Determination of the save distance between the carrier aircraft and launch vehicle at switch-on of the first-stage engine in air launch

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.