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... ''' - 3 Abstract This paper discusses options for achieving spacecraft velocities in the range of 0.1-0.2c. These velocities are desirable to enable missions to Sol's closest stellar neighbours. Frequently ...

File:69-03-03-Apollo9-01-Launch.wav.mp4 (Long Silences Removed) Category:Audio Category:Apollo 9 Audio

File:69-03-03-Apollo9-01b.wav.mp4 (Long Silences Removed) Category:Audio Category:Apollo 9 Audio

... videos. Other features include: Automatically scales the interface for mobile phones and tablets Displays the EXIF/camera data that includes exposure, lens used, and other information, when available from the original ...

... & I_3\end bmatrix , Q(t) = \begin bmatrix \sigma_\upsilon^2 I_ 3x3 &0_ 3x3 \\ 0_ 3x3 &\sigma_u^2I_3\end bmatrix , w(t) = \begin bmatrix \eta_\upsilon (t ... or slowly varying bias: \ \omega^g = \omega + \beta '''(III.22a)''' \overset\cdot\beta \approx 0 '''(III.22b)''' The reading of sensor \ i follows the unit vector measurement ...

... the destruction of the biosphere. Ozone raises the temperature of the upper stratosphere to nearly 0° С at 50 km. In the mesosphere above the temperature falls, reaching its minimum value (about ... environments imaginable: high and low temperatures, high and low pressures, high acidity (e.g. pH ~ 0), high salt, and high radiation. Hyperthermophilic and anaerobic chemoautotrophic bacteria have been found at the ...

... , $253.2 (315.5) million; Office of Space Science and Applications OSSA , $568.1 (528.0) million; Office of Advanced Research and Technology OART , $318.7 (301.5) million; OTDA, $275.0 (270.0) million. In more detail, on Office of Space Science and Applications OSSA , physics and astronomy ...

... >. The true initial attitude for this scenario is \textbf q (t_0) = \begin bmatrix - 0.4060 \ 0.1634 \ 0.2473 \ 0.8645\end bmatrix ^T. The initial unknown bias of the rate gyro is ... . Note that the value for the quaternion error covariance in \textbf P ^ 2STEP (t_0) was the maximum possible value without leading to numerical instability. The large initial angular ...

... .8-mi) apogee, 1368- km (850.1-mi) perigee, 114.1-min period, and 74.0° inclination. Cosmos 529 entered orbit with 1469-km (912.8-mi) apogee, 1404- km (872.4-mi) perigee, 114.5-min period, and 74.0° inclination. Cosmos 530 entered orbit with 1469-km (912.8-mi) apogee, 1335-km (829 ... A. Manke, and to obtain stability and control data at mach 1,1 and mach 0.9 for stability augmentation systems only. Flight objectives were achieved. Vehicle reached 21600-m (71000 ...

... .9-mi) apogee, 1397-km (868.1-mi) perigee, 114.6-min period, and 74.0° inclination. Cosmos 565, with a 1493-km (927.7-mi) apogee, 1448-km (899.7-mi) perigee, 115.3-min period, and 74.0° inclination. Cosmos 566, with a 1484-km (922.1-mi) apogee, 1435-km (891.7 ... .6-mi) apogee, 1322-km (821.5-mi) perigee, 113.7-min period, and 74.0° inclination. ''( GSFC SSR, 6/30/73; SBD, 6/12/73, 233; Shabad, NYT, 6/10 ...

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