CN113022847A - High-speed helicopter with vector duct tail rotor - Google Patents
High-speed helicopter with vector duct tail rotor Download PDFInfo
- Publication number
- CN113022847A CN113022847A CN202110266351.7A CN202110266351A CN113022847A CN 113022847 A CN113022847 A CN 113022847A CN 202110266351 A CN202110266351 A CN 202110266351A CN 113022847 A CN113022847 A CN 113022847A
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- Prior art keywords
- helicopter
- tail
- speed
- rotor
- wing
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Classifications
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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
- B64C27/82—Rotorcraft; Rotors peculiar thereto characterised by the provision of an auxiliary rotor or fluid-jet device for counter-balancing lifting rotor torque or changing direction of rotorcraft
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/82—Rotorcraft; Rotors peculiar thereto characterised by the provision of an auxiliary rotor or fluid-jet device for counter-balancing lifting rotor torque or changing direction of rotorcraft
- B64C2027/8254—Shrouded tail rotors, e.g. "Fenestron" fans
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/82—Rotorcraft; Rotors peculiar thereto characterised by the provision of an auxiliary rotor or fluid-jet device for counter-balancing lifting rotor torque or changing direction of rotorcraft
- B64C2027/8263—Rotorcraft; Rotors peculiar thereto characterised by the provision of an auxiliary rotor or fluid-jet device for counter-balancing lifting rotor torque or changing direction of rotorcraft comprising in addition rudders, tails, fins, or the like
- B64C2027/8281—Rotorcraft; Rotors peculiar thereto characterised by the provision of an auxiliary rotor or fluid-jet device for counter-balancing lifting rotor torque or changing direction of rotorcraft comprising in addition rudders, tails, fins, or the like comprising horizontal tail planes
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/82—Rotorcraft; Rotors peculiar thereto characterised by the provision of an auxiliary rotor or fluid-jet device for counter-balancing lifting rotor torque or changing direction of rotorcraft
- B64C2027/8263—Rotorcraft; Rotors peculiar thereto characterised by the provision of an auxiliary rotor or fluid-jet device for counter-balancing lifting rotor torque or changing direction of rotorcraft comprising in addition rudders, tails, fins, or the like
- B64C2027/829—Rotorcraft; Rotors peculiar thereto characterised by the provision of an auxiliary rotor or fluid-jet device for counter-balancing lifting rotor torque or changing direction of rotorcraft comprising in addition rudders, tails, fins, or the like comprising a V-tail units
Abstract
The invention belongs to the field of aerodynamic layout design of aircrafts, and particularly relates to a vector duct tail rotor high-speed helicopter which comprises a helicopter body, a main rotor, a lift wing, a horizontal tail wing, a vertical tail wing and a duct fan, wherein an air inlet of the duct fan faces to the helicopter body, is rotatably connected above the tail part of the helicopter body and can horizontally rotate above the tail part of the helicopter body; when the helicopter flies ahead at a high speed, the central axis of the ducted fan forms an angle alpha with the central axis of the helicopter body, alpha is more than or equal to 0 degree and less than 90 degrees, and alpha is 90 degrees when hovering and flying at a low speed. The invention realizes the vector control of the thrust of the tail part by horizontally rotating the whole ducted fan, makes up the deficiency of the common ducted tail rotor in the control efficiency, improves the control efficiency and the action efficiency and greatly improves the flight speed. In addition, the vector duct tail rotor system has relatively fewer control channels, so that the operation steps of a pilot are simplified; because the tail part of the ducted fan is not provided with the aerodynamic control surface, the airflow in the wake area is more stable and uniform, and the flying is safer.
Description
Technical Field
The invention belongs to the field of aerodynamic layout design of aircrafts, and particularly relates to a vector duct tail rotor high-speed helicopter which adopts a duct rotatable vector tail rotor system and is additionally provided with a lift wing.
Background
The high-technology local wars in the modern new military transformation environment put higher requirements on the performance of the helicopter, and a high-speed helicopter which can obviously improve the operational, rescue and transport capacities of the military is urgently needed. When the helicopter flies forward at a high speed, the speed at the blade tip of a forward-moving blade (namely the tangential speed of the blade is in the same direction as the forward flying speed of the helicopter) is the superposition of the tangential speed of a rotor wing and the forward flying speed of the helicopter, and the speed at the blade tip of a backward-moving blade is the difference between the tangential speed of the rotor wing and the forward flying speed of the helicopter, so that a larger dynamic pressure difference is generated between the forward-moving blade and the backward-moving blade on a blade disc. The conventional layout helicopter can only balance stress by applying periodic variable pitch control to the forward push rod, but with the further improvement of the flying speed, the forward blades of the rotor wing can generate shock waves due to overhigh speed, and the backward blades can stall due to overlow speed, so that the lift force of the helicopter is reduced, the resistance of the helicopter is increased, and the maximum forward flying speed of the helicopter is limited.
