CN103879556A - Wide flight envelop morphing aircraft - Google Patents

Wide flight envelop morphing aircraft Download PDF

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CN103879556A
CN103879556A CN201410125750.1A CN201410125750A CN103879556A CN 103879556 A CN103879556 A CN 103879556A CN 201410125750 A CN201410125750 A CN 201410125750A CN 103879556 A CN103879556 A CN 103879556A
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wing
sweepforward
low
engine
air duct
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CN103879556B (en
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冯加伟
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Abstract

The invention discloses a wide flight envelop morphing aircraft. The skimming direction, aspect ratio and airfoil type of an airfoil are changed by adopting a morphing manner of a folding airfoil, so that the applicability of the aerodynamic configuration in the wide flight envelop can be improved; an engine is ingeniously combined with a turbojet engine and a dual-mode stamping engine, so that the problems of the engine, such as fewer common runners, large dead weight and difficult ultrasonic burning can be solved; on the aspect of the aerodynamic configuration, a wave-rider machine head is combined with a machine body, a canard is combined with an edge strip, an airfoil front edge notch is combined with a forward-skimming foldable outer airfoil, so that the high performance of the aircraft in a wide speed interval and under the multiple flight gestures can be guaranteed. On the aspect of the engine, a fan rotor is arranged between a low-pressure compressor and a high-pressure compressor and combined with the technologies such as reduction transmission, precooling of fuel gas and the like, the overall performance of the engine is greatly improved; the flow field thrust vector technology is superimposed onto a binary vector to obtain a blow-jet deviation angle of +/-40DEG, so that the mobility and controllability of the aircraft can be improved.

Description

Wide flight envelope morphing aircraft
Technical field
The present invention relates to a kind of aircraft.
Background technology
In recent years, round the various possibilities of following fighter plane development, people have carried out exploring widely.One of main direction has: flying speed faster, higher flying height and unmanned control.Require it can take into account the airworthiness under various height, various attitude.More focus on very long range striking capabilities, outstanding hypervelocity flight, and further strengthen subsonic velocity manoevreability and the supersonic speed manoevreability of modern combat aircraft at low-to-medium altitude.
Summary of the invention
Technical matters to be solved by this invention is to provide one can, according to needs such as flight environment of vehicle, flight profile, mission profile and combat duties, independently change aerodynamic configuration, optimizes the wide flight envelope morphing aircraft of airworthiness.
For solving the problems of the technologies described above, technical scheme of the present invention is: wide flight envelope morphing aircraft, under low speed mode or high speed mode, work or conversion mutually, comprise head and fuselage, shown in the both sides, rear portion of head have canard, the both sides of described fuselage are fixed with sweepback inner wing, the wingtip of described sweepback inner wing is provided with the folding outer wing of sweepforward, the top, rear portion of described fuselage is provided with a pair of full dynamic formula vertical tail, two combination engines are installed in described fuselage, the admission port of described combination engine is positioned at the bottom front of described fuselage, the afterbody of described fuselage is provided with two vector spouts corresponding to described combination engine.
Described Die Design is Waverider head.
The aerofoil profile of described sweepback inner wing is supercritical airfoil; The aerofoil profile of the folding outer wing of described sweepforward is " ∧ " shape missile wing; Under low speed mode, the folding outer wing of described sweepforward launches along the wingtip of described sweepback inner wing; Under high speed mode, described sweepforward folds the bottom surface that outer wing overturns and is fitted in described sweepback inner wing, and the aerofoil profile of the folding outer wing of described sweepforward becomes the inversion of low speed mode aerofoil profile; The fuselage at described canard rear portion is provided with the edge strip extending to both sides.
Described combination engine comprises turbojet engine and dual-mode scramjet.
Described dual-mode scramjet comprises the by-pass air duct that is provided with by-pass air duct admission port, and the front end of described by-pass air duct is outer culvert inlet channel, and described by-pass air duct admission port is positioned at described underbelly and described Waverider head end; Described fuselage is provided with oxidizer Fuel Tank and deoxidation compound Fuel Tank; The inside face of described outer culvert inlet channel is provided with propellant spray mouth.
Described turbojet engine is arranged in described by-pass air duct, comprise the intension inlet channel that is provided with main duct admission port, in described intension inlet channel, low-pressure compressor is installed, described main duct admission port is positioned at described outer culvert inlet channel, described main duct admission port is distinguish and the taper case that can close completely, and it is tip cone forward that described taper case is closed rear profile; After described intension inlet channel, be provided with fan propeller, described fan propeller comprises fan blade, fan petiole and rotor block, and described fan blade is positioned at described by-pass air duct; The described by-pass air duct being positioned at after described fan propeller is provided with main main duct, in described main main duct, high-pressure compressor is installed, in described main main duct after described high-pressure compressor, be provided with precompression chamber, after described precompression chamber, be provided with intension combustion chamber, in described intension combustion chamber, be provided with propellant spray mouth; After described intension combustion chamber, be provided with one-level high-pressure turbine, described high-pressure turbine is fixedly connected with by high pressure rotor axle with described high-pressure compressor; After described high-pressure turbine, be provided with two-stage low-pressure turbine, described low-pressure turbine turns to contrary with high-pressure turbine; Described low-pressure turbine is fixedly connected with by low pressure rotor axle with low-pressure compressor, and described fan propeller is connected with described low pressure rotor axle by fan speed change device; Described high pressure rotor axle is hollow shaft and is sleeved on outside described low pressure rotor axle, and described fan propeller is arranged on described low pressure rotor axle.
Described main main duct after described low-pressure turbine is provided with main main duct exhausr port, the exhaust adjustment sheet that described main main duct exhausr port is provided with size-adjustable and can closes completely; Described main main duct exhausr port is positioned at described by-pass air duct; Between described vector spout and described main main duct exhausr port, be provided with the by-pass air duct extension as afterburner.
The spatial placement of the described by-pass air duct outside described main main duct is outer culvert combustion chamber.
Described vector spout is rectangle vector spout, comprise two up and down can deflection ± 20 ° baffle.
As preferred technical scheme, the relatively described sweepback inner wing of front end of the folding outer wing of described sweepforward is more forward, after gap between the folding outer wing of described sweepforward and described sweepback inner wing is leaned on relatively, and the lower camber line of the folding outer wing first half section of described sweepforward is straight downward-sloping.
As the improvement to technique scheme, the maximum ga(u)ge of the folding outer wing of described sweepforward is at wing chord 68% place.
As preferred technical scheme, in the time of described not deflection of canard, described canard and described edge strip form continuous pneumatic face.
As the improvement to technique scheme, described canard and described edge strip have the inverted diherdral of 4 °.
As the improvement to technique scheme, the clinoid of described canard at the wing root chord of described canard from front end 85%.
As preferred technical scheme, the leading edge sweep at the wingtip place of described sweepback inner wing increases and forms a leading edge of a wing breach with the folding outer wing of described sweepforward.
As preferred technical scheme, described sweepback inner wing has the inverted diherdral of 4 °.
As preferred technical scheme, described by-pass air duct admission port is provided with the lower lip of deflection certain angle up and down.
As preferred technical scheme, in described deoxidation compound Fuel Tank, liquified hydrogen or liquid hydrocarbon are housed, in described oxidizer Fuel Tank, liquid oxygen is housed.
As preferred technical scheme, described head lower surface, whole described by-pass air duct inwall are provided with H Exch, the double fuel feed line being connected with described propellant spray mouth that does of described H Exch.
As preferred technical scheme, described fan speed change device comprises the sun gear being rotatably installed on described low pressure rotor axle, be rotatably installed in the planetary wheel on described sun gear, described planetary wheel is provided with gear ring outward, described gear ring is fixedly connected with rotor block, described rotor block periphery is installed with described fan petiole, and described rotor block is rotatably installed on described low pressure rotor axle; Between described sun gear and described low pressure rotor axle, power-transfer clutch is installed.
As preferred technical scheme, described fan blade is variable-distance blade.
As preferred technical scheme, described high-pressure compressor is level Four axial-flow type Blisk.
As preferred technical scheme, the admission port place of described main main duct is provided with to regulate opens big or small flow deflector.
As preferred technical scheme, in described precompression chamber, be provided with H Exch, the double fuel feed line being connected with described propellant spray mouth that does of described H Exch;
As preferred technical scheme, in described baffle, be provided with the injection passage of a hollow, described injection passage is provided with an injection entrance as admission port; Described injection passage is provided with three injection outlets, be positioned at described vector nozzle divergence section reference position and be provided with main injection outlet, be positioned at described vector nozzle divergence section middle part and afterbody and be respectively equipped with middle part injection outlet and the outlet of afterbody injection, described main injection outlet, the outlet of middle part injection and the outlet of afterbody injection are all provided with by-pass valve control.
As preferred technical scheme, described injection entrance is grid type admission port.
