CN112339987A

CN112339987A - Double-slit flap with flap fixedly connected with additional wing

Info

Publication number: CN112339987A
Application number: CN202011179682.9A
Authority: CN
Inventors: 刘毅
Original assignee: Cetc Wuhu Diamond Aircraft Manufacture Co ltd; Cetc Wuhu General Aviation Industry Technology Research Institute Co ltd
Current assignee: Cetc Wuhu Diamond Aircraft Manufacture Co ltd; Cetc Wuhu General Aviation Industry Technology Research Institute Co ltd
Priority date: 2020-10-29
Filing date: 2020-10-29
Publication date: 2021-02-09
Anticipated expiration: 2040-10-29
Also published as: CN112339987B

Abstract

The invention belongs to the technical field of airplane wings, and particularly relates to a double-slit flap fixedly connected with an additional wing. The wing flap is fixedly connected with the additional wing through a connecting rod, and the fixedly connected additional wing and the fixedly connected flap are integrated to be folded and unfolded under the action of a set of driving connecting mechanism; when the double-slit flap is in a laid-down state, a gap is respectively formed between the main wing and the additional wing and between the additional wing and the flap, so that the high lift effect of the double-slit flap is generated. According to the double-slit flap, the high lift effect of the double-slit flap is realized when the flap is put down through the rigidly connected additional wing-flap structure, meanwhile, the structural complexity of the double-slit flap is kept to be equivalent to that of a single-slit/fullerene flap, and the lift force is improved under the condition of the same structural complexity, so that the area requirements of wings and flaps are reduced, the weight of an airplane is reduced, and the performance of the airplane is improved.

Description

Double-slit flap with flap fixedly connected with additional wing

Technical Field

The invention belongs to the technical field of airplane wings, and particularly relates to a double-slit flap fixedly connected with an additional wing.

Background

The airplane has high flying speed during cruising flight, small required wing area and wing section curvature, and low flying speed during the taking off and landing stage, and large required wing area and wing section curvature. In order to solve the contradictory requirements under the two conditions, the modern aircraft adopts flaps with different complexity, the flaps are retracted during cruising flight and are put down in the taking-off and landing stages to increase the lift force. The main types of trailing edge flap arrangements are shown in fig. 1.

The effect of the flap on increasing lift is measured as the increment Δ CLmax of the maximum lift coefficient produced in the flap-down position relative to the stowed position. In two dimensions, simple and slotted flaps can bring about Δ CLmax of about 0.9, single-slotted flaps Δ CLmax of about 1.3, fuller flaps Δ CLmax of about 1.3 cc/C, double-slotted flaps Δ CLmax of about 1.6 cc/C, and triple-slotted flaps Δ CLmax of about 1.9 cc/C (where C'/C is the ratio of the increase in chord length after the flaps are laid down). The rule is that the more complex the structure and the more wing segments, the larger Δ CLmax is generated.

For a small fixed wing aircraft, a single-slit flap or a fullerene flap with a simpler structural form is usually selected, so that the problem is that the Δ CLmax is smaller, in order to obtain enough lift force in the taking-off and landing stages, the areas of wings and flaps can only be synchronously increased, the structural weight is increased, the cruising flight resistance is increased, and the like.

Disclosure of Invention

The invention aims to provide a double-slit flap fixedly connected with an additional wing.

The technical solution for realizing the purpose of the invention is as follows: a double-slit flap with a flap fixedly connected with an additional wing comprises the additional wing and the flap, wherein the additional wing and the flap are fixedly connected through a connecting rod, and the fixedly connected additional wing and the flap are integrated to be folded and unfolded under the action of a set of driving connecting mechanism; when the double-slit flap is in a laid-down state, a gap is respectively formed between the main wing and the additional wing and between the additional wing and the flap, so that the high lift effect of the double-slit flap is generated.

Further, the additional wing and the flap are fixedly connected through two connecting rods.

Further, when the double-slit flap is in a retracted state, for an airfoil profile with a chord length L of 1000mm, the width L5 of a gap between the additional wing and the flap is 41 +/-1 mm, the horizontal length L3 of the flap is 292 +/-2 mm, the horizontal distance L2 from the front end of the additional wing to the front end of the flap is 104 +/-2 mm, the length L4 of the additional wing is 107 +/-1 mm, and the horizontal distance L1 from the front end of the main wing to the contact point of the additional wing and the main wing is 596 +/-2 mm.

Further, when the double-slit flap is in a 35-degree down state, the distance H between the additional wing and the flap rotating shaft is 218 +/-2 mm, and the distance L6 between the front end of the main wing and the flap rotating shaft is 680 +/-2 mm.

Further, the scaling of the double-slit flap is 0.7-3.0, and the sizes are scaled according to the scaling.

Compared with the prior art, the invention has the remarkable advantages that:

(1) the invention provides a flap scheme which has the lift-increasing effect of a double-slit flap and the structure simplicity similar to a single-slit fullerene flap, achieves the effect of increasing the flap delta CLmax of an airplane at a very low cost, can obviously increase the maximum lift coefficient of the wing profile of the airplane, reduces the requirements of the wing and the flap area, lightens the structural weight and aerodynamic resistance, and improves the airplane performance.

