CN115196008A - Ultra-high-speed helicopter structure based on hybrid electric propulsion - Google Patents
Ultra-high-speed helicopter structure based on hybrid electric propulsion Download PDFInfo
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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
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/20—Rotorcraft characterised by having shrouded rotors, e.g. flying platforms
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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
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- 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
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- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
- B64D27/02—Aircraft characterised by the type or position of power plants
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
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Abstract
The invention relates to an ultra-high speed helicopter configuration based on hybrid electric propulsion, and belongs to the field of aircraft complete machine configuration design. Configurations disclosed herein include: fuselage (4), main wing (8), front wing (1), H type fin, turbofan engine (5), lift fan (10) and power supply system, the middle part top at the fuselage is installed in turbofan engine (5), and the turbofan side of admitting air is equipped with U type clearance (11), main wing (8) overall arrangement is at the turbofan top, front wing (1) overall arrangement is in fuselage head bottom, installation lift fan (10) in main wing (8) and front wing (1) both sides wing, H type fin overall arrangement is in fuselage afterbody middle-end. The invention adopts the integrated design of the helicopter and the turbofan engine, and the three-wing-surface aerodynamic layout staggered with each other in the longitudinal space ensures that the helicopter has the characteristic that winglets expand high lift force and the winglets drop vortex are not influenced mutually, the design of the fan-wing fusion can meet the lift force requirements of ultra-high speed cruising and hovering, and the aerodynamic efficiency and the hovering lift force requirements of the ultra-high speed cruising of the helicopter are ensured.
Description
Technical Field
The invention relates to an ultra-high speed helicopter configuration based on hybrid electric propulsion, and belongs to the field of aircraft complete machine configuration design.
Background
The high-technology local war under the modern new military transformation environment puts higher requirements on the performance of the helicopter, and an ultrahigh-speed helicopter which can quickly support and quickly strike is urgently needed. The rotor forward side blades of the conventional helicopter can generate shock waves due to overhigh speed, and the backward side blades can stall due to overlow speed, so that the lift force of the helicopter is reduced, the resistance of the helicopter is increased, the maximum forward flight speed of the helicopter is limited, and the speed per hour is within the range of 250-350 km/h. In order to improve the flight speed limit of a conventional helicopter, two solutions are mainly proposed in the industry:
first, the rotor that verts, in the wing point department of similar fixed wing aircraft wing, respectively adorn one set can be between level and vertical position free rotation's rotor system components that vert. Although compared with the traditional helicopter, the helicopter has higher cruising speed and longer range, such as the highest speed per hour of V-22 'osprey' is 509 km/h, the propelling force of a rotor system is greatly limited due to the small size of the rotatable rotor, and meanwhile, because the lifting force generated by the tilting rotor is not behind the gravity center of the airplane and is in a static unstable state, the maneuvering performance is far lower than that of the traditional helicopter, the helicopter is easily influenced by 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 reverse rotation can mutually balance the rolling torque of the rotors, a tail rotor structure is not needed, and the tail propulsion propeller can realize higher forward flight speed, such as the S-97 maximum flight speed exceeding 482 kilometers per hour. However, in the case of the coaxial contra-rotating dual-rotor scheme, since the two propellers rotate in opposite directions, the rear propeller continuously passes through the wake flow of the front propeller, which generates a complex dynamic adverse aerodynamic disturbance, so that the overall aerodynamic efficiency of the coaxial contra-rotating propulsion device becomes low, that is, the engine power required by the propellers under the same thrust is increased, the fuel consumption is increased, thereby limiting the further increase of the flight speed, and generating a large aerodynamic noise.
When the high-speed helicopter breaks through mach 0.8 (980 km/h), either a tilt rotor scheme, such as CN106986020A, or a combined scheme of coaxial counter-rotating twin rotors and propulsion propellers, such as CN109665096A, or a mixed scheme of the two, such as CN108045572A, the maximum limit of which is about 500 km/h, is slightly inferior to the cruising speed of a conventional turboprop aircraft at 600 km/h, which means that in the prior art, when the propeller is used for driving the aircraft, mach 0.8 cannot be broken through, so in order to improve the cruising speed, the rotor should be hidden as much as possible, for example, a multi-drive vertical take-off and landing fixed wing unmanned aerial vehicle (ZL 108557075B) is proposed, a ducted fan for the aircraft is proposed, the ducted fan for hovering provides lift, and the wings for cruising provide lift, but the propulsion force is still provided by the propellers, and the opening on the wings is a breaking ring for the aerodynamic efficiency of the aircraft. The invention discloses a three-wing small tilting power universal aircraft (CN 108773475A), and provides a tilting vortex jet driven three-wing aircraft which is expected to break through 0.8 Mach cruise, but is remarkable in that the hovering vortex jet air flow is about 4 times that of 0.8 Mach cruise.
