ALBERT — All Library Books, journals and Electronic Records Telegrafenberg

1

Unbekannt

Tracking and orbit determination program of the Jet Propulsion Laboratory (1960)

Hudson, R. H. ; Carr, R. E.

In: CASI

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Publikationsdatum: 2005-11-29

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Materialart: SEMINAR PROC. ON TRACKING PROGRAMS AND ORBIT DETERMINATION 26 FEB. 1960; P 10-35

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2

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Methods for nonlinear least squares problems and convergence proofs (1960)

Morrison, D. D.

In: CASI

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Publikationsdatum: 2005-11-29

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Materialart: JPL SEMINAR PROC. ON TRACKING PROGRAMS AND ORBIT DETERMINATION 26 FEB. 1960; P 1-9

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3

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Satellite orbit determination and prediction utilizing JPL Goldstone 85-ft antenna and the JPL tracking program (1960)

Muhleman, D.

In: CASI

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Publikationsdatum: 2005-11-29

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Materialart: SEMINAR PROC. ON TRACKING PROGRAMS AND ORBIT DETERMINATION 26 FEB. 1960; P 53-61

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4

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Spacecraft nasa release no. 60-312-1 (1960)

In: CASI

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Publikationsdatum: 2004-10-02

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5

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Remarks on the programming system of project space track (1960)

Wahl, E. W.

In: CASI

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Publikationsdatum: 2005-11-29

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Materialart: JPL SEMINAR PROC. ON TRACKING PROGRAMS AND ORBIT DETERMINATION 26 FEB. 1960; P 161-164

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6

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Western satellite research network (1960)

Mc Cue, G. A. ; Pierce, D. A.

In: CASI

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Publikationsdatum: 2005-11-29

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Materialart: JPL SEMINAR PROC. ON TRACKING PROGRAMS AND ORBIT DETERMINATION 26 FEB. 1960; P 128-138

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7

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Orbital and rotational motion of a rigid satellite (1960)

Lundquist, C. A. ; Naumann, R. J.

In: CASI

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Publikationsdatum: 2005-11-29

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Materialart: JPL SEMINAR PROC. ON TRACKING PROGRAMS AND ORBIT DETERMINATION 26 FEB. 1960; P 96-103

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8

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Technical aspects of satellite tracking on IBM computers at Smithsonian Astrophysical Observatory in Cambridge, Massachusetts (1960)

Rossoni, J. P.

In: CASI

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Publikationsdatum: 2005-11-29

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Materialart: JPL SEMINAR PROC. ON TRACKING PROGRAMS AND ORBIT DETERMINATION 26 FEB. 1960; P 185-191

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9

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The programming system for orbit determination at the IBM Space Computing Center (1960)

Mowlem, A. R.

In: CASI

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Publikationsdatum: 2005-11-29

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Materialart: JPL SEMINAR PROC. ON TRACKING PROGRAMS AND ORBIT DETERMINATION 26 FEB. 1960; P 119-127

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10

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Survey of space flight decks used at ABMA (1960)

Sperling, H. J.

In: CASI

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Publikationsdatum: 2005-11-29

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Materialart: JPL SEMINAR PROC. ON TRACKING PROGRAMS AND ORBIT DETERMINATION 26 FEB. 1960; P 104-107

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11

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NASA computing center predictions (1960)

Bryant, R. W.

In: CASI

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Publikationsdatum: 2005-11-29

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Materialart: JPL SEMINAR PROC. ON TRACKING PROGRAMS AND ORBIT DETERMINATION 26 FEB. 1960; P 114-118

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12

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Evaluation of Pioneer 4 orbit-determination program (1960)

Hiroshige, Y. ; Eimer, M.

In: CASI

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Publikationsdatum: 2005-11-29

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Materialart: SEMINAR PROC. ON TRACKING PROGRAMS AND ORBIT DETERMINATION 26 FEB. 1960; P 36-52

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13

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Tracking a passive satellite by the Doppler method (1960)

Richards, P. B.

In: CASI

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Publikationsdatum: 2005-11-29

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Materialart: JPL SEMINAR PROC. ON TRACKING PROGRAMS AND ORBIT DETERMINATION 26 FEB. 1960; P 192-195

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14

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Early orbit determination scheme for the Juno space vehicle (1960)

Speer, F. ; Kurtz, F.

In: CASI

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Publikationsdatum: 2005-11-29

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Materialart: JPL SEMINAR PROC. ON TRACKING PROGRAMS AND ORBIT DETERMINATION 26 FEB. 1960; P 62-95

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15

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A computer program for first-order error propagation in satellite orbit prediction (1960)

Swerling, P.

In: CASI

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Publikationsdatum: 2005-11-29

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Materialart: JPL SEMINAR PROC. ON TRACKING PROGRAMS AND ORBIT DETERMINATION 26 FEB. 1960; P 199-203

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16

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Lunar and interplanetary trajectory determination activities at General Electric (1960)

Szebehely, V. G.

In: CASI

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Publikationsdatum: 2005-11-29

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Materialart: JPL SEMINAR PROC. ON TRACKING PROGRAMS AND ORBIT DETERMINATION 26 FEB. 1960; P 196-198

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17

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Interim definitive orbits determined at the NASA computing center (1960)

Bryant, R. W.

In: CASI

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Publikationsdatum: 2009-11-16

Schlagwort(e): unknown

Materialart: JPL SEMINAR PROC. ON TRACKING PROGRAMS AND ORBIT DETERMINATION 26 FEB. 1960; P 108-113

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18

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Nuclear rockets for interplanetary propulsion (1960)

Johnson, P. G. ; Rom, F. E.

In: CASI

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Publikationsdatum: 2006-10-26

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19

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On the question of a strength criterion for anisotropic materials (1960)

Geogdzhaev, V. O.

In: CASI

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Publikationsdatum: 2006-10-26

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20

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Analysis of the flow and energy separation in a turbulent vortex (1960)

Perlmutter, M. ; Deissler, R. G.

In: CASI

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Publikationsdatum: 2006-10-26

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21

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Geophysical effects of the trapped particle layer (1960)

Jastrow, R.

In: CASI

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Publikationsdatum: 2006-10-26

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22

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UNSTEADY TURBULENT HEAT TRANSFER IN TUBES (1960)

Sparrow, E. M. ; Siegel, R.

In: CASI

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Publikationsdatum: 2006-10-26

Schlagwort(e): GEOPHYSICS

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23

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THE THERMAL CONDUCTIVITY OF GAS MIXTURES IN CHEMICAL EQUILIBRIUM (1960)

Butler, J. N. ; Brokaw, R. S.

In: CASI

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Publikationsdatum: 2006-10-26

Schlagwort(e): GEOPHYSICS

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24

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TRANSFER, FLOW, AND HEAT TRANSFER ABOUT A ROTATING DISK (1960)

Gregg, J. L. ; Sparrow, E. M.

In: CASI

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Publikationsdatum: 2006-10-26

Schlagwort(e): GEOPHYSICS

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25

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Electric propulsion for space flight (1960)

Mickelsen, W. R.

In: CASI

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26

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Aerospace medicine and biology. an annotated bibliography, 1954 literature, volume iii (1960)

Plavnieks, I. M. ; Marrow, E. ; Voulgaris, K. ; [weitere]

In: CASI

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27

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On the motion of a satellite in an asymmetrical gravitational field (1960)

Musen, P.

In: CASI

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Publikationsdatum: 2006-10-26

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28

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Manned space flight - present and future steps (1960)

Strass, H. K. ; Gilruth, R. R.

