CA2141481A1 - Aircraft with "s"-rotor/"c" blades folding to the "o"-wing - Google Patents
Aircraft with "s"-rotor/"c" blades folding to the "o"-wingInfo
- Publication number
- CA2141481A1 CA2141481A1 CA002141481A CA2141481A CA2141481A1 CA 2141481 A1 CA2141481 A1 CA 2141481A1 CA 002141481 A CA002141481 A CA 002141481A CA 2141481 A CA2141481 A CA 2141481A CA 2141481 A1 CA2141481 A1 CA 2141481A1
- Authority
- CA
- Canada
- Prior art keywords
- wing
- shaped
- aircraft
- rotor
- fuselage
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Abandoned
Links
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C29/00—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft
- B64C29/0008—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft having its flight directional axis horizontal when grounded
- B64C29/0016—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft having its flight directional axis horizontal when grounded the lift during taking-off being created by free or ducted propellers or by blowers
- B64C29/0033—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft having its flight directional axis horizontal when grounded the lift during taking-off being created by free or ducted propellers or by blowers the propellers being tiltable relative to the fuselage
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/22—Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft
- B64C27/24—Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft with rotor blades fixed in flight to act as lifting surfaces
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/22—Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft
- B64C27/26—Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft characterised by provision of fixed wings
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/22—Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft
- B64C27/28—Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft with forward-propulsion propellers pivotable to act as lifting rotors
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Toys (AREA)
Abstract
The present invention provides an aircraft which has the capabilities of the vertical takeoff, landing, hovering operations and flying with supersonic speed utilizing the "S"-shaped rotor-wing as a conventional helicopter rotating wing After transition to forward flight, following the takeoff, the "C"-shaped blades of the "S"-shaped rotor-wing arc pivoted and become a wing of the "O" configuration. The axle of the rotor-wing is designed to be tilted its all directions. The aircraft utilizes two jet engines for rotating the rotor-wing and propulsive force; and four small rocket nozzles, installed on both sides at equal length from the rotor axis at the middle and at the rear of the fuselage, for yaw control at low speed.
Description
TITLE OF THE INVENTION
An aircraft with "S"-shaped rotor wing, consisting of two "C"- shaped blades pivoting to the "O"-shaped wing.
BACKGROUND OF THE INVENTION
1. Field of the Invention The present invention relates to an aircraft capable of vertical takeoff, landing, hovering operations and flying with supersonic speed, which utilizes the "S"-wing as a conventional helicopter rotating wing which, after transition to the forward flight following takeoff, becomes a wing of "O" configuration. The aircraft utilizes six engines within the fuselage. Two jet engines, positioned at the rear of fuselage, provide a torque for the rotor-wing and propulsion force, four rocket engines, positioned on both sides at the front and at the rear of the fuselage, provide a yaw control.
An aircraft with "S"-shaped rotor wing, consisting of two "C"- shaped blades pivoting to the "O"-shaped wing.
BACKGROUND OF THE INVENTION
1. Field of the Invention The present invention relates to an aircraft capable of vertical takeoff, landing, hovering operations and flying with supersonic speed, which utilizes the "S"-wing as a conventional helicopter rotating wing which, after transition to the forward flight following takeoff, becomes a wing of "O" configuration. The aircraft utilizes six engines within the fuselage. Two jet engines, positioned at the rear of fuselage, provide a torque for the rotor-wing and propulsion force, four rocket engines, positioned on both sides at the front and at the rear of the fuselage, provide a yaw control.
2. Description of the Art Helicopters, valued for their vertical takeoff, hovering and cruising capabilities have been available for commercial and military use for many years. Aircrafts which use both the capabilities of a helicopter and fixed wing aircraft have also been available, at least in the design stages, for number of years. A more recent development in this latter type of aircraft has been to provide a mufti-blade (in the shape of an X) rotor which, after the aircraft reaches a desired cruising speed, stops rotating and the blades themselves operate as the fixed aircraft wing.
