Mathematical simulation of two stages onboard feed out catapult launch system operation

Аuthors

Pravidlo M. N., Tikhonov K. M., Belyaev A. N.^*

Toropov Machine-Building Design Bureau "Vimpel", 90, Volokolamskoe shosse, Moscow, 125424, Russia

*e-mail: Alex_JC@mail.ru

Abstract

There exists a number of difficulties by placing guided missiles (GM) into fuselage of the carrier related to the limited space and tight GM placement. These circumstances may cause increased demands on the GM bailout system which should provide GM bailout process without touching GM body and control surfaces both carrier compartment elements and other missiles. An important feature of GM separation chamber is GM length of flight in a limited space due to the substantial depth of the compartment, which leads to a rather large time of the not stabilized GM flight.
Examination of the mentioned above collisions eliminating methods is performed on the basis of the two-stage type ejection device (ED). The first stage of ED prints a second stage with a suspended GM from the carrier compartment to the border of the fuselage and locked it in the down position. GM bailout is performed by the second step of the ED, which can be considered as elastically suspended to ED first stage,fixed in the lowest position.
Description of the system dynamics is based on the second kind Lagrange equations utilization. Using comprehensive mathematical model of the relative GM and carrier motion has been performed simulation of both launching and initial portion of the GM flight applying to the carrier wide range flight conditions Simulations showed that the pre-installation (before the bailout) to dive rudders GM with the values formed safe relative trajectory of AGM in all modes .

Keywords:

inboard ejecting device, air-launched guided missile, two stage ejecting device, safe breakup conditions, spatial stability, aerodynamic interference, pyro actuator internal ballistics

References

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