Electric UniCopter

Single-seat & UAV

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This project may be the design, development and possible construction of a full-size electric UniCopter.

~ comprising ~

Electric future ~ Pilotless future

The utility inventions on this site are openly and publicly disclosed on the Internet to negate an entity from patenting them, to the exclusion of all others whom may wish to use them. ~ Reference patent law 35 U.S.C. 102 A person shall be entitled to a patent unless - (a) the invention was known ... by others in this country, ..., before the invention thereof by the applicant for patent.

 The single seat version of this may be become an advanced version of the OTHER: Aircraft - Gyro/Heli - UniCopter-Lite - Intermeshing - All Electric

Consider the advantages of the Interleaving configuration or the wide stagger Unicopter.

The motor for the propulsor might be the same as one of the motors for the AeroVantage 1*2

Objectives:

Advantages:

Usage:

Drawing:

Single-seat Configuration:

Three preliminary views of the same thing ~ Eventually merged into one.

1097_Wide_Stagger_Electric_2.gif

Advantages of Wide Stagger:

Tractor or Pusher Configuration:

The following are presently the 1/4 scale OTHER: Helicopter - Inside - Intermeshing - Electric UAV drawings.

Note that the 'fat' shape of the UAV fuselage will allow the rotors to have a large stagger and perhaps a smaller 'V' angle

 

 

  

Weight and Balance (UAV):

Taken from UniCopter_WeightAndBalance.html and crudely modified to get some idea about the weight of a full scale electric UniCopter UAV with the UAV 'squat' fuselage.

 Item:

Full Name:

Wt. Ea.

Qty.

Length of Arm (in)

Moment (lb-in)

 

 

Wt. Ea.

Qty.

X

Y

Z

X

Y

Z

1267

Control - Flight - Assembly - Final

20

1

-12

0

24

-240

0

480

1260

Control - Power Train - Assembly - Final

10

1

7

0

24

70

0

240

1261

Electrical - Assembly - Final

9

1

0

0

24

0

0

216

1270

Motor - Assembly - Final

28

1

10.25

0

25

3147

0

7675

 

Motor Controller

10

1

36

0

18

360

0

180

1262

Equipment - Assembly - Final

11

1

-12

0

36

-132

0

396

1264

Fuel - Assembly - Final

17

1

2

0

42

34

0

714

1265

Instrument - Assembly - Final

5

1

-34

0

36

-170

0

180

1266

Landing Gear - Assembly - Final

15

1

13

0

72

195

0

1080

1268

Power Train - Assembly - Final

120

1

3

0

8

360

0

960

1268

Pusher Prop - Assembly - Final

40

1

29

0

29.5

1160

0

1180

1269

Rotor - Assembly - Final - VR-7b - 5.25"

140

1

0

0

0

0

0

0

 

Empty Weight:

425

 

Empty Moment:

 

0

 

1271

Weight & Balance - Load - Test Equipment

75

1

-10

0

40

-1490

0

5960

1272

Weight & Balance - Batteries (2)

??

1

-3

0

48

-150

0

2400

 

Weight & Balance - Misc (2)

50

1

-3

0

48

-150

0

2400

 

Load:

125

 

Load Moment:

 

0

 

 

Total Weight:

550  (2)  (3)

Total Moment:

xx

0

xx

 

 

 

CofG from Origins:

xx"

0"

xx"

 

 

 

Symbol:

xCG

yCG

zCG

Dimensions are in inches and weights are in pounds.

Total weight is item quantity times item weight. 

(1) The guestimate of an electric motor at 1 lb. for 2 hp. 55 hp = 28 lbs

(2) Same as the gross weight of the SynchroLite.

(3) The weight of most of the remaining components, such as rotors etc., have not been reduced from the full UniCopter weights. They may therefor be oversized for this application or, alternatively, they may remain so that batteries and a larger engine may be added in the future.

  

Motor:

Plettenberg Predator 30. This is just for interest. Use a single large motor.

Note that there is a newer, more powerful Predator 37. ~ September 7, 2007

Tesla Motors Inc.

The motor for a high-performance electric car requires a device that is simultaneously light, compact, and high in efficiency. The Tesla Roadster EV motor is just that. We accomplish this by starting with a well-optimized electromagnetic design and then using the lowest loss conductors and the highest quality magnetic steel possible.

The power of the motor is not only limited by how much power you put into it, but also by how fast it can be cooled, how hot it can operate, and how efficiently it runs. We addressed each of these in innovative ways. Our motor can operate continuously around 120C, thanks to the array of air-cooling fins on our aluminum housing.

Without proper efficiency, our motor would convert electrical energy into heat instead of rotational energy. That's why we constructed it with specially designed, high-quality lamination steel that has very low eddy current losses, particularly at high rpm. The rotor is made with a proprietary process that produces a low resistance "squirrel cage" with large end rings using oxygen free copper. This allows the rotor to develop high current flows, and torque, with low resistance losses. The use of a small air gap allows tight inductive coupling which, combined with low loss magnetic materials, enables the development of high torque at high rpm. Together, these factors allow us to induce large currents, even at high rpm, producing much flatter power and efficiency curves from approximately 2,000 rpm to 12,000 rpm.

