You can just give me the equation and I think I can do it fromthere. But if you\
ID: 1723014 • Letter: Y
Question
You can just give me the equation and I think I can do it fromthere. But if you're willing to, then please show me the steps onhow you got the answer cause I would love to learn all theseequations for future references. Thanks all for your help!!! A satellite of mass 190 kg islaunched from a site on Earth's equator into an orbit at185 km above the surface of Earth. (a) Assuming a circular orbit, what is theorbital period of this satellite?s
(b) What is the satellite's speed in its orbit?
m/s
(c) What is the minimum energy necessary to place the satellite inorbit, assuming no air friction?
J You can just give me the equation and I think I can do it fromthere. But if you're willing to, then please show me the steps onhow you got the answer cause I would love to learn all theseequations for future references. Thanks all for your help!!! A satellite of mass 190 kg islaunched from a site on Earth's equator into an orbit at185 km above the surface of Earth. (a) Assuming a circular orbit, what is theorbital period of this satellite?
s
(b) What is the satellite's speed in its orbit?
m/s
(c) What is the minimum energy necessary to place the satellite inorbit, assuming no air friction?
J (a) Assuming a circular orbit, what is theorbital period of this satellite?
s
(b) What is the satellite's speed in its orbit?
m/s
(c) What is the minimum energy necessary to place the satellite inorbit, assuming no air friction?
J
Explanation / Answer
if you just want the equations, hyperphysics has a goodtutorial. otherwise, keep reading. first, find the acceleration due to gravity at that height. use newton's law of universal gravitation: F=m*a=G*M*m/r2 where G is newton's gravitational constant, M is the mass of theearth, r is the distance from the satellite to the center of theearth, and m is an arbitrary mass (which will cancel out). weget the acceleration to be: a=G*M/r2=(6.67*10-11)(5.97*1024)/(6378000+185000)2=9.24m/s2 a satellite's velocity is given by: v=(r*a)=((6563000*9.24)=7790 m/s to find the period, find the total distance the satellitecovers in one orbit, and divide by the velocity: 6563000*2/7787=5300 s KE=.5*mv2=.5*190*77902=5.765*109 PE=mgh=190*9.8*185000=3.44*108 (to simplify, we assumeg=9.8) E=PE+KE=6.11*109 J
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