Water and liquid drainage design method for wing leading and trailing edge structure
By drawing drainage holes, filling with glue and setting up isolation dams on the leading and trailing edge structures of the wing, the drainage path is optimized, the problems of low drainage efficiency and easy blockage of the leading and trailing edge structures of the wing are solved, and efficient drainage and fire safety are achieved.
Patent Information
- Application Number
- CN202510957419.4
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- Filing Date
- 2025-07-11
- Publication Date
- 2025-10-03
AI Technical Summary
In the existing technology, the drainage and liquid drainage design of the leading and trailing edge structures of the wing has the problems of low efficiency and easy clogging. In particular, the drainage path design of the composite wall panel structure is not optimized enough and cannot effectively remove condensed water and flammable liquids.
By drawing drainage holes on the leading and trailing edge structures of the wing, filling glue in the corner areas of the beam rib webs, leaving water gaps at the junction of the crossbeam and longitudinal beam, and setting up isolation dams in the flammable liquid area for sealing, the drainage path is optimized to ensure smooth discharge of the liquid.
It improves the drainage efficiency, avoids path blockage, enhances the fire safety and economy of the structure, and is suitable for various antenna cover end surface processing.
Smart Images
Figure CN120735940A_ABST
Abstract
Description
Technical Field
[0001] The invention belongs to the technical field of aviation structure design and optimization, and in particular relates to a drainage and liquid discharge design method for a wing leading and trailing edge structure. Background Art
[0002] The liquids that need to be controlled and discharged from the aircraft fuselage structure mainly include: condensed water produced by air condensation on various surfaces; rainwater or flushing fluid that penetrates or splashes into the interior of the aircraft due to possible scouring; fuel, hydraulic oil and other liquids that normally leak from the system; gray water that leaks or overflows from the cabin kitchen and toilet sinks; gray water on the floor; waste water in the toilet; snow or muddy water melted on the floor near the boarding gate or service door; antifreeze, etc.
[0003] The purpose of fuselage structural drainage design is to ensure that the aircraft provides drainage, sealing, and ventilation measures where necessary to reduce fire hazards, prevent moisture, corrosion, and wear, and prevent the formation of hazardous ice in specific parts of the aircraft. When the aircraft is parked, the aircraft's pitch angle is used to drain all required fluids out of the aircraft. During takeoff, the aircraft's pitch motion is used to drain fluids through longitudinal and circumferential drainage paths formed on the fuselage panels and drain valves at the bottom of the fuselage to the outside. Drainage can also be performed during descent, but by then the fluid may have frozen.
[0004] Detailed drainage designs are already available on various models of civil airliners currently in service. The present invention aims to propose a universal design solution for the composite material panel structure at the leading and trailing edges of the wings.
[0005] The drainage of the aircraft fuselage structure must ensure that the weakly corrosive water condensed on the structural elements can be discharged to the bottom of the aircraft cabin through the shortest possible drainage path; corrosive liquids discharged from the galley and similar places can be directly discharged outside the aircraft or collected in corrosion-resistant containers for treatment during landing.
[0006] In particular, the leading and trailing edge structures of the wing, where the liquids generated primarily consist of condensed water and flammable liquids such as fuel leaking from the transmission mechanism, require rigorous design to ensure adequate drainage paths and locations to improve drainage efficiency, rather than relying on excessive use of sealants. Drainage from the leading and trailing edge structures is primarily achieved through drainage holes in the composite paneling. The size, placement, and density of the holes are crucial to drainage efficiency. Furthermore, the leading and trailing edges of the wing contain numerous rib structures, and appropriate gaps must be maintained between these structures to prevent blockage of the drainage paths. Summary of the Invention
[0007] The present invention aims at the drainage optimization design problem of composite material wall panel structure at the leading and trailing edges of a wing and provides a drainage and liquid discharge design method for the leading and trailing edge structure of a wing to improve the drainage and liquid discharge efficiency.
[0008] In order to achieve the above object, the present invention adopts the following technical solutions: A method for designing drainage and liquid drainage for a wing leading and trailing edge structure comprises the following steps: Based on the structure's mounting position on the aircraft, determine the location of its lowest point when the aircraft is at rest; Draw the drainage holes based on the location of the lowest point; Fill the corner area of the beam rib web with glue; Leave a water gap at the junction of the transverse beam and the longitudinal beam; Set up isolation dikes to seal areas where flammable liquids are present.
[0009] As a further solution of the present invention: the position of the lowest point of the structure when the aircraft is stationary is determined based on the installation position of the structure on the aircraft. Specifically, in the aircraft structure digital model, the heading direction is generally along the X-axis direction of the coordinate system, and the span direction is along the Z-axis direction. Therefore, the lowest point of the leading and trailing edge structures of the wing along the Y-axis is determined to be the lowest point of the aircraft when it is stationary.
