阅读说明：本技术 具有变形反馈的变弯度机翼结构 (Variable camber wing structure with deformation feedback ) 是由 谢长川 孙萌 冒森 安朝 孟杨 杨澜 于 2019-11-01 设计创作，主要内容包括：本发明提供了一种具有变形反馈的变弯度机翼结构,该结构共分成共分为四个结构段,包括机翼前缘结构段、机翼中部结构段、机翼中后部结构段以及机翼后缘结构段。各个结构段之间通过转轴进行前后连接,并通过与转轴相连的舵机实现机翼结构弯度的变化。在各机翼结构段中分别设置了角度传感器,可与飞机上的舵机控制系统共同组成一套完整的机翼变形反馈控制系统。该结构可根据不同的飞行条件改变自身形状和结构布局,从而改善飞行器的气动特性和飞行性能,同时可实时观察结构的变形情况,针对实际飞行状态对机翼弯度进行相应的调节。(The invention provides a variable camber wing structure with deformation feedback, which is divided into four structural sections, including a wing leading edge structural section, a wing middle and rear structural section and a wing trailing edge structural section. The structural sections are connected front and back through rotating shafts, and the change of wing structural bending degree is realized through steering engines connected with the rotating shafts. The angle sensors are respectively arranged in each wing structure section, and can form a set of complete wing deformation feedback control system together with a steering engine control system on the airplane. The structure can change the shape and the structural layout of the structure according to different flight conditions, thereby improving the aerodynamic characteristics and the flight performance of the aircraft, simultaneously observing the deformation condition of the structure in real time, and correspondingly adjusting the camber of the wing according to the actual flight state.)

1. A inflected wing structure with distortion feedback, comprising:

the wing structure section comprises a wing leading edge structure section (1) from the leading edge to the trailing edge of the wing along the chord direction, a wing middle structure section (2), a wing middle and rear structure section (3) and a wing trailing edge structure section (4),

the rotating mechanism is arranged on the longitudinal walls (5) of the wing middle structure section (2), the wing middle and rear structure section (3) and the wing rear edge structure section (4) and is used for connecting the adjacent wing structure sections,

wherein: the wing leading edge structural section (1), the wing middle structural section (2), the wing middle and rear structural section (3) and the wing trailing edge structural section (4) respectively comprise wing box structures,

the wing box structure comprises a longitudinal wall (5), wing ribs (6) and a mask (7),

the rotating mechanism comprises a driving rotating shaft (8), a steering engine (9) and an angle sensor (10)

The rotating shaft (8) is connected with a reinforced wing rib (14) on the adjacent wing structure to realize the connection between the rotating mechanism and the adjacent wing structure section,

an angle sensor (10) is coupled with the rotating shaft (8) through a driving wheel (12), so that the actual rotating angle of the steering engine is determined according to the data of the sensor (10) and the driving proportion of the driving wheel (12), the feedback and the adjustment of the wing camber are realized,

the variable camber wing structure further comprises:

the steering engine wing ribs (15) are arranged between the longitudinal walls (5) in the structural section, the positions of the steering engine wing ribs (15) are determined according to the position relations among the angle sensor (10), the driving wheel (12) and the rotating shaft (8), so that the steering engine (9) is fixed in the wing structural section,

a steering engine (9) mounted on the steering engine wing ribs (15),

a skin (16) is mounted at the gap between the wing structure sections for maintaining a good aerodynamic profile.

2. The method of claim 1 for controlling the camber feedback of a wing structure having a camber-changed wing structure with a deformation feedback, comprising:

the steering engine (9) receives an electric signal of the external expected camber of the given wing,

the steering engine (9) is used for driving the rotating shaft (8) to drive the reinforcing wing ribs (14) to rotate, so that the wing structure sections connected with the reinforcing wing ribs realize the rotating function,

the steering engine (9) drives the angle sensor (10) to rotate, the angle sensor (10) reads the rotation angle of the steering engine (9), converts the rotation angle into a corresponding electric signal and transmits the corresponding electric signal to the flight control device, and therefore a set of complete angle feedback system is formed.