In: CASI

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Publikationsdatum: 2006-10-26

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29

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Physico-chemical reactions during nozzle flow (1960)

Morris, J. F.

In: CASI

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Publikationsdatum: 2012-05-22

Schlagwort(e): unknown

Materialart: AGARD THE CHEM. OF PROPELLANTS 1960; P 410-490

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30

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On deposits in jet engines (1960)

Breitwieser, R.

In: CASI

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Publikationsdatum: 2012-05-22

Schlagwort(e): unknown

Materialart: AGARD THE CHEM. OF PROPELLANTS 1960; P 491-533

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31

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Compatibility of titanium with liquid propellants (1960)

Chafey, J. E.

In: Other Sources

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Publikationsdatum: 2019-05-31

Schlagwort(e): unknown

Materialart: NASA-CR-54950 , MRG-171

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32

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Low temperature evaluation of shear pin and tensile bolt materials (1960)

Tryon, R. W.

In: Other Sources

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Publikationsdatum: 2019-05-31

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Materialart: NASA-CR-54701

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33

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Photoionization of atomic oxygen and nitrogen (1960)

Dalgarno, A.

In: Other Sources

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Publikationsdatum: 2019-05-31

Schlagwort(e): unknown

Materialart: NASA-CR-74245 , GCA-TR-60-5-N , AD-257880

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34

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Celestial frontiers (1960)

Clement, G. H.

In: Other Sources

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Publikationsdatum: 2019-05-31

Schlagwort(e): unknown

Materialart: P-1915 , AD-616567

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35

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AN EXPERIMENTAL INVESTIGATION OF ABLATING MATERIALS AT LOW AND HIGH ENTHALPY POTENTIALS (1960)

Rashis, B. ; Walton, T. E., Jr.

In: CASI

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Publikationsdatum: 2019-05-11

Beschreibung: Effect of enthalpy variation on ablating materials

Schlagwort(e): GEOPHYSICS

Materialart: NASA-TM-X-263

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Überblick

36

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CASCADE INVESTIGATION OF COOLING CHARACTERISTICS OF A CORRUGATEDINSERT AIR-COOLED TURBINE BLADE FOR USE IN A TURBOPROP ENGINE (1960)

Richards, H. T.

In: CASI

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Publikationsdatum: 2019-05-11

Beschreibung: Heat transfer of air-cooled turbine blade for turboprop engine

Schlagwort(e): GEOPHYSICS

Materialart: NASA-TM-X-85

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Überblick

37

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United States Space Carrier Vehicle Program (1960)

von Braun, Wernher

In: Other Sources

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Publikationsdatum: 2019-01-25

Beschreibung: No abstract available

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38

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Properties of root locus asymptotes (1960)

Titsworth, R. C. ; Lorens, C. S.

In: Other Sources

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Publikationsdatum: 2019-05-25

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Materialart: JPL-EP-587

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39

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A miniature photographic camera for space probe instrumentation (1960)

Stuart, J. L.

In: CASI

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Publikationsdatum: 2019-05-25

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Materialart: JPL-TR-34-137

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40

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Reduction of errors in vibratory gyroscopes by double modulation (1960)

Bush, R. W. ; Newton, G. C., Jr.

In: CASI

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Publikationsdatum: 2019-05-25

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41

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Economic aspects of developing and orbiting a space station (1960)

Margolis, M.

In: CASI

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Publikationsdatum: 2019-05-31

Schlagwort(e): unknown

Materialart: P-1975 , AD-224321

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42

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On the comparison between the solutions of ordinary differential systems (1960)

Onuchic, N. ; Lakshmikantham, V.

In: CASI

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Publikationsdatum: 2019-05-22

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43

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Jpl light collimation and intensity studies (1960)

Riise, H. N.

In: Other Sources

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Publikationsdatum: 2019-05-22

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Materialart: NASA-CR-58679 , WT-TF-3

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44

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Basic principles of reliability prediction and evaluation (1960)

Balaban, H. S.

In: CASI

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Publikationsdatum: 2019-05-22

Schlagwort(e): unknown

Materialart: PUBL.-141-1-176

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45

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Experimental design manual and hazards analysis (1960)

In: Other Sources

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Publikationsdatum: 2019-05-22

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Materialart: NASA-CR-53824

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46

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Arc Jet Engine Performance - Experiment and Theory (1960)

Mironer, A. ; John, R. R. ; Macomber, H. ; [weitere]

In: Other Sources

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Publikationsdatum: 2019-05-22

Beschreibung: No abstract available

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47

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609a - configuration i - /2-3-5-6 unguided/ stability and control analysis of stages 1 and 2 (1960)

Hale, R. ; Barnett, M.

In: CASI

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Publikationsdatum: 2019-05-22

Schlagwort(e): unknown

Materialart: AST''EOR-12745

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48

Unbekannt

Murphy, J. S.

In: Other Sources

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Publikationsdatum: 2019-05-22

Beschreibung: No abstract available

Schlagwort(e): unknown

Materialart: ES-40109

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49

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Jpl/ai seminar proceedings 〈on〈 tracking programs and orbit determination, february 23-26, 1960 (1960)

In: Other Sources

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Publikationsdatum: 2019-05-22

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50

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Experiments on the propagation of weak disturbances in stationary supersonic nozzle flow of chemically reacting gas mixtures (1960)

Cole, J. D. ; Wegener, P. P.

In: Other Sources

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Publikationsdatum: 2019-05-22

Schlagwort(e): unknown

Materialart: JPL-20-134 , AD-252843

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51

Unbekannt

AN INTRODUCTION TO THE OPERATION AND TESTING OF ACCELEROMETERS (1960)

Meisenholder, G. W.

In: CASI

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Publikationsdatum: 2019-05-10

Schlagwort(e): unknown

Materialart: JPL-TM-33-2

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52

Unbekannt

Experimental Determination of the Effects of Frequency and Amplitude of Oscillation on the Roll-Stability Derivatives for a 60 Degree Delta-Wing Airplane Model (1960)

Fisher, Lewis R.

In: CASI

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Publikationsdatum: 2019-06-28

Beschreibung: A 60' delta-wing airplane model was oscillated in roll for several frequencies and amplitudes of oscillation to determine the effects of the oscillatory motion on the roll-stability derivatives for the model. The derivatives were measured at a Reynolds number of 1,600,000 for the wing alone, the wing-fuselage combination, and the complete model which included a triangular-plan-form vertical tail. Both rolling and yawing moments due to rolling velocity exhibited large frequency effects for angles of attack higher than 16 degrees. Variations in these derivatives were measured for the lowest frequencies of oscillation; as the frequency increased, the derivatives because more nearly linear with angle of attack. Both velocity derivatives were considerably different at high angles of attack from the corresponding derivatives measured by the steady-state rolling-flow technique. Rolling and yawing moments due to rolling acceleration were measured and similarly found to be highly dependent on frequency at high angles of attack. Some period and time-to-damp computations, which were made to reveal the significance of the acceleration derivatives, indicated that inclusion of the measured derivatives in the equations of motion lengthened the period of the lateral oscillation by 10 percent for a typical delta-wing airplane and increased the time to damp to one-half amplitude by 50 percent.

Schlagwort(e): Aircraft Design, Testing and Performance

Materialart: NASA-TN-D-232

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Überblick

53

Unbekannt

An infrared Mars probe for gathering evidence on extraterrestrial life (1960)

Gumpel, M. ; Davies, R. W.

