HYBRID AIRCRAFT

Abstract: A hybrid aircraft with a large non-rotating balloon chamber (1) containing a lighter-than-air gas which provides a large static lifting force having a magnitude substantially greater than the weight of the aircraft. It comprises a support structure (20) which is substantially longer in length than in width and is encased within the balloon chamber (1). The support structure system has two ends (22) which protrude from the balloon chamber at opposite sides along the center line of the balloon chamber. A rotatable rotor frame (15) is suspended to the ends of the support structure about the non-rotating balloon chamber. The aircraft has a plurality of blade airfoils (4) connected to the rotor frame and oriented radially relative to the balloon chamber. The angle of attack of each blade can be varied. A thrust means is mounted at or near the outboard end of the blade airfoils. A wing airfoil perpendicularly connected to the end of each blade airfoil at the same end as the thrust means. The angle of attack of each wing airfoil can be varied. The aircraft also has a cab, a load line, and an anti-torque device as required.

Description: HYBRID AIRCRAFT BACKGROUND OF THE INVENTION a) Field of the invention The present invention relates to an aircraft that is capable of ultra-heavy lifting at a slow speed for extended periods of time without refueling. More particularly, the invention relates to a hybrid aircraft that provides both aerostatic and aerodynamic lift. The hybrid aircraft according to the invention, which is particularly useful in both the logging and construction industries, can be briefly disclosed as a semibuoyant composite aircraft comprising a non-rotating aerostat. b) Brief description of the Prior art Semi-buoyant composite aircrafts have already been devised, with a balloon rotating about a vertical axis (see GB-A-1,460,822 and CA-A-1,171,835) . These known aircrafts are efficient but suffer from a substantial increase of crag (3 fold) and side force resulting from the Magnus effect due to the rotation of their balloon. SUMMARY OF THE INVENTION The object of the present invention is to provide 25 a semi-buoyant composite aircraft comprising a balloon that is non-rotating, thereby eliminating the Magnus effect for vertical axis vehicles and the difficult problems associated with the existence of a rotating balloon having a horizontal axis. The invention can be broadly disclosed as a hybrid aircraft with a large non-rotating, balloon chamber containing a lighter-than-air gas which provides a large static lifting force having a magnitude greater than the empty weight of the aircraft. A support structure system ET which is substantially longer in length than in width is encased within the balloon chamber. The support structure system has two ends which protrude from the balloon chamber at opposite sides thereof, along the center line of the balloon chamber. A rotatable rotor frame is suspended from the ends of the support structure system about the nonrotating balloon chamber. Blade airfoils are connected to the rotor frame and are oriented radially relative to the axis. The angle of attack of these blade airfoils can be varied. A thrust means is mounted at or near the outboard end of the blade airfoils. Wing airfoils are perpendicularly connected to the end of the blade airfoil at the same end as the thrust means. The angle of attack of these wing airfoils can also be varied. The aircraft further comprises a cab, a load line and two anti-torque devices when the aircraft has a vertical axis, one to keep the balloon chamber from rotating and the other to maintain and/or adjust the heading of the cab. The aircraft can have either a vertical or horizontal axis. A non-restrictive description of some preferred embodiments of invention will now be given with reference to the accompanying drawings. BRIEF DESCRIPTION OF THE DRAWINGS Fig. 1 is a pictorial partially broken away view of an aircraft with a vertical axis according to the invention, with the aircraft lifting an entire tree from a forest. Fig. 2 is a top plan view of the aircraft with a vertical axis. Fig. 2a is a side view of the aircraft with a vertical axis. Fig. 3 is a schematic top plan view of the aircraft with a vertical axis, showing the angle of attack of the vertical wings in trail, or neutral pitch, when the aircraft is in hover or vertical flight. Fig. 3a is a schematic top plan view of the 5 aircraft with a vertical axis showing the angle of attack of the vertical wings in cyclic pitch when the aircraft is in horizontal flight. Fig. 4 is an enlarged side elevation of the aircraft with a vertical axis, showing a portion of the vertical axis, control cab and tail rotor. Fig. 5 is a pictorial view of an aircraft with a horizontal axis according to the invention, showing the gas containment chamber in phantom. Fig. 6 is a side elevation of the aircraft with a 15 horizontal axis. Figs. 7, 8 and 9 are front elevations of the aircraft with horizontal axis showing the various positions of the blades and wings in flight. Figs. 7a, 8a, and 9a are side elevations of the 20 aircraft with a horizontal axis showing the various positions of the blades and wings shown in figs. 7, 8, and 9. Fig. 10 is a fragmented view of the bottom axle with terminals