CN117864465A - Variable organism structure forward-swept wing unmanned aerial vehicle - Google Patents
Variable organism structure forward-swept wing unmanned aerial vehicle Download PDFInfo
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- CN117864465A CN117864465A CN202410222376.0A CN202410222376A CN117864465A CN 117864465 A CN117864465 A CN 117864465A CN 202410222376 A CN202410222376 A CN 202410222376A CN 117864465 A CN117864465 A CN 117864465A
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Abstract
The invention discloses a forward-swept wing unmanned aerial vehicle with a variable engine body structure, which comprises an aircraft body, wherein the aircraft body adopts a duck-type forward-swept wing layout, the duck-type forward-swept wing layout is that full-motion duck wings are arranged at the front parts of two sides of an aircraft body, foldable forward-swept wing wings are arranged at the rear parts of two sides of the aircraft body, each foldable forward-swept wing comprises an inner wing and an outer wing, the inner wing and the outer wing are connected through a mechanical folding mechanism, an inward folding angle of each outer wing can reach 180 degrees, edge strip wings are arranged between each full-motion duck wing and each foldable forward-swept wing, and foldable full-motion vertical tails are arranged at the two sides of the top surface of the rear part of the aircraft body. The problem that the existing unmanned aerial vehicle is difficult to balance subsonic flight high maneuverability and supersonic flight absolute performance is solved, and the problem of how to park more unmanned aerial vehicles in a limited space is solved.
Description
Technical Field
The invention relates to the field of unmanned aerial vehicles, in particular to a forward-swept wing unmanned aerial vehicle with a variable body structure.
Background
With the rapid improvement of the actual force of the offshore military in China, the unmanned aerial vehicle is increasingly required to land on the ship. The main problems of the current fixed wing unmanned aerial vehicle, namely the warship, are concentrated on two aspects of the overall combat capability of the unmanned aerial vehicle and the carrying quantity of the unmanned aerial vehicle.
The first aspect is that the development of the current fixed-wing unmanned aerial vehicle tends to be specially designed, namely more pneumatic structural design is carried out aiming at a specific task target, and the trade-off between subsonic aeroplane high maneuverability and supersonic speed flight absolute performance is difficult to balance.
The second aspect is that unmanned aerial vehicle combat formation often has a larger number scale than unmanned aerial vehicle combat formation, and is limited by the size of the aircraft carrier and the ship deck, and how to park a larger number in a limited space is a problem that unmanned aerial vehicle boarding must face and need to be solved.
Disclosure of Invention
The invention aims to provide a forward-swept wing unmanned aerial vehicle with a variable engine body structure, which solves the problem that the existing unmanned aerial vehicle is difficult to balance subsonic flight high maneuverability and supersonic flight absolute performance, and solves the problem of how to park more unmanned aerial vehicles in a limited space.
In order to solve the technical problems, the invention adopts the following technical scheme:
the utility model provides a variable organism structure forward-swept wing unmanned aerial vehicle, includes the aircraft body, the aircraft body adopts the forward-swept wing overall arrangement of duck, the forward-swept wing overall arrangement is equipped with full movable duck wing for the front portion of aircraft body fuselage both sides, the rear portion of aircraft body fuselage both sides is equipped with folding forward-swept wing, folding forward-swept wing includes inboard wing and outside wing, link to each other through mechanical folding mechanism between inboard wing and the outside wing, the angle of inwards folding of outside wing can reach 180, still be equipped with the strake wing between full movable duck wing and the folding forward-swept wing, the both sides of aircraft body fuselage rear portion top surface still are equipped with folding full movable vertical tail.
In addition, the scheme not only adopts the folding forward-swept wing, but also adopts the folding full-dynamic vertical fin design, so that the wing span and the fuselage height of the unmanned aerial vehicle can be reduced to the greatest extent through wing surface folding when the ship is parked or stored, and the number scale of the unmanned aerial vehicle on the ship is improved.
In the subsonic speed range, the forward-swept wing aerodynamic design can increase the flying stall attack angle, and the high-motor operational flying capacity of the unmanned aerial vehicle is improved; when in transonic flight or supersonic flight, the forward swept wing can be folded by 180 degrees, the area of the wing can be reduced, the aerodynamic resistance can be further reduced, meanwhile, the problem of torsion and divergence caused by aerodynamic elasticity when the forward swept wing is in high-speed flight is avoided, and the structural strength requirement of the forward swept wing is reduced; the full-moving duck wing is adjusted to a negative attack angle, the center deviation of the lift force of the whole aircraft caused by wing folding is recovered, and the pitching stability of the aircraft is maintained.
