A122

DESIGN: Electrotor-SloMo ~ Rotorhead (aerodynamic)

There is a problem in the Access program, see red below

Possible Arraignments:

Orientation:

Aero-rotor in plane of electric-rotor.
Aero-rotor above electric-rotor.

Torque-pitch by:

Pitch change (active pitch).
Twist change (active twist).

Blade spar:

From tow (UniCopter).
From unidirectional tape (SynchroLite).

Power Requirements of Different Configurations:

Considerations re Interleaving vs. Intermeshing, and also consideration of the Flettner which it is said that it gets 16 lb per horsepower:

	Flettner:	SynchroLite: Intermeshing	Electrotor: 1 rotor only	Electrotor: 1 rotor only	Single: w/ 4 blades
Gross Weight:	2202 lbs	500 lbs	150 lbs	300 lbs	500 lbs
Disk Area (one rotor):	1216 ft²	236 ft²	113	236	236
Total Disk Area:	1292 ft²	272 ft²	113	236	236
Effective Disk Area:	1695 ft²	337 ft²	113	236	236

Blades:	4	4	2	4	4
Radius:	19.675 ft	8.666 ft	6.00 ft	8.666 ft	8.666 ft
Chord:	0.9583 ft	0.4375 ft	0.67 ft	0.4375 ft	0.4375 ft
Aspect Ratio:	20.531	22.087	11.0	19.817	19.817
Twist:	-4º	-7º ⁽¹⁾	-8º ⁽¹⁾	-7º ⁽¹⁾	-7º ⁽¹⁾

Disk Loading:	1.7041	2.4269	1.33	1.2233	2.12
Blade Loading:	29.197	32.351	23.0	32.954	32.954
Rotor Solidity Ratio:	0.0584	0.0750	0.0578	0.0371	0.0642

Stagger:	1.933 ft	2.083 ft	0	0	0
Rotor Speed:	600 rpm	600 rpm	730 rpm ⁽⁵⁾	730 rpm ⁽⁵⁾	730 rpm ⁽⁵⁾

Power Momentum:		24.3 hp	6.0 hp	26.2 hp	26.2 hp
Power Combined:		29.2 hp ⁽³⁾ ⁽⁴⁾	5.1 hp	32.7 hp ⁽³⁾	23.4 hp ⁽³⁾
Guestimate: x 1.2		28.2 hp	7 x 2 = 14.0 hp	30.0 hp ⁽³⁾	30.0 hp ⁽³⁾
		21kW	10.4 kW	22.4kW	22.4 kW

(1) 7º twist used for Access calculations. Actual value will probably be 12º

(3) It appears that the gap factor is not changing for different gaps. It should be higher and thus the horsepower higher. In fact the horsepower should be higher than the Intermeshing.

(4) There is a problem here. This should be less than the intermeshing

The coding may be OK for the single rotor but the changes and additions for the two rotor craft are not working correctly.

(5) This is for hover. Climb and forward flight will be faster.

More information on Power Requirements: All to be combined on one page at some time.

Electrotor - Disk and Power Specifications ~ Access Form
DESIGN: Electrotor-SloMo - Rotor - Disk - General

Thrust to Power Ratios for Hover: The AHS Journal report entitled Technical Note: Twin Rotor Hover Performance. There is also a hard copy in the removable E drive as; For more see; B360.html - ThrustPowerRatio .

Another Blade Manufacturer:

Wirlwind Propellers ~ New W530 Composite Blades

Diameter: 250 cm (98.5 inches)

Construction: Thermo-set Aerospace Graphite composite Wood Leading Edge: Flush bond Nickel Riveted Multi-piece Stainless

Weight: 15.5 lbs. 2 blades

__________________

Note that IVO's Magnum: is

up to 74" diameter
2-blade. 17.5 lb. $1080.00
3-blade. 22.3 lb. $1400.00
This suggests that the blades weigh 4.8 lbs each and the hub weighs 7.9 lbs. See below for more.

More Propellers

An oversize Paramotor propeller might be ideal???? Low induced velocity???

Safety:

xxx

The following is the objective that I am "trying' to achieve; initially under the condition of fully powered rotors. It is based on the premise that a person has more stability standing, when he is also holding on to a railing.

It involves having extremely fast responses from the rotors to the pilot's arm and hand inputs.

The solution of more power is an obvious one. Also the Torque-Pitch coupling c/w extremely rigid, low-inertia blades. This T-P coupling is intended to use the instant increase of the torque to give an instant increase in the pitch, and then let the rotor speed partially catch up. It is intended that, if need be, a fast reaction will 'lift' the pilot out of the problem.

An efficient throttle will allow the pilot to play with the weight on his feet.

Another is the rate of cyclic response. This is to be tackled by having the moments of the 2-rotors, 2 motors and connecting frame assembly concentric with the gimbal. In addition the low mass of this assembly and the very rigid blades will, hopefully provide very fast pitch and roll responses.

There are also a number of ideas for yaw control.

Another consideration is for slow rotors and/or a very fast rotor brake. Theoretically, instantaneous stopping of the rotors on a Coaxial configuration and an Interleaving configuration should have no effect at and beyond the gimbal, assuming that the rotors plus connecting frame can handle the heavy shock load. The sudden stopping of the Intermeshing will cause the frame assembly to rotate top back and this may pull the front legs out of the pilots hands plus tip the pilot backward.

Last Revised: December 31, 2011