CN115946842A - Damping device of aircraft and aircraft - Google Patents
Damping device of aircraft and aircraft Download PDFInfo
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- CN115946842A CN115946842A CN202310227795.9A CN202310227795A CN115946842A CN 115946842 A CN115946842 A CN 115946842A CN 202310227795 A CN202310227795 A CN 202310227795A CN 115946842 A CN115946842 A CN 115946842A
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/10—Drag reduction
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Abstract
The application discloses fairing and aircraft of aircraft, this fairing are located the inside of the wing leading edge of aircraft, and this fairing includes: the device comprises a telescopic pneumatic plate, a gear mechanism and a driving mechanism, wherein the gear mechanism is connected with the driving mechanism, and the rotating torque of the driving mechanism is transmitted to the telescopic pneumatic plate so as to enable the telescopic pneumatic plate to move linearly; the gear mechanisms are positioned on two sides of the telescopic pneumatic plate; an opening is arranged on the front edge of the wing, and the telescopic aerodynamic plate extends to the outer side of the front edge of the wing through the opening; under the condition that the telescopic pneumatic plate is arranged inside the leading edge of the wing, the aircraft flies in a low subsonic speed flight state; under the condition that the telescopic pneumatic plate extends to the outer side of the front edge of the wing, the aircraft flies in a supersonic flying state, and the detached shock waves in the supersonic flying state are changed into oblique shock waves, so that the problem of design balance of low, sub, span and supersonic pneumatic performances at the same time is effectively solved.
Description
Technical Field
The application belongs to the technical field of aircrafts, and particularly relates to a damping device of an aircraft and the aircraft.
Background
The supersonic aircraft taking off and landing in a sliding mode needs to have high-lift-force low-resistance (namely high-lift-drag ratio) characteristics in a full-speed domain range so as to improve ground taking off and landing capability, high-subsonic-speed long-endurance capability and supersonic cruising capability under the condition that an engine does not apply force.
The low subsonic velocity and transonic velocity aerodynamic balance design of the aircraft is a performance contradiction compromise process, and meanwhile, it is difficult to maintain better aerodynamic performance under low subsonic velocity and transonic velocity. The small/medium-sized front edge sweepback angle wing designed by adopting a low-speed high-lift wing profile (such as a blunt-nose thick wing profile, the radius of the front edge is large, and the maximum relative thickness is more than 12 percent) can meet the requirements of taking off and landing and low-speed flight performance to a greater extent, but the high subsonic speed flight has large resistance, short voyage time, difficult long voyage, difficult even high subsonic speed flight under the existing power condition, and difficult realization of transonic speed flight; the small/medium leading edge sweepback angle wing designed by adopting a high subsonic velocity wing type (such as a round head sharp tail wing type, a medium leading edge radius and a maximum relative thickness of 6-12%) can obtain excellent high subsonic velocity aerodynamic performance and basically satisfied low-speed aerodynamic performance, but the resistance is large when the wing flies across supersonic velocity, the long-time cruising flight across supersonic velocity is difficult to realize, and the flying velocity is difficult to reach the supersonic velocity flying velocity under the condition that an engine does not apply force; a medium/large-front-edge sweepback-angle wing designed by adopting a supersonic-speed wing (such as a tip-tail wing with the maximum relative thickness of 3-6%) can obtain better supersonic-speed-crossing pneumatic performance and basically satisfied high-subsonic-speed pneumatic performance, but has poor low-speed performance, thereby causing great difficulty in taking off and landing. How to obtain better aerodynamic performance under low subsonic velocity and cross supersonic velocity simultaneously is the problem that continues to be solved at present.
Disclosure of Invention
This application is intended to provide fairing and aircraft of an aircraft to solve the not enough that exists among the prior art, the technical problem that this application will be solved realizes through following technical scheme.
In a first aspect, embodiments of the present application provide a fairing for an aircraft, the fairing being located inside a leading edge of a wing of the aircraft, the fairing comprising: the device comprises a telescopic pneumatic plate, a gear mechanism and a driving mechanism, wherein the gear mechanism is connected with the driving mechanism, and the rotating torque of the driving mechanism is transmitted to the telescopic pneumatic plate so as to enable the telescopic pneumatic plate to move linearly; the gear mechanisms are positioned on two sides of the telescopic pneumatic plate; an opening is arranged on the wing leading edge, and the telescopic aerodynamic plate extends to the outer side of the wing leading edge through the opening;
with the telescoping aerodynamic panel inboard of the wing leading edge, the aircraft flies in a low subsonic flight regime;
under the condition that the telescopic pneumatic plate extends to the outer side of the leading edge of the wing, the aircraft flies in a supersonic flying state and changes the detached shock waves in the supersonic flying state into oblique shock waves.
