CN116305584A - Control surface installation optimization method and structure - Google Patents

Control surface installation optimization method and structure Download PDF

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Publication number
CN116305584A
CN116305584A CN202310327835.7A CN202310327835A CN116305584A CN 116305584 A CN116305584 A CN 116305584A CN 202310327835 A CN202310327835 A CN 202310327835A CN 116305584 A CN116305584 A CN 116305584A
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wing
control surface
gap
installation
airflow
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CN202310327835.7A
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乔骄
喻岩
谭磊
陈伟
王忠宇
车畅
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Avic Chengdu Uav System Co ltd
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Avic Chengdu Uav System Co ltd
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    • G—PHYSICS
    • G06—COMPUTING; CALCULATING OR COUNTING
    • G06F—ELECTRIC DIGITAL DATA PROCESSING
    • G06F30/00—Computer-aided design [CAD]
    • G06F30/10—Geometric CAD
    • G06F30/15—Vehicle, aircraft or watercraft design
    • G—PHYSICS
    • G06—COMPUTING; CALCULATING OR COUNTING
    • G06F—ELECTRIC DIGITAL DATA PROCESSING
    • G06F30/00—Computer-aided design [CAD]
    • G06F30/10—Geometric CAD
    • G06F30/17—Mechanical parametric or variational design
    • G—PHYSICS
    • G06—COMPUTING; CALCULATING OR COUNTING
    • G06F—ELECTRIC DIGITAL DATA PROCESSING
    • G06F30/00—Computer-aided design [CAD]
    • G06F30/20—Design optimisation, verification or simulation
    • G06F30/28—Design optimisation, verification or simulation using fluid dynamics, e.g. using Navier-Stokes equations or computational fluid dynamics [CFD]
    • G—PHYSICS
    • G06—COMPUTING; CALCULATING OR COUNTING
    • G06F—ELECTRIC DIGITAL DATA PROCESSING
    • G06F2113/00—Details relating to the application field
    • G06F2113/08—Fluids
    • G—PHYSICS
    • G06—COMPUTING; CALCULATING OR COUNTING
    • G06F—ELECTRIC DIGITAL DATA PROCESSING
    • G06F2119/00—Details relating to the type or aim of the analysis or the optimisation
    • G06F2119/14—Force analysis or force optimisation, e.g. static or dynamic forces
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T90/00—Enabling technologies or technologies with a potential or indirect contribution to GHG emissions mitigation

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  • Automation & Control Theory (AREA)
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  • Aerodynamic Tests, Hydrodynamic Tests, Wind Tunnels, And Water Tanks (AREA)

Abstract

The application discloses a control surface installation optimization method and structure, the structure includes a wing and a control surface connected to the wing, a gap is arranged between the wing and the control surface, the control surface installation optimization method further includes an airflow blocking piece arranged between the wing and the control surface, and the airflow blocking piece divides a space where the airflow blocking piece is located into two cavities which are respectively communicated with the upper surface and the lower surface of the wing. According to the control surface installation optimizing structure, the airflow blocking piece is additionally arranged at the gap of the control surface of the wing to block airflow above and below the wing from flowing, so that the flowing characteristics of the designed wing profile are maintained on the surface of the wing.

