CN112572773B

CN112572773B - Wing lift increasing device and wing lift increasing method

Info

Publication number: CN112572773B
Application number: CN202011498954.1A
Authority: CN
Inventors: 罗振兵; 李石清; 刘强; 刘志勇
Original assignee: National University of Defense Technology
Current assignee: National University of Defense Technology
Priority date: 2020-12-17
Filing date: 2020-12-17
Publication date: 2022-10-18
Anticipated expiration: 2040-12-17
Also published as: CN112572773A

Abstract

The invention discloses a wing high lift device and a wing high lift method, which comprise a wing upper surface, a wing lower surface, a wing trailing edge and a wing high lift structure, wherein the wing high lift structure comprises a first jet cavity and a second jet cavity which are arranged between the wing upper surface and the wing lower surface, and a separation plate arranged between the first jet cavity and the second jet cavity; the wing high-lift structure further comprises a first jet orifice and a second jet orifice which are arranged on the trailing edge of the wing, the first jet orifice is communicated with the first jet cavity, the second jet orifice is communicated with the second jet cavity, the first jet cavity is positioned between the upper surface of the wing and the partition plate, and the second jet cavity is positioned between the lower surface of the wing and the partition plate, so that the structure of the synthetic double-jet actuator is formed. Based on the double effects of generating the coanda effect and the virtual trailing edge flap by the synthetic double-jet technology, the traditional circulation lift-increasing technology is combined with the virtual trailing edge flap effect to achieve the purpose of lift increase and improve the lift-increasing efficiency of the traditional circulation lift-increasing technology.

Description

Wing lift increasing device and wing lift increasing method

Technical Field

The invention relates to the technical field of active flow control, in particular to a wing high lift device and a wing high lift method.

Background

At present, the new generation of aircrafts have taken ultra-short-distance take-off and landing, control without control surface and the like as important performance indexes, and the high lift technology is increasingly receiving wide attention and research as a main means for realizing high performance indexes by assistance.

The wing high lift device widely used at present mainly comprises mechanical movable parts such as a flap, a slat and a multi-section wing. The mechanical high lift device also brings many problems while increasing the lift: the moving parts require complex and heavy mechanical control systems, which is not beneficial to simplifying the volume and weight of the airplane; requiring frequent maintenance and repair, increasing maintenance costs of the aircraft, etc. To avoid the above problems, there is a need to develop other reliable means for increasing lift.

In addition to mechanical high-lift technology, another class of power high-lift technology has received much attention in recent years. The circulation control technology is one of the common power high lift technologies, and compared with the traditional high lift device, the circulation control technology has the advantages of simple action, light weight and few movable parts. Therefore, noise caused by the gap flow can be reduced, the specific gravity of the lift device can be reduced, and the manufacturing and maintenance cost can be reduced. At present, the problems of low efficiency, inconvenient application and the like are still faced when the lift force is increased by using the circulation control technology, and one of the main reasons is the problem of an air source. Therefore, the air supply problem must be solved.

Disclosure of Invention

Aiming at the prior art, the invention provides a wing lift-increasing device and a wing lift-increasing method, which are based on the double effects of generating a coanda effect and a virtual trailing edge flap by a synthetic double-jet technology, combine the traditional circulation lift-increasing technology with the virtual trailing edge flap effect to achieve the purpose of lift-increasing and improve the lift-increasing efficiency of the traditional circulation lift-increasing technology.

In order to achieve the above object, the present invention provides a wing high lift device, including a wing upper surface, a wing lower surface, a wing trailing edge and a wing high lift structure, where the wing high lift structure includes a first jet chamber and a second jet chamber that are arranged between the wing upper surface and the wing lower surface and can generate jet, and a separation plate arranged between the first jet chamber and the second jet chamber; the wing rises structure still including establishing first efflux mouth and second efflux mouth on the wing trailing edge, first efflux mouth and first efflux chamber intercommunication, second efflux mouth and second efflux chamber intercommunication, first efflux chamber is located between wing upper surface and the division board, first efflux mouth is located the position that is close to the wing trailing edge on the wing upper surface, the second efflux chamber is located between wing lower surface and the division board, the second efflux mouth is located the position that is close to the wing trailing edge on the wing lower surface to make wing upper surface, first efflux chamber, first efflux mouth, division board, wing lower surface, second efflux chamber, second efflux mouth constitute synthetic dual jet exciter's structure jointly. The first jet flow sprayed out through the first jet flow port deflects due to the coanda effect, so that the circulation is increased, the second jet flow sprayed out through the second jet flow port generates the effect of a virtual trailing edge flap, and the lift-increasing efficiency is higher after the first jet flow and the second jet flow are combined.

