Aviation fire extinguishing water tank based on steepest curve and design method thereof

Abstract

The invention discloses an aviation fire extinguishing water tank based on a steepest curve and a design method thereof, and relates to the technical field of intelligent manufacturing equipment industries, the aviation fire extinguishing water tank comprises a tank body, a discharge port and a filling port, the tank body comprises a side surface formed based on an upper contour line and a side surface formed based on a lower contour line, the upper contour line is constructed from the highest point of the upper contour line to the lowest point of the upper contour line through an overturning steepest curve, the lower contour line is constructed from the highest point of the lower contour line to the lowest point of the lower contour line through the overturning steepest curve, and the box body is installed on an aircraft. The contour lines of the upper and lower water tanks are constructed based on the steepest curve of overturning, so that the fire extinguishing medium in the water tanks can be quickly discharged, the total discharge time of the water tanks is shortened, the discharge speed of the aviation fire extinguishing water tanks is increased, and the aviation fire extinguishing efficiency is favorably improved.

Description

Technical Field

[0001] This invention relates to the field of intelligent manufacturing equipment technology, and in particular to an aviation fire extinguishing water tank based on the steepest curve and its design method. Background Technology

[0002] In existing water tank technology, conventional water tanks are mostly of regular geometric shapes (such as cuboids, cylinders, etc.), and their curved transitions often use simple arcs or no special curve design. These structures have shortcomings in terms of fluid capacity, stress distribution, and spatial adaptability. For example, regular-shaped water tanks have poor adaptability in some special installation spaces, and simple curved transitions lead to local stress concentration in the water tank, affecting its service life. When fluid flows and is stored in conventionally structured water tanks, problems such as dead water zones and large fluid disturbances are easily generated, which cannot meet the requirements of scenarios with higher performance requirements for fluid storage and transmission (such as cooling water tanks for high-precision experimental equipment and special fluid storage devices).

[0003] In existing technologies, traditional water tanks for firefighting aircraft have the following drawbacks: Patent CN110691734A discloses a multi-tank system for aerial firefighting aircraft. This patent mainly utilizes the lateral space of the cabin through a liquid storage tank structure with specific pipe segment combinations. However, the overall shape of the liquid storage tank is relatively fixed, and the curve design is relatively conventional. It is based on the combination of pipe segment angles and positions, and its adaptability is poor for some special and irregular spatial layouts.

[0004] Patent CN209464513U discloses a helicopter fire-fighting water tank and its installation structure. This patent relies on an inertia reduction plate to reduce the inertia of the water flow, but it has limited improvement on the complex flow patterns of fluid in the water tank (such as the optimization of the flow velocity distribution of fluid at different heights and in different areas) and the overall mechanical performance (such as stress concentration problems). The patent mainly focuses on improvements in automatic water intake and structural stability, but its functional expandability is limited.

[0005] Therefore, those skilled in the art are dedicated to developing an aviation fire extinguishing water tank based on the steepest curve design. By drawing on the principle of the steepest curve to construct the water tank outline and optimize the structural performance, the fire extinguishing medium inside the water tank can be discharged quickly, thereby reducing the total discharge time of the water tank and improving the discharge speed of the aviation fire extinguishing water tank, which is conducive to improving the efficiency of aviation fire extinguishing. Summary of the Invention

[0006] In view of the above-mentioned deficiencies of the prior art, the technical problem to be solved by the present invention is how to design an aviation fire extinguishing water tank by drawing on the principle of the fastest curve to improve its discharge speed.

[0007] To achieve the above objectives, the present invention provides an aviation fire extinguishing water tank based on the fastest curve, characterized in that it includes a tank body, a discharge port, and a filling port, wherein the tank body includes a side surface formed based on an upper contour line and a side surface formed based on a lower contour line, the upper contour line being constructed from the highest point to the lowest point of the upper contour line by a flipped fastest curve, and the lower contour line being constructed from the highest point to the lowest point of the lower contour line by a flipped fastest curve, and the tank body being installed on an aircraft.

[0008] Furthermore, the upper contour line is constructed using parametric equations: x = -A (t-sint), y = -A (t-cost) Where x is the horizontal axis direction in the front view of the box, t is the independent variable of the parametric equation, A is the radius of curvature of the upper contour line, and y is the vertical axis direction in the front view of the box.

[0009] Furthermore, the lower contour line is constructed using parametric equations: x = -B (t-sint), y = -B (t-cost) Wherein, B is the radius of curvature of the lower contour line, and the radius of curvature of the upper contour line is greater than the radius of curvature of the lower contour line.

[0010] Furthermore, the filling port is located at the very top of the housing.

[0011] Furthermore, the discharge port is located at the bottom of the housing, and is part of the bottom surface of the housing.

