Wj2 = -3*(Req/p)^2*n*J2*cos(i)/2

where the perturbed mean motion is given by

n = sqrt (mu/a^3)*(1+3*J2*(Req/p)^2*(3*(cos(i))^2-1)/(4*sqrt(1-e^2)))

The period of the orbit is given by

T = 2*pi()/n

The angle, Dlong, between successive ascending nodes, measured in the equatorial plane, is given by

Dlong = (-We + Wj2)*T

and the distance along the equator between successive node crossing points is given by

Dist = Dlong*Req

a = r (for circular orbits only)

p = a * (1 - e^2)

r = Req + ALT (altitude at the ascending node point)

.0010826>td>-228.1365

St	Input	Name	Output	Units	Comments
	6378.16	Req		km	Equatorial radius of Earth
	398598.15	mu		km^3/s^2	Earth's gravitational parameter
	7.2921E-5	We		rad/s	Earth's rotation rate
	J2			Oblateness Coefficient
	1.991E-7	Wj2	rad/s	Sunsynch Node Rotation due to J2
L		ALT	km	Altitude
L		a	6150.0235	km	Semi-major Axis of Orbit
	0	e			Eccentricity of Orbit
L	95	i			deg	Inclination of Orbit
		p	6150.0235	km	Orbit	Parameter
L		r	6150.0235	km	Radius of Orbit
L		T	4803.9284	sec	Period of Orbit
		n	.00130793	sec^-1	Mean Motion of Orbit
L		Dlong	-20.01639	deg	Change in Ascending Node per Rev
L		Dist	-2228.222	km	Distance between successive nodes

Last Modified: Thurs June 26 1997
CSR/TSGC Team Web