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Problem 13.67 Consider a spacecraft in an eliptical orbit around the earth. At the low point, or perigee, of its orbit, at is 450 km above the earth's surface; at the Nigh point, or apogee, it is 4000 km above the earth's surface Y Part A What is the period of the spacecraft's orbi? Express your answer in seconds. T-7040 Submit Previous Answers ✔Correct Part B Pape Using conservation of angular momentum, find the ratio of the spacecraft's speed at perigee to its speed at apogee -1.52 Part C Previous Answers ✓ Correct 11 of 15 Review 1 Constanta
Problem 13.57 Consider a spacecraft in an eliptical orbit around the earth. At the low point, or perigoe, of its orbit, it is 450 km above the earth's surface; at the high point, or apogee, it is 4000 km above the earth's surface. Part C Using conservation of energy, find the speed at perigee and the speed at apogee Enter your answers in meters per second separated by a comma 195] ΑΣΦΑ 810¹.6.56 10¹ Submit Previo Antest Amer * Incorrect; Try Again; 27 attempts remaining Part D 19ΕΙ ΛΕΦ Aper-3.2.10¹ 9 ? ? 10/ It is necessary to have the spacecraft escape from the earth completely. If the spacecraft's rockets are fred at perigee, by how much would the speed have to be increased to achieve this? Express your answer in meters per second. 11 of 15 Review Constants
Consider a spacecraft in an eliptical orbit around the earth. At the low point, or perigee, of its orbit, it is 450 km above the earth's surface; at the high point, or apogee, it is 4000 km above the earth's surface. VD] ΑΣΦ Aperigne 3.2 10³ Submit . Part E 5 Previous Answers Request Answer X Incorrect; Try Again; 27 attempts remaining What if the rockets were fired at apogee? Express your answer in meters per second. [5] ΑΣΦΑ 3 A Atop 6.56 10¹ Submit Previous Answers Request Answer 193 ? X Incorrect; Try Again; 26 attempts remaining m/s m/s
CHW13 Problem 13.67 Consider a spacecraft in an elliptical orbit around the arth. At the low point, or perigee, of its orbit, it is 450 km above the earth's surface, at the high point, or apoges, a is 4000 km above the earth's surface Part A What is the period of the spacecrafts orbit? Express your answer in seconds. T= 7940 # Previous Answers ✔Correct Part 8 Previous Answers 11 of 15 > Using conservation of angular momentum, find the ratio of the spacecraft's speed at perigee to a speed at apogee Correct Betew Constants
Problem 13.67 Consider a spacecraft in an elliptical orbit around the earth. At the low point, or perigee, of its orbit, it is 450 km above the earth's surface; at the high point, or apogee, it is 4000 km above the earth's surface. Part C Using conservation of energy find the speed at perigee and the speed at apogee Enter your answers in meters per second separated by a comma Submit Part D A24 4 810,6.56 10 Previous Anawest Ana X Incorrect; Try Again; 27 attempts remaining ΕΠΙ ΑΣΦ ? to/s 11 of 15 It is necessary to have the spacecraft escape from the earth completely. If the spacecraft's rockets are fred at perigee, by how much would the speed have to be increased to achieve this? Express your answer in meters per second.
Consider a spacecraft in an elliptical orbit around the earth. At the low point, or perigee, of its orbit, it is 450 km above the earth's surface; at the high point, or apogee, it is 4000 km above the earth's surface. Y Part D It is necessary to have the spacecraft escape from the earth completely. If the spacecraft's rockots are fred at perigee, by how much would the speed have to be increased to achieve this? Express your answer in meters per second. VE ΑΣΦΑ Aterigne 3.2 10³ Submit X Incorrect; Try Again; 2tempts remaining Part E Previous Answers Request Answer What if the rockets were fired at apogee? Express your answer in meters per second. ΑΣΦ -6.56 10³ Appe O Review Constants m/s