for hull attachment cables and anti-torque device. DETAILED DESCRIPTION OF THE INVENTION The aircraft with a vertical axis according to the invention as shown in figs. 1 to 4 comprises a support structure 20 oriented vertically and encased within a balloon chamber 1. It also comprises a rotor frame 15 held by means of suspension cables 38 which are connected to the support structure 20 at top terminal 22 and the lower terminal 28. Hull attachment cables 36 position the balloon chamber 1 within the rotor frame 15. A plurality of blade airfoils 4 are connected to the rotor frame. At the end of each blade airfoil 4 are vertical wing airfoils 8 and a thrust means 12. The thrust means causes the rotor frame 15 to rotate around the stationary balloon chamber 1. The thrust means can be a conventional internal combustion engine with a propeller through it is not limited to this means as other means would work effectively also. Peripheral cables 39 hold the blade airfoils 4 in the proper position. A control cab 46 is suspended from the lower terminal 28. An anti-torque device 47 is attached to the control cab. In the embodiment shown in fig. 1, the anti-torque device is a propeller but other similar devices are known to one skilled in this art. Fig. 2 is a top plan view and shows the balloon chamber 1 enclosed with the rotor frame 15. The balloon chamber 1 is positioned by the hull attachment cables 36. The blade airfoils are connected to the rotor frame. The angle of attack of the blade airfoils can be adjusted collectively and cyclicly to creating no lift, positive lift or negative lift. Fig. 2a is a side view of the aircraft with a vertical axis. The balloon chamber 1 extends above and below the rotor frame 15. The balloon chamber is positioned by the hull attachment cables 36 and the peripheral cables 38 position the airfoils 4 in the proper position. Fig. 3 shows the angle of attack of the vertical wings 8 in trail or neutral pitch, when the aircraft is in hover or vertical flight. Fig. 3a shows the angle of attack at four points of the vertical wings 8 in cyclic pitch when the aircraft is in horizontal flight. In these figures the curved arrows show the direction of the rotation of the rotor frame 15 and the arrow in fig. 3a shows the direction of motion of the aircraft based on the cyclic pitch of the vertical wings 8. Fig. 4 shows the control cab 46 with the anti-torque propeller 47. The bottom axle 30 with terminals for ' the hull attachment cables 36 is connected to the support SUBSTITUTE SHEET structure 20. The suspension cables 38 are connected to the bottom bearing housing 28. An additional anti-torque device to keep the cab in the desired heading is shown in fig. 10. The motor 44 drives a spur gear 42 which interacts with the ring gear 41. Fig. 5 shows an aircraft a horizontal axis according to the invention. In this figure, the same reference numeral as above have been used to identify the same structural elements. The aircraft of fig. 5 has support structure 20 in the horizontal position and a balloon chamber 1 surrounding it. The support structure 20 protrudes out of the balloon chamber 1. A rotor frame 15 encircles the balloon chamber 1. Attached to the rotor frame is a set of blade airfoils 4. The angle of attack of the blade airfoil can be adjusted. At the end of each blade airfoil 4, a wing airfoil 8 is perpendicularly mounted. The angle of attack of the wing airfoil can be adjusted. A thrust means 12 is mounted at or near the blade airfoil 4. The thrust means causes the rotor frame 15 to rotate around the balloon chamber 1. Longitudinal brace cables connect the forward bearinq housing 22 to the aft bearing housing 23 and position the rotor frame 15. Peripheral brace cables 39 position the blade airfoils 4 in a radial direction from the balloon chamber 1. A tail assembly 6 is mounted to the aft axle 31. A control cab 46 is suspended by control cab suspension cables 21 which are attached to the forward axle 30 and the aft axle 31. Fig. 6 is a side elevational view of the aircraft with a horizontal axis. A forward ballonet 2 and an aft ballonet 3 are shown within the balloon chamber 1. As is common in the art, the intake fans and exhaust port are located along the bottom center line of the balloon chamber and allow for maintaining a constant pressure or changing pressure of the gas if desired within the balloon chamber. The tail assembly 6 is affixed to the aft axle 31. E SHEET Figs. 7, 7a, 8, 8a, 9, and 9a depict the wing airfoils and the blade airfoils in several different positions during flight. Fig. 7 shows the wing airfoil 8 with cyclic pitch. This is used for producing aerodynamic lift either positive or negative. The blade airfoil 4 is shown in trail or flat pitch. Fig. 7a shows the side view of the aircraft in fig. 7. Fig. 8 shows the blade airfoils 4 collectively pitched to provide forward thrust. They may also be pitched to provide aft thrust. Fig. 8a shows the side view of the aircraft in fig. 8. In fig. 9 the rotor frame is in non-rotational mode. The horizontal blade airfoils 4 develop sufficient lift because of the forward velocity of the aircraft. Fig. 9a shows the side view of the aircraft in fig. 9. Desired directional changes are achieved by a mix of collective and cyclic pitch of the blade airfoils 4.