Typical of the prior art patents relating to helicopters and convertible aircraft are follows:
U.S. Pat. No. 2,989,268 to Andrews describes a convertible aircraft capable of propulsion by a helicopter-type rotor and /or by thrust of jet engine when using fixed wing surfaces;
U.S. Pat. No. 3,807,662 to Velazquez discloses a helicopter devoid of conventional exteriorly mounted anti-torque rotor and having it at the rear end of its aft fuselage a system utilized for auxiliary propulsion and anti-torque and directional control;
U.S. Pat. No. 2,420,323 to Meyer et al discloses a multiple engine jet powered aircraft having the exhaust of the engines ducted to rectangular nozzles with vectoring flaps for pitch control;
U.S. Pat. No. 3,139,936 to Davidson et al describes a helicopter in which lift on the blades is varied by the control of span-wise-extending fluid streams discharged from there;
U.S. Pat. No. 3,362,660 to Dickey discloses a pair of gas turbine engines positioned side by side which drive a main rotor assembly of a helicopter through a combined output gear box;
U.S. Pat. No. 3,744,743 to Nay et al which discloses a helicopter power plant system using two turbine engines, each engine extending laterally within the fuselage resulting in a transmission/gearing system which enables one engine to take over if the other should fail;
U.S. Pat. No. 3,119,577 to Andrews describes a convertible aircraft having a rotating wing for low speed flight and fixed wing for high speed flight;
U.S. Pat. No. 3,792,827 to Girard discloses an aircraft having a combined rotary and fixed wing providing aerodynamic support in vertical takeoff and landing and in high speed cruising flight;
U.S. Pat. No. 2,689,61 S to Fletcher discloses a convertible type aircraft, a fixed wing portion and also a jet-driven lifting rotor;
U.S. Pat. No. 3,588,273 to Kizilos describes a rotary wing aircraft wherein each rotor blade section includes variable deflection thruster jet flap means operable to control the lift produced by each section;
U.S. Pat. No. 2,557,522 to Vautier which discloses a fixed wing aircraft provided with twin jet units and a single fuselage, both jet units being arranged one above the other and offset to provide a small dimension for the main transverse frame of fuselage; and U.S. Pat. No, 4,711,415 to Binden describes scout or attack aircraft having the capabilities of vertical takeoff, landing and hovering operations utilizing the X-wing as the conventional helicopter rotating wing. After transition to forward flight, following takeoff, and reaching the appropriate cruising speed, the rotating wing is stopped and becomes a fixed wing having the "X" configuration.
But, unfortunately, at that moment the aircraft with "X"- rotor has a serious unsteadiness of the flight, because of turbulence on the rotor and, as a result, lack of an air-lift power, that can lead to the crash. To avoid these difficulties the "X"- rotor has to be replaced by another one that could fold its blades smoothly and become the wing with perfect shape and airfoil.
SUMMARY OF THE PRESENT INVENTION
The present invention provides a single or two seats aircraft having the capabilities of vertical takeoff, landing, hovering operations and flying with supersonic speed utilizing the "S"-shaped rotor-wing as a conventional helicopter rotating wing. After transition to forward flight, following takeoff, with growing speed, the "S"-shaped rotor-wing slowly and smoothly pivots its "C"-shaped blades and becomes an "O"-shaped wing.
The "C"-shaped blades are designed with pitch control and pivoting mechanisms, driven by electric motors. The axle of the "S"-shaped rotor-wing is designed to be tilted up to 20 in all directions (360°) by a hydraulic system to enable the aircraft to better maneuver either at Iow and at high speed.
Fixed wing surfaces, as extensions of bottom surfaces of the fuselage, having an angle of 120° between them, are provided for strong stabilization, additional air-lift capability of the aircraft and for carriage of some equipment. The bottom surfaces of the fuselage widen from the front of the aircraft to the back, extending into the fixed wings.
The elevator/rudder surfaces are also attached at an angle of 100° to the fixed wing surfaces.
