Rarinn's Ideas

I noticed that photovoltaics are really cheap now. 19.8 kW of peak power would cost around 20 000 PLN (1 USD is equal to 3.65 PLN when I am writing this). Array of 44 of those, with peak power of 475 W each, which actually will be closer to 450 W, because of marketing and degradation progressing with time, will produce aforementioned amount of total peak electrical power. I accounted only for the initial fast degradation, it will slowly get even worse. Appropriate hybrid inverter costs 11 000 PLN.

Description of this engine is mostly outdated. Newer version can be seen here . My previous posts assumed that two-stroke construction based on Lenoir cycle will be used. Charge would be admitted at higher pressure, and admission would take place only at the beginning of downward stroke, then fuel-oxidizer mixture would be ignited by multiple spark gaps, and power extraction would begin. Various combinations of ammonia, hydrogen, air, and oxygen could be used. After researching multiple options, I came to the conclusion, that burning NH3 with air is the best bet for a land vehicle that is expected to have reasonable range. Separating O2 from air (or H2 from NH3) would require bulky counterflow heat exchangers, that would accumulate H2O and CO2 on their surfaces. I was thinking about marketing it as negative-emissions vehicle, but it probably would be a bad idea, nevertheless it could be possible to have heat exchangers connected in parallel, so when one of them clogs, another one ...

  To convert solar energy into electricity that will be later used to produce ammonia ( electrolyzing water and Haber–Bosch process ) I propose that photovoltaic thermal hybrid solar collectors (PVT) with compound parabolic concentrators (CPC) mounted on dual axis trackers should be used. cpc_c.ods is my attempt to describe basic parameters of CPC with high-school math (to achieve best results ray-tracing and realistic models of irradiance at various conditions should actually be used).

This is initial proposal for a crewed lunar program. It is to be based on a large, partially reusable rocket, that is relatively simple to manufacture, placing lightweight two-person spacecraft (lander) in low lunar orbit (LLO). Spacecraft consists of one engine and only single pressurized crew compartment (but cosmonauts have individual pods with life-support that would keep them alive even after depressurization event ). Propellant tanks needed to leave LLO, along with heat shield are stored in orbit while spacecraft lands on the lunar surface. Tanks needed for initial phase of descent are discarded before touchdown.   Launch vehicle