In: CASI

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Publikationsdatum: 2019-06-27

Schlagwort(e): unknown

Materialart: NASA-CR-97395 , JPL-EP-814

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54

Unbekannt

External Drag of Multijet Exit Configuration with and Without Base Flow at Mach Numbers from 2.0 to 3.0 (1960)

Stitt, L. E. ; Cubbison, R. W.

In: CASI

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Publikationsdatum: 2019-06-27

Schlagwort(e): unknown

Materialart: NASA-TM-X-103

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55

Unbekannt

Lunar vehicle orbit determination (1960)

Tross, C.

In: CASI

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Publikationsdatum: 2019-06-27

Schlagwort(e): unknown

Materialart: JPL SEMINAR PROC. ON TRACKING PROGRAMS AND ORBIT DETERMINATION 26 FEB. 1960; P 147-160

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56

Unbekannt

Response of a single degree of freedom system to various transients (1960)

Streiff, M. L.

In: Other Sources

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Publikationsdatum: 2019-06-27

Schlagwort(e): unknown

Materialart: GDA-AE-60-0125 , AD-672259

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57

Unbekannt

Thermal mechanism related to the photolysis of nitrogen dioxide (1960)

Ford, H.

In: CASI

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Publikationsdatum: 2019-06-27

Schlagwort(e): unknown

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58

Unbekannt

Aerodynamic Characteristics at Low Speed of a Canard Bomber Configuration Designed for Supersonic Cruise Flight (1960)

Fournier, P. G. ; Croom, D. R.

In: CASI

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Publikationsdatum: 2019-06-27

Schlagwort(e): unknown

Materialart: NASA-TM-X-264

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59

Unbekannt

A Wind-tunnel Investigation of the Aerodynamic Characteristics of Three Airplane Configurations Having Diamond-plan-form Wings at a Mach Number of 2.91 (1960)

Van Hise, V. ; Mueller, J. N. ; Grimaud, J. E.

In: CASI

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Publikationsdatum: 2019-06-27

Schlagwort(e): unknown

Materialart: NASA-TM-X-224

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60

Unbekannt

Static Longitudinal Stability Characteristics at a Mach Number of 1.98 of a Nonlifting- Space-capsule Model with Finned-adapter Escape System (1960)

Harris, R. V., Jr. ; Robinson, R. B.

In: CASI

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Publikationsdatum: 2019-06-27

Schlagwort(e): unknown

Materialart: NASA-TM-X-261

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61

Unbekannt

Differential orbit correct experimentation with satellites 1958 Alpha One and 1958 Epsilon (1960)

Gersten, R. H. ; Van Sant, C. T. ; Matlin, G. L. ; [weitere]

In: CASI

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Publikationsdatum: 2019-06-27

Schlagwort(e): unknown

Materialart: JPL SEMINAR PROC. ON TRACKING PROGRAMS AND ORBIT DETERMINATION 26 FEB. 1960; P 139-146

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62

Unbekannt

Measured Base Pressures on Several Twin Rocket-Nozzle Configurations at Mach Numbers of 0.6 to 1.4 with Effects Due to Nozzle Canting and Stabilizing Fins (1960)

Cubbage, James M. ; Andrews, Earl H., Jr.

In: CASI

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Publikationsdatum: 2019-08-16

Beschreibung: An experimental investigation has been conducted at Mach numbers of 0.6 to 1.4 to determine the base pressures on several cylindrical afterbody configurations having two propulsive nozzles and to determine the effect on base pressure of stabilizing fins and the canting outward of the propulsive nozzles. Nozzle design Mach numbers of 2.0 and 3.43 were employed in this investigation and cold air at total pressures up to 120 times the free-stream static pressure was used to simulate nozzle flow. The results show that canting the nozzles outward 11 degrees was effective in increasing base pressures at supersonic speeds and that stabilizing fins caused a decrease in base pressure. The magnitudes of base pressure coefficients obtained in this investigation were consistent with those obtained on similar configurations in previous jet-effect investigations.

Schlagwort(e): Aircraft Design, Testing and Performance

Materialart: NASA/TN-D-544 , L-861

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63

Unbekannt

Hovering Measurements for Twin-Rotor Configurations with and Without Overlap (1960)

Sweet, George E.

In: CASI

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Publikationsdatum: 2019-07-10

Beschreibung: Results of an investigation in the Langley full-scale tunnel of the hovering performance of large-scale twin-rotor-helicopter models are presented. Measurements of thrust, torque, and rotor flapping are given for overlapped (approximately 76 percent of blade radius) and nonoverlapped configurations and for two different rotor solidities. The measured performance is compared with single-rotor measurements and with available rotor theory. These tests show that the hovering performance of a single rotor and of two rotors without overlap or vertical offset are the same and hence may be calculated by single-rotor theory. These tests in conjunction with results of previous coaxial-rotor tests show that the performance of highly overlapped rotors can be reasonably predicted by available rotor theory.

Schlagwort(e): Aircraft Design, Testing and Performance

Materialart: NASA-TN-D-534 , L-95399

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Überblick

64

Unbekannt

Measurement of the Maximum Altitude Attained by the X-15 Airplane Powered with Interim Rocket Engines (1960)

Larson, Terry J. ; Stillwell, Wendell H.

In: CASI

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Publikationsdatum: 2019-08-17

Beschreibung: On August 12, 1960, an X-15 flight was made to achieve essentially the maximum altitude expected to be possible with the interim rocket engines. N l y corrected altitude measurements showed that the maxhum geometric altitude was 136,500 feet k600 and the maximum pressure altitude, referred to the tables of the 0. S . Extension to the ICAO Standard Atmosphere, was indicated to be 133,900 feet.

Schlagwort(e): Aircraft Design, Testing and Performance

Materialart: NASA-TN-D-623 , H-206

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65

Unbekannt

Aerodynamic Characteristics of a Model of an Inflatable-Sphere Launching Vehicle under Simulated Conditions of Mach Number and Altitude (1960)

Morris, Odell A. ; Robinson, Ross B.

In: CASI

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Publikationsdatum: 2019-08-17

Beschreibung: An investigation has been conducted in the Langley 4- by 4-foot supersonic pressure tunnel to determine the aerodynamic characteristics in pitch of a two-stage-rocket model configuration which simulated the last two stages of the launching vehicle for an inflatable sphere. Tests were made through an angle-of-attack range from -6 deg to 18 deg at dynamic pressures of 102 and 255 pounds per square foot with corresponding Mach numbers of 1.89 and 1.98 for the model both with and without a bumper arrangement designed to protect the rocket casing from the outer shell of the vehicle.

Schlagwort(e): Aircraft Design, Testing and Performance

Materialart: NASA-TN-D-640 , L-911

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66

Unbekannt

Thrust Characteristics of Multiple Lifting Jets in Ground Proximity (1960)

Spreeman, Kenneth P. ; Davenport, Edwin E.

In: CASI

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Publikationsdatum: 2019-08-17

Beschreibung: An investigation has been made to determine the thrust characteristics within ground proximity of a series of models which might represent vertical take-off-and-landing (VTOL) aircraft with multiple exit jet engines exhausting vertically downward beneath a lifting surface. Variations in simulated engine configurations were provided by a series of nozzle insert plugs in which the number of jet exits, located symmetrically on a fixed circle, was varied, or the diameter of the circle was varied for a given number of jet exits. represent lifting surfaces, and high-pressure air was used to simulate jet-engine exhaust. Plywood plates were used to The results of the investigation showed that increasing the number of exits, such that an annular jet configuration was approached, provided more favorable thrust characteristics within ground proximity than any other variation in the geometry of these multiple jets. Tests of a configuration with two nozzles approximating a fan-in-wing VTOL aircraft with fans located at different spanwise locations indicated that the augmentation in thrust within ground proximity was greater for the arrangement with the more inboard location of the nozzles.

