Airplane with lower single wing and supporting wings

Abstract

The aircraft comprises a fuselage, the lower single wing, the supporting wing and an empennage, the lower single wing is arranged on the front portion of the fuselage, the supporting wing is arranged on the rear portion of the top of the fuselage, and the empennage is arranged at the tail position of the fuselage; the lower single wing comprises a left outer wing, a right outer wing and a central wing, and the central wing is arranged at the lower part of the fuselage and is connected with the left outer wing and the right outer wing; the supporting wings comprise a left supporting wing, a right supporting wing and a central supporting wing, the supporting wings are arranged behind the top of the fuselage corresponding to the central wing, the left supporting wing is connected with the left outer wing, the right supporting wing is connected with the right outer wing, and the left supporting wing and the right supporting wing are simultaneously connected with the central supporting wing. According to the invention, the configuration, layout form and other aspects of the aircraft are improved, and the functions and effects of increasing the aspect ratio of the aircraft wing, improving the lift-drag ratio of the aircraft and reducing the fuel consumption rate of the aircraft can be realized.

Description

Technical Field

[0001] The invention belongs to the technical field of aircraft structures, and in particular relates to an aircraft with a lower single wing and a supporting wing. Background Art

[0002] At present, in order to reduce the fuel consumption of aircraft, in addition to reducing the fuel consumption rate of the engine, major adjustments have been made to the aircraft configuration, and a relatively systematic study has been carried out on the aerodynamic, structural, power and other characteristics of the strut-wing configuration aircraft. The configuration is an upper wing and a strut wing, and the tail adopts a T-shaped vertical tail. The existing layout has the following disadvantages: there are aerodynamic interference problems between the upper wing and the T-shaped vertical tail, which will affect the aircraft's controllability and safety when the aircraft flies at high speed and maneuvers at a large angle of attack; the lower strut solution causes the wing position to be higher than the conventional configuration to form an upper wing, and the main landing gear space will be limited by the fairing space formed by the lower strut, which is not conducive to the design of the main landing gear; the maintenance of the upper wing and the engine is more difficult than that of the current conventional configuration aircraft. Summary of the invention

[0003] In order to overcome the problems existing in the prior art, the present invention provides an aircraft with a lower single wing and a supporting wing, so as to overcome the existing defects.

[0004] An aircraft with a lower wing and a supporting wing, the aircraft comprising: a fuselage, a lower wing, a supporting wing and a tail wing, wherein the lower wing is arranged at the front of the fuselage, the supporting wing is arranged at the rear of the top of the fuselage, and the tail wing is arranged at the tail position of the fuselage;

[0005] The lower monoplane includes a left outer wing, a right outer wing and a central wing, wherein the central wing is arranged at the lower part of the fuselage and connects the left outer wing and the right outer wing;

[0006] The supporting wing includes a left supporting wing, a right supporting wing and a central supporting wing. The supporting wing is arranged at the rear of the top of the fuselage corresponding to the position of the central wing, and the left supporting wing is connected to the left outer wing, the right supporting wing is connected to the right outer wing, and the left supporting wing and the right supporting wing are connected to the central supporting wing at the same time.

[0007] According to the aspects and any possible implementations described above, there is further provided an implementation, wherein the left outer wing, the right outer wing and the center wing are centrally symmetrical structures relative to the fuselage.

[0008] According to the aspects described above and any possible implementation method, an implementation method is further provided, wherein a left wing box is provided on the left outer wing, a right wing box is provided on the right outer wing, the tail of the left supporting wing is connected to the left outer wing through the left wing box, and the tail of the right supporting wing is connected to the right outer wing through the right wing box.

[0009] According to the aspects described above and any possible implementation, an implementation is further provided, wherein the aircraft also includes a wing tip, a left wing tip is arranged at the end of a left outer wing away from the fuselage, and a right wing tip is arranged at the end of a right outer wing away from the fuselage.

[0010] According to the above aspects and any possible implementation, an implementation is further provided, wherein the tail is a structure of a low horizontal tail and a vertical tail, or a structure of a high horizontal tail and a vertical tail.

