# The orbit of a spacecraft about the sun has a perihelion distance of 0.5 AU and an aphelion of 3.5 AU.? What is the spacecraft’s orbital period?

The period would be about 2.828 years.

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The spacecraft's orbital period can be calculated using Kepler's third law of planetary motion. The formula is T^2 = (4π^2 * a^3) / (G * M), where T is the orbital period, a is the semi-major axis (which is the average of the perihelion and aphelion distances), G is the gravitational constant, and M is the mass of the sun. Given the perihelion distance (0.5 AU) and aphelion distance (3.5 AU), the semi-major axis is (0.5 + 3.5) / 2 = 2 AU. With the values of G and M, which are constants, you can calculate the orbital period using the formula.

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When evaluating a one-sided limit, you need to be careful when a quantity is approaching zero since its sign is different depending on which way it is approaching zero from. Let us look at some examples.

When evaluating a one-sided limit, you need to be careful when a quantity is approaching zero since its sign is different depending on which way it is approaching zero from. Let us look at some examples.

When evaluating a one-sided limit, you need to be careful when a quantity is approaching zero since its sign is different depending on which way it is approaching zero from. Let us look at some examples.

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