Disclosure of Invention
The invention aims to provide an ultra-high speed helicopter configuration based on hybrid electric propulsion, and aims to develop an ultra-high speed helicopter configuration with a cruising Mach number of about 0.8, adopt the integrated design of a helicopter and a turbofan engine, and solve the problem of mutual influence of falling vortexes of airfoils through the aerodynamic layout of three airfoils staggered with each other in the longitudinal space.
In order to achieve the purpose, the invention provides the following technical scheme:
an ultra-high speed helicopter configuration based on hybrid electric propulsion, comprising: fuselage, main wing, front wing, H type fin, turbofan engine, lift fan and power supply system, the turbofan engine is installed on the middle part top of fuselage, adopts helicopter + turbofan engine integrated design, and turbofan and fuselage admit air side bottom are equipped with U type clearance, U type clearance structure be used for reducing the distortion that admits air of turbofan engine, the main wing overall arrangement is at the turbofan engine top, the front wing overall arrangement in fuselage head bottom, main wing and front wing both sides wing, adopt the wing section of taking two parallel surfaces to the structure is used for nested installation a plurality of lift fans and fan folding lid, the ultrahigh-speed helicopter structure has the characteristics of three-wing-surface pneumatic layout which is staggered in the longitudinal space on the whole, is used for reducing the influence of falling vortex of the wing surface on the aerodynamic efficiency of the wing, and has a compact large-capacity helicopter structure with high lift force and winglets;
the cross section structure of the fuselage is a lift-like airfoil, the turbofan engine is equivalent to an air suction source, and airflow flows along the surface of the fuselage without gas separation by utilizing the coanda effect, so that the lift of the fuselage is improved, and the wing load of wings during cruise is reduced;
the lift force fans can be installed with 4, 6, 8 and the like according to the hovering carrying capacity requirement of the helicopter;
the tail parts of the horizontal tail wing and the vertical tail wing are both provided with wing flaps for pitch and yaw control under the cruise mode of the helicopter, and the tail parts of the main wing and the front wing are also provided with wing flaps for roll control during the cruise of the helicopter;
a flight control system of a helicopter adopts a control scheme of a conventional four-rotor unmanned aerial vehicle, and can realize pitching, steering and rolling control in a helicopter hovering mode by controlling and managing the lift force of a plurality of lift force fans;
the electric lift fan is an electric drive fan, the power supply system comprises a generator, a rectifier and an inverter, the rectifier and the inverter are installed in the body, the turbofan engine directly drives the generator installed in the engine to generate electricity, and the electricity is transmitted to a motor for driving the lift fan to rotate through the rectifier and the inverter.
The ultra-high-speed helicopter structure based on hybrid electric propulsion is characterized in that a main wing and a front wing adopt a fan-wing fusion design, the head and the tail of the upper wing surface of the wing are curved surfaces capable of generating lift force, the middle part of the wing is an upper wing plane, the lower wing surface of the wing is a lower wing plane, a square groove of a fan folding cover and a lift fan channel with an expansion lip are arranged at the wing position provided with a lift fan, and the fan is fixed in the lift fan channel through a fan guide vane support.
