Mathematics
Scientific paper
Jan 2002
adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=2002iaf..confe.503g&link_type=abstract
IAF abstracts, 34th COSPAR Scientific Assembly, The Second World Space Congress, held 10-19 October, 2002 in Houston, TX, USA.,
Mathematics
Scientific paper
perspective directions of cargo inject into space expenses decreasing. The detailed analysis of air start regimes at conditions of complex flight loads to launch vehicle is necessary for the choice of rational LV in relation to the PC position, for the optimization of mechanical connections elements between LV and PC, for the safe LV separation supply, for the start timing and LV engine start-up scheme choice. Thus, the features of interaction between LV and P both at a stage of their co- precipitation flight and during their separation and initial cleavage should be taken into account. The mathematical model for the evaluation of the launch vehicle dynamic response at its air start is offered in this article. The model assumes the use of the LV calculated scheme as inhomogeneous on inertial and stiffness characteristics beam construction with concentrated masses in distributed parameters and elastic suspended masses imitating fluid mobility in fuel tanks. The strengthening of the launch vehicle to the plane-carrier is submitted by elastic-dissipate elements. The non-linear character of LV with PC interaction at their separation, change of system structure because of LV holding mechanical connections disfixation, complex action of non-stationary external loads to the launch vehicle are taken into account. The model is applicable for various positions of LV relative to PC (under a wing or a fuselage, inside a fuselage or above it). It allows investigating transient regimes of motion and LV dynamic response at air start. The results of mathematical modeling of dynamic response for the launch vehicle located above a PC fuselage and starting from it with use of aerodynamic and inertial forces are adduced. It is shown that the character, the maximum values of accelerations and forces in LV cross-sections (including places of the mechanical connections with the PC), and dynamics of these parameter changes are essentially depend on the initial launch vehicle start conditions, magnitudes of aerodynamic and inertial forces, break moment of LV with PC connections, position of the launch vehicle relative to the plane-carrier. The obtained results allow to carry out the rational choice of layout schemes of aerospace systems with LV air start, LV to PC strengthening elements, to optimize quantity and parameters of LV and PC mechanical connections.
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