Schlagwort(e): Aircraft Design, Testing and Performance

Materialart: NASA-TN-D-513 , L-868

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Überblick

67

Unbekannt

An Investigation of Landing-Contact Conditions for a Large Turbojet Transport During Routine Daylight Operations (1960)

Silsby, Norman S. ; Stickle, Joseph W.

In: CASI

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Publikationsdatum: 2019-08-17

Beschreibung: An investigation has been made by the NASA to obtain statistical measurements of landing-contact conditions for a large turbojet transport in commercial airline operations. The investigation was conducted at the Los Angeles International Airport in Los Angeles, California. Measurements were taken photographically during routine daylight operations. The quantities determined were vertical velocity, horizontal velocity, rolling velocity, bank angle, and distance from runway threshold, just prior to ground contact. The results indicated that the mean vertical velocity for the turbojet-transport landings was 1.62 feet per second and that 1 landing out of 100 would be expected to equal or exceed about 4.0 feet per second. The mean airspeed at contact was 132.0 knots, with 1 landing in 100 likely to equal or exceed about 153.0 knots. The mean rolling velocity was about 1.6 deg per second. One lending in 100 would probably equal or exceed a rolling velocity of about 4.0 deg. per second in the direction of the first wheel to touch. The mean bank angle for the turbojet transports was 1.04 deg, and right and left angles of bank were about evenly divided. One lending in 100 would be likely to equal or exceed a bank angle of about 3.5 deg. The mean value of distance to touchdown from the runway threshold was 1,560 feet. One lending in 100 would be expected to touchdown at or beyond about 2,700 feet from the runway threshold. The mean values for vertical velocity, airspeed, and distance t o touch-down for the turbojet transports were somewhat higher than those found previously for piston-engine transports. No significant differences were found for values of rolling velocity and bank angle.

Schlagwort(e): Aircraft Design, Testing and Performance

Materialart: NASA-TN-D-527 , L-1009

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68

Unbekannt

An Analysis of the Flapwise Bending Frequencies and Mode Shapes of Rotor Blades Having Two Flapping Hinges to Reduce Vibration Levels (1960)

Leonard, H. Wayne ; Brooks, George W.

In: CASI

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Publikationsdatum: 2019-08-17

Beschreibung: This paper presents the analysis of the flapwise natural bending frequencies and mode shapes of rotor blades with two flapping hinges located at arbitrary blade radii. The equations of motion are derived for a blade of variable mass and stiffness distribution. Solutions to the equations (natural frequencies and mode shapes) are presented for a typical blade of constant cross section having a wide range of hinge locations. The results show that the natural frequencies of the blades can be changed appreciably by varying the locations of the blade hinges, and that with two properly located flapping hinges, blade designs are possible which eliminate or greatly reduce conditions of resonance between the blade natural frequencies and the frequencies of the harmonic air loads. The results also show that ratios of natural frequency to rotor speed below a value of 6.0 are essentially constant for variations in rotor speed consistent with helicopter and VTOL applications.

Schlagwort(e): Aircraft Design, Testing and Performance

Materialart: NASA-TN-D-633

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Überblick

69

Unbekannt

Aerodynamic and Landing Measurements Obtained During the First Powered Flight of the North American X-15 Research Airplane (1960)

In: CASI

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Publikationsdatum: 2019-08-17

Beschreibung: During the first powered flight of the North American X-15 research airplane on September 17, 1959, a Mach number of 2.1 and an altitude of 52,000 feet were attained. Static and dynamic maneuvers were performed to evaluate the characteristics of the airplane at subsonic and supersonic speeds. Data from these maneuvers as well as from the launch and landing phases are presented, discussed, and compared with predicted values. The rate of separation of the X-15 from the B-52 carrier airplane at launch was less than that predicted by wind-tunnel studies and was less rapid than in the lightweight condition of the initial glide flight. In addition, the angular motions and bank angle attained following the launch were of lesser magnitude than in the glide flight. Stable longitudinal-stability trends were apparent during the acceleration to maximum speed, and the pilot reported experiencing little or no transonic trim excursions. An inexplicable high-frequency vibration, which occurred at Mach numbers above 1.4, is being investigated further. Essentially linear lift and stability characteristics were indicated within the limited ranges of angle of attack and angle of sideslip investigated. The dynamic longitudinal and lateral-directional stability and control-effectiveness characteristics appeared satisfactory to the pilot. Although the longitudinal- and lateral-directional-damping ratios showed no significant change from subsonic to supersonic speeds, on the basis of time to damp, the damping characteristics at supersonic speeds appeared to the pilot to be somewhat improved over those at subsonic speeds.

Schlagwort(e): Aircraft Design, Testing and Performance

Materialart: NASA-TM-X-269

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Überblick

70

Unbekannt

Data from a Static-Thrust Investigation of Large-Scale General Research VTOL-STOL Model in Ground Effect (1960)

Huston, Robert J. ; Winston, Matthew M.

In: CASI

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Publikationsdatum: 2019-08-17

Beschreibung: The model was tested at two different elevations with the wing pivot at 1.008 and 2.425 propeller diameters above the ground. The slipstream of the propellers was deflected by tilting the wing and propellers, by deflections of large-chord trailing-edge flaps, and by combinations of flap deflection and wing tilt. Tests were conducted over a range of propeller disk loadings from 7.41 to 29.70 pounds per square foot. Force data for the complete model and pressure distributions for the wing and flaps behind one propeller were recorded and are presented in tabular form without analysis.

Schlagwort(e): Aircraft Design, Testing and Performance

Materialart: NASA-TN-D-397 , L-987

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Überblick

71

Unbekannt

Effect of Blade Cutout on Power Required by Helicopters Operating at High Tip-Speed Ratios (1960)

Gustafson, F. B. ; Gessow, Alfred

In: CASI

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Publikationsdatum: 2019-08-17

Beschreibung: A numerical study was made of the effects of blade cutout on the power required by a sample helicopter rotor traveling at tip-speed ratios of 0.3, 0.4, and 0.5. The amount of cutout varied from 0 to 0.5 of the rotor radius and the calculations were carried out for a thrust coefficient-solidity ratio of 0.04. In these calculations the blade within the cutout radius was assumed to have zero chord. The effect of such cutout on profile-drag power ranged from almost no effect at a tip-speed ratio of 0.3 to as much as a 60 percent reduction at a tip-speed ratio of 0.5. Optimum cutout was about 0.3 of the rotor radius. Part of the large power reduction at a tip-speed ratio of 0.5 resulted from a reduction in tip-region stall, brought about by cutout. For tip-speed ratios greater than 0.3, cutout also effected a significant increase in the ability of the rotor to overcome helicopter parasite drag. It is thus seen that the adverse trends (at high tip-speed ratios) indicated by the uniform-chord theoretical charts are caused in large measure by the center portion of the rotor. The extent to which a modified-design rotor can actually be made more efficient at high speeds than a uniform-chord rotor will depend in practice on the degree of success in minimizing the blade plan form near the center and on special modifications in center-section profiles. A few suggestions and estimates in regard to such modifications are included herein.

