CN104875873A - Aircraft wing with novel aerodynamic layout and aircraft using same - Google Patents

Abstract

The invention provides an aircraft wing with a new type of aerodynamic layout and an aircraft using the wing. The aircraft includes a fuselage and upper and lower wing sections which are fixedly connected to the fuselage and respectively extend outward along the span direction. The wingtips of the wing section and the wingtips of the lower wing section are fixedly connected in series along the chord direction to form a joint wingtip section so that the upper and lower wing sections and the fuselage form a double triangle structure, and the wing The chord direction is defined as the fore-aft direction in which the trailing edge of the wingtip located on the forward side meets the leading edge of the wingtip located on the rear side. According to the modern "near-coupling theory", it can be seen that the wingtip located on the front side will cause disturbance to the airflow received by the rear wingtip, and reduce the drag effect of the airflow disturbance on the rear wingtip, so that the front wingtip The generated wingtip vortex is continuously digested by the rear wingtip, and the wingtip vortex generated by the front wingtip will act as a lift force on the rear wingtip, thereby increasing the generation of this triangular-shaped joint wing The effective wingspan over which lift acts.

Description

Aircraft wing with novel aerodynamic layout and aircraft using the same

technical field

The present invention relates to an aircraft wing with a novel aerodynamic layout and an aircraft using the wing.

Background technique

Light or ultra-light aircraft are not only "friendly to the people", but also have a wide range of applications. Because the cost of this type of aircraft is relatively low, the production is relatively easy, and the development cycle is short, so this type of small aircraft has rich aerodynamic shape, exquisite structural design, and more novel technical manifestations than large aircraft.

In order to obtain a larger lift-to-drag ratio, light aircraft usually adopt a wing structure with a large aspect ratio, and the wing area is usually large so that the span of a single wing is large. However, the mechanical strength structure of such an overly slender wing has low efficiency, which is not conducive to transmitting the lift of the wing to the fuselage, and this thin and large-aspect-ratio wing must have high strength to withstand the huge lift Torque, which makes the wings very difficult to make and not long-lived. The structure of the old-fashioned biplane is relatively simple. It obtains greater lift by using two layers of wings arranged up and down. This kind of biplane has greater lift, stable low-altitude performance, good low-speed flight effect, and easy manipulation. It is widely used in aerial photography, aerial spraying of pesticides and other work. However, this kind of biplane usually adds support or pillars between the upper and lower wings. Although the strength of the wing is increased, it also greatly increases the flight resistance, and the biplane has more than one pair of monoplanes than the monoplane. The wings also add additional induced drag from the extra wingtip vortices.

The existing structure of an aircraft that adopts the aerodynamic layout of wings is shown in Fig. 1 to Fig. 3, which includes a fuselage 300 extending along the front-to-rear direction, and the fuselage 300 is provided with upper wing sections 100 and 100 respectively extending along the span direction. The lower wing section 200, the outer end wingtips of the upper and lower wing sections are connected to each other and vertically overlapped, thus avoiding the double induction caused by the extra wing of the conventional biplane. The problem of resistance, but there are practical problems in the use of this joint wing, because when a wing has an object within a range smaller than the chord length in the vertical direction, it will definitely disturb the flow field of the wing. The above-mentioned up and down The interference formed between the overlapping upper and lower wing sections will form a chaotic vortex, and this part of the chaotic vortex will offset the wing section surrounded by the vortex, and this part of the wing section will no longer produce effective lift, thereby reducing Small effective wingspan to produce effective lift.

In the Chinese utility model patent application specification CN2122834U, the authorization announcement number discloses a kind of biplane, which is to set the end wings at the wingtips of the two pairs of wings of the traditional biplane, and the two wings are connected by the end wings. The wingtips of the two-layer wings are connected and fixed. The wingtips of the upper and lower wings of this biplane are vertically overlapped, and the upper wing, lower wing, fuselage and end plates form a double-port box structure as a whole. The end wing staggers the wingtips of the upper and lower wings by a certain distance vertically to reduce the flow field interference between the upper and lower wing sections, and at the same time, the end wing reduces the induced drag generated by the wingtip vortex. However, the overall resistance of the joint wing layout of this double-port box structure is relatively large, which reduces the lift-to-drag ratio, resulting in a small effective wingspan for the joint wing to play a role in lift. Moreover, the wing layout of the above-mentioned double-port box structure has poor lateral stability due to the large vertical end plates on the side, and is prone to lateral disturbance accidents when encountering large lateral airflows.