[0011] According to the aspects described above and any possible implementation, an implementation is further provided, wherein the left power unit is arranged at a middle position between the wing root of the left outer wing and the left wing box, and the right power unit is arranged at a middle position between the wing root of the right outer wing and the right wing box.

[0012] According to the above aspects and any possible implementation manner, there is further provided an implementation manner, wherein the aircraft further includes a fairing, and the central support wing is arranged inside the fairing.

[0013] According to the aspects and any possible implementations described above, an implementation is further provided, wherein the fuselage, the left supporting wing and the left outer wing form a left triangle, and the fuselage, the right supporting wing and the right outer wing form a right triangle.

[0014] According to the above aspects and any possible implementation, there is further provided an implementation, wherein the left supporting wing and the right supporting wing are made of metal material.

[0015] According to the aspects described above and any possible implementation, an implementation is further provided, wherein the left wing box is arranged at a position between one-third and three-quarters of the distance from the root of the left outer wing to the wing tip, and the right wing box is arranged at a position between one-third and three-quarters of the distance from the root of the right outer wing to the wing tip.

[0016] Compared with the prior art, the present invention has the following beneficial effects:

[0017] The aircraft of the present invention comprises: a fuselage, a lower wing, a supporting wing and a tail wing, wherein the lower wing is arranged at the front of the fuselage, the supporting wing is arranged at the top rear of the fuselage, and the tail wing is arranged at the tail position of the fuselage; the lower wing comprises a left outer wing, a right outer wing and a central wing, the central wing is arranged at the lower part of the fuselage, and is connected to the left outer wing and the right outer wing at the same time; the supporting wing comprises a left supporting wing, a right supporting wing and a central supporting wing, the supporting wing is arranged at the top rear of the fuselage corresponding to the central wing, and the left supporting wing is connected to the left outer wing, the right supporting wing is connected to the right outer wing, and the left supporting wing and the right supporting wing are connected to the central supporting wing at the same time. The purpose of the supporting wing is to reduce the spanwise bending moment load of the wing root of the aircraft, which is conducive to increasing the aspect ratio of the wing, while reducing the thickness of the wing root and the wing box of the wing, which is conducive to improving the lift-to-drag ratio of the aircraft. The supporting wing, the inner section of the wing and the fuselage together form an effective triangle, which is conducive to improving the stability of the wing under load. The present invention improves the configuration and layout of the aircraft, and can achieve the functions and effects of increasing the aspect ratio of the aircraft wing, improving the lift-to-drag ratio of the aircraft, and reducing the fuel consumption rate of the aircraft. BRIEF DESCRIPTION OF THE DRAWINGS

[0018] Figure 1 It is a schematic diagram of a low-tail aircraft of the present invention;

[0019] Figure 2 It is a front view schematic diagram of a low-tail aircraft of the present invention;

[0020] Figure 3 It is a schematic diagram of a T-tail aircraft of the present invention;

[0021] Figure 4 It is a front view schematic diagram of a T-tail aircraft of the present invention. DETAILED DESCRIPTION

[0022] In order to better understand the technical solution of the present invention, the content of the present invention includes but is not limited to the specific implementation methods described below, and similar technologies and methods should be considered to be within the scope of protection of the present invention. In order to make the technical problems, technical solutions and advantages to be solved by the present invention clearer, the following will be described in detail with reference to the accompanying drawings and specific embodiments.

[0023] It should be clear that the embodiments described in the present invention are only part of the embodiments of the present invention, rather than all the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0024] The present invention provides an aircraft with a lower wing and a supporting wing, the aircraft comprising: a fuselage, a lower wing, a supporting wing and a tail wing, wherein the lower wing is arranged at the front of the fuselage, the supporting wing is arranged at the rear of the top of the fuselage, and the tail wing is arranged at the tail position of the fuselage;

[0025] The lower monoplane includes a left outer wing, a right outer wing and a central wing, wherein the central wing is arranged at the lower part of the fuselage and connects the left outer wing and the right outer wing;

[0026] The support wing includes a left support wing, a right support wing and a central support wing. The support wing is arranged at the rear of the top of the fuselage corresponding to the position of the central wing, and the left support wing is connected to the left outer wing, the right support wing is connected to the right outer wing, and the left support wing and the right support wing are simultaneously connected to the central support wing.

