June, another presentation was made to Washington officials proposing development for a ballistic  missile system of 1,000 or more nautical miles range. Throughout this study, it was repeatedly stressed that this development could be effected by  redesign of existing components. The REDSTONE had served as an excellent laboratory and could still be used in such a way to test and prove long-range missile components. In fact, 19 REDSTONES been earmarked for these purposes, especially with regard to resolving the nose cone re-entry problem. A  number of alternative methods were included as to the way in which the missile could be employed, which involved ranges above and below the 1,000- mile mark. All of these proposals hinged on the use of NAA's engine, which was now rated at 135,000 pounds of thrust and had undergone some 334  static tests 9 . No active results came from this proposal. Continuing with the successive monthly proposals, Redstone Arsenal, in July, dropped all  recommendations for shorter range and concentrated on the 1,500-mile version. As to characteristics of the weapon being considered, it was to be a  single-stage, liquid-fuel  ballistic rocket designed to carry a 2,000- pound payload to the specified range. A swivel- mounted 150,000-pound thrust NAA  engine would be used as the power unit (static tests of engines of this capability had already been conducted). The missile would have a diameter of 95  inches and a length of 1,114 inches. Propulsion would be provided by using 45,860 pounds of JP4 as fuel and 103,120 pounds of L0X as the oxidizer to  acquire a maximum burning time of 119.3 seconds. Launching weight would be 167,000 pounds. The missile was not fin controlled but, instead, would  have attached two hydrogen peroxide vernier thrust nozzles of 1,000 pounds of thrust ______________________________