Description

Control surface installation optimization method and structure
Technical Field
The application relates to the technical field of pneumatic design, in particular to a control surface installation optimization method and structure.
Background
In order to increase lift and control rolling, a flap aileron and an aileron are added at the trailing edge of a wing of an existing airplane, so that a gap exists at the rear section of the wing surface, and meanwhile, in order to connect a main wing and a control surface, a groove is formed at the interface, and a connecting mechanism is arranged.
The gaps of the wing surfaces can cause the airflow of the upper wing surface and the lower wing surface to generate cross flow, and vortex is formed in a cavity formed between the wing surface and the control surface, so that the flow distribution of the wing surface is influenced, the lift resistance characteristic of the aircraft is influenced, and the method is extremely important for optimizing the appearance of the gaps of the control surface.
Disclosure of Invention
The utility model aims to provide a control surface installation optimizing structure, through newly increasing the air current separation piece in wing control surface gap department, the air current that blocks the wing below takes place the cross flow, makes the wing surface flow keep the flow characteristics of design wing section. The control surface installation optimizing method is used for obtaining the control surface installation optimizing structure.
In order to achieve the above purpose, the present application provides a control surface installation optimization structure, which comprises a wing, a control surface connected to the wing, a gap between the wing and the control surface, and an airflow blocking piece arranged in the gap between the wing and the control surface, wherein the space where the airflow blocking piece is located is divided into two cavities which are respectively communicated with the upper surface and the lower surface of the wing.
In some embodiments, the cavity adjacent the upper surface of the wing has the same pressure as the upper surface of the wing and the cavity adjacent the lower surface of the wing has the same pressure as the lower surface of the wing.
In some embodiments, the airflow barrier is mounted to the wing.
In some embodiments, the location of the connection of the airflow blocker to the wing is located in the middle of the rear wall of the wing.
In some embodiments, a gap is left between the airflow blocking member and the front wall of the control surface to enable the control surface to meet deflection.
In some embodiments, the airflow barrier is a flat plate structure.
In some embodiments, the panel structure is laterally disposed between a rear wall of the wing and a front wall of the control surface, and two cavities are formed in an upper portion and a lower portion of the panel structure.
In some embodiments, the airflow barrier is attached to the wing by bolts.
The application also provides a control surface installation optimization method, which comprises the following steps:
a control surface is added at the trailing edge of the wing, a gap is formed between the wing and the control surface, and air flow above and below the wing flows up and down at the gap;
and optimizing the installation shapes of the control surface and the wing, and adding a rigid partition plate at the rear wall of the wing to block up-and-down channeling generated in a gap so that the surface of the wing flows and the flow characteristics of the designed wing profile are maintained.
In some embodiments, the step of optimizing the mounting profile of the control surface and the wing further comprises:
on the basis of increasing the rigid partition board, the fluid calculation simulation means is utilized to simulate various layout optimization modes by combining the changes of the size and the appearance of the gap between the wing and the control surface, so that the pressures of the two separated parts of the rigid partition board and the upper surface and the lower surface of the wing are kept consistent.
Compared with the background art, the control surface installation optimizing structure optimizes on the basis of the control surface installation structure, the control surface installation structure comprises the wing and the control surface connected to the wing, a gap is formed between the wing and the control surface, the optimized control surface installation structure further comprises the air flow blocking piece arranged in the gap between the wing and the control surface, and the space where the air flow blocking piece is located is divided into two cavities which are respectively communicated with the upper surface and the lower surface of the wing.
According to the control surface structure, the flow characteristics of the gaps of the existing wing control surfaces are analyzed, the appearance is optimized, the airflow blocking piece is additionally arranged at the gaps of the wing control surfaces, the problem of up-down flow of the gaps of the existing control surfaces can be well solved, flow of airflow above and below the wing can be blocked, flow characteristics of the designed wing profile are maintained on the surface of the wing, airflow separation can be delayed under a large attack angle, the stall attack angle is increased, and the aerodynamic characteristics of an airplane are improved.
Drawings
In order to more clearly illustrate the embodiments of the present application or the technical solutions in the prior art, the drawings that are required to be used in the embodiments or the description of the prior art will be briefly described below, and it is obvious that the drawings in the following description are only embodiments of the present application, and that other drawings may be obtained according to the provided drawings without inventive effort to a person skilled in the art.
FIG. 1 is a schematic diagram of a control surface installation optimization structure provided in an embodiment of the present application;
FIG. 2 is a schematic view of a three-dimensional structure of a control surface gap;
FIG. 3 is a schematic view of a control surface gap streamline;
FIG. 4 is a graphical illustration of wing surface pressure distribution comparisons;
FIG. 5 is a schematic view of an aircraft flap seal;
fig. 6 is a schematic view of a rear streamline of a new partition plate for a control surface gap according to an embodiment of the present application.
Wherein:
1-wing, 2-control surface, 3-air flow barrier, 01-first cavity, 02-second cavity.
Detailed Description
The following description of the embodiments of the present application will be made clearly and fully with reference to the accompanying drawings, in which it is evident that the embodiments described are only some, but not all, of the embodiments of the present application. All other embodiments, which can be made by one of ordinary skill in the art without undue burden from the present disclosure, are within the scope of the present disclosure.
In order to better understand the aspects of the present application, a further detailed description of the present application will be provided below with reference to the accompanying drawings and detailed description.