Optionally, the gear mechanism includes one or more sets of gear units, each gear unit includes a driving gear mechanism and one or more driven gear mechanisms, wherein the driving gear mechanism is connected to the driving mechanism and is configured to drive the telescopic pneumatic plate to perform linear motion, and the driven gear mechanism is configured to position the telescopic pneumatic plate.
Optionally, a rack is arranged between the gear mechanism and the telescopic pneumatic plate, the rack is respectively matched with the gear mechanism, and the rack is used for driving the telescopic pneumatic plate to extend and retract.
Optionally, the aircraft is flying in a low subsonic flight condition with the telescoping aerodynamic panel inside the wing leading edge, comprising:
the aircraft flies in a low subsonic flight condition with the telescoping aerodynamic plate inside the wing leading edge and the telescoping aerodynamic plate leading edge merging with the wing leading edge.
Optionally, in a case where the retractable aerodynamic plate extends to the outer side of the leading edge of the wing, the aircraft flies in a supersonic flight state, and changes a detached shock wave in the supersonic flight state into an oblique shock wave, including:
the driving mechanism drives the telescopic pneumatic plate to move, so that the first part of the telescopic pneumatic plate extends to the outer part of the wing leading edge, the second part of the telescopic pneumatic plate is positioned in the wing leading edge, the wing leading edge forms a sharp leading edge, and the detached shock wave formed by the blunt wing leading edge is converted into the oblique shock wave formed by the telescopic pneumatic plate extending out of the rear sharp leading edge.
Optionally, the length of the first portion of the telescoping pneumatic plate is 100mm.
Optionally, the gear unit comprises one driving gear mechanism and three driven gear mechanisms.
Optionally, the wing of the aircraft is a medium leading edge radius, medium leading edge swept angle wing formed by a hypersonic velocity airfoil.
Optionally, the telescopic pneumatic plate has a thickness of 10mm.
In a second aspect, embodiments of the present application provide an aircraft including a fairing of the aircraft of the first aspect.
The embodiment of the application has the following advantages:
the embodiment of this application provides a fairing and aircraft of aircraft, this fairing is located the inside of the wing leading edge of aircraft, and this fairing includes: the device comprises a telescopic pneumatic plate, a gear mechanism and a driving mechanism, wherein the gear mechanism is connected with the driving mechanism, and the rotating torque of the driving mechanism is transmitted to the telescopic pneumatic plate so as to enable the telescopic pneumatic plate to move linearly; the gear mechanisms are positioned on two sides of the telescopic pneumatic plate; an opening is arranged on the front edge of the wing, and the telescopic aerodynamic plate extends to the outer side of the front edge of the wing through the opening; under the condition that the telescopic pneumatic plate is arranged inside the leading edge of the wing, the aircraft flies in a low subsonic speed flight state; under the condition that the telescopic pneumatic plate extends to the outer side of the front edge of the wing, the aircraft flies in a supersonic flying state and changes the detached shock waves in the supersonic flying state into oblique shock waves.
Drawings
In order to more clearly illustrate the embodiments or prior art solutions of the present application, the drawings used in the description of the embodiments or prior art will be briefly described below, it is obvious that the drawings in the description below are only some embodiments described in the present application, and that other drawings can be obtained by those skilled in the art without inventive labor.
