Water surface aircraft dampening reference model

Abstract

The utility model discloses a water surface aircraft dampening benchmark model, which is formed by a water surface aircraft appearance through shell extraction, the water surface aircraft appearance after shell extraction is divided into a fuselage part, a wing part, a buoy part, a flat tail part and a vertical tail part, the fuselage part is provided with a smooth hull, the hull comprises a fuselage step front body and a fuselage step rear body, and the fuselage step front body is provided with a flat tail part. A fault step is arranged at the joint of the fuselage fault step front body and the fuselage fault step rear body, the oblique lead angle of the fault step is 21 degrees, and the trailing edge angle of the fuselage fault step rear body is 7 degrees; and the mounting angle of the wing component is 3 degrees. The model provided by the utility model is light in weight, and the weight and rotational inertia of the model are similar to those of a real machine in Fourier.

Description

Technical Field

[0001] This utility model belongs to the field of water load testing technology for amphibious aircraft models, and particularly relates to a water landing reference model for a water surface aircraft. Background Technology

[0002] Existing surface aircraft come in a wide variety of shapes and characteristics, and their design concepts are all aimed at meeting various functional requirements. Therefore, when conducting research on various surface aircraft, model tests and numerical simulations are often only conducted for specific configurations and specific operating conditions, and a unified verification standard is often not obtained. Utility Model Content

[0003] Utility Model Purpose

[0004] To address the requirements of load testing for surface aircraft and the challenges of simulation, this invention provides a water-landing reference model for surface aircraft.

[0005] Utility Model Technical Solution

[0006] A water-landing reference model for a surface-to-water aircraft is provided. The model is formed by removing the shell from the surface-to-water aircraft shape. After shell removal, the surface-to-water aircraft shape is divided into fuselage components, wing components, float components, horizontal tail components, and vertical tail components. The fuselage components have a smooth hull, which includes a stepped front fuselage and a stepped rear fuselage. The stepped front fuselage and the stepped rear fuselage are joined by a step with a lift angle of 21 degrees. The trailing edge angle of the stepped rear fuselage is 7 degrees. The wing components have an installation angle of 3 degrees.

[0007] Preferably, the fuselage components, wing components, float components, horizontal stabilizer components, and vertical stabilizer components are all framed by several bulkheads connected by carbon fiber tubes, and the outer surface of the frame is fixed with skin. Weight reduction holes can be provided in the bulkheads as needed.

[0008] Preferably, the test center of gravity adjustment aluminum plate is connected to the frame of the fuselage component, and the center of the test center of gravity adjustment aluminum plate is located at the center of gravity of the fuselage component.

[0009] Preferably, the internal frames of the fuselage components are also connected by stringers.

[0010] Preferably, 13 horizontal partitions are provided inside the fuselage component, which are arranged sequentially from the tail of the fuselage component to the head of the fuselage component 1 as the first horizontal partition to the thirteenth horizontal partition. The first horizontal partition to the thirteenth horizontal partition are connected by a first carbon nanotube assembly, and the first horizontal partition to the fourth horizontal partition are also connected by a second carbon nanotube assembly.

[0011] Preferably, the wing components include left and right wings, and the spacers at the connection points between the left and right wings and the fuselage components are connected by a third carbon fiber assembly. The spacers inside the left and right wings are connected by a fourth carbon fiber assembly and a fifth carbon fiber assembly, respectively, and each spacer is fixed to the skin by a stringer.

[0012] Preferably, the tail section has five horizontal tail frames arranged from top to bottom inside, and the tail frames are connected by several longitudinally arranged stringers and carbon tubes.

[0013] Preferably, a sleeve is fixed at the intersection of the rotation axis of the horizontal tail component and the skin of the vertical tail component, and all the partitions in the horizontal tail component are connected by supporting carbon tubes.

[0014] Preferably, the tail section includes left and right tail sections, and the partitions within the left and right tail sections are connected by support struts.

[0015] Preferably, the partitions inside the horizontal tail section and the vertical tail section are made of 3mm thick aviation plywood or 3mm thick linden wood.

[0016] Advantages of this invention: The model of this invention is lightweight, and its weight and moment of inertia are similar to those of the actual machine, satisfying Fourier's law. Attached Figure Description

[0017] Figure 1 This is a schematic diagram of a water-based landing reference model for a surface-to-water aircraft.

[0018] Figure 2 This is a schematic diagram of the sliding surface at the step break in the fuselage.

[0019] Figure 3 This is a dimensional drawing of the front and rear fuselage components.

[0020] Figure 4 This is a schematic diagram of the wing component installation.

[0021] Figure 5 This is a schematic diagram of the internal structure of the fuselage components.

[0022] Figure 6 This is a schematic diagram of the internal structure of the wing component.

[0023] Figure 7 This is a schematic diagram of the vertical tail component.

[0024] Figure 8 This is a schematic diagram of the internal structure of the horizontal tail section. Detailed Implementation

[0025] This utility model is achieved through the following technical solution.

