阅读说明：本技术 一种可柔性变形的后缘变弯度翼肋 (Flexibly deformable trailing edge variable-camber wing rib ) 是由 丁力 于 2020-05-12 设计创作，主要内容包括：本申请提供了一种可柔性变形的后缘变弯度翼肋,属于变体飞机结构设计技术领域,所述翼肋包括多个肋节及连接板,相邻肋节之间通过连接板连接前后连接在一起构成翼肋的翼型外形,其中,每个肋节具有用于与相邻肋节进行柔性连接的柔性连接结构,所述柔性连接结构受到载荷作用时能够产生柔性伸缩变形,使得相邻两个肋节之间产生相对转动,实现后缘翼肋的弯度变化。本申请提供的可柔性变形的后缘变弯度翼肋,通过多个肋节构建出一整体翼肋且肋节间采用柔性连接,可显著提高翼肋缘条的柔性变形量,获得较大的弯度变化量和承载能力。(The application provides a trailing edge variable camber rib that can flexonics belongs to morphing aircraft structural design technical field, the rib includes a plurality of rib festival and connecting plate, links together the airfoil profile appearance that constitutes the rib around connecting through the connecting plate between the adjacent rib festival, and wherein, every rib festival has the flexible connection structure who is used for carrying out flexonics with adjacent rib festival, flexible connection structure can produce flexible deformation when receiving load effect for produce relative rotation between two adjacent rib festival, realize the camber change of trailing edge rib. The utility model provides a but flexible deformation's trailing edge becomes camber rib constructs a whole rib and adopts the flexonics between the rib festival through a plurality of rib festival, can show the flexible deflection who improves the rib border, obtains great camber change amount and bearing capacity.)

1. The utility model provides a flexible trailing edge variable camber rib which can warp, its characterized in that, the rib includes a plurality of rib festival and connecting plate, connects the airfoil profile appearance that constitutes the rib together around connecting through the connecting plate between the adjacent rib festival, wherein, every rib festival has the flexible connection structure who is used for carrying out flexonics with adjacent rib festival, flexible connection structure can produce flexible deformation when receiving the loading effect for produce relative rotation between two adjacent rib festival, realize the camber change of trailing edge rib.

2. The flexibly deformable trailing edge bending rib of claim 1, wherein the web is connected to a chord plane of the rib intermediate the rib sections.

3. The flexibly deformable trailing edge bending rib of claim 1, wherein the flexible connecting structure comprises an outward tooth structure and an inward tooth structure disposed on the rib segment flanges, the outward tooth structure and the inward tooth structure between two adjacent rib segments engaging each other.

4. The flexibly deformable trailing edge bending rib of claim 3, wherein in the outward and/or inward serrations, the number of teeth is not less than 10.

5. The flexibly deformable trailing edge bending rib of claim 4, wherein the thickness of the teeth is less than 1/6 of the rim thickness.

6. The flexibly deformable trailing edge camber rib of claim 1, further comprising a telescoping drive disposed between two adjacent rib sections, wherein the control of rib section camber deflection is achieved by coordinated control.

7. The flexibly deformable trailing edge bending rib of claim 6 wherein the telescopic drive means comprises a hydraulic ram and a linear reciprocating motor.

Technical Field

The application belongs to the technical field of the structural design of a morphing aircraft, and particularly relates to a flexibly deformable trailing edge variable-camber wing rib.

Background

The morphing aircraft is a novel aircraft which can change shape in real time as required during flight so as to maintain the optimal aerodynamic performance throughout the flight. The change of the camber of the trailing edge of the wing affects the lift-drag ratio of the morphing aircraft, the load of the trailing edge area of the wing is relatively small, and the difficulty of realizing the structure is relatively small.

In the rib of the prior art, a large weight penalty is paid when a mechanical structure is adopted, while the load bearing (rigidity) is insufficient when a structure or deformation capability of the elastic material is utilized.

Therefore, a rib structure is needed to solve the contradiction between the large deformation in the surface of the flexible skin and the rigidity outside the surface, the contradiction between the large deformation of the framework and the bearing capacity, and the problems of distributed driving, shape sensing and control.