[0012] A design method for an aviation fire extinguishing water tank based on the steepest curve, characterized in that the method includes the following steps: Step 1: Construct the overall structure and set the parameters of the box using 3D modeling software; Step 2: Construct coordinate data. In the modeling software, take any point in space as the origin O and establish a three-dimensional coordinate system that satisfies the right-hand rule. Determine the start and end points of the upper and lower contour lines of the box. Construct the upper and lower contour lines through the parametric equations of the steepest curve. Step 3: Using the line connecting the left endpoints of the upper contour line and the lower contour line as the baseline, establish a first reference plane perpendicular to the YOZ plane; Step 4: Within the first reference plane, establish the left side of the box body; Step 5: Using the line connecting the lower endpoints of the upper contour line and the lower contour line as the baseline, establish a second reference plane perpendicular to the YOZ plane; Step 6: Establish the bottom surface of the box within the second reference plane; Step 7: Based on the left side and bottom shapes of the box established in Steps 4 and 6, and using the upper and lower contour lines established in Step 2 as guide lines, the side of the box is formed by lofting. Step 8: Based on the design software, calculate the size and volume of the water tank, and enlarge or reduce the model according to the actual target parameters to obtain the aviation fire extinguishing water tank based on the fastest curve under the rated size or volume.

[0013] Furthermore, in step 1, the parameters of the box include volume, length, width, and height.

[0014] Furthermore, in step 4, the left side cross-section of the water tank is rectangular or trapezoidal.

[0015] Furthermore, in step 6, the bottom cross-section of the box is rectangular or trapezoidal.

[0016] Furthermore, in step 7, the side surface includes a side surface formed based on the upper contour line, a side surface formed based on the lower contour line, a rear side surface, and a front side surface.

[0017] This invention has a high degree of technological maturity, clear application scenarios, and significant industrialization value and feasibility for transformation. Its beneficial technical effects are as follows: 1. Traditional aircraft fire extinguishing water tanks have slow discharge rates and uneven discharge. The brachytherapy curve, constructed from one point to another, converts gravitational potential energy into kinetic energy, achieving the shortest discharge time. This invention borrows the brachytherapy curve principle to construct the water tank outline and inverts the curve. In the initial discharge phase, a steep curve surface allows for rapid acquisition of a high initial velocity, resulting in a larger discharge volume at the beginning of the tank door opening. Later, the extinguishing medium gradually accelerates along the curve, achieving a higher exit velocity, thereby reducing the total discharge time of the water tank and increasing the discharge rate of the extinguishing medium within the aircraft fire extinguishing water tank, which is beneficial for improving the effectiveness of aircraft fire extinguishing.

[0018] 2. This invention optimizes fluid dynamics performance by employing a differentiated curvature design, significantly improving discharge efficiency. The discharge time for 95% of the extinguishing medium is reduced by 29%, and the first 85% of the discharge process maintains near-uniform flow. This improved discharge efficiency reduces firefighting operation time and enhances flight safety. The unique curved structure of this invention makes fluid flow more uniform, reducing dead zones and avoiding the local stagnation problem of traditional water tanks, thus improving extinguishing agent utilization. The water tank of this invention has strong space adaptability and is suitable for irregular installation environments (such as narrow aircraft cabins). Compared to traditional water tanks, its length is reduced by 32% and its width by 15%, resulting in higher space utilization. The 300ml spherical fire extinguishing bag has a filling rate of 57.2%, which is close to the filling rate of traditional water tanks (58.6%) while occupying less space.

[0019] 3. The manufacturing process of this invention is mature, employing CNC machining (cutting, bending, welding) and CAD optimized design, making it suitable for mass production; the material selection is flexible, allowing for the use of metals (aluminum alloy, stainless steel) or high-strength plastics to meet different corrosion resistance requirements; the application scenarios are wide-ranging, including not only aviation fire fighting, but also high-precision instrument cooling water tanks, chemical fluid storage, etc.

[0020] The following will further explain the concept, specific structure, and technical effects of the present invention in conjunction with the accompanying drawings, so as to fully understand the purpose, features, and effects of the present invention. Attached Figure Description

[0021] Figure 1 This is a schematic diagram of the structure of an aviation fire extinguishing water tank based on the fastest curve, which is a preferred embodiment of the present invention. Figure 2 This is a comparison chart of the discharge curves of an aviation fire extinguishing water tank based on the steepest curve of a preferred embodiment of the present invention and the discharge curves of fire extinguishing aircraft water tanks in the prior art. Figure 3 This is a comparison diagram of the design parameters of an aviation fire extinguishing water tank based on the steepest curve in a preferred embodiment of the present invention and fire extinguishing aircraft water tanks in the prior art. Figure 4 This is a schematic diagram of the structure of the water tank of a certain type of firefighting aircraft in the prior art; Among them, 1-side surface formed by the upper contour line, 2-side surface formed by the lower contour line, 3-left side surface, 4-bottom surface, 5-rear side surface, 6-front side surface. Detailed Implementation

[0022] The following description, with reference to the accompanying drawings, illustrates several preferred embodiments of the present invention to make its technical content clearer and easier to understand. The present invention can be embodied in many different forms, and the scope of protection of the present invention is not limited to the embodiments mentioned herein.