Contents of the invention

The present invention provides an aircraft wing to solve the technical problem that the effective wingspan of the joint-wing layout is relatively small due to the large overall resistance of the aerodynamic layout of the joint-wing aircraft in the prior art; at the same time, the present invention also provides a Wing of the aircraft.

The technical scheme of the aircraft wing provided by the present invention is: an aircraft wing, comprising upper and lower wing segments extending outwards respectively along the span direction, the wing tip and the lower wing of the upper wing segment The wingtips of the section are staggered and connected in series along the chord direction to form a joint wingtip section so that the upper and lower wing sections can form a double triangle structure with the fuselage of the aircraft, and the chord direction is defined as the front-to-back direction. The trailing edge of the front wingtip is in contact with the leading edge of the rear wingtip.

The outer side of the combined wing tip section along the span direction is fixedly connected with a swept-back triangular outer wing, and the chord direction at the root of the swept-back triangular outer wing is consistent with the wing tip of the upper and lower wing sections. The chord direction is the same.

A connecting end plate is fixedly connected to the outer side of the combined wing tip section along the span direction, and the swept-back triangular outer wing is fixedly connected to the combined wing tip section through the connecting end plate.

The upper wing section is located in front of the lower wing section, and the wing shape of the upper and lower wing sections adopts one of the following schemes:

(1) The above-mentioned upper and lower wing sections are rectangular wings of equal chord length, and the chord lengths of the upper and lower wing sections are equal;

(2) The above-mentioned upper and lower wing sections are both trapezoidal wings whose wing root chord length is greater than the wing tip chord length;

(3) The above-mentioned upper and lower wing sections are both trapezoidal wings whose wing root chord length is smaller than the wing tip chord length.

The upper wing section is located in front of the lower wing section, and the upper wing section is a penetrating wing section arranged on the upper part of the fuselage along the span direction. The two penetrating wing sections arranged along the span direction The end wingtip is the wingtip of the upper wing section, and the lower wing section includes two split wing sections correspondingly distributed on both sides of the fuselage along the span direction, and the two split wing sections The outer end wingtip arranged along the span direction of the section is the wingtip of the lower wing section, and the inner end wing root arranged along the spanwise direction of the two-split wing section is used to be fixedly connected to the fuselage lower part.

The through-wing section and the two split wing sections are rectangular wings of equal chord length, and the positions of the through-wing section corresponding to the inner end wing roots of the two split wing sections along the chord direction The distance from the inner end wing root of the two split wing sections is greater than the chord length of the through wing section.

The technical scheme of the aircraft using the above-mentioned wings provided by the present invention is: an aircraft, including a fuselage and upper and lower wing sections that are fixedly connected to the fuselage and extend outwards respectively along the span direction. The wingtips of the upper wing section and the wingtips of the lower wing section are staggered and fixed in series along the chord direction to form a joint wingtip section so that the upper and lower wing sections and the fuselage form a double triangle structure. The chord direction is defined as the fore-aft direction in which the trailing edge of the wingtip on the front side meets the leading edge of the wingtip on the rear side.

The outer side of the combined wing tip section along the span direction is fixedly connected with a swept-back triangular outer wing, and the chord direction at the root of the swept-back triangular outer wing is consistent with the wing tip of the upper and lower wing sections. The chord direction is the same.

The upper wing section is located in front of the lower wing section, and the upper wing section is a penetrating wing section arranged on the upper part of the fuselage along the span direction. The two penetrating wing sections arranged along the span direction The end wingtip is the wingtip of the upper wing section, and the lower wing section includes two split wing sections correspondingly distributed on both sides of the fuselage along the span direction, and the two split wing sections The outer end wingtip arranged along the span direction of the section is the wingtip of the lower wing section, and the inner end wing root arranged along the spanwise direction of the two-split wing section is used to be fixedly connected to the fuselage lower part.

The through wing section and the two split wing sections are rectangular wings of equal chord length, and the vertical distance between the through wing section and the inner end wing roots of the two split wing sections is greater than that of the through wing section. The chord length of the wing segment.

