US20120312917A1

US20120312917A1 - Tilt rotor vertical take-off aircraft - K

Info

Publication number: US20120312917A1
Application number: US13/507,084
Authority: US
Inventors: Tom Kusic
Original assignee: Individual
Current assignee: Individual
Priority date: 1998-11-16
Filing date: 2012-06-04
Publication date: 2012-12-13
Also published as: US6598827B2; US8042762B2; US20070102569A1; US20110210212A1; US20040144891A1; US20030029965A1; US8196854B2; US20100264255A1; US20100044497A1

Abstract

A vertical take-off aircraft comprising a main propeller 1 at the top of the aircraft which consists of an assembly of blades 2, 3, and a rotor 4. A drive assembly 5 rotates the propeller. The drive assembly comprises a power plant 5 a. The drive assembly is connected to the main body 6 of the aircraft by a tilt enabling joint 7. The tilt enabling joint is connected to the main body by a telescopic tube assembly comprising tubes 12 and 13. To counter the rotational force exerted on the main body 6 of the aircraft by the rotation of the blades 2, 3, an additional power plant 15 is attached to the drive assembly. Tilting the drive assembly causes tilting of the additional power plant.

Description

CROSS REFERENCE TO RELATED APPLICATIONS

This is a divisional patent application, being a division of the U.S. patent application Ser. No. 09/180,925.

STATEMENT REGARDING FEDERALLY SPONSORED RESEARCH OR DEVELOPMENT

Not applicable.

REFERENCE TO SEQUENCE LISTING

Not applicable.

BACKGROUND OF THE INVENTION

Field of the Invention

This invention relates to the vertical take-off field of aviation.

BRIEF SUMMARY OF THE INVENTION

There are many helicopters in existence today. However, helicopters rely on variable pitch rotor blades to maintain control and provide vertical lift, and the construction of helicopters with variable pitch rotors has resulted in limited operational ability when helicopters are used in forest areas, at high altitudes where the air is thin and when operating near steep mountains. Pitch varying mechanisms require frequent time consuming and expensive maintenance and a failure in the pitch varying mechanism on a helicopter often results in disaster due to instantaneous loss of control that cannot be overcome.
The present invention overcomes the need for varying the pitch of rotor blades while at the same time allowing vertical lift on take-off and directional control by providing a vertical take-off aircraft using a propeller or main blade assembly at the top of the aircraft, which main blade assembly consists of an assembly of blades.
Vertical lift is obtained by the rotation of the propeller or blade assembly thereby forcing air in a downward direction by way of the angle of pitch of the blades. Rotation of the propeller or main blade assembly is achieved using an engine assembly and a rotor located between the main body of the aircraft and the blades of the propeller or main blade assembly, which engine assembly is a rotor drive assembly which rotates the rotor, and which main engine assembly is connected to the main body of the aircraft by a tilt enabling joint. The tilt enabling joint consists of numerous components, some of which provide the means to support the main body of the aircraft below the main engine assembly and allow the tilt enabling joint to have a tilting ability while other components provide the means to control and cause tilting motions in the tilt enabling joint during flight, thereby enabling controlled tilting to occur, such that the main engine assembly and the main blade assembly can be tilted together as a unity relative to the main body of the aircraft in a controlled manner during flight, thereby providing a means for controlling the directional travel of the aircraft during flight and changing the aircraft's direction of travel. The main blade assembly and the main engine assembly can be merged in the form of turboprop. That is, the aircraft could comprise a turboprop at the top of the aircraft, which is connected to the main body of the aircraft by a tilt enabling joint, with vertical lift being achieved by means of the blades of the turboprop forcing air in a downward direction.
During flight, rotational stability of the main body of the aircraft is maintained by means of an additional engine assembly attached to the aircraft which rotates an additional propeller or blade assembly, thereby pushing air primarily in a horizontal direction to counter the rotational force exerted on the main body of the aircraft by the rotation of the upper main blade assembly, which additional blade assembly consists of an assembly of blades.
The additional propeller or blade assembly and the additional engine assembly can be merged in the form a turboprop or even a jet engine.
Hence, in one form the aircraft could comprise a turboprop at the top of the aircraft to force air in a downward direction, which turboprop is connected to the main body by a tilt enabling joint, and an additional turboprop to force air to travel in a horizontal direction to counter the rotational force exerted on main body of the aircraft by operation of the main turboprop at the top of the aircraft.
In another form of the aircraft, the aircraft could comprise a turboprop at the top of the aircraft, connected to the main body of the aircraft by a tilt enabling joint, and a jet that can force exhaust gas to travel in a horizontal direction to counter the rotational force exerted on the main body of the aircraft by operation of the turboprop at the top of the aircraft.
As can be seen from the diagrams that follow, the present invention makes many of the components needed to construct a conventional helicopter obsolete, while providing an aircraft that can perform not only tasks normally performed by conventional helicopters but also other tasks that conventional helicopters cannot perform due to their configuration necessitated by variable pitch rotors—such as landing among trees in a forest without cleared landing zones, and grasping trees growing in a forest with grasping mechanisms to gain support and stability by grasping trees.

