Physics 53Satellite Motion—You know, it's at times likes this when I'm stuck in a Vogon airlock with a man from Betelgeuse, about to die from asphyxiation in deep space, that I wish I had listened to what my mother told me when I was young.— Why, what did she say?—I don't know. I didn't listen.— Hitchhiker's Guide to the GalaxyRadial and angular motionWe will be concerned here with the orbiting motion of a satellite, such as a planet around the sun, or the moon around the earth. We neglect the effects of all other bodies.We will assume that the satellite's mass (m) is much smaller than that (M) of the body it moves around. Both bodies actually orbit around the CM of the system, but M moves only a small amount because the CM is so close to it. We ignore this motion as an approximation, and take the center of M to be the origin of our coordinate system.For a system with two masses of comparable size, such as a double star, obviously this is a bad approximation and one must analyze the motion of both bodies around the CM.Because gravity (a central and conservative force) is the only force doing work:The total mechanical energy E of the system is conserved.The gravitational force acts along the line between the two bodies, so there is no torque about the origin. This means that:The total angular momentum L of the system about the origin is conserved.This is still true if the CM is taken as origin even when we take account of the motion of both bodies.We will find that the nature of the trajectory is determined by the values of these two conserved quantities.The velocity of the satellite has in general two components, one parallel and one perpendicular to the position vector r of the satellite. We call these the radial and tangential velocities and write v = vr+ v⊥.The kinetic energy then breaks into two parts:PHY 53! 1! Satellite MotionK =12mvr2+12mv⊥2.The magnitude of the angular momentum of the satellite is given by L = mrv⊥so we can solve for v⊥ in terms of L and write the kinetic energy as:! K =12mvr2+L22mr2.!Now we add the potential energy to get the total energy:! E =12mvr2+L22mr2− GMmr.This expression is essentially one-dimensional, since the only variables in it are the speed along the radial line between the two bodies and their distance apart along that line. The second term in the formula is actually the tangential part of the kinetic energy, but since L is constant we have been able to express it a function only of the distance r.Because the energy is formally one-dimensional, we can use the methods given earlier (see Energy 2) to determine turning points in the radial motion. This will give us the distances of closest approach and furthest recession of the satellite.The satellite is not actually at rest at these turning points. Its velocity component parallel to r is zero, but it will still have a velocity component perpendicular to r.We define an effective potential energy by combining the terms that depend only on r: Ueff(r) =L22mr2− GMmr,so that E =12mvr2+ Ueff.At points where the total energy E is equal to Ueff the kinetic energy of radial motion along the line between the bodies is (instantaneously) zero. Those are the turning points in the radial motion.We see that as r → ∞, Ueff→ 0. This means that if the total energy E is positive (or zero) there is no turning point for large values of r, hence the motion is unbound. But if E is negative there are two turning points and we have bound orbits.PHY 53! 2! Satellite MotionTypes of orbitsShown is a typical curve for Ueff, with three different possible values of the total energy E.For positive energy E1 there is only one turning point, at r0. If the system has this energy, m approaches M to distance r0 and then moves away, never to return. The motion is unbound; the trajectory can be shown to be a hyperbola passing around M. Comets that appear only once in our solar system are of this type.For negative energy E2 there are turning points at both r1 and r2. The distance between m and M varies back and forth between these values. The motion is bound, and the trajectory can be shown to be an ellipse with M at one focus. (Kepler’s 1st law.)For negative energy E3 the two turning points coincide and the ellipse becomes a circle of radius r3.There is a simple rule about the nature of the trajectories:Positive (or zero) total energy gives unbound motion, while negative total energy gives bound motion.This dichotomy between positive and negative total energy arises from our having chosen potential energy to be zero when the objects are infinitely far apart, so at finite distances it is negative. Ueff E1 E2 E3 r r2 r3 r1 r0PHY 53! 3! Satellite MotionElliptical orbitsShown is a typical elliptical orbit.The turning points rp and ra are the distances of closest approach and furthest recession. These points are usually denoted by the Greek prefixes peri (“around”) and apo (“from”). Thus a planet’s point of closest approach to the sun is called its perihelion, and its point of furthest recession is its aphelion (helios is sun in Greek).For satellites around the earth, the corresponding names are perigee and apogee. We find the turning points by setting Ueff= E, remembering that E is negative.! L22mr2− GMmr= E, or r2+GΜmEr −L22mE= 0The roots of this equation are rp and ra, so it must be the same as! (r − rp)(r − ra) = 0, or r2− (rp+ ra)r + rpra= 0Comparing the coefficients in these different two forms, we see that! rp+ ra= −GMmE, rpra= −L22mEThe turning points are related to the axes of the ellipse by! rp+ ra= 2a, rpra= b2,so we can write the energy and angular momentum of the orbit in terms of a and b:Elliptical orbit relationsEnergy: E = −GMm2aAngular momentum: L2= −2mEb2The first of these is an important formula, showing that the energy depends only on the length of the orbit 2a. The second shows that L is proportional to b, so more eccentric orbits (smaller b) correspond to lower L. Maximum L occurs for a circular orbit, b = a. r a b ra rpPHY 53! 4! Satellite MotionKepler's lawsIn our analysis we did not prove that the orbits are ellipses (Kepler's 1st law), but it can be shown. We will now prove the other two laws.Proof of the 1st law requires an extensive use of calculus, so we will not give it here.Shown is an elliptical orbit and the position of the satellite at two times differing by dt. The satellite moves a distance