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298 SMITHSONIAN ANNALS OF FLIGHT FIGURE 2.—First test in progress. With the first combustion chamber we made a considerable number of more-or-less successful tests at increasing thrusts, finally running the apparatus for periods as long as several minutes at a time. I would frequently run the tests during the lunch hour when the workmen from the shop would come out, gather around the rocket, and amuse themselves by throwing stones into the jet to see how high they would be hurled. I remember once two of the men got a large board and attempted to force it into the jet. Although the thrust of the rocket was only about 25 pounds, they found it difficult to hold the board in position against this force. The tests were duly reported in the April 1938 issue of the journal of the American Rocket Society 4 and constitute some of the very earliest measurements on rockets ever described. Tests of September 1938 After the first set of tests, it was obvious that a man with only two hands could not juggle three valves—air, gasoline, and water—simultaneously, especially since smooth combustion could be obtained only at certain very delicate settings of the mixture ratio. During the succeeding months, the chamber was modified to eliminate the water by using refractory nozzles. A continuously indicating thrust measuring device was provided and a gauge glass was added to the gasoline tank. A Kodak timer was used, and the gauges were photographed by a still camera at intervals determined by the length of time required to wind the film. Figure 3 shows a typical photographic record of the instrument panel. In September 1938, another series of tests was made, again using compressed air and gasoline. Three types of refractory nozzles were used; graphite, fireclay, and aluminum oxide cast from thermit slag. Except for the nozzle change, the motor was identical to that used previously. Only the aluminum oxide nozzle was found satisfactory; the others eroded too rapidly. With the A1203 nozzle, however, runs of many minutes could be made before the chamber became overheated. 5 For record purposes, runs from 15 to 45 seconds were made. The data obtained in these September 1938 tests are summarized in the following tabulation: FIGURE 3.—Instrument panel.
NUMBER S P. (P»i) P, (psi) Po (psi) T (lb) t (sec) f (lb) v (fps) Eth (%) 10 i 300 100 100 70 6 19 0.12 2010 6.5 2 300 110 160 90 7 15 0.065 3250 16.8 3 300 140 200 100 10.4 20 0.13 3220 16.6 R,
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I L SfS HK5M SMITHSONIAN ANNALS OF
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A Bibliographic Note The series Smi
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SMITHSONIAN ANNALS OF FLIGHT Throug
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VI SMITHSONIAN ANNALS OF FLIGHT 19.
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1 Some Jet Propulsion Formulas of O
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NUMBER 10 — — —— . . . -
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SMITHSONIAN ANNALS OF FLIGHT FIGURE
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During these years, in which the fu
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10 SMITHSONIAN ANNALS OF FLIGHT the
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12 SMITHSONIAN ANNALS OF FLIGHT FIG
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18 3. French Patent 318,667, 13 Feb
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20 SMITHSONIAN ANNALS OF FLIGHT tie
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Appendix Considerations Concerning
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NUMBER 10 In the present case, ther
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NUMBER 10 27 III Let us consider wh
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NUMBER 10 29 = 2100 sec, the rate w
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NUMBER 10 31 bring us far away from
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34 SMITHSONIAN ANNALS OF FLIGHT pro
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42 Figure 15. The dispersion of the
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44 SMITHSONIAN ANNALS OF FLIGHT sys
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46 SMITHSONIAN ANNALS OF FLIGHT com
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50 SMITHSONIAN ANNALS OF FLIGHT pla
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Robert H. Goddard and the Smithsoni
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NUMBER 10 to help Mr. Goddard in de
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NUMBER 10 61 flash powder which mig
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NUMBER 10 63 FIGURE 5.—Modificati
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NUMBER 10 65
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NUMBER 10 tion for a U.S. patent on
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NUMBER 10 69 70. Goddard to Abbot,
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72 SMITHSONIAN ANNALS OF FLIGHT lif
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Recollections of Early Biomedical M
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NUMBER 10 r FIGURE 2.—First biome
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FIGURE 4.—Presentation by Dr. Con
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Astrodynamics is defined in terms o
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NUMBER 10 83 But it should be recog
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NUMBER 10 85 were experimenting in
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Vladimir Mandl: Founding Writer on
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NUMBER 10 89 PATENTNl OftAD REPUBLI
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10 Developments in Rocket Engineeri
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NUMBER 10 93 FIGURE 2.—The first
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NUMBER 10 FIGURE 4.—The ORM-9 eng
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NUMBER 10 97 FIGURE 9.—ORM-50 eng
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NUMBER 10 99 Section along AA Firin
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NUMBER 10 101 FIGURE 13.—The expe
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11 A Historical Review of Developme
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NUMBER 10 105 FIGURE 5.—Lithergol
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NUMBER 10 that the possibility of a
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NUMBER 10 109 the contrary; we then
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NUMBER 10 111 rocket combustion cha
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12 On the GALCIT Rocket Research Pr
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NUMBER 10 115 The undertaking we ha
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NUMBER 10 117 advise on the support
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NUMBER 10 methyl-alcohol rocket mot
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NUMBER 10 121 5. "Rocket Performanc
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NUMBER 10 123 FIGURE 5.—Overall v
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NUMBER 10 on the possibility of usi
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NUMBER 10 33. Letters (note 14). 34
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130 SMITHSONIAN ANNALS OF FLIGHT ce
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15 Ludvik OcenaSek: Czech Rocket Ex
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NUMBER 10 159 FIGURE 2.—Ludvik Oc
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NUMBER 10 161 FIGURE 5.—Ludvik Oc
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NUMBER 10 163 FICURE 6.—a, Launch
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NUMBER 10 165 quarry near Prague. E
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168 SMITHSONIAN ANNALS OF FLIGHT re
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17 First Rocket and Aircraft Flight
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NUMBER 10 179 The rocket project wa
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NUMBER 10 181 FIGURE 2.—Second st
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NUMBER 10 FIGURE 3.—DM-2 ramjet e
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18 On Some Work Done in Rocket Tech
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NUMBER 10 187 FICURE 3.—Launching
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NUMBER 10 189 on the smoked tape. A
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NUMBER 10 191 FIGURE 9.—Indicatin
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NUMBER 10 193 FIGURE 13.—Control
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NUMBER 10 195 2000 rpm by rotating
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NUMBER 10 197 Lubricant ^ 9a' " FIG
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NUMBER 10 199 of radio signals to t
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A^ -/••••••.\ D+ VE •
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240 diesel fuel and lox began on th
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242 14 May 1940: Reviewed layout fo
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