FIG. 1 is a schematic diagram of a fairing of an aircraft according to an embodiment of the present application;
FIG. 2 is a schematic view of a two-dimensional airfoil of moderate thickness with a curved leading edge, a sharp trailing edge, according to an embodiment of the present application;
FIG. 3 is a schematic illustration of a three-dimensional airfoil generated as a two-dimensional airfoil with a curved leading edge, a sharp trailing edge, and a medium thickness according to an embodiment of the present application;
FIG. 4 is a schematic view of a detached shock wave of an airfoil with a circular leading edge, a sharp trailing edge and a medium thickness in a supersonic flying state according to an embodiment of the present disclosure;
FIG. 5 is a two-dimensional overall schematic view of a wing leading edge mounted retractable aerodynamic plate fairing in an embodiment of the present application;
FIG. 6 is a three-dimensional global schematic of a wing leading edge mounted retractable aerodynamic plate fairing in an embodiment of the present application;
FIG. 7 is a two-dimensional schematic view of a supersonic flying state detached shock wave when the telescopic aerodynamic plate fairing for the leading edge of the wing in the embodiment of the application is retracted;
FIG. 8 is a schematic two-dimensional representation of a supersonic flight state oblique shock wave when the telescopic aerodynamic plate fairing at the leading edge of the wing of the present application is extended;
reference numerals are as follows:
1- -an airfoil; 2-telescopic pneumatic plate; 3- -driving gear mechanism; 4- -passive gear mechanism.
Detailed Description
To make the objects, technical solutions and advantages of the present application more clear, the technical solutions of the present application will be clearly and completely described below with reference to specific embodiments and corresponding drawings. It should be apparent that the described embodiments are only some of the embodiments of the present application, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present application.
Referring to fig. 1, there is shown a schematic structural view of a fairing of an aircraft of the present application, the fairing being located inside the leading edge of a wing 1 of the aircraft, the fairing comprising: the device comprises a telescopic pneumatic plate 2, a gear mechanism and a driving mechanism, wherein the gear mechanism is connected with the driving mechanism, and the rotating torque of the driving mechanism is transmitted to the telescopic pneumatic plate so as to enable the telescopic pneumatic plate to move linearly; the gear mechanisms are positioned on two sides of the telescopic pneumatic plate; an opening is arranged on the front edge of the wing, and the telescopic aerodynamic plate extends to the outer side of the front edge of the wing through the opening;
under the condition that the telescopic pneumatic plate is arranged inside the leading edge of the wing, the aircraft flies in a low subsonic speed flight state;
under the condition that the telescopic pneumatic plate extends to the outer side of the leading edge of the wing, the aircraft flies in a supersonic flying state, and the detached shock wave in the supersonic flying state is changed into an oblique shock wave.
The embodiment of the application provides a telescopic pneumatic plate supersonic flight fairing of wing leading edge suitable for supersonic aircraft, after stretching out telescopic pneumatic plate through actuating mechanism, can become the detached shock wave under the supersonic flight to oblique shock wave thereby realize the drag reduction, retrieve back wing leading edge through actuating mechanism with telescopic pneumatic plate simultaneously and keep middle leading edge radius, and promote the aerodynamic performance under the low subsonic flight, effectively solved low, inferior, stride, supersonic aerodynamic performance simultaneously better design balance problem.
Optionally, the gear mechanism includes one or more sets of gear units, each of which includes a driving gear mechanism 3 and one or more driven gear mechanisms 4, wherein the driving gear mechanism 3 is connected to the driving mechanism for driving the telescopic pneumatic plate to move linearly, and the driven gear mechanism is used for position clamping the telescopic pneumatic plate.
Wherein the drive mechanism may be a drive motor.
Optionally, a rack is arranged between the gear mechanism and the telescopic pneumatic plate, the rack is respectively matched with the gear mechanism, and the rack is used for driving the telescopic pneumatic plate to extend out and retract.
Optionally, with the retractable aerodynamic plates inside the wing leading edge, the aircraft is flying in a low subsonic flight regime comprising:
under the condition that the telescopic aerodynamic plate is arranged inside the wing leading edge and the telescopic aerodynamic plate leading edge is fused with the wing leading edge, the aircraft flies in a low subsonic speed flight state.
Optionally, in a case where the retractable aerodynamic plate extends to the outside of the leading edge of the wing, the aircraft flies in a supersonic flight state, and changes the detached shock wave in the supersonic flight state into an oblique shock wave, including:
the driving mechanism drives the telescopic air moving plate to move, so that the first part of the telescopic air moving plate extends to the outer part of the wing leading edge, the second part of the telescopic air moving plate is positioned in the wing leading edge, the wing leading edge forms a sharp leading edge, and the shock wave of the blunt wing leading edge is converted into the oblique shock wave formed by the telescopic air moving plate extending out of the front edge.
