CN103879556B - Wide flight envelope morphing aircraft - Google Patents
Wide flight envelope morphing aircraft Download PDFInfo
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- CN103879556B CN103879556B CN201410125750.1A CN201410125750A CN103879556B CN 103879556 B CN103879556 B CN 103879556B CN 201410125750 A CN201410125750 A CN 201410125750A CN 103879556 B CN103879556 B CN 103879556B
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Abstract
The invention discloses a kind of wide flight envelope morphing aircraft, adopt the variant manner of folded wing to change wing and plunder to, aspect ratio and aerofoil profile, improve the adaptive capacity of aerodynamic configuration in wide flight envelope; Driving engine is ingenious at turbojet engine and dual-mode scramjet, solves the problems such as this type of driving engine runner shares less, deadweight is many, the difficult realization of supersonic combustion; In aerodynamic configuration, Waverider head and fuselage, canard and edge strip, leading edge of a wing breach and sweepforward are folded outer wing and to combine complementation, ensure that the High Performance of aircraft under wide speed interval, many flight attitudes.At context engine, fan propeller is arranged on the also design such as deceleration transmission, combustion gas precooling combination utilization between low-pressure compressor and high-pressure compressor, significantly promotes the overall performance of driving engine; The present invention by flow field Thrust Vectoring Technology and dual vector jet pipe superimposed, obtain ± jet deflexion the angle of 40 °, significantly improve maneuverability and the controllability of aircraft.
Description
Technical field
The present invention relates to a kind of aircraft.
Background technology
In recent years, round the various possibilities that following fighter plane develops, people have carried out exploring widely.One of Main way has: flying speed faster, higher flying height and unmanned control.Require that 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 strengthening modern combat aircraft at the subsonic velocity manoevreability of low-to-medium altitude and supersonic speed manoevreability.
Summary of the invention
Technical matters to be solved by this invention is to provide one according to needs such as flight environment of vehicle, flight profile, mission profile and combat duties, can 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, work under low speed mode or high speed mode or mutually change, comprise head and fuselage, there is canard the both sides, rear portion of described head, the both sides of described fuselage are fixed with sweepback inner wing, the wingtip of described sweepback inner wing is provided with sweepforward and folds outer wing, the rear upper of described fuselage is provided with a pair 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 corresponds to described combination engine and is provided with two vector spouts.
Described Die Design is Waverider head.
The aerofoil profile of described sweepback inner wing is supercritical airfoil; Described sweepforward folds the aerofoil profile of outer wing for " ∧ " shape missile wing; Under low speed mode, described sweepforward folds outer wing and launches along the wingtip of described sweepback inner wing; Under high speed mode, described sweepforward folds outer wing and overturns and the bottom surface being fitted in described sweepback inner wing, and the aerofoil profile that described sweepforward folds outer wing becomes the inversion of low speed mode aerofoil profile; The fuselage at described canard rear portion is provided with the edge strip extended to both sides.
Described combination engine comprises turbojet engine and dual-mode scramjet.
Described dual-mode scramjet comprises the by-pass air duct being 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 oxidant fuel case 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 being 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 a tip cone forward that described taper case closes rear profile; Be provided with fan propeller after described intension inlet channel, described fan propeller comprises fan blade, fan petiole and rotor block, and described fan blade is positioned at described by-pass air duct; Be positioned at the described by-pass air duct after described fan propeller and be provided with main main duct, in described main main duct, high-pressure compressor is installed, precompression chamber is provided with in described main main duct after described high-pressure compressor, be provided with intension combustion chamber after described precompression chamber, in described intension combustion chamber, be provided with propellant spray mouth; Be provided with one-level high-pressure turbine after described intension combustion chamber, described high-pressure turbine is fixedly connected with by high pressure rotor axle with described high-pressure compressor; Be provided with two-stage low-pressure turbine after described high-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, and described main main duct exhausr port is provided with size-adjustable and the exhaust adjustment sheet that can close completely; Described main main duct exhausr port is positioned at described by-pass air duct; The by-pass air duct extension as afterburner is provided with between described vector spout and described main main duct exhausr port.
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, comprises about two and can deflect ± the baffle of 20 °.
As preferred technical scheme, the relatively described sweepback inner wing in front end that described sweepforward folds outer wing is more forward, described sweepforward folds gap between outer wing and described sweepback inner wing relatively rearward, and described sweepforward to fold the lower camber line of outer wing first half section straight downward-sloping.
As the improvement to technique scheme, described sweepforward folds the maximum ga(u)ge of outer wing at wing chord 68% place.
As preferred technical scheme, when described canard does not deflect, 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 is at 85% place of wing root chord from front end of described canard.
As preferred technical scheme, the leading edge sweep at the wingtip place of described sweepback inner wing increases and folds outer wing with described sweepforward and forms a leading edge of a wing breach.
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 that can deflect certain angle up and down.
As preferred technical scheme, described deoxidation compound Fuel Tank is built with liquified hydrogen or liquid hydrocarbon, and described oxidant fuel case is built with liquid oxygen.
As preferred technical scheme, described head lower surface, whole described by-pass air duct inwall are provided with H Exch, and described H Exch is double does the fuel feed line be connected with described propellant spray mouth.
As preferred technical scheme, described fan speed change device comprises the sun gear be rotatably installed on described low pressure rotor axle, be rotatably installed in the planetary wheel on described sun gear, outside described planetary wheel, gear ring is installed, 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 the flow deflector that can regulate and open size.
As preferred technical scheme, be provided with H Exch in described precompression chamber, described H Exch is double does the fuel feed line be connected with described propellant spray mouth;
As preferred technical scheme, be provided with the injection passage of a hollow in described baffle, described injection passage is provided with an injection entrance as admission port; Described injection passage is provided with three eductor outlet, be positioned at described vector nozzle divergence section reference position and be provided with main eductor outlet, be positioned in the middle part of described vector nozzle divergence section and be respectively equipped with middle part eductor outlet and afterbody eductor outlet with afterbody, described main eductor outlet, middle part eductor outlet and afterbody eductor outlet are all provided with by-pass valve control.
As preferred technical scheme, described injection entrance is grid type admission port.
Owing to have employed technique scheme, the present invention adopts the variant manner of folded wing to change wing and plunders to, aspect ratio and aerofoil profile, improve the adaptive capacity of aerodynamic configuration in wide flight envelope; Driving engine is ingenious at turbojet engine and dual-mode scramjet, solves the problems such as this type of driving engine runner shares less, deadweight is many, the difficult realization of supersonic combustion; In aerodynamic configuration, Waverider head and fuselage, canard and edge strip, leading edge of a wing breach and sweepforward are folded outer wing and to combine complementation, ensure that the High Performance of aircraft under wide speed interval, many flight attitudes.At context engine, fan propeller is arranged on the also design such as deceleration transmission, combustion gas precooling combination utilization between low-pressure compressor and high-pressure compressor, significantly promotes the overall performance of driving engine; The present invention by flow field Thrust Vectoring Technology and dual vector jet pipe superimposed, obtain ± jet deflexion the angle of 40 °, significantly improve maneuverability and the controllability of aircraft.
