CN203740120U - Aerodynamic structure of morphing aircraft with wide flight envelope - Google Patents
Aerodynamic structure of morphing aircraft with wide flight envelope Download PDFInfo
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- CN203740120U CN203740120U CN201420151460.XU CN201420151460U CN203740120U CN 203740120 U CN203740120 U CN 203740120U CN 201420151460 U CN201420151460 U CN 201420151460U CN 203740120 U CN203740120 U CN 203740120U
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Abstract
The utility model discloses an aerodynamic structure of a morphing aircraft with wide flight envelope. The wing sweeping direction, aspect ratio and airfoil profile are changed by adopting a manner of the variation of a folding wing, so that the adaptability of the aerodynamic configuration in the wide flight envelope is improved; as for the aerodynamic configuration, a wave-rider nose and a fuselage, a canard wing and a strake, as well as a wing front edge notch and a forward-swept folding outer wing are combined and complemented with each other respectively, so that the high performance of the aircraft in a wide speed range and at various flight attitudes is guaranteed; the morphing aircraft can change the aerodynamic configuration on the fly and keeps the optimal state under different flight states; compared with the conventional aircraft with a fixed layout, the morphing aircraft has the advantages that the flight envelope is wider, the operational effectiveness is higher, the aerodynamic configuration can be automatically changed and the flight performance can be optimized according to the requirements for flight environments, flight profiles, operational missions and the like.
Description
Technical field
The utility model 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.
Utility model content
Technical problem to be solved in the utility model is to provide a kind of pneumatic structure that can independently change aerodynamic configuration according to flight environment of vehicle, optimize the wide flight envelope morphing aircraft of airworthiness.
For solving the problems of the technologies described above, the technical solution of the utility model is: the pneumatic structure of 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.
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, the lateral margin of described Waverider head has inverted diherdral and lateral margin lower surface upwards arches upward.
Owing to having adopted technique scheme, the utility model 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; 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, ensure the High Performance of aircraft under wide speed interval, many flight attitudes; The utility model can change aerodynamic configuration awing, can be in property retention optimum regime under different flight state.Compared with the fixing layout aircraft of routine, the utility model flight envelope 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.
Brief description of the drawings
Fig. 1 is the schematic diagram of the folding outer wing of the utility model embodiment sweepforward under deployed condition;
Fig. 2 is the right elevation of Fig. 1;
Fig. 3 is the block diagram of the folding outer wing of the utility model embodiment sweepforward under folded state;
Fig. 4 is the right elevation of Fig. 3;
Fig. 5 is the aerofoil profile schematic diagram of the utility model embodiment sweepback inner wing;
Fig. 6 is the aerofoil profile schematic diagram of the folding outer wing of the utility model embodiment sweepforward;
Fig. 7 is the closed aerofoil profile schematic diagram of the folding outer wing of the utility model embodiment sweepforward and sweepback inner wing;
Fig. 8 is that the pneumatic efficiency of buzzard-type wing and swept wing is with the change curve of speed;
Fig. 9 is the air hydrodynamic schematic diagram of the closed aerofoil profile of the utility model embodiment, 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 10 is the shock wave schematic diagram of the closed aerofoil profile of the utility model embodiment;
Figure 11 is the schematic cross-section of the utility model embodiment Waverider head;
The air hydrodynamic schematic diagram of canard and edge strip when Figure 12 is the utility model embodiment At High Angle of Attack attitude;
Figure 13 is the I place enlarged drawing in Fig. 1, there is shown the leading edge of a wing breach that the folding outer wing of sweepback inner wing and sweepforward forms;
In figure: 1-head; 2-fuselage; 3-canard; 4-sweepback inner wing; 5-sweepforward folds outer wing; 6-vertical tail; 7-edge strip; 8-leading edge of a wing breach; 9-droope snoot; 10-flaperon.
Detailed description of the invention
Understand for technical characterictic of the present utility model, object and effect being had more clearly, now contrast brief description of the drawings detailed description of the invention of the present utility model.
As shown in Figure 1, Figure 2 and Figure 3, the pneumatic structure of 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, and the top, rear portion of described fuselage 2 is provided with a pair of full dynamic formula vertical tail 6.
, 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 5, 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 6, 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 4.
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 7 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. 3.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 10 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 3, 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 9, 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 9, 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 9 of sweepback inner wing 4 can make sweepback inner wing 4, the folding outer wing 5 of sweepforward fit tightr.The droope snoot 9 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, 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 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 ensureing hypersonic flight, can match with fuselage 2 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 11.