Owing to having adopted technique scheme, the present invention adopts the variant mode of folded wing to change wing and plunders to, aspect ratio and aerofoil profile, improves the adaptive capacity of aerodynamic configuration in wide flight envelope; The ingenious combination turbojet engine of driving engine and dual-mode scramjet, solve the problems such as this type of driving engine runner shares less, deadweight is many, the difficult realization of supersonic combustion; Aspect aerodynamic configuration, by the complementation that combines with the folding outer wing of sweepforward of Waverider head and fuselage, canard and edge strip, leading edge of a wing breach, guarantee the High Performance of aircraft under wide speed interval, many flight attitudes.At context engine, fan propeller is arranged between low-pressure compressor and high-pressure compressor and the design such as deceleration transmission, combustion gas precooling in conjunction with utilizing, significantly promote the overall performance of driving engine; The present invention is superimposed to flow field Thrust Vectoring Technology and binary vector spray, obtained ± the jet deflexion angle of 40 °, significantly promoted maneuverability and the controllability of aircraft.
The present invention can change aerodynamic configuration awing, can be in property retention optimum regime under different flight state.Compared with the fixing layout aircraft of routine, flight envelope of the present invention is wider, and fighting efficiency is higher, and it can, according to needs such as flight environment of vehicle, flight profile, mission profile and combat duties, independently change aerodynamic configuration, optimizes its airworthiness.And combination engine has been integrated turbojet engine and the advantage of dual-mode scramjet in each self application flight range, the advantage such as making it have can CTOL, repeated usage, reliability high, low speed performance is good, technical risk is low, has good future in engineering applications.
Accompanying drawing explanation
Fig. 1 is each mode of the each parts of the embodiment of the present invention and the schematic diagram of speed corresponding relation;
Fig. 2 is the block diagram of the folding outer wing of embodiment of the present invention sweepforward under deployed condition;
Fig. 3 is the birds-eye view of Fig. 2;
Fig. 4 is the right elevation of Fig. 3;
Fig. 5 is the block diagram of the folding outer wing of embodiment of the present invention sweepforward under folded state;
Fig. 6 is the right elevation of Fig. 5;
Fig. 7 is the aerofoil profile schematic diagram of embodiment of the present invention sweepback inner wing;
Fig. 8 is the aerofoil profile schematic diagram of the folding outer wing of embodiment of the present invention sweepforward;
Fig. 9 is the closed aerofoil profile schematic diagram of the folding outer wing of embodiment of the present invention sweepforward and sweepback inner wing;
Figure 10 is that the pneumatic efficiency of buzzard-type wing and swept wing is with the change curve of speed;
Figure 11 is the air hydrodynamic schematic diagram of the closed aerofoil profile of the embodiment of the present invention, in figure: N onfor the air hydrodynamic that top airfoil forms, N underfor the air hydrodynamic that lower aerofoil forms, N closefor the air hydrodynamic that upper and lower aerofoil forms is made a concerted effort, F risefor N closeperpendicular to the component of horizontal surface, F resistancefor N closebe parallel to the component of horizontal surface;
Figure 12 is the shock wave schematic diagram of the closed aerofoil profile of the embodiment of the present invention;
Figure 13 is the schematic cross-section of embodiment of the present invention Waverider head;
The air hydrodynamic schematic diagram of canard and edge strip when Figure 14 is embodiment of the present invention At High Angle of Attack attitude;
Figure 15 is the I place enlarged drawing in Fig. 3, there is shown the leading edge of a wing breach that the folding outer wing of sweepback inner wing and sweepforward forms;
Figure 16 is the structure principle chart of embodiment of the present invention combination engine;
Figure 17 is the structure principle chart of the core engine of embodiment of the present invention combination engine;
Figure 18 is the structure principle chart of embodiment of the present invention fan propeller;
Figure 19 is the fundamental diagram of embodiment of the present invention fan blade;
Figure 20 is the fundamental diagram one of embodiment of the present invention low-pressure compressor;
Figure 21 is the fundamental diagram two of embodiment of the present invention low-pressure compressor;
Figure 22 is the fundamental diagram of embodiment of the present invention combination engine under turbofan mode;
Figure 23 is the fundamental diagram of embodiment of the present invention combination engine under the jet mould state of whirlpool;
Figure 24 is the fundamental diagram of embodiment of the present invention combination engine supersonic combustion punching press mode;
Figure 25 is the fundamental diagram of embodiment of the present invention combination engine subsonic combustion punching press mode;
Figure 26 is the structure principle chart of embodiment of the present invention vector spout;
Figure 27 is the fundamental diagram of embodiment of the present invention vector spout shrinkage expansion mode;
Figure 28 is the fundamental diagram of embodiment of the present invention vector spout shrinkage expansion mode Secondary Flow;
Figure 29 is the fundamental diagram of embodiment of the present invention vector spout flow field deflection vector;
Figure 30 is the fundamental diagram of embodiment of the present invention vector spout flow field vector mechanical deflection;
In figure: 1-head; 2-fuselage; 3-canard; 4-sweepback inner wing; 5-sweepforward folds outer wing; 6-vertical tail; 7-combination engine; 8-vector spout; 81-baffle; 9-edge strip; 10-dual-mode scramjet; 11-turbojet engine; 121-by-pass air duct admission port; Lip under 121a-; 122-by-pass air duct extension; 123-is contained inlet channel outward; 124-is contained combustion chamber outward; 12-by-pass air duct; 13-propellant spray mouth; 141-main duct admission port; 14-intension inlet channel; 15-low-pressure compressor; 16-taper case; 17-fan propeller; 171-fan blade; 172-fan petiole; 173-rotor block; The main main duct of 18-; The main main duct exhausr port of 181-; 182-exhaust adjustment sheet; 19-high-pressure compressor; 20-precompression chamber; 21-intension combustion chamber; 22-high-pressure turbine; 221-high pressure rotor axle; 23-low-pressure turbine; 231-low pressure rotor axle; 24-leading edge of a wing breach; 25-H Exch; 26-fuel feed line; 27-sun gear; 28-planetary wheel; 29-gear ring; 30-power-transfer clutch; 31-flow deflector; 32-injection passage; 33-injection entrance; The main injection outlet of 341-; The injection outlet of 342-middle part; The outlet of 343-afterbody injection; 344-by-pass valve control; 35-droope snoot; 36-flaperon.
The specific embodiment
Understand for technical characterictic of the present invention, object and effect being had more clearly, now contrast accompanying drawing explanation the specific embodiment of the present invention.
The future after decades is based in the design of wide flight envelope morphing aircraft, mainly uses of the new technology, new ideas.Consider its practical situations simultaneously, meet the requirements to unmanned plane, fighter plane and hypersonic aircraft.The present invention need to have and is not less than the advantage of modern combat aircraft in low-speed maneuver, also has certain hypersonic cruising ability of sub-track, gains the initiative by striking first and the object of long-range prompt global strike to reach in future war.The present invention and driving engine thereof had both needed to guarantee to be not less than the speed cruising flight of 6Ma, also need in the time of low-speed operations, have better pneumatic efficiency and compared with high thrust.
The present invention is as a wide flight envelope morphing aircraft, and making overall plans between its all parts, each mode is also one of design point.Aerodynamic configuration of the present invention, driving engine and vector spout can change morphosis and mode of operation, and therefore have different operation modes.Aerodynamic configuration of the present invention is divided into low speed mode and high speed mode, driving engine of the present invention is divided into turbofan mode, whirlpool jet mould state, subsonic combustion punching press mode and supersonic combustion punching press mode (both can be collectively referred to as " dual-mode scramjet " afterwards), and vector spout of the present invention is divided into shrinkage expansion mode and expansion mode.Each mode of the each parts of the present invention and the corresponding relation of speed are as shown in Figure 1.
As Fig. 2, Fig. 3, shown in Fig. 4 and Fig. 5, the wide flight envelope morphing aircraft of the present embodiment comprises head 1 and fuselage 2, shown in the both sides, rear portion of head 1 have canard 3, the both sides of described fuselage 2 are fixed with sweepback inner wing 4, the wingtip of described sweepback inner wing 4 is provided with the folding outer wing 5 of sweepforward, the top, rear portion of described fuselage 2 is provided with a pair of full dynamic formula vertical tail 6, two combination engines 7 are installed in described fuselage 2, the admission port of described combination engine 7 is positioned at the bottom front of described fuselage 2, the afterbody of described fuselage 2 is provided with two vector spouts 8 corresponding to described combination engine 7.
, supersonic speed hypersonic in order to take into account, subsonic velocity and At High Angle of Attack attitude, the present embodiment adopts the variant mode (referred to as folding wings) of folded wing that buzzard-type wing is combined with " ∧ " shape missile wing with swept wing, conventional aerofoil profile, and Waverider, canard, edge strip, wing breach etc. are carried out to combination design, to optimize the airworthiness under thru-flight envelope curve and all flight attitudes.
The aerodynamic configuration of the present embodiment is divided into low speed mode and high speed mode, and the conversion between two mode realizes by folded wing.Its wing is divided into 4 two sections of the folding outer wing 5 of sweepforward and sweepback inner wings, and sweepforward folds outer wing 5 wide-angle sweepforwards, the 4 low-angle sweepback of sweepback inner wing.As shown in Figure 7, sweepback inner wing 4 aerofoil profiles are similar to the supercritical airfoil of elongation to the aerofoil profile of sweepback inner wing 4; As shown in Figure 8, and the maximum ga(u)ge of the folding outer wing 5 of sweepforward is at wing chord 68% place, after relatively leaning on for the aerofoil profile of the folding outer wing 5 of sweepforward.And the upper camber line of the folding outer wing 5 aerofoil profile first half sections of sweepforward is inclined upwardly very straightly, profile is similar to " ∧ " shape missile wing of upset.
