- #1
Eagle120
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Homework Statement
Plane shange a satellite's orientation from an inclination of 28.5 degrees to 0 degree
Magnitude velocity is in both orbits is 7.726 km/sec
Determine magnitude and direction needed for velocity change
Calculating Velocity Change to Change Satellite Orientation
- Thread starter Eagle120
- Start date
In summary, the formula for calculating velocity change to change satellite orientation is Δv = (2*π*R*Δθ) / (T*sqrt(1-e^2)), where Δv is the required velocity change, R is the radius of the orbit, Δθ is the desired change in orientation, T is the orbital period, and e is the eccentricity of the orbit. The orbital period of a satellite can be determined using the formula T = 2*π*sqrt(a^3/GM), where a is the semi-major axis of the orbit and GM is the standard gravitational parameter of the central body. The standard gravitational parameter, denoted by GM, is a constant that represents the product of the gravitational constant
Plane shange a satellite's orientation from an inclination of 28.5 degrees to 0 degree
Magnitude velocity is in both orbits is 7.726 km/sec
Determine magnitude and direction needed for velocity change
- #2
tiny-tim
Science Advisor
Homework Helper
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Welcome to PF!
Hi Eagle120! Welcome to PF!
Show us what you've tried, and where you're stuck, and then we'll know how to help!
Hi Eagle120! Welcome to PF!
Show us what you've tried, and where you're stuck, and then we'll know how to help!
What is the formula for calculating velocity change to change satellite orientation?
The formula for calculating velocity change to change satellite orientation is Δv = (2*π*R*Δθ) / (T*sqrt(1-e^2)), where Δv is the required velocity change, R is the radius of the orbit, Δθ is the desired change in orientation, T is the orbital period, and e is the eccentricity of the orbit.
How do I determine the orbital period of a satellite?
The orbital period of a satellite can be determined using the formula T = 2*π*sqrt(a^3/GM), where a is the semi-major axis of the orbit and GM is the standard gravitational parameter of the central body (usually a planet or moon). The semi-major axis can be calculated by adding the altitude of the satellite to the radius of the central body.
What is the standard gravitational parameter?
The standard gravitational parameter, denoted by GM, is a constant that represents the product of the gravitational constant (G) and the mass of the central body (M). It is used in orbital mechanics to calculate various orbital parameters, including the orbital period and the velocity of a satellite.
How do I calculate the required velocity change for a specific orientation change?
To calculate the required velocity change, first determine the orbital period of the satellite using the formula T = 2*π*sqrt(a^3/GM). Then, use the formula Δv = (2*π*R*Δθ) / (T*sqrt(1-e^2)), where R is the radius of the orbit, Δθ is the desired change in orientation, and e is the eccentricity of the orbit.
What is eccentricity and how does it affect the required velocity change?
Eccentricity is a measure of how elliptical an orbit is. It is represented by the letter e and ranges from 0 (circular orbit) to 1 (parabolic orbit). The higher the eccentricity, the greater the required velocity change to change the satellite's orientation. This is because a more elliptical orbit has a larger difference between the fastest and slowest parts of the orbit, requiring a greater change in velocity to change the orientation.
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