A satellite of mass 175 kg is launched from a site on Earth's equator into an orbit at 195 km above the surface of Earth. (a) Assuming a circular orbit, what is the orbital period of this satellite? (b) What is the satellite's speed in its orbit? m/s (c) What is the minimum energy necessary to place the satellite in orbit, assuming no air friction?

A satellite of mass 175 kg is launched from a site on Earth's equator into an orbit at 195 km above the surface of Earth. (a) Assuming a circular orbit, what is the orbital period of this satellite? (b) What is the satellite's speed in its orbit? m/s (c) What is the minimum energy necessary to place the satellite in orbit, assuming no air friction?

Principles of Physics: A Calculus-Based Text

5th Edition

ISBN:9781133104261

Author:Raymond A. Serway, John W. Jewett

Publisher:Raymond A. Serway, John W. Jewett

Chapter11: Gravity, Planetary Orbits, And The Hydrogen Atom

Section: Chapter Questions

Problem 29P

See similar textbooks

Similar questions

It was stated that a satellite with negative total energy is in a bound orbit, whereas one with zero or positive total energy is in an unbounded orbit. Why zero or positive total energy is in an unbounded orbit. Why is this true? What choice for gravitational potential energy was made such that this is true?
Find the escape speed of a projectile from the surface of Jupiter.
What is the orbital radius of an Earth satellite having a period of 1.00 h? (b) What is unreasonable about this result?
If a spacecraft is headed for the outer solar system, it may require several gravitational slingshots with planets in the inner solar system. If a spacecraft undergoes a head-on slingshot with Venus as in Example 11.6, find the spacecrafts change in speed vS. Hint: Venuss orbital period is 1.94 107 s, and its average distance from the Sun is 1.08 1011 m.
Rank the following quantities of energy from largest to the smallest. State if any are equal. (a) the absolute value of the average potential energy of the SunEarth system (b) the average kinetic energy of the Earth in its orbital motion relative to the Sun (c) the absolute value of the total energy of the SunEarth system
A satellite has a mass of 5850 kg and is in a circular orbit 4.10 × 105 m above the surface of a planet. The period of the orbit is 2.00 hours. The radius of the planet is 4.15 × 106 m. (a) Find the mass of the planet,(b) the energy of the orbit, and (c) the escape velocity from this orbit. If the speed of the satellite is increased by 20% what would be the maximum distance above the planet? Needs Complete typed solution with 100% accuracy.
A spaceship with m = 1.00 ✕ 104 kg is in a circular orbit around the Earth, h = 800 km above its surface. The ship's captain fires the engines in a direction tangent to the orbit, and the spaceship assumes an elliptical orbit around the Earth with an apogee of d = 3.00 ✕ 104 km, measured from the Earth's center. How much energy (in J) must be used from the fuel to achieve this orbit? (Assume that all the fuel energy goes into increasing the orbital energy and that the perigee distance is equal to the initial radius.)
How much energy is required to move a satellite of mass 1000 kg from the surface of the Earth to an altitude 3 times the radius of the Earth? I was wondering if I did this question correctly.
For a satellite to be in a circular orbit 890 km above the surface of the earth, (a) what orbital speed must it be given, and (b) what is the period of the orbit (in hours)?
If you wanted to place a satellite in a geosynchronous orbit, at what height above the Earth's surface should you place it? (Earth's mass = 5.98x10^24, Earth's radius = 6x10^6, G = 6.67x10^-11) For the previous situation using the given answer, what is the difference in potential energy between the Earth's surface and the satellite height for a satellite with 1 kg mass?
There exista a spherical planet with a mass of M and a radius of R. How much energy is required to take a rocket of a mass m from rest on the surface of the planet to a circular orbit a height h above the surface?Find using the Energy Difference Ef -Ei where Ef is the energy in orbit and Ei is the energy at rest on the surface. h is not small
A satellite is in a circular low Earth orbit at an altitude of 356 km above the equator's surface. For Earth's radius at the equator, use RE, eq = 6.38 ✕ 106 m. Assuming only the force of Earth's gravity acts on the satellite, determine the smallest required change in the satellite's speed if it is to escape Earth's gravity and never return.