6666.7310 m + 6.5510 m6.6410 m.22apRRa+××===×(b) The apogee and perigee distances are related to the eccentricity eby Ra= a(1 + e) and Rp= a(1−e). Add to obtain Ra+ Rp= 2aand a= (Ra+ Rp)/2. Subtract to obtain Ra−Rp= 2ae. Thus, 6.7310 m6.5510 m0.0136.26.7310 m6.5510 mRRRReaRR−−×−×====+×+×47. (a) The greatest distance between the satellite and Earth’s center (the apogee distance)
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