1. Sir I would like to ask a question How do variations in orbital eccentricity affect the application of Kepler third Law for satellites in non-circular orbits? 😅
@@Ali-iw4wn Thanks for your support. Regarding your question I can say that for elliptical orbit the law holds the same way as it does for circular orbit. The law will be T² proportional to a³, where "a" is the length of the semi-major axis of the elliptical orbit. The relation between the semi-major and semi-minor axis in terms of eccentricity is: b²=a²(1-e²). For circular orbit e=1, so a=b=radius (r). Hope I have cleared your doubt.☺️
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Wow
@@mahimajhanwar928 Thanks for the support. Keep engaging with us.❤️
Very nice sir. Also, give some from our topics 😊
@@Asmita-p7h Thanks for the support. Next time we will try to give on the topic that you want.❤️
1. Sir I would like to ask a question How do variations in orbital eccentricity affect the application of Kepler third Law for satellites in non-circular orbits? 😅
@@Ali-iw4wn Thanks for your support. Regarding your question I can say that for elliptical orbit the law holds the same way as it does for circular orbit. The law will be T² proportional to a³, where "a" is the length of the semi-major axis of the elliptical orbit. The relation between the semi-major and semi-minor axis in terms of eccentricity is: b²=a²(1-e²). For circular orbit e=1, so a=b=radius (r). Hope I have cleared your doubt.☺️
@@SPEducation31 thanks sir