Economics evaluation of the water splitting while space traveling


Economics evaluation of the water splitting while space traveling

Author: David Judbarovski, systems engineering, retired engineer, Israel

judbarovski@gmail.com , Linkedin: David Judbarovski

My idea goes back to 13.06.2015 [1] and more detailed disclosed on 4.12.2016 and later.

 

Here I will show my technology and its economics evaluation on example of world record heaviest rocket of Falcon Heavy can launch more than 15% heavier payload with a help of my technology.

 

A core of the idea is the water splitting can start since LEO (Low Earth Orbit) and producing the oxygen and the hydrogen being much more powerful fuel than kerosene based ones, but the electrolyser is a very heavy device per kW power. Instead it we can use thermal water splitting by concentrated rays of a lot of LED-s or microwave generators, powered by PV-cells on substrate being a very thin film can be unrolled on the orbit, and oriented to the sun by two servomotors fed by a tiny share of the said hydrogen. [1], [2].

 

Really,

My Hydrogen + Oxygen is about 4500 m/s as its specific impulse since LEO, while Falcon Heavy with kerosene + oxygen (liquid) is about 3500 m/s only, but being most suitable fuel for space launch vehicle, can deliver 63.8 ton on LEO and 16.8 ton to Mars if following http://spacex.com/falcon-heavy.

In another hand:

1421 / (2.71 ^ ((7.8 + 400*9.8/1000)/4.5) = 106

1421 / (2.71 ^ ((7.8 + 0.4*9.8)/3.5) = 50 ton

So Falcon Heavy really uses something about kerosene with Cryogenic Oxidant with specific impulse I = (7.8 + 0.4*9.8)/ ln(1421 / 63.8) = 3780 m/s ~== 3500.

So we can deliver the Mars payload,

(2.71^(11.2 -7.8)/3.78) / (2.71 ^ (11.2 – 7.8)/4.5)) = 1.15, so more than 15 % heavier, because it needs more than 11.2 km/s to Mars.

 

References:

[1] “About usage of the water decomposed by solar energy for satellite orbit correction”, 13.06.2015, http://judbarovski.livejournal.com/115334.html

 

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