4 fusions of sweepback inner wing are connected on fuselage 2, and sweepback inner wing 4 is connected through the hinge with the folding outer wing 5 of sweepforward, and the folding outer wing 5 of sweepforward can rotate 184 ° around sweepback inner wing 4 wingtips in the time of flight, as shown in Figure 6.
When the present embodiment uprises fast mode by low speed mode, thereby the folding outer wing 5 of sweepforward inwardly rotates 184 ° by open configuration and fits with sweepback inner wing 4, form new closed aerofoil profile as shown in Figure 9 with sweepback inner wing 4, and merge mutually with canard, new aircraft leading edge and the wing shapes of the common formation of three, specifically refer to Fig. 5.During by high speed mode step-down speed mode, program is contrary.
The hinge type mapped structure of folding wings is fairly simple physical construction, and the change wing of its folding relative alternate manner of mapping mode, have be convenient to safeguard, cost is low, the advantage such as little particularly takes up room.The present embodiment not only simple in structure and act on powerful, aerodynamic arrangement that both can change of flight device, aerofoil profile that again can change of flight device.
The essence of folding wings is to switch between forward-swept-wing configuration and swept-wing layout, changes the span and aspect ratio simultaneously.Figure 12 is that the pneumatic efficiency of buzzard-type wing and swept wing is with the change curve of speed.
As can be seen from the figure, the pneumatic efficiency of buzzard-type wing in the time of subsonic velocity is significantly higher than swept wing.And after supersonic speed, swept wing starts to preponderate gradually.Folding wings makes folding outer wing 5 buzzard-type wings of the present embodiment sweepforward in the time of low speed mode, has very high At High Angle of Attack performance and manoevreability when subsonic velocity.And make the present embodiment become swept wing in high speed mode, the resistance while significantly reducing hypersonic flight.Folding wings by change wing plunder to, thereby make wing in all flight envelopes, keep optimum pneumatic efficiency.
As everyone knows, low aspect ratio, highly swept aircraft are suitable for high-speed flight, but performance is not good when low-speed operations.And the aircraft of high aspect ratio, low sweep angle is applicable to low-speed operations, its subsonic velocity 1ift-drag ratio is larger, but is not suitable for high-speed flight.Due to the effect of folding wings, when the present embodiment is when low speed mode becomes high speed mode, its aspect ratio becomes 0.79 from 2.49, and wing setting becomes 56.3 ° from 19.8 °.Thereby make the present embodiment can both keep best airworthiness in the time of low-speed operations and high-speed flight.
Mapping mode by folding wings knows, after low speed mode becomes high speed mode, the folding outer wing 5 of sweepforward fits with sweepback inner wing 4, and the folding outer wing 5 of sweepforward spins upside down, and its aerofoil profile becomes the inversion of low speed mode aerofoil profile.As shown in Figure 5, because the folding relative sweepback inner wing 4 of outer wing 5 of sweepforward is more forward, so now the front end of closed aerofoil profile is the front end of the folding outer wing 5 of sweepforward, the bottom of closed aerofoil profile first half section is that sweepforward folds outer wing 5.After this leans on gap between the folding outer wing 5 of sweepback inner wing 4 and interior sweepforward relatively, and the lower camber line of aerofoil profile first half section is straight downward-sloping.
Air hydrodynamic when hypersonic flight is very large, and wing front end can produce oblique shock wave.As shown in figure 11, the lower camber line of closed aerofoil profile first half section is straight downward-slopingly makes it can be as " ∧ " shape missile wing, and the aerofoil of declivity also produces power upwards when air compressing is produced to power backward, thereby utilizes air hydrodynamic to produce lift.Its anterior oblique shock wave forming can further be strengthened this compression lift.When hypersonic flight, this dependence air hydrodynamic provides compression lift mode, and more conventional aerofoil profile has higher efficiency.
As seen from Figure 11, top airfoil also can produce air hydrodynamic, and it causes the lift of aerofoil profile to reduce resistance increment.The size of top airfoil air hydrodynamic depends primarily on the flatness of closed aerofoil profile top airfoil, and the existence of sweepback inner wing 4 makes the top airfoil of closed aerofoil profile protruding upward just.In order to reduce sweepback inner wing 4 protrusion degree, the present embodiment is the more straight supercritical airfoil in stage casing by sweepback inner wing 4 Airfoil Design, closed aerofoil profile top airfoil is tried one's best straight time, the appearance of shock wave can also postpone high subsonic velocity time, reduce the degree that boundary-layer separates, increase the Mach number increment between critical Mach number and drag divergence Mach number.Therefore can obtain good high subsonic velocity and airworthiness transonic speed.
In addition, as can be seen from Figure, the present embodiment has been partially submerged into sweepback inner wing 4 the folding outer wing 5 of sweepforward of upset, sweepback inner wing 4, the folding outer wing 5 of sweepforward are fitted more closely, also further optimized the upper lower aerofoil of closed aerofoil profile, make it transition more level and smooth, top airfoil is more straight, has improved 1ift-drag ratio.Secondly, the adjusting of the droope snoot 35 of sweepback inner wing 4 can make sweepback inner wing 4, the folding outer wing 5 of sweepforward fit tightr.The droope snoot 35 of the folding outer wing 5 of sweepforward can regulate the inclination angle of compression ramp, thereby changes the size and Orientation of air hydrodynamic.
The problem that may cause adverse effect for the gap between sweepback inner wing 4, the folding outer wing 5 of sweepforward, contriver thinks that it is unimportant.First,, because sweepback inner wing 4, the folding outer wing 5 of sweepforward embed mutually, the folding outer wing 5 of sweepforward has certain effect of blocking to this gap.In addition, the oblique shock wave that wing front end forms has deflecting action to incoming flow, makes its flow direction have the component that deviates from gap, thereby further weakens the impact in gap.
The closed aerofoil profile (High Mach number, high reynolds number) in the time of hypersonic flight that folding wings forms has compared with high lift efficiency and 1ift-drag ratio, has proved feasibility and the preceence of folding wings aspect aerofoil profile.
Folded wing formula its variant designs makes the present embodiment change aerodynamic arrangement, sweepback angle, aspect ratio and aerofoil profile according to different flying speeds, has the advantages such as variable parameter is many, mapped structure is simple compared with other its variant designs.Can meet better the different demands of the present embodiment to high speed and low speed, guarantee can have optimum performance in all flight envelopes.
Waverider is a kind of hypersonic lifting body, and it has shock wave to be attached to its leading edge in the time that design point flies, just as whole lifting body rides on shock wave.This makes it in the time of hypersonic flight, have very high lift efficiency.The head 1 of the present embodiment adopts Waverider design, and higher airworthiness when guaranteeing hypersonic flight, can match with fuselage 2 and combination engine 7 simultaneously better.
The design of the present embodiment Waverider head 1 has adopted by the known anti-method of designing as departure point without sticky compressible supersonic flow field, and the moderate 6Ma of access speed is design point.In addition, selection can make β=12 of designed Waverider 1ift-drag ratio maximum as half benchmark circular cone Angle of Shock Waves of design Waverider.The present embodiment, after preliminary design generates Waverider prototype, is optimized and is incorporated in unit design, and final Waverider head 1 cross section forming as shown in figure 13.
The present embodiment Waverider head 1 merges with fuselage 2 and canard 3 perfections, has further reduced the resistance of complete machine, has improved the utilization ratio of Waverider head 1.In addition, the lateral margin of the present embodiment Waverider head 1 has certain inverted diherdral and lateral margin lower surface upwards arches upward, improve the distribution of pressure of its lower surface and increased the higher-pressure region area of lower surface, thereby help Waverider to obtain higher lift efficiency, provide compression effectiveness better air inlet also can to the admission port that is in fuselage 2 bottoms.
This design using Waverider as head 1, makes the present embodiment under hypersonic, have advantages of high lift, low resistance, high lift-drag ratio, thereby adapts to better high-speed flight.And the head 1 of its declivity also can with the supersonic combustion punching press mode matched of combination engine 7, when improving pneumatic producing effects, strengthen engine performance.Due to after the high lift of Waverider is mainly reflected in supersonic speed, after this makes supersonic speed, the present embodiment head 1 lift increases rapidly, has suppressed the phenomenon of moving after aerodynamic center after aircraft supersonic speed.In addition, the profile that Waverider head 1 is roomy not only more easily combines with fuselage 2, also can increase the internal capacity of forward fuselage 2, makes the present embodiment that the radar of larger diameter can be installed, thereby promotes its whole battle performance.
As shown in Figure 3, the present embodiment, by the unitized design of special canard and edge strip, makes both jointly form a pneumatic system.This pneumatic system not only can guarantee the low resistance in the time of high-speed flight, can also form powerful eddy current in At High Angle of Attack attitude, improves the flow condition of itself and fuselage 2, promotes the At High Angle of Attack performance of the present embodiment.
The present embodiment is in the time of not deflection, and canard 3 is coplanar with edge strip 9, and both combine together and form continuous pneumatic face.For with edge under anti-Waverider head 1 better merge, also, in order to adapt to lower anti-sweepback inner wing 4, canard 3 and edge strip 9 have the inverted diherdral of 4 °.The clinoid of described canard 3 at the wing root chord of described canard 3 from front end 85%, therefore, after canard 3 deflections, canard 3 no longer contacts with edge strip 9, both do not reconstruct continuous pneumatic face.
