To prove: The ratio A − P A + P is equal to the eccentricity of the elliptical orbit of the planet/satellite, where P is the closest distance of the planet/satellite to the focus and A is the greatest distance from the focus.

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Answer 1

Question

Chapter 7.2, Problem LC

(a)

To determine

To prove: The ratio A−PA+P is equal to the eccentricity of the elliptical orbit of the planet/satellite, where P is the closest distance of the planet/satellite to the focus and A is the greatest distance from the focus.

(b)

To determine

To calculate: The apogee and perigee for the satellite Sputnik I whose altitude varies from 132 miles to 583 miles above the surface of the earth and the center of the earth is one focus of the elliptical orbit of the satellite.

(c)

To determine

To calculate: The eccentricity of the satellite Sputnik I whose perigee is 4082 miles and apogee is 4533 miles.

(d)

To determine

To calculate: The apogee for planet Pluto whose perigee is 29.64 AU and the eccentricity of its elliptical orbit is 0.2484.

(e)

To determine

To calculate: The perigee for planet Mars whose apogee is 2.492×108 km and the eccentricity of its elliptical orbit is 0.0934.

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1 Matching 10 points Factor and Solve 1)x3-216 0, x = {6,[B]} 2) 16x3 = 54 x-[3/2,[D]] 3)x4x2-42 0 x= [ +/-isqrt(7), [F] } 4)x+3-13-9x x=[+/-1.[H]] 5)x38x2+16x=0, x = {0,[K}} 6) 2x6-10x-48x2-0 x-[0, [M], +/-isqrt(3)) 7) 3x+2x²-8 x = {+/-i sqrt(2), {Q}} 8) 5x³-3x²+32x=2x+18 x = {3/5, [S]} [B] [D] [F] [H] [K] [M] [Q] +/-2 sqrt(2) +/- i sqrt(6) (-3+/-3 i sqrt(3))/4 +/- 1 +/-sqrt(6) +/- 2/3 sqrt(3) 4 -3 +/- 3 i sqrt(3) [S]

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Graph without using the calculator y-1 = | x+4 |

Answer 2

Question

Chapter 7.2, Problem LC

(a)

To determine

To prove: The ratio A−PA+P is equal to the eccentricity of the elliptical orbit of the planet/satellite, where P is the closest distance of the planet/satellite to the focus and A is the greatest distance from the focus.

(b)

To determine

To calculate: The apogee and perigee for the satellite Sputnik I whose altitude varies from 132 miles to 583 miles above the surface of the earth and the center of the earth is one focus of the elliptical orbit of the satellite.

(c)

To determine

To calculate: The eccentricity of the satellite Sputnik I whose perigee is 4082 miles and apogee is 4533 miles.

(d)

To determine

To calculate: The apogee for planet Pluto whose perigee is 29.64 AU and the eccentricity of its elliptical orbit is 0.2484.

(e)

To determine

To calculate: The perigee for planet Mars whose apogee is 2.492×108 km and the eccentricity of its elliptical orbit is 0.0934.

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Answer 3

Question

Chapter 7.2, Problem LC

(a)

To determine

To prove: The ratio A−PA+P is equal to the eccentricity of the elliptical orbit of the planet/satellite, where P is the closest distance of the planet/satellite to the focus and A is the greatest distance from the focus.

(b)

To determine

To calculate: The apogee and perigee for the satellite Sputnik I whose altitude varies from 132 miles to 583 miles above the surface of the earth and the center of the earth is one focus of the elliptical orbit of the satellite.

(c)

To determine

To calculate: The eccentricity of the satellite Sputnik I whose perigee is 4082 miles and apogee is 4533 miles.

(d)

To determine

To calculate: The apogee for planet Pluto whose perigee is 29.64 AU and the eccentricity of its elliptical orbit is 0.2484.

(e)

To determine

To calculate: The perigee for planet Mars whose apogee is 2.492×108 km and the eccentricity of its elliptical orbit is 0.0934.

Expert Solution & Answer

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Answer 4

Question

Chapter 7.2, Problem LC

(a)

To determine

To prove: The ratio A−PA+P is equal to the eccentricity of the elliptical orbit of the planet/satellite, where P is the closest distance of the planet/satellite to the focus and A is the greatest distance from the focus.

(b)

To determine

To calculate: The apogee and perigee for the satellite Sputnik I whose altitude varies from 132 miles to 583 miles above the surface of the earth and the center of the earth is one focus of the elliptical orbit of the satellite.

(c)

To determine

To calculate: The eccentricity of the satellite Sputnik I whose perigee is 4082 miles and apogee is 4533 miles.

(d)

To determine

To calculate: The apogee for planet Pluto whose perigee is 29.64 AU and the eccentricity of its elliptical orbit is 0.2484.