The present invention can change aerodynamic configuration awing, can in property retention optimum regime under different flight state.Compared with fixing airplane with routine, flight envelope of the present invention is wider, and fighting efficiency is higher, and it according to needs such as flight environment of vehicle, flight profile, mission profile and combat duties, independently can change aerodynamic configuration, optimize its airworthiness.And combination engine incorporates turbojet engine and the advantage of dual-mode scramjet in each self application flight range, make it have can CTOL, repeated usage, the advantage such as reliability high, low speed performance is good, technical risk is low, there is good future in engineering applications.
Accompanying drawing explanation
Fig. 1 is each mode of each parts of the embodiment of the present invention and the schematic diagram of speed corresponding relation;
Fig. 2 be embodiment of the present invention sweepforward fold outer wing be in deployed condition under block diagram;
Fig. 3 is the birds-eye view of Fig. 2;
Fig. 4 is the right elevation of Fig. 3;
Fig. 5 be embodiment of the present invention sweepforward fold outer wing be in folded state under block diagram;
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 that embodiment of the present invention sweepforward folds outer wing;
Fig. 9 is the closed aerofoil profile schematic diagram that embodiment of the present invention sweepforward folds outer wing and sweepback inner wing;
Figure 10 is the change curve of pneumatic efficiency with speed of buzzard-type wing and swept wing;
Figure 11 is the air hydrodynamic schematic diagram that the embodiment of the present invention closes aerofoil profile, in figure: the upper air hydrodynamic for top airfoil formation of N, it is the air hydrodynamic of lower aerofoil formation under N, the air hydrodynamic that N is combined into the formation of upper and lower aerofoil is made a concerted effort, F is upgraded to the component of N conjunction perpendicular to horizontal surface, and F hinders for N closes the component being parallel to horizontal surface;
Figure 12 is the shock wave schematic diagram that the embodiment of the present invention closes aerofoil profile;
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 sweepback inner wing and sweepforward and folds the leading edge of a wing breach that outer wing formed;
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-contains inlet channel outward; 124-contains 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-is vented 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 eductor outlet of 341-; Eductor outlet in the middle part of 342-; 343-afterbody eductor outlet; 344-by-pass valve control; 35-droope snoot; 36-flaperon.
Detailed description of the invention
In order to there be understanding clearly to technical characteristic of the present invention, object and effect, now contrast accompanying drawing and the specific embodiment of the present invention is described.
The design of wide flight envelope morphing aircraft, based on the future after decades, mainly to use 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 needs to have to be not less than the advantage of modern combat aircraft in low-speed maneuver, also has certain hypersonic cruising ability of sub-track, to reach the object of gaining the initiative by striking first with long-range prompt global strike in future war.The present invention and driving engine thereof had both needed to guarantee to be not less than the speed cruise flight of 6Ma, also needed to have when low-speed operations better pneumatic efficiency and comparatively 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 (rear both can be collectively referred to as " dual-mode scramjet "), and vector spout of the present invention is divided into shrinkage expansion mode and expansion mode.Each mode of 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, there is canard 3 both sides, rear portion of described head 1, 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 sweepforward and folds outer wing 5, the rear upper of described fuselage 2 is provided with a pair 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 corresponds to described combination engine 7 and is provided with two vector spouts 8.
In order to take into account hypersonic, supersonic speed, subsonic velocity and At High Angle of Attack attitude, the present embodiment adopts the variant manner (referred to as folding wings) of folded wing to be combined with " ∧ " shape missile wing with swept wing, conventional aerofoil profile by buzzard-type wing, and Waverider, canard, edge strip, wing breach etc. are carried out 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 is realized by folded wing.Its wing is divided into sweepforward to fold outer wing 5 and sweepback inner wing 4 two sections, and sweepforward folds the sweepforward of outer wing 5 wide-angle, the sweepback of sweepback inner wing 4 low-angle.As shown in Figure 7, sweepback inner wing 4 aerofoil profile is similar to the supercritical airfoil of elongation to the aerofoil profile of sweepback inner wing 4; Sweepforward folds the aerofoil profile of outer wing 5 as shown in Figure 8, and sweepforward folds the maximum ga(u)ge of outer wing 5 at wing chord 68% place, relatively rearward.And the upper camber line that sweepforward folds outer wing 5 aerofoil profile first half section is inclined upwardly very straightly, profile is similar to " ∧ " shape missile wing of upset.
Sweepback inner wing 4 merges and is connected on fuselage 2, and sweepback inner wing 4 and sweepforward fold outer wing 5 and be connected through the hinge, and sweepforward folds outer wing 5 can rotate 184 ° when flying around sweepback inner wing 4 wingtip, as shown in Figure 6.
When the present embodiment uprises fast mode by low speed mode, sweepforward folds outer wing 5 and inwardly rotates 184 ° by open configuration thus fit with sweepback inner wing 4, new closed aerofoil profile is as shown in Figure 9 formed with sweepback inner wing 4, and merge mutually with canard, three forms new aircraft leading edge and wing shapes jointly, specifically refers to Fig. 5.Contrary by program during high speed mode step-down speed mode.
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, particularly take up room the advantage such as little.The present embodiment not only structure is simple and act on powerful, both can the aerodynamic arrangement of change of flight device, again can the aerofoil profile of change of flight device.
The essence of folding wings switches between forward-swept-wing configuration and swept-wing layout, changes the span and aspect ratio simultaneously.Figure 10 is the change curve of pneumatic efficiency with speed of buzzard-type wing and swept wing.
As can be seen from the figure, the pneumatic efficiency of buzzard-type wing when subsonic velocity is significantly higher than swept wing.And after supersonic speed, swept wing starts to preponderate gradually.Folding wings makes the present embodiment sweepforward when low speed mode fold outer wing 5 buzzard-type wing, has very high At High Angle of Attack performance and manoevreability during subsonic velocity.And make the present embodiment become swept wing in high speed mode, significantly reduce resistance during hypersonic flight.Folding wings by change wing plunder to, thus make wing keep optimum pneumatic efficiency in all flight envelopes.
