.com question/22816263rch for an answer to any question...it worksFor parents For teachersHonor code16 nours agO• Chemistry Hign Scnoo1You are currently in a stable orbit 9000 km(1km=1000m) from the center of planet ProximaCentauri B.According to the calculations done by NASA, Planet Proxima Centauri B hasa mass of approximately 7.6x10^24kg.Based on fuel consumption and expected material aboard the ship, yourcolony ship lander has a mass of approximately 1.1x10^5 kg.1. Using Newton's Law of Universal Gravitation, determine what the force ofgravity on your ship at that orbit be using the early measurements2.Using Newton's second law determine the acceleration of your lander dueto gravity3.Upon arrival, you measure the actual force of gravity to be 6x10^5 N,whichic difforent from vourcalclated vauein cuection 1 ldentify 2cnocifice to search

Givenmass of proxima centauri m1=7.6×1024kgmass of ship lander m2=1.1×105kgradius of orbit…

Answered: prding to the calculations done by…

prding to the calculations done by NASA, Planet P ass of approximately 7.6x10^24kg. ed on fuel consumption and expected material abc ny ship lander has a mass of approximately 1.1x10

Principles of Heat Transfer (Activate Learning with these NEW titles from Engineering!)

8th Edition

ISBN:9781305387102

Author:Kreith, Frank; Manglik, Raj M.

Publisher:Kreith, Frank; Manglik, Raj M.

Chapter11: Heat Transfer By Radiation

Section: Chapter Questions

Problem 11.14P

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There are variety of errors that might affect the attitude motion of a spacecraft. Discuss what type of errors can be considered, and what kind of influence those errors might have on the resulting attitude motion. In all of our analysis so far, we have had an assumption that the orbit is circular. However, in general,we may also want to consider elliptic orbits depending on mission scenarios. Discuss how the equationsof motion and the subsequent analysis would be different if we consider elliptic orbits. Can we findrelative equilibrium solutions? How would the stability chart look like? Can we infer the attitudemotion in elliptic orbits from the circular orbit results?
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