BRIEF DESCRIPTION OF THE SEVERAL VIEWS OF THE DRAWINGS

Embodiments of the invention will now be described by way of example with reference to the accompanying drawings, of which:

FIG. 1 is a view of the left side of one form of aircraft according to this invention.

FIG. 2 is a view of the right side of the aircraft of FIG. 1.

FIG. 3 is a view of the front of yet another form of aircraft according to this invention.

FIG. 4 is the left side view of the aircraft of FIG. 3.

FIG. 5 is an enlarged view of a universal joint.

FIG. 6 is a rotated view of the universal joint of FIG. 5.

FIG. 7 shows the rotor drive assembly comprising two power plants.

FIG. 8 shows one form of the aircraft with the additional engine assembly and additional rotor assembly replaced by a jet engine.

FIG. 9 shows how variable pitch fins could be positioned on the aircraft.

FIG. 10 shows how one form of the aircraft could be used to evacuate people from the side of a building.

FIG. 11 shows how the aircraft could make contact with the side of steep mountain while the rotors are kept at a safe distance.

FIG. 12 shows that by keeping the main rotor at a large distance from the main body of the aircraft, the aircraft would be able to land among trees while the main rotor is kept above the trees, and grasp surrounding trees with grasping mechanisms.

FIG. 13 shows a enlarged view of a grasping mechanism used by the aircraft of FIG. 12.

FIG. 14 shows that as many as eight rotor blades can be assembled around a small rotor hub when blade pitch varying components are not required.