As everyone knows, low aspect ratio, highly swept aircraft are suitable for high-speed flight, but during low-speed operations, performance is not good.And the aircraft of high aspect ratio, low sweep angle is applicable to low-speed operations, its subsonic velocity 1ift-drag ratio is comparatively large, but is not suitable for high-speed flight.Due to the effect of folding wings, when the present embodiment becomes high speed mode from low speed mode, its aspect ratio becomes 0.79 from 2.49, and wing setting becomes 56.3 ° from 19.8 °.Thus make the present embodiment can both keep best airworthiness when low-speed operations and high-speed flight.
Known by the mapping mode of folding wings, become after high speed mode from low speed mode, sweepforward folds outer wing 5 and fits with sweepback inner wing 4, and sweepforward folds outer wing 5 and spins upside down, and its aerofoil profile becomes the inversion of low speed mode aerofoil profile.As shown in Figure 5, because sweepforward folds outer wing 5, sweepback inner wing 4 is more forward relatively, so now the front end of closed aerofoil profile is the front end that sweepforward folds outer wing 5, the bottom of closed aerofoil profile first half section is that sweepforward folds outer wing 5.This gap that sweepback inner wing 4 and interior sweepforward are folded between outer wing 5 is relative rearward, and the lower camber line of aerofoil profile first half section is straight downward-sloping.
Air hydrodynamic during hypersonic flight is very large, and wing nose 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 enables it as " ∧ " shape missile wing, and the aerofoil of declivity also produces power upwards while air compressing being produced to power backward, thus utilizes air hydrodynamic to produce lift.Its anterior oblique shock wave formed can strengthen this compression lift further.During 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 increases.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.Degree is protruded in order to reduce sweepback inner wing 4, sweepback inner wing 4 Airfoil Design is the more straight supercritical airfoil in stage casing by the present embodiment, while making closed aerofoil profile top airfoil as far as possible straight, the appearance of shock wave during high subsonic velocity can also be postponed, reduce the degree that boundary-layer is separated, increase the Mach number increment between critical Mach number and drag divergence Mach number.Therefore good high subsonic velocity and transonic speed airworthiness can be obtained.
In addition, as can be seen from Figure, the sweepforward that sweepback inner wing 4 has been partially submerged into upset by the present embodiment folds outer wing 5, make sweepback inner wing 4, sweepforward folds outer wing 5 and fit more closely, also the upper lower aerofoil of closed aerofoil profile is optimized further, make it transition more level and smooth, top airfoil is more straight, improves 1ift-drag ratio.Secondly, the adjustment of the droope snoot 35 of sweepback inner wing 4 can make sweepback inner wing 4, sweepforward folds outer wing 5 and fits tightr.The droope snoot 35 that sweepforward folds outer wing 5 then can regulate the inclination angle of compression ramp, thus changes the size and Orientation of air hydrodynamic.
May cause the problem of adverse effect for sweepback inner wing 4, the sweepforward gap folded between outer wing 5, contriver thinks that it is unimportant.First, because sweepback inner wing 4, sweepforward fold outer wing 5 and mutually embed, sweepforward folds outer wing 5 to be had this gap and certain blocks effect.In addition, the oblique shock wave that wing nose is formed has deflecting action to incoming flow, makes it flow to and has the component deviating from gap, thus weakens the impact in gap further.
The closed aerofoil profile (High Mach number, high reynolds number) when hypersonic flight that folding wings is formed has comparatively high lift efficiency and 1ift-drag ratio, demonstrates the feasibility of folding wings in aerofoil profile and preceence.
Folded wing formula its variant designs makes the present embodiment can 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.The present embodiment can be met better at a high speed and the different demands of low speed, ensure 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, just as whole lifting body rides on shock wave when design point flies.This makes it have very high lift efficiency when hypersonic flight.The head 1 of the present embodiment adopts Waverider to design, airworthiness higher during to ensure hypersonic flight, can match with fuselage 2 and combination engine 7 better simultaneously.
The design of the present embodiment Waverider head 1 have employed by known without the mimetic design method of sticky compressible supersonic flow field as departure point, and the moderate 6Ma of access speed is design point.In addition, select β=12 that designed Waverider 1ift-drag ratio can be made maximum as the half benchmark circular cone Angle of Shock Waves designing Waverider.The present embodiment generates after Waverider prototype through preliminary design, is optimized and incorporates in unit design, and final Waverider head 1 cross section formed as shown in figure 13.
The present embodiment Waverider head 1 merges with fuselage 2 and canard 3 perfection, further reduces the resistance of complete machine, improves 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 increase the higher-pressure region area of lower surface, thus help Waverider to obtain higher lift efficiency, also can provide compression effectiveness better air inlet to the admission port being in fuselage 2 bottom.
This using the design of Waverider as head 1, enable the present embodiment have the advantage of high lift, low resistance, high lift-drag ratio under hypersonic, thus adapt to high-speed flight better.And the head 1 of its declivity also can with the supersonic combustion punching press mode matched of combination engine 7, while improving pneumatic producing effects strengthen engine performance.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, the phenomenon of moving after aerodynamic center after inhibit 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, enable the present embodiment install the radar of larger diameter, thus promote its whole battle performance.
As shown in Figure 3, the present embodiment, by the unitized design of special canard and edge strip, makes both together form a pneumatic system.This pneumatic system not only can ensure the low resistance when 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 not when deflecting, and canard 3 is coplanar with edge strip 9, and both combine together and form continuous pneumatic face.In order to better merge with anti-Waverider head 1 under edge, 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 is at 85% place of wing root chord from front end of described canard 3, and therefore after canard 3 deflects, canard 3 no longer contacts with edge strip 9, and both do not reconstruct continuous pneumatic face.
The Main Function that the canard 3 of the present embodiment deflects is to provide faces upward control torque of bowing, and forms favourable aerodynamic with edge strip 9 and be coupled, and improves the aerodynamic characteristic of the present embodiment when At High Angle of Attack attitude.
When 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-LEX vortex.This whirlpool is formed from canard 3 leading edge, and blank is the body-shedding vortex of canard 3.Eddy current can be reinforced when edge strip 9, is blown and is imported canard-LEX vortex, thus significantly improve its turbulence rate and range of control by the lower surface high energy air-flow that edge strip 9 lateral margin is let out.Canard-LEX vortex can inswept sweepback inner wing 4 wing root and wing body afterwards, slows down burbling and provides stronger vortex lift.
As shown in figure 14, due to when At High Angle of Attack attitude, canard 3 is fuselage 2 negative angle partially relatively, and therefore canard 3 and edge strip 9 can form the seam road that is tilted to point to upper surface.Fuselage 2 lower surface high pressure draft will flow to upper surface by seam road, cause the reduction of local pressure difference.Make the anterior loss of lift of fuselage 2, but therefore the lift of full machine can't reduce.Lower surface high energy air-flow is introduced upper surface by the seam road that canard 3 and edge strip 9 are formed, and strengthens canard-LEX vortex, postpones high energy air-flow and breaks, for rear fuselage 2 and sweepback inner wing 4 provide stronger vortex lift.The canard effect of washing for 3 times and canard-LEX vortex can also be strengthened controlling the flowing at edge strip 9 and pneumatic of rear portion, slow down burbling.Showing as on aerodynamic force, when 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 control of bowing.
