CN203283375U

Movatterモバイル変換

Info

Publication number: CN203283375U
Application number: CN2013201900319U
Authority: CN
Inventors: 赵嘉珩
Original assignee: Individual
Current assignee: Individual
Priority date: 2013-04-16
Filing date: 2013-04-16
Publication date: 2013-11-13
Anticipated expiration: 2023-04-16

Abstract

Translated fromChinese

本实用新型采用的技术方案提供一种飞行器的机翼布局结构，该飞行器包括机身、机头、主翼和垂直尾翼，所述飞行器还包括翼尖小翼、后翼和鸭翼，其中所述主翼的端部设有翼尖小翼，后翼与主翼通过连接板连接，所述后翼与垂直尾翼联接，机身前端耦合鸭翼；本实用新型的有益效果是采用连翼布局前后翼联结，显著提高机翼强度和刚度，其中后部机翼除了提供一部分升力外，还承担一部分机翼的弯曲力矩，可以减少机翼的尺寸和重量；本实用新型设计成大展弦比，提高升力线斜率和最大升力系数，在给定翼展和重量的情况下，可降低诱导阻力。

The technical scheme adopted by the utility model provides a wing layout structure of an aircraft, the aircraft includes a fuselage, a nose, a main wing and a vertical tail, and the aircraft also includes a winglet, a rear wing and a canard, wherein the The end of the main wing is provided with winglets, the rear wing is connected to the main wing through a connecting plate, the rear wing is connected to the vertical empennage, and the front end of the fuselage is coupled to the canard; , significantly improve the strength and stiffness of the wing, wherein the rear wing not only provides a part of the lift, but also bears a part of the bending moment of the wing, which can reduce the size and weight of the wing; the utility model is designed with a large aspect ratio to improve the lift The slope of the line and the maximum lift coefficient reduce the induced drag for a given span and weight.

Description

Translated fromChinese

一种飞行器的机翼布局结构A kind of wing layout structure of aircraft

技术领域:Technical field:

本实用新型属于飞行器设计领域,特别是一种涉及各类飞行器的机翼布局结构。The utility model belongs to the field of aircraft design, in particular to a wing layout structure related to various aircrafts.

背景技术：Background technique:

中国大型运输机一直受之于无法生产大推力航空发动机与高强度复合材料（比如T1000碳纤维），目前我国没有可靠的运输机进行远程搜救。众所周知，2001年4月1日上午，中国发现美国一架EP-3型侦察机飞抵中国海南岛东南海域上空，中国派出两架F-8歼击机进行监视。9时7分，中国飞机在海南岛东南104公里处正常飞行时，美机突然转向，其机头和左翼同一架中国飞机相撞，造成中国飞机坠毁，驾驶员王伟跳伞后牺牲。此次事件的主要原因不仅是因为我国战斗机实力较差（相比于苏联）、做驱逐机动经验不足，但最重要的是我国没有可靠的运输机进行远程搜救。 China's large transport aircraft have been suffering from the inability to produce high-thrust aero-engines and high-strength composite materials (such as T1000 carbon fiber). At present, my country does not have reliable transport aircraft for long-range search and rescue. As we all know, on the morning of April 1, 2001, China spotted an American EP-3 reconnaissance plane flying over the waters southeast of China's Hainan Island, and China sent two F-8 fighter planes to monitor it. At 9:07, when the Chinese plane was flying normally 104 kilometers southeast of Hainan Island, the American plane turned suddenly. Its nose and left wing collided with the Chinese plane, causing the Chinese plane to crash. The pilot, Wang Wei, died after parachuting. The main reason for this incident is not only that our country's fighter jets are weaker (compared to the Soviet Union) and have insufficient experience in expulsion maneuvers, but the most important thing is that our country does not have reliable transport aircraft for long-range search and rescue.

