If the position vector of the International Space Station in the geocentric equatorial frame is
r = – 5368 \hat{I} – 1784 \hat{J} + 3691 \hat{K} (km)
what are its RA and Dec?
We employ Algorithm 4.1.
Step 1:
r={\sqrt{\left(-5368\right)^{2}+\left(-1784\right)^{2}+3691^{2}}}=6754\,\mathrm{km}
Step 2:
I={\frac{-5368}{6754}}=-0.7947\;\;\;\;m={\frac{-1784}{6754}}=-0.2642\;\;\;\;n={\frac{3691}{6754}}=0.5462
Step 3:
\delta={\sin}^{-1}0.5464=33.12°
Step 4:
Since the direction cosine m is negative ,
\alpha=360^{\circ}-\cos^{-1}\left({\frac{I}{\cos\delta}}\right)=360^{\circ}-\cos^{-1}\left({\frac{-0.7947}{\cos33.12^{\circ}}}\right)=360^{\circ}-161.6^{\circ}=198.4^{\circ}