Disclosure of Invention

The utility model aims at providing a trailing edge bending degree rib that can flexibly deform to solve or alleviate among the prior art wing trailing edge rib can't satisfy the requirement of bearing when obtaining great camber variation, or satisfy the problem that the requirement of bearing can't realize great camber variation yet.

The technical scheme of the application is as follows: the utility model provides a flexible trailing edge variable camber rib, the rib includes a plurality of rib festival and connecting plate, links together the airfoil profile appearance that constitutes the rib through connecting plate front and back between the adjacent rib festival, wherein, every rib festival has the flexible connection structure who is used for carrying out flexonics with adjacent rib festival, flexible connection structure can produce flexible deformation when receiving load effect for produce relative rotation between two adjacent rib festival, realize the camber change of trailing edge rib.

In one embodiment of the application, the web is connected to the chord plane of the rib in the middle of the rib section.

In an embodiment of the present application, the flexible connection structure includes an outward-facing tooth structure and an inward-facing tooth structure disposed on the rib segment, and the outward-facing tooth structure and the inward-facing tooth structure between two adjacent rib segments are engaged with each other.

In an embodiment of the present application, the number of the tooth sheets in the outward tooth structure and/or the inward tooth structure is not less than 10.

In one embodiment of the subject application, the teeth have a thickness less than 1/6 the rim thickness.

In an embodiment of the application, the device is characterized by further comprising a telescopic driving device, wherein the telescopic driving device is arranged between two adjacent rib sections, and the deflection and bending degree of the rib sections are controlled through coordination control.

In one embodiment of the present application, the telescopic driving means includes a hydraulic cylinder and a linear reciprocating motor.

The utility model provides a but flexible deformation's trailing edge becomes camber rib constructs a whole rib and adopts the flexonics between the rib festival through a plurality of rib festival, can show the flexible deflection who improves the rib border, obtains great camber change amount and bearing capacity.

Drawings

In order to more clearly illustrate the technical solutions provided by the present application, the following briefly introduces the accompanying drawings. It is to be expressly understood that the drawings described below are only illustrative of some embodiments of the invention.

FIG. 1 is a schematic view of a typical aircraft wing structure.

FIG. 2 is a schematic view of a trailing edge camber rib of the present application.

FIG. 3 is a schematic view of the connection between adjacent rib sections of the present application.

FIG. 4 is a schematic view of a single rib section of the present application.

Detailed Description

In order to make the implementation objects, technical solutions and advantages of the present application clearer, the technical solutions in the embodiments of the present application will be described in more detail below with reference to the drawings in the embodiments of the present application.

As shown in fig. 1, which is a schematic diagram of a typical aircraft wing mechanism, a main beam, a front wall 1 and a rear wall 2 form a main bearing structure of a wing, a trailing edge rib 3 is installed and arranged at the rear end of the rear wall 2 along the airflow direction, and a skin 4 is laid on the bearing structure to form an aerodynamic surface. The rib 3 in the control surface area 5 needs to provide a large deformation and to carry a large aerodynamic force.

Therefore, the application provides a flexible deformable trailing edge bending rib, the trailing edge bending rib mainly comprises a rib structure forming the rib profile formed by connecting a plurality of sections of rib sections 31 in a front-back manner through connecting plates 32, the first section of rib section 31 is fixedly connected to the rear wall 2 of the wing, the later section of rib section 31 is connected with the previous section of rib section 31, and the connecting point is arranged at the chord plane position of the rib in the middle of each section of rib section 31, so that the later section of rib section 31 can rotate relative to the previous section of rib section 31 and the profile surface of the rib is basically kept not to generate large fluctuation. Flexible connection structures are arranged on the front edge strip and the rear edge strip of each rib section 31, the rear rib section 31 and the front rib section 31 are flexibly connected through the flexible structures, flexible expansion deformation is generated when load is applied, and adjacent rib sections generate relative deflection. The relative deflection of each adjacent rib section is adjusted according to the required camber variation of the trailing edge rib, and then the larger deformation of the rib can be realized.

Fig. 2 shows a trailing edge bending rib comprising 12 rib sections 31 according to an embodiment of the present invention, in which the rib sections in the initial state in the solid line form the rib profile in the normal state, and the broken line forms the deformed rib profile formed by the relative rotation of the rib sections after a force is applied.