早在20世纪20年代，就有人设计出了一种将纵向串列式机翼连接在一起的钻石形“连翼”布局。到70年代，洛克希德和波音等公司分别提出了多种“连翼”和“盒式飞机”概念，并希望将其用于潜在的商业运输机和军用加油机的方案。但至今无已服役的军用或民用大型运输机（主要原因是由于资金有限、暂无需求、技术难度较大等）。As early as the 1920s, a diamond-shaped "wing-wing" arrangement was devised that connected longitudinal tandem wings together. By the 1970s, companies such as Lockheed and Boeing proposed a variety of "connected wing" and "box aircraft" concepts, and hoped to use them for potential commercial transport aircraft and military tanker programs. But so far there is no military or civilian large transport aircraft in service (mainly due to limited funds, no demand, technical difficulty, etc.).

为了解决我国没有可靠的运输机进行远程搜救问题，我们计划了几种机翼布局方式：1、飞翼布局，其优点是隐形、气动效率高等，缺点是造价高昂、无过多创新、飞控复杂；2、可变翼布局，其优点是适合不同速度、飞行品质好，缺点是过于复杂、造价过于高昂；3、连翼布局，其优点是高机翼强度和刚度、前后翼共同承担一部分机翼的弯曲力矩、小机翼的尺寸和重量、大展弦比、高升力线斜率、最大升力系数、低诱导阻力，缺点是飞控复杂。在综合考虑各个方案有缺点的基础上，我们采用连翼布局，现有制造能力的基础上，由于连翼布局带来的结构强度高（相比同样的展弦比飞机）、诱导阻力小，可在现有条件下进行生产。In order to solve the problem of long-distance search and rescue without reliable transport aircraft in our country, we have planned several wing layout methods: 1. The flying wing layout has the advantages of invisibility and high aerodynamic efficiency, but the disadvantages are high cost, no too much innovation, and complicated flight control ; 2. The variable wing layout has the advantages of being suitable for different speeds and good flight quality. The disadvantage is that it is too complicated and the cost is too high; 3. The wing layout has the advantages of high wing strength and stiffness, and the front and rear wings share a part of the aircraft. The bending moment of the wing, the size and weight of the small wing, the large aspect ratio, the high lift line slope, the maximum lift coefficient, and the low induced drag, the disadvantage is that the flight control is complicated. On the basis of comprehensive consideration of the shortcomings of each scheme, we adopt the wing layout. On the basis of the existing manufacturing capacity, due to the high structural strength brought by the wing layout (compared to the same aspect ratio aircraft), the induced resistance is small, Can be produced under existing conditions.

发明内容：Invention content:

本实用新型为了克服现有飞行器机翼设计的不足，设计一种新的机翼布局具有高的机翼强度和高度。In order to overcome the deficiencies in the existing aircraft wing design, the utility model designs a new wing layout with high wing strength and height.

本实用新型采用的技术方案提供一种飞行器的机翼布局结构，该飞行器包括机身、机头、主翼和垂直尾翼，所述飞行器还包括翼尖小翼、后翼和鸭翼，其中所述主翼的端部设有翼尖小翼，后翼与主翼通过连接板连接，所述后翼与垂直尾翼联接，机身前端耦合鸭翼；The technical scheme adopted by the utility model provides a wing layout structure of an aircraft, the aircraft includes a fuselage, a nose, a main wing and a vertical tail, and the aircraft also includes a winglet, a rear wing and a canard, wherein the The end of the main wing is provided with winglets, the rear wing is connected to the main wing through a connecting plate, the rear wing is connected to the vertical empennage, and the front end of the fuselage is coupled to the canard;

进一步地，所述翼尖小翼上装有外侧阻尼板，在转向时协助连接板的内侧阻尼板联动；Further, the winglet is equipped with an outer damping plate, which assists the linkage of the inner damping plate of the connecting plate when turning;

进一步地，所述后翼前掠含下反角并装有襟翼，所述下反角的角度为1-2度；Further, the rear wing is swept forward with a dihedral angle and is equipped with flaps, and the angle of the anhedral angle is 1-2 degrees;

进一步地，所述后翼与主翼所述的连接位置在主翼上距离机身的70%位置处；Further, the connection position between the rear wing and the main wing is at 70% of the main wing from the fuselage;

进一步地，所述外侧阻尼板和外侧阻尼板由航空铝合金构成；Further, the outer damping plate and the outer damping plate are made of aviation aluminum alloy;

进一步地，所述后翼与垂直尾翼距离机身在1/3尾翼高度处；Further, the rear wing and the vertical tail are at 1/3 of the height of the tail from the fuselage;

进一步地，所述主翼后掠上反，装有双襟开襟翼，前缘可调缝翼；Further, the main wing is swept up and reversed, equipped with double flaps and adjustable leading edge slats;

进一步地，所述主翼的展弦比为8-12。Further, the aspect ratio of the main wing is 8-12.