Another effect of canard 3 is to provide faces upward control torque of bowing.But the comparatively large and jet deflexion angle of the vector spout 8 of the present embodiment of flaperon 36 area due to fuselage 2 rear portion is up to ± 40 °, and both can provide very large and face upward control torque of bowing, and there is no need canard 3 to design too large.Therefore the canard 3 of the present embodiment is relatively little, to reduce the burden of braking machinery.
In addition, when the present embodiment be level-flight attitude or change high speed mode into time, canard 3 does not participate in not deflecting in the trim of aircraft yet.At this moment canard 3 combines together with overall aerodynamic arrangement as one fixing pneumatic, thus improves the 1ift-drag ratio of aircraft.Embody the wide flight envelope design concept taking into account high-speed flight.And the trim work of aircraft has come primarily of the flaperon 36 of afterbody and vector spout 8.
Canard-edge strip system can when At High Angle of Attack attitude, and by forming favourable aerodynamic coupling, make that the stalling characteristics of the present embodiment improve, lift forms platform, move after facing upward moment flex point of bowing, stalling incidence increases.And its profile being blended in overall aerodynamic arrangement can take into account high-speed flight again.While the manoevreability significantly promoting the present embodiment, strengthen pneumatic efficiency during its cruising flight, improve whole battle performance.
From the variant manner of folding wings, the sweepback angle of wing when the sweepforward angle that during low speed mode, sweepforward folds outer wing 5 is high speed mode, in order to ensure the high speed performance of the present embodiment, this plunders angle must be larger.But the large sweepforward angle that during low speed mode, sweepforward folds outer wing 5 can bring two problems: one is aeroelastic divergence problem, two is that buzzard-type wing wing root place exists more serious unfavorable air flow status.
The solution of first problem does not belong to aerodynamics category, is mainly concerned with structure design and materials application aspect.In fact, this is in buzzard-type wing extensive Problems existing existing terms of settlement at present with it.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 direction, the flexural deformation of wing can be made to cause additional negative torsional deflection, thus offset the positive torsional deflection of buzzard-type wing 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 and controls the unfavorable flow condition that sweepforward folds outer wing 5 wing root place.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, folds outer wing 5 form a leading edge of a wing breach 24 with sweepforward.When At High Angle of Attack, this breach can form strong eddy current, sweepforward can be folded the separation bubble piled up at outer wing 5 wing root place and sweep away, thus improve sweepforward and fold the disadvantageous air flow status in outer wing 5 wing root place.And this breach whirlpool also can fold with sweepforward sweepforward that outer wing 5 produces and folds outer wing volute and become favourable interference.Plunder on the contrary because sweepback inner wing 4, sweepforward fold outer wing 5, it is contrary with the hand of rotation in breach whirlpool that sweepforward folds outer wing whirlpool, and the flow direction of its contact surface is identical, and both strengthen mutually, 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, while control sweepback inner wing 4 wingtip, sweepforward fold outer wing 5 wing root burbling, also for present embodiments providing stronger vortex lift, and solves the problem that sweepforward folds the unfavorable flow condition in outer wing 5 wing root place.Improve the At High Angle of Attack performance of the present embodiment, thus post stall maneuver when promoting its low speed mode and sustained maneuver ability.
The design of leading edge of a wing breach 24 is also the change airfoil characteristics in order to meet folding wings.From above, one of closed aerofoil profile necessary condition having superior performance that folding wings is formed is: sweepforward folds outer wing 5, and sweepback inner wing 4 is more forward relatively.Sweepforward could be made after wing is closed to fold before outer wing 5 aerofoil profile is in sweepback inner wing 4 aerofoil profile like this, could form high speed performance and close aerofoil profile preferably.And if there is no this wing breach, joint at them overlaps by the leading edge that sweepback inner wing 4, sweepforward fold outer wing 5, make the present embodiment when high speed mode, at least cannot form previously described closed aerofoil profile at wing wingtip place, and sweepback inner wing 4, sweepforward fold outer wing 5 gap and be directly exposed in high speed incoming flow, likely cause extremely bad impact.
From the variant manner of folding wings, when high speed mode, sweepback inner wing 4 leading edge by completely by sweepforward fold outer wing 5 cover.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 wing area be increased, reduce unit wing load, and promote subsonic velocity pneumatic efficiency, thus manoevreability when 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 high speed mode under wing, thus utilizes compression lift better.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.Wing anti-under the present embodiment can hold together these press packet of " scattering ", obtains produce effects more.
Sweepforward folded outer wing-sweepback inner wing system and is associated by folding wings and pneumatic coupling, the connected applications designs such as buzzard-type wing, swept wing, wing breach.When promoting low speed mode separately while performance, taking into account the characteristic applying folding wings, thus improve overall performance.Again embody the wide flight envelope design concept taking into account high low-speed operations.
In order to solve the problem of hypersonic flight stability rapid drawdown, the present embodiment remains the design of vertical tail 6 (abbreviation vertical fin).Its Main Function ensures horizontal stability, participates in crosswise joint simultaneously.Therefore less by the area design of the present embodiment vertical tail 6, and sweepback angle is comparatively large, and have 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 crosswise joint 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, while subsonic velocity provides compared with high thrust, also can provide flying power when hypersonic flight, and can transit to hypersonic from principal and subordinate's subsonic velocity.The combination engine 7 of the present embodiment in friction speed interval, respectively with four kinds of different Modality 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 regard a unconventional turbojet engine 11 as, and high-pressure compressor 19 is level Four axial-flow type, Blisk.Core engine air inlet place be in after fan propeller 17 is called the admission port of main main duct 18, is provided with the flow deflector 31 that can regulate and open size here.This flow deflector 31 is called throughput ratio adjustment sheet, it open size and can regulate the inside and outside throughput ratio contained, thus makes driving engine change throughput ratio in turbofan mode according to the different speed of aircraft and demand, improves the conformability of turbofan mode.
Be precompression chamber 20 after high-pressure compressor 19, precompression chamber 20 is exactly the space of a hollow, within be provided with H Exch 25, described H Exch 25 is double does the fuel feed line 26 be connected with described propellant spray mouth 13.Air is by H Exch 25 precooling after flowing through precompression chamber 20, and temperature declines and continues supercharging, thus shares the work of part air compressor.It is less that this makes the progression of high-pressure compressor 19 to design, thus strengthen engine efficiency, increases thrust-weight ratio.