Schlagwort(e): Aircraft Design, Testing and Performance

Materialart: NASA-TN-D-382 , L-696

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Überblick

72

Unbekannt

Aerodynamic Performance and Static Stability at Mach Number 3.3 of an Aircraft Configuration Employing Three Triangular Wing Panels and a Body Equal Length (1960)

James, Carlton S.

In: CASI

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Publikationsdatum: 2019-08-17

Beschreibung: An aircraft configuration, previously conceived as a means to achieve favorable aerodynamic stability characteristics., high lift-drag ratio, and low heating rates at high supersonic speeds., was modified in an attempt to increase further the lift-drag ratio without adversely affecting the other desirable characteristics. The original configuration consisted of three identical triangular wing panels symmetrically disposed about an ogive-cylinder body equal in length to the root chord of the panels. This configuration was modified by altering the angular disposition of the wing panels, by reducing the area of the panel forming the vertical fin, and by reshaping the body to produce interference lift. Six-component force and moment tests of the modified configuration at combined angles of attack and sideslip were made at a Mach number of 3.3 and a Reynolds number of 5.46 million. A maximum lift-drag ratio of 6.65 (excluding base drag) was measured at a lift coefficient of 0.100 and an angle of attack of 3.60. The lift-drag ratio remained greater than 3 up to lift coefficient of 0.35. Performance estimates, which predicted a maximum lift-drag ratio for the modified configuration 27 percent greater than that of the original configuration, agreed well with experiment. The modified configuration exhibited favorable static stability characteristics within the test range. Longitudinal and directional centers of pressure were slightly aft of the respective centroids of projected plan-form and side area.

Schlagwort(e): Aircraft Design, Testing and Performance

Materialart: NASA-TN-D-330

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Überblick

73

Unbekannt

Characteristics at Mach Number of 2.03 of a Series of Wings Having Various Spanwise Distributions of Thickness Ratio and Chord (1960)

Robins, A. Warner ; Harris, Roy V., Jr. ; Jackson, Charlie M., Jr.

In: CASI

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Publikationsdatum: 2019-08-16

Beschreibung: A series of semispan wing models having various spanwise distributions of both thickness ratio and chord but having the same effective thickness ratio was tested in the Langley 4-by 4-foot supersonic pressure tunnel at Mach number 2.03 and Reynolds numbers from 1.9 x 10(exp 6) to 6.5 x 10(exp 6) complex wing forms with thickened roots, extended root chords, and higher volumes show appreciably lower zero-lift wave drag coefficients than the plain swept wings. A calculative technique for the determination of wave drag has been applied to one of the complex wings of the series and good agreement is shown with experimental results. The complex wing forms showed higher drags due to lift than the plain swept wings.

Schlagwort(e): Aircraft Design, Testing and Performance

Materialart: NASA-TN-D-631

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74

Unbekannt

Flight Investigation of the Lift and Drag Characteristics of a Swept-Wing, Multijet, Transport-Type Airplane (1960)

Tambor, Ronald

In: CASI

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Publikationsdatum: 2019-08-16

Beschreibung: The lift and drag characteristics of a Boeing KC-135 airplane were determined during maneuvering flight over the Mach number range from 0.70 to 0.85 for the airplane in the clean configuration at an altitude of 26,000 feet. Data were also obtained over the speed range of 130 knots to 160 knots at 9,000 feet for various flap deflections with gear down.

Schlagwort(e): Aircraft Design, Testing and Performance

Materialart: NASA-TN-D-30 , H-119

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Überblick

75

Unbekannt

Solar Cosmic Rays and Soft Radiation Observed at 5,000,000 Km from Earth (1960)

Hoffman, R. A. ; Winckler, J. R. ; Arnoldy, R. L.

In: CASI

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Publikationsdatum: 2019-08-14

Beschreibung: No abstract available

Schlagwort(e): unknown

Materialart: CR-29

Format: text

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76

Unbekannt

Some Characteristics of the Signal Received from 1958 Delta 2 (1960)

De Mendonca, F. ; Garriot, O. K. ; Villard, O. G., Jr.

In: CASI

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Publikationsdatum: 2019-08-14

Beschreibung: The study of the rapid fluctuation in the received signal strength from artificial earth satellites has led to a better understanding of the irregularities in electron density which exist in the ionosphere. In particular, the dimensions and locations of these inhomogeneities have been investigated. This note may serve as additional confirmation of some of the work mentioned above and, in addition, will report several new features of the received satellite radio signals.

Schlagwort(e): unknown

Materialart: Proceedings of the IRE; 48; 12

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77

Unbekannt

Subsonic Flight Tests of a 1/7-Scale Radio-Controlled Model of the North American X-15 Airplane with Particular Reference to High Angel-of-Attack Conditions (1960)

Hassell, James L., Jr. ; Hewes, Donald E.

In: CASI

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Publikationsdatum: 2019-08-15

Beschreibung: An investigation of the subsonic stability and control characteristics of an unpowered 1/7-scale model based on the North American X-15 airplane was conducted by using a radio-controlled model launched from a helicopter and flown in free-gliding flight. At angles of attack below about 20 deg. where the model motions represent those of the X-15 airplane, the model was found to be both longitudinally and laterally stable, and the all-movable tail surfaces were found to be very effective. The model could also be flown at much higher angles of attack where the model motions did not necessarily represent those of the airplane because of slight geometrical differences and Reynolds number effects, but these test results are useful in evaluating the effectiveness at these angles of the type of lateral control system used in the X-15 airplane. In some cases, the model was flown to angles of attack as high as 60 or 70 deg. without encountering divergent or uncontrollable conditions. For some flights in which the model was subjected to rapid maneuvers, spinning motions were generated by application of corrective controls to oppose the direction of rotation. Rapid recoveries from this type of motion were achieved by applying roll control in the direction of rotation.

Schlagwort(e): Aircraft Design, Testing and Performance

Materialart: NASA-TM-X-283

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78

Unbekannt

Landing-Impact Characteristics of Load-Alleviating Struts on a Model of a Winged Space Vehicle (1960)

Blanchard, Ulysse J.

In: CASI

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Publikationsdatum: 2019-08-15

Beschreibung: A brief experimental investigation was made of the landing-impact characteristics of a 1/9-scale dynamic model of a winged space vehicle. The landing tests were made by catapulting a free model onto a hard; surface runway and onto water. The model had a conical fuselage and a flat - plate wing with a basic delta planform and 75 deg sweepback of the leading edge. The use of yielding-metal shock absorbers and various landing-gear arrangements was investigated during landing impact. The basic landing gear consisted of a dual rubber-tired nose wheel and twin main skids aft of the center of gravity near the wing tips. landing motion and acceleration data were obtained over a range of landing attitudes, gross weights, and initial sinking speeds. Brief tests were made with an alternate nose-wheel location. An all-skid configuration also was briefly evaluated for hard-surface and water landings. The landing gear employing yielding struts for impact-energy absorption during hard-surface landings resulted in accelerations of approximately 5 1/2 g near the nose gear over a range of landing parameters. Replacing the nose wheel and tire with a skid did not significantly change the accelerations. Landings in smooth water with rigid struts and adequate planing area at the nose skid resulted in a maximum landing acceleration of approximately 4g.

Schlagwort(e): Aircraft Design, Testing and Performance

Materialart: NASA-TN-D-541 , L-958

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79

Unbekannt

Flight Evaluation of Several Spring Force Gradients and a Bobweight in the Cyclic-Power-Control System of a Light Helicopter (1960)

Mallick, Donald L. ; Reeder, John P.