[0027] Furthermore, the left outer wing, the right outer wing and the central wing are centrally symmetrical structures relative to the fuselage.

[0028] Furthermore, a left wing box is provided on the left outer wing, a right wing box is provided on the right outer wing, the tail of the left supporting wing is connected to the left outer wing through the left wing box, and the tail of the right supporting wing is connected to the right outer wing through the right wing box.

[0029] Furthermore, the aircraft also includes a wing tip, wherein a left wing tip is arranged at an end of a left outer wing away from the fuselage, and a right wing tip is arranged at an end of a right outer wing away from the fuselage.

[0030] Furthermore, the tail is a structure of a low horizontal tail and a vertical tail, or a structure of a high horizontal tail and a vertical tail.

[0031] Furthermore, the left power unit is arranged at a middle position between the wing root of the left outer wing and the left wing box, and the right power unit is arranged at a middle position between the wing root of the right outer wing and the right wing box.

[0032] Furthermore, the aircraft also includes a fairing, and the central support wing is arranged inside the fairing.

[0033] Furthermore, the fuselage, the left supporting wing and the left outer wing form a left triangle, and the fuselage, the right supporting wing and the right outer wing form a right triangle.

[0034] Furthermore, the left supporting wing and the right supporting wing are made of metal material.

[0035] Furthermore, the left wing box is arranged at a position between one third and three quarters of the distance from the root of the left outer wing to the wing tip, and the right wing box is arranged at a position between one third and three quarters of the distance from the root of the right outer wing to the wing tip.

[0036] Specifically, if Figure 1 , 3As shown, the present invention provides an aircraft configuration of an upper supporting wing and a lower monoplane, the aircraft having a fuselage 1, a left outer wing 11, a right outer wing 4, a right supporting wing 5, a left supporting wing 10 and a tail wing. The left outer wing 11, the right outer wing 4 and the central wing are arranged at the lower part of the fuselage, respectively connected to the left outer wing 11 and the right outer wing 4, the left outer wing 11, the right outer wing 4 and the central wing together form a lower monoplane, wherein the left outer wing 11, the right outer wing 4 and the central wing are a left-right symmetrical structure, and the left outer wing 11 and the right outer wing 4 are collectively referred to as wings. The left supporting wing 10, the right supporting wing 5 and the central supporting wing are arranged at the rear of the top of the fuselage corresponding to the position of the central wing. The left and right supporting wings are respectively fixedly connected to the left outer wing and the right outer wing, so that the left and right outer wings bend upward during the flight of the aircraft to prevent the left and right outer wings from being deformed too much and damaged, and to improve the supporting stiffness of the left and right outer wings, and to provide conditions for increasing the wingspan of the left and right outer wings. The central supporting wing is similar to the central wing, and is used to balance the loads of the left and right supporting wings. The shape of the supporting wing is similar to the shape of the wing surface, and can provide lift and reduce the wing area. The aircraft also includes wing tips, the left wing tip is arranged at the end of the left outer wing 11 away from the fuselage, and the right wing tip is arranged at the end of the right outer wing 4 away from the fuselage. The central supporting wing is located inside the supporting wing fairing 6, and the left supporting wing 10 and the right supporting wing 5 are located on the upper part of the lower wing, one end of which is connected to the top of the fuselage, and the other end is connected to a position of one-third to three-quarters of the wing span length. This position is the one-third to three-quarters position from the root of the wing to the wing tip connected to the wing, that is, the one-third to three-quarters position from the root of the left outer wing to the left wing tip connected thereto and the one-third to three-quarters position from the root of the right outer wing to the right wing tip connected thereto. The length of the wingspan is the distance between the apex of the left wing tip and the apex of the right wing tip. The above connection method limits the length of the left and right support wings. This length will not cause the aircraft to become unstable. If the support wings are too long, they are prone to instability, and if they are too short, the effect is not obvious. The left and right support wings are mainly under pressure. In order to withstand the pressure, the left and right support wings are made of metal. Generally, the underwing support is just for tension, and composite materials are more suitable. However, the present invention adopts metal materials for the left and right supporting wings, which has a greater weight advantage than composite materials and can meet the pressure situation. The left and right outer wings are respectively provided with left and right wing boxes at this position. The tail of the left supporting wing 10 is connected to the left wing box at this position, and then fixedly connected to the left outer wing 11. The tail of the right supporting wing 5 is connected to the right wing box at this position, and then fixedly connected to the right outer wing 4. All of the above are fixed static connections. The purpose of setting the left and right supporting wings 5 ​​and 10 is to reduce the spanwise bending moment load of the aircraft wing root, which is beneficial to increase the aspect ratio of the wing. At the same time, the thickness of the wing root and the left and right wing boxes is reduced, which is beneficial to improve the lift-drag ratio of the aircraft, thereby reducing the fuel consumption rate of the aircraft. If the supporting wings are not provided on the upper part of the aircraft, the bending resistance of the left and right outer wings mainly depends on the wall thickness of the upper and lower wall panels of the wing root. Now the supporting wings are provided for the pull-up operation, and the thickness of the left and right outer wing wall panels is greatly reduced because most of the load is borne by the supporting wings.The engine is located between the roots of the left and right outer wings and the connection point of the supporting wing (i.e., the location of the left and right wing boxes). The engine is part of the power unit, providing power for the aircraft while unloading the upward bending load of the wing. The supporting wing and the inner section of the wing, that is, the wing part extending from the connection point between the wing and the supporting wing to the fuselage, together with the fuselage, form an effective triangle, that is, the left triangle formed by the wing part extending from the connection point between the fuselage, the left supporting wing and the left outer wing and the left supporting wing to the fuselage, and the right triangle formed by the wing part extending from the connection point between the fuselage, the right supporting wing and the right outer wing and the right supporting wing to the fuselage. This double triangle shape design is conducive to improving the stability of the wing load.