In order to improve the flight speed limit of a helicopter, two schemes are mainly proposed in the industry:
first, the rotor that verts, at the wing tip department of similar fixed wing aircraft wing, each adorns one set can be between level and vertical position free rotation's rotor system components that vert. When the rotor tilting system assembly is in a vertical position, the tilting rotorcraft is similar to a double-rotor tandem helicopter and can hover, fly sideways, fly backwards and take off and land vertically; when the rotor tilting system component is in a horizontal position, the tilting rotor aircraft is equivalent to a fixed-wing aircraft, can perform high-speed long-distance flight, and increases a flight envelope, so that the vertical take-off and landing capability of a common helicopter and the high-speed cruising flight capability of a turboprop aircraft are both provided, such as XV-15 and V-22 'osprey'. However, for the tilt-rotor aircraft solution, although it has higher cruising speed and longer range than the conventional helicopter, the overload capacity of its rotor system is greatly limited due to the small size of its rotor, the maneuverability is much lower than that of the conventional helicopter, and at the same time, because the lift force generated by the dual rotors of the tilt-rotor aircraft in the course is not on the gravity center of the aircraft, it is easily affected by the gust, and the hovering stability is also poor.
And secondly, a coaxial reverse rotation double-rotor wing and propulsion propeller combined structure is adopted. The upper and lower groups of rotors in coaxial reversal can mutually balance the rotor rolling torque, a tail rotor structure is not needed, the tail rotor power consumption for balancing the reverse torque is saved while the backswing stall phenomenon is eliminated, the tail propulsion propeller can realize higher forward flight speed, the total longitudinal size of the tail propulsion propeller is only about 60% of that of a traditional helicopter under the same propeller disc load, engine and total weight, the pitching and yawing rotary inertia are greatly reduced, and therefore the tail propulsion propeller has better acceleration and hovering characteristics, such as American X2 and S-97 combined unmanned aerial vehicles. However, for the coaxial contra-rotating dual-rotor scheme, since the rotation directions of the two propellers are opposite, the propeller at the rear continuously passes through the wake flow of the propeller at the front, which generates a complex dynamic adverse aerodynamic interference, so that the overall aerodynamic efficiency of the coaxial contra-rotating propulsion device becomes low, that is, the engine power required by the propeller under the same thrust is increased, the fuel consumption rate is increased, thereby limiting the further increase of the flight speed, generating larger aerodynamic noise and having poorer flight safety and reliability.
In addition, by adding lift wings on the basis of the conventional helicopter layout and adopting a vector propulsion propeller system to replace a compound helicopter with a tail rotor, a vertical tail and a horizontal tail structure, the combined helicopter has become a key research direction of high-speed helicopters in recent years due to the superior acceleration and deceleration performance and the lower rotor wing washing speed. The lift wings can gradually bear part of lift unloaded by the rotor wings when the helicopter flies forward at a high speed, so that the burden of a main engine is reduced, and the stalling of the blades is not a problem any more. The vectoring tail rotor can provide lateral vectoring thrust to replace a tail rotor to balance reactive torque when the helicopter is hovered, and the thrust direction of the vectoring tail rotor can completely point to the rear direction when the helicopter flies at a high speed and is used as a tail propulsion propeller. The vector tail rotor is combined with a lifting wing, so that the helicopter has higher flying speed, larger takeoff weight and operation radius, such as an S-66, S-72 and X-49A helicopter. However, for the scheme of adopting the lift wing and vector tail rotor combined structure, the existing vector tail rotor scheme is a pneumatic control plane vector, namely, the ducted fan is fixed, the vector propulsion control is realized by installing an adjustable pneumatic control plane at the tail part of the ducted fan, the number of control channels is more, the coupling is stronger, compared with the conventional tail rotor, the stability is poorer, the control is difficult, and meanwhile, the differential pressure resistance is also larger because the control plane is arranged behind the ducted fan.