DETAILED DESCRIPTION OF THE DRAWINGS

FIG. 1 shows one form of aircraft according to this invention.
Looking at the aircraft in FIG. 1 it can be seen that the aircraft consists of a main propeller 1 at the top of the aircraft, which main propeller consists of an assembly of blades 2 and 3. A rotor 4 is connected to the bottom of the propeller 1. The rotor 4 connects the propeller 1 to a drive assembly 5. The drive assembly is an assembly that can cause the rotor 4 to rotate thereby causing the propeller 1 to rotate. The drive assembly comprises a power plant 5 a which provides power for the drive assembly to rotate the rotor 4. Vertical lift is achieved by the rotation of the main propeller 1. Rotation of the main propeller forces air in a downward direction over the main body of the aircraft by way of the angle of pitch of the blades 2 and 3. The blades 2 and 3 are above the drive assembly 5. The drive assembly is connected to the main body 6 of the aircraft by a tilt enabling joint 7. The tilt enabling joint 7 allows tilting of the drive assembly 5 relative to the main body 6 of the aircraft to occur in a controlled manner. A universal joint 8 is used to allow tilting to occur. The tilt enabling joint 7 is fitted with a combination of hydraulic actuators 9, 10 and 11, that allow the tilting of the tilt enabling joint 7 to be controlled.
Tilting of the drive assembly 5 initiates changes in the direction of travel of the aircraft without the need to change the pitch angles of the blades 2 and 3. The tilt enabling joint 7 is connected to the main body 6 by telescopic tube assembly comprising oblong shaped tubes 12 and 13. The base 14 of the tilt enabling joint is connected to tube 12.
To counter the rotational force exerted on the main body 6 of the aircraft by the rotation of the main propeller, FIG. 1 shows an additional power plant 15 connected to the drive assembly 5. The additional power plant 15 comprises an engine 16, and blades 17 and 18 in the form of a propeller, and a rotor 19. Rotation of the propeller of the additional power plant pushes air in a primarily horizontal direction by way of the pitch of the blades 17 and 18. By forcing air to travel in a horizontal direction, the additional power plant acts to counter the rotational force exerted on the main body 6 of the aircraft by the rotation of the main propeller. Tilting of the drive assembly thus causes the additional power plant to move relative to the main body of the aircraft.
FIG. 2 shows the aircraft of FIG. 1 rotated horizontally 180 degrees to show the hydraulic actuator 10 a on right side of the tilt enabling joint.
FIG. 3 shows the front view of another form of the aircraft with handles 20 and 21 forming part of the tilt enabling joint 7. The handles 20 and 21 are attached to the upper section of the tilt enabling joint. The tilting ability of the tilt enabling joint is achieved by the universal joint 8. The aircraft has a main propeller 1 which is rotated by a drive assembly 5. Directional control of the aircraft during flight is achieved by controlled tilting of the drive assembly relative to the main body 6 of the aircraft, thereby tilting the main propeller 1. Controlled tilting of the drive assembly 5 during flight is enabled by the handles 20 and 21. Moving the handles 20 and 21 relative to the main body of the aircraft 6 would be capable of causing a forward and rearward tilting of the main drive assembly, as well as sideways tilting. The tilt enabling joint is connected to the main body by a telescopic tube assembly comprising oblong shaped tubes 22 and 23. A seat 24 is positioned in the main body for the pilot.
FIG. 4 is the left side view of FIG. 3, showing the position of the left handle 20 from a side view and the additional power plant 15.
FIGS. 5 and 6 show the universal joint 8 of the tilt enabling joint of FIG. 1. FIG. 6 is FIG. 5 rotated 90 degrees horizontally.
FIG. 7 shows a version of the aircraft with the main drive assembly 5 comprising two power plants 25 and 26. The drive assembly in FIG. 1 comprised a single power plant. An assembly 26 a enables the power plants 25 and 26 to rotate the rotor 4.
FIG. 8 shows a version of the aircraft of FIG. 1 with a jet engine 27 replacing the additional power plant 15 shown in FIG. 1. The jet engine is connected to the main drive assembly. The jet engine shown is a turbojet. In another form of the aircraft, the jet engine is a turbofan.
FIG. 9 shows how variable pitch fins 28 and 29 could be positioned on the aircraft. The variable pitch fins could augment control of the aircraft, and could be used as airbrakes. They could also provide lift during high speed forward flight, such as wings on an airplane, since downward airflow from the main rotor assembly would be directed to the rear of the aircraft, due to the tilting of the main rotor assembly in a forward direction and the distance of the main rotor assembly from the variable pitch fins.
FIG. 10 shows how an aircraft according to this invention could be used as an evacuation vehicle for persons trapped in a building 30. An extension ladder 31 secured to the main body 6 of the aircraft is shown in extended form, with a basket 32 at the end of the extension ladder. FIG. 10 shows how a person 33 could be rescued from the building. The large distance between the main rotor and the main body of the aircraft makes the main body 6 of the aircraft act like a keel on a yacht, so that an extension ladder has a minimal effect on the ability to control the aircraft. The main body could be tilted slightly, while the main rotor assembly could be maintained in a level position.
FIG. 11 shows how the aircraft could be used to quickly unload supplies on the side of a steep mountain 34, or quickly evacuate injured persons without having to use a winch. The relatively short distance between the main rotor and the main body of a conventional helicopter would prevent the main body of a conventional helicopter being able to make contact with such a steep mountain without a high risk of the rotor blades impacting with the mountain.
FIG. 12 shows how a form of the aircraft could land between trees 35 and 36, while the main rotor assembly is kept above the tops of the trees. Cargo could be loaded and unloaded or injured persons evacuated without using a winch. Grasping mechanisms 37 and 38 are shown grasping trees 35 and 36 respectively, providing support and stability for the aircraft while a sharpened section 39 protruding beneath the main body bears some of the weight of the aircraft. The aircraft could land in an area such as a forest where the rotors of a conventional helicopter would impact with the trees. The aircraft would not require a cleared landing zone to land in a forest. In a war, the possible landing area would be less predictable by an enemy force, reducing the risk of an ambush around a cleared landing zone. If the aircraft was operated on a battle field and the aircraft was targeted by a heat seeking missile during flight, having the main power plant and the additional power plant located away from the main body of the aircraft would provide the occupants with a greater chance of survival than if the main power plant was attached directly to the main body of the aircraft if the missile caused a fire at the main power plant.
FIG. 13 shows the grasping mechanism 38 from FIG. 12 as viewed from above. The grasping mechanism comprises a moveable component 42 a which can be moved towards a rigid component 42 b by hydraulic actuator 43 a. Expansion of the hydraulic actuator 43 a creates a grasping motion between 42 a and 42 b. The grasping mechanism is connected to the main body of the aircraft by a hollow beam 40 a, which can be extended outward by means of hydraulic actuator 41 a, such that the beam 40 a can operate in a telescopic manner sliding in and out of an enclosure 40 b. The enclosure 40 b is connected to the main body of the aircraft by a bolt 41 b, which enables the enclosure 40 b to swivel relative to the main body. The swiveling motion of the enclosure 40 b is controlled by hydraulic actuator 43 b. Hydraulic actuator 43 b is connected to the enclosure 40 b and the main body of the aircraft.
FIG. 14 shows how eight rotor blades 44, 45, 46, 47, 48, 49, 50, 51, can be assembled around a rotor 4, forming a propeller 1, when space is not required for blade pitch varying components. This number of rotor blades would allow the main rotor assembly to be rotated at a lower rate of revolution than a rotor assembly with fewer blades, to achieve the same lifting ability, resulting in a relatively quieter aircraft. Having a high number of rotor blades would help the aircraft to operate in high altitude mountainous regions or hot regions, where the air is thin.

