Item 1505
OTHER:
Helicopter - Inside - Interleaving - Pros & Cons vs. Tilt-rotorTilt-rotor
Interleaving
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Advantages:
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Disk Area:
Drawing:

The Interleaving disks can be significantly reduced in size, and the stagger reduced, while still provide a lower disk loading than the Tilt-rotor can.
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Tilt-rotor vs. Interleaving:
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Tilt-rotor vs. Interleaving, Intermeshing & Coaxial, during Forward Flight:
In addition ![]()
Tilt-rotor vs. Intermeshing:
Intermeshing vs. Interleaving:
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Supporting Information for the Above Statements:
Calculation used for obtaining the area of overlap: The overlapping area is only counted once. (Angle is in Radians.)
A = 1/2 (R2
(θ - sinθ)) = 1/2 (10 * 10 (2.891 - sin(2.891))) = 1/2 (100 (2.891 - 0.050)) = 1/2 (100 * 2.841) = 142.05The following table and notes uses nondimensionalized numbers for the comparison. The shaded values are the actual dimensions of V-22, in feet.
A single rotor and a comperable Intermeshing configuration are also added for interest.
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|
Individual Twin Disk: |
Intermeshing Twin Disks: |
Interleaving Twin Disks: |
Tilt-rotor V-22 |
|
Radius of Individual Disk: |
10 |
10 |
10 |
10 [19.04 1] |
|
~ |
2.5 |
11 |
11 [46.58 1] |
|
|
Total Area of Disks: |
314.3 |
628.6 |
628.6 |
127.3 [9114.8 1] |
|
Area of Overlap (Circular Segments): |
~ |
284.1 |
107.1 |
~ |
|
Area Excluding Overlaps: |
260.75 |
344.5 |
521.5 |
127.3 [9114.8 1] |
|
Total Lateral Span: |
20.0 |
22.5 |
31.0 |
20 [84.55 1] |
|
Total Longitudinal Span: |
20.0 |
20.0 |
20.0 |
9 [76.16 1] |
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Additional Advantages:
OTHER: Aerodynamic - Rotor Disk - Dual Configuration - Interleaving ~ Advantages
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Concerns:
The inability to fold the rotor blades due to the extreme rigidity of the rotors. Swinging the complete rotors back and inward will reduce the footprint somewhat.
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"At stage lengths of about 200 n. mi., where the maximum number of revenue flights occur, rotary wing cruise speeds of about 240 knots are required to produce the same block speeds as existing jet transports." ~
from the 1977 report, 'A review of Advanced Rotorcraft Research'.This should be obtainable from today's technology, particularly if active blade twist and individual blade control were to be implemented.
However to achieve faster speeds, and therefore a longer range, reverse velocity utilization or some other type of configuration such as perhaps the AeroVantage will be required.
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Comparison ~ Wayne Johnson's Coaxial & Side-by-Side(1) to V-22 Osprey and Mil V-12:
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|
Coaxial (1) |
Side-by-Side (1) |
V-22 Osprey (2) |
Russian Mil V-12 (1969) (3) |
|
Rotor diameter: (ft) |
113.1 |
113.1 |
38' |
114'-10" |
|
Width with rotors: (ft) |
113.1 |
260 |
84'-7" |
223' |
|
Disk area: (sq-ft) |
10,051 |
20,101 |
2268 |
20;782 |
|
Maximum takeoff weight: (lb) |
149,681 |
149,715 |
60,500 |
213,850 |
|
Disk loading: (lb/sq-ft) |
15 |
7.5 |
20.9 |
10.3 |
|
Total power: (hp) |
21,812 |
16,644 |
12,300 |
26,000 |
|
Power to mass: (hp/lb) |
0.146 |
0.111 |
0.259 |
0.122 |
|
Cruse Speed: (kts) |
250 |
250 |
241 |
140 |
(1) Influence of Lift Offset on Rotorcraft Performance by Wayne Johnson
(2)
(3)
Wikipedia ~ Russian Mil Mi-12![]()
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Last Revised: August 3, 2010