One concern that caught my eye is the rigid configuration of the Ivoprop style blade: should it have lead/lag and flapping hinges. If so, given that it is not a rotor blade regarding the rotor chord width and span, would flapping hinges cause too much blade coning and lose lift? It's an intriguing platform.
I decided to attempt to design a rotor head that would allow a small amount of flapping action & lead/lag, but without adding excessive weight.
WARNING: Do not attempt to use the following sketches herein on a manned platform. UAS/UAV will require testing. Considerations need to be addressed when scaling up. You are responsible for your on actions and any damage or injuries that may result in not following sound design and fabrication processes. Flying any aircraft, manned or unmanned, can result in injury or death to you and/or others. You are legally, financially, & medically responsible for you on actions. This rotor hub may be sound for /UAVUAS. Keep in mind that allowing the hub to flex/flap in this design will require more distance bewteen the lower and upper hubs when utilized in a UAV/UAS platform if you intend to use the def gear assembly between the hubs to attain counter rotation. Personally I like the idea of two rotor shafts.
This video is the reason for my concern for not having flapping hinges for dealing with dissymmetry of lift. Not a Schoffmann helicopter.
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