The utility model provides an hypervelocity helicopter configuration based on mix electric propulsion which characterized in that, fan folding cover include first apron, apron extension, second apron, guide rail slide bar, guide rail groove and motor, first apron one end connect in the fixed hinge point on the wing to with the motor shaft connection, the other end and apron extend coplane connection, two symmetrical hinge points are installed to both junctures, second apron one end pass through two symmetrical hinge points are connected on first apron, install the guide rail slide bar on the other end to fix in the guide rail groove of wing, and the structure is used for opening and closing of lift fan passageway, its course of operation is:
(1) cruise state → hover state: the motor drives the first cover plate to rotate clockwise, the angle formed by the first cover plate and the second cover plate is reduced, the guide rail slide bar of the second cover plate moves leftwards along the guide rail groove until the first cover plate and the second cover plate are overlapped, the process from closing to opening of the fan folding cover is finished, and the lifting force of the fan is increased by expanding the lifting force fan channel of the lip;
(2) hover state → cruise state: the motor drives the first cover plate to rotate anticlockwise, the angle formed by the first cover plate and the second cover plate is enlarged until the first cover plate and the second cover plate are coplanar, the process from opening to closing of the fan folding cover is finished, and the aerodynamic efficiency of the wing is high.
The ultra-high-speed helicopter structure based on hybrid electric propulsion is characterized in that the ultra-high-speed helicopter is controlled by a flight control system and an engine controller and comprises four working processes of I-starting, II-hovering, III-mode switching and IV-cruising, during mode conversion, a pilot operates a throttle lever and a working mode switch, the flight control system coordinately controls the power output and the fan folding cover of a lift fan motor, the engine controller coordinately controls a bypass ratio, a nozzle area and fuel flow, and the specific working process of the ultra-high-speed helicopter is as follows:
(1) i: starting the ultra-high-speed helicopter, fully opening the fan folding cover and keeping the flying distance S idle And a flying height H idle All are 0, the outer duct of the turbofan engine is completely closed, the tail nozzle is completely expanded, and the rotating speed is accelerated to a slow vehicle rotating speed n idle ；
(2) I → II: ultra-high-speed helicopter climbing to hovering height H hover The engine controller increases the fuel flow and the rotor speed follows the slow speed n idle Accelerating to hover speed n hover And working at the suspension point A, the outer duct is completely closed, the air flow can only enter the core machine through the inner duct, and the tail of the core machine isThe jet pipe is completely expanded to ensure that the speed of the airflow outlet of the inner duct is almost zero, namely jet propulsion is hardly generated, at the moment, the turbine drives the generator to generate electricity to drive the plurality of lift fans to rotate, the lift fans adopt the expansion lip to increase the hovering air inflow, and almost all energy of the engine is converted into the hovering lift of the ultra-high-speed helicopter in the mode;
(3) II → III → IV: the flight control system controls the rotating speeds of a plurality of lift fans, so that the ultrahigh-speed helicopter flies forwards at a low speed, the wings generate certain lift, the suspension point A accelerates to a hovering switching point B, then the controller slowly opens the outer duct and increases the fuel flow to adapt to the increase of the load of the duct fan, meanwhile, the tail nozzle slowly starts to converge, the work capacity of the inner duct turbine is weakened, the engine controller increases the fuel flow to realize the constant rotating speed of the turbine, the overall effect is that the jet propulsion force of the inner duct and the jet propulsion force of the inner duct are increased, the flight control system reduces the power output of the lift fan motor, the rotating speed of the lift fan is reduced, the lift force of the wings is increased along with the increase of the flying speed, when the hovering switching point B transits to a cruising switching point C, the outer duct is completely opened, the tail nozzle is completely converged, the rotating speed of the lift fan is zero, the lift force of the lift fan is completely replaced by the wings, then the folding cover (3) is switched from open to close, the aerodynamic efficiency of the wings is increased, the cruising speed is accelerated from the point C to the point D, almost all energy of the engine is converted into the propulsion force of the ultrahigh-speed of the jet propulsion force, the jet propulsion force is not changed, and the total thrust force is slowly increased;
(4) IV → III → II: the engine controller reduces the fuel flow, the flight control system opens the fan folding cover, the ultra-high speed helicopter decelerates from a cruising D point to a switching C point, at the moment, the engine controller starts to slowly close the outer duct and the expansion tail nozzle, the flight control system accelerates the lift fan, almost all energy of the engine is converted into the lift force of the lift fan when finally transitioning to a hovering switching point B, the engine can decelerate from the point B to the point A according to the descending height requirement, the total lift force is unchanged in the switching process, and the propulsion force is slowly reduced;
in the process of I → II → III → IV and IV → III → II → I of the turbofan engine, oil supply curves of an engine controller are close to an overtemperature surge boundary line, so that the performance potential of the engine is fully exerted;
when the ultra-high-speed helicopter cruises, the fan folding cover is closed, so that the pneumatic efficiency of the cruises is fully improved.
