Airplane vertical fin damping device based on shape memory alloy net-shaped non-planar weaving and integrated compression molding method thereof

Abstract

The invention discloses an aircraft vertical fin damping device based on shape memory alloy net-shaped non-planar weaving and an integrated compression molding method of the aircraft vertical fin damping device, and relates to the technical field of aviation composite material structures, the aircraft vertical fin damping device comprises a composite material combined thin-wall plate, and the appearance of the composite material combined thin-wall plate is matched with a curved surface structure of a vertical stabilizer of a new energy aircraft; the non-planar net-shaped woven shape memory alloy steel wire rope vibration reduction unit is formed by weaving horizontal memory alloy steel wire ropes and vertical memory alloy steel wire ropes in a transverse and longitudinal staggered mode. The integral forming mould pressing system comprises an inner surface forming mould, an outer surface forming mould, a bottom plate and a steel wire rope clamping device; the epoxy resin adhesive is used for bonding and curing the vibration reduction unit and the composite material thin-wall plate, the vibration reduction device and the composite material vertical fin are integrally formed through a mold pressing process, the additional weight and installation space occupation of a traditional externally-hung device are avoided, and additional energy supply is not needed based on the passive vibration reduction characteristic of the shape memory alloy.

Description

Technical Field

[0001] This invention relates to the field of aerospace composite material structure technology, specifically to an aircraft vertical tail vibration damping device based on shape memory alloy mesh non-planar weaving and its integrated molding method. Background Technology

[0002] In the high-end equipment manufacturing fields such as aerospace and vehicle engineering, the large-scale production of composite thin-walled plate structures is underway.

[0003] Applications place higher demands on their adaptability to operating conditions. Taking the composite vertical stabilizer of new energy aircraft as an example, this type of typical load-bearing component is prone to vibration response under external impact loads or continuous excitation, leading to material performance degradation or even structural damage. Traditional solutions mainly focus on technical routes such as high-performance substrate selection, topology optimization, and local thickening reinforcement, but there are multiple technical bottlenecks in practical engineering applications: the selection of high-performance substrates is constrained by the supply chain system, complex structural designs increase the difficulty of process implementation, and thickness compensation schemes are fundamentally in conflict with lightweight design concepts.

[0004] To address the aforementioned technical challenges, the industry needs to develop innovative vibration reduction solutions for aerospace composite material components.

[0005] The design, in particular, needs to meet the synergistic optimization requirements of structural adaptability, process simplicity, lightweight indicators, and integrated molding process. Although existing vibration suppression devices can achieve basic vibration reduction, they generally suffer from problems such as large installation space occupation and strong dependence on additional energy, making it difficult to adapt to the design requirements of compact layout and energy efficiency optimization of new energy aircraft.

[0006] This technical solution proposes a mesh-like non-planar braided vibration damping device based on shape memory alloy steel wire rope, and develops a matching integral molding process for composite material vertical tail structures. This solution combines excellent mechanical properties with significant vibration resistance advantages, achieving structural-functional integration of the vibration damping unit and the load-bearing structure in both manufacturing process and functional implementation. It effectively solves the contradiction between increased structural weight and functional loss in traditional methods. Summary of the Invention

[0007] To address the shortcomings of existing technologies, this invention provides an aircraft vertical tail vibration damping device based on shape memory alloy mesh non-planar weaving and its integrated molding method. This solves the problem that load-bearing components in existing technologies are prone to vibration response under external impact loads or continuous excitation, leading to material performance degradation or even structural damage. Traditional solutions mainly focus on high-performance substrate selection, topology optimization, and local thickening reinforcement, but these approaches face multiple technical bottlenecks in practical engineering applications: the selection of high-performance substrates is constrained by the supply chain system, complex structural designs increase the difficulty of process implementation, and thickness compensation schemes fundamentally conflict with lightweight design concepts.