An ejection seat for the crew member allows emergency egress while the blades of the "S"-shaped rotor-wing are pivoted.
Two jet engines provide torque to the "S"-shaped rotor-wing via common gear box or via an electric system called generator-motor.
Also these jet engines provide propulsive force on any speed. Four small rocket nozzles, installed at equal length from the rotor-wing axis on both sides at the middle and at the rear of the fuselage, provide perfect yaw control at low speed.
The present invention thus allows an aircraft to be manufactured and successfully utilized in wide variety of needs.
BRIEF DESCRIPTION OF THE DRAWINGS
For a better understanding of the invention, as well as further feature and objects therefore, reference is made to the following description which is to be read in conjunction with the accompanying drawing wherein:
Fig. 1 is a prospective view of the aircraft of the present invention;
Fig. 2 is a side view of the aircraft of the present invention;
Fig. 3 is a front view of the aircraft of the present invention;
Fig. 4 is a plan view of the aircraft of the present invention.
DETAILED DESCRIPTION OF THE FNVENTION
Referring now to Fig.l, a prospective view of the novel aircra8 of the present invention is illustrated. The aircraft comprises of a fuselage l, a cockpit 2, fined wings 5, an "S "-shaped rotor wing comprising of two "C"-shaped blades configuration 4, elevator/rudder surfaces 6, a covered tilting assembly 7, intakes 3 and nozzles 10 of the jet engines, rear edge 16 of each blade.
Fig. 2 is a side view of the aircraft and shows the rocket nozzles 8 and 9 that provide yaw control at the takeoff, hovering and landing.
Fig. 3 is a front view of the aircraft and shows the airfoil of rotor-wing 4 pivoted into the "O"-shaped wing, f xed wings 5 as extensions of bottom surfaces of the fuselage 1, having an angle of 120° between them and widening from the middle to the rear of the fuselage, elevatorlrudder surfaces 6, which are attached to the fixed wings 5 at an angle of 100°.
Fig. 4 is a plan view of the aircraft and shows the shape of the "O"-shaped wing and the "C"-shaped blades configuration 4 as follows: a main circle 14-15-14 divided by two smaller semi-circles 11-14 and 11-15 that are opposingly connected by one end at point 11, creating an "S"-shape cut, and by another end to the main circle at points 14 and 15. A rear edge 16 of each blade is designed as a cutout surface of an imaginary inverted 9(?° cone, whose top is under the opposite blade on its axis. The centres 12 of the semi-circles are at the same time the pivoting axes of the "C"-shaped blades. The centre 11 of the main circle is a rotation axis of the "O"-shaped wing and the "C"-shaped blades of configuration 4. The "O"-shaped wing is designed with flat Iower surface and convex upper surface. Honeycomb inner structure is designed to strengthen the "C"-shaped blades against twisting.
In operation, when the jet engines I O are turned on, a rotor shaft is rotated causing the "S"-shaped wing 4 to rotate as a conventional helicopter rotor. At the takeoff, a substamial part of the torque generated by the jet engines 10 is directed to the shaft of the rotor-wing 4 through gear box. An alternative version: the jet engines 10 coupled to a generator, which is electrically connected with a series electric motor, that rotates the shaft of the rotor-wing 4. When the aircraft is aloft and reaches the desired speed of about 400 km/h, the "C"-shaped blades are pivoted in the "O"-shaped wing configurat'ron far maximum lift for conventional flying. In addition, the "O"-shaped wing configuration 4 is designed to be tilted in all directions up to 20° for better maneuverability of the aircraft. Moreover, the pitch control mechanism is provided to the "C"-shaped blades to maximize lift power at the takeoff. The f xed wing surfaces 5 are provided for strong stabilizatian, additional Lift capability in the "O"-shaped wing flight mode, arid for external stores carriage.
