*To estimate the semi-major axis (a) from the orbital period (T) in seconds for a circular orbit, you can use the formula: a ≈ (G * T^2 / (4π^2))^1/3, where ‘G’ is the gravitational constant (approximately 6.674 × 10^-11 N(m/kg)^2) and ‘π’ is approximately 3.14159. This formula assumes a two-body system and circular orbit for simplicity.*

## Period to Semi-Major Axis Calculator

Here’s a table with sample period-to-semi-major-axis conversions:

Orbital Period (T) | Semi-Major Axis (a) |
---|---|

1 hour | 23,930,994 meters |

1 day | 42,164,846 meters |

1 month | 102,828,520 meters |

1 year (365 days) | 214,464,047 meters |

## FAQs

**How do you convert orbital period to semi-major axis?** The relationship between orbital period (T) and semi-major axis (a) depends on the mass of the central body (usually a planet or star) and follows Kepler’s Third Law: T^2 ∝ a^3. So, to convert period to semi-major axis, you can use the formula a ≈ (T^2)^(1/3).

**What is period and semi-major axis?** Period (T) is the time it takes for an object to complete one orbit around another object (e.g., a planet orbiting the Sun). Semi-major axis (a) is half of the longest diameter of the elliptical orbit, which determines the size of the orbit.

**What is the relationship between period T and the semi-major axis?** The relationship is governed by Kepler’s Third Law: T^2 ∝ a^3. This means that the square of the orbital period is proportional to the cube of the semi-major axis.

**What is the semi-major axis of orbit?** The semi-major axis (a) of an orbit is the half of the major axis, which is the longest diameter of the elliptical orbit. It represents the average distance between the two objects in an elliptical orbit.

**How do you calculate the semi-major axis of a binary star system?** To calculate the semi-major axis of a binary star system, you would typically need observational data, such as the stars’ orbital periods and their masses. Then, you can use Kepler’s Third Law (T^2 ∝ a^3) and rearrange it to solve for ‘a’ using the known values of T and the masses of the stars.

**How do you find the semi-minor axis?** The semi-minor axis (b) of an ellipse can be calculated using the formula: b = a * √(1 – e^2), where ‘a’ is the semi-major axis and ‘e’ is the eccentricity of the ellipse.

**What is the formula for period?** The formula for the period (T) of an object in orbit is given by Kepler’s Third Law: T^2 = (4π^2 * a^3) / (G * M), where ‘a’ is the semi-major axis, ‘G’ is the gravitational constant, and ‘M’ is the mass of the central body.

**Is semi-major axis equal to radius?** No, the semi-major axis is not equal to the radius. The semi-major axis represents half of the longest diameter of an elliptical orbit, while the radius typically refers to the distance from the center of a circular orbit to the orbiting object.

**What is the difference between the semi-major axis and the minor axis?** The semi-major axis (a) is the half of the longest diameter of an elliptical orbit, while the semi-minor axis (b) is the half of the shortest diameter, perpendicular to the semi-major axis. The major axis is longer than the minor axis in an ellipse.

**What is the semi-major axis of low Earth orbit?** The semi-major axis of a typical low Earth orbit (LEO) is approximately 6,378 kilometers, which is roughly the average radius of the Earth.

**What is the semi-major and minor axis of an ellipse?** The semi-major axis (a) is half of the longest diameter of an ellipse, while the semi-minor axis (b) is half of the shortest diameter, perpendicular to the semi-major axis.

**How to find semi-major axis given perihelion and eccentricity?** You can calculate the semi-major axis (a) of an elliptical orbit using the perihelion distance (r_peri) and the eccentricity (e) with the formula: a = r_peri / (1 – e).

**What determines semi-major axis?** The semi-major axis of an orbit is primarily determined by the size and shape of the orbit, which is influenced by the gravitational force between the two objects in orbit, as described by Kepler’s laws of planetary motion.

**What is the ratio of semi-major and semi-minor axis called?** The ratio of the semi-major axis (a) to the semi-minor axis (b) in an ellipse is called the eccentricity (e). It measures how “stretched out” or elongated the ellipse is.

**What is the semi-minor axis in astronomy?** The semi-minor axis (b) in astronomy is half of the shortest diameter of an elliptical orbit or the minor axis of an ellipse. It is perpendicular to the semi-major axis (a).

**How do you calculate period and frequency?** Period (T) and frequency (f) are inversely related. You can calculate the period from frequency using the formula: T = 1 / f, and you can calculate frequency from period using: f = 1 / T.

**How do you calculate period in precalculus?** The calculation of period depends on the specific context. In precalculus, you may calculate the period of functions like trigonometric functions or periodic waves using mathematical equations specific to those functions.

