Geodesic
Determination of the save distance between the carrier aircraft and launch vehicle at switch-on of the first-stage engine in air launch
Matematičeskoe modelirovanie, Tome 17 (2005) no. 11, pp. 25-42 
Yu. G. Sikharulidze; V. A. Cherkashin; A. S. Karpov; R. K. Ivanov. Determination of the save distance between the carrier aircraft and launch vehicle at switch-on of the first-stage engine in air launch. Matematičeskoe modelirovanie, Tome 17 (2005) no. 11, pp. 25-42. http://geodesic.mathdoc.fr/item/MM_2005_17_11_a2/
@article{MM_2005_17_11_a2,
     author = {Yu. G. Sikharulidze and V. A. Cherkashin and A. S. Karpov and R. K. Ivanov},
     title = {Determination of the save distance between the carrier aircraft and launch vehicle at switch-on of the first-stage engine in air launch},
     journal = {Matemati\v{c}eskoe modelirovanie},
     pages = {25--42},
     year = {2005},
     volume = {17},
     number = {11},
     language = {ru},
     url = {http://geodesic.mathdoc.fr/item/MM_2005_17_11_a2/}
}
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Voir la notice de l'article provenant de la source Math-Net.Ru

The emergency conditions in the air launch of the Launch Vehicle after injection from the Carrier Aircraft is considered. It is supposed that the Launch Vehicle is exploded at switch-on of the first stage engine. All factors those affect on the Carrier Aircraft are estimated. The method of the detonation wave calculation is given for solution of the two-dimensional non-stationary gas-dynamic tasks with detonation. Numerical calculations results are given those allow to determine a compromise delay of the engine switch-on. Carrier Aircraft safety and minimal payload loss are provided simultaneously.

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