The Main Function of canard 3 deflections of the present embodiment is to provide faces upward the control torque of bowing, and forms favourable pneumatic coupling with edge strip 9, improves the aerodynamic characteristic of the present embodiment in the time of At High Angle of Attack attitude.
In the time of At High Angle of Attack attitude, canard 3 can form an eddy current jointly with edge strip 9, and this specification sheets is referred to as canard-edge strip whirlpool.This whirlpool starts to form from canard 3 leading edges, and blank is the body-shedding vortex of canard 3.When eddy current process edge strip 9, can be reinforced, blow and import canard-edge strip whirlpool by the lower surface high energy air-flow of letting out on edge strip 9 lateral margins, thereby significantly improve its turbulence rate and range of control.Canard-edge strip whirlpool can inswept sweepback inner wing 4 wing roots and wing body afterwards, slows down burbling and stronger vortex lift is provided.
As shown in figure 14, due to when the At High Angle of Attack attitude, the inclined to one side negative angle of the relative fuselage 2 of canard 3, therefore canard 3 can form one with edge strip 9 and tilts to point to upper surface Feng road.Fuselage 2 lower surface high pressure draft Jiang Youfeng roads flow to upper surface, cause poor the reducing of local pressure.Make the anterior loss of lift of fuselage 2, but therefore the lift of full machine can't reduce.Canard 3 forms Feng road with edge strip 9 lower surface high energy air-flow is introduced to upper surface, has strengthened canard-edge strip whirlpool, postpones high energy air-flow and breaks, for rear portion fuselage 2 and sweepback inner wing 4 provide stronger vortex lift.The mobile control to pneumatic of edge strip 9 and rear portion can also be strengthened in the effect of washing under canard 3 and canard-edge strip whirlpool, slows down burbling.Showing as on aerodynamic force, in the situation that not damaging lift, moves after full machine aerodynamic center, and stability nose-down pitching moment increases, and is conducive to the trim of the present embodiment and faces upward the control of bowing.
Another effect of canard 3 is to provide faces upward the control torque of bowing.But the jet deflexion angle of the vector spout 8 of and the present embodiment large due to flaperon 36 areas at fuselage 2 rear portions is up to ± 40 °, and both can provide the very large control torque of bowing of facing upward, and there is no need canard 3 to design too greatly.Therefore the canard 3 of the present embodiment is relatively little, to reduce to brake mechanical burden.
In addition, when the present embodiment is level-flight attitude or while changing high speed mode into, canard 3 does not participate in not deflection the trim of aircraft yet.At this moment canard 3 combines together with overall aerodynamic arrangement as one fixing pneumatic, thereby improves the 1ift-drag ratio of aircraft.Embody the wide flight envelope design concept of taking into account high-speed flight.And the trim work of aircraft is mainly completed by flaperon 36 and the vector spout 8 of afterbody.
Canard-edge strip system can be in the time of At High Angle of Attack attitude, by forming favourable pneumatic coupling, the stalling characteristics of the present embodiment is improved, lift forms platform, moves after facing upward the moment flex point of bowing, and stalling incidence increases.And its profile that is blended in overall aerodynamic arrangement can be taken into account again high-speed flight.Pneumatic efficiency strengthen its cruising flight in the manoevreability that significantly promotes the present embodiment time, has promoted whole battle performance.
From the variant mode of folding wings, the sweepback angle of wing when the sweepforward angle of the folding outer wing 5 of sweepforward is high speed mode when low speed mode, in order to guarantee the high speed performance of the present embodiment, this plunders angle must be larger.But when low speed mode, the large sweepforward angle of the folding outer wing 5 of sweepforward can be brought two problems: the one, and aeroelastic divergence problem, the 2nd, there is more serious unfavorable air flow status in buzzard-type wing wing root place.
The solution of first problem does not belong to aerodynamics category, is mainly concerned with structure design and material application aspect.In fact, this problem extensively existing with it at buzzard-type wing existing terms of settlement at present.Utilize the bending Coupling Deformation effect of composite structure just can overcome the shortcoming of buzzard-type wing aeroelastic divergence.By arranging the laying of different machine directions, can make the flexural deformation of wing cause additional negative torsional deflection, thereby offset the positive torsional deflection of buzzard-type wing being caused by lift, do not dispersed and lightweight buzzard-type wing.
And the solution of Second Problem, the present embodiment, by special configuration design, utilizes vortex system to disturb to control the unfavorable flow condition at the folding outer wing of sweepforward 5 wing root places.As shown in figure 15, at the wingtip place of sweepback inner wing 4, the leading edge sweep of sweepback inner wing 4 increases suddenly, forms a leading edge of a wing breach 24 with the folding outer wing 5 of sweepforward.In the time of At High Angle of Attack, this breach can form strong eddy current, and the separation bubble that folding sweepforward outer wing 5 wing root places can be piled up sweeps away, thereby improves the folding outer wing 5 disadvantageous air flow status in wing root place of sweepforward.And the folding outer wing volute of sweepforward that this breach whirlpool also can produce with the folding outer wing 5 of sweepforward becomes favourable interference.Because the folding outer wing 5 of sweepback inner wing 4, sweepforward is plunderred on the contrary, the folding outer wing of sweepforward whirlpool is contrary with the hand of rotation in breach whirlpool, and the flow direction of its contact surface is identical, and both strengthen mutually, and delayed crack forms stronger vortex lift.The pneumatic coupling in two whirlpools is herein called breach vortex system by this specification sheets.
This breach vortex system, in controlling sweepback inner wing 4 wingtips, the folding outer wing 5 wing root burbling of sweepforward, also for the present embodiment provides stronger vortex lift, and has solved the problem of the folding outer wing 5 unfavorable flow conditions in wing root place of sweepforward.Improve the At High Angle of Attack performance of the present embodiment, thus post stall maneuver and sustained maneuver ability while promoting its low speed mode.
The design of leading edge of a wing breach 24 is also the change airfoil characteristics in order to meet folding wings.From above, the closed aerofoil profile that folding wings forms has one of necessary condition of superior performance and is: the folding relative sweepback inner wing 4 of outer wing 5 of sweepforward is more forward.Could after wing closure, make so folding outer wing 5 aerofoil profiles of sweepforward before sweepback inner wing 4 aerofoil profiles, could form the good closed aerofoil profile of high speed performance.And if there is no this wing breach, the leading edge of sweepback inner wing 4, the folding outer wing 5 of sweepforward overlaps the joint at them, make the present embodiment in the time of high speed mode, at least cannot form previously described closed aerofoil profile at wing wingtip place, and sweepback inner wing 4, the folding outer wing of sweepforward 5 gaps are directly exposed in high speed incoming flow, likely cause extremely bad impact.
From the variant mode of folding wings, in the time of high speed mode, sweepback inner wing 4 leading edges will be covered by the folding outer wing 5 of sweepforward completely.Therefore sweepback inner wing 4 is plunderred to more free with the selection of plunderring angle.Sweepback inner wing 4 is designed to low-angle sweepback, can increases wing area, reduce unit wing load, and promote subsonic velocity pneumatic efficiency, thus the manoevreability while strengthening the present embodiment low speed mode.
In addition, in the present embodiment, sweepback inner wing 4 has the inverted diherdral of 4 °, and this is anti-in order to make when the high speed mode under wing, thereby utilizes better compression lift.Mention above, in high speed mode, closed wing produces lift by shock wave and air hydrodynamic.But the pressure that wing produces is not only downward, also to double side acting.The press packet that under the present embodiment, anti-wing can " scatter these " is held together, and obtains produce effects more.
Sweepforward folds outer wing-sweepback inner wing system and is associated by folding wings and pneumatic coupling, in conjunction with having applied the designs such as buzzard-type wing, swept wing, wing breach.In the time promoting low speed mode, separately in performance, take into account the characteristic of having applied folding wings, thereby improved overall performance.Again embody the wide flight envelope design concept of taking into account high low-speed operations.
In order to solve the problem of hypersonic flight stability rapid drawdown, the present embodiment has retained vertical tail 6(and has been called for short vertical fin) design.Its Main Function is to guarantee horizontal stability, participates in laterally controlling simultaneously.That therefore the area of the present embodiment vertical tail 6 is designed is less, and sweepback angle is larger, and has the camber angle of 30 °, to reduce weight, resistance and radar return.In addition, vertical tail 6 is designed to full dynamic formula, to strengthen horizontal control ability.
As shown in figure 16, based on the present embodiment, to low-speed high-thrust and the requirement simultaneously of hypersonic power, the combination engine 7 of the present embodiment is designed to tandem turbine base combined cycle engine.Combination engine 7, when subsonic velocity provides compared with high thrust, also can provide flying power, and can transit to from principal and subordinate's subsonic velocity hypersonic in the time of hypersonic flight.The combination engine 7 of the present embodiment is in friction speed interval, respectively with four kinds of different mode work, respectively: turbofan mode, v ∈ [0Ma, 0.8Ma]; Whirlpool jet mould state, v ∈ [0.8Ma, 3Ma]; Subsonic combustion punching press mode, v ∈ [3Ma, 5Ma]; Supersonic combustion punching press mode, v ∈ [5Ma, 15Ma].