Intension combustion chamber 21 is connect, the fuel mix after-combustion that air is vaporized at this and preheating after precompression chamber 20.Be one-level high-pressure turbine 22 after intension combustion chamber 21, the rotor that high-pressure turbine 22 and high-pressure compressor 19 are fixedly connected to form by high pressure rotor axle 221 is called high pressure rotor.Be two-stage low-pressure turbine 23 after high-pressure turbine 22, turn to contrary with high-pressure turbine 22.Low-pressure turbine 23 links with low-pressure compressor 15 and fan propeller 17, and the rotor that low-pressure turbine 23 is fixedly connected with rear formation with low-pressure compressor 15 (not comprising fan propeller 17) by low pressure rotor axle 231 is called low pressure rotor.This high and low pressure rotor, to the mode of operation turned, can make to act on two epitrochanterian gyro torque major parts during aircraft maneuvering flight and offset, reduce the moment load to aircraft, strengthen the handling of aircraft; This structure makes the middle bearing inner and outer ring be loaded between two rotors turn on the contrary in addition, reduces the rotating speed of retainer inner and outer ring relative to 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.And low-pressure turbine 23 to be designed to secondary be consider low-pressure turbine 23 except wanting energize low-pressure air compressor 15 also will drive fan propeller 17, its duty ratio is larger.Though be designed to secondary can increase complex structure degree and weight, decrease the load of single-stage turbine, improve turbine efficiency, thus export more superpower for low-pressure compressor 15 and fan propeller 17.It is main main duct exhausr port 181 after turbine, described main main duct exhausr port 181 place is provided with exhaust adjustment sheet 182, its size-adjustable and can closing completely, its effect is except regulating core engine exhaust, can also be formed in subsonic combustion punching press mode and supersonic combustion punching press mode and by-pass air duct 12 and comparatively seamlessly transit, burning and gas-exhausting will carry out first time at this and expand.
The combination engine 7 of the present embodiment have employed the scheme being in provided with fan rotor 17 between low-pressure compressor 15 and high-pressure compressor 19, while increase turbofan mode and whirlpool jet mould state thrust efficiency, better can 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 except the rate of supercharging that turbofan mode regulates fan, can also can better adapt to other mode to by-pass air duct 12 permeability and resistance demand.Fan propeller 17 comprises fan blade 171, fan petiole 172 and rotor block 173 3 part, and a part is the fan petiole 172 being positioned at main duct, and it is comparatively very thin, only plays a supportive role; The part being in by-pass air duct 12 is only fan blade 171, and therefore fan only gives by-pass air duct 12 supercharging air.
Fan propeller 17 is linked by fan speed change device and low pressure rotor axle 231, and this interlock can be disconnected by power-transfer clutch 30.When turbofan mode, fan propeller 17 drives by low pressure rotor axle 231, fan blade 171 pairs of by-pass air duct 12 supercharging airs; And when 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 displacement is adjusted to along slurry position, fan blade 171 is parallel with incoming flow, and fan blade 171 resistance is reduced as far as possible.The variable-distance of fan blade 171 embodies engine design taking into account different modalities, meets 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 be rotatably installed on described low pressure rotor axle 231, be rotatably installed in the planetary wheel 28 on described sun gear 27, outside described planetary wheel 28, gear ring 29 is installed, described gear ring 29 is fixedly connected with rotor block 173, described rotor block 173 periphery is 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 increase charge air, the low-pressure compressor 15 being 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 circular and can closes completely, and after closing, profile is the cone before a sensing, can play compression in subsonic combustion punching press mode and the air inlet of supersonic combustion punching press mode external duct 12.
As shown in figure 16, the inlet channel of by-pass air duct 12 is called outer culvert inlet channel 123, and its first half carries all air inlets of main main duct 18 and by-pass air duct 12, and rear portion bag holds together intension inlet channel 14.The by-pass air duct admission port 121 of outer culvert inlet channel 123 is positioned at the present embodiment fuselage 2 bottom, Waverider head 1 end, still can provide sufficient air inlet when aircraft at high angle of attack attitude like this, and can provide by the precompressed air inlet of Waverider for driving engine when hypersonic flight.In the present embodiment, the lower lip 121a of by-pass air duct admission port 121 can deflect certain angle up and down, is used for regulating air inlet.Outer culvert inlet channel 123 is slightly to surface thereof, and this is the result that unit design is made overall plans, and the resistance of aircraft can be made to 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 portion is provided with the by-pass air duct extension 122 of the core engine of being longer than main main duct 18, core engine is vented and by-pass air duct 12 is vented to be mixed by by-pass air duct extension 122 and discharges.This by-pass air duct extension 122 mixing mode makes combination engine 7 when turbofan mode and whirlpool jet mould state, and main main duct 18, by-pass air duct 12 air-flow again can do energy exchange before ejection, thus improves engine efficiency; By-pass air duct extension 122 has the function of afterburner and conveniently installs vector spout 8.
By-pass air duct 12, except the afterbunring outdoor at rear portion, in the middle, arises from fan propeller 17 until main this section of main duct exhausr port is by-pass air duct 12 independently combustion chamber, 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.Propellant spray mouth 13 is established with outer culvert inlet channel 123 wall in intension combustion chamber 21.
In the present embodiment head 1 surface, whole by-pass air duct 12 inwall, precompression chamber 20 and propellant spray mouth 13 place be provided with H Exch 25.Wherein the H Exch 25 of by-pass air duct 12 inwall is divided into front and back independently two parts, 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 thermal protection effect can be played 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 fuel is made to shift to an earlier date preheating vaporization, to burning advantageously.
Mode of operation during combination engine 7 different modalities and mapping mode between mode:
1. turbofan mode
As shown in figure 22, now outer culvert inlet channel 123 and intension inlet channel 14 are all opened and are opened comparatively large, 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, fan blade 171 pairs of by-pass air duct 12 supercharging airs.Open with the H Exch 25 at propellant spray mouth 13 place in precompression chamber 20, fuel first flows through the H Exch 25 in precompression chamber 20, then flows through the H Exch 25 at propellant spray mouth 13 place, 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 half, then flows into low-pressure compressor 15.Low-pressure compressor 15 drives, to supercharging air by low-pressure turbine 23.Because combination engine 7 adopts the design of middle fan, therefore low-pressure compressor 15 can not be subject to the unfavorable interference of fan.Major part is entered core engine by the fan petiole 172 that the air of low-pressure compressor 15 supercharging can flow through fan blade 171; And have small part can be spilled over to by-pass air duct 12 from fan propeller 17, can increase the pressure of by-pass air duct 12 exhaust 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 supercharging.Air is discharged into precompression chamber 20 afterwards.In precompression chamber 20, be pressurized and the high pressure draft of temperature rising flows through H Exch 25, do interchange of heat with low temp fuel.Fuel heats up, and air-flow is lowered the temperature.The cooling of air-flow can improve compression efficiency again, prepares to be used as burning.
