the Hohmann orbit transfer

29032016, 09:33 PM
Post: #1




the Hohmann orbit transfer
This HP Prime program solves the Hohmann orbit transfer problem between two circular Earth orbits. It is valid for both coplanar and noncoplanar orbits.
The companion zip file contains a PDF document that describes the mathematics of the Hohmann transfer and the solution method. The following is the output from this program. Hohmann Orbit Transfer Analysis initial orbit altitude 300 km initial orbit radius 6678.14 km initial orbit inclination 28.4999999999 deg initial orbit velocity 7725.75849386 mps final orbit altitude 35786.2 km final orbit radius 42164.34 km final orbit inclination 2.5 deg final orbit velocity 3074.65388637 mps first inclination change 2.06933377042 deg second inclination change 23.9306662295 deg total inclination change 25.9999999999 deg first deltav 2446.72845032 mps second deltav 1732.48150109 mps total deltav 4179.20995141 mps T/O semimajor axis 24421.24 km T/O eccentricity 0.726543779104 T/O inclination 26.4306662295 deg T/O perigee velocity 10151.4931415 mps T/O apogee velocity 1607.83003856 mps T/O coast time 18990.3317865 seconds T/O coast time 316.505529775 minutes T/O coast time 5.27509216292 hours 

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