OTHER: SynchroLite ~ Concerns & Tasks
A listing of Potential Concerns, Tasks and Thoughts, regarding the SynchroLite.
It does not have as much flight-control as I would like.Therefore, develop and test the Electrotor-Plus.
3-blade CVJ w/ Hub Spring:
The weight is almost certainly to be above 254 lbs. The 3-blade rotors will have a slightly smaller rotor disks, however they will require more power.
Breakage in Secondary Reduction:
Make sure that the breakage of any part in one of the two power trains cannot lockup the rotors. The gear calculation, which were based on reverse engineering of the K-Max, do not appear to show provision for the other factors (safety etc.) that my calculations do. What am I not understanding in the gear and bearing (perhaps whole power-train) design process?
Oscillation between Rotors:
The long masts may allow a dynamic torsional oscillation to take place between the two rotors. If the is no damping, this may excite to a critical level.
Idea (2): By changing the wall thickness of the masts, make sure that the oscillation frequency of the rotor-rotor connection is as far away from RRPM as possible. This may not work; particularly during autorotation.
Another crazy idea: Use composite, perhaps with varying diameter.
Perhaps the profile drag of the rotors, which varies with speed, may dampen any desire to oscillate.
Run-0n Supports for Emergency Landings:
A number of people have expressed the need to provide for this. See:- DESIGN: Landing Gear
Could start off with long blades and highest gearing, then later reduce the blade lengths and reduce the belt/pulley reduction. This will give better lift &/or less load on engines (re cooling etc).
Vibration: Rotor - Rotor Interaction
The action of the blades as they enter and leave the downwash from the blades of the other rotor.
Vibration: Rotor - Appendage
The blades in the two rotors will pass over the tail 6 * rotor RPM (approximately 6 * 600 / 60 = 60 times a second). If the downwashes have any rotation to them (CW & CCW) then this may possibly rock the tail in each direction 30 times per second. The bracing from the top of the seat should be such a length so as to set up a frequency in the tail that counters the blade wash or the wrap of the plies in the composite boom offset this action. See DESIGN: Fuselage - Tail - Airflow from Downwash
Forward Speed Limitation
What limits the speed of forward flight with the synchropter? DRAG? Could it be that the amount of teetering must be limited so that the blades will not hit each other and this limited teetering limits the amount of forward longitudinal cyclic. If this is the case could the longitudinal cyclic be augmented by controllable pitch on the stabilizer?
Cooling of engine:
Safety of bystanders:
The blade tips are relatively low, especially at the sides. For partial solutions see: B196 ~ Personnel on Ground
The clearance between blade tips and the ground, particularly at the sides. See web page 0775.
Torque ~ Pitch Cross-coupling:
A change of torque in the intermeshing configuration causes a change in pitch.
See: 0842. OTHER: Flight Dynamics - General Cross-Coupling - Torque ~ Pitch
Concerns About the Large Stagger Configuration:See drawing 0472_Wide_Stagger.dc
Testing of Prototype:
The intent is to;
Tasks (to do):
Potential Future Safety Features:
Electronics - Sensors, computers and actuators (I.E. input, processing & output) will play major roll in future. FADEC (Full Authority Digital Engine Control), HUMS (Health and Usage Monitoring), Digipod
Same Page Different Craft:~ UniCopter ~ Nemesis
Considerations as to which Helicopter to Build;
OTHER: Miscellaneous - SynchroLite vs. UniCopter
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Last Revised: August 15, 2008