In: CASI

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Publikationsdatum: 2019-08-15

Beschreibung: Several feel springs of different rates were evaluated in the power-control system of a light helicopter. In addition, a bobweight and viscous damper for providing maneuvering forces were evaluated. The evaluation was qualitative, based upon the combined opinions of eight research pilots and four non-pilot engineers from NASA. The evaluation revealed that desirable all-around forces for the helicopter were obtained with a 1/2-lb/in. feel spring for both longitudinal and lateral control combined with a 14-lb/g bobweight. Further investigation proved the necessity of the viscous damper in the bobweight system.

Schlagwort(e): Aircraft Design, Testing and Performance

Materialart: NASA/TN-D-537 , L-643

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80

Unbekannt

Effect of Base Bleed and Terminal Fairings on the Performance of Exhaust-Nozzle-Afterbody Combinations at Mach Numbers of 1.93, 2.55, and 3.05 (1960)

Keith, Arvid L., Jr. ; Norton, Harry T., Jr.

In: CASI

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Publikationsdatum: 2019-08-15

Beschreibung: An investigation of four exhaust-nozzle-afterbody combinations has been conducted in the Langley 9- by 12-inch blowdown tunnel at Mach numbers of 1.93, 2.55, and 3.05. The models were tested on a pylon-mounted nacelle and the jet exhaust was simulated with cold air. Base bleed w a s varied from 0 to about 12 percent of the primary jet weight flow and was discharged in to the base region through either a sonic or supersonic bleed nozzle. The models were tested at zero degree angle of attack and the Reynolds number range was from 8 x 10(exp 6) to 9 x 10(exp 6) per foot. The results indicate that the base pressure and the performance of the exhaust-nozzle-afterbody combinations were little affected gy the high-velocity base bleed. The efficiency of the terminal-fairing model was only slightly less than that of the convergent-divergent nozzle-afterbody combinations; this difference indicates the loss associated with improved transonic efficiency at higher Mach numbers.

Schlagwort(e): Aircraft Design, Testing and Performance

Materialart: NASA/TN-D-539 , L-977

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81

Unbekannt

Measurement of the Maximum Speed Attained by the X-15 Airplane Powered with Interim Rocket Engines (1960)

Stillwell, Wendell H. ; Larson, Terry J.

In: CASI

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Publikationsdatum: 2019-08-15

Beschreibung: On August 4, 1960, a flight was made with the X-15 airplane to the maximum speed expected with the interim rocket engines. Fully corrected airspeed measurements showed that the maximum Mach number of 3.1 +/- 0.04 and maximum true airspeed of 2,196 mph +/- 35 were attained at an altitude of 69,600 feet. At Mach numbers greater than 2.0 the pitot-static tube exhibited a negative static-pressure error which resulted in a Mach number correction of -0.18 at the maximum speed.

Schlagwort(e): Aircraft Design, Testing and Performance

Materialart: NASA-TN-D-615 , H-187

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82

Unbekannt

Experimental and Calculated Flow Fields Produced by Airplanes Flying at Supersonic Speeds (1960)

Smith, Harriet J.

In: CASI

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Publikationsdatum: 2019-08-15

Beschreibung: Results are presented of a flight investigation conducted to survey the flow field generated by airplanes flying a t supersonic speeds. The pressure signatures of an F-100, an F-104, and a B-58 airplane, representing widely varying configurations, a t distances from 120 t o 425 f e e from the generating aircraft and at Mach numbers from 1.2 t o 1.8 are shown. Calculations were made by using Whitham's method and were compared with the experimental results.

Schlagwort(e): Aircraft Design, Testing and Performance

Materialart: NASA-TN-D-621 , H-190

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83

Unbekannt

Response of Rotor Lift to an Increase in Collective Pitch in the Case of Descending Flight, the Regime of the Rotor Being Near Autorotation (1960)

Soulez-Lariviere, Jean ; Valensi, Jacques ; Rebont, Jean

In: CASI

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Publikationsdatum: 2019-08-15

Beschreibung: An elementary calculation inspired by the classic treatment for the steady state permits the determination of the induced velocity and the overall lift of the rotor as a function of the collective pitch for all values of the advance per turn. The nature of the lift response is shown to be essentially a function of the rate of pitch change.

Schlagwort(e): Aircraft Design, Testing and Performance

Materialart: NASA-TT-F-18 , L-455 , Comptes Rendus; 247; 9; 738-741

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84

Unbekannt

A Flight Study of the Conversion Maneuver of a Tilt-Duct VTOL Aircraft (1960)

Kelley, Henry L. ; Tapscott, Robert J.

In: CASI

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Publikationsdatum: 2019-08-15

Beschreibung: Flight records are presented from an early flight test of a wing-tip mounted tilting-ducted-fan, vertical-take-off and landing (VTOL) aircraft configuration. Time histories of the aircraft motions, control positions, and duct pitching-moment variation are presented to illustrate the characteristics of the aircraft in hovering, in conversion from hovering to forward flight, and in conversion from forward flight to hovering. The results indicate that during essentially continuous slow level- flight conversions, this aircraft experiences excessive longitudinal trim changes. Studies have shown that the large trim changes are caused primarily by the variation of aerodynamic moments acting on the duct units. Action of the duct-induced downwash on the horizontal stabilizer during the conversion also contributes to the longitudinal trim variations. Time histories of hovering and slow vertical descent in the final stages of landing in calm air show angular motions of the aircraft as great as +/- 10 deg. about all axes. Stick and pedal displacements required to control the aircraft during the landing maneuver were on the order of 50 to 60 percent of the total travel available.

Schlagwort(e): Aircraft Design, Testing and Performance

Materialart: NASA-TN-D-372 , L-891

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85

Unbekannt

Some Landing Studies Pertinent to Glider-Reentry Vehicles (1960)

Houbolt, John C. ; Batterson, Sidney A.

In: CASI

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Publikationsdatum: 2019-08-15

Beschreibung: Results are presented of some landing studies that may serve as guidelines in the consideration of landing problems of glider-reentry configurations. The effect of the initial conditions of sinking velocity, angle of attack, and pitch rate on impact severity and the effect of locating the rear gear in various positions are discussed. Some information is included regarding the influence of landing-gear location on effective masses. Preliminary experimental results on the slideout phase of landing include sliding and rolling friction coefficients that have been determined from tests of various skids and all-metal wheels.

Schlagwort(e): Aircraft Design, Testing and Performance

Materialart: NASA-TN-D-448 , L-1066

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Überblick

86

Unbekannt

Flight Investigation of the Low-Speed Characteristics of a 45 deg Swept-Wing Fighter-Type Airplane with Blowing Boundary-Layer Control Applied to the Leading- and Trailing-Edge Flaps (1960)

Innis, Robert C. ; Anderson, Seth B. ; Quigley, Hervey C.

In: CASI

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Publikationsdatum: 2019-08-15

Beschreibung: A flight investigation has been conducted to study how pilots use the high lift available with blowing-type boundary-layer control applied to the leading- and trailing-edge flaps of a 45 deg. swept-wing airplane. The study includes documentation of the low-speed handling qualities as well as the pilots' evaluations of the landing-approach characteristics. All the pilots who flew the airplane considered it more comfortable to fly at low speeds than any other F-100 configuration they had flown. The major improvements noted were the reduced stall speed, the improved longitudinal stability at high lift, and the reduction in low-speed buffet. The study has shown the minimum comfortable landing-approach speeds are between 120.5 and 126.5 knots compared to 134 for the airplane with a slatted leading edge and the same trailing-edge flap. The limiting factors in the pilots' choices of landing-approach speeds were the limits of ability to control flight-path angle, lack of visibility, trim change with thrust, low static directional stability, and sluggish longitudinal control. Several of these factors were found to be associated with the high angles of attack, between 13 deg. and 15 deg., required for the low approach speeds. The angle of attack for maximum lift coefficient was 28 deg.