In one embodiment, the isolation plate is a vibrating diaphragm, so that the synthetic dual-jet technology is used for generating jets in the first jet cavity and the second jet cavity simultaneously under the action of the same vibrating diaphragm.

In one embodiment, a jet flow generation mode of the vibrating diaphragm is not adopted, and a bleed air mechanism can be directly arranged in the first jet flow cavity and the second jet flow cavity and connected with an aircraft engine to generate continuous jet flows in the first jet flow cavity and the second jet flow cavity by utilizing an engine bleed air mode.

In one embodiment, the trailing edge of the airfoil takes the form of a coanda wall, wherein the coanda wall shape is not limited to a circular arc configuration.

In one embodiment, the number of the wing high-lift structures is multiple and the wing high-lift structures are distributed between the upper surface of the wing and the lower surface of the wing in an array structure.

In order to achieve the above object, the present invention provides a method for increasing the lift of an airfoil, which includes the steps of: generating a first jet flow and a second jet flow at the rear edge of the wing through a first jet flow port and a second jet flow port, wherein the first jet flow and the second jet flow are not interfered with each other; the first jet flow is ejected from the upper trailing edge of the wing, and the annular volume is increased by means of the coanda wall surface, so that the lift force is increased; the second jet flow is sprayed out from the lower trailing edge of the wing, and the effect of a virtual trailing edge flap is generated by spraying out the second jet flow, so that the streamline at the lower trailing edge of the wing is bent, the positive pressure at the lower wall surface is improved, and the lift force is increased.

In one embodiment, in the process of high lift of the wing, the high lift requirement is met in real time by adjusting the phases, the jet intensity and the jet frequency of the first jet and the second jet.

Compared with the prior art, the wing high-lift device and the wing high-lift method have the following beneficial technical effects:

1. the invention is based on the synthetic double-jet technology, can utilize a single vibration diaphragm to generate double jets, is still zero-mass jet in nature, does not need an external air source, can break through the air source limitation of the power lift-increasing technology, solves the air source problem of the circulation control, and has higher vibration energy utilization rate of the vibration diaphragm;

2. the lift-increasing effect of the existing mechanical lift-increasing device such as a trailing edge flap is good and the application is mature, but the reasons of maintenance, overhaul and the like are considered, the optimization space is larger, the virtual trailing edge flap effect generated in the invention plays a role in improving the advantages and avoiding the disadvantages, and the negative influence is weakened while the lift-increasing capability is ensured;

3. according to the invention, the traditional circulation high lift technology and the virtual trailing edge flap effect are combined, the control mode is more flexible after combination, and the high lift efficiency is higher than that of the traditional circulation high lift technology.

Drawings

In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly described below, it is obvious that the drawings in the following description are only some embodiments of the present invention, and for those skilled in the art, other drawings can be obtained according to the structures shown in the drawings without creative efforts.

Fig. 1 is a schematic structural diagram of a high lift device of an airfoil in an embodiment of the invention.

The reference numbers illustrate: the aircraft comprises an upper surface 1 of the wing, a lower surface 2 of the wing, a first jet cavity 3, a second jet cavity 4, a first jet orifice 5, a second jet orifice 6, a vibrating diaphragm 7, a virtual trailing edge flap 8, a coanda effect 9 and a trailing edge 10.

The implementation, functional features and advantages of the objects of the present invention will be further explained with reference to the accompanying drawings.

Detailed Description

The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.

It should be noted that all directional indicators (such as upper, lower, left, right, front, and rear … …) in the embodiment of the present invention are only used to explain the relative position relationship between the components, the movement situation, and the like in a specific posture (as shown in the drawing), and if the specific posture is changed, the directional indicator is changed accordingly.

In addition, the descriptions related to "first", "second", etc. in the present invention are only for descriptive purposes and are not to be construed as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include at least one such feature. In the description of the present invention, "a plurality" means at least two, e.g., two, three, etc., unless specifically limited otherwise.

In the present invention, unless otherwise explicitly stated or limited, the terms "connected", "fixed", and the like are to be understood broadly, for example, "fixed" may be fixedly connected, may be detachably connected, or may be integrated; the connection can be mechanical connection, electrical connection, physical connection or wireless communication connection; they may be directly connected or indirectly connected through intervening media, or they may be connected internally or in any other suitable relationship, unless expressly stated otherwise. The specific meanings of the above terms in the present invention can be understood by those skilled in the art according to specific situations.