[0037] Furthermore, if Figure 2 and Figure 4 As shown, the tail includes two configurations, one tail is a low horizontal tail and a vertical tail (i.e. a low horizontal tail); the other is a T-type tail layout, i.e. a high horizontal tail and a vertical tail (i.e. a high horizontal tail).

[0038] When an aircraft with an upper support, lower single wing and low horizontal tail configuration flies in the airflow, both the wing and the supporting wing can provide a certain amount of lift. Compared with the traditional configuration aircraft, the supporting wing provides a certain amount of lift, which is conducive to reducing the outer wing area of ​​the wing. This tail is used to ensure the visibility and maintainability of the tail. Compared with the T-shaped vertical tail, the low position makes it easier to observe and maintain. For the horizontal tail affected by the supporting wing, the wake of the wing and the supporting wing will affect the aerodynamic performance of the horizontal tail and the vertical tail. The main reason is that the airflow is more chaotic after passing through the wing and the supporting wing. The balance requirements of the aircraft can be met by slightly increasing the tail area or span; when a T-shaped tail with an upper support and lower single wing is used, the T-shaped horizontal tail can avoid the influence of the wake of the upper support and the lower single wing.

[0039] Further, there are inner flaps 14, outer flaps 15 and ailerons 16 inside the trailing edge of the wing, and a wing tip or winglet 17 is connected to the edge of the wing. The aileron 16 includes an inner aileron and an outer aileron. When the wing span exceeds the airport limit, the airport's operating requirements can be met by folding the wing. The folding wing is set at other positions except the connection between the supporting wing and the wing. There are two forms of forming the folding wing. When the wing span is short and does not encroach on the aileron, the folding wing tip 17 is sufficient, the supporting wing is connected to the wing box on the wing, and the folding position is set in the wing area except the position of the wing box; when the folding wing span is large and encroaches on the aileron 16, the aileron can be cut, and the folding position is set between the inner aileron and the outer aileron. The folding wing formed after folding assumes the function of the outer aileron, and the outer aileron is integrated into the folding wing when folding. When the folding wing is unfolded, the outer aileron on the folding wing can provide a rolling function.

