As it describes an elliptic orbit about the sun, a spacecraft reaches a maximum distance of 202
Question:
As it describes an elliptic orbit about the sun, a spacecraft reaches a maximum distance of 202 × 106 mi from the center of the sun at Point A (called the aphelion) and a minimum distance of 92 × 106 mi at Point B (called the perihelion). To place the spacecraft in a smaller elliptic orbit with aphelion at A' and perihelion at B', where A' and B' are located 164.5 × 106 mi and 85.5 × 106 mi, respectively, from the center of the sun, the speed of the spacecraft is first reduced as it passes through A and then is further reduced as it passes through B'. Knowing that the mass of the sun is 332.8 × 103 times the mass of the earth, determine
(a) The speed of the spacecraft at A,
(b) The amounts by which the speed of the spacecraft should be reduced at A and B' to insert it into the desired elliptic orbit.
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Step by Step Answer:
First note 6 R earth 3960 mi 209088 10 6 ft r A 202 10 6 mi 106656 10 9 ft r B 92 10 6 mi 485...View the full answer
Vector Mechanics for Engineers Statics and Dynamics
ISBN: 978-0073398242
11th edition
Authors: Ferdinand Beer, E. Russell Johnston Jr., David Mazurek, Phillip Cornwell, Brian Self