[0023] In the accompanying drawings, components with the same structure are indicated by the same numerical designation, and components with similar structures or functions are indicated by similar numerical designations. The dimensions and thicknesses of each component shown in the drawings are arbitrary, and the present invention does not limit the dimensions and thicknesses of each component. To make the illustrations clearer, the thickness of some components is appropriately exaggerated in the drawings.

[0024] This invention relates to an aviation fire extinguishing water tank based on the fastest curve, the shape and structure of which are as follows: Figure 1 As shown, the tank includes a housing, a discharge port, and a filling port. The housing includes a side 1 formed based on an upper contour line, a side 2 formed based on a lower contour line, a left side 3, a bottom surface 4, a rear side 5, and a front side 6. The upper contour line is constructed from the highest point to the lowest point of the upper contour line by a steepest curve of rotation. The lower contour line is constructed from the highest point to the lowest point of the lower contour line by a steepest curve of rotation. The discharge port is located on the bottom surface 4 at the bottom of the water tank, and the filling port is located on the left side surface 3 at the top of the water tank. The cross-section of the bottom of the water tank is rectangular, trapezoidal, or any other arbitrary shape. The housing is installed on an aircraft.

[0025] The design process for this water tank is as follows: Step 1: Using the known volume of a certain type of water tank as a constraint, set the target water tank volume to 9.34 m³. 3 ; Step 2: In the modeling software, establish a 3D coordinate system that satisfies the right-hand rule, with any point in space as the origin O. Construct the following two parametric equations in the XOY plane. The parametric equation of the upper contour line is x = -A. (t-sint), y= -A (t-cost), t∈[0,π], the parametric equation of the lower contour line is x = -B (t-sint), y = -B (t-cost), t∈[0,π]; where x is the horizontal axis direction in the front view of the box, t is the independent variable of the parametric equation, A is the radius of curvature of the upper contour line, y is the vertical axis direction in the front view of the box, A is the radius of curvature of the upper contour line, B is the radius of curvature of the lower contour line, A>B, in this embodiment, A=150mm, B=100mm.

[0026] Step 3: Connect the left endpoint of the upper contour line and the left endpoint of the lower contour line to construct the first baseline. Based on the first baseline, establish the first reference plane perpendicular to the YOZ plane. Step 4: On the first reference plane, with the left endpoints of the upper and lower contour lines as the center, draw a rectangle with a length of 150 mm and a width of 100 mm as the left side face 3 of the water tank. Step 5: Using the line connecting the lower endpoint of the upper contour line and the lower endpoint of the lower contour line of the water tank as the second baseline, establish a second reference plane perpendicular to the YOZ plane; Step 6: In the second reference plane, with the left endpoints of the upper contour line and the left endpoints of the lower contour line as the center, draw a rectangle with a length of 100 mm and a width of 100 mm as the bottom surface 4 of the water tank. Step 7: Based on the shapes of the left side 3 and bottom 4 established in Step 4 and Step 6, and using the upper and lower contour lines of the water tank established in Step 2 as guide lines, the side of the aviation fire extinguishing water tank based on the fastest curve is formed by lofting. The side includes side 1 formed based on the upper contour line, side 2 formed based on the lower contour line, rear side 5 and front side 6. Step 8: Using design software, calculate the dimensions and volume of the water tank. Then, scale the model up or down according to actual target parameters, such as maximum size constraints and minimum volume constraints, to obtain the water tank based on a fast curve at its rated size or volume. In this embodiment, the calculated volume of the water tank is 5840.7 cm³. 3 Based on the actual target volume, the model's magnification is 11.695 times. Through this scaling, the water tank volume is 9.34 m³. 3 This allows us to obtain a water tank with the same volume as a known water tank model based on a fast curve.

[0027] Step 9, Performance Verification: The water tank volume is 9.34 m³. 3 The water tank is 4.84 m long, 1.75 m wide, and 3.48 m high. When filled with 300 ml spherical fire extinguishing bags, it can hold 18,018 bags, achieving a filling rate of 57.85%. A comparison of the parameters of the water tank of this invention with those of a certain model of water tank in a fire-fighting aircraft in the prior art is provided. Figure 3 As shown.

