future upgrade is to power push prop not from shaft same engine but diff extra/ separate or hybrid or electric only engine. 2nd upgrade is hving push prop angle up & down as well as right & left a must feature.
If the engine on this thing has a fixed gear ratio to the rotors, isn't the relative air speed of the rotor tips going to be very different during high speed flight and hover? This seems like a difficult trade-off. Ideally, you would probably want to have the ability to slow down the rotors during high speed flight while maintaining a high rpm on the engine, but this would require separate different gear ratios.
@Tom Gulbranson Are you sure all of that applies to this given that it's A: a coaxial rotor and B: uses a pusher propeller for forward flight rather than rotor pitch? Lift asymmetry presumably wouldn't be as much of a problem when you have advancing and retreating blades on both sides at any given time. I was more thinking of the potential problem of the advancing blade reaching transonic speeds at some point if the point of this vehicle is to reach new levels of speed. Do you know for a fact that the rotor has lead-lag and flapping hinges? It could be a rigid rotorhead.
God, the push prop must b able to turn & gear must b able to fold down from winglets in case of crash. Not military buy means fully tested for 5yrs min fully operational flight hrs reach no major reworks/design fixes needed.
future upgrade is to power push prop not from shaft same engine but diff extra/ separate or hybrid or electric only engine. 2nd upgrade is hving push prop angle up & down as well as right & left a must feature.
Awesome 👏
@Team Defiant don't throw away that prototype or schematic yet I have a feeling the V280 isn't going to really make it 🤔
If the engine on this thing has a fixed gear ratio to the rotors, isn't the relative air speed of the rotor tips going to be very different during high speed flight and hover? This seems like a difficult trade-off. Ideally, you would probably want to have the ability to slow down the rotors during high speed flight while maintaining a high rpm on the engine, but this would require separate different gear ratios.
@Tom Gulbranson Are you sure all of that applies to this given that it's A: a coaxial rotor and B: uses a pusher propeller for forward flight rather than rotor pitch?
Lift asymmetry presumably wouldn't be as much of a problem when you have advancing and retreating blades on both sides at any given time.
I was more thinking of the potential problem of the advancing blade reaching transonic speeds at some point if the point of this vehicle is to reach new levels of speed.
Do you know for a fact that the rotor has lead-lag and flapping hinges? It could be a rigid rotorhead.
@Tom Gulbranson Would you mind sharing your sources?
👍🏻🇺🇸
Lockheed is eternally damned too!
boeing not allowed to exist ever forever any longer.
God, the push prop must b able to turn & gear must b able to fold down from winglets in case of crash. Not military buy means fully tested for 5yrs min fully operational flight hrs reach no major reworks/design fixes needed.
This is russia aircraft helo design fine but hurts the rotating quick snap or power turning.