Zobrazeno 1 - 7
of 7
pro vyhledávání: '"Bob L. Uselton"'
Autor:
Bob L. Uselton, James C. Uselton
Publikováno v:
Journal of Spacecraft and Rockets. 13:266-270
An investigation was conducted to evaluate the validity of the small-amplitude oscillation test technique for obtaining pitch-damping data. The effects of model oscillation frequency, oscillation amplitude, and sting length on pitch-damping character
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_________::e97d55ea8db867888b40bef1be6d24f4
https://doi.org/10.2514/3.57086
https://doi.org/10.2514/3.57086
Publikováno v:
Journal of Spacecraft and Rockets. 13:424-429
Wind tunnel tests were conducted to measure the pitch, yaw, and roll-damping characteristics of an early shuttle orbiter configuration. Data were obtained utilizing the small amplitude forced-oscillation technique at angles of attack of -4.9 to 26.5
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_________::c86cd4a0169ef55230d56e82470bc445
https://doi.org/10.2514/3.57103
https://doi.org/10.2514/3.57103
Publikováno v:
Journal of Spacecraft and Rockets. 13:635-640
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_________::fb975dbd98e08adcd4f5c6a6c3bc25e5
https://doi.org/10.2514/3.57125
https://doi.org/10.2514/3.57125
Publikováno v:
Journal of Spacecraft and Rockets. 10:443-449
Sting support interference effects on the pitch damping derivatives and a comparison of damping characteristics using forced and free oscillation test methods were investigated on 140° spherically blunted cone configurations at M = 1.76-3.0. Sting i
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_________::cc4cef8c3eb1d5a14093d539bc0b6b1e
https://doi.org/10.2514/3.61906
https://doi.org/10.2514/3.61906
Autor:
Bob L. Uselton, James C. Uselton
Pitch-damping tests were conducted at M = 1.96 to evaluate the newly developed high-alpha missile test mechanism. Data were obtained using the small-amplitude free-oscillation technique at angles of attack from -12 to 86 deg at Reynolds numbers, base
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_________::355e48204fba3c81a18da0abbd49ad4e
https://doi.org/10.21236/ada009865
https://doi.org/10.21236/ada009865
Autor:
Bob L Uselton
Wind tunnel tests were conducted for the Air Force Armament Laboratory to obtain experimental data at Mach number 3 on an impulse correction guidance system. The guidance system is based on the principle of impulse correction. The purpose of the test
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_________::c2c1abcb9f38ec58adb5659878cebba3
https://doi.org/10.21236/ada024210
https://doi.org/10.21236/ada024210
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