Exercises

- Demonstrate that if a particle moves in a central force field with zero angular momentum, so
that
, then the particle's trajectory lies
on a fixed straight line that passes through the origin. [Hint: Show that
.]
- Demonstrate that
is the magnitude of the angular momentum (per unit mass)
vector
. Here, and are plane polar coordinates.
- Consider a planet in a Keplerian elliptical orbit about the Sun. Let be the planet's position vector, relative to the Sun, and
let
be its angular momentum per unit mass. Demonstrate that the so-called
*eccentricity vector*, - Given the Sun's mean apparent radius seen from the Earth (), the Earth's mean apparent radius seen from the Moon (),
and the mean number of lunar revolutions in a year (), show that the ratio of the Sun's mean density to that of the Earth
is . (From Lamb 1923.)
- Prove that the orbital period of a satellite close to the surface of a spherical planet depends on the
mean density of the planet, but not on its size. Show that if the mean density is that of water then the period
is 3 h. 18 m. (From Lamb 1923.)
- Jupiter's satellite Ganymede has an orbital period of 7 d. 3 h. 43 m. and a mean orbital radius that is times the
mean radius of the planet. The Moon has an orbital period of 27 d. 7 h. 43 m. and a mean orbital radius that is times the Earth's
mean radius. Show that the ratio of Jupiter's mean density to that of the Earth is . (From Lamb 1923.)
- Halley's comet has an orbital eccentricity of and a perihelion
distance of 55,000,000 miles. Find the orbital period and the comet's speed at
perihelion and aphelion.
- Show that the velocity at any point on a Keplerian elliptical orbit can be resolved into
two constant components: a velocity
at right angles to the radius vector, and
a velocity
at right angles to the major axis. Here, is the mean orbital angular
velocity, the major radius, and the eccentricity. (From Lamb 1923.)
- The
*latus rectum*of a conic section is a chord that passes through a focus; it is perpendicular to the major axis (or the symmetry axis, in the case of a parabola or a hyperbola). Show that, for a body in a Keplerian orbit around the Sun, the maximum value of the radial speed occurs at the points where the latus rectum (associated with the non-empty focus, in the case of an ellipse) intersects the orbit, and that this maximum value is . Here, is the angular momentum per unit mass, the orbital eccentricity, and the perihelion distance. - A comet is observed a distance astronomical units from the Sun,
traveling at a speed that is times the Earth's mean orbital speed. Show that the orbit of the
comet is hyperbolic, parabolic, or elliptical, depending on whether the quantity
is
greater than, equal to, or less than 2, respectively. (Modified from Fowles and Cassiday 2005.)
- Consider a planet in an elliptical orbit of major radius and
eccentricity about the Sun. Suppose that the eccentricity of the orbit is small
(i.e., ), as is indeed the case for all of the planets. Demonstrate that, to first order in , the orbit can be approximated as a circle whose center is shifted a distance from
the Sun, and that the planet's angular motion appears uniform when
viewed from a point (called the equant) that is shifted a distance
from the Sun, in the same direction as the center of the circle.
[This theorem is the
basis of Ptolemy's model of planetary motion (Evans 1998).]
- How long (in days) does it take the Sun-Earth radius vector to
rotate through , starting at the perihelion point? How long does it take starting at the aphelion point? The period and eccentricity of the Earth's orbit are days, and , respectively.
- If is the Sun's ecliptic longitude, measured from the perigee (the point of closest approach
to the Earth), show that the Sun's apparent diameter is given by
- Show that the time-averaged apparent diameter of the Sun, as seen from a planet describing a low-eccentricity elliptical orbit,
is approximately equal to the apparent diameter when the planet's distance from the Sun equals the major radius of the orbit.
(From Lamb 1923.)
- Consider an asteroid orbiting the Sun. Demonstrate that, at fixed orbital energy, the
orbit that maximizes the orbital angular momentum is circular.
- Demonstrate that for a Keplerian orbit
where , , and are the elliptic anomaly, the true anomaly, and the eccentricity, respectively.
- Derive Equations (4.102)–(4.104).
- Derive Equations (4.105)–(4.107).
- A parabolic Keplerian orbit is specified by Equation (4.102), which can be written
*parabolic mean anomaly*. Here, is the solar mass, the perihelion distance, and the time of perihelion passage. Demonstrate that the preceding equation has the analytic solution - Consider a comet in an elliptical orbit about the Sun. Let and be Cartesian coordinates in the
orbital plane, such that corresponds to the Sun, and the -axis is
parallel to the orbital major axis. Demonstrate that
where is the orbital major radius, the eccentricity, and the eccentric anomaly.
- Consider a comet in a parabolic orbit about the Sun. Let and be Cartesian coordinates in the
orbital plane, such that corresponds to the Sun, and the -axis is
parallel to the orbital symmetry axis. Demonstrate that
where is the perihelion distance, and the parabolic anomaly.
- Consider a comet in an hyperbolic orbit about the Sun. Let and be Cartesian coordinates in the
orbital plane, such that corresponds to the Sun, and the -axis is
parallel to the orbital symmetry axis. Demonstrate that
where is the orbital major radius, the eccentricity, and the hyperbolic anomaly.
- Consider a comet in an elliptical orbit about the Sun.
If and are the radial distances from the Sun of two neighboring points, and , on the orbit, and
if is the length of the straight line joining these two points, prove that the time, , required for the comet to
move from to is
Here, and are the period and the major radius of the orbit, respectively.
- Consider a comet in a parabolic orbit about the Sun.
If and are the radial distances from the Sun of two neighboring points, and , on the orbit, and
if is the length of the straight line joining these two points, prove that the time required for the comet to
move from to is
- Consider a comet in a hyperbolic orbit about the Sun.
If and are the radial distances from the Sun of two neighboring points, and , on the orbit, and
if is the length of the straight line joining these two points, prove that the time, , required for the comet to
move from to is
Here, is major radius of the orbit, and is the period of an elliptical orbit with the same major radius. (From Smart 1951.)
- A comet is in a parabolic orbit that lies in the plane of the Earth's
orbit. Regarding the Earth's orbit as a circle of radius , show that the points
at which the comet intersects the Earth's orbit are given by
- The orbit of a comet around the Sun is a hyperbola of eccentricity , lying in the ecliptic plane, whose
least distance from the Sun is times the radius of the Earth's orbit (which is approximated as a circle).
Prove that the time that the comet remains within the Earth's orbit is
, where
, and is the periodic time of a planet describing an elliptic
orbit whose major radius is equal to that of the hyperbolic orbit. (From Smart 1951.)
- Consider a comet in a hyperbolic orbit focused on the Sun. The
*impact parameter*, is defined as the the distance of closest approach in the absence of any gravitational attraction between the comet and the Sun. Demonstrate that , where is the comet's angular momentum per unit mass, and its energy per unit mass. Show that the relationship between the impact parameter, , and the true distance of closest approach, , is - Spectroscopic analysis has revealed that Spica is a double star whose components revolve around one another with a period of 4.1 days, the
greatest relative orbital velocity being 36 miles per second. Show that the mean distance between the components
of the star is
miles, and that the total mass of the system is
that of the Sun. The mean distance of the Earth from the Sun is million miles. (From Lamb 1923.)
- Consider the binary star system discussed in Section 4.16. Show that
where and , are integrals of the the reduced equation of motion, (4.110) (in other words, and are constants of the motion). Demonstrate that, in the center of mass frame, the net angular momentum and energy of the system arerespectively, where is the reduced mass.