本实用新型的有益效果是采用连翼布局前后翼联结，显著提高机翼强度和刚度，其中后部机翼除了提供一部分升力外，还承担一部分机翼的弯曲力矩，可以减少机翼的尺寸和重量；本实用新型设计成大展弦比，提高升力线斜率和最大升力系数，在给定翼展和重量的情况下，可降低诱导阻力。The beneficial effect of the utility model is that the front and rear wings are connected by the connecting wing layout, which significantly improves the strength and stiffness of the wing. In addition to providing a part of the lift, the rear wing also bears a part of the bending moment of the wing, which can reduce the size and size of the wing. Weight; the utility model is designed with a large aspect ratio, which improves the slope of the lift line and the maximum lift coefficient, and can reduce the induced resistance under the condition of given wingspan and weight.

附图说明：Description of drawings:

图1是本实用新型的总体结构图；Fig. 1 is the general structural diagram of the present utility model;

图2是本实用新型的局部结构放大示意图。Fig. 2 is an enlarged schematic diagram of a partial structure of the present invention.

具体实施方式：Detailed ways:

以下内容结合说明书附图对本实用新型的具体实施方式作详细说明：The following content describes in detail the specific implementation of the present utility model in conjunction with the accompanying drawings:

参见附图1-2，飞行器包括机身、机头、主翼1和垂直尾翼5，其中主翼1的端部装设有翼尖小翼2，翼尖小翼2上装有外侧阻尼板7，该外侧阻尼板7由航空铝合金构成，在转向时协助连接板4的内侧阻尼板8联动；后翼3前掠含下反角，该角度为1-2度，装有襟翼(图中未标出)，与主翼1的连接位置在主翼1上离机身的70%位置处，后翼3与主翼1通过连接板4连接，其中连接板4装有内侧阻尼板8，转弯时与外侧阻尼板7联动，外侧阻尼板也由航空铝合金构成。Referring to accompanying drawing 1-2, aircraft comprises fuselage, nose,main wing 1 and vertical empennage 5, wherein the end ofmain wing 1 is equipped with winglet 2, andouter damping plate 7 is housed on winglet 2, this Theouter damping plate 7 is made of aviation aluminum alloy, and assists the linkage of theinner damping plate 8 of the connecting plate 4 when turning; marked), the connection position with themain wing 1 is at the 70% position on themain wing 1 from the fuselage, therear wing 3 is connected with themain wing 1 through the connecting plate 4, wherein the connecting plate 4 is equipped with aninner damping plate 8, and when turning Thedamping plate 7 is linked, and the outer damping plate is also made of aviation aluminum alloy.

后翼3与垂直尾翼5联接，连接处与机身有一定距离，约在1/3尾翼高度处，具有能够减小前后机翼的气流干扰的效果。Therear wing 3 is connected with the vertical empennage 5, and the joint has a certain distance from the fuselage, about 1/3 of the height of the empennage, which has the effect of reducing the airflow interference of the front and rear wings.

主翼1后掠上反，装有双襟开襟翼，前缘可调缝翼，具有较大展弦比，展弦比为8-12。Themain wing 1 is swept up and reversed, equipped with double flaps, adjustable leading edge slats, has a large aspect ratio, and the aspect ratio is 8-12.

机身前端远距耦合鸭翼6，起飞与降落时打开，飞行时收回，其活动范围为与水平基线呈+35至-10度。The front end of the fuselage is remotely coupled withthecanard 6 , which is opened during take-off and landing and retracted during flight, and its range of motion is +35 to -10 degrees from the horizontal baseline.

