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Glacier height is determined by the range and orbit height of the satellite. The Range (R) is measured between the satellite and the surface of glacier using a space-borne altimeter. The satellite orbit height (H) is measured from the reference ellipsoid using Global Positioning System (GPS). The difference of orbital height and the altimeter range (H-R) is termed as the glacier height 'h.' Accuracy of the glacier height depends on the precise measurement of both orbital height and altimeter range. The orbital height measured using GPS is accurate compared to all the other tracking systems available. The optimal estimate of the satellite position is obtained using the ODTK tool by setting the mathematical model of the equation of Low Earth Orbit (LEO) satellite and the GPS measurements by applying Kalman filtering.

Minimization of drag has always been a concern to achieve high efficiency and performance. Drag reduction techniques can be used to minimize vortex shedding and make. This method can be used for building launch vehicles and missiles. Vortex shedding can be observed when there for over blufſ body, which creates drag. Design modification like the attachment of splitter plates to the base of the body helps to trap the vertices and suppress vortex shedding. It also helps in recovering the pressure at the base of the body. This can be considered as the most effective passive control technique. The paper mainly focuses about the computational study on the effect of aft-body attachment on base drag using locked vortex flow management technique, which proves to be an efficient method in reducing drag.

A scientific payload is used for deep space observations. It consists of several components, which are used to observe and detect the objects and its details. Such payloads are used to collect data for tin-filer research and understanding about the universe and to know its hidden mysteries. This research is conducted using several observatory instruments like, X-ray spectroscope, hyper spectral image camera, laser ranging instruments, etc. In this project. a mechanical configuration of X-ray spectroscope is designed considering all the design parameters and constraints. Boeing recently tested a scaled variable area jet nozzle capable of a 20% area change Shape Memory Alloy actuators were used to position 12 interlocking panels at the nozzle exit. A closed loop control system was used to maintain a range of constant diameters with varying flow conditions and to vary the diameter under constant flow conditions. Acoustic data by sideline microphones and flow field measurements at several cross-sections using PIV was collected at each condition. In this paper the variable area nozzle's design is described. The effect of the nozzle's diameter on acoustic performance is presented flow field data is shown including the effects of the joints between the interlocking panels.