JAWAHARLAL NEHRU TECHNOLOGICAL UNIVERSITY HYDERABAD
JAWAHARLAL NEHRU TECHNOLOGICAL UNIVERSITY HYDERABAD B.Tech II Year II Semester INTRODUCTION TO SPACE TECHNOLOGY Previous Question Paper (December - 2018 - R13)
Note: This question paper contains two parts A and B. Part A is compulsory which carries 25 marks. Answer all questions in Part A. Part B consists of 5 Units. Answer any one full question from each unit. Each question carries 10 marks and may have a, b, c as sub questions.
Part A
Explain the conditions of Impact point calculation and injection.
Answer
Impact point calculation determines the landing or crash location by integrating the equations of motion under gravity and atmospheric drag. Injection refers to the precise moment and state vector (position and velocity) at which a spacecraft is released into its target orbit or trajectory from the launch vehicle.
Explain the concept of flight Dispersions.
Answer
Flight dispersions are the deviations from the nominal flight path caused by uncertainties in parameters such as atmospheric density, thrust magnitude, mass properties, and navigation errors. These dispersions necessitate the use of guidance and control systems to maintain the trajectory within acceptable mission limits.
Write a short note on Aero-Capture and Aero Assist.
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Explain the concept of Aero- braking.
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Explain the concept of two-body motion.
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Show that for any two body trajectory
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What is stabilization and explain the types used in it.
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Explain the technique of YO-YO mechanism.
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What are different types of Mission phases?
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Write a note on Missions operations center (MOC).
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Part B
Explain Basic configuration of Liquid propellant rocket system using neat sketches.
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Explain Injection process and types of injectors used in Liquid propellant rocket system.
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Write a note on the following: i) Regenerative cooling. ii) Film or boundary layer cooling.
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Discuss different types of grain configuration found in solid motors.
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Bring out the significance of Re-entry corridor using ballistic orbital re-entry.
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What are the potential forces that act on a re-entry vehicle? Among these which is the dominant force during re-entry. Explain why?
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Explain the effects of heating on the trajectory of a re-entry space vehicle. Indicate the heating rate profiles for launch vehicles having various ballistic coefficient values, in a graphical form.
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Write a short note on ‘the three competing re-entry requirements’.
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Consider a Hohmann transfer from a circular orbit of radius r1 to another coplanar circular orbit or radius r2. Let Δv be the sum of the two velocity increments required for the maneuver. Show that for a fixed gravitational parameter and radius r1, the maximum required Δv occurs for r2= 15.58 r1.
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Derive an equation in terms of velocity at any point on a Parabolic orbit under Two body motions.
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In general co planner maneuver, consider an initial direct, circular earth orbit of radius 9100 km and a final direct, co- planner, elipitical orbit with e=0.1 and rp=9000km.what velocity change is require to make the transfer?
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Explain how spacecraft attitude sensors used in attitude determination?
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Explain how jet damping is useful in controlling spinning vehicles.
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Write a note on spacecraft attitude sensors.
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Write about attitude control for gravity-gradient stabilization of a spacecraft.
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Explain high level space mission operations architecture with the help of neat sketches.
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Explain various types of ground supporting systems in space operations?
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Discuss how the weather conditions are going to affect the launching of a space vehicle and the role of flight control team in adverse situations.
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Distinguish between down link, up link, forward link, return link, and cross link related to communication of information transfer between ground control station and a space craft.
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