The sum of all these features is a single motor with efficiencies of 85 to 95 percent, power output of up to 185 kW, and a small footprint that measures just 250 mm (diameter) by 350 mm (length).

Type designation

3-phase, 4-pole electric motor

Max. net power

185kW [248hp]

Max. rpm

13,500

Efficiency

90% average, 80% at peak power

Torque

see torque curve chart

Weight

< 150 lb.

Technologies M4:

Zytek:

UQM Technologies, Inc.:

IDAM - INA Drives & Mechatronics

From bill111 at Eng Tips Forum

INA may have what your looking for all developed. http://www.ina-dam.de/en/sub.php?page=16 Their main is impossible, but the link above should get you there (will these huge companies ever get a clue as to what the engineers need).
Read the descriptions carefully. They do have inside out brushless motors, of a fairly high power level.

Radial Engine: Rotapower:

Enstroj:

OUR PRODUCTS - Electric Motors - electric propulsion systems for air-planes

 Homebuilt motor from the three existing motors ~ To be located in a large diameter worm:

  

Power Storage ~ Same Page ~ Different Craft:

  

Cooling of Motor:

  

Engine:

If a reciprocating engine is to be considered as an alternative to an electric motor then the Limbach L2400 DT/ET should be seriously looked at.

  

Power Train:

Ratio, HP, Torque & Losses: Will eventually be on a separate web page.

From full size UniCopter 1510.html and then MODIFIED

The final reduction should be 3:1 and the secondary reduction should probably be 3:1

 

At Maximum Vertical Climb:

At Maximum Forward Velocity:

 

Speed:

 

Power:

 

Torque:

 

Speed:

 

Power:

 

Torque:

 

 

Ratio:

 

Loss:

 

 

 

Ratio:

 

Loss:

 

 

 

[Motor]

4800

rpm

55

hp

60

ft-lb

4800

rpm

55

hp

60

ft-lb

 

 

 

 

 

 

 

 

 

 

 

 

 

[Prop]

0

 

0

 

0

 

2400

rpm

(55/2)*0 = 27.5

hp

60

ft-lb

 

 

 

 

 

 

 

 

 

 

 

 

 

Intermediate:

4800

rpm

55

hp

60

ft-lb

2400

rpm

27.5

hp

60

ft-lb

Secondary:

2.6

: 1

1.0

%

 

 

2.6

: 1

1.0

%

 

 

X-shaft:

1833

rpm

54.5

 

156

ft-lb

923

rpm

27.2

 

155

ft-lb

Final:

3.33

: 1

1.0

%

 

 

3.33

: 1

1.0

%

 

 

[Rotor]

550

rpm

53.9

hp

515

ft-lb

277

rpm

27.0

hp

512

ft-lb

Total:

8.65

: 1

2.0

%

 

 

8.65

: 1

2.0

%

 

 

The above [Maximum Forward Velocity] columns use an assumed speed distribution between the rotor and the propeller.

  

Controls:

  

Propeller:

  

Features to Consider:

  

Concerns:

  

Progressive Developmental Steps:

      1. Pusher Propeller.
      2. Speed Controller.
      3. Independent Root & Tip - Torque Tube Method rotor.
      4. Electric flight controls.

  

Miscellaneous:

  

Other Electric Stuff:

Related Inside Web Sites:

DESIGN: UniCopter - Power Train - Alternative Idea - Ball-Worm & Gear Reducer

Related Outside Web Sites:

Electric Aircraft Team Proposal

Goggle ["Lafayette" "E-Plane"] 415 hits

Introduction Page | SynchroLite Home Page | Electrotor Home Page | UniCopter Home Page | Nemesis Home Page | AeroVantage Home Page

Initially displayed: June 9, 2006 ~ Posted on Rotary Wing; June 9, 2006 ~ Latest revision; March 14, 2011

The above utility invention is openly and publicly disclosed on the Internet to negate an entity from patenting it, to the exclusion of all others whom may wish to use them. ~ Reference patent law 35 U.S.C. 102 A person shall be entitled to a patent unless - (a) the invention was known ... by others in this country, ..., before the invention thereof by the applicant for patent.

 

  

  

Probable Future Rotorcraft:

Gross Weight Reduction:

Small unmanned (UAV) rotorcraft for in-flight assignments.

Medium and large unmanned (UAV) rotorcraft for transportation.

~ The reason for 'unmanned' is the high power/weigh ratio of helicopters and the high pilot/payload ratio of helicopters.

Configurations:

Bilaterally symmetrical, Intermeshing and Interleaving configurations.

~ The reasons are reduced cross-couplings and improved disk loading.

Power:

All electric drive

Elimination of or minimization of gears.

~ The reasons are reduced noise and pollution.

Rotor:

Advancing Blade Concept

'Absolutely" Rigid Rotors.

Large chord and Low Tip Speed

Reverse Velocity Utilization

Flight Controls:

Active Blade Twist

Greater than 1P flight control

High Frequency Leading + Trail Edge Flaps

All electric or optical controls

Forward thrust:

Horizontal thrusters ~ propellers or ultra high bypass turbofans

Construction:

All lightweight composite construction, perhaps man-made silk.