As shown in figure 17, the core engine of combination engine 7 can be regarded a unconventional turbojet engine 11 as, and high-pressure compressor 19 is level Four axial-flow type, Blisk.Air inlet place of core engine after fan propeller 17 is called the admission port of main main duct 18, is provided with here to regulate to open big or small flow deflector 31.This flow deflector 31 is called throughput ratio adjustment sheet, it open size and can regulate the inside and outside throughput ratio of containing, thus make driving engine change throughput ratio in turbofan mode according to the different speed of aircraft and demand, improve the conformability of turbofan mode.
After high-pressure compressor 19, be precompression chamber 20, precompression chamber 20 is exactly the space of a hollow, within be provided with H Exch 25, the double fuel feed line 26 being connected with described propellant spray mouth 13 that does of described H Exch 25.Air is rear by H Exch 25 precoolings at the precompression chamber 20 of flowing through, and temperature declines and continues supercharging, thus the work of sharing part air compressor.This can design still less the progression of high-pressure compressor 19, thereby strengthens engine efficiency, increases thrust-weight ratio.
After precompression chamber 20, connect intension combustion chamber 21, the fuel mix after-combustion that air is vaporized in this and preheating.After intension combustion chamber 21, be one-level high-pressure turbine 22, high-pressure turbine 22 is called high pressure rotor with the rotor that high-pressure compressor 19 is fixedly connected to form by high pressure rotor axle 221.After high-pressure turbine 22, be two-stage low-pressure turbine 23, turn to contrary with high-pressure turbine 22.Low-pressure turbine 23 links with low-pressure compressor 15 and fan propeller 17, and low-pressure turbine 23 does not comprise fan propeller 17 with low-pressure compressor 15() rotor that is fixedly connected with rear formation by low pressure rotor axle 231 is called low pressure rotor.This high and low pressure rotor, to the mode of operation turning, acts on two most of counteractings of epitrochanterian gyro torque can make aircraft maneuvering flight time, reduce the moment load to aircraft, strengthens the handling of aircraft; This structure makes to be loaded on two middle bearing inner and outer ring switched in opposite between rotor in addition, has reduced the rotating speed of retainer with the relative inner and outer ring of rotor assembly, favourable to the work of bearing; And high and low pressure rotor is to turning the combustion gas pilot blade that also can save between high and low pressure turbine 23.Be to consider that low-pressure turbine 23 also will drive fan propeller 17 except will driving low-pressure compressor 15 and low-pressure turbine 23 is designed to secondary, its duty ratio is larger.Can increase complex structure degree and weight though be designed to secondary, reduce the load of single-stage turbine, improve turbine efficiency, thereby export more superpower for low-pressure compressor 15 and fan propeller 17.It after turbine, is main main duct exhausr port 181, described main main duct exhausr port 181 places are provided with exhaust adjustment sheet 182, its size-adjustable and can closing completely, its effect is except regulating core engine exhaust, can also form and seamlessly transit at subsonic combustion punching press mode and supersonic combustion punching press mode and by-pass air duct 12, burning and gas-exhausting will expand for the first time at this.
The combination engine 7 of the present embodiment has adopted the scheme of provided with fan rotor 17 between low-pressure compressor 15 and high-pressure compressor 19, in increasing turbofan mode and whirlpool jet mould state thrust efficiency, can better adapt to subsonic combustion punching press mode and supersonic combustion punching press mode.
As shown in Figure 18 and Figure 19, the fan blade 171 of the present embodiment is variable-distance, and variable-distance fan blade 171 designs except regulating the rate of supercharging of fan in turbofan mode, can also better adapt to other mode to by-pass air duct 12 permeabilities and resistance demand.Fan propeller 17 comprises fan blade 171, fan petiole 172 and rotor block 173 3 parts, and a part is the fan petiole 172 that is positioned at main duct, and it is comparatively very thin, only plays a supportive role; The part that is in by-pass air duct 12 is only fan blade 171, and therefore fan is only given by-pass air duct 12 supercharging airs.
Fan propeller 17 links by fan speed change device and low pressure rotor axle 231, and this interlock can disconnect by power-transfer clutch 30.In the time of turbofan mode, fan propeller 17 is driven by low pressure rotor axle 231, and fan blade 171 is to by-pass air duct 12 supercharging airs; And in the time of whirlpool jet mould state, subsonic combustion punching press mode and this three mode of supersonic combustion punching press mode, fan propeller 17 will disconnect interlock with low pressure rotor axle 231, stopping fan rotation, fan blade 171 displacements are adjusted to along slurry position, fan blade 171 is parallel with incoming flow, and fan blade 171 resistances are reduced as far as possible.The variable-distance of fan blade 171 has embodied engine design to the taking into account of different modalities, and has met the demand of the wide flight envelope of the present embodiment.
In the present embodiment, described fan speed change device comprises the sun gear 27 being rotatably installed on described low pressure rotor axle 231, be rotatably installed in the planetary wheel 28 on described sun gear 27, the outer gear ring 29 that is provided with of described planetary wheel 28, described gear ring 29 is fixedly connected with rotor block 173, described rotor block 173 peripheries are installed with described fan petiole 172, and described rotor block 173 is rotatably installed on described low pressure rotor axle 231; Between described sun gear 27 and described low pressure rotor axle 231, power-transfer clutch 30 is installed.
As shown in Figure 20 and Figure 21, in order to reduce resistance and to increase charge air, the low-pressure compressor 15 in driving engine forefront is designed to three grades of axial flow compressors, Blisk.Low-pressure compressor 15 has independently inlet channel, is called intension inlet channel 14.Intension inlet channel 14 is in outer culvert inlet channel 123, and its cross section is for circular and can close completely, and closing rear profile is a cone before sensing, can play compression in subsonic combustion punching press mode and external duct 12 air inlets of supersonic combustion punching press mode.
As shown in Figure 6, the inlet channel of by-pass air duct 12 is called outer culvert inlet channel 123, and its first half is being born all air inlets of main main duct 18 and by-pass air duct 12, and intension inlet channel 14 is being wrapped in rear portion.The by-pass air duct admission port 121 of outer culvert inlet channel 123 is positioned at the present embodiment fuselage 2 bottoms, Waverider head 1 end, sufficient air inlet can still can be provided like this in the time of aircraft at high angle of attack attitude, and can provide by the precompressed air inlet of Waverider for driving engine in the time of hypersonic flight.In the present embodiment, the lower lip 121a of the by-pass air duct admission port 121 certain angle of deflection up and down, is used for regulating air inlet.Outer culvert inlet channel 123 is inclined upwardly slightly, and this is the result that unit design is made overall plans, and can make the resistance of aircraft increase to some extent, but also makes inlet channel have certain bridging effect to engine blade, is conducive to stealthy.
By-pass air duct 12 rear portions are provided with the by-pass air duct extension 122 of the core engine of being longer than main main duct 18, make core engine exhaust be mixed and be discharged by by-pass air duct extension 122 with by-pass air duct 12 exhausts.This by-pass air duct extension 122 mixing modes make combination engine 7 in the time of turbofan mode and whirlpool jet mould state, and main main duct 18, by-pass air duct 12 air-flows can again do energy exchange before ejection, thereby improve engine efficiency; By-pass air duct extension 122 has function the convenient vector spout 8 of installing of afterburner.
By-pass air duct 12 is outdoor except the afterbunring at rear portion, in the middle, arises from fan propeller 17 until this section of main main duct exhausr port, for independently combustion chamber of by-pass air duct 12, is called outer culvert combustion chamber 124.This combustion chamber is as the major air cell of dual-mode scramjet 10.
The combination engine 7 of the present embodiment uses liquified hydrogen or liquid hydrocarbon, liquid oxygen as fuel, simultaneously as heat exchanging agent.In intension combustion chamber 21, establish propellant spray mouth 13 with outer culvert inlet channel 123 walls.
In the present embodiment head 1 surface, whole by-pass air duct 12 inwalls, precompression chamber 20 and propellant spray mouth 13 places be provided with H Exch 25.Wherein the H Exch 25 of by-pass air duct 12 inwalls is divided into independently two parts of front and back, and boundary is near fan propeller 17.
Arranging of H Exch 25 can shift to an earlier date precooling air inlet, increases the compression efficiency of air inlet; Also can play thermal protection effect to propellant spray mouth 13 and high-speed aircraft head.And use fuel can reduce structural weight and the complexity of heat-exchange system as heat exchanging agent, simplify pipe arrangement; Also make fuel shift to an earlier date preheating vaporization, more favourable to burning.
Mapping mode between mode of operation when combination engine 7 different modalities and mode:
1. turbofan mode
As shown in figure 22, now outer contain inlet channel 123 and intension inlet channel 14 all open and open larger, main main duct Exhaust Open.Now fan is in turbofan mode, and fan propeller 17 is driven by low pressure rotor by low pressure rotor-fan deceleration transmission system, and fan blade 171 is to by-pass air duct 12 supercharging airs.In precompression chamber 20, open with the H Exch 25 at propellant spray mouth 13 places, fuel first flows through the H Exch 25 in precompression chamber 20, then flows through the H Exch 25 at propellant spray mouth 13 places, finally injects combustion chamber and mixes with air.