It should be noted that, in this embodiment, the rib section of the last 4 sections can be regarded as one section because the overall structure is small, and in the bending deformation, the rib section of the last 4 sections does not rotate relatively, and the bending degree is kept unchanged.

In one embodiment of the present application, the rib section 31 has a shape similar to an i-beam cross-sectional shape. Two adjacent rib sections 31 are connected by a connecting plate 32. The shape of the connecting plate 32 may be similar to a structure with a single lug at one end and two lugs at one end, the single lug end of the connecting plate 32 is fixedly connected (for example, riveting, screwing, welding or the like may be adopted) at the connecting hole of the web of the rear rib section 31, and the lug end of the connecting plate 32 and the single lug of the previous connecting plate 32 are hinged at the connecting hole of the web of the front rib section 31, as shown in fig. 3. Or the two ends of the connecting plate 32 are of double-lug structures, wherein the double-lug structure at the rear side is larger and is fixedly connected with the web plate of the rib section at the rear side, the double-lug structure at the front side is smaller, and the fork lug opening is larger and can clamp the web plate of the rib section at the front end and the double lugs at the rear side.

It should be noted that, depending on the aerodynamic load to be borne by the trailing edge portion of the wing, the thickness of the web of each rib section 31 and the thickness of the connecting plate 32 may be adjusted to suit or satisfy the aerodynamic load to be borne.

In one embodiment of the present application, the flexible connection structure includes an outward-facing tooth structure and an inward-facing tooth structure disposed on the rib segment, and the outward-facing tooth structure and the inward-facing tooth structure between two adjacent rib segments are engaged with each other.

For example, as shown in fig. 4, the single rib section 31 of one embodiment has a structure, where the connection portion of the front end edge of the rib section 31 has a set of outward teeth or plate-like structures 311, the connection portion of the rear end edge of the rib section 31 has a set of inward teeth or plate-like structures 312, the outward teeth-like structures are engaged with the inward teeth-like structures of the front section rib section 31 in a staggered manner, and the inward teeth-like structures are engaged with the outward teeth-like structures of the rear section rib section 31 in a staggered manner.

When the rear section rib section 31 rotates around the connection point of the front section rib section 31, the edge of the front section rib section 31 and the edge of the rear section rib section 31 generate relative displacement, the interlaced and meshed toothed structures bend and deform and mutually press to generate friction between the tooth sheets, and the pressing and friction enable the edge of the front section rib section 31 and the edge of the rear section rib section 31 to realize flexible connection₁The lengths of the front section rib section and the rear section rib section are both (L + L)₁)/2. Meanwhile, the number of the tooth sheets is more than 10. When the front section rib joint strip and the rear section rib joint strip do not have relative displacement, the two groups of tooth sheets are meshed by slight force, the friction force is small at the moment, and the larger the displacement, the larger the friction force is.

It should be noted that the distance between the teeth should be uniform, and the gap between two sets of teeth should be as small as possible to increase the friction force; the two groups of tooth sheets can slide relatively to increase the flexible deformation and the energy absorption effect, but the bending deformation of the tooth sheets is not excessive when the bending deformation is controlled.

In the present application, the length of the blade can be adjusted according to the required movement stroke, or the thickness and surface roughness of the blade can be adjusted according to the working load and friction requirements at the meshing part, or the adjustment can be carried out simultaneously. In one embodiment of the present application, the thickness of the teeth is less than 1/6 the thickness of the rim.

In the present application, the trailing edge bending rib further comprises a telescopic driving device arranged at each two sections of rib joints 31 close to the flanges, so as to assist in bearing load, and the precise control of the bending shape of the trailing edge can be realized through the telescopic driving device.

In some embodiments of the present application, the telescopic drive may be a product or device such as a hydraulic ram or a linear motor.

The application provides a but trailing edge bending degree rib that flexibly deforms constructs a holistic rib and adopts flexonics between the rib festival through a plurality of rib festival, can show the flexible deformation volume that improves the rib border, obtains great bending change volume, and rib trailing edge bending change volume is big, and the smooth and straight of deformation, and structure weight is lighter relatively.

The above description is only for the specific embodiments of the present application, but the scope of the present application is not limited thereto, and any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope of the present application should be covered within the scope of the present application. Therefore, the protection scope of the present application shall be subject to the protection scope of the claims.