G = 6.67 x 10-11 N-m²/kg²
ME = 5.97 x 1024 kg
U = -G ME m / r
ΔU = Up - Ua = (-G ME m /
rp) - (-G ME m / ra) = G
ME m (1 / ra - 1 / rp)
= (6.67*10-11)*(5.97*1024)*83.5((1/7330*103)-(1/6610*103))
= - 4.94 x 108 J
The mass of Sputnik I was 83.5 kg, and its distances from the center of the Earth at apogee and perigee were 7330 km an...
Sputnik The first artificial satellite to orbit the Earth was Sputnik I, launched October 4, 1957. The mass of Sputnik I was 83.5 kg, and its distances from the center of the Earth at apogee and perigee were 7330 km and 6610 km, respectively. Find the difference in gravitational potential energy for Sputnik I as it moved from apogee to perigee. (Joules)
Sputnik the first artificial satellite to orbit the Earth was Sputnik I launched October 4,1957. The mass of Sputnik I was 83.5 kg and it’s distance from the center of the Earth at apogee and perigee were 7330km and 6610 km respectively.Find the difference in gravitational potential energy for Sputnik I as it moved from apogee to perigee
1) The first artificial satellite to orbit the Earth was Sputnik I, launched October 4, 1957. The mass of Sputnik I was 83.5 kg, and its distances from the center of the Earth at apogee and perigee were approximately 7380 km and 6630 km, respectively. Find the difference in gravitational potential energy for Sputnik I as it moved from apogee to perigee. (Use a positive sign for an increase, negative sign for a decrease in U.) Answer in Joules. 2)...
a 83.5 kg satellite has a perigee of 6.61 x 10^6m and a apogee
of 7.33 x 10^6m. What is the difference in gravitational potential
energy as it moves from perigee to apogee.
9. An 83.5-kg satellite has a perigee (the distance from the point of closest approach to the T center of the Earth) of 6.61 *10 m and an apogee (the distance from the furthest point in the orbit to the center of the Earth) of 7.33 x...
In July 1965, the USSR launched Proton I, weighing 12,200 kg (at launch), with a perigee height of 183 km, an apogee height of 589 km and a period of 92.25 minutes. Using the relevant data for the mass of Earth (5.975 × 10^24 kg) and the gravitational constant G (G = 6.6720 × 10^−11 Nm^2/kg^2 ), find the semimajor axis a of the orbit. Compare your answer with the number you get by adding the perigee and apogee heights...
A satellite is put into an elliptical orbit around the Earth. When the satellite is at its perigee, its nearest point to the Earth, its height above the ground is hp = 249.0 km, and it is moving with a speed of up = 7.950 km/s. The gravitational constant G equals 6.67 x 10-11 mº.kg-1.5-2 and the mass of Earth equals 5.972 x 1024 kg. When the satellite reaches its apogee, at its farthest point from the Earth, what is...
A satellite is put into an elliptical orbit around the Earth. When the satellite is at its perigee, its nearest point to the Earth, its height above the ground is hp=227.0 km, and it is moving with a speed of vp=8.950 km/s. The gravitational constant G equals 6.67×10−11 m3·kg−1·s−2 and the mass of Earth equals 5.972×1024 kg. When the satellite reaches its apogee, at its farthest point from the Earth, what is its height ha above the ground? For this...
A satellite is put into an elliptical orbit around the Earth. When the satellite is at its perigee, its nearest point to the Earth, its height above the ground is he = 227.0 km, and it is moving with a speed of up = 8.050 km/s. The gravitational constant G equals 6.67 x 10-'1 m² kg---5-2 and the mass of Earth equals 5.972 x 1024 kg. When the satellite reaches its apogee, at its farthest point from the Earth, what...
Problem 1 a. The apogee and perigee altitude (distance from the surface of Earth) of the Chandra X-rays Observatory are 139,200 km and 9,620 km (final orbit after 4th burn, Aug 7, 1999). Estimate its orbital period (in hours). Hint: the mass of Chandra is much smaller than the mass of Earth. b. Communications and weather satellites are often placed in geosynchronous “parking” orbits above Earth. These are the orbits where satellites can remain fixed above a specific point on...
A satellite is put into an elliptical orbit around the Earth. When the satellite is at its perigee, its nearest point to the Earth, its height above the ground is ho = 207.0 km, and it is moving with a speed of v, = 8.050 kr/s. The gravitational constant G equals 6.67 x 10-11 m² kg-15-2 and the mass of Earth equals 5.972 x 1024 kg. When the satellite reaches its apogee, at its farthest point from the Earth, what...