Consider a US Air Force launch of its latest GPS satellite from Cape Canaveral. Radar tracking shows the following J2000 state vector (X,Y,Z and Vx,Vy,Vz) at burnout. 26 Feb 2022 17:10:00.000 (X,Y,Z): 5210.345121 -549.481941 4300.883291 (Vx,Vy,Vz): -1.451280 7.391098 2.690198 Calculate the minimum total delta V required to maneuver this spacecraft into a circular orbit with a 12-hour period and an inclination of 61 degrees, assuming impulsive maneuvers and two-body dynamics. Please solve using equations from Howard Curtis's Orbital Mechanics for Engineering Students, 4th Edition. Or if not possible name the equations you use. If you could solve with specific angular momentum "h", earth gravitational parameter "mu", semimajor axis "a", and the target velocity for orbit "v_target". Also please use matlab syntax for solving or write the equations out clearly. Thanks!

Consider a US Air Force launch of its latest GPS satellite from Cape Canaveral. Radar tracking shows the following J2000 state vector (X,Y,Z and Vx,Vy,Vz) at burnout. 26 Feb 2022 17:10:00.000 (X,Y,Z): 5210.345121 -549.481941 4300.883291 (Vx,Vy,Vz): -1.451280 7.391098 2.690198 Calculate the minimum total delta V required to maneuver this spacecraft into a circular orbit with a 12-hour period and an inclination of 61 degrees, assuming impulsive maneuvers and two-body dynamics. Please solve using equations from Howard Curtis's Orbital Mechanics for Engineering Students, 4th Edition. Or if not possible name the equations you use. If you could solve with specific angular momentum "h", earth gravitational parameter "mu", semimajor axis "a", and the target velocity for orbit "v_target". Also please use matlab syntax for solving or write the equations out clearly. Thanks!

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Question

Consider a US Air Force launch of its latest GPS satellite from Cape Canaveral. Radar tracking shows the following J2000 state vector (X,Y,Z and Vx,Vy,Vz) at burnout.

26 Feb 2022 17:10:00.000

(X,Y,Z):

5210.345121 -549.481941 4300.883291

(Vx,Vy,Vz):

-1.451280 7.391098 2.690198

Calculate the minimum total delta V required to maneuver this spacecraft into a circular orbit with a 12-hour period and an inclination of 61 degrees, assuming impulsive maneuvers and two-body dynamics.

Please solve using equations from Howard Curtis's Orbital Mechanics for Engineering Students, 4th Edition. Or if not possible name the equations you use. If you could solve with specific angular momentum "h", earth gravitational parameter "mu", semimajor axis "a", and the target velocity for orbit "v_target".

Also please use matlab syntax for solving or write the equations out clearly. Thanks!

Definition Definition Product of the moment of inertia and angular velocity of the rotating body: (L) = Iω Angular momentum is a vector quantity, and it has both magnitude and direction. The magnitude of angular momentum is represented by the length of the vector, and the direction is the same as the direction of angular velocity.

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