Answered: an asteroid has 47000kg semi major axis… | bartleby

Related questions

Question

an asteroid has 47000kg semi major axis a =3.7 AU (1AU=1.5e11m) with eccentricity e=0.67 the mass of the sun is 2.0 e30 kg

Using conservation of energy find the velocity of the comet at aphelion (show work)

Expert Solution

Trending now

This is a popular solution!

Step by step

Solved in 2 steps with 2 images

SEE SOLUTION Check out a sample Q&A here

Blurred answer

Similar questions

The Molniya orbit is a 12 hour period highly eccentric orbit used by Russia for communication satellites. Perigee and Apogee of the Molniya orbit are 500 km and 39, 873 km respectively. Consider a satellite deployed in such a orbit. Determine the satellite's time of flight from the perigee to an altitude of 30, 000 km ( when the satellite is past the apogee and returning back to the perigee).
Can you show me how to solve this?
The escape velocity on the surface of the Moon is 2.4 Km/sec, and the radius of the Moon is 0.27 Earth's radius. Find the mass of the Moon from this. Screenshot
What is the change in gravitational potential energy of a 65.5 kg astronaut lifted fromEarth’s surface into a circular orbit of altitude 4.50 x 10^2 km?
The orbit of a 1.5 x 1010 kg comet around the Sun is elliptical, with an aphelion distance of 11.0 AU and perihelion distance of 0.890 AU. (Note: 1 AU = one astronomical unit = the average distance from the Sun to the Earth = 1.496 x 101" m.) (a) What is its orbital eccentricity? (b) What is its period? (Enter your answer in yr.) yr (c) At aphelion what is the potential energy (in J) of the comet-Sun system?
A hypothetical planet was discovered orbiting around the star HD68988. Its orbitaldistance was measured to be 15.00 million kilometers. If it’s mass is twice of our Sun,what is the orbital period of the planet? Please show work.
A satellite is in a circular orbit at an altitude of 250km above the earth's surface. The onboard rocket provides a Av = 200m/s, calculate the new velocity at perigee (v2) in the transfer orbit, Specific angular momentum of the transfer orbit (h₂), and eccentricity of the transfer orbit (e₂). Hohmann transfer ellipse B Apoapsis AUB Circle Circle AVA A Periapsis
Given data for the earth below find the distance a satellite would be from the center of the earth if is orbital speed was 15000m/s? is this possible (or would it put the satellite inside the earth ie would the satellite crash immediately?) you must back up your answer with a calculation note that the mass of the satellite is not needed here Me= 6.0×1024kg Re=6.4×103km G=6.7×10-11 Nm2/kg2