While the invention has been described with reference to its embodiments, it should be understood by these skilled in the art that various changes may be made and equivalents may be substituted for elements therefore without departing from the true spirit and scope of the invention. In addition, many modifications may be made to adapt to a particular situation or material to the teaching of the invention without departing from its essential teachings. What is claimed is:
1. An aircraft with an "S"-shaped rotor-wing comprising of two "C"-shaped blades, which pivot into an "6"-shaped wing; a fuselage defining a longitudinal axis of the said aircraft, an "S"-shaped rotor-wing assembly mounted on the said fuselage for rotation during Iow speed lzelfcopter phase operations and its "C"-shaped blades being pivoted to provide an "O"-shaped wing airfoil, a tilting assembly inside which a tiltable axle of the said "S"-shaped wing configuration is mounted for better maneuverability of the said aircraft, fixed wings, as extensions of bottom surfaces of the fuselage, which widen from the middle to the rear of the fuselage, having an ale of I20° between them, elevator/rudder surfaces attached to the said fixed wings at an angle of 100°; two jet engines mounted inside of the fuselage between the rotor axis and rear of the fuselage, rocket nuzzles mounted at equal distance from the rotor-wing axis on both sides of the said fuselage for yaw control.
2. The aircraft of claim 1 wherein jet engines each having a drive shaft are coupled to a gear box which is coupled to a rotor drive mechanism causing the rotor shaft to rotate when the drive mechanism is actuated, 3. As an alternative version, the drive shafts from each of the jet engines are coupled to an electric generator which is electrically coupled to a series electric motor causing the said rotor shaft to rotate.
4. The aircraft of claim 1 wherein the "S"-shaped rotor wing comprising said two "C"-shaped blades each having: a main circle formed by two smaller equal semi-circles that are opposingly connected by one end of each other, creating an "S"-shape cut, and by another end to the main circle; the rear edge of each blade is designed as a surface of an imaginary inverted 90° cone, whose top is under the opposite blade on its axis.
Typical of the prior art patents relating to helicopters and convertible aircraft are follows:
U.S. Pat. No. 2,989,268 to Andrews describes a convertible aircraft capable of propulsion by a helicopter-type rotor and /or by thrust of jet engine when using fixed wing surfaces;
U.S. Pat. No. 3,807,662 to Velazquez discloses a helicopter devoid of conventional exteriorly mounted anti-torque rotor and having it at the rear end of its aft fuselage a system utilized for auxiliary propulsion and anti-torque and directional control;
U.S. Pat. No. 2,420,323 to Meyer et al discloses a multiple engine jet powered aircraft having the exhaust of the engines ducted to rectangular nozzles with vectoring flaps for pitch control;
U.S. Pat. No. 3,139,936 to Davidson et al describes a helicopter in which lift on the blades is varied by the control of span-wise-extending fluid streams discharged from there;
U.S. Pat. No. 3,362,660 to Dickey discloses a pair of gas turbine engines positioned side by side which drive a main rotor assembly of a helicopter through a combined output gear box;
U.S. Pat. No. 3,744,743 to Nay et al which discloses a helicopter power plant system using two turbine engines, each engine extending laterally within the fuselage resulting in a transmission/gearing system which enables one engine to take over if the other should fail;
U.S. Pat. No. 3,119,577 to Andrews describes a convertible aircraft having a rotating wing for low speed flight and fixed wing for high speed flight;
U.S. Pat. No. 3,792,827 to Girard discloses an aircraft having a combined rotary and fixed wing providing aerodynamic support in vertical takeoff and landing and in high speed cruising flight;
U.S. Pat. No. 2,689,61 S to Fletcher discloses a convertible type aircraft, a fixed wing portion and also a jet-driven lifting rotor;
U.S. Pat. No. 3,588,273 to Kizilos describes a rotary wing aircraft wherein each rotor blade section includes variable deflection thruster jet flap means operable to control the lift produced by each section;
U.S. Pat. No. 2,557,522 to Vautier which discloses a fixed wing aircraft provided with twin jet units and a single fuselage, both jet units being arranged one above the other and offset to provide a small dimension for the main transverse frame of fuselage; and U.S. Pat. No, 4,711,415 to Binden describes scout or attack aircraft having the capabilities of vertical takeoff, landing and hovering operations utilizing the X-wing as the conventional helicopter rotating wing. After transition to forward flight, following takeoff, and reaching the appropriate cruising speed, the rotating wing is stopped and becomes a fixed wing having the "X" configuration.
