Does the speed of a satellite change in elliptical orbit

The speed at which a satellite travels in an elliptical orbit varies. At perigee, the centripetal force f=mv 2 r1 required is greater than the centripetal force f=gmm r1 provided to do centrifugal motion. The centripetal force required by the satellite f=mv2 r2 is less than the centripetal force provided f=gmm r2 2 to do centripetal motion.

The velocity of the gravitational force near the apogee gradually increases, and the velocity of the perigee is the largest. Then move away along the elliptical orbit and the velocity decreases, and this will continue and so on regardless of the air resistance.

Since the speed of a circular orbit is constant, it is naturally impossible for an elliptical orbit to have a constant velocity, otherwise there will be multiple orbits in the same velocity state

The energy of the elliptical orbit is conserved, the velocity near perigee increases, and the velocity at apogee decreases.

When the orbit change accelerates, in order to increase the speed with the orbital radius unchanged, the eccentricity needs to increase at the perigee and decrease the eccentricity at the apogee.

That is, the perigee accelerates, and the orbit will gradually become flattened, pulling up the apogee radius; The apogee accelerates, and the orbit gradually becomes circular, which also raises the perigee radius. When the velocity is just enough to reach a circular orbit, it is a circular orbit with apogee as the radius.

Of course, it depends on how big the acceleration is, if you add too much, you can't keep an elliptical orbit, and you can't come back when you fly out into a hyperbolic orbit with a centrifugality greater than 1

The velocity of satellites in elliptical orbits is basically different, and the centripetal force is also different, but the centripetal force is equal to the gravitational force of the earth at each moment. The circular motion of the satellite is called orbital velocity, that is, the first cosmic velocity, and the velocity between the first cosmic velocity and the second cosmic velocity orbiting the earth is elliptical, and beyond the second velocity, it can escape the gravitational pull of the earth.

There is also no centrifugal force, only centripetal force, and centrifugal force is only a hypothetical force embodied in the centripetal force. For the intersection of elliptical and circular orbits that you are talking about, the velocity is different.

Because in addition to the centrifugal force generated by the earth's gravitational pull and the earth's rotation, artificial satellites are also affected by tidal forces. The periodic effect of tidal forces will cause the perigee and apogee periodic changes of artificial satellites. This periodic change causes the artificial satellite to suddenly accelerate into an elliptical orbit due to the increase in the earth's gravitational attraction when it approaches the perigee.

Because the acceleration is slow, it can only be accelerated slowly.

Let the distance between the center of gravity of the two objects in the last state be R1, and the distance between the center of gravity of the two objects in the last state is R2.

The mass of the Earth is m, and the mass of an artificial satellite is m; According to the conservation of mechanical energy, when the distance is r1 and r2, the velocity of the artificial satellite is v1 and v2 and Kepler's second law gives the simultaneous equation of v1r1=v2r2

The resultant external moment is zero, the angular momentum is conserved, r1*m*v1=r2*m*v2

1.Energy is conserved, and gravitational potential energy and kinetic energy are converted into each other.

The velocity decrease is the conversion of kinetic energy into gravitational potential energy and vice versa.

You know 2After centrifugation, because the force and velocity are not perpendicular, they are actually obtuse angles, so that the force can be decomposed into a and velocity.

degrees of opposing force, so that the object slows down while another.

The components make the object perpendicular to the original velocity.

produces a velocity, which in the process of object motion.

The obtuse angle is increasing, and the velocity of the object is increasing.

small, and the actual velocity at this time can be broken down into one.

Horizontal velocity, a vertical velocity, though is subjected.

The change in force but speed is still predictable.

The vertical velocity is decreasing, the horizontal velocity is increasing, and the vertical velocity is increasing.

The velocity is decreasing, and when the vertical velocity is 0, it is an ellipse.

farthest point. The Earth is a focal point of the ellipse.

3.When changing from a circle to an ellipse is from a low orbit to a variable orbit.

The principle of centrifugal motion is used, so it is necessary to accelerate.

Changing from an ellipse to a circle is when the orbit changes to a high orbit.

The kinetic energy is converted into gravitational potential energy, as previously analyzed.

At this point, the velocity of the highest point of the ellipse is already very small, so small.

It is less than the speed of maintaining a high orbit, so there is only acceleration.

in order to become a high track.

??It is not possible to change to high orbit at perigee, because the velocity is greatest at perigee, while high orbit is a decrease in velocity, and acceleration at apogee is actually an angle that changes the velocity, changing the satellite from an elliptical orbit to a circular orbit. Acceleration or deceleration is inevitably associated with changing the direction (angle) of the speed.

At a certain point of acceleration, the linear velocity of this point increases, and the required centripetal force increases, but the centripetal force is provided by the gravitational force and remains unchanged for the time being, so the centripetal force is insufficient, and the centrifugal motion begins.

During centrifugation, the gravitational force decreases and the centripetal force decreases. And in this process, gravitational force does negative work (the satellite moves away from the planet), so the linear velocity decreases.

When the farthest point (apogee) is reached, the linear velocity is small and the centripetal force is large, then the centripetal motion begins, the gravitational force increases, the linear velocity increases, until it returns to the original acceleration point (this point is the perigee), so that it becomes an elliptical orbit ......

The team will answer for you.

Circular orbit and elliptical orbit have a unified orbital energy formula e=-gmm 2a, (gravitational potential energy + kinetic energy), at apogee, the energy of the circular orbit is greater than that of elliptical orbit, so it should be accelerated. (with a formula explanation), the same is true for perigee.

At perigee, the corresponding circular orbit energy is less than that of the elliptical orbit, and further acceleration will only make the elliptical orbit longer on the semi-major axis.

Conversely, it is variable at any point in the circular orbit. After acceleration, it becomes an ellipse with a semi-major axis greater than the radius, and the orbit change point is perigee. After deceleration, it becomes an ellipse with a semi-major axis smaller than the radius, and the orbit change point is the apogee.

Circular orbits and elliptical orbits have a uniform orbital energy formula e=-gmm 2a, (gravitational potential dispersion energy.

kinetic energy), at apogee, the energy of the circular orbit is greater than that of the elliptical orbit, so it should be accelerated. (with a formula explanation), the same is true for perigee.

At perigee, the energy of the corresponding circular orbit is small and the elliptical orbit is accelerated, and then acceleration will only make the elliptical orbit half major axis.

Longer. Conversely, it is variable at any point in the circular orbit. After acceleration, it becomes an ellipse with a semi-major axis larger than the radius, and the orbit point is perigee. After deceleration, it becomes an ellipse with a semi-major axis smaller than the radius, and the orbit change point is the apogee.

The satellite is moving from low orbit to high orbit, and the satellite is doing centrifugal motion.

When the satellite moves in a uniform circular motion in its original orbit, the gravitational force is equal to the required centripetal force, i.e., f=mv 2 r

To change the orbit: the gravitational force does not change, only the velocity.

Acceleration: The centripetal force mv 2 r required for the satellite to make a uniform circular motion in the original orbit

The gravitational force f that actually points to the center of the circle does not change.

Therefore, there is: f gall penalty book nuclear aunt cha too advocate coffee <

mv^2/r

The satellites will be centrifuged into high orbits.

Counter-Knowledge: When slowing down: F

It hasn't changed, but. mv^2/r

Smaller, FMV 2 R

Satellites are close to low orbit.