Transit Plan
Launch Phase
We propose to launch on 01JUL2017. We will then follow a minimum energy (Hohmann)
transfer orbit from Earth to Venus. The probe will transit for 146 days to rendezvous with Venus
on 24NOV2017.
For source code of the above calculations, please follow the following link:
Source Code
Transfer Orbit
Holding Orbit Phase
The probe will then enter a circular orbit around Venus at an altitude of 15079km and
a period of about 9.5 hours. This holding orbit lasts for 287 days.
As Venus and Earth approach inferior conjunction, the probe will deorbit and commence the
Landing Phase.
For source code of these calculations, please follow the link above under Launch Phase.
Circular Holding Orbit around Venus
Space Propulsion
Following separation from the third stage of the Delta II rocket motor, propulsion will
be provided by a system modeled after the Venus Express / Mars Express missions. There
will be approximately 400kg of fuel for trajectory corrections, circularizing orbit upon
arrival at Venus, and deorbiting. The primary fuel source will be gaseous helium stored under
high pressure. The main engine can be expected to provide about 400N of thrust and each
thruster about 10N. [1]
[1] European Space Agency. (July 26, 2013). Venus Express: Engineering: Propulsion.
Available: http://sci.esa.int/venus-express/33877-engineering/?fbodylongid=1436