Schlagwort(e): Aircraft Design, Testing and Performance

Materialart: NASA-TN-D-321

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87

Unbekannt

A Summary of Operating Conditions Experienced by Three Military Helicopters and a Mountain-Based Commercial Helicopter (1960)

Connor, Andrew B.

In: CASI

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Publikationsdatum: 2019-08-15

Beschreibung: The results of a survey of the flight conditions experienced by three military helicopters engaged in simulated and actual military missions, and a commercial helicopter operated in the mountainous terrain surrounding Denver, CO, are presented. The data, obtained with NASA helicopter VGHN recorders, represent 813 flights or 359 flying hours, and are compared where applicable to previous survey results. The current survey results show that none of the helicopters exceeded the maximum design airspeed. One military helicopter, used for instrument flight training, never exceeded 70 percent of its maximum design airspeed. The rates of climb and descent utilized by the IFR training helicopter and of the mountain-based helicopter were generally narrowly distributed within all the airspeed ranges. The number of landings per hour for all four of the helicopters ranged from 1.6 to 3.3. The turbine-engine helicopter experienced more frequent normal-acceleration increments above a threshold of +/-0.4g (where g is acceleration due to gravity) than the mountain-based helicopter, but the mountain-based helicopter experienced acceleration increments of greater magnitude. Limited rotor rotational speed time histories showed that all the helicopters were operated at normal rotor speeds during all flight conditions.

Schlagwort(e): Aircraft Design, Testing and Performance

Materialart: NASA-TN-D-432 , L-1157

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88

Unbekannt

Effect of Body-Mounted Lateral Controls and Speed Brakes on the Aerodynamic Load Distribution over a 45 deg Swept Wing at Mach Numbers from 0.80 to 0.98 (1960)

West, F. E., Jr.

In: CASI

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Publikationsdatum: 2019-08-15

Beschreibung: An investigation has been made in the Langley 16-foot transonic tunnel to determine the effect of body-mounted lateral controls and speed brakes on the aerodynamic load distribution over a swept wing. The lateral controls and speed brakes consisted of flat plates which rotated out of the side of the fuselage, were approximately perpendicular to the wing chord plane, and extended either above or below the chord plane. The wing had 45 deg sweep of the quarter-chord line, an aspect ratio of 3, a taper ratio of0.2, and 4-percent-thick airfoil section. Data were obtained at Mach numbers of 0.80, 0.94, and 0.98 fir angels of attack that usually ranged from about 0 deg to 21 deg. The results show that at the higher angles of attack a lower-surface body-mounted lateral control located along the wing trailing edge had higher effectiveness than a similar upper-surface control. Reduction in span from 0.3 to 0.2 of the wing semispan of an upper-surface body-mounted lateral control located along the wing trailing edge resulted in a less than proportiona1,change in control effectiveness.

Schlagwort(e): Aircraft Design, Testing and Performance

Materialart: NASA/TN-D-522 , L-789

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89

Unbekannt

Hydrodynamic and Aerodynamic Characteristics of a Model of a Supersonic Multijet Water-Based Aircraft Equipped with Supercavitating Hydrofoils (1960)

Pearson, Albin O. ; McKann, Robert E. ; Blanchard, Ulysse J.

In: CASI

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Publikationsdatum: 2019-08-15

Beschreibung: The hydrodynamic and aerodynamic characteristics of a model of a multijet water-based Mach 2.0 aircraft equipped with hydrofoils have been determined. Takeoff stability and spray characteristics were very good, and sufficient excess thrust was available for takeoff in approximately 32 seconds and 4,700 feet at a gross weight of 225,000 pounds. Longitudinal and lateral stability during smooth-water landings were good. Lateral stability was good during rough-water landings, but forward location of the hydrofoils or added pitch damping was required to prevent diving. Hydrofoils were found to increase the aerodynamic lift-curve slope and to increase the aerodynamic drag coefficient in the transonic speed range, and the maximum lift-drag ratio decreased from 7.6 to 7.2 at the cruise Mach number of 0.9. The hydrofoils provided an increment of positive pitching moment over the Mach number range of the tests (0.6 to 1.42) and reduced the effective dihedral and directional stability.

Schlagwort(e): Aircraft Design, Testing and Performance

Materialart: NASA-TM-X-191

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90

Unbekannt

Longitudinal Aerodynamic Characteristics of a Four-Propeller Deflected Slipstream VTOL Model Including the Effects of Ground Proximity (1960)

Grunwald, Kalman J. ; Kuhn, Richard E.

In: CASI

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Publikationsdatum: 2019-08-16

Beschreibung: Results are presented of a wind-tunnel investigation of the longitudinal stability, control, and performance characteristics of a model of a four-propeller deflected-slipstream VTOL airplane in the transition speed range. These results indicate that steady level-flight transition and descending flight-path angles up to 7 or 8 deg. out of the region of ground effect can be accomplished without wing stall being encountered. In general, the pitching moments out of ground proximity can be adequately trimmed by programming the stabilizer incidence to increase with increasing flap deflection, except for a relatively large diving moment in the hovering condition. The deflection of the slipstream onto the horizontal tail in proximity of the ground substantially increases the diving moment in hovering, unless the tail is set at a large nosedown incidence.

Schlagwort(e): Aircraft Design, Testing and Performance

Materialart: NASA-TN-D-248 , L-735

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91

Unbekannt

Preliminary Investigation of a Paraglider (1960)

Lowry, John G. ; Taylor, Robert T. ; Croom, Delwin R. ; [weitere]

In: CASI

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Publikationsdatum: 2019-08-16

Beschreibung: A preliminary investigation of the aerodynamic and control characteristics of a flexible glider similar to a parachute in construction has been made at the Langley Research Center to evaluate its capabilities as a reentry glider. Preliminary weight estimates of the proposed vehicle indicate that such a structure can be made with extremely low wing loading. Maximum temperatures during the reentry maneuver might be held as low as about 1,500 F. The results of wind-tunnel and free-glide tests show that the glider when constructed of nonporous material performed extremely well at subsonic speeds and could be flown at angles of attack from about 200 to 900. At supersonic speeds the wing showed none of the unfavorable tendencies exhibited by conventional parachutes at these speeds, such as squidding and breathing. Several methods of packing and deploying the glider have been successfully demonstrated. The results of this study indicate that this flexible-lifting-surface concept may provide a lightweight controllable paraglider for manned space vehicles.

Schlagwort(e): Aircraft Design, Testing and Performance

Materialart: NASA-TN-D-443 , L-827

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92

Unbekannt

The Supersonic Transport: A Technical Summary (1960)

In: CASI

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Publikationsdatum: 2019-12-11

Beschreibung: No abstract available

Schlagwort(e): Aircraft Design, Testing and Performance

Materialart: NASA-TN-D-423

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93

Digitale Medien

Darstellung einiger 8-Alkyl- und 8-Alkenyl-theophylline (1960)

Fürst, Hans ; Ebert, Inge

Weinheim : Wiley-Blackwell

Berichte der deutschen chemischen Gesellschaft 93 (1960), S. 99-102

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ISSN: 0009-2940

Schlagwort(e): Chemistry ; Inorganic Chemistry

Quelle: Wiley InterScience Backfile Collection 1832-2000

Thema: Chemie und Pharmazie

Notizen: 8-Alkyl- und 8-Alkenyl-theophylline werden aus 1.3-Dimethyl-4.5-diaminouracil und gesättigten Carbonsäuren bzw. β.γ- und γ.δ-ungesättigten Carbonsäuren durch Kondensation nach TRAUBE dargestellt; α.β-ungesättigte Säuren reagieren nicht.

