Aeronautics and astronautics – Aircraft – heavier-than-air – Airplane and fluid sustained
Reexamination Certificate
1999-09-16
2001-08-07
Jordan, Charles T. (Department: 3644)
Aeronautics and astronautics
Aircraft, heavier-than-air
Airplane and fluid sustained
C244S02300R
Reexamination Certificate
active
06270036
ABSTRACT:
FIELD OF INVENTION
The present invention relates to a new and unobvious type of a circular or round rotating airfoil aircraft and methods associated with enabling aircraft flight. More particularly, the present invention is directed to a new and unobvious aircraft which utilizes in flight an actively blown circular or round airfoil to produce vertical lift.
BACKGROUND OF THE INVENTION
Man has been able to cause powered aircraft to fly through the atmosphere since the early part of the Twentieth Century. Much work has been done and continues to be done in developing improved and more versatile aircraft.
The most commonly used type of aircraft today requires enormous landing strips for take off and landing. However, over the years, much work has been done in attempting to develop suitable, practical and improved vertical take off and landing (VTOL) aircraft. These have included helicopters as well as dirigibles, balloons and blimps.
Lighter-than-air- aircraft such as dirigibles and the like which utilize helium or other lighter-than-air gases have the disadvantage of not only the need to supply the lighter-than-air gas itself, the need to increase and decrease the volume of the gas for ascent and descent, the substantial structure, including its weight, for containing the lighter-than-air gas and the very large structure sizes required to house gases which are only somewhat lighter than air.
Helicopters are a much heavier-than-air aircraft requiring rotating propeller blade structures. Some attempt has also been made for providing vertical take off either by the means of propellers or rockets, sometimes mounted on wings which may be directed vertically for take off and horizontally for lateral flight.
However, none of these prior art devices nor any combination of them teaches or suggests a new class of aircraft as discussed and claimed herein.
SUMMARY OF THE INVENTION
The present invention creates a new category of aircraft or air transport vehicle. The present invention further includes new methods of achieving vertical take off and landing and flight in an economical, efficient and effective manner.
The present invention provides numerous advantages. An advantage of the present invention is that it provides an aircraft with vertical take off and landing (VTOL) capabilities thereby eliminating the need for enormous take off and landing runways. The VTOL capabilities of the present invention significantly reduce infrastructure requirements at ground-based air terminal facilities with consequent and substantial reductions in the environmental and economic impacts of such terminals, regardless of whether there are a small number of large terminal facilities or a large number of small terminal facilities.
Another advantage of the present invention is that its VTOL capabilities substantially improve the safety attributes of the aircraft as contrasted with most conventional aircraft since emergency landings may be safely conducted at vastly more locations.
Another advantage of the present invention is reduction in likelihood of sudden precipitous descent typically encountered by aircraft such as helicopters on the occurrence of a mechanical failure.
Another advantage of the present invention is that it provides an aircraft with a rotating airfoil that provides significant inertial stability to the total aircraft to resist outside disturbances and, therefore, provide a smooth flight.
Another advantage of the present invention is that it is able to provide such an aircraft constructed and operated as a light-weight vehicle by utilizing centrifugal force to provide structural rigidity to the rotating airfoil. This structural rigidity resulting from centrifugal force provides resistance to the external forces associated with airfoil lift and provides resistance to the external forces associated with aerodynamic pressure on the airfoil that occur when the aircraft is traveling in a lateral direction.
Another advantage of the present invention is the ability to provide control in flight utilizing both the lift of a blown rotating airfoil as well as the conventional lift provided by a conventional airfoil moving laterally depending upon the conditions of flight.
Another advantage of the present invention is that it provides an aircraft that is capable of both high speed, long distance, intercontinental operations as well as being a highly maneuverable VTOL aircraft thereby enabling a given volume of airspace to be safely occupied by a substantially larger number of aircraft.
Another advantage of the present invention is that it provides more efficient airspace utilization both at terminal locations as well as in areas between such terminal or airport locations thereby helping to reduce the growing problem of airspace congestion.
Another advantage of the present invention is that it provides an aircraft that is significantly more economical to manufacture and to operate and one that utilizes infrastructure and environmental resources much more efficiently.
Another advantage of the present invention is that it provides an aircraft that is significantly more fuel efficient thereby reducing the cost of air transport as well as reducing consequent chemical and noise pollution of the atmosphere.
Another advantage of the present invention is that aircraft based on the present invention may also incorporate the unique features, benefits and advantages provided by the invention entitled Evacuated Rotating Envelope Aircraft, of U.S. Pat. No. 6,016,991, particularly for larger aircraft.
Another advantage of the present invention is that it provides an aircraft that incorporates a rotating airfoil that provides the primary source of lift during lateral flight. The fact that this airfoil rotates provides an opportunity for cooling of the leading edge of the airfoil as portions of it rotate into and out of the area of maximum aerodynamic heating.
Briefly and basically, in accordance with the present invention, an aircraft is disclosed wherein vertical lift is provided by means of a blown rotating airfoil. In other words, in accordance with the present invention, air is caused to flow over a rotating airfoil producing reduced pressure above the airfoil and airflow is directed downwardly under the rotating airfoil, both producing an upward force or lift on the aircraft. The invention also contemplates employing the centrifugal force or inertial force of rotation of the rotating airfoil to augment the structural rigidity of the aircraft and to thereby improve its cost effectiveness. The terms centrifugal force and inertial force of rotation are used herein throughout interchangeably.
Further, in accordance with the present invention, the means for rotating the envelope is attached to the rotating airfoil and rotates with the airfoil. The means for rotating the envelope may be an engine (et, turbojet, turbofan or even turboprop), which provides sufficient force to rotate the airfoil against the force of air friction acting upon the external surfaces of the airfoil and to operate the centrifugal air fan(s) rotating with the airfoil.
Further, in accordance with the present invention, means such as exhaust baffles or deflectors are provided for dividing the output air exhaust of the central engine(s) into multiple flow streams with a purpose of creating a rotating torque force on the central engine(s) and the attached airfoil.
Further, in accordance with the present invention, the means for rotating is selected to provide rotation necessary to provide a sufficient centrifugal force on the material of the rotating airfoil whereby the need for and weight of mechanical support structures to withstand lifting forces and the forces produced by aerodynamic pressures on the airfoil may be reduced and/or minimized.
Further, the means for rotation of the envelope causes the envelope to rotate about an axis normal to the direction of lateral motion of the aircraft during flight thereby exposing the leading edges and surfaces of the airfoil to aerodynamic heating caused by contact with atmosphere during only a portion o
Best Christian M.
Jordan Charles T.
Petock, Esq. Michael F.
LandOfFree
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