(e)

To determine

To calculate: The perigee for planet Mars whose apogee is 2.492×108 km and the eccentricity of its elliptical orbit is 0.0934.

Expert Solution & Answer

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Answer 5

Chapter 7.2, Problem LC

(a)

To determine

To prove: The ratio A−PA+P is equal to the eccentricity of the elliptical orbit of the planet/satellite, where P is the closest distance of the planet/satellite to the focus and A is the greatest distance from the focus.

(b)

To determine

To calculate: The apogee and perigee for the satellite Sputnik I whose altitude varies from 132 miles to 583 miles above the surface of the earth and the center of the earth is one focus of the elliptical orbit of the satellite.

(c)

To determine

To calculate: The eccentricity of the satellite Sputnik I whose perigee is 4082 miles and apogee is 4533 miles.

(d)

To determine

To calculate: The apogee for planet Pluto whose perigee is 29.64 AU and the eccentricity of its elliptical orbit is 0.2484.

(e)

To determine

To calculate: The perigee for planet Mars whose apogee is 2.492×108 km and the eccentricity of its elliptical orbit is 0.0934.

Answer 6

Chapter 7.2, Problem LC

(a)

To determine

To prove: The ratio A−PA+P is equal to the eccentricity of the elliptical orbit of the planet/satellite, where P is the closest distance of the planet/satellite to the focus and A is the greatest distance from the focus.

Answer 7

Chapter 7.2, Problem LC

(a)

To determine

To prove: The ratio A−PA+P is equal to the eccentricity of the elliptical orbit of the planet/satellite, where P is the closest distance of the planet/satellite to the focus and A is the greatest distance from the focus.

Answer 8

(b)

To determine

To calculate: The apogee and perigee for the satellite Sputnik I whose altitude varies from 132 miles to 583 miles above the surface of the earth and the center of the earth is one focus of the elliptical orbit of the satellite.

Answer 9

(b)

To determine

To calculate: The apogee and perigee for the satellite Sputnik I whose altitude varies from 132 miles to 583 miles above the surface of the earth and the center of the earth is one focus of the elliptical orbit of the satellite.

Answer 10

(c)

To determine

To calculate: The eccentricity of the satellite Sputnik I whose perigee is 4082 miles and apogee is 4533 miles.

Answer 11

(c)

To determine

To calculate: The eccentricity of the satellite Sputnik I whose perigee is 4082 miles and apogee is 4533 miles.

Answer 12

(d)

To determine

To calculate: The apogee for planet Pluto whose perigee is 29.64 AU and the eccentricity of its elliptical orbit is 0.2484.

Answer 13

(d)

To determine

To calculate: The apogee for planet Pluto whose perigee is 29.64 AU and the eccentricity of its elliptical orbit is 0.2484.

Answer 14

(e)

To determine

To calculate: The perigee for planet Mars whose apogee is 2.492×108 km and the eccentricity of its elliptical orbit is 0.0934.

Answer 15

(e)

To determine

To calculate: The perigee for planet Mars whose apogee is 2.492×108 km and the eccentricity of its elliptical orbit is 0.0934.

Answer 16

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Answer 17

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Answer 18

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Answer 19

Ch. 7.1 - True or False? Explain. A parabola with focus (0,...Ch. 7.1 - Prob. 2FT Ch. 7.1 - Prob. 3FT Ch. 7.1 - Prob. 4FT Ch. 7.1 - Prob. 5FT Ch. 7.1 - Prob. 6FT Ch. 7.1 - Prob. 7FT Ch. 7.1 - Prob. 8FT Ch. 7.1 - Prob. 9FT Ch. 7.1 - Prob. 10FT

To prove: The ratio A − P A + P is equal to the eccentricity of the elliptical orbit of the planet/satellite, where P is the closest distance of the planet/satellite to the focus and A is the greatest distance from the focus.

Solution Summary: The author calculates the eccentricity of the elliptical orbit of a planet/satellite.

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To prove: The ratio A−PA+P is equal to the eccentricity of the elliptical orbit of the planet/satellite, where P is the closest distance of the planet/satellite to the focus and A is the greatest distance from the focus.

To calculate: The apogee and perigee for the satellite Sputnik I whose altitude varies from 132 miles to 583 miles above the surface of the earth and the center of the earth is one focus of the elliptical orbit of the satellite.

To calculate: The eccentricity of the satellite Sputnik I whose perigee is 4082 miles and apogee is 4533 miles.

To calculate: The apogee for planet Pluto whose perigee is 29.64 AU and the eccentricity of its elliptical orbit is 0.2484.

To calculate: The perigee for planet Mars whose apogee is 2.492×108 km and the eccentricity of its elliptical orbit is 0.0934.

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Chapter 7 Solutions