A satellite has the following position and velocity vectors: R vector = 7000I^ + 5000J^ + 728K^(km) V vector = 0.29I^ - 0.80J^ - 8.12K^(km/s) a.

A satellite has the following position and velocity vectors: R vector = 7000I^ + 5000J^ + 728K^(km) V vector = 0.29I^ – 0.80J^ – 8.12K^(km/s) a.

1. A satellite has the following position and velocity vectors: R vector = 7000I^ + 5000J^ + 728K^(km) V vector = 0.29I^ – 0.80J^ – 8.12K^(km/s) a. What is the specific angular momentum of the satellite? b. What is the satellite’s inclination? c. Calculate the ascending node vector. d. What is the spacecraft’s right ascension of the ascending node?

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A satellite has the following position and velocity vectors: R vector = 7000I^ + 5000J^ + 728K^(km) V vector = 0.29I^ – 0.80J^ – 8.12K^(km/s) a.

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A satellite has the following position and velocity vectors: R vector = 7000I^ + 5000J^ + 728K^(km) V vector = 0.29I^ – 0.80J^ – 8.12K^(km/s) a.

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