Precompression chamber 20 is also used to supercharged air, and it has shared the task of a part of compressor pressure air, thus the progression of high-pressure compressor 19 can design less.Therefore the high-pressure compressor 19 of combination engine 7 only has level Four rotor blade, reduces structure complexity and the weight of driving engine, shortens size, reduces the startup inertia of high pressure rotor.And less air compressor progression also just means the load that turbine is less, also just less to the energy ezpenditure of combustion gas, combustion gas can retain more multi-energy and form thrust in order to drive low pressure rotor and last ejection, indirectly improves rotating speed and the engine thrust of low pressure rotor.And this hollow space between combustion chamber and air compressor of precompression chamber 20, the effect of certain suppression engine surge can be played.
Fuel is after intension combustion chamber 21 combustion, 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 portion through main main duct exhausr port, will be vented to mix with by-pass air duct 12 there and finally be discharged by vector spout 8.
At by-pass air duct 12, air enters by-pass air duct 12 through outer culvert inlet channel 123.Air is through fan forced and being mixed by the air of low-pressure compressor 15 supercharging of overflowing from intension with part afterwards, then flows through from core engine and coolant core machine.Last exhaust with core engine mixes, and is sprayed by vector spout 8.Compared with the fanjet of modern combat aircraft, the bypass ratio of combination engine 7 is comparatively large, has higher efficiency or larger thrust; This is also for dual-mode scramjet 10 reserves enough spaces simultaneously.
As shown in figure 22, fuel flows into H Exch 25 in precompression chamber 20 and propellant spray mouth 13 (external pipeline does not provide), finally injecting compressed air in intension combustion chamber 21 successively.
2. whirlpool jet mould state
As shown in figure 23, now by-pass air duct admission port 121 opens less, 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, thus fan propeller 17 and low pressure rotor is disconnected link.Now low-pressure turbine 23 is only used for driving low-pressure compressor 15, and low-pressure compressor 15 rotating speed rises, and meets whirlpool jet mould state to the high efficiency demand of air compressor.Now fan propeller 17 stall, fan blade 171 displacement, blade is parallel to incoming flow, reduces fan resistance as far as possible.The operation mode of other parts is similar to during turbofan mode.
Air enters low-pressure compressor 15 through main duct admission port 141 and intension inlet channel 14, core engine is flowed into through the fan petiole 172 of fan blade 171 by most of air after low-pressure compressor 15 supercharging, and a small part air can be spilled over to by-pass air duct 12, increase by-pass air duct 12 stream pressure while coolant core machine, improve engine efficiency.The air flowing into core engine flows through high-pressure compressor 19, precompression chamber 20, intension combustion chamber 21 and high-pressure turbine 22 more successively, and the mode of operation of core engine is identical with during turbofan.
Link because fan propeller 17 and low pressure rotor disconnect, the load of low-pressure turbine 23 is reduced, rotating speed promotes, thus improves the rate of supercharging of low-pressure compressor 15, has adapted to turbojet engine 11 pairs of high efficiency requirements of air compressor.
3. supersonic combustion punching press mode
Because the most of design point in dual-mode scramjet 10 is to meet supersonic combustion punching press mode, so this specification sheets describes before supersonic combustion punching press mode is placed on subsonic combustion punching press mode.
When 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 comparatively large, 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.Open at the H Exch 25 at the present embodiment head 1 surface, whole by-pass air duct 12 inwall and propellant spray mouth 13 place.
Air enters outer culvert inlet channel 123 by after Waverider head 1 precompressed compression of the present embodiment, and continues deceleration supercharging under containing the effect of the series of shock string in inlet channel 123 outside.Mention above, inlet channel is slightly to surface thereof, and this will certainly increase resistance.But the first shock wave that admission port front end produces makes air flow direction thereafter slightly toward upper deflecting, and acclivitous inlet channel has in fact just in time adapted to the flow direction of air-flow.
Air inlet is flow through after outer culvert inlet channel 123 and is flow through fan propeller 17 again with fuel mix, and fan propeller 17 is outer culvert combustion chamber 124 afterwards.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 burns under ensureing supersonic speed in the mode of long combustion chamber fully.But its problem brought needs the area of cooling also very large, this problem is solved by the fuel playing cooling effect flow through in inwall herein.
Because combination engine 7 adopts middle fan design, intension, in fan place "off", makes the provided with internal duct and external duct 12 at fan place communicate.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-flow.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 because ejector action, far below by-pass air duct 12, even becomes class hollow state.This can form transverse-pressure gradient at fan place, makes the trend that the oriented centre of by-pass air duct 12 air-flow is drawn close.Simultaneously fan also plays the effect of certain vortex generator, and this two kinds of effects produce very complicated pneumatic coupling mutually, forms the higher and baroque eddy current of intensity after making fan.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 inwall is also probably involved in.Research shows, when the abundant premix of fuel, can burn in advance in the boundary-layer of High Temperature High Pressure.After the boundary-layer having occurred to burn is involved in eddy current, the burning of other pre-mixing gas combustion can be caused rapidly, thus light outer culvert combustion chamber 124.The particular design configuration of middle fan, makes combination engine 7 by forming eddy current and the mode that pre-burning boundary-layer is involved in being spread and maintain flame, solves that supersonic combustion is lighted a fire, the problem of flame spread and maintenance flame difficulty.
4. subsonic combustion punching press mode
As shown in figure 25, the mode of operation of driving engine when subsonic combustion punching press mode is identical with mode of operation during supersonic combustion punching press mode, what just contain the interior generation of combustion chamber 124 outside is subsonic combustion, and supersonic flow contains in inlet channel 123 diffusion that just slows down outside to subsonic velocity.
The admission port now containing inlet channel 123 outward opens less, and vector spout 8 is adjusted to shrinkage expansion spout, and the mode of operation of other tunable component and supersonic combustion punching press mode phase are together.
Incoming flow contain outside in inlet channel 123 slow down be pressurized to subsonic velocity and and fuel mix, then accelerate to supersonic speed ejection by shrinkage expansion spout after outer culvert combustion chamber 124 burns.
