The radius of an artificial satellite orbiting an elliptical orbit

If you understand what curvature is, then you know everything.

If you ask this question, you may still be a junior or high school student. Also: not the radius of the inscribed circle, but the maximum radius of the inscribed circle.

In fact, the radius of the largest inscribed circle and the smallest inscribed circle and a half are very identical.

You can use either as the radius of the track.

Summary. t=2 (a 3 gm), a is the major semiaxis of the ellipse.

The simplest way is to use Kepler's third law to calculate the period of circular motion first, and then the period of elliptical motion.

How to calculate the radius r of a satellite in an elliptical orbit during the operation of a celestial body.

t=2 (a 3 gm), a is the major semiaxis of the ellipse. The simplest is to use Kepler's third law to calculate the period of circular motion first, and then calculate the period of elliptical circular motion.

Can it be understood as the distance from the satellite to the central celestial body?

OK. If the wide Nian fruit r is regarded as the distance between the satellite and the central celestial body, then at the intersection of the elliptical orbit and the circular orbit, it is not coincidental that the velocity is not equal, but the actual slip is not equal, then what does that r mean?

r should have added the radius of the celestial body.

C. Test Question Analysis: The orbit of a flying object flying around the earth is generally an ellipse, and the farthest from the earth on the ellipse is apogee, and the closest is perigee. When the satellite is at perigee, the altitude from the earth is the smallest, the gravitational potential energy is the smallest, the speed is the fastest, and the kinetic energy is the largest. At apogee, the altitude above the Earth is maximum, the gravitational potential energy is maximum, the velocity is the slowest, and the kinetic energy is minimal.

When the satellite moves from apogee to perigee, the mass of the satellite remains unchanged, the altitude decreases, and the gravitational potential energy decreases. But the speed of motion increases, the kinetic energy increases, and the decreasing gravitational potential energy is equal to the increased kinetic energy, that is to say, in the process of energy conversion, the total amount of mechanical energy remains the same, so choose c

There are two cases: according to Kepler's third law r 3 t 2 = constant (r: the semi-major axis of the orbit, for circular motion r is the radius of the circle, t: the revolution period) can be analyzed.

1.If it is an accelerated orbit change at apogee, the period will become larger, which generally occurs during launch;

2.If it is a perigee deceleration and orbit change, the cycle will become smaller, which generally occurs in the ** process.

It depends on whether the satellite changes its orbit at perigee or at apogee, according to the gravitational formula, the farther away from the earth is the circumferential orbit, the greater the period.

If the orbit changes at perigee, the period of motion will become smaller;

If the orbit is changed at apogee, the period becomes larger.

If the elliptical orbit is in a circular orbit, it changes from the near orbit to the far orbit, accelerates in the near orbit, and the speed of the circular motion after the orbit change decreases compared with before.

If the circular orbit is in the elliptical orbit, it changes from the far orbit to the near orbit, and the speed of the circular motion after the orbit change increases compared with before.

Yes, the reason why the orbit of the mallet is elliptical is because its DAO velocity is not perpendicular to its running version of the sagittal diameter (the line between the satellite and the center of the earth).

Not all satellite orbits are elliptical, and some satellites for special missions (such as reconnaissance satellites, geosynchronous satellites) have circular orbits. For elliptical orbits, the variable orbit becomes a circular orbit with appropriate acceleration at its apogee.

Not all celestial orbits are elliptical.