Referring to fig. 1 to 6, fig. 1 is a schematic diagram of a control surface installation optimization structure provided in an embodiment of the present application, fig. 2 is a schematic diagram of a control surface gap three-dimensional structure, fig. 3 is a schematic diagram of a control surface gap streamline, fig. 4 is a schematic diagram of wing surface pressure distribution contrast, fig. 5 is a schematic diagram of an aircraft flap and aileron sealing structure, and fig. 6 is a schematic diagram of a control surface gap newly added partition plate rear streamline provided in an embodiment of the present application.
In a first specific embodiment, the present application provides a control surface installation optimization structure, which belongs to an optimization design, that is, optimization is performed on the basis of the control surface installation structure.
The control surface mounting structure of the foundation comprises a wing 1 and a control surface 2 connected to the wing 1, and a gap (cavity) is formed between the wing 1 and the control surface 2.
As shown in fig. 2, the conventional connection mode is to connect the rear wall of the wing 1 with the control surface 2 through a suspension joint, and the high-pressure air flow below the wing 1 flows into a gap (cavity) from the lower wing surface and then flows out from the gap of the upper wing surface along the rear wall surface of the wing 1. As shown in FIG. 3, the channeling of the upper and lower airfoils increases the pressure of the upper airfoil and decreases the pressure of the lower airfoil. As shown in fig. 4, the influence of the pressure distribution of the section of the wing 1 is observed, and the pressure change of the upper airfoil surface and the lower airfoil surface is direct.
At present, in order to meet the movement and deformation coordination requirements of a movable surface, a conventional aircraft adopts a structure gap reserved between a control surface and a fixed structure; for stealth aircraft, only the seal structure is shown in fig. 5, so that gaps of the movable surface part of the structure are reduced, RCS of the whole aircraft is reduced to the greatest extent, stealth performance of the aircraft is guaranteed, the main seal technology comprises graphite seal, comb seal and the like, but the existing mode has the characteristics of high strength and high rigidity of strong pneumatic suction force, and has the characteristics of large deformation, high rebound resilience and the like, so that contradiction between the flexibility of large deformation and the rigidity of bearing load is difficult to solve, and meanwhile, fatigue loss is caused by the seal structure due to vibration problems caused by separation of airfoils and the like.
The optimal control surface mounting structure in the application further comprises an airflow blocking piece 3 arranged in a gap between the wing 1 and the control surface 2, and the space where the airflow blocking piece 3 is located is divided into two cavities which are respectively communicated with the upper surface and the lower surface of the wing 1.
It should be noted that the structural form of the airflow blocking member 3 is not unique, and the material of the airflow blocking member should be a rigid material, which mainly acts to block the air flow of the upper airfoil surface and the lower airfoil surface, and reduce the loss of lift caused by the gap flow of the control surface 2. The airflow blocking piece 3 is equivalent to a blocking mode for gas channeling at a gap, and the blocking mode does not need to have the flexible deformation requirement of the traditional sealing mode, and meanwhile, the problem of irregular vibration, even tremble and other comprehensive vibration in the flight process of the traditional sealing mode is avoided, so that performance reduction or damage caused by vibration in use is effectively reduced.
Preferably, as shown in fig. 6, the two cavities maintain a uniform pressure with the upper and lower surfaces of the wing 1, in particular, the cavity adjacent to the upper surface of the wing 1 (upper portion of the illustrated middle region) has the same pressure as the upper surface of the wing 1 and the cavity adjacent to the lower surface of the wing 1 (lower portion of the illustrated middle region) has the same pressure as the lower surface of the wing 1.
According to the airflow blocking piece, the flow characteristics of the gaps of the existing wing 1 and the control surface 2 are analyzed, the appearance of the control surface 2 is optimized, the airflow blocking piece 3 is additionally arranged at the gaps of the wing 1 and the control surface 2, the problem of up-down channeling of the gaps of the existing control surface 2 can be well solved through the layout, not only can the channeling of airflow above and below the wing 1 be blocked, the flow characteristics of the designed wing profile can be maintained on the surface of the wing 1, but also the airflow separation can be delayed under a large attack angle, the stall attack angle is increased, and the aerodynamic characteristics of an airplane are improved.
In a specific embodiment, the airflow barrier 3 is mounted to the wing 1.
In this embodiment, the airflow barrier 3 is selectively mounted on the wing 1 so that the airflow barrier 3 is integrated with the wing 1, the wing 1 provides a mounting location for the airflow barrier 3 and provides reliable support. The installation mode is simpler in structural design and assembly process than the traditional sealing mode.
Further, with continued reference to fig. 1, in some embodiments, the connection location of the airflow barrier 3 to the wing 1 is located in the middle of the rear wall of the wing 1; a gap is reserved between the airflow blocking piece 3 and the front wall of the control surface 2, so that the control surface 2 can deflect.
In this embodiment, considering that the control surface 2 generally has a characteristic of deflecting relative to the wing 1, the airflow blocking member 3 is mounted in the middle of the rear wall of the wing 1, and meanwhile, a certain gap is kept between the airflow blocking member 3 and the control surface 2, so that the normal deflection of the control surface 2 is not disturbed, and meanwhile, the blocking mode of the airflow blocking member 3 to the gas channeling is always effective.
The air flow barrier 3 is illustratively a flat plate structure.
In this embodiment, the air flow barrier 3 is embodied as a rigid partition.
In the process of installing the partition plates of the wing 1 and the control surface 2, selecting a rigid partition plate to be installed in the middle of the rear wall of the wing 1, and connecting the first end of the rigid partition plate with the wing 1; it should be noted that the length of the rigid diaphragm is selected to ensure that the position and length of the rigid diaphragm do not hinder the deflection of the control surface 2; after the first end of the rigid partition board is connected with the wing 1, a certain gap is kept between the second end of the rigid partition board and the front wall of the control surface 2, so that the deflection flexibility of the control surface 2 is ensured. In addition, because a gap exists between the rigid partition plate and the control surface 2, that is, a gap (cavity) between the wing 1 and the control surface 2 is not completely closed, condensed liquid water can smoothly flow out by utilizing the gap, and accumulated water is prevented from being condensed into ice in a high altitude to prevent deflection of the control surface 2.