[0028] The structure of the water tank of a certain type of firefighting aircraft in the prior art is as follows: Figure 4 As shown, the optimized water tank, with the same volume as the existing real water tank, has a 32% reduction in length, a 15% reduction in width, and a 16% increase in height, while maintaining a roughly the same fill rate. The time required to achieve a 95% discharge rate is reduced by 29%. The discharge curves are comparable. Figure 2 As shown, the optimized water tank maintains a good uniform discharge rate in the first 85% of the discharge process, fully demonstrating that the water tank based on the fastest curve has a good fire extinguishing medium discharge capability, verifying the innovation and advantages of the present invention.

[0029] The preferred embodiments of the present invention have been described in detail above. It should be understood that those skilled in the art can make numerous modifications and variations based on the concept of the present invention without creative effort. Therefore, all technical solutions that can be obtained by those skilled in the art based on the concept of the present invention through logical analysis, reasoning, or limited experimentation on the basis of existing technology should be within the scope of protection defined by the claims.

Claims

1. An aviation fire extinguishing water tank based on the steepest curve, characterized in that, The container includes a housing, an outlet, and a filling port. The housing includes a side surface formed based on an upper contour line and a side surface formed based on a lower contour line. The upper contour line is constructed from the highest point to the lowest point of the upper contour line by a steepest-rate curve of rotation. The lower contour line is constructed from the highest point to the lowest point of the lower contour line by a steepest-rate curve of rotation. The housing is installed on an aircraft.

2. The aviation fire extinguishing water tank based on the fastest curve as described in claim 1, characterized in that, The upper contour line is constructed using parametric equations: x = -A (t-sint),y = -A (t-cost) Where x is the horizontal axis direction in the front view of the box, t is the independent variable of the parametric equation, A is the radius of curvature of the upper contour line, and y is the vertical axis direction in the front view of the box.

3. An aviation fire extinguishing water tank based on the fastest curve as described in claim 2, characterized in that, The lower contour line is constructed using parametric equations: x = -B (t-sint),y = -B (t-cost) Wherein, B is the radius of curvature of the lower contour line, and the radius of curvature of the upper contour line is greater than the radius of curvature of the lower contour line.

4. An aviation fire extinguishing water tank based on the fastest curve as described in claim 1, characterized in that, The filling port is located at the very top of the box.

5. An aviation fire extinguishing water tank based on the fastest curve as described in claim 1, characterized in that, The discharge port is located at the bottom of the housing and is part of the bottom surface of the housing.

6. A design method for an aviation fire extinguishing water tank based on the steepest curve as described in any one of claims 1 to 5, characterized in that, The method includes the following steps: Step 1: Construct the overall structure and set the parameters of the box using 3D modeling software; Step 2: Construct coordinate data. In the modeling software, take any point in space as the origin O and establish a three-dimensional coordinate system that satisfies the right-hand rule. Determine the start and end points of the upper and lower contour lines of the box. Construct the upper and lower contour lines through the parametric equations of the steepest curve. Step 3: Using the line connecting the left endpoints of the upper contour line and the lower contour line as the baseline, establish a first reference plane perpendicular to the YOZ plane; Step 4: Within the first reference plane, establish the left side of the box body; Step 5: Using the line connecting the lower endpoints of the upper contour line and the lower contour line as the baseline, establish a second reference plane perpendicular to the YOZ plane; Step 6: Establish the bottom surface of the box within the second reference plane; Step 7: Based on the left side and bottom shapes of the box established in Steps 4 and 6, and using the upper and lower contour lines established in Step 2 as guide lines, the side of the box is formed by lofting. Step 8: Based on the design software, calculate the size and volume of the water tank, and enlarge or reduce the model according to the actual target parameters to obtain the aviation fire extinguishing water tank based on the fastest curve under the rated size or volume.

7. The design method for an aviation fire extinguishing water tank based on the steepest curve as described in claim 6, characterized in that, In step 1, the parameters of the box include volume, length, width, and height.

8. The design method for an aviation fire extinguishing water tank based on the steepest curve as described in claim 6, characterized in that, In step 4, the left side cross-section of the water tank is rectangular or trapezoidal.

9. The design method for an aviation fire extinguishing water tank based on the steepest curve as described in claim 6, characterized in that, In step 6, the bottom cross-section of the box is rectangular or trapezoidal.

10. The design method for an aviation fire extinguishing water tank based on the steepest curve as described in claim 6, characterized in that, In step 7, the side surface includes a side surface formed based on the upper contour line, a side surface formed based on the lower contour line, a rear side surface, and a front side surface.

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