2016年8月8日 · Launch azimuth is constrained at the Cape between 35 and 120 degrees due to land mass overflight restrictions. All launches from Cape Canaveral are therefore restricted in inclination between 28.5 and 59 degrees." So what I don't understand is how the orbital inclination is calculated knowing the azimuth. $\endgroup$ –

2020年1月13日 · If the launch site was on the equator, it's not difficult to imagine that if you launch exactly due East, i.e. tangential to the target orbit, the orbital plane is coincident with the equatorial plane, so your orbital inclination equals the latitude of your launch location: 0 degrees. But as your launch location moves away from the equation ...

2019年8月15日 · Consider a transfer between two circular orbits of similar radius, the only difference being the inclination difference, $\alpha$. What's the minimal $\Delta v$ required to perform this transfer? Inclination change strategies I have considered so far: A single burn inclination change.

Yes, it is possible to determine the orbital inclination from the Longitude of the Ascending Node, and a position vector that is not the Ascending node or the Descending Node, because both the ascending node and your position are points in the orbital plane, and the vectors pointing to each from the body being orbited uniquely define that plane.

2017年4月13日 · ...or, "What is the inclination of a satellite that travels over Earth's equator?" Considering Earth's axial tilt is 23.4°, it's a significant difference - is the inclination calculated relative t...

2009年10月17日 · The Inclination based on the elliptic is the angle between the line between the (Earth's center of mass and Sun's center of mass) and the Sun's axis of rotation. The data enclosed says that Earth is N/A. Why? Does not the Inclination change or at least the angle changes due to the fixed nature of the tilt dynamics of the planets and the sun.

2020年7月21日 · $\begingroup$ @RossPresser You could burn elsewhere to raise the ascending/descending node, then do the inclination-change burn at the higher AN/DN, and do a final burn to return to the original orbital altitude. For large inclination changes when the AN/DN is low, this can be more efficient than just going straight for the inclination change ...

If you're going to a higher inclination than your launch latitude (for example, going from Cape Canaveral at 28º to ISS at 51º), you'll want to do it as early as possible, while your horizontal velocity is minimal -- essentially immediately when you start your gravity turn. The velocity you start with from Earth's rotation is less than that ...

2021年1月28日 · Consider a rocket launch from Kennedy, latitude 28.5 deg, to a target orbital inclination of 50.6 degrees for rendezvous with the ISS. The launch azimuth for this orbital inclination is roughly 45 deg north of due east. At T0, inertial velocity is roughly 400 m/s due east imparted by earth's rotation.

2024年2月12日 · "a" is desired inclination change "b" is optimum thrust direction. Blue vector is the thrust vector to achieve red orbit inclination "a" without affecting scalar velocity or apoapsis. Purple vector is the thrust vector at right angle to the green orbit needed to achieve desired new orbital inclination "a".