Question

consider a spacecraft in an elliptical orbit around the earth. At the low point, or perigee,...

consider a spacecraft in an elliptical orbit around the earth. At the low point, or perigee, of its orbit, it is 300 km above the earth's surface; at the high point or apogee, it is 2500 km above the earth's surface.

Part A: find ratio of the spacecraft's speed at perigee to its speed at apogee?

(Vperigee / Vapogee) = .....

Part B: find the speed at the apogee?

V apogee = ........ m/s

Part C: find speed at perigee?

V perigee = ..... m/s

Homework Answers

Know the answer?
Your Answer:

Post as a guest

Your Name:

What's your source?

Earn Coins

Coins can be redeemed for fabulous gifts.

Not the answer you're looking for?
Ask your own homework help question
Similar Questions
consider a spacecraft in an elliptical orbit around the earth. At the low point, or perigee,...
consider a spacecraft in an elliptical orbit around the earth. At the low point, or perigee, of its orbit, it is 300 km above the earth's surface; at the high point or apogee, it is 2500 km above the earth's surface. Part A: find ratio of the spacecraft's speed at perigee to its speed at apogee? (Vperigee / Vapogee) = ..... Part B: find the speed at the apogee? V apogee = ........ m/s Part C: find speed at perigee?...
A satellite is put into an elliptical orbit around the Earth. When the satellite is at...
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=241.0 km,hp=241.0 km, and it is moving with a speed of ?p=7.850 km/s.vp=7.850 km/s. The gravitational constant ?G equals 6.67×10−11 m3·kg−1·s−26.67×10−11 m3·kg−1·s−2 and the mass of Earth equals 5.972×1024 kg.5.972×1024 kg. When the satellite reaches its apogee, at its farthest point from the Earth, what is its height ℎaha above...
A spacecraft of mass 6.00 ? 104 kg is in a circular orbit at an altitude...
A spacecraft of mass 6.00 ? 104 kg is in a circular orbit at an altitude of 200 km above the Earth's surface. Mission Control wants to fire the engines so as to put the spacecraft in an elliptical orbit around the Earth with an apogee of 4.00 ? 104 km. How much energy must be used from the fuel to achieve this orbit? (Assume that all of the fuel energy goes into increasing the orbital energy. This model will...
Planetary Resources, Inc. launched it’s “tug” spacecraft to bring an asteroid into a elliptical Earth orbit...
Planetary Resources, Inc. launched it’s “tug” spacecraft to bring an asteroid into a elliptical Earth orbit with a semimajor axis of 7000 km and an eccentricity of 0.05. At the completion of this mission, a second “miner” spacecraft was launched into the asteroid orbit. When the spacecraft reaches orbit perigee, it is 20° behind the asteroid. Calculate the semimajor axis of the “miner” spacecraft’s phasing orbit required to rendezvous with the asteroid. Assume the phasing maneuver is initiated at perigee....
A satellite orbiting Earth has a speed of 28,070 km/hr when it is at its perigee...
A satellite orbiting Earth has a speed of 28,070 km/hr when it is at its perigee of 220km above Earth’s surface. Find the apogee distance, its speed at apogee and its period of revolution.
Two satellites are in circular orbits around the earth. The orbit for satellite A is at...
Two satellites are in circular orbits around the earth. The orbit for satellite A is at a height of 406 km above the earth's surface, while that for satellite B is at a height of 904 km. Find the orbital speed for satellite A and satellite B.
.A low Earth orbit (LEO) is an orbit around Earth with an altitude between 160 kilometers...
.A low Earth orbit (LEO) is an orbit around Earth with an altitude between 160 kilometers (99 mi) (orbital period of about 88 minutes). If the radius of the earth is around 6400km, what is the speed of a satellite (in Km/s) on this LEO?
14. Consider an artificial Satellite whose PERIGEE (closest point to Earth) is 3000 miles above the...
14. Consider an artificial Satellite whose PERIGEE (closest point to Earth) is 3000 miles above the Earth’s surface and whose APOGEE (farthest point to Earth) is 4200 miles above the surface. If we compare the satellite with Moon’s that is 239,000 miles far from the Earth and its time period is 27.3 days. Find the time period of the Satellite? Note: Radius of Earth is 3960 miles and average distance is R = (Rmax + Rmin) / 2 15. If...
A spacecraft of 150 kg mass is in a circular orbit about the Earth at a...
A spacecraft of 150 kg mass is in a circular orbit about the Earth at a height h = 5RE. (a) What is the period of the spacecraft's orbit about the Earth? T = answer in hours (b) What is the spacecraft's kinetic energy? K = Units in J (c) Express the angular momentum L of the spacecraft about the center of the Earth in terms of its kinetic energy K. (Use the following as necessary: RE for the radius...
On December 1, 2005, a spacecraft left a 180 km altitude circular orbit around Earth on...
On December 1, 2005, a spacecraft left a 180 km altitude circular orbit around Earth on a mission to Venus. It arrived at Venus 121 days later on April 1, 2006, entering a 300 km by 9000 km capture ellipse around the planet. Calculate the total delta v required for this mission.
ADVERTISEMENT
Need Online Homework Help?

Get Answers For Free
Most questions answered within 1 hours.

Ask a Question
ADVERTISEMENT