Compared with the prior art, the invention has the advantages that: the ultra-high-speed helicopter structure with the cruise Mach number of about 0.8 is developed, the integrated design of the helicopter and the turbofan engine is adopted, in the process, the U-shaped gap is utilized to reduce the intake distortion of the turbofan engine arranged at the top end of the middle part of the helicopter body, and the three-wing-surface aerodynamic layout staggered with each other in the longitudinal space is adopted, so that the helicopter has the characteristic that small-span large cruise lift force and wing surface shedding vortex are not influenced mutually. Compared with a tilt rotor aircraft, the turbofan jet propulsion cruise speed is higher, the helicopter with the three-wing-surface layout has better stability, and compared with a coaxial reverse double-rotor and propulsion propeller combined structure, the design of the fan-wing fusion and lift fan folding cover can meet the lift requirements of hovering and high-aerodynamic-efficiency cruise, and the sound absorption effect of the wall surface of the duct is good.
Drawings
FIG. 1 is a perspective view, front view and left side view of the ultra-high speed helicopter configuration of the present invention in cruise and hover states, respectively.
Fig. 2 is a schematic view of the folding cover of the fan of the present invention.
Fig. 3 is a profile characteristic of the front and main wings of the lift fan of the present invention.
FIG. 4 is a schematic diagram of the operation of the entire power system of the present invention in cruise and hover states.
Fig. 5 is a graph showing the variation of the oil supply to the rotational speed of the turbofan engine according to the present invention in different modes.
Fig. 6 is a mission profile of the ultra-high-speed helicopter of the present invention.
FIG. 7 is a control parameter and performance parameter variation curve of the entire power system mode conversion transition process of the present invention.
In the figure: 1-front wing, 2-front wing wingtip winglet, 3-fan folding plate, 31-first cover plate, 32-cover plate extension, 33-second cover plate, 34-guide rail slide bar, 35-guide rail groove, 4-fuselage, 5-turbofan engine, 6-horizontal tail wing, 7-vertical tail wing, 8-main wing, 9-main wing wingtip winglet, 10-lift fan, 11-U-shaped gap, A-suspension point, B-suspension switching point, C-cruise switching point and D-cruise point.
Detailed Description
The technical solutions in the embodiments of the present invention will be described clearly and completely with reference to the accompanying drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
Referring to fig. 1, in an embodiment of the present invention, an ultra-high speed helicopter configuration based on hybrid electric propulsion includes: the high-speed aerodynamic helicopter comprises a fuselage 4, a main wing 8, a front wing 1, an H-shaped empennage, a turbofan engine 5, a lift fan 10 and a power supply system, wherein the turbofan engine 5 is installed at the top end of the middle part of the fuselage, U-shaped gaps 11 are formed in the bottoms of the air inlet sides of the turbofan and the fuselage, the U-shaped gaps 11 are used for reducing air inlet distortion of the turbofan engine, the main wing 8 is arranged at the top of the turbofan engine, the front wing 1 is arranged at the bottom end of the head of the fuselage, wings on two sides of the main wing 8 and the front wing 1 are provided with double parallel surfaces, the wing is used for embedding and installing the lift fan 10 and a fan folding cover 3, a plurality of lift fans can improve the cruising aerodynamic efficiency, wingtip winglets are installed on the main wing 8 and the front wing 1, the H-shaped empennage is arranged at the middle end of the tail of the fuselage, the H-shaped empennage comprises a horizontal empennage 6 and a vertical empennage 7, two vertical empennages are arranged at two ends of the horizontal empennages 6 and form an H-shaped layout, the H-shaped empennage, the vertical empennage is provided with the three vertical empennages which are staggered in the longitudinal space on the whole structure, and can realize the characteristic that the aerodynamic configuration that the three vertical empennages of the three vertical empennages are compact and can reduce the aerodynamic configuration and the aerodynamic configuration of the large lifting effect on the shedding of the large wings can be achieved;
the cross section structure of the fuselage 4 is a lift-like airfoil, the turbofan engine 5 is equivalent to an air suction source, and airflow flows along the surface of the fuselage without gas separation by utilizing the coanda effect, so that the lift of the fuselage is improved, and the wing load of wings during cruise is reduced;
when the lift fan is specifically implemented according to the hovering carrying capacity of the helicopter, 4 lift fans are uniformly arranged on the front wing and the main wing;
the tail parts of the horizontal tail wing 6 and the vertical tail wing 7 are both provided with a flap for pitch and yaw control in a cruise mode of the helicopter, and the tail parts of the main wing 8 and the front wing 1 are also provided with a flap for roll control in the cruise mode of the helicopter;
a flight control system of a helicopter adopts a control scheme of a conventional four-rotor unmanned aerial vehicle, and can realize pitching, steering and rolling control under a helicopter hovering mode by controlling and managing the lift forces of four lift force fans;
referring to fig. 4, in the embodiment of the present invention, the lift fan 10 is an electrically driven fan, the power supply system includes a generator, a rectifier and an inverter, the rectifier and the inverter are installed in the body 4, and the turbofan engine 5 directly drives the generator installed in the engine to generate power and sequentially transmits the power to the motor driving the lift fan to rotate through the rectifier and the inverter.