At main duct, air flows into intension inlet channel 14 through outer culvert inlet channel 123 first halfs, then flows into low-pressure compressor 15.Low-pressure compressor 15 is driven by low-pressure turbine 23, to supercharging air.Due to the design of fan in the middle of combination engine 7 employings, therefore low-pressure compressor 15 can not be subject to the unfavorable interference of fan.The fan petiole 172 that major part can be flow through fan blade 171 by the air of low-pressure compressor 15 superchargings enters core engine; And have small part to be spilled over to by-pass air duct 12 from fan propeller 17, and can increase the pressure of by-pass air duct 12 exhausts and the fuel efficiency of driving engine, its effect is similar to " the middle duct " that the U.S. is the change circulation fanjet of the 6th generation opportunity of combat development.
High-pressure compressor 19 is driven rotation by high-pressure turbine 22, to enter core engine by the high pressure air supercharging again of low-pressure compressor 15 superchargings.Air is discharged into precompression chamber 20 afterwards.In precompression chamber 20, be pressurized and the high pressure draft of temperature rise flows through H Exch 25, do interchange of heat with low temp fuel.Fuel heats up, air-flow cooling.The cooling of air-flow can improve compression efficiency again, prepares as burning.
Precompression chamber 20 is also used for supercharged air, and it has shared the task of a part of air compressor supercharged air, thereby the progression of high-pressure compressor 19 can design still less.Therefore the high-pressure compressor 19 of combination engine 7 only has level Four rotor blade, has reduced structure complexity and the weight of driving engine, has shortened size, has reduced the startup inertia of high pressure rotor.And less air compressor progression also just means the load that turbine is less, to the energy consumption of combustion gas also just still less, combustion gas can retain more multipotency and, in order to drive low pressure rotor and last ejection to form thrust, indirectly improve rotating speed and the engine thrust of low pressure rotor.And precompression chamber 20 these hollow spaces between combustion chamber and air compressor, can play the effect of certain inhibition engine surge.
Fuel is after the interior burning of intension combustion chamber 21, and combustion gas is flow through successively and driven high-pressure turbine 22 and low-pressure turbine 23 to rotate.Combustion gas afterwards enters by-pass air duct 12 rear portions through main main duct exhausr port, will mix finally and be discharged by vector spout 8 with by-pass air duct 12 exhausts there.
At by-pass air duct 12, air enters by-pass air duct 12 through outer culvert inlet channel 123.Air mixes through the air by low-pressure compressor 15 superchargings fan forced and that overflow from intension with part afterwards, then from core engine, flows through and coolant core machine.Finally mix with core engine exhaust, sprayed by vector spout 8.Compared with the fanjet of modern combat aircraft, the bypass ratio of combination engine 7 is larger, has higher efficiency or larger thrust; This is to be also the reserved enough spaces of dual-mode scramjet 10 simultaneously.
As shown in figure 22, H Exch 25 and the external pipeline of propellant spray mouth 13(that fuel flows in precompression chamber 20 successively do not provide), finally at the interior injecting compressed air of intension combustion chamber 21.
2. whirlpool jet mould state
As shown in figure 23, now by-pass air duct admission port 121 opens littlely, and the taper case 16 of main duct admission port 141 opens larger.The power-transfer clutch 30 of described fan speed change device disconnects, and described low pressure rotor axle 231 dallies, and described sun gear 27 is motionless, thereby makes fan propeller 17 and low pressure rotor disconnect interlock.Now 23 of low-pressure turbines are used for driving low-pressure compressor 15, and low-pressure compressor 15 rise of rotational speed have met whirlpool jet mould state to the high efficiency demand of air compressor.Now fan propeller 17 stalls, fan blade 171 displacements, blade is parallel to incoming flow, reduces fan resistance as far as possible.The operation mode of other parts is similar during to turbofan mode.
Air enters low-pressure compressor 15 through main duct admission port 141 and intension inlet channel 14, flow into core engine by most of air after low-pressure compressor 15 superchargings through the fan petiole 172 of fan blade 171, and a small part air can be spilled over to by-pass air duct 12, when coolant core machine, increase by-pass air duct 12 stream pressures, improve engine efficiency.Flow into the air of core engine and flow through successively high-pressure compressor 19, precompression chamber 20, intension combustion chamber 21 and high-pressure turbine 22 again, the mode of operation of core engine is identical during with turbofan.
Because fan propeller 17 and low pressure rotor disconnect interlock, the load of low-pressure turbine 23 is reduced, rotating speed promotes, thereby improves the rate of supercharging of low-pressure compressor 15, has adapted to turbojet engine 11 to the high efficiency requirement of air compressor.
3. supersonic combustion punching press mode
Because the most of design point in dual-mode scramjet 10 is in order to meet supersonic combustion punching press mode, so this specification sheets is narrated before supersonic combustion punching press mode is placed on to subsonic combustion punching press mode.
In the time of supersonic combustion punching press mode, the taper case 16 of main duct admission port 141 is closed completely, forms the cone before a sensing.The admission port of outer culvert inlet channel 123 opens larger, and main main duct exhausr port is closed completely, forms the cone after a sensing.Fan blade 171 is still parallel to incoming flow, reduces the resistance of fan blade 171 as far as possible.On the present embodiment head 1 surface, the H Exch 25 at whole by-pass air duct 12 inwalls and propellant spray mouth 13 places opens.
After Waverider head 1 precompressed compression of air by the present embodiment, enter outer culvert inlet channel 123, and contain outside under the effect of the series of shock string in inlet channel 123 and continue deceleration supercharging.Above, mention, inlet channel is inclined upwardly a little, and this will certainly increase resistance.But the first shock wave that admission port front end produces slightly upward deflects air flow direction thereafter, and acclivitous inlet channel has in fact just in time adapted to the flow direction of air-flow.
Charge flow is crossed outer culvert inlet channel 123 afterwards and fuel mix flows through fan propeller 17 again, after fan propeller 17, is outer culvert combustion chamber 124.Outer culvert combustion chamber 124 arises from fan propeller 17 and terminates in main intension to exhausr port, and its length is very large as seen, and the present embodiment guarantees burning fully under supersonic speed in the mode of long combustion chamber.But its problem of bringing is to need cooling area also very large, this problem solves by the fuel that plays cooling effect flowing through in inwall herein.
Because combination engine 7 adopts middle fan design, intension, in fan place "off", communicates the provided with internal duct and external duct 12 at fan place.Therefore can depart from wall at fan place at the boundary-layer of intension outer wall and be involved in by-pass air duct 12 air-flows.And the high velocity air of by-pass air duct 12 can aspirate the air in intension by ejector action.The air pressure of intension can be because ejector action, far below by-pass air duct 12, even becomes class hollow state.This can form at fan place transverse-pressure gradient, the trend that the by-pass air duct 12 oriented centres of air-flow are drawn close.Simultaneously fan also plays the effect of certain vortex generator, and this two kinds of effects produce very complicated pneumatic coupling mutually, makes to form after fan the higher and baroque eddy current of intensity.The boundary-layer of intension outer wall is bound to be involved in eddy current, and the eddy current of by-pass air duct 12 inwalls is also probably involved in.Research shows, in the time of the abundant premix of fuel, in the boundary-layer of High Temperature High Pressure, can burn in advance.The boundary-layer that burning has occurred is involved in after eddy current, can cause rapidly the burning of other pre-mixing gas combustion, thereby light outer culvert combustion chamber 124.The particular design configuration of middle fan, makes combination engine 7 be spread and be maintained flame by the mode that forms eddy current and pre-burning boundary-layer is involved in, and has solved supersonic combustion igniting, flame spread and has maintained the problem of flame difficulty.
4. subsonic combustion punching press mode
As shown in figure 25, the mode of operation of the mode of operation of driving engine in the time of subsonic combustion punching press mode during with supersonic combustion punching press mode is identical, what just contain outside combustion chamber 124 interior generations is subsonic combustion, and supersonic flow is contained outside in inlet channel 123 and just slowed down diffusion to subsonic velocity.
Now the outer admission port of containing inlet channel 123 opens littlely, and vector spout 8 is adjusted to shrinkage expansion spout, and the mode of operation of other tunable component is identical during with supersonic combustion punching press mode.
Incoming flow is contained outside the interior deceleration of inlet channel 123 and is pressurized to subsonic velocity also and fuel mix, then accelerates to supersonic speed ejection by shrinkage expansion spout after outer culvert combustion chamber 124 burnings.
The combination engine 7 of the present embodiment combines the designs such as variable-pitch fan, middle fan, low pressure rotor-fan deceleration transmission system, combustion gas precooling, in realizing hypersonic flight power, has also obtained high thrust, big thrust loading at low speed.By optimizing the design of the each runner of each parts, the problems such as turbine base combined cycle engine runner shares less, deadweight is many are solved.Improve the thrust efficiency of turbofan and whirlpool jet mould state by middle fan design, and solved supersonic combustion punching press mode engine ignition, maintain the problem of flame difficulty.Combination engine 7 has met the power demand of the wide speed envelope curve of the present embodiment aircraft, makes it under all speed, all have powerful heart.