But, unfortunately, at that moment the aircraft with "X"- rotor has a serious unsteadiness of the flight, because of turbulence on the rotor and, as a result, lack of an air-lift power, that can lead to the crash. To avoid these difficulties the "X"- rotor has to be replaced by another one that could fold its blades smoothly and become the wing with perfect shape and airfoil.
SUMMARY OF THE PRESENT INVENTION
The present invention provides a single or two seats aircraft having the capabilities of vertical takeoff, landing, hovering operations and flying with supersonic speed utilizing the "S"-shaped rotor-wing as a conventional helicopter rotating wing. After transition to forward flight, following takeoff, with growing speed, the "S"-shaped rotor-wing slowly and smoothly pivots its "C"-shaped blades and becomes an "O"-shaped wing.
The "C"-shaped blades are designed with pitch control and pivoting mechanisms, driven by electric motors. The axle of the "S"-shaped rotor-wing is designed to be tilted up to 20 in all directions (360°) by a hydraulic system to enable the aircraft to better maneuver either at Iow and at high speed.
Fixed wing surfaces, as extensions of bottom surfaces of the fuselage, having an angle of 120° between them, are provided for strong stabilization, additional air-lift capability of the aircraft and for carriage of some equipment. The bottom surfaces of the fuselage widen from the front of the aircraft to the back, extending into the fixed wings.
The elevator/rudder surfaces are also attached at an angle of 100° to the fixed wing surfaces.
An ejection seat for the crew member allows emergency egress while the blades of the "S"-shaped rotor-wing are pivoted.
Two jet engines provide torque to the "S"-shaped rotor-wing via common gear box or via an electric system called generator-motor.
Also these jet engines provide propulsive force on any speed. Four small rocket nozzles, installed at equal length from the rotor-wing axis on both sides at the middle and at the rear of the fuselage, provide perfect yaw control at low speed.
The present invention thus allows an aircraft to be manufactured and successfully utilized in wide variety of needs.
BRIEF DESCRIPTION OF THE DRAWINGS
For a better understanding of the invention, as well as further feature and objects therefore, reference is made to the following description which is to be read in conjunction with the accompanying drawing wherein:
Fig. 1 is a prospective view of the aircraft of the present invention;
Fig. 2 is a side view of the aircraft of the present invention;
Fig. 3 is a front view of the aircraft of the present invention;
Fig. 4 is a plan view of the aircraft of the present invention.
DETAILED DESCRIPTION OF THE FNVENTION
Referring now to Fig.l, a prospective view of the novel aircra8 of the present invention is illustrated. The aircraft comprises of a fuselage l, a cockpit 2, fined wings 5, an "S "-shaped rotor wing comprising of two "C"-shaped blades configuration 4, elevator/rudder surfaces 6, a covered tilting assembly 7, intakes 3 and nozzles 10 of the jet engines, rear edge 16 of each blade.
Fig. 2 is a side view of the aircraft and shows the rocket nozzles 8 and 9 that provide yaw control at the takeoff, hovering and landing.
Fig. 3 is a front view of the aircraft and shows the airfoil of rotor-wing 4 pivoted into the "O"-shaped wing, f xed wings 5 as extensions of bottom surfaces of the fuselage 1, having an angle of 120° between them and widening from the middle to the rear of the fuselage, elevatorlrudder surfaces 6, which are attached to the fixed wings 5 at an angle of 100°.
