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300 SMITHSONIAN ANNALS OF FLIGHT - FIGURE 5.—Oxygen test stand. *& *T fr regulators with the outlet connection. In this fashion I was able to completely bypass the regulator, conforming to the letter, if not the spirit, of the rule book, giving the appearance (see Figure 5), at least to the casual observer, that the regulator was being employed! For this series of tests, a new thrust chamber was built of light-gauge stainless steel, designed to be water cooled and equipped to accept interchangeable nozzles, either metal or refractory. With this chamber, and the test stand modified for the use of gaseous oxygen, a final program of tests was performed in December 1938. The initial tests were performed to evaluate refractory nozzles. Silica, alumina, and tungsten carbide were tried. Only the latter gave reasonable success, although it tended to oxidize. The tungsten carbide nozzle also cracked from thermal shock, but the pieces remained in place. 7 r1 ) l •
NUMBER 10 301 Figure 6 shows these tests in progress. Note the blow torch for igniting* the motor, the natural convection water cooling jacket, and the different appearance of the flame under different operating conditions. Tests of this nature were continued for five or six months into 1939 and culminated in operation of a motor having forced convective cooling with water. At this point, the U.S. Navy expressed an interest in the work, looking to the use of rockets to assist the takeoff of large flying boats. My design for such a rocket, prepared in October 1939, is shown in Figure 7. This particular drawing was used as an instrument for getting a development program started. This program, initiated two years later under my direction, continued the development of rockets for JATO and guided missiles throughout World War II. NOTES Under the title Razrabotka raketnykh dvilateley v Annapolise v 1936-1938, this paper appeared on pages 162-68 of Iz istorii astronavtiki i raketnoi tekhniki: Materialy XVIII mezhdunarodnogo astronavticheskogo kongressa, Belgrad, 25- FIGURE 7.—Proposed rocket engine for aircraft take-off assist. 29 Sentyavrya 1967 [From the History of Rockets and Astronautics: Materials of the 18th International Astronautical Congress, Belgrade, 25-29 September 1967], Moscow: Nauka, 1970. 1. "Light Weight Rocket Motor Developed in Germany," Bulletin of the American Interplanetary Society, no. 8, March- April 1931, p. 14; and "German Rocket Car Tested," ibid., no. 9, May 1931, p. 1. 2. Robert C. Truax, "Rocket Development," U.S. Naval Institute Proceedings, September 1964, pp. 81-94. 3. Truax had written Dr. Robert H. Goddard during this time and received a reply with comments to his questions and suggesting that he obtain a copy of his "Liquid-Propellant Rocket Development" (<strong>Smithsonian</strong> Miscellaneous Collections, vol. 95, no. 3, 1936). See Esther C. Goddard and G. Edward Pendray, editors, The Papers of Robert H. Goddard (New York: McGraw-Hill Book Company, 1970), vol. 2, pp. 985, 988.—Ed. 4. Truax, "Gas, Air, Water," Astronautics, no. 40 (April 1938), pp. 9-11. 5. Truax, "Annapolis Motor Tests," Astronautics, no. 42 (February 1939), pp. 6-10. 6. John Shesta, H. Franklin Pierce, and James H. Wyld, "Report on the 1938 Rocket Motor Tests," Astronautics, no. 42 (February 1939), pp. 2-6. 7. Truax, "Addenda to September Report," Astronautics, no. 42 (February 1939), p. 10.
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A Bibliographic Note The series Smi
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