Orbital Maneuver: Design an Elliptical Orbit with e=0.20 and Altitude 700 km?

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In summary, an orbital maneuver is a process of changing the trajectory of an object in space to achieve a desired orbit or alter its current orbit. An elliptical orbit is a type of orbit where the object follows an elliptical path around the focus, with a varying distance between the object and the focus. The value of e, or eccentricity, in an elliptical orbit represents how elongated the orbit is, with a value of 0.20 indicating a slightly elongated orbit. The altitude of an orbit refers to the distance between the object and the Earth's surface at its closest point, and in this scenario, the altitude is 700 km. To design an elliptical orbit with e=0.20 and altitude 700 km
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ExoP
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Hi!

I need help with a problem regarding orbital maneuvre. The question is:
You're doing a first-order analysis on a new satellite in an elliptical orbit with eccentricity e=0.20 and altitude 700 km. Can you design the orbit so that no maneuvers are necessary to maintain it?

Where should I begin? I know that it is a polar orbit since the altitude is 700 km, and the inclination is then 90 degrees. J2 is approximately 10^-3

Thanks!
 
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What is an orbital maneuver?

An orbital maneuver is a process of changing the trajectory of an object in space, typically a spacecraft, to achieve a desired orbit or alter its current orbit.

What is an elliptical orbit?

An elliptical orbit is a type of orbit in which the object follows an elliptical path around the focus of its orbit. This means that the distance between the object and the focus will vary at different points along the orbit.

What does e=0.20 mean in an elliptical orbit?

The value of e, or eccentricity, in an elliptical orbit represents how elongated the orbit is. A value of 0.20 means that the orbit is slightly elongated, with a distance between its closest and farthest points being 0.20 times the length of the semi-major axis.

What is the altitude of an orbit?

The altitude of an orbit refers to the distance between the object and the Earth's surface at its closest point, also known as perigee. In this scenario, the altitude is 700 km.

How is an elliptical orbit with e=0.20 and altitude 700 km designed?

An elliptical orbit with these specific parameters can be designed using mathematical equations and computer simulations. It would involve carefully calculating the object's velocity and direction of thrust at different points in the orbit to achieve the desired trajectory. This process requires precise calculations and careful planning to ensure the object maintains its desired orbit.

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