The beneficial effects of the present invention are: the wingtip of the upper wing section of the aircraft wing provided by the present invention and the wingtip of the lower wing section are staggered in series along the chord direction and fixedly connected to form a joint wingtip section, like this, the upper and lower wing sections The lower wing section and the fuselage of the aircraft form a double triangular structure. This double triangular structure makes the overall stability of the wing better, and the disturbance of the lateral airflow reduces its influence. The chord direction is misaligned and connected in series. According to the "near coupling theory", the wingtip located on the front side will cause favorable interference to the airflow received by the rear wingtip, and the wingtip vortex generated by the front wingtip is The rear wingtips are continuously digested, and the two wingtips of the upper and lower wing sections only generate the wingtip vortex of one pair of wingtips, thereby reducing the induced drag.

Further, a swept-back triangular outer wing is fixedly connected to the outer side of the joint wing tip section along the span direction, and this outer wing can effectively absorb the wing tip vortex generated by the joint wing tip section and reduce the induced drag, so that this Compared with the existing wingtips stacked up and down in parallel, the combined wing with the wingtip series structure, that is, the combined wingtip section, increases the effective span of the lift effect, and becomes a high-lift high-strength structure with very little induced drag, and , the wing root chord length of this kind of swept-back triangular outer wing is larger, which can play a larger lift contribution.

Further, the outer wing and the united wingtip section are fixed together through the connecting end plate, which is convenient for assembly and replacement.

Further, the upper wing section is a through-wing section arranged through the upper part of the fuselage along the span direction, so that the influence of the fuselage on the wing flow field can be minimized and the lift generation efficiency of the wing can be improved.

Further, the vertical distance between the through wing section and the inner end wing roots of the two split wing sections is greater than the chord length of the through wing section, and the distance between the two can be set to reduce the distance between the through machine The aerodynamic interference between the lower surface of the wing section, ie the upper wing section, and the upper surface of the two-part wing section, ie the lower wing section.

Description of drawings

Fig. 1 is the structural representation of the aircraft with united wing in the prior art;

Fig. 2 is a top view of the aircraft shown in Fig. 1;

Fig. 3 is a side view of the aircraft shown in Fig. 1;

Fig. 4 is a schematic structural view of an embodiment of an aircraft provided by the present invention;

Figure 5 is a top view of the aircraft shown in Figure 4;

Fig. 6 is a side view of the aircraft shown in Fig. 4;

Fig. 7 is a schematic structural view of the wing in Fig. 4;

Figure 8 is a top view of the wing shown in Figure 7;

Figure 9 is a side view of the wing shown in Figure 7;

Fig. 10 is a schematic structural view of Embodiment 2 of the wing provided by the present invention;

Figure 11 is a top view of the wing shown in Figure 10;

Figure 12 is a side view of the wing shown in Figure 10;

Fig. 13 is a schematic structural view of Embodiment 3 of the wing provided by the present invention;

Figure 14 is a top view of the wing shown in Figure 13;

Figure 15 is a side view of the airfoil shown in Figure 13 .

Detailed ways

As shown in Fig. 4 to Fig. 9, a kind of embodiment of aircraft, in this embodiment, aircraft comprises fuselage 1, is provided with wing on fuselage 1, is different from the wing in the prior art: in this embodiment The wing comprises the combined wing with upper and lower wing sections and the outer wing 4 arranged on the outside of the combined wing along the span direction, the upper wing section 2 and the lower wing section 3 of the combined wing are respectively Extend outward along the span direction, and the upper wing section 2 is located in front of the lower wing section 3, and the upper wing section 1 is a through-wing section for being arranged on the upper part of the fuselage along the span direction. The wingtips at both ends of the section arranged along the span direction are the wingtips of the upper wing section 2, while the lower wing section 3 includes two wings correspondingly distributed on both sides of the fuselage along the span direction. Two split wing sections, the inner end wing roots arranged along the span direction of the two split wing sections are used to be fixedly connected to the lower part of the fuselage, and the outer wings arranged along the span direction of the two split wing sections The end wingtip is the wingtip of the lower wing section 3. In this embodiment, the wingtip of the upper wing section 2 and the wingtip of the lower wing section 3 are fixedly connected in series along the chord direction. Combine the wing tip section 5 so that the upper and lower wing sections can form a double triangle structure with the fuselage of the aircraft, and the chord direction is defined as the front and rear direction, behind the wing tip of the upper wing section 2 on the front side The edge adjoins the leading edge of the wingtip of the lower wing section 3 located on the rear side.

