The solid rocket motor upper stage for a space launch vehicle is a more efficient propulsion technology than the liquid rocket motor upper stage. Its grain design has the potential to be crucial in terms of lowering inert mass by adopting improved volume efficiency with the lowest practicable sliver size while keeping maximum strength. Specifically, the strategy for (3D) grain arrangement of the slot for the upper stage solid rocket engine has been described in this paper. The complex configuration is established by the design process, which takes place under a parametric model of geometry in (CAD) software and is typified by varied dynamics. When constructing solid propellant rocket motors, grain arrangement is a vital and critical step. Accurate estimates of grain geometric properties play a key role in performance prediction and can be a vital and critical stage in the design of solid propellant rocket motors. This research study proposes an effective performance-matching design framework for solid rocket motors that are tuned to suit a range of thrust performance criteria. The framework is constructed utilising an innovative and specialised general design technique that was designed to evaluate the general design parameters, which is given in this study. Because of the findings obtained, it can be stated that the recommended framework is a practical and efficient approach for solid rocket engine design and development.
Blended wing body is a fixed wing aircraft which are smoothly blended together with no clear dividing line and no distinct wings also be given a wide Aerofoil shaped body. The future transportation is of aircrafts will incline towards the aerodynamically efficient and capable of carrying large number of passengers over long range and environmental benefits is the main paradigm in the design of aircraft BWB has a high lift to drag ratio which increases the CL max and velocity of the airplane with high load factor and high economy compared with traditional aircraft. Evacuation pressure or the cabin pressurization is the major issues in most of the designs with the minimum aerodynamic lift coefficient and drag coefficient. On the other side of the trend is towards the increasing cruise speed. High speed flow is connected with overcoming of intensive drag rise accruing due to existence of intensive shock, closing local area of supersonic flow. Increase of flight Mach number is possible only by using flow control methods and through affecting the shock increases of aspect ratio leads to increase of lift coefficient corresponding to maximal lift to drag. High bypass ratio engines have smaller fuel consumption and lower noise level but have negative effect on flow around airframe including take-off and landing phases. The necessity of solving problem of intensive aerodynamic heating of surface element of flight vehicles and by ensuring of their stability and controllability and also by need of implementing of high-volume tanks for hydrogen fuel and super high bypass ratio engines.
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