By C. T. Morrow
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Additional info for Re-Entry. Ballistic Missile and Aerospace Technology
A r , N , N 2, N O <3 6* kD = kR Constant 1 —0e x p ( - 5 9 3 7 3 / T ) c m 3/ m o l e c s 1 2 χ 1 0 23 3 ' 2T exp (-59373/T)cm /mole sec °2 kD = Ο kD = 3 2χ 10 2 23 Te x p (-59373/T)cm 3 /mole sec kD Ν-, + Μ + 9. 8 e v — Ν + Ν + Μ kR A r , 0 , 0 2, N O 6ζ N2 Ν kD N O + Μ + 6. 5x10 19 χ Τ" 1, 5 x T k D = 7 . 6x10 k2 2 ° ' 5e x p ( - 3 1 2 0 / T ) c m 3/ m o r e = lxl01 T k2 = 1. 4ev = k2 Ο, + Ν kl N 2 + Ο + 3. 3 e v — sec 2 NO + N k2 kl N 2 + ° 2 + 1. 9 e v ~ k2 NO +NO 2 . 6 x l 0 2 x3 T - 2- 5e x p ( - 4 3 0 3 0 / T ) cm^/mole sec N o t e : T h e s e r a t e c o n s t a n t s w e r e u s e d i n the c a l c u l a t i o n s s h o w n i n F i g s .
E) Axial Location of the Center of Gravity. The axial location of the center of gravity is shown in Fig. 19 to have no effect on the angle-of-attack envelope until the region of the re-entry trajectory where the aerodynamic forces become significant. In the lower altitude regions, sis indicated in the curves for 200,000 and 85,000 feet, the rearward movement of the center of gravity resulted in a gradually higher angle of-attack envelope until the center of gravity was such that the vehicle became unstable.
Since the drop was not aspect-sensitive, it may be attributed to breakdown rather than flame attenuation. Vol tage breakdown, as well as attenuation, has also been re ported during re-entry. These results definitely show that plasma-induced voltage breakdown must be considered in the design of any transmission system to be used during re-entry. The experimental data reported here are the result of several separate experiments involving antenna and cavity breakdown measurements employing different methods of pro ducing the initial ionization in the breakdown field.