The design engineer explore the design space and to reduce the cost and time of theĬonceptual design phase that is developed by the authors.The optimization process is
CRYOSPACE DEFINITION SOFTWARE
LVCD algorithm is coded in a software to let Transfer because of its lower cost and its access to various inclinations in departure andĪrrival.The optimal Launch Vehicle Conceptual Design (LVCD) algorithm is based on This method is more preferable and flexible than Hohmann Orbitadopted CRTBP as dynamical model and obtained three-dimensional Earth to Moon Motion of a spacecraft in the Earth/Moon system. Optimal maneuvering orbit isĭesigned with respect to Circular Restricted Three Body Problem (CRTBP) to model the Maneuvering orbit, payload and launch vehicle design. The main goal of this paper is to introduce the Moon exploration mission designīased on existing technology.The Moon exploration mission design entailsoptimal Also, the mechanism of generation and disappearance of aircore is proposed with the help of numerical results. The small variation in the drain time even when the initial water level is reduced is explained by the aircore duration during draining. On the other hand, the drain time remains almost the same for all initial heights tested with initial tank rotation. It is found that in the experiments without initial tank rotation, the drain time of water increases with increasing initial height. For the different initial water heights, the experiments were performed with and without initial rotation of the tank.
The numerical study shows good agreement with the experimental data and promotes understanding of the generation and disappearance of an aircore during draining. Eight different initial heights of water in the tank between 310 and 450 mm with a 20-mm increment were tested in each experiment. In this study, water draining through cylindrical tanks was studied using experimental and numerical techniques. Understanding the aircore formation and its growth during draining has attracted appreciable interest in the literature. KeywordsCritical height-Launch vehicle-Propellant-Vortex breaker-Weber and Reynolds numbersĭraining of liquids through cylindrical tanks is a very common phenomenon and has many applications. In orbital altitude, which in turn proves the considerable improvement in launch vehicle mass/energetic capabilities. Additionally, the carried out simulations for an existing two-stage launch vehicle indicate a 13% increase Experimental results show that a 30% decrease can be achieved in critical height by using a particular type Some experiments are conducted to examine the effectiveness of the applied vortex breakers in reduction of the critical height TheĪnalytical criteria are verified by two-dimensional, axis symmetrical, transient and two-phase numerical model. In the absence of a vortex breaker show that the effects of the Weber and Reynolds numbers in the flow field can be ignoredįor values greater than 720 and 1.1 × 105, respectively and critical height can be considered as a function of Froude number under aforementioned conditions. Tanks on postponing vortex formation and decreasing the critical height of propellants while discharging.
The focus of the present study is to investigate the effectiveness of installing vortex breakers at the outlet of launch vehicle
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