In the preceding section the route to Mars was identified, along a Hohmann Transfer Ellipse. The time required was derived, about 8.5 months, as well as the position of Mars at the time of launch, about 45° past closest approach.
This section calculates two essential details: the velocity boost needed to inject the Mars spaceship into the transfer orbit, and the arrival velocity at the orbit of Mars. Will the spaceship be overtaking the planet or be overtaken by it, and what will be the velocity mismatch between ship and planet--a mismatch which will probably require an additional rocket firing? Keep reading, and if you can handle elementary algebra, you may find out.
19.Motion in a Circle
20. Newton's Gravity
21. Kepler's 3rd Law
21a.Applying 3rd Law
21b. Fly to Mars! (1)
21c. Fly to Mars! (2)
21d. Fly to Mars! (3)
22c. Flight (1)
22d. Flight (2)
23. Inertial Forces
23a. The Centrifugal Force
24a.The Rotating Earth
24b. Rotating Frames
Notation and Escape Velocities
Before starting out, it helps to establish a notation for the quantities involved here. Even though some of them are vectors, only their magnitudes are handled. Bold face is only used to accentuate, never to indicate vector character.
As before, r1 = 1 AU is the distance of Earth from the Sun, r2 = 1.523691 AU that of Mars, and (as an approximation) both planets are assumed to move in circles.
Velocity V will be measured in kilometers per second (km/s), and different velocities are identified by subscripts. Lower-case v identifies velocities associated with orbits around Earth rather than around the Sun.
The preceding section already introduced the orbital velocity V0 of Earth around the Sun, amounting to about 30 km/s, much larger than v0 ~ 8 km/s (approx.) required by a satellite circling the Earth just above the surface(ignoring the atmosphere!). In section #21 it was noted that the escape velocity ve from such a low orbit is obtained by multiplying v0 by the square root of 2, equal to 1.41421356.... approximated here by 1.414. This gives
Such a spacecraft, however, is still not free to move to any point in space. The velocity ve has purchased its freedom from the Earth's gravity, but not freedom from the pull of the Sun, around which it continues to move in an orbit similar to Earth's, at approximately V0 =30 km/s.
The situation is now completely analogous to escape from a low altitude Earth orbit (only the cost is higher!). To break free from a circular orbit around the Sun and leave the Solar system, the spacecraft needs to boost its velocity to a "second escape velocity"
To reach Ve it must somehow increase its velocity by an additional 12.42 km/s--more than is needed to escape the Earth's gravity, starting from rest on the surface! Luckily, ways exist (discussed in Section #35) of making the motion of planets (or of the Moon) provide part of this boost.
Other velocities entering the calculation are the velocity V1 with which the spaceship starts from near Earth and enters the Hohmann ellipse (distance r1 from the Sun), and the velocity V2 with which it reaches the orbit of Mars (distance r2). Also, V3 will be the velocity of Mars in its orbit, assuming it has a constant magnitude (i.e assuming the orbit of Mars is circular).
If V2 > V3, the spaceship overtakes Mars, while with V2 < V3 it is being overtaken.
(1) Kepler's Laws
The drawing here shows the orbit of Mars (solid) and the transfer ellipse (broken line), with radiuses (r1, r2) to the (perigee, apogee) points, at which the spacecraft velocity is (V1, V2). The short segments drawn at these locations represent the distance covered by the spacecraft in the next second after passing perigee or apogee, and by the definition of velocity ("distance per second") they also equal V1 and V2. Actually, those segments should be curved like the orbit, but being so short they differ negligibly from straight lines We then complete the long thin triangles, which have these lines as bases.
Note that each of these triangles has a right angle at its bottom, because at apogee and at perigee (and nowhere else), the line to the Sun is perpendicular to the orbit.
At perigee, the height of the triangle is r1, the length of its base is V1, so by the equation for the area A1 of a triangle
At apogee, the height is r2, the base V2, and the area is
Each of these triangles is swept in one second, so by Kepler's 2nd law their areas can be set as equal. Multiplying both sides of that equality by 2 yields
The equation is numbered to help refer to it later. Please note this relation only holds between apogee and perigee. At other points of the orbit, the angle between the radius and the orbit is not 900, and the area also depends on its exact value.
Kepler's third law was already used in determining the orbital period. It will be needed again at the end.
(2) The Energy Equation
In section #12 it was stated that the energy E of a satellite of mass m orbiting Earth, at any point in its orbit, is
where r is the point's distance from the center of Earth, V is the satellite's velocity at that point, and k is some constant, related to the gravitational acceleration g. Because the energy E is conserved, the right-hand expression has the same value anywhere on the orbit. A similar relation holds for orbits around the Sun, although the value of k is different. We can express k in that case by using a simple trick, based on the escape velocity.
As noted earlier, for an object in the Earth's orbit to completely escape the Sun (but just barely!), it needs a velocity Ve = 1.414..V0 = 42.42 km/s. Let E0 be the energy of such an object. Then since
Because it has escape velocity, if we wait a long, long time, this object will be extremely far from Earth, and, having exhausted practically all of its kinetic energy, its velocity will be very close to zero. Then both terms on the right side of equation (2) tend to zero, suggesting
So we have
Dividing by m and shifting the negative Ve term to the right
from which the value of k may be written
CalculationIn earlier sections we approximated
In what follow more precision will be used, taking the astronomical unit as
A circular orbit around the sun with this radius has length
and assuming a Julian year of 365.25 days of 86400 seconds each gives
Returning now to the spaceship in a Mars transfer orbit, its energy should be the same at the perigee P and the apogee A, so by equation (2)
Divide both sides by m ("cancel m") and multiply both sides by 2
Transferring terms (by adding suitable quantities to both sides) and substituting (3) gives
= 2 V02 (1 – (r1/r2))   (4)
We therefore have all we need to calculate the right side of equation (4).
2 V02 (1 – (r1/r2)) = 2 (887.163) (0.343699) = 609.834 (km/s)2
On the left side we have two unknown quantities V1 and V2, but we can use (1)
Substituting this on the left side of (4)
Extracting square root
showing we need add just 2.945 km/s, a shade short of 3 km/s or 10% of the orbital velocity.
Arrival at MarsThe velocity V2 at which the spaceship arrives at Mars is found from (5)
It has given up some of its kinetic energy to overcome the pull of the Sun and moVe further outward from the Sun. The big question now is--how does this compare with the velocity V3 of Mars in its orbit?
To derive a velocity in km/s, distances must be ultimately rendered in kilometers and times in seconds, but "for the benefit of pedestrians," we break up the calculation, avoiding big numbers and scientific notation. We start with Kepler's 3rd law for circular orbits, with distance r in AU and orbital period T in years. As derived in the preceding section (and also in section #10), in these units
For Mars, r = 1.523691, T2 = (1.523691)3 = 3.53745
Assuming 365.25 days per (Julian) year:
During that time the spaceship covers
Dividing by T, this comes to
Each day has (24)(3600) = 86400 seconds, so the orbital distance covered by Mars each second is
Distance-per-second is of course the definition of velocity. Therefore
we see that Mars is the one moving faster, and will be overtaking the spaceship. To match velocities with Mars, the spaceship must generate an extra boost of 2.649 km/s .
Next Stop: #21d. Flight to Mars: the Return Trip
Timeline Glossary Back to the Master List
Author and Curator: Dr. David P. Stern
Mail to Dr.Stern: stargaze("at" symbol)phy6.org .
Last updated: 9-22-2004
Reformatted 24 March 2006