An earth satellite is placed in an elliptic orbit. Thesatellite apogee is 9,000

Question

An earth satellite is placed in an elliptic orbit. Thesatellite apogee is 9,000 km. The satellite perigee is 6,000 km,The earth radius is 6,370 km. (1) What is the eccentricity of the orbit? (2) What is the velocity at apogee in meters per second? (3) What is the velocity at perigee in meters persecond? An earth satellite is placed in an elliptic orbit. Thesatellite apogee is 9,000 km. The satellite perigee is 6,000 km,The earth radius is 6,370 km. (1) What is the eccentricity of the orbit? (2) What is the velocity at apogee in meters per second? (3) What is the velocity at perigee in meters persecond?

Explanation / Answer

1)Eccentricity of theorbit(e)=1-b2/a2             =1-(6000)2/(9000)2             =0.7454 2)Velocity at apogee= va2    =   (  8.871 X 108 / a *6.68458134× 10-9 ) ( 1 - e ) / ( 1 + e )
Va=1.46*103Km/s 3)Velocityat perigee
vp2   =    ( 8.871 X108 / a ) ( 1 + e) / ( 1 - e )
Vp2=( 8.871 X108AU.m/s / 9000 *6.68458134 × 10-9) (1 + 0.7454 ) / ( 1-0.7454)
Vp=10.06*103Km/s

Related Questions

Navigate

• Browse (All)
• Browse A
• Subjects

---

---

Integrity-first tutoring: explanations and feedback only — we do not complete graded work. Learn more.