由于本实用新型采用连翼布局前后翼联结，显著提高机翼强度和刚度，其中后部机翼除了提供一部分升力外，还承担一部分机翼的弯曲力矩，可以减少机翼的尺寸和重量；本实用新型设计成大展弦比，提高升力线斜率和最大升力系数，在给定翼展和重量的情况下，可降低诱导阻力。Because the utility model adopts the connection of the front and rear wings of the wing layout, the strength and stiffness of the wing are significantly improved, and the rear wing not only provides a part of the lift, but also bears a part of the bending moment of the wing, which can reduce the size and weight of the wing; The utility model is designed with a large aspect ratio, increases the slope of the lift line and the maximum lift coefficient, and can reduce the induced drag under the given wingspan and weight.

采用连翼-鸭翼布局的飞机在正常飞行状态下并没有多少优越性，但是当飞机需做大强度的机动如上仰、小半径盘旋等动作时，飞机的前翼和主翼上都会产生强大的涡流，两股涡流之间的相互耦合和增强，产生比常规布局更强的升力。The aircraft with the wing-canard layout does not have many advantages in normal flight conditions, but when the aircraft needs to perform high-intensity maneuvers such as pitching up and circling with a small radius, powerful forces will be generated on the front and main wings of the aircraft. The vortex, the mutual coupling and enhancement between the two vortices, produces a stronger lift than the conventional layout.

在大迎角状态下，鸭翼只需要减少产生升力即可产生低头力矩，从而有效保证大迎角下抑制过度抬头的可控性。鸭翼可有效加强飞机的机动性和短距离起飞着陆性能。由于可控舵面较多，便于实现直接力控制。In the state of high angle of attack, the canard only needs to reduce the lift to generate the nose-down moment, thus effectively ensuring the controllability of suppressing excessive nose-up at high angle of attack. The canard can effectively enhance the maneuverability and short-distance take-off and landing performance of the aircraft. Since there are many controllable rudder surfaces, it is convenient to realize direct force control.

以上内容是结合具体实施方式对本实用新型所作的进一步详细说明，不能认定本实用新型的具体实施只局限于这些说明。对于本实用新型所属技术领域的普通技术人员来说，在不脱离本实用新型构思的前提下，还可以做出若干简单推演或替换，都应当视为属于本实用新型的保护范围。The above content is a further detailed description of the utility model in combination with specific implementation methods, and it cannot be determined that the specific implementation of the utility model is only limited to these descriptions. For a person of ordinary skill in the technical field to which the utility model belongs, without departing from the concept of the utility model, some simple deduction or substitutions can also be made, which should be regarded as belonging to the protection scope of the utility model.

Claims

1. the wing configurations structure of an aircraft, this aircraft comprises fuselage, head, main wing (1) and vertical tail (5), it is characterized in that, described aircraft also comprises winglet (2), rear wing (3) and canard (6), the end of wherein said main wing (1) is provided with winglet (2), rear wing (3) is connected by connecting panel (4) with main wing (1), and described rear wing (3) connects with vertical tail (5), front fuselage coupling canard (6).

2. layout structure according to claim 1, is characterized in that, outside damping panel (7) is housed on described winglet (2), assists inboard damping panel (8) interlock of connecting panel (4) when turning to.

3. layout structure according to claim 1, is characterized in that, described rear wing (3) sweepforward contains inverted diherdral and wing flap is housed, and the angle of described inverted diherdral is the 1-2 degree.

4. layout structure according to claim 1, is characterized in that, described rear wing (3) and the described connection location of main wing are in upper 70% position apart from fuselage of main wing (1).

5. layout structure according to claim 2, is characterized in that, described outside damping panel (7) and outside damping panel (8) consist of aerolite.

6. layout structure according to claim 1, is characterized in that, described rear wing (3) and vertical tail (5) apart from fuselage at 1/3 empennage At The Height.

7. layout structure according to claim 1, is characterized in that, and is anti-in described main wing (1) sweepback, double breasted is housed opens wing flap, the adjustable slat of leading edge.

8. layout structure according to claim 7, is characterized in that, the aspect ratio of described main wing (1) is 8-12.