Aeronautics and astronautics – Aircraft – heavier-than-air – Airplane and helicopter sustained
Reexamination Certificate
1998-12-01
2001-05-22
Barefoot, Galen L. (Department: 3644)
Aeronautics and astronautics
Aircraft, heavier-than-air
Airplane and helicopter sustained
C244S00700B, C244S017110, C416S019000, C416S024000
Reexamination Certificate
active
06234422
ABSTRACT:
GROSS-REFERENCE TO RELATED APPLICATIONS
Not Applicable
STATEMENT REGARDING FEDERALLY SPONSORED RESEARCH OR DEVELOPMENT
Not Applicable
BACKGROUND OF THE INVENTION
1. Field of the Invention
This invention is related to air flight vehicles, such as apparatus of vertical take off and landing (VTOL), helicopters, covercraft, flighting automobiles, motorcycles, and traditional airplanes.
2. Description of the Related Art.
Known in art are helicopter rotors having 2, 3, 4, 6 and more blades (Jane's Aircraft Directory, 1995-1996), (
FIG. 1
a-d
). Requirement of 2 or more blades is dictated by the blades aerodynamic force and weight balance. Total resultant lift force of blades thrust must act along blade axis O (
FIG. 1
) and blades' centrifugal force must be balanced, while the blade horizontal axis O
i
is located close to vertical axis O, but O
i
and O do not cross each other (
FIG. 1
e
).
BRIEF SUMMARY OF THE INVENTION
The goal of this invention is to create an air rotor designed so that while in flight, it can be stopped, fixed in a specific position and hidden into the fuselage (gondola
0
thus eliminating air drag when the rotor is not in working state.
On lending this rotor can be extended out, brought into rotation and used for creation of lift force and vertical landing.
The indicated goal is achieved by means of the rotor made as single blade (uniblade). The center of gravity of the counter weight B (
FIG. 2
) is located below the horizontal blade plane, and blade has the horizontal sway axis O
1
that crosses the vertical rotor's rotation axis O (
FIG. 2
a
).
Uniblade rotor has huge advantages when compared to a helicopter rotor with 2,3 of more blades. The uniblade rotor can be stopped (in direction of air stream) and moved in to the fuselage (gondola). In hidden position, the uniblade rotor does not interfere with the air flow whereby the air vehicle can reach designed speed, even supersonic speed. On landing, the uniblade rotor is easy to move out of the fuselage, bring into rotation and make landing in helicopter mode.
However, the uniblade rotor posses a problem of the blade balancing. The most important of which is that large unbalanced blade lifting force P rotates along circumference Q together with the blade at angular speed &ohgr; (
FIG. 2
b
) and creates large capsizing moment, direction of which also changes (rotates).
In order to eliminate these negative effects, the inventor proposes to place the blade counterbalance B. The counter balance gravity center is shifted down (distance CB in
FIG. 2
a
) from the blade plane, and for elimination of the capsizing moment, the axis of horizontal swing O of the blade is located so that it crosses rotation axis O of the engine power drive.
REFERENCES:
patent: 2173291 (1939-09-01), Ash
patent: 2297815 (1942-10-01), Tidd
patent: 2418274 (1947-04-01), Nemeth
patent: 2471687 (1949-05-01), Holmes
patent: 2742095 (1956-04-01), Pitcairn
patent: 3074487 (1963-01-01), Dershmidt
patent: 3166129 (1965-01-01), Bryan
patent: 3490720 (1970-01-01), Girard
patent: 3693910 (1972-09-01), Aldi
patent: 4528564 (1985-07-01), Trampnau
patent: 4793572 (1988-12-01), Mecca
patent: 4874291 (1989-10-01), Roberts et al.
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