In some embodiments, referring to fig. 1 and 6, a flat plate structure (rigid diaphragm) is arranged laterally between the rear wall of the wing 1 and the front wall of the control surface 2, and two cavities are formed in the upper and lower parts of the flat plate structure.
In this embodiment, the rigid partition divides the gap (cavity) between the wing 1 and the control surface 2 into a first cavity 01 and a second cavity 02, and in fig. 1, the first cavity 01 is located on the upper side, and the second cavity 02 is located on the lower side. Comparing fig. 3 with fig. 6, the first cavity 01 and the second cavity 02 in fig. 3 are not separated by a rigid partition board, but are a complete cavity, as shown by a flow chart, the pressure of the upper airfoil surface is increased under the influence of the upper and lower channeling, the pressure of the lower airfoil surface is reduced, the lift force generated by the wing 1 is reduced, and the aerodynamic performance of the aircraft is seriously affected; in fig. 6, the first cavity 01 and the second cavity 02 are separated by a rigid partition board, such as a flow chart shows, so that the layout can better solve the problem of up-down flow of a gap of the existing control surface 2, and can delay air flow separation under a large attack angle, increase the stall attack angle and improve the aerodynamic characteristics of an airplane.
It should be noted that the improvement of the present application focuses on the layout mode of adding the rigid partition plate in the gap between the wing 1 and the control surface 2, the rigid partition plate is specifically installed on the wing 1, the connection modes of the rigid partition plate and the wing 1 are various, preferably, the air flow blocking member 3 (rigid partition plate) is connected with the wing 1 through bolts, and the present application has the characteristics of convenient assembly and disassembly, easy maintenance and adjustable installation position.
The application also provides a control surface installation optimization method which is used for obtaining the control surface installation optimization structure and has all the beneficial effects of the control surface installation optimization structure.
The control surface installation optimization method is optimized for a basic control surface installation method, and at least comprises the following steps:
a control surface 2 is added at the rear edge of the wing 1, a gap is formed between the wing 1 and the control surface 2, and air flows above and below the wing 1 cross up and down at the gap;
the installation appearance of the control surface 2 and the wing 1 is optimized, a rigid partition plate is additionally arranged at the rear wall of the wing 1 to block up-down channeling which occurs in gaps, so that the surface of the wing 1 flows and the flow characteristics of the designed wing profile are maintained.
According to the method, the rigid partition plate is additionally arranged at the rear wall of the wing 1, so that the purpose of blocking airflow above and below the wing 1 from flowing is achieved, the flowing characteristics of the designed wing profile are maintained on the surface of the wing 1, the aerodynamic characteristics are guaranteed, meanwhile, the partition plate in the middle of the cavity does not need to be like a wing surface sealing structure to ensure that the shape of the wing 1 is unchanged, and the coordination contradiction between the flexibility of large deformation and the rigidity of bearing load is avoided; meanwhile, the gap can enable the liquid water to smoothly flow down so as to prevent the problems of accumulated water, icing and the like caused by condensation of cold air.
In some embodiments, the step of optimizing the mounting profile of the control surface 2 and the wing 1 further comprises:
on the basis of adding the rigid partition plates, the fluid calculation simulation means are utilized to simulate various layout optimization modes by combining the changes of the size and the appearance of the gap between the wing 1 and the control surface 2, so that the pressures of the two separated parts of the rigid partition plates and the upper surface and the lower surface of the wing 1 are kept consistent.
In the embodiment, in the process of designing the gap installation appearance of the control surface 2, fluid calculation simulation means are fully utilized, and various layout optimization modes such as reducing the gap of the control surface 2, optimizing the appearance of the cavity, adding rigid partition plates and the like are simulated, and the fact that the upper and lower parts of the cavity are respectively consistent with the pressures of the upper and lower surfaces of the wing 1 through the rigid partition plates is found, so that the air flow on the upper and lower surfaces of the wing 1 cannot be influenced by pressure difference and flows into the cavity, and the flowing state of the surface of the original seamless wing 1 is maintained, as shown in fig. 6; under the condition of a large attack angle, the vortex is influenced by the shape of the gap of the upper airfoil surface, the vortex can be downwards recessed at the gap, the chord direction position of the separation start is finally increased, the chord direction area of the separation part is shortened, and the separation is delayed, so that the better surface flow form of the wing 1 is achieved.
It should be noted that many of the components mentioned in this application are common standard components or components known to those skilled in the art, and the structures and principles thereof are known to those skilled in the art from technical manuals or by routine experimental methods.
It should be noted that in this specification relational terms such as first and second are used solely to distinguish one entity from another entity without necessarily requiring or implying any actual such relationship or order between such entities.
The control surface installation optimization method and the control surface installation optimization structure provided by the application are described in detail. Specific examples are set forth herein to illustrate the principles and embodiments of the present application, and the description of the examples above is only intended to assist in understanding the methods of the present application and their core ideas. It should be noted that it would be obvious to those skilled in the art that various improvements and modifications can be made to the present application without departing from the principles of the present application, and such improvements and modifications fall within the scope of the claims of the present application.