The wing and the tail wing are folded in a tilting mode around the shaft, so that compared with a conventional plane inner deformation wing structure, the tilting mechanism is simple and reliable, and the variable angle is larger; under the complete folding state, span size and the aircraft height of unmanned aerial vehicle are all showing and are reducing, effectively promote deck and park with the unmanned aerial vehicle total number of parking in the naval vessel cabin.
As a further preferred aspect of the present invention, the rear end of the fuselage of the aircraft body is free of horizontal tail wings, and the aileron control surface of the foldable forward-swept wing replaces the horizontal tail wing.
As a further preferred aspect of the invention, the power system of the aircraft body employs a lift fan + a vector thrust gas turbine engine.
As a further preferred aspect of the invention, the forward sweep angle of the walker body is 20 °.
As a further preferred aspect of the present invention, the full motion duck wing is adjustable within a range of 10 ° to-20 °, and the area of the single side full motion duck wing is 1.81m2.
As a further preferred aspect of the invention, the two-sided foldable forward swept wing constitutes an M-shaped forward swept wing, the one-sided foldable forward swept wing having an area of 18.6752M 2.
As a further preferred aspect of the invention, the mechanical folding mechanism is located at one third of the wing tip of the foldable forward swept wing.
As a further preferable mode of the invention, the area of a single side of the foldable full-movable vertical fin is 3.172m2, and the foldable full-movable vertical fin is a V-shaped vertical fin.
The unmanned aerial vehicle of above-mentioned scheme has following several mode:
in a conventional flight mode, the forward swept wing and the V-shaped vertical fin are kept at normal positions, and only the low-speed aileron on the outer side of the wing is used.
Transonic or supersonic flight mode, namely 180-degree tilting folding of a forward swept wing, wherein only a high-speed aileron on the inner side of the wing is used, and the duck wing is adjusted to a negative attack angle.
Short take-off or vertical landing mode, in which the lift fan is activated while the engine vector thrust is adjusted.
And in a parking state, the sweepforward wing and the V-shaped vertical double-inclined turning part are overlapped on the upper surface of the wing.
Compared with the prior art, the invention can at least achieve one of the following beneficial effects:
1. the aerodynamic performance of the transonic flying unmanned plane in the full speed range is improved; the aerodynamic layout of the short-distance coupled duck-type sweepforward wings can improve the lift coefficient and maneuverability when flying at a large attack angle, and improve the landing performance of the unmanned aerial vehicle.
2. In the subsonic speed range, the forward-swept wing aerodynamic design can increase the flying stall attack angle, and the high-motor operational flight capacity of the unmanned aerial vehicle is improved.
3. When in transonic flight or supersonic flight, the forward swept wing can be folded by 180 degrees, the area of the wing can be reduced, the aerodynamic resistance can be further reduced, meanwhile, the problem of torsion and divergence caused by aerodynamic elasticity when the forward swept wing is in high-speed flight is avoided, and the structural strength requirement of the forward swept wing is reduced. The full-moving duck wing is adjusted to a negative attack angle, the center deviation of the lift force of the whole aircraft caused by wing folding is recovered, and the pitching stability of the aircraft is maintained.
4. The wing and the tail wing are folded in a tilting mode around the shaft, so that compared with a conventional plane inner deformation wing structure, the tilting mechanism is simple and reliable, and the variable angle is larger; under the complete folding state, span size and the aircraft height of unmanned aerial vehicle are all showing and are reducing, effectively promote deck and park with the unmanned aerial vehicle total number of parking in the naval vessel cabin.
Drawings
FIG. 1 is a schematic view of the structure and aerodynamic layout of the cover plates of the present invention prior to opening.
Fig. 2 is a schematic view of the structure and aerodynamic layout of the cover plates of the present invention after opening.
Fig. 3 is a bottom view of fig. 2 in accordance with the present invention.
Fig. 4 is a schematic view of the structure of the conventional flight mode of the present invention.
Fig. 5 is a schematic diagram of the structure of the transonic or supersonic flight mode of the present invention.
FIG. 6 is a schematic view of the short take-off configuration of the present invention.
Fig. 7 is a schematic view of the vertical drop structure of the present invention.
Fig. 8 is a schematic view of the present invention when parked.
A 2-vector thrust gas turbine engine, a 3-inboard wing; 4-outboard wing; 5-wing leading edge slats (outboard); 7-full-motion duck wings, 8-rib air inlets, 9-lift fan upper hatches, 10-auxiliary air inlets, 11-nose landing gear hatches, 12-nose landing gear, 13-lift fan lower hatches, 14-belly load hatches, 15-fuselage side load hatches, 16-main landing gear, 17-main landing gear hatches.