In addition, the technical solutions in the embodiments of the present invention may be combined with each other, but it must be based on the realization of those skilled in the art, and when the technical solutions are contradictory or cannot be realized, such a combination of technical solutions should not be considered to exist, and is not within the protection scope of the present invention.

Fig. 1 shows a high lift device for an airfoil disclosed in this embodiment, which specifically includes an upper surface 1 of the airfoil, a lower surface 2 of the airfoil, a trailing edge 10 of the airfoil, and a high lift structure for the airfoil. The high-lift structure of the wing comprises a first jet cavity 3, a second jet cavity 4, a first jet port 5, a second jet port 6 and a partition plate; the first jet cavity 3 and the second jet cavity 4 are positioned between the upper surface 1 and the lower surface 2 of the wing and can generate jet, and the isolation plate is positioned between the first jet cavity 3 and the second jet cavity 4; the first jet orifice 5 and the second jet orifice 6 are positioned on the trailing edge 10 of the wing, the first jet orifice 5 is communicated with the first jet cavity 3, and the second jet orifice 6 is communicated with the second jet cavity 4. The first jet cavity 3 is located between the wing upper surface 1 and the partition plate, the first jet orifice 5 is located on the wing upper surface 1 and close to the wing trailing edge 10, the second jet cavity 4 is located between the wing lower surface 2 and the partition plate, and the second jet orifice 6 is located on the wing lower surface 2 and close to the wing trailing edge 10, so that the wing upper surface 1, the first jet cavity 3, the first jet orifice 5, the partition plate, the wing lower surface 2, the second jet cavity 4 and the second jet orifice 6 jointly form a structure of a synthetic double-jet actuator. The first Jet flow Jet1 ejected from the first Jet orifice 5 deflects due to the coanda effect 9, so that the circulation is increased, the second Jet flow Jet2 ejected from the second Jet orifice 6 has the effect of a virtual trailing edge flap 8, the lift increasing efficiency is higher after the combined action of the first Jet flow Jet1 and the virtual trailing edge flap 8, wherein the trailing edge 10 of the wing adopts a coanda wall surface, and the shape of the coanda wall surface is not limited to a circular arc structure. The wing lift-increasing device generates double effects of a coanda effect 9 and a virtual trailing edge flap 8 based on a synthetic double-jet technology, combines the traditional circulation lift-increasing technology with the effect of the virtual trailing edge flap 8, achieves the purpose of lift increase, and improves the lift-increasing efficiency of the traditional circulation lift-increasing technology.

In this embodiment, the isolation plate is a vibrating diaphragm 7, so that the synthetic dual-jet technology is used to generate jets in the first jet cavity 3 and the second jet cavity 4 under the action of the same vibrating diaphragm 7, and the energy utilization rate of the jet is far higher than that of the conventional jet. When the aircraft works, the first Jet1 is ejected from the first Jet port 5 at the upper rear edge of the wing, and the annular volume is increased by means of the coanda wall surface, so that the lift force is increased; the second Jet2 is ejected from the second Jet orifice 6 at the lower trailing edge, and the effect of the virtual trailing edge flap 8 is generated by ejecting the Jet, so that the streamline at the lower trailing edge is bent, the positive pressure at the lower wall surface is improved, and the lift force is increased.

Of course, the generation mode of the synthetic double jet technology of the vibrating diaphragm 7 may not be adopted, or a bleed mechanism may be directly arranged in the first jet cavity 3 and the second jet cavity 4, and the bleed mechanism is connected to the aircraft engine to generate continuous jet flow in the first jet cavity 3 and the second jet cavity 4 by using the engine bleed mode, so as to generate the coanda effect 9 and the virtual trailing edge flap 8 effect, thereby increasing the lift force.

In this embodiment, the number of the wing high lift structures is multiple, and the wing high lift structures are distributed between the wing upper surface 1 and the wing lower surface 2 in an array structure, so that a plurality of synthetic dual jet actuator structures are formed on the wing trailing edge 10, and the wing high lift efficiency is improved.

In this embodiment, parameters such as the opening positions and the opening sizes of the first jet orifice 5 and the second jet orifice 6 can be adjusted in real time according to the real-time flight condition of the aircraft, and the parameters of the jet flow can be adjusted according to the vibration condition of the vibrating diaphragm 7, which are conventional technical means in the field, and therefore are not described in detail in this embodiment.

The invention concept that the synthetic dual-jet actuator is formed by the wing high-lift structure, the upper surface 1 of the wing and the lower surface 2 of the wing together in the embodiment can not only be used for the high lift of the wing, but also be used for providing the flight moment control after the flaperon is removed by the aircraft without the control surface. And corresponding control torque is generated by adjusting different device parameters of the left wing and the right wing, so that the attitude control is performed.

