To make sure that The craft will not rotate about its mass center G at liftoff, the orbiter engine thrust is directed at angle theta to make the resultant moment acting on the entire craft assembly (external tank, solid rocket boosters, and orbiter) equal to zero {i.e.. sigma M_G = 0|. Note that sigma F_x notequalto 0|and sigma F_y notequalto 0|. (a) Resolve the orbiter thrust T_S, into horizontal and vertical components, and then sum moments about point G. the craft mass center. Set the resulting moment equation equal to zero. This equation can now be solved for the value of theta| required for liftoff. (b) Plot sigma M_G| for 0 lessthanorequalto theta lessthanorequalto x/2|at liftoff for the following launch information and visually determine the angle that balances out the moments. W_e = 1.7 times 10^5 lb, W_S = 0.3 times 10^5 lb, T _S = 5 3 times 10^5 lb, T_S = 1.1 times 10^5 lb To make sure that The craft will not rotate about its mass center G at liftoff, the orbiter engine thrust is directed at angle theta to make the resultant moment acting on the entire craft assembly (external tank, solid rocket boosters, and orbiter) equal to zero {i.e.. sigma M_G = 0|. Note that sigma F_x notequalto 0|and sigma F_y notequalto 0|. (a) Resolve the orbiter thrust T_S, into horizontal and vertical components, and then sum moments about point G. the craft mass center. Set the resulting moment equation equal to zero. This equation can now be solved for the value of theta| required for liftoff. (b) Plot sigma M_G| for 0 lessthanorequalto theta lessthanorequalto x/2|at liftoff for the following launch information and visually determine the angle that balances out the moments. W_e = 1.7 times 10^5 lb, W_S = 0.3 times 10^5 lb, T _S = 5 3 times 10^5 lb, T_S = 1.1 times 10^5 lb