Fig. 4 is a plan view of the aircraft and shows the shape of the "O"-shaped wing and the "C"-shaped blades configuration 4 as follows: a main circle 14-15-14 divided by two smaller semi-circles 11-14 and 11-15 that are opposingly connected by one end at point 11, creating an "S"-shape cut, and by another end to the main circle at points 14 and 15. A rear edge 16 of each blade is designed as a cutout surface of an imaginary inverted 9(?° cone, whose top is under the opposite blade on its axis. The centres 12 of the semi-circles are at the same time the pivoting axes of the "C"-shaped blades. The centre 11 of the main circle is a rotation axis of the "O"-shaped wing and the "C"-shaped blades of configuration 4. The "O"-shaped wing is designed with flat Iower surface and convex upper surface. Honeycomb inner structure is designed to strengthen the "C"-shaped blades against twisting.
In operation, when the jet engines I O are turned on, a rotor shaft is rotated causing the "S"-shaped wing 4 to rotate as a conventional helicopter rotor. At the takeoff, a substamial part of the torque generated by the jet engines 10 is directed to the shaft of the rotor-wing 4 through gear box. An alternative version: the jet engines 10 coupled to a generator, which is electrically connected with a series electric motor, that rotates the shaft of the rotor-wing 4. When the aircraft is aloft and reaches the desired speed of about 400 km/h, the "C"-shaped blades are pivoted in the "O"-shaped wing configurat'ron far maximum lift for conventional flying. In addition, the "O"-shaped wing configuration 4 is designed to be tilted in all directions up to 20° for better maneuverability of the aircraft. Moreover, the pitch control mechanism is provided to the "C"-shaped blades to maximize lift power at the takeoff. The f xed wing surfaces 5 are provided for strong stabilizatian, additional Lift capability in the "O"-shaped wing flight mode, arid for external stores carriage.
While the invention has been described with reference to its embodiments, it should be understood by these skilled in the art that various changes may be made and equivalents may be substituted for elements therefore without departing from the true spirit and scope of the invention. In addition, many modifications may be made to adapt to a particular situation or material to the teaching of the invention without departing from its essential teachings. What is claimed is:
1. An aircraft with an "S"-shaped rotor-wing comprising of two "C"-shaped blades, which pivot into an "6"-shaped wing; a fuselage defining a longitudinal axis of the said aircraft, an "S"-shaped rotor-wing assembly mounted on the said fuselage for rotation during Iow speed lzelfcopter phase operations and its "C"-shaped blades being pivoted to provide an "O"-shaped wing airfoil, a tilting assembly inside which a tiltable axle of the said "S"-shaped wing configuration is mounted for better maneuverability of the said aircraft, fixed wings, as extensions of bottom surfaces of the fuselage, which widen from the middle to the rear of the fuselage, having an ale of I20° between them, elevator/rudder surfaces attached to the said fixed wings at an angle of 100°; two jet engines mounted inside of the fuselage between the rotor axis and rear of the fuselage, rocket nuzzles mounted at equal distance from the rotor-wing axis on both sides of the said fuselage for yaw control.
2. The aircraft of claim 1 wherein jet engines each having a drive shaft are coupled to a gear box which is coupled to a rotor drive mechanism causing the rotor shaft to rotate when the drive mechanism is actuated, 3. As an alternative version, the drive shafts from each of the jet engines are coupled to an electric generator which is electrically coupled to a series electric motor causing the said rotor shaft to rotate.
4. The aircraft of claim 1 wherein the "S"-shaped rotor wing comprising said two "C"-shaped blades each having: a main circle formed by two smaller equal semi-circles that are opposingly connected by one end of each other, creating an "S"-shape cut, and by another end to the main circle; the rear edge of each blade is designed as a surface of an imaginary inverted 90° cone, whose top is under the opposite blade on its axis.
5. The aircraft of claim 3 wherein the two "C"-shaped blades are pivoted to form the "O"-shaped wing when the aircraft transitions to a high speed flight.
