C(x, y) , where x = propellant loading and y = Engine thrust & configurationcan any one explain me what is
c(27,20): is it cryo stage with 27 ton propellant?
sc (500,5*200) :is it semi cryo with 500 ton propellant? what is 5*200?
explanation from br:
I'm afraid an improvement is due here.
Few issues with this one:I'm afraid an improvement is due here.
180nm is too dated as a fabrication process. It belongs to the late 90s level of semiconductor technology.
Tech has grown leaps & bounds since then. The latest is only 14nm, and while I clearly cannot expect ISRO or any space agency to remain up-to-date with semicon fabs (afterall it is not an electronics company like Nvidia), I'd like to see atleast a 32nm process replacing this 180nm CMOS.
Dawn has 3 ion thrusters that provide 90mN each, adding up to 270mN. Are we looking at a single 300mN engine or did I misread? Sorry I can't see the video at the moment.- ISRO is developing 10 ton methane/lox engine for interplanetary missions, eg, propulsion for lander like Morpheus
- Developing space tug to launch sats directly to GTO. this will render LAM useless and will be removed once ion propulsion is reliable.
- 300mN ion engine under development, will be used for a Dawn like psacecraft.