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For a launch vehicle, the base line aerodynamic coefficients are generated using wind tunnel tests at various Mach numbers, angles of attack and wind plane angles. Thereafter the contribution of differences in wind tunnel model and flight configuration, Reynolds number differences and Jet-on effect are quantified separately and included as incremental coefficients over the baseline data either...
Cocuring process is a unique characteristic of composite materials wherein multiple parts like stringers, ribs and spars are simultaneously cured and bonded to a composite skin resulting in an integral structure. It has many benefits like reduction in part count, elimination of stress concentration due to fastener holes in the cocured regions and reduced assembly time and related costs. However, the...
Turbulent flow in a mixed compression intake is investigated. The unsteady compressible Navier–Stokes equations are solved using a stabilized finite element method with 6-noded triangular element. The Spalart–Allmaras model is used for turbulence closure. For comparison, the laminar flow is studied as well. A bleed of 6 % is utilized to overcome the start-up problem of the intake. The effect of back...
Cryogenic propulsion systems using liquid hydrogen and liquid oxygen propellant combination are used in satellite launch vehicles in view of the higher specific impulse (I SP ). Due to extreme low temperature of cryogenic propellant and low density and explosive nature of LH 2 , the development of cryogenic propulsion system is very complex and time consuming. In ISRO...
Reusable launch vehicle (RLV) is a goal pursued by different aerospace agencies, world-wide. Indian space research organization is also one among them. This paper covers the challenges faced and the solutions developed for control law design of a typical re-entry vehicle. The first stage of the test vehicle, used for technology demonstration mission, is a conventional solid rocket motor. The second...
Unmanned aircraft systems (UAS) have been widely recognised as efficient platforms to perform surveillance and reconnaissance missions. The promising roles played by UAS in peace time missions coupled with their lower operating cost motivate the military world to evolve doctrines and concept of operations with UAS as the main elements in the future integrated network centric digital battlefield environment...
A bstract ISRO Satellite Centre (ISAC) is a premier research and development Centre for satellite systems under the Indian Space Research Organization. Over the last four decades, ISAC has achieved remarkable success in the realization of state-of-the-art spacecraft missions covering wide spectrum of applications and services in the areas of television broadcasting, radio networking, VSAT...
A summary of the results obtained using the flow solver HiFUN for the 3D High lift NASA Trapezoidal wing are presented. Hybrid unstructured grids have been used for the computations. Grid converged solution obtained for the clean wing and the wing with support brackets, are compared with experimental data. The ability of the solver to predict critical design parameters associated with the high...
In this study we carry out multi-disciplinary multi-objective optimization of a solid fin for sounding rocket by considering its (i) aerodynamic performance in terms of static aerodynamic stability and drag, (ii) structural performance in terms of torsional deflection and factor of safety (FOS), and (iii) flight performance in terms of peak altitude (PA) and maximum payload capability for given propulsion...
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