[0008] To achieve the above objectives, the present invention provides the following technical solution: an aircraft vertical tail vibration damping device based on shape memory alloy mesh non-planar braiding, comprising:

[0009] Composite thin-walled panels: their shape is adapted to the curved structure of the vertical stabilizer of new energy aircraft;

[0010] Non-planar mesh braided shape memory alloy steel wire rope vibration damping unit: It is composed of horizontal and vertical shape memory alloy steel wire ropes woven in a cross pattern;

[0011] Integrated molding system: includes inner surface molding mold, outer surface molding mold, base plate and wire rope clamping device;

[0012] Epoxy resin adhesive: used to bond and cure vibration damping units to composite thin-walled panels;

[0013] The non-planar mesh braided shape memory alloy steel wire rope vibration damping unit is integrally formed with a composite material thin-walled plate through a molding process and is perpendicular to the inner surface molding mold or the outer surface molding mold.

[0014] Preferably, the horizontal and vertical shape memory alloy wire ropes are composed of one nickel-titanium alloy wire twisted together with six stainless steel wires, with a diameter of 0.6 mm, wherein the nickel-titanium mass ratio of the nickel-titanium alloy is 60:40.

[0015] Preferably, the non-planar mesh braided shape memory alloy steel wire rope vibration damping unit comprises: a combination structure of an inclined parallelogram plate and a straight right-angled trapezoid plate, wherein the inclined parallelogram plate has a width of 200mm and an inclined angle of 86°, the straight right-angled trapezoid plate has a long side of 300mm and a short side of 200mm, and the widest part of the combination plate is 60mm.

[0016] Preferably, the wire rope clamping device comprises:

[0017] Clamping assembly for inner surface forming: including inclined vertical rope clamping bottom block and inclined vertical rope clamping top block, flat vertical rope clamping bottom block and flat vertical rope clamping top block, horizontal rope clamping bottom strip and horizontal rope clamping top strip, inner surface V-shaped clamping block and V-shaped clamping block fixing strip;

[0018] Both the inclined vertical rope clamping base block and the planar vertical rope clamping base block are provided with a semi-circular lower groove and a semi-circular upper groove;

[0019] Both the inclined vertical rope clamping top block and the planar vertical rope clamping top block are equipped with U-shaped convex semi-cylinders;

[0020] Clamping assembly for outer surface forming: including inclined vertical rope clamping bottom block and inclined vertical rope clamping top block, flat vertical rope clamping bottom block and flat vertical rope clamping top block, flat vertical rope top clamping block, horizontal rope clamping top bar and V-shaped clamping block fixing bar.

[0021] Preferably, the composite material thin-walled panel uses T700 carbon fiber prepreg, with an even number of layers (≥4), a single layer thickness of 0.1 mm, and a symmetrical design of layup angles of [0 / 90 / 0 / 90 / 0] or [0 / 45 / 90 / -45 / 0].

[0022] Preferably, the epoxy resin adhesive comprises bisphenol A type E51 epoxy resin and polyetheramine D230 curing agent in a mass ratio of 3.3:1, with a single coating amount of 5-10g.

[0023] An aircraft vertical tail vibration damping device based on shape memory alloy mesh non-planar braiding and its integrated molding method are characterized by the following steps:

[0024] Step 1: Lay a release cloth on the surface of the mold;

[0025] Step 2: Lay the carbon fiber prepreg according to the designed angle;

[0026] Step 3: Secure the horizontal portion of the mesh wire rope using the clamping device;

[0027] Step 4: Weave and fix the vertical part of the mesh steel wire rope;

[0028] Step 5: Apply epoxy resin and cure at room temperature for 4-6 hours;

[0029] Step 6: After removing the clamping device, autoclave molding is performed with the parameters set to 4 standard atmospheres, 120-150℃, and 3-6 hours.

[0030] Preferably, in step 3, the horizontal shape memory alloy steel wire rope is positioned by the inner surface V-shaped clamping block and the V-shaped clamping block fixing strip, and the clamping force is provided by the bolt connection.

[0031] Preferably, in step 4, the vertical shape memory alloy steel wire rope is positioned on the curved surface by means of a combination of a semi-circular groove and a U-shaped convex semi-cylinder clamping structure using a "threading the needle" method.

[0032] Preferably, the autoclave is vacuum-sealed during molding, and the vacuum bag is made of Teflon-based release fabric with a thickness of 0.18 mm.