The designs such as variable-pitch fan, middle fan, low pressure rotor-fan deceleration transmission system, combustion gas precooling combine by the combination engine 7 of the present embodiment, while realizing hypersonic flight power, also obtain high thrust, big thrust loading at low speed.By optimizing the design of each runner of each parts, solve the problems such as turbine base combined cycle engine runner shares less, deadweight is many.Improve the thrust efficiency of turbofan and whirlpool jet mould state by middle fan design, and solve the problem of supersonic combustion punching press mode engine ignition, maintenance flame difficulty.Combination engine 7 meets 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 being combined, obtains the jet deflexion angle much larger than modern vector spout, significantly can improve the manoevreability of the present embodiment.And the design of the vector spout 8 of the present embodiment is also towards combination engine, the different demands of combination engine 7 different modalities can be met.The Main Function of the vector spout 8 of the present embodiment regulates the jet flow of combination engine 7, the control efficiency improving the present embodiment and manoevreability.
As shown in Figure 2, the vector spout 8 of the present embodiment is designed to rectangle vector spout, can better and rear body 2 merge, and improve manoevreability, simplified structure, the Stealth Fighter of the complete machine back segment that also can ensure better.
As shown in figure 26, the deflection vector of the vector spout 8 of the present embodiment, spout type and geometric shape adjustment conversion primarily of upper and lower two can deflect ± baffle 81 of 20 ° completes.Have a hollow channel in baffle 81, 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 eductor outlet 341.Two other less outlet lays respectively in the middle part of expansion segment and afterbody, is called middle part eductor outlet 342 and afterbody eductor outlet 343.Three eductor outlet control size and opening and closing by by-pass valve control 344.
The mode of operation of vector spout:
1. shrinkage expansion mode
As shown in figure 27, at the Many times of turbofan mode, whirlpool jet mould state and subsonic combustion punching press mode, the direct exhaust of engine chamber is all subsonic velocity, and vector spout 8 needs 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, is also entered the Secondary Flow jet curtain adjustment of vector spout 8 by injection.Open injection entrance 33 and eductor outlet, extraneous air will inject the expansion segment of vector spout 8, and its jet curtain formed can play the effect of certain suppression jet cutting car flow expansion.By the injection rate and the Secondary Flow pressure that regulate the size of injection entrance 33 and eductor outlet to regulate Secondary Flow, thus play the effect regulating vector spout 8 to export size.
Thisly control to regulate vector spout 8 to export the design of size by flowing, relative to the mode of mechanical adjustment, have structure simple, lightweight advantage.Thus provide engine thrust-weight ratio, and reduce the maintenance cost of vector spout 8.
2. expand mode
In supersonic combustion punching press mode, the direct exhaust of engine chamber is supersonic speed, and vector spout 8 needs to be accelerated higher speed ejection.Now two baffles 81 one-tenth open shape, form an expansion vector spout.Size adjustment vector spout 8 degrees of expansion is opened with two baffles 81.Because speed of incoming flow during this mode is too fast, and vector nozzle shape resistance is large.In order to reduce resistance as far as possible, when this mode, injection entrance 33 and eductor outlet Close All.
3. deflection vector
The vector spout 8 of the present embodiment, by being combined with mechanical deflection vector by flow field vectoring technology, can obtain the maximum jet deflexion angle reaching 40 °.But fly most of time, jet flow drift angle is without the need to so huge.Therefore when jet flow drift angle is between 0 to 20 °, the vector spout 8 of the present embodiment uses the flow field vectoring technology without the need to too many machinery change, to reduce access times and the degree of mechanical movable parts, thus increases reliability and the service life of vector spout 8.
3.1 flow field deflection vectors (0-20 °)
As shown in figure 29, when needing the angle of deflection to be less than 20 °, the vector spout 8 of the present embodiment carries out jet deflexion by means of only a kind of mode controlled that flows.
When jet flow needs to upward deflect 0-20 °, baffle 81 does not deflect, and injection entrance 33, the eductor outlet of lower baffle 81 are all opened; The injection entrance 33 of upper baffle 81 closes or opens less, and eductor outlet is all opened.At this moment when 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 in lower injection passage 32 and supplements the air run off, and its internal pressure changes hardly.And the closedown of upper injection entrance 33 supplements after making the air in injection passage 32 be pumped 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 gradient, and low pressure is high, and upper pressure is low.Jet flow upward deflects with pressure gradient.When jet deflexion angle large to a certain extent time, jet flow can produce attached wall effect (Coanda effect) with upper baffle 81, and make jet flow along upper baffle 81 surface flowing, deflection angle rises to.The pressure in upper injection passage 32 can be regulated by the stool and urine of the injection entrance 33 regulating upper baffle 81, thus regulate the change size of pressure gradient, and then regulate the deflection angle of jet flow.When deflecting down 0-20 °, mode of operation is identical.
This by flowing control deflection way can make the deflection angle of jet flow reach ± about 20 °, thrust efficiency about 90%.Realization with modern vector spout with isogonic and efficiency while, eliminate a large amount of mechanical moving element, simplify the structure, alleviate aircraft weight, reduce maintenance cost.
3.2 flow field deflection vector+mechanical deflections (20 °-40 °)
As shown in figure 30, when angle of inclination are greater than 20 °, the vector spout 8 of the present embodiment needs mechanical deflection is carried out on the basis of above-mentioned flow field vector.
When jet flow needs 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 at about ± 20 °, and thrust efficiency is about 90%.Superimposed with flow field deflection vector again, the final deflection angle of jet flow can reach ± and about 40 °, thrust efficiency about 81%.
The degree of deflection of the far super modern vector spout of deflection vector of ± 40 °, will give that the present embodiment is extremely strong can handling and manoevreability, comprises fault speed super maneuver ability.
Deflection vector (0-10 °) during 3.3 expansion mode
The vector spout 8 of the present embodiment is when expanding mode in order to reduce hypersonic resistance, and injection gangway Close All, therefore can only use mechanical deflection.Due to significantly maneuver can not be done during hypersonic flight, without the need to the deflection vector of wide-angle.Therefore the present embodiment vector spout 8 expand mode time mechanical deflection angle be set to ± about 10 °, be mainly used in the trim demand meeting the present embodiment.
The main design parameters of the present embodiment (in this specification sheets to the calculating of relative area with low speed mode gross wing area for calculating parameter):
| Captain | 20.929m | High speed mode gross wing area | 36.926m 2 |
| High speed mode machine width | 13.32m | High speed mode wing span | 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 |
| Low speed mode wing span | 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 | Sweepforward folds outer wing 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, have higher variant efficiency compared with other morphing aircraft.
As a fighter plane, connected applications of the present invention canard, edge strip, buzzard-type wing, swept wing and wing breach, by ingenious coupling vortex system, while solving many places aerodynamic deficiencies, significantly enhance At High Angle of Attack performance of the present invention, the manoevreability making it have to be not of the common run.And the designs such as combustion gas precooling, deceleration transmission, middle fan are incorporated the turbofan mode of combination engine 7, by optimizing detailed design further, improve efficiency and the thrust-weight ratio of driving engine, thus ensure that the high power demand of the present invention as a fighter plane.