Specifically, in the embodiment of the invention, the telescopic aerodynamic plate is divided into two parts, the part extending to the outer part of the wing leading edge is determined as a first part, and the part positioned in the inner part of the wing leading edge is determined as a second part.
Optionally, the length of the first portion of the telescoping pneumatic plate is 100mm. That is, the portion extending outside the leading edge of the wing is 100mm in length.
Optionally, the gear unit comprises one driving gear mechanism and three driven gear mechanisms.
Optionally, the wing of the aircraft is a medium leading edge radius, medium leading edge sweepback wing constructed of a high subsonic velocity airfoil.
Optionally, the telescopic pneumatic plate has a thickness of 10mm.
In the embodiment of the present application, an arc leading edge, a sharp trailing edge, an airfoil profile with a maximum thickness of 6% to 12% and a maximum camber of about 2% are adopted, as shown in fig. 2, fig. 2 is a schematic diagram of a two-dimensional airfoil profile with an arc leading edge, a sharp trailing edge and a medium thickness in an embodiment of the present application, a high lift-drag ratio performance and an internal large space volume of a flight speed below a high subsonic speed can be obtained, in order to further adapt to high subsonic flight, a sweepback angle of a leading edge is generally taken within a range of 25 ° to 35 °, a total difference of geometric torsion angles of a span-wise station airfoil profile is about 3 ° to 6 °, which facilitates improvement of stall characteristics of an outer wing section, and a wing is generated according to the above parameters, as shown in fig. 3, fig. 3 is a schematic diagram of a three-dimensional wing generated by a two-dimensional airfoil profile with an arc leading edge, a sharp trailing edge and a medium thickness in an embodiment of the present application, the wing-shaped suspension type supersonic aircraft is suitable for flying at a speed below a high subsonic speed, but is not suitable for flying at a cross/supersonic speed, because the wing profile is too thick, strong shock waves are generated on the upper surface of the wing under the cross/supersonic speed flying state, so that wave resistance is overlarge, and the wing leading edge with a larger radius generates detached shock waves so that resistance is overlarge under the cross/supersonic speed flying state, as shown in fig. 4, fig. 4 is a schematic diagram of the detached shock waves of the wing profile with an arc leading edge, a sharp trailing edge and a medium thickness under the supersonic speed flying state in the embodiment of the application.
In order to solve the problem, the application proposes to design a retractable aerodynamic plate inside the leading edge of the wing, as shown in fig. 5 to 6, fig. 5 is a two-dimensional global schematic diagram of a retractable aerodynamic plate fairing installed on the leading edge of the wing in an embodiment of the application, fig. 6 is a three-dimensional global schematic diagram of a retractable aerodynamic plate fairing installed on the leading edge of the wing in an embodiment of the application, the thickness is about 10mm to keep the requirement of rigidity and strength, the windward side of the retractable aerodynamic plate is a shape cut from the shape of the leading edge of the wing, and when the retractable aerodynamic plate is retracted, the retractable aerodynamic plate and the leading edge of the wing keep high fusion, and the shape is consistent with the wing shape of the device without the aerodynamic plate, in order to change the detached shock waves into oblique shock waves and reduce the supersonic flight resistance, as shown in fig. 8, and fig. 8 is a two-dimensional schematic diagram of the oblique shock waves in the supersonic flight state when the telescopic aerodynamic plate fairing for the leading edge of the wing extends out, the telescopic aerodynamic plate extends out of the leading edge of the wing under the driving of a gear mechanism, and the extension length is about 100mm, so that the drag reduction effect is achieved.
The telescopic aerodynamic plate at the front edge of the wing is a flat plate along the expansion direction and comprises a hidden part inside the wing, the chord direction length of the aerodynamic plate is about 200-300 mm, the thickness of the aerodynamic plate is about 10mm, a rack assembled with a gear mechanism is installed near the gear mechanism so as to be convenient for driving the aerodynamic plate to extend out and retract, when the telescopic aerodynamic plate extends out of the front edge of the wing, the shape of the front edge of the wing is changed from an arc shape to a pointed shape, the shock wave generated by the arc front edge is converted into oblique shock wave, the aerodynamic resistance of the shock wave to the wing is reduced, and meanwhile, the shock wave form on the upper surface of the wing is indirectly changed.