[0033] Preferably, the non-planar mesh braided shape memory alloy steel wire rope vibration damping unit provides a nonlinear damping force Fnet=Δnet(k1x+k3x) 3 +c1 ), where Δnet is the position weight function, preferably the Dirac function, and k1, k3, c1, r 21 r 12 The parameters are taken from Table 1.

[0034] Preferably, the value of k1 ranges from 1167.8 to 1265.4 N / m, and the value of k3 ranges from 1.42 × 10⁻⁶ N / m. 8 -7.57×10 8 N / m 3 The value of c1 ranges from 21.12 to 28.76 N·s / m.

[0035] This invention provides an aircraft vertical tail vibration damping device based on shape memory alloy mesh non-planar weaving and its integrated molding method, which has the following beneficial effects:

[0036] Structure-Function Integration

[0037] The vibration damping device and the composite material vertical tail are integrally molded through a molding process, avoiding the additional weight and installation space occupation of traditional external devices.

[0038] Lightweight design compatibility

[0039] The lightweight shape memory alloy steel wire rope (0.6mm in diameter) is used to achieve vibration reduction without conflicting with the lightweight design.

[0040] Adaptability to complex surfaces

[0041] Non-planar weaving technology can match the combination structure of inclined and planar surfaces of vertical stabilizing surfaces.

[0042] No external energy dependence

[0043] Based on the passive vibration reduction properties of shape memory alloys, no additional energy supply is required.

[0044] Simplicity of process

[0045] A dedicated clamping device enables synchronous positioning of the wire rope and prepreg, simplifying the process.

[0046] Multifunctional clamping device

[0047] A composite clamping system using a U-shaped semi-cylindrical clamping group and a V-shaped prism clamping group is adopted to achieve more stable fastening and clamping of shape memory alloy steel wire rope.

[0048] Material performance optimization

[0049] Nickel-titanium alloy steel wire rope combines fatigue resistance and strong hysteresis energy dissipation characteristics, thus improving vibration reduction efficiency. Attached Figure Description

[0050] Figure 1This is a schematic diagram of the structure of the mesh non-planar braided shape memory alloy steel wire rope of the present invention;

[0051] Figure 2 This is a cross-sectional view of the nickel-titanium alloy steel wire rope of the present invention;

[0052] Figure 3 This is a flowchart of the integral molding process of the present invention;

[0053] Figure 4 This is a schematic diagram of the process for integrally molding the inner surface of the present invention;

[0054] Figure 5 This is an exploded view of the parts of the integral molding system for the inner surface of the present invention;

[0055] Figure 6 This invention relates to a vertical steel wire rope clamping assembly with an inner inclined surface.

[0056] Figure 7 This is a schematic diagram of the processing of integral molding of the outer surface of the present invention;

[0057] Figure 8 This is an exploded view of the parts of the integral molding system for the outer surface of the present invention;

[0058] Figure 9 This invention relates to a vertical steel wire rope clamping assembly with an outer surface inclined plane.

[0059] Figure 10 This is a cross-sectional view of the vertical steel wire rope clamping assembly on the inner surface of the present invention;

[0060] Figure 11 This is a cross-sectional view of the inner surface horizontal steel wire rope clamping assembly of the present invention;

[0061] Figure 12 This is a cross-sectional view of the vertical steel wire rope clamping assembly on the outer surface of the present invention;

[0062] Figure 13 This is a cross-sectional view of the horizontal steel wire rope clamping assembly on the outer surface of the present invention.

[0063] In the diagram: 101: Horizontal shape memory alloy steel wire rope; 102: Vertical shape memory alloy steel wire rope; 201: Composite material composite thin-walled plate; 301: Inner surface forming mold; 302: Inclined vertical rope clamping bottom block; 303: Inclined vertical rope clamping top block; 304: Planar vertical rope clamping bottom block; 305: Planar vertical rope clamping top block; 306: Horizontal rope clamping bottom strip; 307: Horizontal rope clamping top strip; 30... 8: Inner surface V-shaped clamping block; 309: V-shaped clamping block fixing strip; 401: Outer surface forming mold; 402: Inclined vertical rope clamping bottom block; 403: Inclined vertical rope clamping top block; 405: Planar vertical rope clamping bottom block; 406: Planar vertical rope clamping top block; 407: Planar vertical rope top clamping block; 408: Horizontal rope clamping top strip; 409: V-shaped clamping block fixing strip; 410: Base plate. Detailed Implementation