[0040] The wing of the aircraft of the present invention is a lower monoplane, and an upper supporting wing connected to the wing is arranged on the fuselage. This arrangement increases the aspect ratio and wingspan of the wing. When the wingspan exceeds the airport limit, the operation requirements of the airport can be met by adding folding wingtips.

[0041] like Figure 1 , Figure 2 , Figure 3 and Figure 4 As shown, the power unit 2, 13 is located in the middle of the wing root and the left and right wing boxes, providing power to the aircraft while unloading the wing upward bending load. The left and right support wings 10, 5, the inner section of the wing and the fuselage together form an effective triangle, which is conducive to improving the stability of the wing load, and at the same time ensures that the power unit 2, 13 is located at the lower part of the lower wing, which facilitates the maintenance and replacement of the power unit 2, 13.

[0042] The terms used in the embodiments of the present invention are only for the purpose of describing specific embodiments, and are not intended to limit the present invention. The singular forms "a", "said" and "the" used in the embodiments of the present invention and the appended claims are also intended to include plural forms, unless the context clearly indicates other meanings.

[0043] The above description shows and describes several preferred embodiments of the present invention, but as mentioned above, it should be understood that the present invention is not limited to the form disclosed herein, and should not be regarded as excluding other embodiments, but can be used in various other combinations, modifications and environments, and can be modified within the scope of the application concept described herein through the above teachings or the technology or knowledge of the relevant field. The changes and modifications made by those skilled in the art shall not depart from the spirit and scope of the present invention, and shall be within the scope of protection of the claims attached to the present invention.

Claims

1. An aircraft having a lower monoplane wing and a supporting wing, characterized in that: The aircraft comprises: a fuselage, a lower wing, a supporting wing and a tail wing, wherein the lower wing is arranged at the front of the fuselage, the supporting wing is arranged at the rear of the top of the fuselage, and the tail wing is arranged at the tail position of the fuselage; The lower monoplane includes a left outer wing, a right outer wing and a central wing, wherein the central wing is arranged at the lower part of the fuselage and connects the left outer wing and the right outer wing; The supporting wing includes a left supporting wing, a right supporting wing and a central supporting wing. The supporting wing is arranged at the rear of the top of the fuselage corresponding to the position of the central wing, and the left supporting wing is connected to the left outer wing, the right supporting wing is connected to the right outer wing, and the left supporting wing and the right supporting wing are connected to the central supporting wing at the same time.

2. The aircraft according to claim 1, characterized in that The left outer wing, the right outer wing and the central wing are centrally symmetrical structures relative to the fuselage.

3. The aircraft according to claim 2, characterized in that The left outer wing is provided with a left wing box, the right outer wing is provided with a right wing box, the tail of the left supporting wing is connected to the left outer wing through the left wing box, and the tail of the right supporting wing is connected to the right outer wing through the right wing box.

4. The aircraft according to claim 1, characterized in that The aircraft further comprises wing tips, wherein a left wing tip is arranged at an end of a left outer wing away from the fuselage, and a right wing tip is arranged at an end of a right outer wing away from the fuselage.

5. The aircraft according to claim 1, characterized in that The tail wing is a structure of a low horizontal tail and a vertical tail, or a structure of a high horizontal tail and a vertical tail.

6. The aircraft according to claim 3, characterized in that The aircraft also includes a power unit, wherein the left power unit is arranged at a middle position between the wing root of the left outer wing and the left wing box, and the right power unit is arranged at a middle position between the wing root of the right outer wing and the right wing box.

7. The aircraft according to claim 1, characterized in that The aircraft further comprises a fairing, wherein the central support wing is arranged inside the fairing.

8. The aircraft according to claim 1, characterized in that The fuselage, the left supporting wing and the left outer wing form a left triangle, and the fuselage, the right supporting wing and the right outer wing form a right triangle.

9. The aircraft according to claim 6, characterized in that The left supporting wing and the right supporting wing are made of metal material.

10. The aircraft according to claim 4, characterized in that The left wing box is arranged at a position between one third and three quarters of the distance from the root of the left outer wing to the wing tip, and the right wing box is arranged at a position between one third and three quarters of the distance from the root of the right outer wing to the wing tip.

Images