Disclosure of Invention
Aiming at the problems, the invention provides a layout scheme of a combined high-speed helicopter adopting a duct rotatable vector tail rotor system. The vector ducted tail rotor can unload partial thrust of the main rotor wing part, and the lift wings arranged on the two sides of the fuselage are used for unloading partial lift of the main rotor wing part, so that airflow separation of backward blades and shock wave stall of forward blades are delayed, and the flight speed of the helicopter is remarkably improved. The difference of the layout scheme of the helicopter with the common vector tail rotor is that the helicopter with the common vector tail rotor is fixedly connected with an outer duct structure at the tail part, thrust vector control can be realized only through the change of a pneumatic control surface at the tail part of the duct, in addition, the influence of the outer duct structure limits the diameter of the duct-type tail rotor, the damping is small, and the action efficiency of the duct-type tail rotor is not as good as that of the traditional tail rotor in the hovering and low-speed flight stages. The tail of the helicopter is provided with the ducted fan structure which can integrally rotate around the ducted rotating shaft in a horizontal mode, the tail of the ducted fan is not provided with the pneumatic control surface, the vector control of the thrust of the tail is realized by horizontally rotating the whole ducted fan, the control efficiency and the action efficiency can be greatly improved, and the defects of a common ducted tail rotor are overcome.
In order to achieve the purpose, the invention provides a vector duct tail rotor high-speed helicopter, which comprises a helicopter body, a main rotor wing, a lift wing, a horizontal tail wing, a vertical tail wing and a duct fan, wherein an air inlet of the duct fan faces to the helicopter body, is rotatably connected above the tail part of the helicopter body and is configured to horizontally rotate above the tail part of the helicopter body; when the helicopter flies ahead at a high speed, the central axis of the ducted fan forms an angle alpha with the central axis of the helicopter body, alpha is more than or equal to 0 degree and less than 90 degrees, and when the helicopter hovers and flies at a low speed, the central axis of the ducted fan is perpendicular to the central axis of the helicopter body, namely alpha is 90 degrees.
Preferably, the ducted fan is rotatably connected above the tail of the fuselage through a ducted rotating shaft.
Preferably, the main rotor is installed directly over the fuselage, the lift wing bilateral symmetry is installed the lower half position of fuselage both sides, horizontal tail wing bilateral symmetry ground rigidity link in fuselage afterbody both sides, perpendicular fin install in horizontal tail wing's free end.
The invention has the beneficial effects that:
the invention realizes the vector control of the thrust of the tail part by installing the ducted fan structure which can rotate integrally in the horizontal direction at the tail part of the helicopter. Compared with the traditional helicopter scheme, the front flight resistance is reduced, the aerodynamic noise is reduced, and the maximum front flight speed limit is improved; compared with a tilt rotor aircraft scheme, the maneuvering performance and flight stability of the helicopter are improved; compared with a coaxial reverse dual rotor wing, the aerodynamic structure reduces the adverse aerodynamic interference among helicopter components, improves the aerodynamic efficiency and reduces the aerodynamic noise; compared with the common vector tail rotor scheme, the invention mainly has the following advantages: firstly, vector control of tail thrust is realized by horizontally rotating the whole ducted fan, the defect of a common ducted tail rotor in control efficiency is overcome, the control efficiency and action efficiency of the helicopter are improved, and the forward flight speed limit of the helicopter is further improved; and secondly, the invention does not need to install a pneumatic control surface at the tail part of the duct, thereby not only reducing the number of control channels of the tail rotor system and simplifying the operation steps of a pilot, but also leading the airflow in the wake area to be more stable and uniform and leading the flight to be safer.
Drawings
FIG. 1 is an isometric view of a ducted fan deflected 0 during high speed forward flight of a helicopter in accordance with an embodiment of the present invention;
FIG. 2 is a front view of a ducted fan deflected 0 during high speed forward flight of a helicopter in accordance with an embodiment of the present invention;
FIG. 3 is a side view of a ducted fan deflected 0 during high speed forward flight of a helicopter in accordance with an embodiment of the present invention;
FIG. 4 is a top view of a ducted fan deflected 0 during high speed forward flight of a helicopter in accordance with an embodiment of the present invention;
FIG. 5 is a rear elevation view of a ducted fan deflected 0 during high speed forward flight of a helicopter in accordance with an embodiment of the present invention;
FIG. 6 is an isometric view of a ducted fan deflected 45 when flying forward at high speed of a helicopter in accordance with an embodiment of the present invention;
figure 7 is an isometric view of a ducted fan deflected 90 deg. when a helicopter of an embodiment of the present invention is hovering and in low speed flight.
