Question

A spacecraft has rendezvoused with an asteroid. The spacecraft is in station-keeping mode and the position of the asteroid center-of-gravity (c.g.) relative to the spacecraft is constant. The spacecraft's control system has stabilized the spacecraft and the spacecraft is inertially stable. That is, the spacecraft's reference frame is an inertial frame. The asteroid is rotating about its c.g. at a rate, o. The mission is to land a small probe on the asteroid at the point designated "P". The spacecraft must control the probe and must match the velocity of "P". a. Given the parameters below, find the velocity of "P" relative to the spacecraft in the spacecraft reference frame. RA-1700is 400j, 50ks m.-constant R, 150,A-200Ja + 300ka m.-constant ω-0025 İA + 0.01 2Ja + 0.027ka rad / sec .-constant Currently: Θ-890 Φ 0° Ψ_0° A 3-2-1 (Ψ,9,4) rotation sequence was used to transform from the inertial (spacecraft) frame to the asteroid frame. What is the velocity of "P" relative to the asteroid reference frame? b. Rp RA

Answer 1