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170 SMITHSONIAN ANNALS OF FLIGHT I Gases Ignition limits of combustible mixtures Acetylene fy "2 Hydrogen H% Carbon dioxide CO Water (blue) gas C0*H2 Hydrogen sulfide H%S Ethylene fy^ Dithiane C% Hi Ethane Z% Hs Methane jjf^ . Ammonia NH3 Butylene ^H2 Propylene Cj Hg Pentane tjH^ Propane fyHj Butane II Vapors Ct, Hfo Carbon bisulfide C$i Ethyl ether Ci,H^0 Methyl alcohol CH
NUMBER 10 171 Lithium [Al2] powder heat content (cal/1) 10000 - 8000 6000 4000 2000 0 o°c ^.^£20°C ^50°C 200 400 600. P(abs atm") Cast magnesium Gasoline, kerosene •Benzine Phosphorus Ethylene blue gas oil gas Methane lighting gas hydrogen FIGURE 4.—Calorific content per liter of fuel at various pressures. As the work procedure has shown, our choice of propellant was a good one. At the same time, we also decided to use "solid benzene" as a propellant. Therefore the ramjet engine intended for the operation on an artillery projectiles was designed with due regard to the possibility of using both phosphorus and benzene. To prepare a ramjet engine model for free flight testing, a special mobile test stand was constructed in which the rotating combustion chamber of a jet engine was installed and on 12 July 1933, at one of the proving grounds near Moscow, the first test of the phosphorus-operated combustion chamber in the rotating ramjet engine was carried out. The aim of the first test was to investigate the properties of phosphorus as a propellant for a jet engine, and in particular for an engine installed on an artillery projectile. The whole second half of 1933 was devoted to the preparation of the ramjet engine to the flight tests. Owing to the harmonious and cohesive work of a small group of the third team of GIRD, all the bench tests and preparatory work that had been set by the program to pave the way for the beginning of flight tests were effected in a short period of time, and in autumn 1933 the ramjet engines were given their first flight tests. The ramjet engine models had the contour of a long-range shell of a 76-mm (3-in.) cannon (Figure 5). The internal part of a ramjet engine comprised an entry channel, a combustion chamber and a nozzle. The propellant grain was placed directly in the combustion chamber. In order to prevent the penetration of combustion gases into the internal cavity of the engine, the exit nozzle was plugged with a metal stopper (part 4 in Figure 6) prior to firing the cannon. After the ramjet engine had cleared the cannon channel, the plug would detach from the projectile and fall near the cannon. Direction of flight a FIGURE 5.—Ramjet engine under study: a, Plan view; b, design; c, rear part of missile, with plug. 1, ogival part (nose) 5, nozzle 2, fuel cap 6, cavity for payload 3, shell body 7, intake channel 4, plug 8, air inlet
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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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18 3. French Patent 318,667, 13 Feb
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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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42 Figure 15. The dispersion of the
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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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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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240 diesel fuel and lox began on th
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242 14 May 1940: Reviewed layout fo
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NUMBER 10 253 FIGURE 6.—a, Model
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262 SMITHSONIAN ANNALS OF FLIGHT N?
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264 B C FIGURE 7.—Drawing from Sw
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266 SMITHSONIAN ANNALS OF FLIGHT in
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24 Some New Data on Early Work of t
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NUMBER 10 271 jy.. FIGURE 3. /# £
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NUMBER 10 275 thrust engines. A for
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25 Early Developments in Rocket and
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NUMBER 10 279 Time reference 5 sec
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NUMBER 10 281 During measurement of
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27 Annapolis Rocket Motor Developme
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NUMBER S P. (P»i) P, (psi) Po (psi
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NUMBER 10 301 Figure 6 shows these
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304 Frank-Kamenetskiy, D.A., 193 Fr
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TUT10N NOIifUIISNt NVINOSHlitNS S3f
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