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Viewing 169981 to 170010 of 183200
1961-01-01
Technical Paper
610157
C. J. RAHNKE, R. H. CARMODY
1961-01-01
Technical Paper
610155
C. F. FIGG
1961-01-01
Technical Paper
610156
G. A. BALL, A. H. BELL, L. B. MANN
1961-01-01
Technical Paper
610165
G. W. SHERMAN
1961-01-01
Technical Paper
610164
H. NAKAMURA, S. SATO, J. SAKAGAMI
1961-01-01
Technical Paper
610163
MINEO YAMAMOTO
1961-01-01
Technical Paper
610161
F. N. Beauvais, C. Garelis, D. H. lacovoni
A brief review of some of the major works in vehicle stability analysis is given. An over-all definition of the problem is presented and the scope of the present work outlined. A description of the present vehicle analog used by Ford and the refinements, such as the use of non-linear tire characteristics, are described. Computer steady state and transient response data are presented for a typical vehicle analysis. The special test instrumentation and techniques used for experimental substantiation are described, and the correlation between vehicle and computer results shown.
1961-01-01
Technical Paper
610176
F. PICARD, A. WISNER
1961-01-01
Technical Paper
610172
D. A. GOTSCH
1961-01-01
Technical Paper
610167
R. R. LOVE, A. D. BOSLEY
1961-01-01
Technical Paper
610178
THOMAS C. MUSE
1961-01-01
Technical Paper
610185
E. J. NEWILL
1961-01-01
Technical Paper
610197
JOSEPH A. MORLEY
1961-01-01
Technical Paper
610180
GALE R. BEARDSLEY
1961-01-01
Technical Paper
610186
CHARLES A. BLESSING
1961-01-01
Technical Paper
610199
J. C. WAGNER
1961-01-01
Technical Paper
610194
J. R. WELTY
1961-01-01
Technical Paper
610203
JOHN MacDOUGALL
1961-01-01
Technical Paper
610440
HERBERT D. VAN SCIVER
1961-01-01
Technical Paper
610443
R. O. LOWREY, J. T. RAY
1961-01-01
Technical Paper
610437
HERBERT MUND
1961-01-01
Technical Paper
610428
S. J. PEARSON, T. J. BISCHOFF
1961-01-01
Technical Paper
610439
HOWARD J. SIEGEL, DONALD L. KUMMER
The utilization of radiative systems for control of heat transfer on advanced flight vehicles is discussed. One of the major problems in attaining efficient radiative systems is achieving a high or low emissivity; the desired value depending on whether heat flow is to he maximized or minimized. Means of achieving high and low emissivity surfaces on present and future flight vehicles are presented. It is pointed out that the temperature of space vehicles is dependent upon the thermal radiation characteristics of the exterior surface and applicable materials are discussed. Methods of measuring the thermal radiation properties of materials are briefly mentioned.
1961-01-01
Technical Paper
610429
S. K. COBURN, J. W. STEWART, R. B. MEARS
1961-01-01
Technical Paper
610420
T. J. BISCHOFF
1961-01-01
Technical Paper
610427
F. S. KING
1961-01-01
Technical Paper
610417
R. D. Brewer

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