For an aircraft, vector spout is very huge on the impact of its performance.The vector spout 8 of the present embodiment, by flow field vectoring technology and traditional mechanical deflection vector are combined, has obtained the jet deflexion angle much larger than modern vector spout, can significantly improve the manoevreability of the present embodiment.And the design of the vector spout 8 of the present embodiment is also towards combination engine, can meet the different demands of combination engine 7 different modalities.The Main Function of the vector spout 8 of the present embodiment is the jet flow that regulates combination engine 7, control efficiency and the manoevreability that improves the present embodiment.
As shown in Figure 2, the vector spout 8 of the present embodiment is designed to rectangle vector spout, can be better and rear body 2 merge, and improve manoevreability, simplified structure, the Stealth Fighter of the complete machine back segment that also can guarantee better.
As shown in figure 26, the adjusting of the deflection vector of the vector spout 8 of the present embodiment, spout type and geometric shape conversion mainly by upper and lower two can deflection ± 20 ° baffle 81 complete.In baffle 81, have a hollow channel, this passage is called injection passage 32.Injection passage 32 has an admission port, is called injection entrance 33, and injection entrance 33 is grid type admission port, is used for adjusting air inflow quantity.Injection passage 32 has three outlets, and larger outlet is positioned at nozzle divergence section reference position, is called main injection outlet 341.Two other less outlet lays respectively at expansion segment middle part and afterbody, is called middle part injection outlet 342 and afterbody injection outlet 343.Three injection outlets are controlled size and open and close by by-pass valve control 344.
The mode of operation of vector spout:
1. shrinkage expansion mode
As shown in figure 27, in the time of turbofan mode, whirlpool jet mould state and subsonic combustion punching press mode most, the direct exhaust of engine chamber is all subsonic velocity, and vector spout 8 need to be accelerated to supersonic speed ejection.Now two baffles 81 form a shrinkage expansion spout.The size of opening of two baffles 81 can regulate spout throat size and export size.
As shown in figure 28, the outlet size of vector spout 8 is not only regulated by two baffles 81, and the Secondary Flow jet curtain that also enters vector spout 8 by injection regulates.Open injection entrance 33 and injection outlet, extraneous air will inject the expansion segment of vector spout 8, and the jet curtain of its formation can play the effect of certain inhibition jet cutting car flow expansion.Regulate injection rate and the Secondary Flow pressure of Secondary Flow by the size that regulates injection entrance 33 and injection outlet, regulate vector spout 8 to export big or small effect thereby play.
This by flow control regulate vector spout 8 to export big or small design, with respect to the mode of mechanical adjustment, have simple in structure, lightweight advantage.Thereby driving engine thrust-weight ratio is provided, and reduces the maintenance cost of vector spout 8.
2. expansion mode
In supersonic combustion punching press mode, the direct exhaust of engine chamber is supersonic speed, and vector spout 8 need to be accelerated higher speed ejection.Now 81 one-tenth of two baffles open shape, form an expansion vector spout.Open size adjustment vector spout 8 degrees of expansion with two baffles 81.Speed of incoming flow during due to this mode is too fast, and vector nozzle shape resistance is large.In order to reduce resistance as far as possible, in the time of this mode, injection entrance 33 and injection outlet Close All.
3. deflection vector
The vector spout 8 of the present embodiment, by flow field vectoring technology is combined with mechanical deflection vector, can obtain the jet deflexion angle that maximum reaches 40 °.But flight most of time, jet flow drift angle is without so huge.Therefore in the time that jet flow drift angle is between 0 to 20 °, the flow field vectoring technology that 8 uses of vector spout of the present embodiment change without too many machinery, to reduce access times and the degree of mechanical movable member, thereby increases reliability and the service life of vector spout 8.
3.1 flow field deflection vectors (0-20 °)
As shown in figure 29, in the time needing the angle of deflection to be less than 20 °, the vector spout 8 of the present embodiment only carries out jet deflexion by a kind of mode of mobile control.
When jet flow need to upward deflect 0-20 °, baffle 81 not deflections, injection entrance 33, the injection outlet of lower baffle 81 are all opened; The injection entrance 33 of upper baffle 81 closes or opens less, and injection outlet is all opened.At this moment in the time that jet flow flows through vector spout 8 venturi, due to ejector action, the air in upper and lower injection passage 32 is constantly aspirated.Because lower injection entrance 33 is opened, extraneous air constantly enters the air of lower injection passage 32 interior supplementary losses, and its internal pressure can change hardly.And closing after the air making in injection passage 32 is pumped of upper injection entrance 33 supplements nowhere, the pressure drop in upper injection passage 32 even becomes class vacuum state.This makes vector spout 8 in the vertical direction mineralization pressure gradients, and bottom pressure is high, and upper pressure is low.Jet flow upward deflects with pressure gradient.When jet deflexion angle is greatly to a certain extent time, jet flow can produce attached wall effect (Coanda effect) with upper baffle 81, and jet flow is flowed along upper baffle 81 surfaces, and deflection angle rises to.The stool and urine of the injection entrance 33 by regulating upper baffle 81 can regulate the pressure in upper injection passage 32, thereby regulates the variation size of pressure gradient, and then regulates the deflection angle of jet flow.While deflecting down 0-20 °, mode of operation is identical.
This deflection way by the control of flowing can make reach ± 20 ° of left and right of the deflection angle of jet flow, thrust efficiency 90% left and right.Realize with modern vector spout with isogonic and efficiency in, save a large amount of mechanical moving elements, simplify the structure, alleviated aircraft weight, reduced maintenance cost.
3.2 flow field deflection vector+mechanical deflections (20 °-40 °)
As shown in figure 30, in the time that angle of inclination are greater than 20 °, the vector spout 8 of the present embodiment need to carry out mechanical deflection on the basis of above-mentioned flow field vector.
When jet flow need to upward deflect 20 °-40 °, first the degree of deflection of flow field vector becomes maximum, latter two baffle 81 upward deflect simultaneously.The deflection angle of this mechanical deflection mode is ± 20 ° of left and right, and thrust efficiency is in 90% left and right.Superimposed with flow field deflection vector again, can reach ± 40 ° of left and right of the final deflection angle of jet flow, thrust efficiency 81% left and right.
The degree of deflection of the far super modern vector spout of the deflection vector of ± 40 °, will give that the present embodiment is extremely strong can handling and manoevreability, comprises the super maneuverability of fault speed.
Deflection vector (0-10 °) when 3.3 expansion mode
The vector spout 8 of the present embodiment is in order to reduce hypersonic resistance in the time of expansion mode, and injection gangway Close All, therefore can only use mechanical deflection.During due to hypersonic flight, can not do significantly maneuver, without the deflection vector of wide-angle.Therefore the vector spout 8 of the present embodiment in expansion the be made as ± 10 ° of left and right of mechanical deflection angle when mode, be mainly used in meeting the trim demand of the present embodiment.
The main design parameters of the present embodiment (in this specification sheets to the calculating of relative area take low speed mode gross wing area as calculating parameter):
Captain 20.929m High speed mode gross wing area 36.926m 2
High speed mode machine width 13.32m The span of high speed mode wing 5.412m
Low speed mode machine width 18.72m High speed mode wing aspect ratio 0.7932011
Machine is high 2.327m High speed mode wing setting 56.3°
Low speed mode gross wing area 46.856m 2 Wing body area 38.092m 2
The span of low speed mode wing 10.812m ? ?
Low speed mode wing aspect ratio 2.49486392 ? ?
Sweepback inner wing area 28.696m 2 Sweepforward folds outer blade area 18.16m 2
Sweepback inner wing sweepback angle 19.8° Sweepforward folds outer wing sweepforward angle 56.3°
The span of sweepback inner wing 5.412m Sweepforward folds the outer wing span 5.4m
Sweepback inner wing aspect ratio 1.02069083 Sweepforward folds outer wing aspect ratio 1.60572687
Sweepback inner wing is with tip ratio 2.28911343 The folding outer wing of sweepforward is with tip ratio 1.07464528
Sweepback inner wing inverted diherdral 4° Sweepforward folds outer wing inverted diherdral 0°
Canard area 6.21m 2 Vertical tail area 4.534m 2
Canard relative area 13.253372％ Vertical tail area ratio 9.676456％
Canard leading edge sweep 65.7° Fin sweep 59.7°
Trailing edge of canard sweepback angle 31.3° The vertical tail span 2.87m
The canard span 3.304m Fin and rudder aspect ratio 1.8169607
Canard aspect ratio 1.75787697 Vertical tail is with tip ratio 3.00972222
Canard is with tip ratio 3.56938326 Vertical tail camber angle 30°
Canard inverted diherdral 4° ? ?
The present invention is as a morphing aircraft, and the variant structure of its folded wing makes it can change more aerodynamic parameters, and simplifies variant structure; Reach the high motor-driven and hypersonic object of cruising of low speed, had higher variant efficiency compared with other morphing aircraft.
As a fighter plane, the present invention is in conjunction with having applied canard, edge strip, buzzard-type wing, swept wing and wing breach, by ingenious coupling vortex system, when solving the pneumatic defect in many places, significantly strengthen At High Angle of Attack performance of the present invention, make it have the manoevreability being not of the common run.And the designs such as combustion gas precooling, deceleration transmission, middle fan are incorporated to the turbofan mode of combination engine 7, by further optimization detailed design, improve efficiency and the thrust-weight ratio of driving engine, thereby guaranteed the high power demand of the present invention as a fighter plane.
