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An Earth-orbiting satellite has an eccentricity vector whose components are known in the ECI frame to be ([0.2730, 0.2730, -0.1310]). The RAAN is also known
An Earth-orbiting satellite has an eccentricity vector whose components are known in the ECI frame to be ([0.2730, 0.2730, -0.1310]). The RAAN is also known to be 0.2990 radians. What is the argument of perigee? Give your answer in radians with four digits to the right of the decimal place
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Introduction To Solid State Physics
Authors: Charles Kittel
6th Edition
471874744, 978-0471874744