3. The method of claim 2, comprising:

three rotating mechanisms for connecting the wing leading edge structure section (1) with the wing middle structure section (2), the wing middle structure section (2) with the wing middle and rear structure section (3) and the wing middle and rear structure section (3) with the wing trailing edge structure section (4) can work independently, angle sensors (10) in the rotating mechanisms form independent feedback devices, and finally, the change of the bending degree of the whole wing structure and the feedback control of the bending degree are achieved.

Technical Field

The invention relates to a variable camber wing structure with deformation feedback, and belongs to the technical field of aviation products.

Background

The aircraft wing camber changing technology can adjust wing camber in real time to improve flight efficiency so as to adapt to complex and changeable task environments, and is considered to be one of future aviation technology research directions. The existing camber change design at home and abroad mainly adopts a flexible mechanism, piezoelectric ceramics, memory alloy and other novel functional materials and a driving mechanism to realize the function of variable camber of the wing. However, the above-mentioned techniques still have many problems in practical application, such as the technology of the compliant mechanism is not mature enough, the driving force provided by the piezoelectric ceramic is small, and the deformation efficiency of the memory alloy is low due to the heat dissipation problem of the structure. Rigid mechanisms are the first choice for current wing camber design from the standpoint of technical maturity and reliability.

The existing variable camber wing generally lacks real-time shape deformation detection and feedback, and only a camber change driving structure is designed, and the system is an open-loop control system. The wing steering engines are designed to have unchanged deformation effect after being subjected to pneumatic load, and the actual conditions are quite different, so that the wing camber cannot be accurately adjusted according to the flight state and the flight conditions. Therefore, in order to ensure higher precision and reduce the influence of external disturbance and system parameter change on the system, a corresponding angle sensor is configured in the variable camber wing to form a complete deformation feedback control system.

Disclosure of Invention

Aiming at the defects in the prior art, the invention provides a wing structure with variable camber and a feedback adjusting device, which can adjust the camber of the wing according to different flight conditions so as to improve the lift-drag ratio and the maneuverability of an airplane and perform real-time feedback and corresponding adjustment on the camber of the wing.

The invention provides a technical scheme of a variable camber wing structure with deformation feedback regulation, which mainly comprises the following technical measures: the wing structure is divided into four structural sections from the front edge to the rear edge along the chord direction, and the four structural sections comprise a wing front edge structural section, a wing middle rear structural section and a wing rear edge structural section. Each wing structure section is a wing box structure composed of longitudinal walls, wing ribs, a mask and the like, and the main beam is arranged in the wing leading edge structure section.

The wing structure sections are connected through the connecting pieces between the wing ribs at the part of the connecting part, compared with the common wing ribs at the non-connecting part, the wing ribs at the connecting part are additionally provided with lug pieces connected with the rotating shaft, and are simultaneously used for being connected with the rotating shaft through the connecting pieces. And at the rotating shaft, the outer sides of the two connecting pieces are respectively and tightly connected with the two common wing ribs. The front middle part, the rear middle part and the rear edge structure section of the wing realize rotation control through a rotating mechanism, an angle sensor is connected with a rotating shaft on a wing rotating device through a driving wheel, and the actual rotating angle of a steering engine is calculated by utilizing the data of the sensor and the driving proportion of the driving wheel, so that the feedback and the adjustment of the wing camber are realized.

The bending feedback control process of the scheme is as follows: given the expected camber of the wing, the flight control device outputs a corresponding signal, the steering engine receives the signal from the flight control device, and the rotating shaft drives the reinforcing wing rib connected with the rotating shaft to rotate under the driving of the steering engine, so that the rotating function of the wing structural section connected with the rotating shaft is realized. Meanwhile, the steering engine drives the angle sensor connected with the steering engine to rotate, and the angle sensor reads the rotation angle of the steering engine and converts the rotation angle into a corresponding electric signal to be transmitted to the flight control device, so that a set of complete angle feedback system is formed. The three steering engines can work independently, and form independent feedback devices with the corresponding three angle sensors, so that the change of the bending degree of the whole wing structure and the feedback control of the bending degree of the whole wing structure are finally realized.

The variable camber wing structure with deformation feedback mainly comprises: common wing ribs, joint wing ribs, steering engine wing ribs, main beams, longitudinal walls, connecting pieces, steering engines, rotating shafts, angle sensors, transmission devices, masks and the like.

