# Mechanics and thermodynamics of propulsion addison

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"Mechanics and Thermodynamics of Propulsion". Addison-Wesley Publishing Company, Inc., USA. ISBN 0-201-14659-2. Each question carry 10 points each, in total 30 points for the assignment. Page 10

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All the data provided in the question need not be necessary to use for finding the solution. The dead line to submit the assignment is 30 th April 2009 before 16:00. You can hand in your assignment through email only if it is typed not if hand written or at my office, room number L322 located near HPT Kitchen (first floor), call using phone at the entrance with number 7682 to get in. All the best! Page 11
ROCKET PROPULSION - HOME ASSIGNMENT 3 (Chapter 12) 1. The results of calculations with the STANJAN code show that the equilibrium composition resulting from a mixture of 1 kg of RP1 fuel (composition given by CH 1.96 ) and 2.58 kg of O 2 at 3676 K and 6.89 MPa has the mole fractions shown in Table 12.2. Given the following values of the equilibrium constant K P at 3676 K, check whether the stated mole fractions are approximately consistent with these values. (Problem 2, Page 608) = = 0.295 = = 0.740 = = 0.44 = = 2.42 = = 0.559 Page 12

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2. A certain solid propellant burns at a rate shown in the figure. It is being used in a rocket combustion chamber in which the stagnation pressure is approximately constant at 3.5 MPa. The initial grain temperature is 280 K. Suddenly a large crack develops in the propellant grain, which increases the burning area by 10%. What will happen to the chamber pressure? If the gas temperature, chamber volume, burning area, and the throat area were known, show how the pressure transient could be calculated. (Problem 12, Page 611 and 612) Note: The second part of the question needs qualitative answer not quantitative. Refer equation 12.28 Page 599 and equation 12.29 for first part of the question. Page 13
Problem 12, Page 612 3. The burning rate of a particular propellant is given by r = c/( T 1 T ) P o n in which r is in mm/s, P o is in MPa, T is in K and c = 176, T 1 = 415 K, n = 0.716. When the propellant initial temperature is 20 o C, the chamber pressure is 3 MPa (Steady) for 4 min. If the same propellant grain in the same rocket is heated to 45 o C, what would be the new steady state pressure level and burning period? Assume the time required to reach steady state is small compared to the burning time. (Problem 17, Page 613) Page 14

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INSTRUCTIONS: All the question numbers, tables, figures, page numbers correspond to book Hill, P. and Peterson, R. 1992.
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