Claims

1. A vertical take-off aircraft consisting of a main body, a propeller, and a means for rotating the propeller, which means for rotating the propeller comprises at least one power plant, and which propeller is above the means for rotating the propeller, with vertical lift able to be achieved by the means for rotating the propeller rotating the propeller, thereby forcing air in a downward direction by means of the propeller, and which aircraft comprises at least one additional power plant, which at least one additional power plant is able to produce thrust extending in a lateral direction relative to the main body of the aircraft such that a rotational force exerted on the main body of the aircraft by rotation of the propeller can be countered,

and which means for rotating the propeller and the propeller are connected to the main body of the aircraft by a tilt enabling joint such that the means for rotating the propeller and the propeller are able to be tilted together in a plurality of directions and angles relative to the main body of the aircraft, in a controlled manner.

2. A vertical take-off aircraft consisting of a main body, a rotor and blade assembly, and a means for rotating the rotor and blade assembly, which means for rotating the rotor and blade assembly comprises at least one power plant, and which rotor and blade assembly comprises an assembly of blades and a rotor, and which blades are above the means for rotating the rotor and blade assembly, with vertical lift able to be achieved by the means for rotating the rotor and blade assembly rotating the rotor and blade assembly, thereby forcing air in a downward direction by means of the blades, and which aircraft comprises at least one additional power plant, which at least one additional power plant is able to produce thrust extending in a lateral direction relative to the main body of the aircraft such that a rotational force exerted on the main body of the aircraft by rotation of the rotor and blade assembly can be countered, and which means for rotating the rotor and blade assembly and the rotor and blade assembly are connected to the main body of the aircraft by a tilt enabling joint such that the means for rotating the rotor and blade assembly and the rotor and blade assembly are able to be tilted together in a plurality of directions and angles relative to the main body of the aircraft, in a controlled manner.

