By S. G. Aleksandrov
SOVIET SATELLITES AND house SHIPS (SELECTED ARTICLES)
S.G. Aleksandrov, R.Ye. Federov
English Pages: 269
Sovetskiye Sputniki I Kosmicheskiye Korabli,
2nd variation, Moscow 1961, Akademiy Nauk SSSR
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Additional resources for Soviet Satellites and Space Ships: Selected Articles
For an orbit with an apogee height of 800 km and a perigee height of 250 km, a 1 ° error in the angle at the end of the ejection phase decreases the perigee by 25 km, oausing a two-fold deorease in the lifetime of the satellite. o of the apogee and unchanged perigee heighit. with inoreasing height For an orbit with a perigee of 250 km and an apogee of 1500 km, the perigee deoreases by 13 km due to the same error in the ejeotion angle as above. 5-fold decrease in the lifetime of the satellite due to this ejection angle error.
Payload 6,7 1 8,5 0,00001 27P5 0,001 During descent with aerodynamic forces we must consider the two main oasest a) i Only the drag force aots on the spacecraft and its nection occurs over a ballistic trajectory; 55 motion in this son- In adition to the drag force, and aerodynamio life force acts of the b) spacecraft and it moves along a gliding trajectory. In the first case the spacecraft, or its descending part, can be represented as an axisymmetrio body moving with sers angle of attack. In the second case, it should have lifting surfaces.
Ku/sec. Bel. wt. paqload 130 1,5 2,5 12,0 5,8 6805 30 1,8 114,3 0 3,4 132 46,0 41,0 0,0001 Descent from circular orbit Character, vel. km/sec 8:1 1,5 7:4 Bel. wt. payload 6,7 1 8,5 0,00001 27P5 0,001 During descent with aerodynamic forces we must consider the two main oasest a) i Only the drag force aots on the spacecraft and its nection occurs over a ballistic trajectory; 55 motion in this son- In adition to the drag force, and aerodynamio life force acts of the b) spacecraft and it moves along a gliding trajectory.