In this embodiment, the outer wing 4 is a swept-back triangular outer wing, and the outer wing 4 is fixedly connected to the outer side of the combined wing tip section 5 along the span direction through the connecting end plate, and the connecting end plate is fixedly connected to the combined wing tip section 5 , the direction of the chord at the root of the swept-back triangular outer wing is consistent with the direction of the chord at the tip of the upper and lower wing sections. Moreover, the outer wing 4 is a foldable outer wing that can be folded when the aircraft is stored to reduce the space occupied by the aircraft.

In this embodiment, the through wing section as the upper wing section 2 and the two split wing sections as the lower wing section 3 are rectangular wings with equal chord length, and the through wing section along the chord direction The distance between the position corresponding to the inner end wing root of the two split wing sections and the inner end wing root of the two split wing sections is greater than the chord length of the through wing section.

In order to reduce the aerodynamic interference between the lower surface of the upper wing section and the upper surface of the lower wing section, the distance between the through wing section and the inner end wing roots of the two split wing sections in the vertical direction is greater than that of the through machine The chord length of the wing segment.

In the aircraft provided by this embodiment, the upper and lower wing sections form a joint wing structure, and the wingtips of the upper and lower wing sections are dislocated and connected in series along the chord direction to form a combined wingtip section, so that the upper wing section The wingtip vortex generated by the wingtip is intercepted by the wingtip of the lower wing section. According to the modern near-coupling design theory, the wingtip vortex generated by the wingtip on the front side will generate an upward lift force on the rear wingtip. The effective wingspan for providing lift of this joint wing structure is improved. Moreover, the swept-back triangular outer wing set on the outer side of the joint wing structure can absorb the wingtip vortex generated by the joint wing tip section and reduce the induced drag, making this joint wing structure with the joint wing tip section an induced drag Minimal high-lift high-strength construction.

The aircraft wing in this embodiment is the embodiment 1 of the wing, and two other aircraft wing embodiments of different wing shapes are introduced below.

Example 2:

As shown in Figures 10 to 12, this embodiment provides an aircraft wing, the main difference between this aircraft wing and the above-mentioned aircraft embodiments is the wing shape of the wing, the combined aircraft in this embodiment The first upper wing section 21 and the first lower wing section 31 of the wing are all trapezoidal wings whose chord length is greater than the chord length of the wingtip. Although the first upper wing section 21 also runs through the wing section here, However, the wing root 210 of the first upper wing section 21 is located in the middle of the through wing section. At this time, the chord of the combined wing tip section formed by the dislocation and serial connection of the outer ends of the upper and lower wing sections is less than the difference between the wing root chord length of the upper wing section and the wing root chord length of the lower wing section. And, the joint wing structure of this structure is matched with the first outer wing 41 that area is smaller again, is suitable for transportation task.

Example 3:

As shown in Figures 13 to 15, this embodiment provides an aircraft wing, the main difference between this aircraft wing and the above-mentioned aircraft embodiments is the wing shape of the wing, the combined aircraft in this embodiment The second upper wing section 22 and the second lower wing section 32 of the wing are all trapezoidal wings whose chord length of the wing root is less than the chord length of the wingtip, although the second upper wing section 22 also runs through the wing section here, However, the wing root 220 of the second upper wing section 22 is located in the middle of the through wing section. At this time, the chord of the joint wing tip section formed by the dislocation and serial connection of the outer ends of the upper and lower wing sections is greater than the difference between the wing root chord length of the upper wing section and the wing root chord length of the lower wing section. And, the joint-wing structure of this structure is matched with the larger second outer wing 42 of area again, is suitable for high mobility task.

It can be seen from the above embodiments that by appropriately changing the wing shape of the upper and lower wing sections and adding an outer wing with a suitable area, the biplane can be adapted to different performance requirements.

In the above-mentioned embodiment, the upper wing section is located in front of the lower wing section. In other embodiments, the upper wing section can also be arranged behind the lower wing section, as long as the wing tips of the upper and lower wing sections are edged The chord direction is misplaced and connected in series to form a joint wing tip section.

In the embodiments of the above-mentioned aircraft and wing, the outer wings are arranged horizontally, and in other embodiments, the outer wings can also be upturned.

