Determine the parameter (p) for this orbit. Use 2 decimal places. Calculate the eccentricity (e) of this orbit and identify the shape of the orbit.

305 Week 2 Homework Assignment

In preparation for this Homework Assignment, review the information in this Week’s Lesson Readings and Read Chapter 2 of our Textbook, then Respond the Following Questions (Assume the average Earth Radius RE = 6378 km):

Using Newton’s Law of Universal Gravitation (G = 6.67 x 10–11 N·m2 /kg2 ) Calculate the average gravitational pull between the Earth and the Sun. The mass of the Sun is M Sun = 1.9891 x 10 30 kg and the mass of the Earth is m Earth = 5.9737 x 10 24 kg . 1 AU = 149,597,871 km. (6 Points)

A satellite is orbiting the Earth at an altitude of alt = 242 km . Its inertial velocity of v = 8.95 km/s and its flight-path angle is γ = 14°.

Determine the total specific energy (ξ) for this orbit. Use 2 decimal places. (4 Points)

Determine the semimajor axis (a) for the satellite. Use 2 decimal places. (4 Points)

What is the angular momentum (h) of the satellite? Use 2 decimal places. (4 Points)

Determine the parameter (p) for this orbit. Use 2 decimal places. (4 Points)

Calculate the eccentricity (e) of this orbit and identify the shape of the orbit. Use 4 decimal places. (6 Points)

A low-Earth satellite orbits at an average altitude of alt = 878 km and has a parameter of p = 7204 km.

Determine the total specific energy (ξ) for the orbit. Use 2 decimal places. (4 Points)

Determine the angular momentum (h) of this satellite. Use 2 decimal places. (4 Points)

Determine the eccentricity (e) of this orbit. Use 4 decimal places. (4 Points)

Calculate the Perigee radius (r p ) for this orbit. Will this satellite pass through any noticeable part of the Earth’s atmosphere? Use 2 decimal places. (6 Points)

Calculate the Apogee altitude (alta ) for this orbit. Use 2 decimal places. (5 Points)

A satellite has an apogee altitude of alt a = 4500 km and a perigee altitude of alt p = 500 km. The true anomaly is currently θ = 136°.

Calculate the semimajor axis (a) for this orbit. (4 Points)

Calculate the eccentricity (e) of this orbit. Use 4 decimal places (4 Points)

Determine the parameter (p) for this orbit. Use 2 decimal places. (4 Points)

Calculate the angular momentum (h) for this satellite. Use 2 decimal places. (4 Points)

Calculate the total specific energy (ξ) for this orbit. Use 2 decimal places. (4 Points)

Determine the current radius (r) of the orbit (at θ = 136°). Use 2 decimal places. (5 Points)

What is current velocity (v)of the satellite (at θ = 136°)? Use 2 decimal places. (5 Points)

What is the current flight path angle (h) of the satellite (at θ = 136°)? Use 2 decimal places. (5 Points)

A satellite has a very elliptical orbit with an apogee altitude of alt a = 265622 km and a perigee altitude of alt p = 222 km.

What is the semimajor axis (a) for this orbit? (4 Points)

What is the eccentricity (e) of this orbit? Use 4 decimal places. (4 Points)

Calculate the orbital period (Tperiod ) for this orbit. Express your final answer in days, minutes, and seconds. Express your answer in hours, minutes, and seconds (i.e., (2:25:23 or (2 hr, 25 min, 23 sec). Use 2 decimal places in your calculations (none required in the final answer). (6 Points)

The points for each problem are noted next to each part (100 Points Total for the Assignment)

 

Determine the parameter (p) for this orbit. Use 2 decimal places. Calculate the eccentricity (e) of this orbit and identify the shape of the orbit.
Scroll to top