Claims (9)
1. An aircraft with an "S"-shaped rotor-wing comprising of two "C"-shaped blades, which pivot into an "O"-shaped wing; a fuselage defining a longitudinal axis of the said aircraft, an "S"-shaped rotor-wing assembly mounted on the said fuselage for rotation during low speed helicopter phase operations and its "C"-shaped blades being pivoted to provide an "O"-shaped wing airfoil, a tilting assembly inside which a tiltable axle of the said "S"-shaped wing configuration is mounted for better maneuverability of the said aircraft, fixed wings, as extensions of bottom surfaces of the fuselage, which widen from the middle to the rear of the fuselage, having an ale of I20° between them, elevator/rudder surfaces attached to the said fixed wings at an angle of 100°, two jet engines mounted inside of the fuselage between the rotor axis and rear of the fuselage, rocket nuzzles mounted at equal distance from the rotor-wing axis on both sides of the said fuselage for yaw control.
2. The aircraft of claim 1 wherein jet engines each having a drive shaft are coupled to a gear box which is coupled to a rotor drive mechanism causing the rotor shaft to rotate when the drive mechanism is actuated,
3. As an alternative version, the drive shafts from each of the jet engines are coupled to an electric generator which is electrically coupled to a series electric motor causing the said rotor shaft to rotate.
4. The aircraft of claim 1 wherein the "S"-shaped rotor wing comprising said two "C"-shaped blades each having: a main circle formed by two smaller equal semi-circles that are opposingly connected by one end of each other, creating an "S"-shape cut, and by another end to the main circle; the rear edge of each blade is designed as a surface of an imaginary inverted 90° cone, whose top is under the opposite blade on its axis.
5. The aircraft of claim 3 wherein the two "C"-shaped blades are pivoted to form the "O"-shaped wing when the aircraft transitions to a high speed flight.
6. The aircraft of claim 4 wherein the said "O"-shaped wing has a flat lower surface and a convex upper surface, a honeycomb inner structure is provided for strength against twisting of the said "C"-shaped blades.
7. The aircraft of claim 1 wherein the said rotor assembly is mounted on the top of the fuselage and is tiltable up to 20° in all directions for better maneuverability:
8. An aircraft has an "S"-shaped rotor-wing which is rotatable and tiltable for vertical takeoff, hovering and landing operations arid is capable of pivoting "C"-shaped blades to an "O"-shaped wing airfoil during flight; the aircraft comprises of a main fuselage, which includes a cockpit, defining a longitudinal axis; and having engine air intakes on opposite sides of the said fuselage, fixed wings as extensions of bottom surfaces of the fuselage, having an angle of 120° between them, elevator/rudder surfaces mounted at an angle of 100° to each of the fixed wings, an "S"-shaped rotor-wing , rotatable and tiltable, mounted to the top of the fuselage, the "S"-shaped rotor wing has two "C"shaped blades each having: a main circle form two smaller equal semi-circles that are opposingly connected by one end of each other, creating an "S"-shape, and by another end to the main circle; the rear edge of each blade is designed as a cutout surface of an imaginary inverted 90° cone, whose top is under the opposite blade on its axis, two jet engines mounted horizontally to the said longitudinal axis, the said two jet engines respectively receiving air from the engine air intakes of the fuselage and directing jet exhaust stream towards the aft end of the aircraft; two rotary power shafts;
respectively coupled to the said jet engines, selectively receiving and communicating rotary torque from there, a common gear box connected to the two rotary power shafts for communicating rotary torque from the two rotary power shafts to the "S"-shaped rotor-wing.
respectively coupled to the said jet engines, selectively receiving and communicating rotary torque from there, a common gear box connected to the two rotary power shafts for communicating rotary torque from the two rotary power shafts to the "S"-shaped rotor-wing.