In the above-mentioned embodiment, the connecting end plate and the outer wing are arranged on the outside of the joint wing tip section. Of course, in other embodiments, the outer wing can also be removed, and only the joint wing tip section is retained, and the wing tip located at the front can also be used. The generated lift vortex generates a lift effect on the rear wingtip to increase the effective lift wing length of the entire joint wing structure.

Claims (10)

1. an aircraft wing, comprise respectively along the outward extending upper and lower wing section of spanwise, it is characterized in that: the wingtip of described top wing section and the wingtip chordwise dislocation tandem of lower wing section are connected and form associating wingtip section to make the fuselage formation ditrigon structure of described upper and lower wing Duan Keyu aircraft, chordwise is defined as fore-and-aft direction, and the trailing edge being positioned at the wingtip of front side connects with the leading edge of the wingtip being positioned at rear side.

2. aircraft wing according to claim 1, it is characterized in that: the outside along spanwise of described associating wingtip section is fixed with swept-back triangle outer wing, the chordwise at the wing root place of swept-back triangle outer wing is consistent with the chordwise of the wingtip of described upper and lower wing section.

3. aircraft wing according to claim 2, is characterized in that: the outside along spanwise of described associating wingtip section is fixed with connection end plate, and described swept-back triangle outer wing is connected with described wingtip section of combining by connecting end plate.

4. the aircraft wing according to claim 1 or 2 or 3, is characterized in that: described top wing section is positioned at the front of lower wing section, and the wing shapes of described upper and lower wing section adopt following wherein a kind of scheme:

(1) RECTANGULAR WINGS of the chord lengths such as the upper and lower wing section described in is, and the chord length of upper and lower wing section is equal;

(2) the upper and lower wing section described in is wing root chord and grows up in the tapered airfoil of wingtip chord length;

(3) the upper and lower wing section described in is the tapered airfoil that wing root chord length is less than wingtip chord length.

5. the aircraft wing according to claim 1 or 2 or 3, it is characterized in that: described top wing section is positioned at the front of lower wing section, top wing section is for along the through through wing section being arranged in back of spanwise, the two ends wingtip along spanwise layout of through wing section is the wingtip of described top wing section, lower wing section comprises two the split air conditioner wing panels being distributed in described fuselage both sides along described spanwise correspondence, the outer end wingtip along spanwise layout of two split air conditioner wing panels is the wingtip of described lower wing section, the inner wing root along spanwise layout of two split air conditioner wing panels is used for being fixedly connected at described underbelly.

6. aircraft wing according to claim 5, it is characterized in that: described through wing section and two split air conditioner wing panels such as to be at the RECTANGULAR WINGS of chord length, the inner wing root of through wing section and two split air conditioner wing panels is greater than the chord length of described through wing section in the spacing on vertical up and down.

7. an aircraft, comprise fuselage and to be connected on fuselage and respectively along the outward extending upper and lower wing section of spanwise, it is characterized in that: the wingtip chordwise dislocation tandem of the wingtip of described top wing section and lower wing section is connected and forms associating wingtip section and form ditrigon structure to make described upper and lower wing section and described fuselage, chordwise is defined as fore-and-aft direction, and the trailing edge being positioned at the wingtip of front side connects with the leading edge of the wingtip being positioned at rear side.

8. aircraft according to claim 7, it is characterized in that: the outside along spanwise of described associating wingtip section is fixed with swept-back triangle outer wing, the chordwise at the wing root place of swept-back triangle outer wing is consistent with the chordwise of the wingtip of described upper and lower wing section.

9. the aircraft according to claim 7 or 8, it is characterized in that: described top wing section is positioned at the front of lower wing section, top wing section is for along the through through wing section being arranged in back of spanwise, the two ends wingtip along spanwise layout of through wing section is the wingtip of described top wing section, lower wing section comprises two the split air conditioner wing panels being distributed in described fuselage both sides along described spanwise correspondence, the outer end wingtip along spanwise layout of two split air conditioner wing panels is the wingtip of described lower wing section, the inner wing root along spanwise layout of two split air conditioner wing panels is used for being fixedly connected at described underbelly.

10. aircraft according to claim 9, it is characterized in that: described through wing section and two split air conditioner wing panels such as to be at the RECTANGULAR WINGS of chord length, the spacing of the inner wing root of the position that the chordwise of through wing section is corresponding with the inner wing root of two split air conditioner wing panels and described two split air conditioner wing panels is greater than the chord length of described through wing section.