[0010] As a further solution of the present invention: for composite sandwich panel structures, the drainage holes should be drawn away from the honeycomb area and should be drawn in the solid area at the edge.
[0011] As a further solution of the present invention: the minimum distance between the drainage hole and the wall panel boundary is not less than twice the diameter of the drainage hole.
[0012] As a further solution of the present invention: the diameter of the drainage hole is determined according to the thickness of the wall panel, and a drainage hole is set at an interval of no more than 1.5m.
[0013] As a further solution of the present invention: the glue filling in the corner area of the beam rib web is specifically: for the pits in the front and rear edge structures where it is inconvenient to open drainage holes, and for the situation where the drainage holes cannot be opened at the lowest point of the structure due to the influence of structural strength, glue filling is performed in the area where more liquid can be accumulated.
[0014] As a further solution of the present invention: a water gap is left at the junction of the crossbeam and the longitudinal beam, specifically: there are many rib structures and beam structures at the leading and trailing edges of the wing, and a closed water gap is left at the connection between the rib structure and the beam structure.
[0015] As a further solution of the present invention: the length or width of the closed water gap must be greater than or equal to 5 mm.
[0016] As a further solution of the present invention: isolation dikes are set up in the areas where flammable liquids exist for sealing. Specifically, there are areas in the leading and trailing edge structures of the wing where flammable liquids may leak, and the discharge must be completed within the respective fire protection zones. Isolation dikes should be set up in the areas where flammable liquids exist for sealing to prevent them from mixing with condensed water.
[0017] As a further solution of the present invention, a sealant is filled in the connection gap between the rib and the front and rear beams of the wing to form an isolation dam.
[0018] In summary, due to the adoption of the above technical solution, the beneficial effects of the present invention are: 1. This application is easy to operate and is suitable for processing the end faces of various radomes of this type.
[0019] 2. This application can achieve drainage functions without affecting the structural strength of the leading and trailing edges of the wing, thereby improving the design and drainage efficiency and improving the economy of civil aircraft. BRIEF DESCRIPTION OF THE DRAWINGS
[0020] Figure 1 It is a structural schematic diagram of the drainage hole of the present invention; Figure 2 This is a schematic diagram of glue filling in the water accumulation area of the present invention; Figure 3 This is a schematic structural diagram of a closed water gap according to the present invention; Figure 4 This is a schematic structural diagram of the isolation dam of the present invention; Figure 5 This is a schematic structural diagram of a wall panel according to an embodiment of the present invention; Figure 6 This is a schematic diagram of the lowest point position of the wall panel according to an embodiment of the present invention; Figure 7 This is a structural diagram of the distance between the drainage hole and the wall panel boundary according to an embodiment of the present invention; Figure 8 This is a structural diagram of a beam-rib structure according to an embodiment of the present invention; Figure 9 Schematic diagram of glue filling comparison according to an embodiment of the present invention; Figure 10 Schematic diagram of the structure of the junction of the crossbeam and the longitudinal beam according to an embodiment of the present invention; Figure 11 Schematic diagram of the structure of the corner piece and composite material wall panel according to an embodiment of the present invention. DETAILED DESCRIPTION
[0021] In order to make the purpose, technical solutions and advantages of the present invention more clear, the technical solutions in the embodiments of the present invention will be described in more detail below with reference to the accompanying drawings in the embodiments of the present invention.
[0022] In the drawings, the same or similar reference numerals throughout the drawings represent the same or similar elements or elements having the same or similar functions. The described embodiments are only some of the embodiments of the present invention, but not all of the embodiments.
[0023] The embodiments described below with reference to the accompanying drawings are exemplary and intended to explain the present invention, and should not be construed as limiting the present invention. All other embodiments derived by persons of ordinary skill in the art based on the embodiments of the present invention without creative effort shall fall within the scope of protection of the present invention.
[0024] The following is combined with Figure 1-11 The embodiments of the present invention are described in detail.
[0025] Example 1 The present invention provides a method for designing drainage and liquid drainage for a wing leading and trailing edge structure, comprising the following steps: Based on the structure's mounting position on the aircraft, determine the location of its lowest point when the aircraft is at rest; Draw the drainage holes based on the location of the lowest point; Fill the corner area of the beam rib web with glue; Leave a water gap at the junction of the transverse beam and the longitudinal beam; Set up isolation dikes to seal areas where flammable liquids are present.