Wherein, the gear mechanism comprises a plurality of groups of gear units, each gear unit takes four gears as a group and comprises a driving gear mechanism 3 and a plurality of driven gear mechanisms 4, the driving gear mechanism transmits the rotating torque of the power driving motor to the rack of the pneumatic plate through the gears and converts the rotating torque into linear motion, the driven gear mechanism mainly clamps the position of the pneumatic plate, so that the pneumatic plate does not generate position deviation when extending or retracting, and simultaneously bears the pneumatic force on the pneumatic plate and transmits the pneumatic force to the wing bearing part.
The telescopic pneumatic plate drag reduction device for the wing leading edge solves the problem that the wave resistance of the wing with the medium leading edge radius and the medium leading edge sweepback angle formed by the high subsonic velocity wing profile is large and difficult to apply during supersonic flight, also solves the problem that the excellent aerodynamic performance of the wing with the medium leading edge radius and the medium leading edge sweepback angle formed by the high subsonic velocity wing profile is kept during low subsonic velocity flight, and effectively meets the flight performance at low/subsonic/span/supersonic flight speed.
As can be seen from fig. 6, the fairing includes a wing 1, a telescopic aerodynamic plate 2, a driving gear mechanism 3 and a plurality of driven gear mechanisms 4.
The telescopic aerodynamic plate 2 is positioned near the front edge of the wing 1 and is completely positioned in the wing when being retracted, the front edge of the telescopic aerodynamic plate 2 is highly fused with the front edge of the wing 1, the appearance of the wing is kept when the aerodynamic plate is not designed, a part of the telescopic aerodynamic plate is exposed out of the wing 1 when the aerodynamic plate extends out, and the rest part of the telescopic aerodynamic plate is still concealed in the wing 1 and is connected with the driving gear mechanism 3 and the driven gear mechanism 4; the driving gear mechanism 3 and the driven gear mechanism 4 are hidden in the wing 1, are connected with the telescopic pneumatic plate 2 in a gear mode, position clamping is carried out on the telescopic pneumatic plate 2, driving power required by extending and retracting of the telescopic pneumatic plate 2 is transmitted, the driving gear mechanism is connected with a force bearing part of the wing 1, pneumatic power borne by the telescopic pneumatic plate 2 is transmitted to the force bearing part of the wing 1, meanwhile, the driving gear mechanism 3 is also connected with the power driving motor, and rotating torque of the power driving motor is transmitted to the telescopic pneumatic plate 2 to form linear motion, so that the telescopic pneumatic plate 2 is driven to extend or retract.
The front edge of the telescopic aerodynamic plate 2 and the front edge of the wing 1 are designed in a fusion mode, the telescopic aerodynamic plate is in shape-preserving with the wing 1 when being retracted, the original flight performance under the low subsonic flight speed is kept, the front edge of the wing 1 is changed into a sharp front edge when being extended out, the detached shock wave under the supersonic flight speed is changed into oblique shock wave, the drag reduction effect under the aerodynamic supersonic flight speed is achieved, the extending length of the telescopic aerodynamic plate 2 is about 100mm, and the thickness of the telescopic aerodynamic plate is about 10mm.
The driving gear mechanism 3 is connected with a power driving motor, transmits driving power required by the telescopic pneumatic plate 2, and meanwhile, the driven gear mechanism 4 clamps the position of the telescopic pneumatic plate 2 and transmits the pneumatic power of the telescopic pneumatic plate 2 to the force bearing part of the wing 1.
The working process of the wing leading edge telescopic type aerodynamic plate damping device is as follows:
(a) When the aircraft flies at low subsonic speed, under the driving of the driving gear mechanism 3, the position is blocked by the driving gear mechanism 3 and the driven gear mechanism 4, the telescopic aerodynamic plate 2 is retracted into the wing 1, the front edge of the telescopic aerodynamic plate 2 is highly fused with the front edge of the wing 1, the wing shape without the telescopic aerodynamic plate 2 is formed, and the excellent aerodynamic performance of the wing under low subsonic speed flight is kept.
(b) When the aircraft flies at the supersonic-crossing speed, under the driving of the driving gear mechanism 3, the position is blocked by the driving gear mechanism 3 and the driven gear mechanism 4, the telescopic type aerodynamic plate 2 extends to the outside of the wing 1 for a certain length, so that the front edge of the wing 1 forms a pointed front edge, the detached shock wave formed by the front edge of the blunt wing is converted into the oblique shock wave formed by the front edge of the telescopic type aerodynamic plate 2 extending out of the pointed front edge, the flight resistance of the blunt-leading-edge wing at the supersonic-crossing speed can be effectively reduced, the flight performance of the blunt-leading-edge wing at the supersonic-crossing speed is improved, and the application speed range of the blunt-leading-edge wing is expanded.