Compared with the common wing rib, the wing rib at the joint is added with the lug connected with the rotating shaft, and the thickness of the wing rib serving as the connecting piece is correspondingly increased so as to meet the strength of the joint.

The steering engine wing ribs are arranged between the longitudinal walls in the structural section, the positions of the steering engine wing ribs are determined according to the position relations among the angle sensors, the driving wheels and the rotating shafts, the steering engine wing ribs are used for fixing the steering engine in the wing structural section,

the main beam is an internal structure of the wing and is arranged in the leading edge structure section of the wing, and the wing beam penetrates through the whole wing structure and is connected with the fuselage, so that the wing and the fuselage are fixedly connected into a whole.

The longitudinal wall is an internal structure of the wing and is connected with each wing rib section along the wing span direction. At the rotating shaft, the longitudinal wall is split, so that sufficient rotating space is reserved for the rotating shaft.

The connecting piece is fixedly connected with the wing rib at the connecting part of the wing rib and the rotating shaft, and the connecting mode of the connecting piece and the wing rib is determined according to the material selection mode.

The turning system formed by the steering engine and the rotating shaft realizes the change of the camber of the wing, meanwhile, the rotating shaft bears certain load, and the connection mode between the steering engine and the rotating shaft is determined according to the structure of the steering engine and the material of the rotating shaft.

The angle sensor is fixed on the longitudinal wall in a way determined according to the specific structure of the wing.

The transmission device connects the angle sensor with a rotating shaft on the wing rotating device, and the actual rotating angle of the steering engine is calculated by using the data of the sensor and the transmission ratio of the transmission wheel, so that the feedback and the adjustment of the wing camber are realized. The form of the transmission wheel is selected according to the structure of the wing, and is a gear, a rubber wheel or other forms.

The covering plate is laid on the internal bearing structure of the wing, and forms a closed wing box together with the longitudinal wall, the main beam, the wing ribs and other structures, and the connection mode of the covering plate is determined according to specific materials.

The skin is arranged at the joint of each wing structure section and is used for maintaining the aerodynamic shape of the wing structure, and the connection mode is determined according to specific materials.

According to one aspect of the present invention, there is provided a camber wing structure with deformation feedback, comprising:

the wing structure section comprises a wing leading edge structure section, a wing middle and rear structure section and a wing trailing edge structure section from the leading edge to the trailing edge of the wing along the chord direction,

a rotating mechanism arranged on the longitudinal walls of the wing middle structure section, the wing middle and rear structure section and the wing rear edge structure section and used for connecting the adjacent wing structure sections,

wherein: the wing leading edge structural section, the wing middle rear structural section and the wing trailing edge structural section respectively comprise wing box structures,

the wing box structure comprises a longitudinal wall, wing ribs and a mask,

the rotating mechanism comprises a driving rotating shaft, a steering engine and an angle sensor,

the rotating shaft is connected with the reinforced wing ribs on the adjacent wing structures to realize the connection between the rotating mechanism and the adjacent wing structure sections,

the angle sensor is coupled with the rotating shaft through the driving wheel, so that the actual rotating angle of the steering engine is determined according to the data of the sensor and the driving proportion of the driving wheel, the feedback and the adjustment of the wing camber are realized,

the variable camber wing structure further comprises:

the steering engine wing ribs are arranged between the longitudinal walls in the structural section, the positions of the steering engine wing ribs are determined according to the position relationship among the angle sensor, the driving wheel and the rotating shaft, so that the steering engine is fixed in the wing structural section,

a steering engine, which is arranged on the wing rib of the steering engine,

a skin is mounted at the gap between the wing structure sections for maintaining a good aerodynamic profile.

According to another aspect of the present invention, there is provided a method for controlling camber feedback of a wing structure based on the above-mentioned variable camber wing structure with deformation feedback, comprising:

the steering engine is enabled to receive an electric signal of the expected camber of an external given wing,

the steering engine is used for driving the rotating shaft to drive the reinforcing wing ribs to rotate, so that the wing structure sections connected with the steering engine realize the rotating function,

the steering engine drives the angle sensor to rotate, the angle sensor reads the rotation angle of the steering engine, converts the rotation angle into a corresponding electric signal and transmits the corresponding electric signal to the flight control device, and therefore a set of complete angle feedback system is formed.