[0026] Preferably, the position of the lowest point of the structure when the aircraft is stationary is determined based on the installation position of the structure on the aircraft. Specifically, in a digital model of aircraft structure, the direction along the X-axis of the coordinate system is generally the heading direction, and the direction along the Z-axis is the span direction. Therefore, the lowest point of the leading and trailing edge structures of the wing along the Y-axis is determined to be the lowest point of the aircraft when it is stationary.
[0027] Preferably, for composite sandwich panel structures, the drainage holes should be drawn away from the honeycomb area and in the solid area at the edge.
[0028] Preferably, the minimum distance between the drainage hole and the wall panel boundary is not less than twice the diameter of the drainage hole.
[0029] Preferably, the diameter of the drainage hole is determined according to the thickness of the wall panel, and a drainage hole is set at an interval of no more than 1.5m.
[0030] Preferably, the glue filling in the beam rib web corner area is specifically: for the pits in the front and rear edge structures where it is inconvenient to open drainage holes, and for the situation where the drainage holes cannot be opened at the lowest point of the structure due to the influence of structural strength, glue filling is performed in the area where more liquid can be accumulated.
[0031] Preferably, a water gap is left at the junction of the transverse beam and the longitudinal beam, specifically: there are many rib structures and beam structures at the leading and trailing edges of the wing, and a closed water gap is left at the connection between the rib structure and the beam structure.
[0032] Preferably, the length or width of the closed water gap should be greater than or equal to 5 mm.
[0033] Preferably, an isolation dam is set up in the area where flammable liquid exists for sealing. Specifically, there are areas in the leading and trailing edge structures of the wing where flammable liquid may leak, and the discharge must be completed within the respective fire protection zones. An isolation dam should be set up in the area where flammable liquid exists for sealing to prevent it from mixing with condensed water.
[0034] Preferably, the connection gaps between the ribs and the front and rear beams of the wing are filled with sealant, that is, an isolation dam is formed.
[0035] Example 2 The present invention provides a method for designing drainage and liquid drainage for a wing leading and trailing edge structure, comprising the following steps: a) To achieve the drainage function of the machine structure, the holes set in the drainage passage to discharge the liquid inside the machine structure are called drainage holes, and the holes arranged on the structural parts in the drainage passage to pass the accumulated water inside the structure to the drainage holes are called water holes. Figure 1 The following shows drainage holes in a composite panel. Drain holes are generally located at the lowest point when the aircraft is at rest. For the wing leading edge, the lowest point is in the direction opposite the panel's heading; for the wing leading edge, the lowest point is in the direction of the panel's heading. Table 1 lists the minimum diameter requirements for drain and water holes. If structural strength permits, a water hole diameter of 8.5 mm or greater is recommended.
[0036] Table 1 Minimum diameter of water holes and drainage holes Unit: mm
[0037] The leading and trailing edges of the wing are mainly composed of slender wall panel structures, and the drainage path is a slender passage. In order to ensure that the leading and trailing edge structures have good drainage efficiency, drainage holes are generally set at intervals of no more than 1.5m.
[0038] b) For the pits on the front and rear edges where it is not convenient to open water holes, or where the water holes / drain holes cannot be opened at the lowest point of the structure due to the influence of structural strength, filling with glue should be considered when the amount of liquid accumulation is large, such as Figure 2 This type of filling should be avoided or reduced as much as possible during the structural design process.
[0039] c) There are many rib structures on the leading and trailing edges of the wing that are connected to the leading and trailing beams of the wing to form a closed water gap. Figure 3 As shown, the length or width of the closed water gap must be greater than or equal to 5mm.
[0040] d) The leading and trailing edge structures of the wing may leak flammable liquids. In principle, flammable liquids must be discharged within their respective fire compartments and not across them. Therefore, dikes should be installed in areas where flammable liquids are present to prevent mixing with condensate. Dikes are constructed by filling the gaps between the ribs and the leading and trailing spars with sealant to block the passage between them.
[0041] Example 3 by Figure 5 The three panels shown are taken as an example. The structure of the composite panels is a honeycomb sandwich panel, and there are metal beams at the junction of the panels.
[0042] The present invention provides a method for designing drainage and liquid drainage for a wing leading and trailing edge structure, comprising the following steps: Step 101, first determine the lowest point of the three panels when the aircraft is stationary based on their installation positions on the aircraft. In aircraft structure digital models, the X-axis direction is generally the heading direction, and the Z-axis direction is the span direction. Therefore, the lowest point of the three panels along the Y-axis is the lowest point of the aircraft when it is stationary. The location of the lowest point is as follows: Figure 6 shown.