Referring to fig. 3, in the embodiment of the present invention, the configuration of the hybrid electric propulsion-based ultra-high speed helicopter is characterized in that the main wing 8 and the front wing 1 adopt a fan-wing fusion design, the head and the tail of the upper wing surface of the wing profile are curved surfaces capable of generating lift force, the middle of the wing profile is an upper wing plane, the lower wing surface of the wing profile is a lower wing plane, at the wing position where the lift fan is installed, the wing profile includes a square groove of the fan folding cover 3 and a lift fan channel with an expansion lip, and the fan is fixed in the lift fan channel through the fan guide vane support.
Referring to fig. 2, in an embodiment of the present invention, the configuration of the hybrid electric propulsion based ultra-high speed helicopter is characterized in that the folding fan cover 3 includes a first cover plate 31, a cover plate extension 32, a second cover plate 33, a guide rail slide bar 34, a guide rail groove 35, and a motor, one end of the first cover plate 31 is connected to the fixed hinge point on the wing and connected to the motor shaft, the other end of the first cover plate 31 is connected to the cover plate extension 32 in a coplanar manner, two symmetrical hinge points are installed at the junction of the two hinge points, one end of the second cover plate 33 is connected to the first cover plate 31 through the two symmetrical hinge points, the other end of the second cover plate 33 is installed with the guide rail slide bar 34 and fixed in the guide rail groove 35 of the wing, and is configured for opening and closing the lift fan channel, and the operation process thereof is as follows:
(1) cruise state → hover state: the motor drives the first cover plate 31 to rotate clockwise, the angle formed by the first cover plate 31 and the second cover plate 33 is reduced, the guide rail slide bar 34 of the second cover plate 33 moves leftwards along the guide rail groove 35 until the first cover plate 31 and the second cover plate 33 are overlapped, and then the process from closing to opening of the fan folding cover 3 is completed;
(2) hover state → cruise state: the motor drives the first cover plate 31 to rotate counterclockwise, and the first cover plate 31 and the second cover plate 33 form an angle which becomes larger until the first cover plate 31 and the second cover plate 33 are coplanar, so that the process from opening to closing the fan folding cover 3 is completed.