In the drawings:
1. a body; 2. a main rotor; 3. a lift wing; 4. a horizontal rear wing; 5. a vertical tail; 6. a ducted fan; 7. a duct rotating shaft.
Detailed Description
The invention is further described below with reference to the accompanying drawings and examples, it being understood that the examples described below are intended to facilitate the understanding of the invention, and are not intended to limit it in any way.
As shown in fig. 1-5, the composite high-speed helicopter with duct rotatable vector propellers provided in this embodiment includes a fuselage 1, a main rotor 2, a lift wing 3, a horizontal tail 4, a vertical tail 5, a duct fan 6, and a duct rotating shaft 7. The main rotor 2 is arranged right above the fuselage 1, and the lift wings 3 are symmetrically arranged at the lower half parts of the two sides of the fuselage 1 from left to right so as to weaken the adverse aerodynamic interference effect between the main rotor 2 and the lift wings 3. The horizontal tail wings 4 are rigidly connected with the two sides of the tail part of the fuselage 1 in a bilateral symmetry way, and the vertical tail wings 5 are arranged at the free ends of the horizontal tail wings 4. Specifically, the air inlet of the ducted fan 6 faces the fuselage 1 and is rotatably connected above the tail of the fuselage 1 by a ducted rotating shaft 7 so as to rotate horizontally in a horizontal plane above the tail of the fuselage 1. In this embodiment, the lower end of the ducted fan 6 is rigidly connected to the upper end of the ducted rotating shaft 7, and the lower end of the ducted rotating shaft 7 is rotatably connected to the upper portion of the tail of the fuselage 1 and can rotate horizontally.
When the helicopter flies forward at a high speed, in order to delay the stalling phenomenon of the blades, the main rotor 2 starts to gradually unload lift force and thrust force, at the moment, the lift force part is borne by the lift force wings 3, and the thrust force part is borne by the ducted fan 6. When the central axis X2 of the ducted fan 6 is parallel to the central axis X1 of the fuselage 1, as shown in fig. 1-5, the thrust generated by the ducted fan 6 is all used to refer to the helicopter flight speed. When the ducted fan 6 deflects clockwise or anticlockwise through the ducted rotating shaft 7, so that the central axis X2 of the ducted fan 6 forms an angle alpha with the central axis X1 of the helicopter body 1, wherein alpha is more than or equal to 0 degrees and less than 90 degrees, for example, the ducted fan deflects anticlockwise by 45 degrees, as shown in FIG. 6, a thrust component generated by the ducted fan 6 and perpendicular to the central axis X1 of the helicopter body 1 is used for balancing the anti-torque, and a thrust component parallel to the central axis X1 of the helicopter body 1 drives the helicopter to accelerate forward flight, so that the forward flight speed of the helicopter is improved.
When the helicopter is hovering and flying at low speed, the lift and thrust of the helicopter are mainly provided by the main rotor 2, and the ducted fan 6 is deflected clockwise or counterclockwise to the central axis X2 which is completely perpendicular to the central axis X1 of the fuselage 1, as shown in fig. 7, at this time, the ducted fan 6 plays the role of a traditional tail rotor, the thrust generated by the ducted fan is all used for balancing the anti-torque generated by the main rotor 2, and the heading control is realized by the horizontal tail fin 4 and the vertical tail fin 5 together. So that the counter-torque generated by the main rotor 2 can be efficiently overcome and sufficient course steering force can be provided by the ducted fan 6.
In the description of the present invention, it is to be noted that the terms "above", "directly above", "lower half", "upper end", "lower end", "horizontal", "both sides", and the like indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, and are only for convenience of describing the present invention and simplifying the description, but do not indicate or imply that the elements referred to must have a specific orientation or be constructed and operated in a specific orientation, and thus, cannot be construed as limiting the present invention.
In the description of the present invention, it should be noted that, unless otherwise explicitly specified or limited, the terms "mounted," "fixedly connected," and "connected" are to be construed broadly, and may be, for example, fixedly connected, detachably connected, or integrally connected; may be a mechanical connection; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meanings of the above terms in the present invention can be understood in specific cases to those skilled in the art.
It will be apparent to those skilled in the art that various modifications and improvements can be made to the embodiments of the present invention without departing from the inventive concept thereof, and these modifications and improvements are intended to be within the scope of the invention.
