program ipto - interplanetary trajectory optimization
=====================================================
 
initial orbital elements and state vector
(heliocentric ecliptic and equinox of J2000)
--------------------------------------------
 
Earth
 
calendar date  	June 7 2003
 
UTC time       	20 hours 36 minutes 49.43 seconds
 
semimajor axis          	1.0000010180 AU
eccentricity            	0.0167071774
orbital inclination     	0.0004 degrees
argument of perigee     	288.0835 degrees
RAAN                    	174.8649 degrees
true anomaly            	153.6979 degrees
 
position vector x-component  	-3.506686626636e+07	 kilometers
position vector y-component  	-1.477252709901e+08	 kilometers
position vector z-component  	1.174872460684e+03	 kilometers
 
position vector magnitude    	1.518303026416e+08	 kilometers
 
velocity vector x-component  	2.849840251725e+01	 kilometers/second
velocity vector y-component  	-6.991575298582e+00	 kilometers/second
velocity vector z-component  	3.450069449798e-05	 kilometers/second
 
velocity vector magnitude    	2.934350134514e+01	 kilometers/second
 
 
final orbital elements and state vector
(heliocentric ecliptic and equinox of J2000)
--------------------------------------------
 
Mars
 
calendar date  	December 28 2003
 
UTC time       	12 hours 56 minutes 32.04 seconds
 
semimajor axis          	1.5236793420 AU
eccentricity            	0.0934042294
orbital inclination     	1.8494 degrees
argument of perigee     	286.5316 degrees
RAAN                    	49.5463 degrees
true anomaly            	72.9019 degrees
 
position vector x-component  	1.443324368932e+08	 kilometers
position vector y-component  	1.659191955418e+08	 kilometers
position vector z-component  	-7.016935399128e+04	 kilometers
 
position vector magnitude    	2.199114292449e+08	 kilometers
 
velocity vector x-component  	-1.735727441052e+01	 kilometers/second
velocity vector y-component  	1.796707126749e+01	 kilometers/second
velocity vector z-component  	8.028848351405e-01	 kilometers/second
 
velocity vector magnitude    	2.499470441817e+01	 kilometers/second
 
initial delta-v vector and magnitude
(heliocentric ecliptic and equinox of J2000)
--------------------------------------------
 
delta-v vector x-component  	2895.449599 meters/second
delta-v vector y-component  	-653.699580 meters/second
delta-v vector z-component  	-21.760090 meters/second
 
delta-v magnitude           	2700.672241 meters/second
 
orbital energy              	7.293631 km^2/sec^2)
 
 
final delta-v vector and magnitude
(heliocentric ecliptic and equinox of J2000)
--------------------------------------------
 
delta-v vector x-component  	-2019.677630 meters/second
delta-v vector y-component  	1609.283132 meters/second
delta-v vector z-component  	790.405355 meters/second
 
delta-v magnitude           	2700.672241 meters/second
 
orbital energy              	7.293631 km^2/sec^2)
 
 
total deltav magnitude      	5401.344482 meters/second
 
total orbital energy        	14.587261 km^2/sec^2)
 
total time of flight        	203.680354 days
 
 
transfer orbital elements and state vector after first delta-v
(heliocentric ecliptic and equinox of J2000)
--------------------------------------------
 
semimajor axis          	1.2598682075 AU
eccentricity            	0.1945049751
orbital inclination     	0.0385 degrees
argument of perigee     	177.2951 degrees
RAAN                    	77.3056 degrees
true anomaly            	2.0456 degrees
 
 
transfer orbital elements and state vector prior to second delta-v
(heliocentric ecliptic and equinox of J2000)
--------------------------------------------
 
semimajor axis          	1.2598682075 AU
eccentricity            	0.1945049751
orbital inclination     	0.0385 degrees
argument of perigee     	177.2951 degrees
RAAN                    	77.3056 degrees
true anomaly            	154.3793 degrees
