From: leech@mahler.cs.unc.edu (Jon Leech)
Newsgroups: sci.astro,sci.space,news.answers
Subject: Space FAQ 06/16 - Constants and Equations
Keywords: Frequently Asked Questions
Date: 16 Apr 92 00:09:19 GMT
Expires: 30 May 92 00:09:18 GMT
Followup-To: poster
Organization: University of North Carolina, Chapel Hill
Supersedes: <constants_700343619@cs.mit.edu>

Archive-name: space/constants
Last-modified: $Date: 92/04/15 19:57:07 $

CONSTANTS AND EQUATIONS FOR CALCULATIONS

    This list was originally compiled by Dale Greer. Additions would be
    appreciated.

    Numbers in parentheses are approximations that will serve for most
    blue-skying purposes.

    Unix systems provide the 'units' program, useful in converting
    between different systems (metric/English, etc.)

    NUMBERS

	7726 m/s	 (8000)  -- Earth orbital velocity at 300 km altitude
	3075 m/s	 (3000)  -- Earth orbital velocity at 35786 km (geosync)
	6378 km		 (6400)  -- Mean radius of Earth
	1738 km		 (1700)  -- Mean radius of Moon
	5.974e24 kg	 (6e24)  -- Mass of Earth
	7.348e22 kg	 (7e22)  -- Mass of Moon
	1.989e30 kg	 (2e30)  -- Mass of Sun
	3.986e14 m^3/s^2 (4e14)  -- Gravitational constant times mass of Earth
	4.903e12 m^3/s^2 (5e12)  -- Gravitational constant times mass of Moon
	1.327e20 m^3/s^2 (13e19) -- Gravitational constant times mass of Sun
	384401 km	 ( 4e5)  -- Mean Earth-Moon distance
	1.496e11 m	 (15e10) -- Mean Earth-Sun distance (Astronomical Unit)

	1 megaton (MT) TNT = about 4.2e15 J or the energy equivalent of
	about .05 kg (50 gm) of matter. Ref: J.R Williams, "The Energy Level
	of Things", Air Force Special Weapons Center (ARDC), Kirtland Air
	Force Base, New Mexico, 1963. Also see "The Effects of Nuclear
	Weapons", compiled by S. Glasstone and P.J. Dolan, published by the
	US Department of Defense (obtain from the GPO).

    EQUATIONS

	Where d is distance, v is velocity, a is acceleration, t is time.

	For constant acceleration
	    d = d0 + vt + .5at^2
	    v = v0 + at
	  v^2 = 2ad

	Acceleration on a cylinder (space colony, etc.) of radius r and
	    rotation period t:

	    a = 4 pi**2 r / t^2

	For circular Keplerian orbits, where u is gravitational constant, a is
	    semimajor axis of orbit, P is period.
	    v^2 = u/a
	    P	= 2pi/(Sqrt(u/a^3))
	    u	= G * M (can be measured much more accurately than G or M)

	    Vc = sqrt(M * G / r)
	    Vesc = sqrt(2 * M * G / r) = sqrt(2) * Vc
	    The period of an eccentric orbit is the same as the period of a
	       circular orbit with the same semi-major axis
	    1/2 V**2 - G * M / r = K  (conservation of energy)
		    where
	    Vc	 = velocity of a circular orbit (you have something like this)
	    Vesc = escape velocity
	    K	 = -G * M / 2 / a
	    M	 = Mass of orbited object
	    G	 = Gravitational constant
	    r	 = radius of orbit (measured from center of mass of system)
	    V	 = orbital velocity

	Change in velocity required for a plane change of angle phi in a
	circular orbit:

	    delta V = 2 sqrt(GM/r) sin (phi/2)

	Energy to put mass m into a circular orbit (ignoring rotational
	velocity of the Earth, which reduces the energy a bit).

	    GMm (1/Re - 1/2Rcirc)
	    Re = radius of the earth
	    Rcirc = radius of the circular orbit.

	Classical rocket equation (dv = change in velocity, ve = exhaust
	  velocity, x = reaction mass, m1 = rocket mass excluding reaction
	  mass):

	    dv = Ve * ln((m1 + x) / m1)
	       = Ve * ln((final mass) / (initial mass))
	    Ve = Isp * g = exhaust velocity, m / s
	    Isp = specific impulse of engine
	    g = 9.80665 m / s^2

	Relativistic rocket equation (constant acceleration)

	    t (unaccelerated) = c/a * sinh(a*t/c)
	    d = c**2/a * (cosh(a*t/c) - 1)
	    v = c * tanh(a*t/c)

	Relativistic rocket with exhaust velocity Ve and mass ratio MR:

	    at/c = Ve/c * ln(MR), or

	    t (unaccelerated) = c/a * sinh(Ve/c * ln(MR))
	    d = c**2/a * (cosh(Ve/C * ln(MR)) - 1)
	    v = c * tanh(Ve/C * ln(MR))

	Converting from parallax to distance:

	    d (in parsecs) = 1 / p (in arc seconds)
	    d (in astronomical units) = 206265 / p

	Miscellaneous
	    f=ma    -- Force is mass times acceleration
	    w=fd    -- Work (energy) is force times distance

	Atmospheric density varies as exp(-mgz/kT) where z is altitude, m is
	molecular weight in kg of air, g is acceleration of gravity, T is
	temperature, k is Bolztmann's constant. Up to 100 km,

	    d = d0*exp(-z*1.42e-4)

	where d is density, d0 is density at 0km, is approximately true, so

	    d@12km (40000 ft) = d0*.18
	    d@9 km (30000 ft) = d0*.27
	    d@6 km (20000 ft) = d0*.43
	    d@3 km (10000 ft) = d0*.65


	Titius-Bode Law for approximating planetary distances:

	    R(n) = 0.4 + 0.3 * 2^N Astronomical Units (N = -infinity for
	    Mercury, 0 for Venus, 1 for Earth, etc.)

	    This fits fairly well except for Neptune.

    CONSTANTS

	6.62618e-34 J-s  (7e-34) -- Planck's Constant "h"
	1.054589e-34 J-s (1e-34) -- Planck's Constant / (2 * PI), "h bar"
	1.3807e-23 J/K	(1.4e-23) - Boltzmann's Constant "k"
	5.6697e-8 W/m^2/K (6e-8) -- Stephan-Boltzmann Constant "sigma"
    6.673e-11 N m^2/kg^2 (7e-11) -- Newton's Gravitational Constant "G"
	0.0029 m K	 (3e-3)  -- Wien's Constant "sigma(W)"
	3.827e26 W	 (4e26)  -- Luminosity of Sun
	1370 W / m^2	 (1400)  -- Solar Constant (intensity at 1 AU)
	6.96e8 m	 (7e8)	 -- radius of Sun
	1738 km		 (2e3)	 -- radius of Moon
	299792458 m/s	  (3e8)  -- speed of light in vacuum "c"
	9.46053e15 m	  (1e16) -- light year
	206264.806 AU	  (2e5)  -- \
	3.2616 light years (3)	 --  --> parsec
	3.0856e16 m	 (3e16)  -- /


Black Hole radius (also called Schwarzschild Radius):

	2GM/c^2, where G is Newton's Grav Constant, M is mass of BH,
		c is speed of light

    Things to add (somebody look them up!)
	Basic rocketry numbers & equations
	Aerodynamical stuff
	Energy to put a pound into orbit or accelerate to interstellar
	    velocities.
	Plane change delta-vee formula?
	Non-circular cases?
	Atmosphere scale height for various planets.


NEXT: FAQ #7/15 - Astronomical Mnemonics
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