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.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 1, 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 ensure 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 7, 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 7 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 7, 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 7, 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 7, 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 7, can be reinforced, blow and import canard-edge strip whirlpool by the lower surface high energy air-flow of letting out on edge strip 7 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 12, 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 7 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 7 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 7 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 10 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 10 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 ensure 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 13, 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 8 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 8 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 ensure 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.
The utility model 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 utility model 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 utility model, make it have the manoevreability being not of the common run.
As a hypersonic aircraft, the utility model has adopted the designs such as Waverider, compression lift aerofoil profile, large sweepback angle delta wing, makes its high speed mode aerodynamic configuration in the time of hypersonic flight, have higher pneumatic efficiency.
As mentioned above, described particularly embodiment of the present utility model in the above, but the utility model is not limited to this.It should be appreciated by those skilled in the art, can carry out various amendments, combination, sub-portfolio or replacement according to designing requirement or other factors, and they are in the scope of claims and equivalent thereof.
Claims (9)
1. the pneumatic structure of 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, and the top, rear portion of described fuselage is provided with a pair of full dynamic formula vertical tail;
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.
2. the pneumatic structure of 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. the pneumatic structure of 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.
4. the pneumatic structure of wide flight envelope morphing aircraft as claimed in claim 1, is characterized in that: in the time of described not deflection of canard, described canard and described edge strip form continuous pneumatic face.
5. the pneumatic structure of wide flight envelope morphing aircraft as claimed in claim 4, is characterized in that: described canard and described edge strip have the inverted diherdral of 4 °.
6. the pneumatic structure of wide flight envelope morphing aircraft as claimed in claim 5, is characterized in that: the clinoid of described canard at the wing root chord of described canard from front end 85%.
7. the pneumatic structure of 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.
8. the pneumatic structure of wide flight envelope morphing aircraft as claimed in claim 1, is characterized in that: described sweepback inner wing has the inverted diherdral of 4 °.
9. the pneumatic structure of 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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Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109278983A (en) * | 2018-11-26 | 2019-01-29 | 中国航空工业集团公司沈阳空气动力研究所 | A kind of change buzzard-type wing and canard clutch mechanism and its working method |
| CN111605724A (en) * | 2020-05-22 | 2020-09-01 | 成都飞机工业（集团）有限责任公司 | Simulation test method for atmospheric data system |
| CN112339991A (en) * | 2020-11-05 | 2021-02-09 | 江西洪都航空工业股份有限公司 | Aircraft tail structure for stability and drag enhancement |
| CN114852299A (en) * | 2022-04-30 | 2022-08-05 | 西北工业大学 | Wing body fusion underwater glider with forward swept wing layout |
| CN115946842A (en) * | 2023-03-10 | 2023-04-11 | 中国空气动力研究与发展中心计算空气动力研究所 | Damping device of aircraft and aircraft |
-
2014
- 2014-03-31 CN CN201420151460.XU patent/CN203740120U/en not_active Expired - Fee Related
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109278983A (en) * | 2018-11-26 | 2019-01-29 | 中国航空工业集团公司沈阳空气动力研究所 | A kind of change buzzard-type wing and canard clutch mechanism and its working method |
| CN109278983B (en) * | 2018-11-26 | 2023-09-29 | 中国航空工业集团公司沈阳空气动力研究所 | Front-sweep wing-changing and duck wing overlapping mechanism and working method thereof |
| CN111605724A (en) * | 2020-05-22 | 2020-09-01 | 成都飞机工业（集团）有限责任公司 | Simulation test method for atmospheric data system |
| CN112339991A (en) * | 2020-11-05 | 2021-02-09 | 江西洪都航空工业股份有限公司 | Aircraft tail structure for stability and drag enhancement |
| CN112339991B (en) * | 2020-11-05 | 2023-01-03 | 江西洪都航空工业股份有限公司 | Aircraft tail structure for stability and drag enhancement |
| CN114852299A (en) * | 2022-04-30 | 2022-08-05 | 西北工业大学 | Wing body fusion underwater glider with forward swept wing layout |
| CN115946842A (en) * | 2023-03-10 | 2023-04-11 | 中国空气动力研究与发展中心计算空气动力研究所 | Damping device of aircraft and aircraft |
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