A telescopic pneumatic plate is arranged in the vicinity of the front edge of the wing, the driving gear mechanism is used for conveying telescopic and withdrawing power required by the telescopic pneumatic plate, a group of mechanisms are formed by 1 driving gear mechanism and 3 driven gear mechanisms for position clamping and pneumatic force transmission on the telescopic pneumatic plate, the telescopic pneumatic plate extends out of the front edge of the wing through the driving mechanism, the original shock wave of the detached body crossing at supersonic flying speed can be changed into oblique shock wave to achieve pneumatic drag reduction effect, meanwhile, the telescopic pneumatic plate is withdrawn through the driving mechanism, and then the front edge of the telescopic pneumatic plate is highly fused with the front edge of the wing, so that the original appearance of the wing without the telescopic pneumatic plate is formed, the pneumatic performance of the original wing at low subsonic flying speed is kept, and the design balance problem of low, subsonic, striding and supersonic pneumatic performance is better is effectively solved.
The embodiment of the application provides an aircraft, including foretell aircraft's fairing.
The embodiment of this application provides a fairing and aircraft of aircraft, this fairing is located the inside of the wing leading edge of aircraft, and this fairing includes: the device comprises a telescopic pneumatic plate, a gear mechanism and a driving mechanism, wherein the gear mechanism is connected with the driving mechanism, and the rotation torque of the driving mechanism is transmitted to the telescopic pneumatic plate so as to enable the telescopic pneumatic plate to move linearly; the gear mechanisms are positioned on two sides of the telescopic pneumatic plate; an opening is arranged on the front edge of the wing, and the telescopic aerodynamic plate extends to the outer side of the front edge of the wing through the opening; under the condition that the telescopic pneumatic plate is arranged inside the leading edge of the wing, the aircraft flies in a low subsonic speed flying state; under the condition that the telescopic pneumatic plate extends to the outer side of the front edge of the wing, the aircraft flies in a supersonic flying state and changes the detached shock wave in the supersonic flying state into oblique shock wave.
It should be noted that the above detailed description is exemplary and is intended to provide further explanation of the disclosure. Unless defined otherwise, all technical and scientific terms used herein have the same meaning as commonly understood by one of ordinary skill in the art to which this application belongs.
It is noted that the terminology used herein is for the purpose of describing particular embodiments only and is not intended to be limiting of exemplary embodiments according to the present application. As used herein, the singular is intended to include the plural unless the context clearly dictates otherwise. Furthermore, it will be further understood that the terms "comprises" and/or "comprising," when used in this specification, specify the presence of stated features, steps, operations, devices, components, and/or combinations thereof.
It should be noted that the terms "first," "second," and the like in the description and claims of this application and in the drawings described above are used for distinguishing between similar elements and not necessarily for describing a particular sequential or chronological order. It is to be understood that the terms so used are interchangeable under appropriate circumstances such that the embodiments of the application described herein are capable of operation in other sequences than those illustrated or otherwise described herein.
Furthermore, the terms "include" and "have," as well as any variations thereof, are intended to cover a non-exclusive inclusion. For example, a process, method, system, article, or apparatus that comprises a list of steps or elements is not necessarily limited to those steps or elements explicitly listed, but may include other steps or elements not explicitly listed or inherent to such process, method, article, or apparatus.
For ease of description, spatially relative terms such as "over 8230," "upper surface," "above," and the like may be used herein to describe the spatial positional relationship of one device or feature to other devices or features as illustrated in the figures. It will be understood that the spatially relative terms are intended to encompass different orientations of the device in use or operation in addition to the orientation depicted in the figures. For example, if a device in the figures is turned over, devices described as "above" or "on" other devices or configurations would then be oriented "below" or "under" the other devices or configurations. Thus, the exemplary terms "at 8230; \8230; above" may include both orientations "at 8230; \8230; above" and "at 8230; \8230; below". The device may also be oriented in other different ways, such as by rotating it 90 degrees or at other orientations, and the spatially relative descriptors used herein interpreted accordingly.