Detailed Description
For the purpose of making the objects, technical solutions and advantages of the embodiments of the present invention more apparent, the technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present invention, and it is apparent that the described embodiments are some embodiments of the present invention, but not all embodiments. The components of the embodiments of the present invention generally described and illustrated in the figures herein may be arranged and designed in a wide variety of different configurations.
Thus, the following detailed description of the embodiments of the invention, as presented in the figures, is not intended to limit the scope of the invention, as claimed, but is merely representative of selected embodiments of the invention. All other embodiments, based on the embodiments of the invention, which are apparent to those of ordinary skill in the art without inventive faculty, are intended to be within the scope of the invention.
In addition, the embodiments of the present invention and the features of the embodiments may be combined with each other without collision.
It should be noted that: like reference numerals and letters denote like items in the following figures, and thus once an item is defined in one figure, no further definition or explanation thereof is necessary in the following figures.
In the description of the present invention, it should be noted that, directions or positional relationships indicated by terms such as "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer", etc., are directions or positional relationships based on those shown in the drawings, or are directions or positional relationships conventionally put in use of the inventive product, or are directions or positional relationships conventionally understood by those skilled in the art, are merely for convenience of describing the present invention and for simplifying the description, and are not to indicate or imply that the apparatus or element to be referred to must have a specific direction, be constructed and operated in a specific direction, and thus should not be construed as limiting the present invention. Furthermore, the terms "first," "second," and the like, are used merely to distinguish between descriptions and should not be construed as indicating or implying relative importance.
In the description of the present invention, it should also be noted that, unless explicitly specified and limited otherwise, the terms "disposed," "mounted," "connected," and "connected" are to be construed broadly, and may be, for example, fixedly connected, detachably connected, or integrally connected; can be mechanically or electrically connected; can be directly connected or indirectly connected through an intermediate medium, and can be communication between two elements. The specific meaning of the above terms in the present invention will be understood in specific cases by those of ordinary skill in the art.
Specific example 1:
fig. 1, fig. 2, fig. 3, fig. 4, fig. 5, fig. 6, fig. 7 and fig. 8 show a forward-swept wing unmanned aerial vehicle with a variable engine body structure, which comprises an aircraft body, wherein the aircraft body adopts a duck-type forward-swept wing layout, the front parts of two sides of an aircraft body are provided with full-moving duck wings, the rear parts of two sides of the aircraft body are provided with foldable forward-swept wing wings, the foldable forward-swept wing comprises an inner wing and an outer wing, the inner wing and the outer wing are connected through a mechanical folding mechanism, an inward folding angle of the outer wing can reach 180 degrees, side bar wings are further arranged between the full-moving duck wings and the foldable forward-swept wing wings, and two sides of the top surface of the rear part of the aircraft body are further provided with foldable full-moving vertical tails.
In addition, the scheme not only adopts the folding forward-swept wing, but also adopts the folding full-dynamic vertical fin design, so that the wing span and the fuselage height of the unmanned aerial vehicle can be reduced to the greatest extent through wing surface folding when the ship is parked or stored, and the number scale of the unmanned aerial vehicle on the ship is improved.
In the subsonic speed range, the forward-swept wing aerodynamic design can increase the flying stall attack angle, and the high-motor operational flying capacity of the unmanned aerial vehicle is improved; when in transonic flight or supersonic flight, the forward swept wing can be folded by 180 degrees, the area of the wing can be reduced, the aerodynamic resistance can be further reduced, meanwhile, the problem of torsion and divergence caused by aerodynamic elasticity when the forward swept wing is in high-speed flight is avoided, and the structural strength requirement of the forward swept wing is reduced; the full-moving duck wing is adjusted to a negative attack angle, the center deviation of the lift force of the whole aircraft caused by wing folding is recovered, and the pitching stability of the aircraft is maintained.
The wing and the tail wing are folded in a tilting mode around the shaft, so that compared with a conventional plane inner deformation wing structure, the tilting mechanism is simple and reliable, and the variable angle is larger; under the complete folding state, span size and the aircraft height of unmanned aerial vehicle are all showing and are reducing, effectively promote deck and park with the unmanned aerial vehicle total number of parking in the naval vessel cabin.
Specific example 2:
the embodiment further describes the aircraft body based on the specific embodiment 1, wherein the rear end of the aircraft body is free of a horizontal tail wing, and the aileron control surface of the foldable forward-swept wing replaces the horizontal tail wing to act.
