The interceptor is behind the target by 15 Solution We know that the value of eccentrcity is zero for circular orbit. e=0 Therefore the apogee and perigee distance from the earth will be same. Here we know the altitude of the orbit is 200 km. therefore the perigee of the phasing orbit will be = Radius of earth+ Altitude(= 200 km) Now we have to calculate dV which is change in velocity during transfer of orbit. So e= -u/2a where e(epsilon) is spacecraft mechaical energy Similalrly Now R can be calculated by the help of interceptor angle and the radius of the orbit. For orbit 1 we know the value of R which we have calculated in step1. For transfer orbit the value of R will be calculated = Initial value of R + Arc produced(due to 15 degree phase angle) Hence on putting the values in the above equation we can calculate the value of dV.

1. The interceptor is behind the target by 15
Solution
We know that the value of eccentrcity is zero for circular orbit.
e=0
Therefore the apogee and perigee distance from the earth will be same.
Here we know the altitude of the orbit is 200 km. therefore the perigee of the phasing orbit will
be
= Radius of earth+ Altitude(= 200 km)
Now we have to calculate dV which is change in velocity during transfer of orbit.
So e= -u/2a where e(epsilon) is spacecraft mechaical energy
Similalrly
Now
R can be calculated by the help of interceptor angle and the radius of the orbit.
For orbit 1 we know the value of R which we have calculated in step1.
For transfer orbit the value of R will be calculated = Initial value of R + Arc produced(due to 15
degree phase angle)
Hence on putting the values in the above equation we can calculate the value of dV