In the foregoing detailed description, reference is made to the accompanying drawings, which form a part hereof. In the drawings, like numerals typically identify like components, unless context dictates otherwise. The illustrated embodiments described in the detailed description, drawings, and claims are not meant to be limiting. Other embodiments may be utilized, and other changes may be made, without departing from the spirit or scope of the subject matter presented here.
The above description is only a preferred embodiment of the present application and is not intended to limit the present application, and various modifications and changes may be made by those skilled in the art. Any modification, equivalent replacement, improvement and the like made within the spirit and principle of the present application shall be included in the protection scope of the present application.
Claims (10)
1. A fairing for an aircraft, said fairing being located inside a leading edge of a wing of the aircraft, said fairing comprising: the device comprises a telescopic pneumatic plate, a gear mechanism and a driving mechanism, wherein the gear mechanism is connected with the driving mechanism, and the rotation torque of the driving mechanism is transmitted to the telescopic pneumatic plate so as to enable the telescopic pneumatic plate to move linearly; the gear mechanisms are positioned on two sides of the telescopic pneumatic plate; an opening is arranged on the wing leading edge, and the telescopic aerodynamic plate extends to the outer side of the wing leading edge through the opening;
with the telescoping aerodynamic panel inboard of the wing leading edge, the aircraft is flying at a low subsonic flight regime;
under the condition that the telescopic pneumatic plate extends to the outer side of the leading edge of the wing, the aircraft flies in a supersonic flying state, and the detached shock wave in the supersonic flying state is changed into an oblique shock wave.
2. The aircraft fairing as recited in claim 1, wherein said gear mechanism comprises one or more sets of gear units, each gear unit comprising a driving gear mechanism and one or more driven gear mechanisms, wherein said driving gear mechanism is connected to said driving mechanism for driving said retractable aerodynamic plates to move linearly, and said driven gear mechanisms are used for position-locking said retractable aerodynamic plates.
3. The drag reducing device for aircraft according to claim 1, wherein a rack is provided between the gear mechanism and the telescopic pneumatic plate, the rack is respectively matched with the gear mechanism, and the rack is used for driving the extension and retraction of the telescopic pneumatic plate.
4. The fairing device of claim 1, wherein said aircraft is flying at a low subsonic flight condition with said telescoping aerodynamic plate inboard of said wing leading edge, comprising:
the aircraft flies in a low subsonic flight condition with the telescoping aerodynamic plate inside the wing leading edge and the telescoping aerodynamic plate leading edge merging with the wing leading edge.
5. The fairing device of claim 2 wherein said aircraft is flying in supersonic flight with said telescoping aerodynamic plates extending outboard of said leading edge of said wing and turning the detached shock wave in supersonic flight into an oblique shock wave comprising:
the driving mechanism drives the telescopic pneumatic plate to move, so that the first part of the telescopic pneumatic plate extends to the outer part of the wing leading edge, the second part of the telescopic pneumatic plate is positioned in the wing leading edge, the wing leading edge forms a sharp leading edge, and the detached shock wave formed by the blunt wing leading edge is converted into the oblique shock wave formed by the telescopic pneumatic plate extending out of the rear sharp leading edge.
6. The fairing of claim 1, wherein said first section of said telescoping aerodynamic plate is 100mm in length.
7. Drag reducing device for aircraft according to claim 2, characterized in that the gear unit comprises one driving gear mechanism and three driven gear mechanisms.
8. The fairing as recited in claim 1, wherein said aircraft wing is a mid-leading-edge radius, mid-leading-edge swept-angle airfoil formed of a hypersonic airfoil.
9. Drag reducing device for aircraft according to claim 1, characterized in that the thickness of the telescopic pneumatic plate is 10mm.
10. An aircraft comprising the fairing of any one of claims 1 to 9.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202310227795.9A CN115946842B (en) | 2023-03-10 | 2023-03-10 | Drag reduction device of aircraft and aircraft |
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| Application Number | Priority Date | Filing Date | Title |
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| CN202310227795.9A CN115946842B (en) | 2023-03-10 | 2023-03-10 | Drag reduction device of aircraft and aircraft |
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| CN115946842A true CN115946842A (en) | 2023-04-11 |
| CN115946842B CN115946842B (en) | 2023-05-26 |
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