Effect of pitch program variations on launch availability of Atlas/Centaur-AC-7 to AC-15
Pitch programs for Atlas Centaur vehicle launch times based on wind profile data
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Pitch programs for Atlas Centaur vehicle launch times based on wind profile data
Anatomy and dc characteristics of arterial system, and pulsating flow /ac/ characteristics
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Electrical, and calorimetric measurements on alternating current loss in niobium zirconium, niobium titanium, and niobium stannide superconductors
Josephson currents interaction with LF surface plasmons in superposed thin dielectric and superconducting metal films, noting I-V characteristics
Input impedances of several hundred megohms and input capacitances of less than one picofarad are achieved with a conventional unity gain are buffer amplifier modified by addition of positive feedback. The circuit is stable over a temperature range of 25 to 70 deg C.
Resistance weld monitoring of Centaur tanks
Atlas Centaur 16 flight performance in injecting OAO-2 into nearly circular earth orbit
Characteristics of high power, low distortion, alternating current power amplifier
Satellite plasma diagnostics for electric and magnetic fields and fine structure of collisionless shocks in solar wind plasma flows and interplanetary shocks
Magnetic fluctuations observed by ground observatories, suggesting large amplitude waves as field line resonances driven by magnetopause motion
Bistable multivibrator circuits operating at high speed and low power dissipation
Closed loop servosystem for variable speed tape recorders on board spacecraft
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No abstract available
The Atlas-Centaur with the ATS-5 spacecraft was successfully launched from Eastern Test Range on August 12, 1969, and the ATS-5 was placed in the required highly elliptical transfer orbit with apogee near synchronous altitude. From this orbit the ATS-5, using its apogee motor, achieved the desired near-synchronous circular equatorial orbit. All launch vehicle systems performed satisfactorily.
Items covered in this study include: (1) refining the baseline avionics system design; (2) clarification of key issues for RFP; and (3) refining the baseline avionics system costs.
The equivalent source impedance of a solar array is an important parameter in the design and analysis of solar array power conditioning equipment. Laboratory impedance tests have been performed on individual silicon solar cells and the test results have been correlated with P-N junction theory as developed by Shockley. The impedance has been broken into resistive and reactive components. The impedance has been expressed as a function of DC operating point and frequency. A practical application of the individual cell characteristics is presented in a solar array simulator design.