Claims (3)
1. A vector duct tail rotor high-speed helicopter comprises a helicopter body, a main rotor, a lift wing, a horizontal tail wing, a vertical tail wing and a duct fan, and is characterized in that an air inlet of the duct fan faces the helicopter body, is rotatably connected above the tail part of the helicopter body and is configured to horizontally rotate above the tail part of the helicopter body; when the helicopter flies ahead at a high speed, the central axis of the ducted fan forms an angle alpha with the central axis of the helicopter body, alpha is more than or equal to 0 degree and less than 90 degrees, and when the helicopter hovers and flies at a low speed, the central axis of the ducted fan is perpendicular to the central axis of the helicopter body, namely alpha is 90 degrees.
2. The high-speed helicopter of claim 1 wherein the ducted fan is rotatably connected above the aft portion of the fuselage by a ducted rotor shaft.
3. A high-speed helicopter according to claim 1 or 2 wherein said main rotor is mounted directly above said fuselage, said lift wings are symmetrically mounted at the lower half of said fuselage on both sides, said horizontal tail wing is rigidly attached to both sides of said tail of said fuselage in a symmetrical manner, and said vertical tail wing is mounted at the free end of said horizontal tail wing.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110266351.7A CN113022847A (en) | 2021-03-11 | 2021-03-11 | High-speed helicopter with vector duct tail rotor |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110266351.7A CN113022847A (en) | 2021-03-11 | 2021-03-11 | High-speed helicopter with vector duct tail rotor |
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| CN113022847A true CN113022847A (en) | 2021-06-25 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN202110266351.7A Pending CN113022847A (en) | 2021-03-11 | 2021-03-11 | High-speed helicopter with vector duct tail rotor |
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113306726A (en) * | 2021-07-01 | 2021-08-27 | 西北工业大学 | Novel high-speed coaxial double-rotor helicopter propulsion system |
| CN113734424A (en) * | 2021-11-05 | 2021-12-03 | 尚良仲毅(沈阳)高新科技有限公司 | Unmanned helicopter and control system thereof |
| CN114771817A (en) * | 2022-04-29 | 2022-07-22 | 中国航空研究院 | Coaxial high-speed helicopter with deflection intermediate shaft fairing |
| CN115196008A (en) * | 2022-07-12 | 2022-10-18 | 南京航空航天大学 | Ultra-high-speed helicopter structure based on hybrid electric propulsion |
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| CN203005744U (en) * | 2012-10-30 | 2013-06-19 | 武卫平 | Tilt rotor helicopter |
| CN106741941A (en) * | 2016-11-30 | 2017-05-31 | 宁秀芬 | A kind of floating marine refuse collection unmanned plane |
| CN208947593U (en) * | 2018-08-13 | 2019-06-07 | 湘潭市湘盾道路交通设施建设维护有限责任公司 | Variable tail rotor high-speed aircraft |
| CN110723284A (en) * | 2018-07-17 | 2020-01-24 | 刘建国 | Vertical lifting fixed wing aircraft with tiltable ducted fan |
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2021
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| US20100019079A1 (en) * | 2007-06-20 | 2010-01-28 | General Electric Company | Thrust generator for a rotary wing aircraft |
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Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113306726A (en) * | 2021-07-01 | 2021-08-27 | 西北工业大学 | Novel high-speed coaxial double-rotor helicopter propulsion system |
| CN113306726B (en) * | 2021-07-01 | 2023-09-22 | 西北工业大学 | High-speed coaxial double-rotor helicopter propulsion system |
| CN113734424A (en) * | 2021-11-05 | 2021-12-03 | 尚良仲毅(沈阳)高新科技有限公司 | Unmanned helicopter and control system thereof |
| CN114771817A (en) * | 2022-04-29 | 2022-07-22 | 中国航空研究院 | Coaxial high-speed helicopter with deflection intermediate shaft fairing |
| CN114771817B (en) * | 2022-04-29 | 2023-06-16 | 中国航空研究院 | Coaxial high-speed helicopter with deflectable intermediate shaft fairing |
| CN115196008A (en) * | 2022-07-12 | 2022-10-18 | 南京航空航天大学 | Ultra-high-speed helicopter structure based on hybrid electric propulsion |
| CN115196008B (en) * | 2022-07-12 | 2024-03-22 | 南京航空航天大学 | Ultra-high speed helicopter configuration based on hybrid electric propulsion |
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