**What is the period of an orbit?** The period of an orbit is the time it takes for an object to complete one full revolution around another object. For example, the period of the Earth’s orbit around the Sun is approximately 365.25 days.

**Is the period of the orbit 1 year?** Yes, the period of Earth’s orbit around the Sun is approximately 1 year, which is why we use a year as the unit of time for this orbital period.

**How do you find the distance from an orbital period on a calculator?** To find the distance from an orbital period, you would need additional information such as the mass of the central body and the gravitational constant. You can then use the formula for the semi-major axis (T^2 = (4π^2 * a^3) / (G * M)) to calculate the distance.

**How do you calculate the time period of a geostationary satellite?** The time period of a geostationary satellite can be calculated using Kepler’s Third Law and is typically approximately 24 hours. The formula is T = 2π√(a^3 / GM), where ‘a’ is the semi-major axis, ‘G’ is the gravitational constant, and ‘M’ is the mass of the Earth.

**What does the time period of a satellite in a circular orbit depend on?** The time period of a satellite in a circular orbit depends primarily on the mass of the central body (planet or star) and the radius of the orbit. It follows Kepler’s Third Law, T^2 ∝ r^3.

**Is semi-major axis the same as distance from the sun?** No, the semi-major axis is not the same as the distance from the Sun. The semi-major axis represents the size of an elliptical orbit, while the distance from the Sun to a celestial body can vary along its orbit.

**Is the semi-major axis A or B?** The semi-major axis is typically denoted as ‘a,’ while the semi-minor axis is denoted as ‘b’ in an ellipse.

**Is semi-major axis the same as altitude?** No, the semi-major axis is not the same as altitude. The semi-major axis is a measure of the size of an orbit, while altitude typically refers to the distance above the surface of a celestial body (e.g., Earth).

**Is the semi-major axis constant?** In most celestial orbits, the semi-major axis is not constant. It can change over time due to gravitational interactions with other celestial bodies.

**Can semi-major axis be negative?** The semi-major axis is a positive value representing the average distance of an orbit. It is not typically negative.

**Is semi-major axis the same as apogee?** No, the semi-major axis is not the same as apogee. The semi-major axis is a fundamental parameter that defines the size and shape of an elliptical orbit, while apogee is the point in an orbit farthest from the central body.

**What is the relationship between semi-major axis, semi-minor axis, and eccentricity?** The relationship between semi-major axis (a), semi-minor axis (b), and eccentricity (e) in an ellipse is given by: a = b / √(1 – e^2).

**What is the relation between minor and major axis?** The major axis is the longest diameter of an ellipse, while the minor axis is the shortest diameter, perpendicular to the major axis. They are related by the semi-major axis (a) and semi-minor axis (b).

**How long is Earth’s semi-major axis?** Earth’s semi-major axis, which represents the average distance from the Earth to the Sun in its elliptical orbit, is approximately 149.6 million kilometers.

**What is the lowest stable Earth orbit?** The lowest stable Earth orbit is the Low Earth Orbit (LEO), which typically starts at an altitude of around 160 kilometers (100 miles) and extends up to about 2,000 kilometers (1,242 miles) above the Earth’s surface.

**What is the radius of the semi-major axis of the Earth?** The radius of the semi-major axis of the Earth is approximately 6,378 kilometers, which is equal to the Earth’s mean radius.

**Is the semi-major axis of an orbit half the major axis?** Yes, the semi-major axis of an orbit is indeed half of the major axis, which is the longest diameter of the elliptical orbit.

**What is the formula for the semi-major axis of an ellipse?** The formula for the semi-major axis (a) of an ellipse is half of the major axis and is typically denoted as ‘a’ in mathematical equations.

**What is the semi-major axis of an ellipse quizlet?** The semi-major axis of an ellipse represents half of the longest diameter of the ellipse and is a fundamental parameter in describing its size and shape.

**What is the semi-major axis of an ellipse denoted by?** The semi-major axis of an ellipse is typically denoted by the letter ‘a’ in mathematical notation.

**What is the formula for semi-major axis and eccentricity?** The formula relating the semi-major axis (a) and eccentricity (e) of an ellipse is: a = b / √(1 – e^2), where ‘b’ is the semi-minor axis.

**How to calculate semi-major axis with perihelion and aphelion?** You can calculate the semi-major axis (a) of an elliptical orbit using the perihelion distance (r_peri) and the aphelion distance (r_aphelion) with the formula: a = (r_peri + r_aphelion) / 2.

**How do you find the semi-major axis with orbital velocity?** To find the semi-major axis (a) with orbital velocity (v) and the gravitational constant (G), you can use the formula: a = (G * M) / (4π^2 * v^2), where ‘M’ is the mass of the central body.

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