I looked elsewhere for info about Jupiter Injections. Other sources give a more consistent delta-v requirement of ~9,300 m/s - mainly by a simple Googling of Earth-Jupiter Delta-V.
For that, and having recalculated the maximum payload for the Argo-HU at 33,420Kg for a 225x225Km Orbit at 51.6 degrees. I get a payload of 36,230Kg for a 185x185Km orbit at 7 degrees - the one I find most likely for GTO and Trans-Anywhere-Injection.
That means for a TJI assuming I actually need 9,300 m/s of delta-v, 31,700Kg of the Parking Orbit Payload must be propellant. Leaving me with 4,530Kg for not only the payload, but the dry mass of the upper stage. The above using In(TM/DM)*9.8*448.
If the above is incorrect in any way, could someone alert me to how it's actually done, and the correct number.
In any case. Even if it is correct, that would suggest that the Shuttle-C planned for TTL would have the necessary payload budget to accomplish sending a Juno-sized (3.635Kg) probe straight to Jupiter without the need for Planetary Flyby Assist. Though it also suggests that a Venus-Venus-Earth-Jupiter Trajectory would still be required for the 5,900Kg - IOTL - Cassini/Huygens mission.
Clearly a lot of work to be done if I wanna get this right.
For that, and having recalculated the maximum payload for the Argo-HU at 33,420Kg for a 225x225Km Orbit at 51.6 degrees. I get a payload of 36,230Kg for a 185x185Km orbit at 7 degrees - the one I find most likely for GTO and Trans-Anywhere-Injection.
That means for a TJI assuming I actually need 9,300 m/s of delta-v, 31,700Kg of the Parking Orbit Payload must be propellant. Leaving me with 4,530Kg for not only the payload, but the dry mass of the upper stage. The above using In(TM/DM)*9.8*448.
If the above is incorrect in any way, could someone alert me to how it's actually done, and the correct number.
In any case. Even if it is correct, that would suggest that the Shuttle-C planned for TTL would have the necessary payload budget to accomplish sending a Juno-sized (3.635Kg) probe straight to Jupiter without the need for Planetary Flyby Assist. Though it also suggests that a Venus-Venus-Earth-Jupiter Trajectory would still be required for the 5,900Kg - IOTL - Cassini/Huygens mission.
Clearly a lot of work to be done if I wanna get this right.