The beneficial effects and advantages of the invention include:

the wing structure with variable camber and the feedback adjusting device can adjust the camber of the wing according to different flight conditions so as to improve the lift-drag ratio and the maneuvering performance of the airplane. The invention provides a camber measuring device which is combined with a rotating device to realize real-time feedback and corresponding adjustment of wing camber.

Drawings

FIG. 1 is an overall isometric view of a inflected wing structure with distortion feedback according to one embodiment of the present invention.

FIG. 2 is a schematic view of a portion of a structure of a variable camber airfoil configuration with distortion feedback according to an embodiment of the present invention.

FIG. 3 is a schematic illustration of a reinforced rib structure of a variable camber wing structure with distortion feedback according to an embodiment of the present invention.

Reference numerals:

Detailed Description

The invention will now be further described with reference to examples and figures.

The invention provides a variable camber wing structure with deformation feedback, which is divided into four structural sections from a leading edge to a trailing edge along a chord direction. Each wing structure section is a wing box structure composed of longitudinal walls, wing ribs, a mask and the like, and the main beam is arranged in the wing leading edge structure section. The wing structural sections are connected with the rotating shaft through partial wing ribs. The rotating mechanism of the wing structure consists of a driving rotating shaft, a steering engine and a coupling. The steering engine drives the rotating shaft connected with the structural section to rotate so as to realize the change of the camber of the wing. Meanwhile, the variable camber wing structure achieves a deformation feedback function through the angle measuring device, the angle sensor is connected with the steering engine through the driving wheel, and the rotating angle of the steering engine is indirectly calculated according to the rotating angle of the sensor and the transmission ratio. The outer surface of the integral structure of the wing is wrapped by a flexible skin.

The main design comprises the following structures: firstly, a morphing wing structural section comprises a wing leading edge structural section, a wing middle and rear structural section and a wing trailing edge structural section; a rotating mechanism comprises a steering engine, a rotating shaft, a coupling and the like; the angle feedback mechanism comprises an angle sensor, a detachable bracket and a rotating wheel;

as shown in fig. 1 and 2:

according to one embodiment of the invention, the variable camber wing structure with deformation feedback is divided into a wing leading edge structural section (1), a wing middle structural section (2), a wing middle rear structural section (3) and a wing trailing edge structural section (4) from the leading edge to the trailing edge along the chord direction. Each wing structure section is a wing box structure (fig. 1) including a longitudinal wall (5), a wing rib (6), a skin panel (7), and the like. The rotating mechanism of the variable camber wing structure comprises a driving rotating shaft (8) and a steering engine (9). The rotating shaft (8) is connected with a reinforced wing rib (14) on the adjacent wing structure to realize the connection between the rotating mechanism and the adjacent wing structure section. The steering engine (9) is arranged at the root part of the wing and fixed on the steering engine wing rib (15) (figure 2). An angle sensor (10) is connected with a rotating shaft (8) in the wing rotating mechanism through a driving wheel (12) (figure 2), and the actual rotating angle of the steering engine is determined by using the data of the sensor (10) and the driving proportion of the driving wheel (12), so that the feedback and the adjustment of the wing camber are realized.

A skin (16) is mounted at the gap between the wing structure sections for maintaining a good aerodynamic profile.

As shown in fig. 2, the process of curvature feedback control of the embodied mechanism is as follows: the steering engine (9) receives an electric signal of an external given expected bending degree, and the rotating shaft (8) drives the reinforcing wing rib (14) connected with the rotating shaft to rotate under the driving of the steering engine (9), so that the wing structure section connected with the rotating shaft realizes a rotating function. Meanwhile, the steering engine (9) drives the angle sensor (10) connected with the steering engine to rotate, and the angle sensor (10) reads the rotation angle of the steering engine (9) and converts the rotation angle into a corresponding electric signal to be transmitted to the flight control device, so that a set of complete angle feedback system is formed.

The rotating mechanisms connected with the wing structure sections can work independently, and form independent feedback devices with the corresponding three angle sensors, so that the change of the bending degree of the whole wing structure and the feedback control of the bending degree of the whole wing structure are finally realized.