As a hypersonic aircraft, present invention employs 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, its high speed mode aerodynamic configuration is made to have higher pneumatic efficiency when hypersonic flight.And utilize the special intension configuration of middle fan design, difficult problem of lighting a fire when solving dual-mode scramjet 10 super burn.The function of each parts of further optimal combination driving engine 7, each duct, while making it meet hypersonic power demand, has greater efficiency.
Vector spout 8 of the present invention, while meeting the different demand of driving engine different modalities, by the mode combined with dual vector by flow field vector, reaches ± jet deflexion the angle of 40 °, thus has consolidated outmaneuver of the present invention further.
The design of the present invention and major part thereof is all the time round the design concept of wide speed envelope curve.The multiple technology having different advantage under different conditions combines by the present invention, meets all demands in whole flight envelope, and in subsonic velocity with hypersonicly obtain extremely strong maneuvering performance and to cruise pneumatic efficiency.The design of the present invention and major part thereof meets wide speed envelope curve, performance-oriented Design Orientation, and has stronger reference and using value.
As mentioned above, specifically describing embodiments of the invention, but the present invention is not limited thereto.It should be appreciated by those skilled in the art, various amendment, combination, sub-portfolio or replacement can be carried out according to designing requirement or other factors, and they are in the scope of claims and equivalent thereof.
Claims (7)
1. wide flight envelope morphing aircraft, work under low speed mode or high speed mode or mutually change, it is characterized in that: comprise head and fuselage, there is canard the both sides, rear portion of described head, the both sides of described fuselage are fixed with sweepback inner wing, the wingtip of described sweepback inner wing is provided with sweepforward and folds outer wing, the rear upper of described fuselage is provided with a pair 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 corresponds to described combination engine and is provided with two vector spouts,
Described Die Design is Waverider head;
The aerofoil profile of described sweepback inner wing is supercritical airfoil; Described sweepforward folds the aerofoil profile of outer wing for " ∧ " shape missile wing; Under low speed mode, described sweepforward folds outer wing and launches along the wingtip of described sweepback inner wing; Under high speed mode, described sweepforward folds outer wing and overturns and the bottom surface being fitted in described sweepback inner wing, and the aerofoil profile that described sweepforward folds outer wing becomes the inversion of low speed mode aerofoil profile; The fuselage at described canard rear portion is provided with the edge strip extended to both sides;
Described combination engine comprises turbojet engine and dual-mode scramjet;
Described dual-mode scramjet comprises the by-pass air duct being 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 oxidant fuel case 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 being 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 a tip cone forward that described taper case closes rear profile; Be provided with fan propeller after described intension inlet channel, described fan propeller comprises fan blade, fan petiole and rotor block, and described fan blade is positioned at described by-pass air duct; Be positioned at the described by-pass air duct after described fan propeller and be provided with main main duct, in described main main duct, high-pressure compressor is installed, precompression chamber is provided with in described main main duct after described high-pressure compressor, be provided with intension combustion chamber after described precompression chamber, in described intension combustion chamber, be provided with propellant spray mouth; Be provided with one-level high-pressure turbine after described intension combustion chamber, described high-pressure turbine is fixedly connected with by high pressure rotor axle with described high-pressure compressor; Be provided with two-stage low-pressure turbine after described high-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, and described main main duct exhausr port is provided with size-adjustable and the exhaust adjustment sheet that can close completely; Described main main duct exhausr port is positioned at described by-pass air duct; The by-pass air duct extension as afterburner is provided with between described vector spout and described main main duct exhausr port;
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, comprises about two and can deflect ± the baffle of 20 °;
The relatively described sweepback inner wing in front end that described sweepforward folds outer wing is more forward, and described sweepforward folds gap between outer wing and described sweepback inner wing relatively rearward, and described sweepforward to fold the lower camber line of outer wing first half section straight downward-sloping;
Described sweepforward folds the maximum ga(u)ge of outer wing at wing chord 68% place; When described canard does not deflect, 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 is at 85% place of wing root chord from front end of described canard;
The leading edge sweep at the wingtip place of described sweepback inner wing increases and folds outer wing with described sweepforward and forms a leading edge of a wing breach; Described sweepback inner wing has the inverted diherdral of 4 °.
2. wide flight envelope morphing aircraft as claimed in claim 1, is characterized in that: described deoxidation compound Fuel Tank is built with liquified hydrogen or liquid hydrocarbon, and described oxidant fuel case is built with liquid oxygen; Described head lower surface, whole described by-pass air duct inwall are provided with H Exch, and described H Exch is double does the fuel feed line be connected with described propellant spray mouth.
3. wide flight envelope morphing aircraft as claimed in claim 1, it is characterized in that: described fan speed change device comprises the sun gear be rotatably installed on described low pressure rotor axle, be rotatably installed in the planetary wheel on described sun gear, outside described planetary wheel, gear ring is installed, 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.
4. 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 the flow deflector that can regulate and open size; Described by-pass air duct admission port is provided with the lower lip that can deflect certain angle up and down.
5. wide flight envelope morphing aircraft as claimed in claim 1, is characterized in that: be provided with H Exch in described precompression chamber, and described H Exch is double does the fuel feed line be connected with described propellant spray mouth.
6. wide flight envelope morphing aircraft as claimed in claim 1, is characterized in that: the injection passage being provided with a hollow in described baffle, described injection passage is provided with an injection entrance as admission port; Described injection passage is provided with three eductor outlet, be positioned at described vector nozzle divergence section reference position and be provided with main eductor outlet, be positioned in the middle part of described vector nozzle divergence section and be respectively equipped with middle part eductor outlet and afterbody eductor outlet with afterbody, described main eductor outlet, middle part eductor outlet and afterbody eductor outlet are all provided with by-pass valve control; Described injection entrance is grid type admission port.
7. 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.
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| CN114077771A (en) * | 2022-01-07 | 2022-02-22 | 中国空气动力研究与发展中心计算空气动力研究所 | Pneumatic shape reverse design method |
| CN114313253B (en) * | 2022-03-03 | 2022-05-17 | 中国空气动力研究与发展中心计算空气动力研究所 | Aerodynamic layout and design method of high-lift-drag-ratio air-breathing hypersonic aircraft |
| CN116985994B (en) * | 2023-09-21 | 2023-11-28 | 中国空气动力研究与发展中心计算空气动力研究所 | Invisible aircraft |
| CN117330084B (en) * | 2023-12-01 | 2024-02-23 | 中国航空工业集团公司西安飞机设计研究所 | Civil aircraft attitude envelope determining method |
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