pattern injector that worked well in subscale engines. But the design proved unstable in the 25 tf engine. Therefore, it was decided to stick with the 18-head chamber for V-2 production.

The A4 assembly hall at Area 7 at Peenemuende was 30 m high and 50 m long. After assembly, the missile was moved to the cold flow test stand. There each rocket was tested and calibration documents were generated, necessary for the launch troops to take into account when preparing the rocket and programming its guidance system. The launch pad itself was ringed by a 7 m wide concrete embankment, and sunk 6 m into the ground. The viewpoint was 150 m from the pad, at the southern, smaller end of the complex.

The pad was surrounded by instrumentation rooms. Water was delivered at 500 litres/second through a 1.20 m diameter pipe to a molybdenum steel cooling section, consisting of many pipes running around the exhaust blast diverter. Other test stands included number 10, where the effects of the rocket exhaust on different material surfaces was tested; and number 8, where newly delivered engines were fired and calibrated. These certification tests ran as long as 650 seconds on the water-cooled stand. Area 9 was used for launches of the Wasserfall surface-to-air missile, and Area 2 for tests of the A4 using nitric acid and Visol as propellants. Area 4 was devoted to firing tests of engines installed in aircraft fuselages, and Area 3 contained the 1000 kgf engine test stand. This stand included pump and steam test stands, and a hydrogen peroxide plant. Area 6 was built to the same design as the largest test stands at Kummersdorf, and used for A5 tests. Hundreds of A5's were shot from Greifswalder Oie.

American test pilot astronaut 1978-1993. Flew 550 combat missions in Vietnam. USAF helicopter pilot who would fly his T-38 trainer at alarmingly low altitude during cross-country trips. Paradoxically later appointed NASA Administrator for Safety. 3 spaceflights, 19.0 days in space. Flew to orbit on STS-51B (1985), STS-33, STS-44.

Barre completed a comprehensive report on the military potential of rocketry. He sketeched out ballistic missiles with 1000 km range, powered by liquid oxygen/gasoline engines. Armor-piercing rockets could reach 2000 m/s and defeat any tank armor. Anti-aircraft rockets would intercept aircraft in half the time. Rocket-boosted bombs would destroy enemey emplacements. Air-augmented rockets could reach even higher range and efficiencies.

Ukrainian test pilot cosmonaut 1977-1988. Graduated from Chernigov Higher Air Force School, 1964. Buran test pilot; cosmonaut training December 1978 - July 1980. Later a civil test pilot for the Soviet Air Force Ministry. Died of a brain tumor in Moscow. 1 spaceflight, 7.9 days in space. Flew to orbit on Soyuz TM-4 (1987).

Barre's report worked its way through the wartime bureaucracy, finally reaching the Minister of State for War in Vichy France. It is immediately classived top secret, and Barre is given 300,000 francs to start development of a liquid propellant rocket. In order to keep the work from the notice of the occupying Germans, it is officially for development of automotive gas generators.

Messerschmitt Me-163A powered by "cold" H. Walther rocket successfully flown at Augsburg, Germany, development of which had begun in 1937, but "cold" engine proved unreliable. Flights were also made in October which reached speeds of 1,003 km/hr, or Mach 0.85.

The Goddard P series pump-turbine tests had run from November 1939-October 1941. The series included 15 proving-stand tests and nine attempts at flight tests, of which only two resulted in flights. Average interval between tests was 28 days. This also ended Goddard development of liquid fuel rockets for space flight. Beginning in September 1941 with the impending involvement of the US in the world war, the Goddard rocket establishment worked under contracts with the Bureau of Aeronautics of the Navy Department and the Army Air Forces. Up to that point Goddard's team had completed 103 liquid rocket proving stand tests and made 48 attempts at flight tests, of which 31 resulted in rocket flights

In preparation for the A9/A10 transatlantic missile, the Peenemuende team completed design of a Mach 10 wind tunnel. However construction would not begin for another two years due to priority on devoting all available engineering time to getting the A4 into production.