A GPS satellite with upper stage is delivered by the second stage of a launch vehicle...

 

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A GPS satellite with upper stage is delivered by the second stage of a launch vehicle into a parking orbit with the following initial conditions in the ECI frame: overline r 1 =6900 hat i(km) overline v 1 = dot overline r 1 =4.359 hat j +6.226 hat k(km/ s) Giving the orbit angular momentum vector: vec h =-42959 hat j +30077 hat k (k*m ^2/ s) The upper stage will deliver the satellite to its destination orbit, which is circular with a radius of 26,500 km and an inclination of 0.96 rad (55deg). The total mass of the upper stage before the orbit transfer is 7000 kg, including the satellite payload, propellant This uppere stage has a propulsion system with an effective I sp of 340 sec. (Note: mu oplus = 3.986*10^5*k* m^3/(s^2)) A GPS satellite with upper stage is delivered by the second stage of a launch vehicle into a parking orbit with the following initial conditions in the ECI frame: overline r 1 =6900 hat i(km) overline v 1 = dot overline r 1 =4.359 hat j +6.226 hat k(km/ s) Giving the orbit angular momentum vector: vec h =-42959 hat j +30077 hat k (k*m ^2/ s) The upper stage will deliver the satellite to its destination orbit, which is circular with a radius of 26,500 km and an inclination of 0.96 rad (55deg). The total mass of the upper stage before the orbit transfer is 7000 kg, including the satellite payload, propellant This uppere stage has a propulsion system with an effective I sp of 340 sec. (Note: mu oplus = 3.986*10^5*k* m^3/(s^2))

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To determine the deltav required for the orbit transfer we need to calculate the velocity change nee... View the full answer