Based on the wing high lift device, the embodiment also discloses a wing high lift method, the high lift structure is sampled, and the high lift process specifically comprises the following steps: generating a first Jet flow Jet1 and a second Jet flow Jet2 at the trailing edge 10 of the wing through a first Jet flow port 5 and a second Jet flow port 6, wherein the first Jet flow Jet1 and the second Jet flow Jet2 are not interfered with each other; the first Jet1 is ejected from the upper trailing edge of the wing, and the annular volume is increased by means of the coanda wall surface, so that the lift force is increased; the second Jet2 is sprayed out from the lower trailing edge of the wing, and the effect of the virtual trailing edge flap 8 is generated by spraying out the Jet, so that the streamline at the lower trailing edge of the wing is bent, the positive pressure at the lower wall surface is improved, and the lift force is increased. In the wing high lift process, the high lift requirement is met in real time by adjusting the phases, the Jet intensity and the Jet frequency of the first Jet1 and the second Jet 2. How to change the phase, the Jet intensity and the Jet frequency of the first Jet1 and the second Jet2 by adjusting the driving voltage, the driving frequency and the diaphragm thickness of the vibrating diaphragm 7 is a conventional technical means for synthesizing the dual-Jet actuator, and the details are not repeated in this embodiment.

The above description is only a preferred embodiment of the present invention, and is not intended to limit the scope of the present invention, and all modifications and equivalents of the present invention, which are made by the contents of the present specification and the accompanying drawings, or directly/indirectly applied to other related technical fields, are included in the scope of the present invention.

Claims

1. The wing high lift device is characterized by comprising a wing upper surface, a wing lower surface, a wing trailing edge and a wing high lift structure, wherein the wing high lift structure comprises a first jet cavity and a second jet cavity which are arranged between the wing upper surface and the wing lower surface and can generate jet flow, and a separation plate arranged between the first jet cavity and the second jet cavity; the isolation plate is a vibrating diaphragm, and jet flows are generated in the first jet flow cavity and the second jet flow cavity simultaneously under the action of the same vibrating diaphragm based on a synthetic double-jet flow technology;

the wing lift-increasing structure further comprises a first jet orifice and a second jet orifice which are arranged on the wing trailing edge, the first jet orifice is communicated with a first jet cavity, the second jet orifice is communicated with a second jet cavity, the first jet cavity is positioned between the upper surface of the wing and the partition plate, the first jet orifice is positioned on the upper surface of the wing and close to the wing trailing edge, the second jet cavity is positioned between the lower surface of the wing and the partition plate, and the second jet orifice is positioned on the lower surface of the wing and close to the wing trailing edge, so that the upper surface of the wing, the first jet cavity, the first jet orifice, the partition plate, the lower surface of the wing, the second jet cavity and the second jet orifice jointly form a structure of a synthetic double-jet actuator;

the trailing edge of the wing adopts a coanda wall surface, the first jet flow ejected from the first jet flow port deflects due to the coanda effect, so that the circulation is increased, the second jet flow ejected from the second jet flow port generates the effect of a virtual trailing edge flap, and the lift increasing efficiency is higher after the combined action of the first jet flow and the second jet flow.

2. The wing high lift device of claim 1, wherein the coanda wall surface is shaped as a circular arc structure.

3. The wing high lift device of claim 1, wherein the number of the wing high lift structures is plural and distributed between the upper surface of the wing and the lower surface of the wing in an array structure.

4. A method for increasing the lift of an airfoil, which is characterized in that the method for increasing the lift of the airfoil according to claim 1, 2 or 3 is adopted, and the method for increasing the lift of the airfoil comprises the following steps: generating a first jet flow and a second jet flow at the rear edge of the wing through a first jet flow port and a second jet flow port, wherein the first jet flow and the second jet flow are not interfered with each other; the first jet flow is ejected from the upper trailing edge of the wing, and the annular volume is increased by means of the coanda wall surface, so that the lift force is increased; the second jet flow is sprayed out from the lower trailing edge of the wing, the effect of a virtual trailing edge flap is generated by spraying out the second jet flow, the streamline at the lower trailing edge of the wing is bent, the positive pressure at the lower wall surface is improved, and therefore the lift force is increased.

5. The wing high lift method according to claim 4, characterized in that in the wing high lift process, the high lift requirement is met in real time by adjusting the phases, the jet strength and the jet frequency of the first jet and the second jet.