9. An alternative version: a generator connected to the two rotary power shafts for generating electric power for a series electric motor rotating the "S"-shaped rotor-wing, each "C"-shaped blade is designed with pitch control and pivoting mechanisms powered by electric motors, a crew seat is ejectable in case of emergency while the "C"-shaped blades are pivoted.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CA002141481A CA2141481A1 (en) | 1995-01-31 | 1995-01-31 | Aircraft with "s"-rotor/"c" blades folding to the "o"-wing |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CA002141481A CA2141481A1 (en) | 1995-01-31 | 1995-01-31 | Aircraft with "s"-rotor/"c" blades folding to the "o"-wing |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CA2141481A1 true CA2141481A1 (en) | 1996-08-01 |
Family
ID=4155153
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CA002141481A Abandoned CA2141481A1 (en) | 1995-01-31 | 1995-01-31 | Aircraft with "s"-rotor/"c" blades folding to the "o"-wing |
Country Status (1)
| Country | Link |
|---|---|
| CA (1) | CA2141481A1 (en) |
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| ES2485215A1 (en) * | 2013-02-11 | 2014-08-12 | Universidad Politécnica de Madrid | Aeronave convertible to flow two speeds (Machine-translation by Google Translate, not legally binding) |
| US10464668B2 (en) | 2015-09-02 | 2019-11-05 | Jetoptera, Inc. | Configuration for vertical take-off and landing system for aerial vehicles |
| CN112141328A (en) * | 2019-06-27 | 2020-12-29 | 沃科波特有限公司 | Aircraft with a flight control device |
| US10875658B2 (en) | 2015-09-02 | 2020-12-29 | Jetoptera, Inc. | Ejector and airfoil configurations |
| CN112298578A (en) * | 2020-11-27 | 2021-02-02 | 成都云鼎智控科技有限公司 | Control system of unmanned aerial vehicle engine |
| US11001378B2 (en) | 2016-08-08 | 2021-05-11 | Jetoptera, Inc. | Configuration for vertical take-off and landing system for aerial vehicles |
| US11148801B2 (en) | 2017-06-27 | 2021-10-19 | Jetoptera, Inc. | Configuration for vertical take-off and landing system for aerial vehicles |
| CN114212250A (en) * | 2022-01-14 | 2022-03-22 | 北京航空航天大学 | Novel six-rotor aircraft with horizontal attitude locking capability |
-
1995
- 1995-01-31 CA CA002141481A patent/CA2141481A1/en not_active Abandoned
Cited By (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| ES2485215A1 (en) * | 2013-02-11 | 2014-08-12 | Universidad Politécnica de Madrid | Aeronave convertible to flow two speeds (Machine-translation by Google Translate, not legally binding) |
| US10464668B2 (en) | 2015-09-02 | 2019-11-05 | Jetoptera, Inc. | Configuration for vertical take-off and landing system for aerial vehicles |
| US10875658B2 (en) | 2015-09-02 | 2020-12-29 | Jetoptera, Inc. | Ejector and airfoil configurations |
| US11001378B2 (en) | 2016-08-08 | 2021-05-11 | Jetoptera, Inc. | Configuration for vertical take-off and landing system for aerial vehicles |
| US11148801B2 (en) | 2017-06-27 | 2021-10-19 | Jetoptera, Inc. | Configuration for vertical take-off and landing system for aerial vehicles |
| CN112141328A (en) * | 2019-06-27 | 2020-12-29 | 沃科波特有限公司 | Aircraft with a flight control device |
| CN112141328B (en) * | 2019-06-27 | 2023-11-24 | 沃科波特有限公司 | Aircraft |
| CN112298578A (en) * | 2020-11-27 | 2021-02-02 | 成都云鼎智控科技有限公司 | Control system of unmanned aerial vehicle engine |
| CN112298578B (en) * | 2020-11-27 | 2021-07-27 | 成都云鼎智控科技有限公司 | Control system of unmanned aerial vehicle engine |
| CN114212250A (en) * | 2022-01-14 | 2022-03-22 | 北京航空航天大学 | Novel six-rotor aircraft with horizontal attitude locking capability |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| EEER | Examination request | ||
| FZDE | Discontinued |