initial commit / add all books

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diff --git a/1172/CH8/EX8.14/8_14.txt b/1172/CH8/EX8.14/8_14.txt
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+ # Problem 14 # 

+

+ Standard formula used 1/2 *(m_s * v ^2 / r) = g * R_E^2 * m /R_e^2 

+ Magnitude and direction of impulse required are respectively 8.047626e+05kgm/s and 18.098444 degree.

+

diff --git a/1172/CH8/EX8.14/Example8_14.sce b/1172/CH8/EX8.14/Example8_14.sce
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+clc

+//Given that

+h = 600 // distance of satellite from surface of Earth in km

+R_e = 6400 // radius of Earth in km

+m_s = 100  // mass of satellite in kg

+g = 10 // gravitational acceleration in m/s2 

+v_y = 2500 // upward velocity of launched satellite

+// sample problem 14 page No. 306

+printf("\n\n\n # Problem 14 # \n")

+

+printf("\n Standard formula used 1/2 *(m_s * v ^2 / r) = g * R_E^2 * m /R_e^2 ")

+r = R_e + h// calculation of effective height of satellite

+

+v = sqrt (g * (R_e * 1e3)^2 / (r * 1e3)) // calculation of orbital velocity of satellite

+

+P_x = m_s * v// calculation of momentum in x direction

+P_y = m_s * v_y// calculation of momentum in y direction

+U = sqrt(P_x^2 + P_y^2 ) // calculation of magnitude of impulse required

+

+theta = (180 / %pi) * atan (P_y / P_x ) // calculation of direction of impulse required

+printf ("\n Magnitude and direction of impulse required are respectively %ekgm/s and %f degree.",U , theta)