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^ ^ ^ FIGURE 12.—Layout of KB-7 engine test stand in 1937, prior to installation of periscope: 1, firing bay; 2 shaft for escape of spent gases; 3, lox bay; 4, alcohol bay; 5, bay for spectrographic measurement; 6, bay for compressed nitrogen and air.
NUMBER 10 193 FIGURE 13.—Control and instrument panel for visual measurement and making motion picture records at KB-7 test stand. tute. In 1937 a ceramic laboratory (chief of the laboratory was M.Yu. Gollender) was organized. A ceramic developed for the nozzle was manufactured of chemically purified electrically molten magnesium oxide with prolonged calcination carried out according to a special program. During operation of the engine for 60-90 sec the throat diameter of these nozzles increased by 0.5-1.5 mm. Together with utilization of ceramics in the engine all-metal cooled structures of the engine were partly developed, the nozzle mainly was manufactured with a multiple thread from the side of the cooling liquid (see, for example, Figure 26). An experimental engine was designed, built, and FIGURE 14.—Direct-action explosive valve: 1, electric primer; 2, non-return valve; and 3, diaphragms. FIGURE 15.—Breakdown explosive valve: 1, diaphragm; 2, punch; 3, spring; 4, explosive valve. tested in which the casing of the nozzle was made of welded coils of square tubing. All-metal engines with smooth wall surface from the side of cooling liquid (F. L. Yakaytis) were designed. To obtain more accurately the characteristics of the combustion products of different types of fuels, a method of calculation of I-S diagrams for combustion products of fuels, taking into consideration the latest data on dissociation, was worked out for KB-7 by the Institute of Chemical Physics (Ya.B. Zeldovich and D.A. Frank-Kamenetskiy). Investigations of complete fuel combustion in the engine by the method of chemical analysis, carried out at KB-7 in cooperation with the Institute, showed that with accepted volumes of combustion chambers, completeness of combustion at first increased (this may be related to the influence of the walls) and then became constant and maintained a comparatively high level. The test results proved the balanced exhausting of the combustion products of alcohol with oxygen. Research into special problems involved in mixture formation and combustion in a rocket engine required a more profound knowledge of changes developing in the composition of combustion products and temperature in different sections of the FIGURE 16.—On-board remote-reading manometers: a, Contact-type; b, Rheostat-type.
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A Bibliographic Note The series Smi
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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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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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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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Recollections of Early Biomedical M
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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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Vladimir Mandl: Founding Writer on
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10 Developments in Rocket Engineeri
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11 A Historical Review of Developme
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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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12 On the GALCIT Rocket Research Pr
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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 10 253 FIGURE 6.—a, Model
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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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25 Early Developments in Rocket and
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27 Annapolis Rocket Motor Developme
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304 Frank-Kamenetskiy, D.A., 193 Fr
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TUT10N NOIifUIISNt NVINOSHlitNS S3f
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