[0026] A water-landing reference model for a surface aircraft is provided. Based on the characteristics of the water-landing model of a surface aircraft, the shape of the surface aircraft is extracted in 3D modeling software, and the shape is divided into fuselage component 1, wing component 2, float component 3, horizontal tail component 4, and vertical tail component 5.

[0027] The fuselage component 1 has a smooth hull, which includes a stepped front fuselage 1-1 and a stepped rear fuselage 1-3. The junction of the stepped front fuselage 1-1 and the stepped rear fuselage 1-3 is stepped. The planing surface of the stepped front fuselage 1-1 has no bilge, and the angle of ascent at the step is 21 degrees (the angle between the planing surface at the step and the baseline is 21 degrees). In this embodiment, the length of the stepped front fuselage 1-1 is 1551.26 mm, the length of the stepped rear fuselage 1-3 is 2027.99 mm, and the length ratio of the stepped front fuselage 1-1 to the stepped rear fuselage 1-3 is 0.765.

[0028] The keel of the fuselage stepped forebody 1-1 has a straight section 1-2 that gradually curves toward the bow. The straight section 1-2 is 802.8 mm long, and its ratio to the total length of the fuselage stepped forebody 1-1 is 0.517.

[0029] The trailing edge angle of fuselage step 1-3 is 7 degrees.

[0030] Thirteen horizontal partitions are installed inside fuselage component 1 (see...). Figure 5 The transverse bulkheads are made of aerospace-grade laminate. From the tail to the head of fuselage component 1, the transverse bulkheads are arranged sequentially from the first transverse bulkhead 1-4 to the thirteenth transverse bulkhead 1-16. The seventh transverse bulkhead 1-10 to the ninth transverse bulkhead 1-12 are 5mm thick, and a test center-of-gravity adjustment aluminum plate (whose center is located at the center of gravity of fuselage component 1) is fixed between the seventh and eighth transverse bulkheads 1-10. The remaining transverse bulkheads are 3mm thick. The transverse bulkheads are bonded to the skin and to the carbon fiber tubes using adhesive bonding. The transverse bulkheads are also connected by stringers to increase overall strength.

[0031] To ensure the longitudinal strength of fuselage component 1, two sets of carbon tubes are symmetrically arranged inside fuselage component 1. The first set of carbon tubes 1-18 has a specification of 20 (outer diameter) × 18 mm (inner diameter) and a length of 2000 mm. The second set of carbon tubes 1-17 has a specification of 20 (outer diameter) × 18 mm (inner diameter) and a length of 1000 mm. The first set of carbon tubes 1-18 is nested within frames 1-6 to 1-16 to form the main carbon tubes of the fuselage, which are used to ensure the overall longitudinal strength of the nose, front fuselage, middle fuselage, and middle and rear fuselage. The second set of carbon tubes 1-17 passes through the first transverse partition frame 1-4 to the fourth transverse partition frame 1-7, which are used to ensure the overall strength of the middle and rear fuselage and the rear fuselage. The two sets of carbon tubes are fixed to the transverse partition frames by adhesive bonding. The arrangement of the fuselage transverse partition frames and the two sets of carbon tubes is shown in the figure. Figure 6 .

[0032] The connection between wing component 2 and fuselage component 1 is formed by four metal bulkheads 2-3, which together connect the left and right wing frames into a single unit via a third carbon fiber assembly. This carbon fiber assembly measures 30mm (outer diameter) × 28mm (inner diameter), increasing the overall strength of wing component 2. The nacelle section on wing component 2 is framed by bulkhead 2-1. Two additional frame frames are located on the outermost side of wing component 2. The bulkheads within the left and right wings are connected by the fourth and fifth carbon fiber assemblies, respectively, with carbon fiber measuring 20mm (outer diameter) × 18mm (inner diameter). Corresponding stringers connect and secure the bulkheads to the skin.

[0033] Wing component 2 adopts a high-lift airfoil, and the installation angle of wing component 2 is 3 degrees.

[0034] The upper surface of wing component 2 is made of two layers of carbon fiber composite material wing skin bonded to the internal partition of wing component 2.

[0035] The float component 3 is composed of two 3mm thick aviation-grade laminate frames with built-in wooden blocks, and is connected to the wing component 2 via 10mm diameter carbon fiber tubes.

[0036] The vertical tail component 5 is composed of two 12mm diameter carbon fiber tubes 5-3 and a vertical tail bulkhead 5-1 made of 3mm thick aviation laminate or 3mm thick linden wood, which are cross-combined and connected to the fuselage component 1.

[0037] To ensure the strength of the vertical tail structure 5 and its firm connection with the fuselage component 1, five horizontal vertical tail frames 5-1 are arranged sequentially from top to bottom inside the vertical tail component 5. Three stringers 5-2 are arranged longitudinally to connect the vertical tail frames 5-1 into an integral frame to increase the overall strength. Two vertical carbon tubes are arranged longitudinally, with a specification of 10mm (outer diameter) × 8mm (inner diameter), and extend into the lower fuselage skin.

[0038] The horizontal tail component 4 is composed of two 12mm diameter supporting carbon tubes 4-2 and eight horizontal tail bulkheads 4-1 made of 3mm thick aviation floorboards or 3mm thick linden wood boards.