As a hypersonic aircraft, the present invention has adopted the designs such as Waverider, compression lift aerofoil profile, large sweepback angle delta wing, in conjunction with the correlation properties of folding wings and the related needs of combination engine 7, make its high speed mode aerodynamic configuration in the time of hypersonic flight, have higher pneumatic efficiency.And the special intension configuration of fan design in the middle of utilizing, solve the difficult problem of lighting a fire when dual-mode scramjet 10 surpasses combustion.Further the function of the each parts of optimal combination driving engine 7, each duct, when making it meet hypersonic power demand, has greater efficiency.
Vector spout 8 of the present invention, in meeting the different demands of driving engine different modalities, by by flow field vector and the mode that binary vector combines, has reached ± the jet deflexion angle of 40 °, thereby has further consolidated outmaneuver of the present invention.
The design of the present invention and major part thereof is all the time round the design concept of wide speed envelope curve.The present invention combines the multiple technology that has different advantages under different conditions, has met all demands in whole flight envelope, and at subsonic velocity and hypersonic extremely strong maneuvering performance and the pneumatic efficiency that cruises of having obtained.The design of the present invention and major part thereof has met wide speed envelope curve, performance-oriented Design Orientation, and has stronger reference and using value.
As mentioned above, describe particularly embodiments of the invention in the above, but the invention is not restricted to this.It should be appreciated by those skilled in the art, can carry out various modifications, combination, sub-portfolio or replacement according to designing requirement or other factors, and they are in the scope of claims and equivalent thereof.

Claims (10)

1. wide flight envelope morphing aircraft, under low speed mode or high speed mode, work or conversion mutually, it is characterized in that: comprise head and fuselage, shown in the both sides, rear portion of head have canard, the both sides of described fuselage are fixed with sweepback inner wing, the wingtip of described sweepback inner wing is provided with the folding outer wing of sweepforward, the top, rear portion of described fuselage is provided with a pair of full dynamic formula vertical tail, two combination engines are installed in described fuselage, the admission port of described combination engine is positioned at the bottom front of described fuselage, the afterbody of described fuselage is provided with two vector spouts corresponding to described combination engine,
Described Die Design is Waverider head;
The aerofoil profile of described sweepback inner wing is supercritical airfoil; The aerofoil profile of the folding outer wing of described sweepforward is " ∧ " shape missile wing; Under low speed mode, the folding outer wing of described sweepforward launches along the wingtip of described sweepback inner wing; Under high speed mode, described sweepforward folds the bottom surface that outer wing overturns and is fitted in described sweepback inner wing, and the aerofoil profile of the folding outer wing of described sweepforward becomes the inversion of low speed mode aerofoil profile; The fuselage at described canard rear portion is provided with the edge strip extending to both sides;
Described combination engine comprises turbojet engine and dual-mode scramjet;
Described dual-mode scramjet comprises the by-pass air duct that is provided with by-pass air duct admission port, and the front end of described by-pass air duct is outer culvert inlet channel, and described by-pass air duct admission port is positioned at described underbelly and described Waverider head end; Described fuselage is provided with oxidizer Fuel Tank and deoxidation compound Fuel Tank; The inside face of described outer culvert inlet channel is provided with propellant spray mouth;
Described turbojet engine is arranged in described by-pass air duct, comprise the intension inlet channel that is provided with main duct admission port, in described intension inlet channel, low-pressure compressor is installed, described main duct admission port is positioned at described outer culvert inlet channel, described main duct admission port is distinguish and the taper case that can close completely, and it is tip cone forward that described taper case is closed rear profile; After described intension inlet channel, be provided with fan propeller, described fan propeller comprises fan blade, fan petiole and rotor block, and described fan blade is positioned at described by-pass air duct; The described by-pass air duct being positioned at after described fan propeller is provided with main main duct, in described main main duct, high-pressure compressor is installed, in described main main duct after described high-pressure compressor, be provided with precompression chamber, after described precompression chamber, be provided with intension combustion chamber, in described intension combustion chamber, be provided with propellant spray mouth; After described intension combustion chamber, be provided with one-level high-pressure turbine, described high-pressure turbine is fixedly connected with by high pressure rotor axle with described high-pressure compressor; After described high-pressure turbine, be provided with two-stage low-pressure turbine, described low-pressure turbine turns to contrary with high-pressure turbine; Described low-pressure turbine is fixedly connected with by low pressure rotor axle with low-pressure compressor, and described fan propeller is connected with described low pressure rotor axle by fan speed change device; Described high pressure rotor axle is hollow shaft and is sleeved on outside described low pressure rotor axle, and described fan propeller is arranged on described low pressure rotor axle;
Described main main duct after described low-pressure turbine is provided with main main duct exhausr port, the exhaust adjustment sheet that described main main duct exhausr port is provided with size-adjustable and can closes completely; Described main main duct exhausr port is positioned at described by-pass air duct; Between described vector spout and described main main duct exhausr port, be provided with the by-pass air duct extension as afterburner;
The spatial placement of the described by-pass air duct outside described main main duct is outer culvert combustion chamber;
Described vector spout is rectangle vector spout, comprise two up and down can deflection ± 20 ° baffle.
2. wide flight envelope morphing aircraft as claimed in claim 1, it is characterized in that: the relatively described sweepback inner wing of front end of the folding outer wing of described sweepforward is more forward, after gap between the folding outer wing of described sweepforward and described sweepback inner wing is leaned on relatively, and the lower camber line of the folding outer wing first half section of described sweepforward is straight downward-sloping.
3. wide flight envelope morphing aircraft as claimed in claim 2, is characterized in that: the maximum ga(u)ge of the folding outer wing of described sweepforward is at wing chord 68% place; In the time of described not deflection of canard, described canard and described edge strip form continuous pneumatic face; Described canard and described edge strip have the inverted diherdral of 4 °; The clinoid of described canard at the wing root chord of described canard from front end 85%.
4. wide flight envelope morphing aircraft as claimed in claim 1, is characterized in that: the leading edge sweep at the wingtip place of described sweepback inner wing increases and forms a leading edge of a wing breach with the folding outer wing of described sweepforward; Described sweepback inner wing has the inverted diherdral of 4 °.
5. wide flight envelope morphing aircraft as claimed in claim 1, is characterized in that: in described deoxidation compound Fuel Tank, liquified hydrogen or liquid hydrocarbon are housed, in described oxidizer Fuel Tank, liquid oxygen are housed; Described head lower surface, whole described by-pass air duct inwall are provided with H Exch, the double fuel feed line being connected with described propellant spray mouth that does of described H Exch.
6. wide flight envelope morphing aircraft as claimed in claim 1, it is characterized in that: described fan speed change device comprises the sun gear being rotatably installed on described low pressure rotor axle, be rotatably installed in the planetary wheel on described sun gear, described planetary wheel is provided with gear ring outward, described gear ring is fixedly connected with rotor block, described rotor block periphery is installed with described fan petiole, and described rotor block is rotatably installed on described low pressure rotor axle; Between described sun gear and described low pressure rotor axle, power-transfer clutch is installed.
7. wide flight envelope morphing aircraft as claimed in claim 1, is characterized in that: described fan blade is variable-distance blade; Described high-pressure compressor is level Four axial-flow type Blisk; The admission port place of described main main duct is provided with to regulate opens big or small flow deflector; Described by-pass air duct admission port is provided with the lower lip of deflection certain angle up and down.
8. wide flight envelope morphing aircraft as claimed in claim 1, is characterized in that: in described precompression chamber, be provided with H Exch, the double fuel feed line being connected with described propellant spray mouth that does of described H Exch.
9. wide flight envelope morphing aircraft as claimed in claim 1, is characterized in that: in described baffle, be provided with the injection passage of a hollow, described injection passage is provided with an injection entrance as admission port; Described injection passage is provided with three injection outlets, be positioned at described vector nozzle divergence section reference position and be provided with main injection outlet, be positioned at described vector nozzle divergence section middle part and afterbody and be respectively equipped with middle part injection outlet and the outlet of afterbody injection, described main injection outlet, the outlet of middle part injection and the outlet of afterbody injection are all provided with by-pass valve control; Described injection entrance is grid type admission port.
10. wide flight envelope morphing aircraft as claimed in claim 1, is characterized in that: the lateral margin of described Waverider head has inverted diherdral and lateral margin lower surface upwards arches upward.
CN201410125750.1A 2014-03-31 2014-03-31 Wide flight envelope morphing aircraft Expired - Fee Related CN103879556B (en)

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CN104648656A (en) * 2015-02-12 2015-05-27 厦门大学 Vertical take-off and landing unmanned plane lift augmentation control device and vertical take-off and landing unmanned plane lift augmentation control method
EP3515813A4 (en) * 2015-09-22 2020-07-15 Nctar, LLC Shockwave mitigation system for supersonic aircraft
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CN105752315A (en) * 2016-04-20 2016-07-13 西北工业大学 New-concept airfoil profile with combined transonic-velocity and hypersonic-velocity aerodynamic properties
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CN107161322A (en) * 2017-05-05 2017-09-15 西北工业大学 One kind becomes sweepback STOL Fixed Wing AirVehicle
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CN109808871A (en) * 2018-11-22 2019-05-28 成都飞机工业（集团）有限责任公司 A kind of all-wing aircraft combination rudder face with high maneuvering characteristics
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