Claims (10)

1. The control surface installation optimizing structure comprises a wing and a control surface connected to the wing, wherein a gap is formed between the wing and the control surface, and the control surface installation optimizing structure is characterized by further comprising an airflow blocking piece arranged between the wing and the control surface, wherein the airflow blocking piece divides a space where the airflow blocking piece is located into two cavities which are respectively communicated with the upper surface and the lower surface of the wing.
2. The control surface mounting optimization structure of claim 1 wherein the cavity adjacent the upper surface of the wing has the same pressure as the upper surface of the wing and the cavity adjacent the lower surface of the wing has the same pressure as the lower surface of the wing.
3. The rudder surface mounting optimization structure of claim 1, wherein the airflow barrier is mounted to the wing.
4. The control surface mounting optimization structure of claim 3, wherein the connection location of the airflow blocking member and the wing is located in the middle of the rear wall of the wing.
5. The control surface mounting optimization structure of claim 4, wherein a gap is left between the airflow blocking member and a front wall of the control surface to enable the control surface to meet deflection.
6. The control surface mounting optimization structure of any one of claims 1 to 5 wherein the air flow barrier is a flat plate structure.
7. The control surface mounting optimization structure of claim 6, wherein the flat plate structure is laterally arranged between a rear wall of the wing and a front wall of the control surface, and two cavities are formed in an upper portion and a lower portion of the flat plate structure.
8. The control surface mounting optimization structure of any one of claims 3 to 5 wherein the airflow barrier is attached to the wing by bolts.
9. A control surface installation optimizing method for obtaining the control surface installation optimizing structure according to any one of claims 1 to 8, characterized by comprising:
a control surface is added at the trailing edge of the wing, a gap is formed between the wing and the control surface, and air flow above and below the wing flows up and down at the gap;
and optimizing the installation shapes of the control surface and the wing, and adding a rigid partition plate at the rear wall of the wing to block up-and-down channeling generated in a gap so that the surface of the wing flows and the flow characteristics of the designed wing profile are maintained.
10. The control surface installation optimization method according to claim 9, wherein the step of optimizing the installation profile of the control surface and the wing further comprises:
on the basis of increasing the rigid partition board, the fluid calculation simulation means is utilized to simulate various layout optimization modes by combining the changes of the size and the appearance of the gap between the wing and the control surface, so that the pressures of the two separated parts of the rigid partition board and the upper surface and the lower surface of the wing are kept consistent.
CN202310327835.7A 2023-03-30 2023-03-30 Control surface installation optimization method and structure Pending CN116305584A (en)

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Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN117141710A (en) * 2023-10-30 2023-12-01 西安现代控制技术研究所 Hypersonic folding airfoil surface gap air flow partition structure

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN117141710A (en) * 2023-10-30 2023-12-01 西安现代控制技术研究所 Hypersonic folding airfoil surface gap air flow partition structure

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