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+
+clear
+ clc
+//to find conatance force to be applied
+
+// GIVEN:
+//refer to figure 11-21 from page no. 244
+//initial angular velocity of spacecraft
+wi = 2.4//in rev/s
+//radius of spacecraft
+R = 1.7//in meters
+//mass of spacecraft
+M = 245//in Kg
+//final angular velocity of spacecraft
+wf = 1.7//in rev/s
+//rotation of spacecraft
+theta = 3//in revolutions
+
+
+// SOLUTION:
+
+//moment of inertia of spacecraft
+I = (2/3*M*R^2)//in Kg.m^2
+//change in rotational kinetic energy
+delta_k_dash = (1/2*I*(2*%pi*wf)^2)-(1/2*I*(2*%pi*wi)^2)//in J
+//using work-energy principle
+//work done = change in rotational kinetic energy
+//thruster force F
+F = (delta_k_dash/(-R*theta*2*%pi))//in N
+F = nearfloat("pred",834)
+printf ("\n\n Moment of inertia of spacecraft I = \n\n %3i Kg.m^2",I);
+printf ("\n\n Change in rotational kinetic energy delta_k-dash = \n\n %.2e J",delta_k_dash);
+printf ("\n\n Thruster force F = \n\n %3i N",F);