Specific example 3:
the embodiment is further described with respect to the specific embodiment 1, wherein the power system of the aircraft body adopts a lift fan and a vector thrust gas turbine engine.
Specific example 4:
this example further illustrates the aircraft body on the basis of embodiment 1, with a forward sweep of 20 °.
Specific example 5:
this embodiment is further described with respect to the full-motion duck wing of embodiment 1, which can be adjusted within the range of 10 ° to-20 °, and the area of the single-side full-motion duck wing is 1.81m2.
Specific example 6:
in this embodiment, the foldable forward-swept wing is further described on the basis of embodiment 1, where the two-sided foldable forward-swept wing forms an M-type forward-swept wing, and the area of the one-sided foldable forward-swept wing is 18.6752M 2.
Specific example 7:
this embodiment is a further illustration of the mechanical folding mechanism on the basis of embodiment 1, which is located at one third of the wing tip of the foldable forward swept wing.
Specific example 8:
the embodiment further illustrates a foldable full-movable vertical fin on the basis of the specific embodiment 1, wherein the area of a single side of the foldable full-movable vertical fin is 3.172m2, and the foldable full-movable vertical fin is a V-shaped vertical fin.
Although the present invention has been described with reference to the foregoing embodiments, it will be apparent to those skilled in the art that modifications may be made to the embodiments described, or equivalents may be substituted for elements thereof, and any modifications, equivalents, improvements and changes may be made without departing from the spirit and principles of the present invention.
Claims (8)
1. The utility model provides a changeable organism structure sweepforward wing unmanned aerial vehicle, includes aircraft body, its characterized in that: the aircraft body adopts the forward-swept wing overall arrangement of duck formula, the forward-swept wing overall arrangement is equipped with full-motion duck wing for the front portion of aircraft body fuselage both sides, the rear portion of aircraft body fuselage both sides is equipped with folding forward-swept wing, folding forward-swept wing includes inboard wing and outside wing, link to each other through mechanical folding mechanism between inboard wing and the outside wing, the angle of inwards folding of outside wing can reach 180, still be equipped with the strake wing between full-motion duck wing and the folding forward-swept wing, the both sides of aircraft body fuselage rear portion top surface still are equipped with folding full-motion vertical fin.
2. The variable airframe structure forward-swept unmanned aerial vehicle of claim 1 wherein: the rear end of the aircraft body is free from horizontal tail wings, and the aileron control surface of the foldable forward-swept wing replaces the action of a horizontal tail wing.
3. The variable airframe structure forward-swept unmanned aerial vehicle of claim 1 wherein: the power system of the aircraft body adopts a lifting fan and a vector thrust gas turbine engine.
4. The variable airframe structure forward-swept unmanned aerial vehicle of claim 1 wherein: the forward sweep angle of the walker body is 20 °.
5. The variable airframe structure forward-swept unmanned aerial vehicle of claim 1 wherein: the full-motion duck wing can be adjusted within the range of 10 degrees to-20 degrees, and the area of the single-side full-motion duck wing is 1.81m < 2 >.
6. The variable airframe structure forward-swept unmanned aerial vehicle of claim 1 wherein: the two-sided foldable forward swept wing forms an M-shaped forward swept wing, and the area of the single-sided foldable forward swept wing is 18.6752M 2.
7. The variable airframe structure forward-swept unmanned aerial vehicle of claim 1 wherein: the mechanical folding mechanism is located at one third of the wing tip of the foldable forward swept wing.
8. The variable airframe structure forward-swept unmanned aerial vehicle of claim 1 wherein: the area of the single side of the foldable full-movable vertical tail is 3.172m2, and the foldable full-movable vertical tail is a V-shaped vertical tail.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202410222376.0A CN117864465A (en) | 2024-02-28 | 2024-02-28 | Variable organism structure forward-swept wing unmanned aerial vehicle |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202410222376.0A CN117864465A (en) | 2024-02-28 | 2024-02-28 | Variable organism structure forward-swept wing unmanned aerial vehicle |
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| Publication Number | Publication Date |
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| CN117864465A true CN117864465A (en) | 2024-04-12 |
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|---|---|---|---|
| CN202410222376.0A Pending CN117864465A (en) | 2024-02-28 | 2024-02-28 | Variable organism structure forward-swept wing unmanned aerial vehicle |
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| CN (1) | CN117864465A (en) |
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- 2024-02-28 CN CN202410222376.0A patent/CN117864465A/en active Pending
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