High 1 physics does the radius of the satellite increase from orbit 1 to orbit 2? ）

That is true. The satellite accelerates at the Q point of the 1 orbit, at this moment, the tangential velocity of the satellite at the Q point increases, according to Newton's second law, the centripetal force is no longer enough to bind the satellite, so the satellite will undergo centrifugal phenomena and enter the 2 orbit.

When the satellite is in orbit 2, through force analysis, the velocity is always in the tangential direction, and the gravitational force is always directed to the center of the circle (the center of the earth), so the satellite speed is getting slower and slower, and when it reaches point p, it is the lowest speed of the satellite in orbit 2. As the satellite approaches the Earth after point p, the speed of the satellite increases, and when it returns to point Q, the satellite has the maximum speed in orbit 2. So the 2 orbit is elliptical, and the satellite moves on the ellipse.

The satellite adjusts its attitude and ignition at point P in orbit 2, and accelerates again so that the speed of the satellite is equal to the speed of the centripetal force required in orbit 3, and then the satellite enters orbit 3 at point P and moves in a uniform circular motion.

Yes. Circles are special ellipses. The semi-major axis of 2 is greater than the radius of 1, so it can be understood that the radius of the satellite has increased from orbit 1 to orbit 2.

Notice that in the process of this series, the rocket has been igniting and accelerating, and the conservation of energy knows, right? This shows that the energy of the rocket has been increasing, so why is the speed of orbit 3 smaller than that of orbit 1? Because the potential energy is also changing, since the kinetic energy is decreasing, the potential energy must be increasing, and it is increasing faster than the kinetic energy, so the total energy of the rocket and the earth's system is increasing.

The second orbit is an elliptical orbit, and its orbital radius changes continuously over the [a-c,a+c] interval with time.

It can be considered that it has increased, and this kind of topic memorizes the skill: the farther away the satellite, the slower.

From low orbit to high orbit is to overcome gravitational force to do work, so there needs to be a force to do positive work on the object, and the work done on the satellite is realized by jet, in the low orbit to move to the high orbit, so there must be an external force to do positive work on it, and doing positive work on it will make his kinetic energy increase and the speed will increase, so he will start to do centrifugal motion;

However, in the process of centrifugation, it is necessary to overcome the gravitational force to do work, so the speed will become smaller, and it is impossible to change the orbit from the circular orbit to the high orbit after only one orbit change, but only to become an elliptical orbit, to become a high orbit, it is necessary to change the orbit again from the apogee, and at the apogee, the speed of the operation is the smallest, and then the orbit change repeats the process mentioned above.

Analyzed from an energy point of view

Estimate: The mass of the artificial satellite is 2 tons, the original orbit radius is km, and the orbit is now changed to 349 km. The increase in the gravitational potential energy of the satellite is (assuming that there is no change in the gravitational acceleration value in this process and the value is 10 m/s2) and the decrease in the kinetic energy of the satellite in this process is (gravitational constant g = N·m 2 kg 2, Earth mass m = kg).

From the above estimates, it can be seen that the gravitational potential energy increase is much greater than the kinetic energy reduction in the process of orbit change (from low orbit to high orbit).

v= (gm r) indicates the relationship between the radius of the orbit and the velocity of the orbit, which is a static relation. The satellite operates normally in a circular orbit, the full gravitational force provides the centripetal force of flight (gravity is equal to the centripetal force), and the satellite is in equilibrium.

If it is considered that the speed required for the high orbit is small and the speed is slowed down, the Earth's gravitational force will be greater than the required centripetal force due to the constant r, and the satellite will "fly" towards the Earth. Therefore, adjust the attitude and accelerate briefly to make the satellite "fly high". As the altitude of the satellite increases, the kinetic energy changes into potential energy, and the velocity decreases.

When the predetermined orbital altitude is reached, the attitude of the satellite is adjusted again and the speed is controlled to complete the orbit change operation.

1.From low orbit to high orbit, overcome gravity to do work, accelerate so that the speed on the original orbit increases, the gravitational force is less than the centripetal force, do centrifugal motion, in order to move to a larger radius of orbit.

2.The formula for the centripetal force is provided according to the external gravitational force: gmm r 2 = mv 2 r gets: v = gm r under the root number, the larger r the smaller the velocity.

Why does the higher the orbit of a satellite, the greater the launch speed?

Because the higher the orbit of a satellite, the greater its mechanical energy.

Why do different geostationary satellites have the same orbital altitude?

Because the angular velocity of a geostationary satellite is constant, the angular velocity is constant, and the height is also constant.

The orbital altitude is the distance from the satellite to the surface of the central celestial body, but there are mountains and craters on the surface, why is it the same?

Because I think of the earth as a sphere.

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.

Option A The gravitational acceleration near the Earth's surface is a square multiple of k of the centripetal acceleration of the geostationary satellite.

The satellite can move in a circular motion around the moon must have centripetal force, in this problem, there is the gravitational force between the satellite and the moon to provide centripetal force, according to the centripetal force formula f (to) = m (guard) v square r, where r is the radius of circular motion, according to the figure, it can be found that the radius of motion of the three orbits is different, and the other items (gravitational force, mass, etc.) are the same, so the speed must be different, if I choose I will choose b, the reason is similar to the above, the mechanical energy is different from the p point, The velocity of point P is different each time, but the height is the same. As for gravitation, of course, it becomes, this is an elliptical orbit, and the distance from the moon at different points is different Do you understand?

Select B. It's because the speed is different, the track will be different.