[0039] The horizontal tail component 4 is made of a single layer of carbon fiber composite material and is bonded to the horizontal tail frame 4-1.

[0040] To address the connection issue with the horizontal tail component 4, a sleeve is installed at the intersection of the horizontal tail component 4's rotation axis and the vertical tail component 5's skin. The sleeve is glued and fixed to the corresponding skin location. A horizontal tail carbon tube 4-2 is rotatably mounted inside the sleeve, facilitating the horizontal tail's rotation around its axis. The sleeve uses a carbon tube with dimensions of 14mm (outer diameter) × 12mm (inner diameter), while the supporting carbon tube 4-2 has dimensions of 12mm (outer diameter) × 10mm (inner diameter), allowing the horizontal tail to fit snugly onto the supporting carbon tube 4-2.

[0041] To ensure the strength of the horizontal tail component 4 and its secure connection with the vertical tail, four partitions are arranged on each of the left and right horizontal tails. Because the skin used for the horizontal tail is relatively thin, to prevent the ends of the horizontal tail from collapsing and deforming, two support struts 4-3 (made of 3mm thick linden wood board) and one support carbon tube 4-2 are arranged in the longitudinal direction on the horizontal tail component 4. The support carbon tube 4-2 has a specification of 12mm (inner diameter) × 10mm (inner diameter) and runs through all the partitions of the entire horizontal tail. At the same time, the sleeve fixed on the vertical tail is inserted into the support carbon tube 4-2 in the horizontal tail to realize the rotation of the horizontal tail.

[0042] The scope of protection of this utility model is not limited to the above-described embodiments. Obviously, those skilled in the art can make various modifications and variations to this utility model without departing from its scope. If these modifications and variations fall within the scope of the claims of this utility model and their equivalents, then the intent of this utility model also includes these modifications and variations.

Claims

1. A water-landing reference model for a surface-to-air vehicle, characterized in that, The model is formed by shelling the shape of a waterplane. After shelling, the shape of the waterplane is divided into fuselage (1), wing (2), float (3), horizontal tail (4), and vertical tail (5). The fuselage (1) has a smooth hull, which includes a stepped fuselage front body (1-1) and a stepped fuselage rear body (1-3). The stepped fuselage front body (1-1) and the stepped fuselage rear body (1-3) are connected by a step, and the angle of ascent at the step is 21 degrees. The trailing edge angle of the stepped fuselage rear body (1-3) is 7 degrees. The wing (2) has an installation angle of 3 degrees.

2. The water-landing reference model for a surface aircraft as described in claim 1, characterized in that, The fuselage component (1), wing component (2), float component (3), horizontal tail component (4), and vertical tail component (5) are all framed by several partitions connected by carbon tubes, and the outer surface of the frame is fixed with skin.

3. The water-landing reference model for a surface aircraft as described in claim 2, characterized in that, The test center of gravity adjustment aluminum plate is connected to the frame of the fuselage component (1), and the center of the test center of gravity adjustment aluminum plate is located at the center of gravity of the fuselage component (1).

4. The water-landing reference model for a surface aircraft as described in claim 2, characterized in that, The internal frames of the fuselage component (1) are also connected by stringers.

5. The water-landing reference model for a surface aircraft as described in claim 2, characterized in that, Thirteen transverse partitions are arranged inside the fuselage component (1). From the tail of the fuselage component (1) to the head of the fuselage component (1), they are the first transverse partition (1-4) to the thirteenth transverse partition (1-16). The first transverse partition (1-4) to the thirteenth transverse partition (1-16) are connected by the first carbon nanotube assembly (1-18). The first transverse partition (1-4) to the fourth transverse partition (1-7) are also connected by the second carbon nanotube assembly (1-17).

6. The water-landing reference model for a surface aircraft as described in claim 1, characterized in that, The wing component (2) includes left and right wings. The spacers at the connection points between the left and right wings and the fuselage component (1) are connected by a third carbon tube group. The spacers inside the left and right wings are connected by a fourth carbon tube group and a fifth carbon tube group, respectively. Each spacer is fixed to the skin by a stringer.

7. The water-landing reference model for a surface aircraft as described in claim 1, characterized in that, The vertical tail component (5) has five horizontal vertical tail frames (5-1) arranged from top to bottom inside. The vertical tail frames (5-1) are connected to carbon tubes by several longitudinally arranged stringers (5-2).

8. The water-landing reference model for a surface aircraft as described in claim 1, characterized in that, A sleeve is fixed at the intersection of the rotation axis of the flat tail component (4) and the skin of the vertical tail component (5). The flat tail carbon tube (4-2) is rotatably installed inside the sleeve. All the partitions inside the flat tail component (4) are connected by the supporting carbon tube (4-2).

9. A water-landing reference model for a surface aircraft as described in claim 8, characterized in that, The tail section (4) includes left and right tail sections, and the partitions inside the left and right tail sections are connected by support struts (4-3).

10. A water-landing reference model for a surface aircraft as described in claim 1, characterized in that, The partitions inside the horizontal tail component (4) and vertical tail component (5) are made of 3mm thick aviation plywood or 3mm thick linden wood.

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