Referring to fig. 5 and 6, in an embodiment of the present invention, a hybrid electric propulsion based ultra-high speed helicopter configuration is characterized in that the ultra-high speed helicopter is controlled by a flight control system and an engine controller, and includes four working processes of I-start, II-hover, III-mode switch, and IV-cruise, during mode conversion, a pilot operates a throttle lever and a working mode switch, the flight control system coordinately controls power output of a lift fan motor and a fan folding cover, and the engine controller coordinately controls a bypass ratio, a nozzle area, and a fuel flow, and the specific working processes of the ultra-high speed helicopter are as follows:
(1) i: starting the ultra-high-speed helicopter, fully opening the fan folding cover 3 and keeping the flying distance S idle And a flying height H idle All are 0, turbofan engine 5 outer ductCompletely closed, the tail nozzle is completely expanded, and the rotating speed is accelerated to a slow vehicle rotating speed n idle ；
(2) I → II: ultra-high-speed helicopter climbing to hovering height H hover The engine controller increases the fuel flow and the rotor speed follows the slow speed n idle Accelerating to hover speed n hover The tail nozzle is fully expanded to enable the speed of the airflow outlet of the inner duct to be almost zero, namely jet propulsion force is hardly generated, the turbine drives the generator to generate electricity to drive a plurality of lift fans to rotate, the lift fans adopt the expansion lips to increase the hovering air inflow, and almost all energy of the engine is converted into hovering lift of the ultra-high-speed helicopter in the mode;
(3) II → III → IV: the flight control system controls the rotating speeds of the four lift fans, so that the ultrahigh-speed helicopter flies forwards at a low speed, the wings generate certain lift, the suspension point A accelerates to a hovering switching point B, then the controller slowly opens the outer duct and increases the fuel flow to adapt to the increase of the load of the duct fan, meanwhile, the tail nozzle slowly starts to converge, the work capacity of the inner duct turbine is weakened, the engine controller increases the fuel flow to realize the constant rotating speed of the turbine, the overall effect is that the jet propulsion of the inner duct and the jet propulsion of the outer duct are increased, the flight control system reduces the power output of the lift fan motor, the rotating speed of the lift fan is reduced, the lift of the wings is increased along with the increase of the flying speed, when the hovering switching point B is transited to a cruising switching point C, the outer duct is completely opened, the tail nozzle is completely converged, the rotating speed of the lift fan is zero, the lift of the lift fan is completely replaced by the lift of the lift fan, then the folding cover 3 is switched from open to close, the aerodynamic efficiency is increased, the cruising speed is accelerated from the point C to the point D, almost all energy of the engine is converted into the jet propulsion of the ultrahigh-speed, the total jet propulsion is not changed, and the total lift force is slowly increased in the switching process;
(4) IV → III → II: the engine controller reduces the fuel flow according to the throttle lever instruction and the working mode switch, the flight control system opens the fan folding cover 3, the ultra-high-speed helicopter decelerates from a cruise D point to a switching C point, at the moment, the engine controller starts to slowly close the bypass and the expansion tail nozzle, the flight control system accelerates the lift fan, almost all energy of the engine is converted into the lift force of the lift fan when finally transitioning to a hovering switching point B, the engine can decelerate from the point B to the point A according to the descending height requirement, the total lift force is unchanged in the switching process, and the propelling force is slowly reduced;
in the process of I → II → III → IV and IV → III → II → I, the oil supply curves of the engine controller are all close to the overtemperature surge boundary line, so that the performance potential of the engine is fully exerted;
when the ultra-high-speed helicopter cruises, the fan folding cover 3 is closed, so that the pneumatic efficiency of the cruises is fully improved;
referring to FIG. 7, in an embodiment of the present invention, the powertrain system adjusts the fuel flow W f The ratio a of front and rear ducts of the ducted fan and the area A of the tail spray pipe 8 Lifting force electric fan power P fan Realizes the lift force L of the lift fan of the superspeed helicopter fan Alternative wing lift L wing Total lift force L in the process total Invariably, thrust F of turbofan jet duct Alternative lift fan forward force F fan In-process power system propulsion F total Slowly increases, realizes coordination control, and has the mode switching time as short as possible. The specific control process is as follows: at t 1 Fuel flow W of time turbofan engine f At the beginning of increasing, the flight control system realizes the forward flight of the ultra-high speed helicopter by controlling the four lift electric fans, the ultra-high speed helicopter is provided with a small forward flight incidence angle, and the thrust generated by the lift electric fans is F fan Time from t 1 To t 2 The power of the lift electric fan is slowly increased in an oblique wave increment control mode at t 2 At the moment, the power of the lift electric fan is controlled to be reduced by adopting negative acceleration increment, the front flight incidence angle of the ultrahigh-speed helicopter is slowly reduced, and the turbofan engine starts to generate jet propulsion force F duct And at t 3 Moment jet propulsion F duct Completely replacing fan thrust F fan Whole t 1 To t 2 Process F total Slowly increasing, total literForce L total Is constant.
The present invention is not limited to the above embodiments, and based on the technical solutions disclosed in the present invention, those skilled in the art can make some simple modifications, equivalent changes and modifications to some technical features without creative efforts based on the disclosed technical contents, and all fall into the technical solution of the present invention.