(2) The two wing sections are rigidly connected through the connecting rod and move as a whole, and in the state that the flap is put down, the whole system is a double-slit flap, namely, gaps with optimized design are respectively formed between the main wing and the additional wing and between the additional wing and the flap, so that the high lift effect of the double-slit flap is generated; the additional wing and the flap are rigidly connected, so that the folding and unfolding operation can be realized only by one set of driving and connecting system, the complexity is equivalent to that of a single-slit/fullerene flap, the size of a connecting rod between the additional wing and the flap is small, and the influence on the high lift effect is small.

Drawings

Fig. 1 shows the leading trailing edge flap type of the prior art.

FIG. 2 is a schematic view of a double-slit flap of the present invention shown with the flap laid down.

FIG. 3 is a schematic view of a retracted double-slotted flap of the present invention.

FIG. 4 is a side view of a double-slotted flap of the present invention in a flap stowed position.

FIG. 5 is a side view of a double-slotted flap of the present invention with the flap down at 35.

FIG. 6 is a binary lift characteristic of the double-slotted flap of the present invention.

Description of reference numerals:

1-connecting rod, 2-main wing, 3-additional wing and 4-flap.

Detailed Description

The present invention is described in further detail below with reference to the attached drawing figures.

As shown in fig. 2 and 3, a double-slit flap with a flap fixedly connected with an additional wing comprises an additional wing 3 and a flap 4, wherein the additional wing 3 and the flap 4 are fixedly connected through a connecting rod 1, and the fixedly connected additional wing 3 and the flap 4 are integrated to be retracted under the action of a set of driving connection mechanism; when the double-slit flap is in a laid-down state, a gap is respectively formed between the main wing 2 and the additional wing 3 and between the additional wing 3 and the flap 4, so that the high lift effect of the double-slit flap is generated.

The additional wing 3 and the flap 4 are fixedly connected by two connecting rods 1.

As shown in FIGS. 4 and 5, when the double-slit flap is in a retracted state, for an airfoil shape with a chord length L of 1000mm, the width L5 of the gap between the additional wing 3 and the flap 4 is 41 + -1 mm, the horizontal length L3 of the flap 4 is 292 + -2 mm, the horizontal distance L2 from the front end of the additional wing 3 to the front end of the flap 4 is 104 + -2 mm, the length L4 of the additional wing 3 is 107 + -1 mm, and the horizontal distance L1 from the front end of the main wing 2 to the contact point of the additional wing 3 and the main wing 2 is 596 + -2 mm.

The flap-lowering profile is obtained by rotation through 35 ° about the pivot axis, the profile diagram and the position of the pivot axis being shown in fig. 5. When the double-slit flap is laid down at 35 degrees, the distance H between the additional wing 3 and the flap rotating shaft is 218 +/-2 mm, and the distance L6 between the front end of the main wing 2 and the flap rotating shaft is 680 +/-2 mm.

The airfoil profile and the double-slit flap can be used in a scalable mode, the scaling ratio is 0.7-3.0, and the sizes are scaled according to the scaling ratio.

The lift characteristics of a double-slit flap, a single-slit flap and a no-flap state in which the flap is fixedly connected with the additional wing are researched by adopting a numerical calculation method, and the result is shown in fig. 6. The peak value of the lift coefficient curve in the graph is the maximum lift coefficient CLmax, and it can be seen that the delta CLmax obtained by the single-slit flap is 1.3, the delta CLmax obtained by the double-slit flap fixedly connected with the additional wing is 1.8, the lift ratio is 38%, and the data is also relatively consistent with the theoretical value.

The double-slit flap with the flap fixedly connected with the additional wing has the main advantages that through the rigidly connected additional wing-flap structure, the high lift effect of the double-slit flap is realized when the flap is put down, meanwhile, the structural complexity of the double-slit flap is kept equivalent to that of a single-slit/fullerene flap, and the lift force is improved under the condition of the same structural complexity, so that the area requirements of the wing and the flap are reduced, the weight of the airplane is reduced, and the performance of the airplane is improved.

Claims

1. The double-slit flap with the flap fixedly connected with the additional wing is characterized by comprising the additional wing (3) and the flap (4), wherein the additional wing (3) and the flap (4) are fixedly connected through a connecting rod (1), and the fixedly connected additional wing (3) and the flap (4) are integrally folded and unfolded under the action of a set of driving connecting mechanism; when the double-slit flap is in a laid-down state, a gap is respectively formed between the main wing (2) and the additional wing (3) and between the additional wing (3) and the flap (4), so that the high lift effect of the double-slit flap is generated.

2. The double-slit flap of claim 1, characterized in that the additional wing (3) and the flap (4) are fixedly connected by two connecting rods (1).

3. The double-slit flap as claimed in claim 1, characterized in that, for an airfoil profile with a chord length L of 1000mm, the width L5 of the gap between the additional wing (3) and the flap (4) is 41 ± 1mm, the horizontal length L3 of the flap (4) is 292 ± 2mm, the horizontal distance L2 from the front end of the additional wing (3) to the front end of the flap (4) is 104 ± 2mm, the length L4 of the additional wing (3) is 107 ± 1mm, and the horizontal distance L1 from the front end of the main wing (2) to the contact point of the additional wing (3) with the main wing (2) is 596 ± 2mm when the double-slit flap is in the retracted state.

4. The double-slit flap as claimed in claim 3, characterized in that the distance H of the additional wing (3) from the flap pivot is 218 ± 2mm and the distance L6 of the front end of the main wing (2) from the flap pivot is 680 ± 2mm when the double-slit flap is in the lowered 35 °.

5. The double-slit flap of claim 4 wherein the double-slit flap is used at a scale of 0.7-3.0.