Claims: CLAIMS 1. A hybrid aircraft comprising: a large balloon chamber containing a lighter- than-air gas which provides a large static lifting force having a magnitude greater than the empty weight of said aircraft; a support structure which is substantially longer in length than in width and is encased within the balloon chamber, said support structure having two ends which protrude from the balloon chamber at opposite sides along the center line of the balloon chamber; a rotor frame which is suspended from the ends of the support structure and extend around the balloon chamber; a plurality of blade airfoils connected to the 15 rotor frame and oriented radially relative to said balloon chamber, whereby the angle of attack of each blade airfoil can be varied; a thrust means mounted at or near the outboard end of the blade airfoils; a wing airfoil perpendicularly connected to the end of each blade airfoil at the same end as the thrust means, whereby the angle of attack of each wind airfoil can be varied; a control cab attached to said support structure; 25 and a load line, characterized in that: the balloon chamber is non-rotating; the rotor frame is rotatable about said non-rotating balloon chamber; and anti-torque means are provided on the craft to keep it stable when the length of the support structure is vertical. 2. The device as claimed in claim 1 wherein the length of the support structure is substantially horizontal. ET 3. The device as claimed in claim 1 wherein the length of the support structure is substantially vertical and the anti-torque means includes a tail rotor and a spur and ring gear driven with a motor. SUBSTITUTE SHEET AMENDED CLAIMS [received by the International Bureau on 25 November 1992 (25.11.92); original claims 1-3 replaced by amended claims 1-3 (2 pages)] 1. A hybrid aircraft comprising: a large non-rotatable balloon chamber containing a lighter-than-air gas which provides a large static lifting force having a magnitude greater than the empty weight of said aircraft; a support structure which is substantially longer in length than in width and is encased within the balloon chamber, said support structure having two ends which protrude from the balloon chamber at opposite sides along the center line of the balloon chamber; a rotor frame which is rotatable about said balloon chamber, is suspended from the ends of the support structure, and extends around the balloon chamber; a plurality of blade airfoils connected to the rotor frame and oriented radially relative to said balloon chamber, whereby the angle of attack of each blade airfoil can be varied; a thrust means mounted at or near the outboard end of the blade airfoils; a wing airfoil perpendicularly connected to the end of each blade airfoil at the same end as the thrust means, whereby the angle of attack of each wing airfoil can be varied; a control cab attached to said support structure; a load line, and anti-torque means for keeping the craft stable when the length of the support structure is vertical. 2. The device as claimed in claim 1 wherein the length of the support structure is substantially horizontal. 3. The device as claimed in claim 1 wherein the length of the support structure is substantially vertical and the anti-torque means includes a tail rotor and a spur and ring gear driven with a motor. STATEMENT UNDER ARTICLE19 Pursuant to Article 19(1) and Rule 46.1, applicant hereby amends the claims of the above-captioned application and files the following statement in connection with the amendment. Attached hereto are replacement pages 7 through 8 for the application. Independent claim 1 has been amended to conform to a conventional U.S. claim format. Independent claim 1 is essentially the same as claim l of United States Patent No. 5,082,205 which issued on January 21, 1992, and claims 2 and 3 have not been amended. The amendment to claim 1 deletes the characterized clause and incorporates the elements previously recited in the characterized clause into the body of the claim to highlight the overall novel combination of elements. The amendment to claim 1 clearly distinguishes it from United States Patent No. 4,061,293 which was indicated in the International Search Report as being relevant to claim 1. United States Patent No. 4,061,293 does not disclose or suggest a large balloon chamber which contains lighter-than-air gas and provides a large static lifting force having a magnitude greater than the empty weight of the aircraft, a support structure encased in the balloon chamber, a rotor frame suspended from ends of the support structure, and a wing foil perpendicularly connected to a blade foil.

Inventors: CAUFMAN ROBERT L, CAUFMAN, ROBERT, L.
Applicants: BUOYANT COPTER INC, BUOYANT COPTER, INC.
Application year: 1992
Main classification: B64B1
IPC codes: B64B1