Materialart: Digitale Medien

URL: http://dx.doi.org/10.1002/cber.19600930117

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Volltext

94

Digitale Medien

Notiz über 7-Mercapto-cholesterin (1960)

Hauptmann, Heinrich ; Bobbio, Paulo Ana

Weinheim : Wiley-Blackwell

Berichte der deutschen chemischen Gesellschaft 93 (1960), S. 280-282

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ISSN: 0009-2940

Schlagwort(e): Chemistry ; Inorganic Chemistry

Quelle: Wiley InterScience Backfile Collection 1832-2000

Thema: Chemie und Pharmazie

Notizen: 7-Mercapto-cholesterin wurde durch Hydrogenolyse des aus 7-Brom-cholesterylbenzoat hergestellten 7-Acetylmercapto-cholesteryl-benzoats erhalten. Seine Konfiguration am Kohlenstoff 7 wird diskutiert.

Materialart: Digitale Medien

URL: http://dx.doi.org/10.1002/cber.19600930142

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95

Digitale Medien

Notiz über 5-Methyl-pyridin-aldehyd-(3) (1960)

Mathes, Wilhelm ; Sauermilch, Walter

Weinheim : Wiley-Blackwell

Berichte der deutschen chemischen Gesellschaft 93 (1960), S. 286-288

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ISSN: 0009-2940

Schlagwort(e): Chemistry ; Inorganic Chemistry

Quelle: Wiley InterScience Backfile Collection 1832-2000

Thema: Chemie und Pharmazie

Materialart: Digitale Medien

URL: http://dx.doi.org/10.1002/cber.19600930145

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96

Digitale Medien

Masthead (1960)

Weinheim : Wiley-Blackwell

Berichte der deutschen chemischen Gesellschaft 93 (1960)

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ISSN: 0009-2940

Schlagwort(e): Chemistry ; Inorganic Chemistry

Quelle: Wiley InterScience Backfile Collection 1832-2000

Thema: Chemie und Pharmazie

Materialart: Digitale Medien

URL: http://dx.doi.org/10.1002/cber.19600930101

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97

Digitale Medien

Darstellung der 1.3.5-Triacetyl-2-desoxy-β-D-ribofuranose (1960)

Venner, Harry ; Zinner, Helmut

Weinheim : Wiley-Blackwell

Berichte der deutschen chemischen Gesellschaft 93 (1960), S. 137-140

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ISSN: 0009-2940

Schlagwort(e): Chemistry ; Inorganic Chemistry

Quelle: Wiley InterScience Backfile Collection 1832-2000

Thema: Chemie und Pharmazie

Notizen: Es wird die Synthese der 1.3.5-Triacetyl-2-desoxy-β-D-ribofuranose beschrieben. Die Struktur wird durch Messung der kernmagnetischen Resonanz unter Vergleich mit den beiden β-D-Ribose-tetraacetaten (1.3.4 bzw. 1.3.5) bewiesen.

Zusätzliches Material: 2 Ill.

Materialart: Digitale Medien

URL: http://dx.doi.org/10.1002/cber.19600930122

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98

Digitale Medien

Silylierung von Aminosäuren (1960)

Birkofer, Leonhard ; Ritter, Alfred

Weinheim : Wiley-Blackwell

Berichte der deutschen chemischen Gesellschaft 93 (1960), S. 424-427

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ISSN: 0009-2940

Schlagwort(e): Chemistry ; Inorganic Chemistry

Quelle: Wiley InterScience Backfile Collection 1832-2000

Thema: Chemie und Pharmazie

Notizen: Durch Einwirkung von Silazanen auf Aminosäuren entstehen N-Trialkylsilyl-aminosäure-trialkylsilylester und Aminosäure-trialkylsilylester.

Zusätzliches Material: 2 Tab.

Materialart: Digitale Medien

URL: http://dx.doi.org/10.1002/cber.19600930223

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99

Digitale Medien

Zur Kenntnis der Reaktionen des Kobalttetracarbonyls mit verschiedenartigen Basen, VII. Reaktionen des Kobaltcarbonyls mit Verbindungen des 3-wertigen Phosphors und seiner Homologen (1960)

Hieber, Walter ; Freyer, Walter

Weinheim : Wiley-Blackwell

Berichte der deutschen chemischen Gesellschaft 93 (1960), S. 462-467

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ISSN: 0009-2940

Schlagwort(e): Chemistry ; Inorganic Chemistry

Quelle: Wiley InterScience Backfile Collection 1832-2000

Thema: Chemie und Pharmazie

Notizen: In Fortführung der Versuche über phosphinhaltige Kobaltcarbonyle hat sich ergeben, daß der Reaktionsverlauf von der speziellen Art des Phosphins, d. h. den am Phosphor gebundenen organischen Resten, abhängt. So entstehen mit Triäthyl- und Tricyclohexyl-phosphin bevorzugt (ca. 10°) die 2-ionigen Verbindungen [Co(CO)3L2][Co(CO)4] (L = P(C2H5)3, P(C6H11)3); nur bei höherer Temperatur (ca. 35°) und in indifferenten Mitteln bildet sich das betr. echte Derivat des Kobaltcarbonyls [Co(CO)3L]2, das mit Triphenylphosphin auch schon bei tieferer Temperatur entsteht. Häufig liegen Gemische beider Verbindungstypen vor. - Mit Triphenyl-arsin und -stibin sind die gleichfalls bei tieferer Temperatur (0°) gebildeten 2-ionigen Verbindungen nur labil und wandeln sich spontan unter CO-Abgabe in die echten Derivate um. - Ergänzende weitere Versuche wurden mit Mangancarbonyl und der 2-zähligen Base Äthylen-bis-[diphenylphosphin] und mit Rheniumcarbonyl und Triphenylphosphin durchgeführt. Im letzteren Fall erhält man das diamagnetische Monosubstitutionsprodukt [Re(CO)4P(C6H5)3]2.

Materialart: Digitale Medien

URL: http://dx.doi.org/10.1002/cber.19600930228

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100

Digitale Medien

Über die Kupplungsaktivität einiger heterocyclischer Diazoverbindungen (1960)

Goerdeler, Joachim ; Haubrich, Heinz

Weinheim : Wiley-Blackwell

Berichte der deutschen chemischen Gesellschaft 93 (1960), S. 397-405

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ISSN: 0009-2940

Schlagwort(e): Chemistry ; Inorganic Chemistry

Quelle: Wiley InterScience Backfile Collection 1832-2000

Thema: Chemie und Pharmazie

Notizen: Eine Anzahl diazotierter heterocyclischer Amine wurde mit Phenoläthern und aromatischen Kohlenwasserstoffen auf ihr Kupplungsvermögen geprüft. Die Versuche zeigten, daß insbesondere Verbindungen aus der 1.2.4- und 1.3.4-Thiodiazol-Reihe eine sehr hohe Reaktivität besitzen, die diejenige des diazotierten 2.4-Dinitro-anilins deutlich übertrifft.

Materialart: Digitale Medien

URL: http://dx.doi.org/10.1002/cber.19600930220

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