Claims (4)
1. An ultra-high speed helicopter configuration based on hybrid electric propulsion, comprising: fuselage (4), main wing (8), front wing (1), H type fin, turbofan engine (5), lift fan (10) and power supply system, turbofan engine (5) are installed on the middle part top of fuselage, and turbofan and fuselage admit air side bottom are equipped with U type clearance (11), U type clearance (11) structure be used for reducing the distortion that admits air of turbofan engine, main wing (8) overall arrangement is at the turbofan engine top, front wing (1) overall arrangement in fuselage head bottom, main wing (8) and front wing (1) both sides wing, adopt the wing section of taking two parallel planes to the structure is used for nested a plurality of lift fan (10) of installation and fan folding lid (3), the ultra-high-speed helicopter structure is characterized in that wingtip winglets are arranged on the main wing (8) and the front wing (1), the H-shaped empennage is arranged at the middle end of the tail of the helicopter body and comprises a horizontal empennage (6) and a vertical empennage (7), the two vertical empennages are positioned at two ends of the horizontal empennage (6) and form an H-shaped layout, the ultra-high-speed helicopter structure integrally has the characteristic of three-wing-surface pneumatic layout which is staggered in the longitudinal space, and is constructed to reduce the influence of falling vortex of a wing surface on the aerodynamic efficiency of the wing and has a compact type large-capacity helicopter structure with a wingtip and a large lift force;
the cross section structure of the fuselage (4) is of a lift-like wing type, the turbofan engine (5) is equivalent to an air suction source, and airflow flows along the surface of the fuselage without gas separation by utilizing the coanda effect, so that the lift of the fuselage is improved, and the wing load of wings during cruising is reduced;
the lift force fans can be installed with 4, 6, 8 and the like according to the hovering carrying capacity requirement of the helicopter;
the tail parts of the horizontal tail wing (6) and the vertical tail wing (7) are provided with flaps for pitch and yaw control of the helicopter in a cruise mode, and the tail parts of the main wing (8) and the front wing (1) are also provided with flaps for roll control of the helicopter in the cruise mode;
a flight control system of a helicopter adopts a control scheme of a conventional four-rotor unmanned aerial vehicle, and can realize pitching, steering and rolling control in a helicopter hovering mode by controlling and managing the lift force of a plurality of lift force fans;
the lift fan (10) is an electrically driven fan, the power supply system comprises a generator, a rectifier and an inverter, the rectifier and the inverter are installed in the body (4), and the turbofan engine (5) directly drives the generator installed in the engine to generate power and transmits the power to a motor for driving the lift fan to rotate through the rectifier and the inverter.
2. A configuration of a hybrid electric propulsion based ultra high speed helicopter according to claim 1 characterized in that the main wing (8) and the front wing (1) adopt a fan-wing fusion design, the head and tail of the upper wing surface of the wing are curved surfaces, the middle is an upper wing plane, the lower wing surface of the wing is a lower wing plane, at the wing position where the lift fan is installed, the lift fan channel with an expansion lip and a square groove of the fan folding cover (3) are included, and the fan is fixed in the lift fan channel through a fan guide vane support.
3. A hybrid electric propulsion based ultra high speed helicopter configuration as claimed in claim 1 wherein said fan flap (3) comprises a first cover plate (31), a cover plate extension (32), a second cover plate (33), a rail slide bar (34), a rail groove (35) and a motor, said first cover plate (31) having one end connected to the wing at a fixed hinge point and connected to the motor shaft and the other end connected to the cover plate extension (32) in a coplanar manner, and two symmetrical hinge points are installed at the junction, said second cover plate (33) having one end connected to the first cover plate (31) through said two symmetrical hinge points and the other end provided with a rail slide bar (34) and fixed to the wing in the rail groove (35) and configured for opening and closing the lift fan duct, and the operation is:
(1) cruise state → hover state: the motor drives the first cover plate (31) to rotate clockwise, the angle formed by the first cover plate (31) and the second cover plate (33) is reduced, the guide rail slide bar (34) of the second cover plate (33) moves leftwards along the guide rail groove (35) until the first cover plate (31) and the second cover plate (33) are overlapped, and the process from closing to opening of the fan folding cover (3) is completed;
(2) hover state → cruise state: the motor drives the first cover plate (31) to rotate anticlockwise, the angle formed by the first cover plate (31) and the second cover plate (33) is increased until the first cover plate (31) and the second cover plate (33) are coplanar, and then the process from opening to closing of the fan folding cover (3) is completed.