3. A vertical take-off aircraft comprising a means for downwardly extending thrust, a main body, and a means for extending thrust in a lateral direction relative to the main body, which means for downwardly extending thrust is connected to the main body by a tilt enabling means such that the means for downwardly extending thrust is able to be tilted in a plurality of directions and angles relative to the main body, in a controlled manner, and which means for extending thrust in a lateral direction is connected to the main body such that tilting of the means for downwardly extending thrust relative to the main body is able to cause the means for extending thrust in a lateral direction to move relative to the main body.

4. A vertical take-off aircraft comprising a means for downwardly extending thrust and a main body, which means for downwardly extending thrust is connected to the main body by a tilt enabling means such that the means for downwardly extending thrust is able to be tilted in a plurality of directions and angles relative to the main body, in a controlled manner, and which tilt enabling means is connected to the main body such that the distance between the base of the tilt enabling means and the main body is able to be varied and such that means for downwardly extending thrust is able to be raised and lowered relative to the main body without being tilted relative to the main body.

5. A vertical take-off aircraft comprising a means for downwardly extending thrust and a main body, which means for downwardly extending thrust is connected to the main body by a tilt enabling means such that the means for downwardly extending thrust is able to be tilted in a plurality of directions and angles relative to the main body, in a controlled manner, and which tilt enabling means is connected to the main body such that the distance between the base of the tilt enabling means and the main body is able to be varied and such that the tilt enabling means is able to be vertically aligned with the main body.

6. A vertical take-off aircraft comprising a means for downwardly extending thrust, a main body, and a means for extending thrust in a lateral direction relative to the main body, which means for downwardly extending thrust is connected to the main body by a tilt enabling means such that the means for downwardly extending thrust is able to be tilted in a plurality of directions and angles relative to the main body, in a controlled manner, and which tilt enabling means is connected to the main body such that the distance between the means for downwardly extending thrust and the main body is able to be varied and such that the means for downwardly extending thrust is able to be raised and lowered relative to the main body, and which means for extending thrust in a lateral direction is connected to the main body such that the means for extending thrust in a lateral direction is able to be raised and lowered relative to the main body, and such that raising and lowering the means for downwardly extending thrust relative to the main body is able to cause the means for extending thrust in a lateral direction to be raised and lowered, respectively.

7. The vertical take-off aircraft of claim 4, wherein the vertical take-off aircraft comprises a means for extending thrust in a lateral direction relative to the main body, which means for extending thrust in a lateral direction is connected to the main body such that the means for extending thrust in a lateral direction is able to be raised and lowered relative to the main body, and such that raising and lowering the base of the tilt enabling means relative to the main body is able to cause the means for extending thrust in a lateral direction to be raised and lowered, respectively.

8. The vertical take-off aircraft of claim 1, wherein the which means for rotating the propeller and the propeller are connected to the main body of the aircraft by the tilt enabling joint such that the means for rotating the propeller and the propeller are able to be tilted together in a plurality of directions and angles relative to the main body of the aircraft, in a controlled manner, and such that the main body of the aircraft is able to be vertically aligned with the means for rotating the propeller.

9. The vertical take-off aircraft of claim 2, wherein the which means for rotating the rotor and blade assembly and the rotor and blade assembly are connected to the main body of the aircraft by the tilt enabling joint such that the means for rotating the rotor and blade assembly and the rotor and blade assembly are able to be tilted together in a plurality of directions and angles relative to the main body of the aircraft, in a controlled manner, and such that the main body of the aircraft is able to be vertically aligned with the means for rotating the rotor and blade assembly.