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Advances in Aircraft and Spacecraft Science
  Volume 4, Number 4, July 2017 , pages 437-448

Analysis of payload compartment venting of satellite launch vehicle
R. C. Mehta

    The problem of flow through the vent is formulated as an unsteady, nonlinear, ordinary differential equation and solved using Runge-Kutta method to obtain pressure inside payload faring. An inverse problem for prediction of the discharge coefficient is presented employing measured internal pressure of the payload fairing during the ascent phase of a satellite launch vehicle. A controlled random search method is used to estimate the discharge coefficient from the measured transient pressure history during the ascent period of the launch vehicle. The algorithm predicts the discharge coefficient stepwise with function of Mach number. The estimated values of the discharge coefficients are in good agreement with differential pressure measured during the flight of typical satellite launch vehicle.
Key Words
    depressurization; discharge coefficient; heat shield; inverse problem; numerical analysis; reentry module; satellite launch vehicle; venting
R. C. Mehta: Department of Aeronautical Engineering, Noorul Islam University, Kumaracoil, 629180, India

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