4. The hybrid electric propulsion-based ultra-high-speed helicopter configuration as claimed in claim 1, characterized in that the ultra-high-speed helicopter is controlled by a flight control system and an engine controller and comprises four working processes of I-start, II-hover, III-mode switching and IV-cruise, during mode conversion, a pilot operates a throttle lever and a working mode switch, the flight control system coordinately controls the power output of a lift fan motor and a fan folding cover (3), the engine controller coordinately controls a bypass ratio, a nozzle area and a fuel flow, and the specific working process of the ultra-high-speed helicopter is as follows:
(1) i: the ultra-high speed helicopter is started, the fan folding cover (3) is completely opened, and the flying distance S is idle And a flying height H idle All are 0, the outer duct of the turbofan engine (5) is completely closed, the tail nozzle is completely expanded, and the rotating speed of the engine is accelerated to a slow vehicle rotating speed n idle ；
(2) I → II: ultra-high-speed helicopter climbing to hovering height H hover The engine controller increases the fuel flow and the rotor speed follows the slow speed n idle Accelerating to hover speed n hover And working at the suspension point A, the outer duct is still completely closed, the airflow can only enter the core machine through the inner duct, the tail nozzle is completely expanded to ensure that the speed of the airflow outlet of the inner duct is almost zero, namely, the jet propulsion force is hardly generated, at the moment, the turbine drives the generator to generate electricity to drive the plurality of lift fans to rotate, and the lift fans adopt the expanded lip to increase hovering and hoverAir inflow, wherein almost all energy of the engine in the mode is converted into hovering lift force of the ultra-high-speed helicopter;
(3) II → III → IV: the flight control system controls the rotating speeds of a plurality of lift fans, so that the ultrahigh-speed helicopter flies forwards at a low speed, the wings generate certain lift, the suspension point A accelerates to a hovering switching point B, then the controller slowly opens the outer duct and increases the fuel flow to adapt to the increase of the load of the duct fan, meanwhile, the tail nozzle slowly starts to converge, the work capacity of the inner duct turbine is weakened, the engine controller increases the fuel flow to realize the constant rotating speed of the turbine, the overall effect is that the jet propulsion of the inner duct and the jet propulsion of the inner duct are increased, then the flight control system reduces the power output of the lift fan motor, the rotating speed of the lift fan is reduced, the lift force of the wings is increased along with the increase of the flying speed, when the hovering switching point B is transited to a cruising switching point C, the outer duct is completely opened, the tail nozzle is completely converged, the rotating speed of the lift fan is zero, the lift force of the lift fan is completely replaced by the lift force of the lift fan, then the folding cover (3) is switched from open to close, the aerodynamic efficiency of the wings is increased, the cruise speed is accelerated from the point C to the D, almost all energy of the engine is converted into the jet propulsion of the helicopter, the ultrahigh-speed is unchanged, and the thrust of the ultrahigh-speed is slowly increased;
(4) IV → III → II: the engine controller reduces the fuel flow, the flight control system opens the fan folding cover (3), the ultra-high speed helicopter decelerates from a cruising D point to a switching C point, at the moment, the engine controller starts to slowly close the outer duct and expand the tail spray pipe, the flight control system accelerates the lift fan, and almost all energy of the engine is converted into the lift force of the lift fan when finally transitioning to a hovering switching point B, the engine can decelerate from the point B to the point A according to the descending height requirement, the total lift force is unchanged in the switching process, and the propulsion force is slowly reduced;
in the turbofan engine (5), the oil supply curves of the engine controller are close to the overtemperature surge boundary line in the processes of I → II → III → IV and IV → III → II → I.
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| CN113022847A (en) * | 2021-03-11 | 2021-06-25 | 北京航空航天大学 | High-speed helicopter with vector duct tail rotor |
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| US20030136873A1 (en) * | 2000-10-03 | 2003-07-24 | Churchman Charles Gilpin | V/STOL biplane aircraft |
| US20090008510A1 (en) * | 2006-03-03 | 2009-01-08 | David Posva | Aircraft having the ability for hovering flight, fast forward flight, gliding flight, short take-off, short landing, vertical take-off and vertical landing |
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| CN115196008B (en) | 2024-03-22 |
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