[0043] Step 102, draw the drainage holes. For composite sandwich panel structures, the drainage holes should be drawn away from the honeycomb area and in the solid area at the edge. The diameter D of the drainage hole is determined according to the thickness of the panel according to the data in Table 1. In particular, considering the strength of the panel, the minimum distance between the drainage hole and the panel boundary should be no less than twice the diameter of the drainage hole, that is, ≥2D. Figure 7 shown.
[0044] Step 103, after the drainage holes are drawn, consider the influence of the beam ribs on drainage. Figure 8 The slope of the location shown is large, and the beam-rib structure is likely to block the drainage path. Figure 2 Shown in Figure 8 The area shown in the red frame is filled with glue. The final effect is as follows Figure 9 As shown, the yellow plane represents the top surface of the filler.
[0045] Figure 9 Before filling (left image, red indicates areas prone to water accumulation) and after filling (yellow represents the top surface of the filling) Step 104, Figure 10 The area shown, that is, the junction of the crossbeam and the longitudinal beam, usually has an angle piece to connect the two, so you need to refer to Figure 3 To set the corner piece size, leave enough drainage path.
[0046] Step 105: In particular, if there is a possibility of flammable liquid leakage in the area where the composite sandwich panel is located, the area in step 104, i.e. Figure 11 In the area shown, the gap between the corner piece and the composite wall panel is completely sealed with sealant.
[0047] So far, the purpose of the present invention has been achieved.
[0048] The above are only preferred embodiments of the present invention and are not intended to limit the present invention. Any modifications, equivalent replacements, improvements, etc. made within the spirit and principles of the present invention should be included in the scope of protection of the present invention.
Claims
1. A method for designing drainage and liquid drainage for the leading and trailing edge structures of a wing, characterized in that: The following steps are involved: Based on the structure's mounting position on the aircraft, determine the location of its lowest point when the aircraft is at rest; Draw the drainage holes based on the location of the lowest point; Fill the corner area of the beam rib web with glue; Leave a water gap at the junction of the transverse beam and the longitudinal beam; Set up isolation dikes to seal areas where flammable liquids are present.
2. A method for designing drainage and liquid discharge for a wing leading and trailing edge structure according to claim 1, characterized in that: The position of the lowest point of the structure when the aircraft is stationary is determined based on the installation position of the structure on the aircraft. Specifically, in the aircraft structure digital model, the heading direction is generally along the X-axis direction of the coordinate system, and the span direction is along the Z-axis direction. Therefore, the lowest point of the leading and trailing edge structures of the wing along the Y-axis is determined to be the lowest point of the aircraft when it is stationary.
3. The method for designing drainage and liquid discharge for the leading and trailing edge structures of a wing according to claim 1, characterized in that: For composite sandwich panel structures, drainage holes should be drawn away from the honeycomb area and in the solid area at the edge.
4. The method for designing drainage and liquid discharge for the leading and trailing edge structures of a wing according to claim 1, characterized in that: The minimum distance between the drainage hole and the wall panel boundary shall not be less than twice the drainage hole diameter.
5. The method for designing drainage and liquid discharge for the leading and trailing edge structures of a wing according to claim 1, characterized in that: The diameter of the drainage hole is determined according to the thickness of the wall panel, and a drainage hole is set at an interval of no more than 1.5m.
6. The method for designing drainage and liquid discharge for the leading and trailing edge structures of a wing according to claim 1, characterized in that: The said filling of glue in the corner area of the beam rib web is specifically: for the pits in the front and rear edge structures where it is inconvenient to open drainage holes, and for the situation where the drainage holes cannot be opened at the lowest point of the structure due to the influence of structural strength, glue filling is performed in the area where more liquid can be accumulated.
7. The method for designing drainage and liquid discharge for the leading and trailing edge structures of a wing according to claim 1, characterized in that: The water-passing gap is left at the junction of the crossbeam and the longitudinal beam. Specifically, there are many rib structures and beam structures at the leading and trailing edges of the wing, and a closed water-passing gap is left at the connection between the rib structure and the beam structure.
8. The method for designing drainage and liquid discharge for the leading and trailing edge structures of a wing according to claim 7, characterized in that: The length or width of the closed water gap must be greater than or equal to 5mm.
9. The method for designing drainage and liquid discharge for the leading and trailing edge structures of a wing according to claim 1, characterized in that: The said isolation dikes are set up to seal the areas where flammable liquids exist. Specifically, there are areas in the leading and trailing edge structures of the wing where flammable liquids may leak, and the discharge must be completed within the respective fire protection zones. Isolation dikes should be set up to seal the areas where flammable liquids exist to prevent them from mixing with condensed water.
10. A method for designing drainage and liquid discharge for a wing leading and trailing edge structure according to claim 9, characterized in that: The sealant is filled in the connection gap between the rib and the front and rear beams of the wing to form an isolation dam.