[0064] The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0065] Please see Figure 1-13 This invention provides a technical solution: an aircraft vertical tail vibration damping device based on shape memory alloy mesh non-planar weaving, comprising:

[0066] Composite thin-walled panels: their shape is adapted to the curved structure of the vertical stabilizer of new energy aircraft;

[0067] Non-planar mesh braided shape memory alloy steel wire rope vibration damping unit: It is composed of horizontal and vertical shape memory alloy steel wire ropes woven in a cross pattern;

[0068] Integrated molding system: includes inner surface molding mold, outer surface molding mold, base plate and wire rope clamping device;

[0069] Epoxy resin adhesive: used to bond and cure vibration damping units to composite thin-walled panels;

[0070] The non-planar mesh braided shape memory alloy steel wire rope vibration damping unit is integrally formed with a composite material combined thin-walled plate through a molding process and is perpendicular to the inner surface molding mold or the outer surface molding mold.

[0071] Since the mesh braided steel wire rope vibration damping device can be installed on the inner or outer surface of the composite material composite thin-walled plate 201, it is necessary to design a molding die suitable for installing the mesh braided vibration damping device on the inner surface and a molding die suitable for installing the mesh braided vibration damping device on the outer surface, namely, an inner surface integral molding die and an outer surface integral molding die.

[0072] An inner surface integral molding mold 301 is used to lay the carbon fiber prepreg on its inner side. After laying, the inner side of the carbon fiber prepreg is an open surface, which can be used to install the mesh braided steel wire rope vibration damping device, thus forming an inner surface installation. After molding, the mesh braided steel wire rope vibration damping device can be installed on the inner side of the vertical stabilizer of the resulting composite material electric aircraft.

[0073] The inner surface inclined vertical steel wire rope clamping assembly includes an inclined vertical rope clamping bottom block 302 and an inclined vertical rope clamping top block 303. The vertical shape memory alloy steel wire rope in the mesh braided steel wire rope first passes through the semi-circular lower groove of the inclined vertical rope clamping bottom block 302, and then passes through the semi-circular upper groove of the inclined vertical rope clamping bottom block 302 in the opposite direction. Then, through the U-shaped convex semi-cylinder on the inclined vertical rope clamping top block 303, after clamping, the inner surface inclined vertical steel wire rope clamping assembly is installed on the inner surface integral forming mold 301 by bolts.

[0074] The inner surface planar vertical steel wire rope clamping assembly includes a planar vertical rope clamping bottom block 304 and a planar vertical rope clamping top block 305. The vertical shape memory alloy steel wire rope in the mesh braided steel wire rope first passes through the semi-circular lower groove of the planar vertical rope clamping bottom block 304, and then passes through the semi-circular upper groove of the planar vertical rope clamping bottom block 304 in the opposite direction. Then, it is clamped by the U-shaped convex semi-cylinder on the planar vertical rope clamping top block 305. After clamping, the inner surface planar vertical steel wire rope clamping assembly is installed on the inner surface integral molding mold 301 by bolts.

[0075] Furthermore, the horizontal and vertical shape memory alloy wire ropes are composed of one nickel-titanium alloy wire and six stainless steel wires twisted together, with a diameter of 0.6 mm, wherein the nickel-titanium mass ratio of the nickel-titanium alloy is 60:40.

[0076] Furthermore, the non-planar mesh braided shape memory alloy steel wire rope vibration damping unit includes a combination structure of an inclined parallelogram plate and a straight right-angled trapezoid plate. The inclined parallelogram plate has a width of 200mm and an inclined angle of 86°. The straight right-angled trapezoid plate has a long side of 300mm and a short side of 200mm. The widest part of the combination plate is 60mm.

[0077] Furthermore, the wire rope clamping device includes:

[0078] Clamping assembly for inner surface forming: including inclined vertical rope clamping bottom block and inclined vertical rope clamping top block, flat vertical rope clamping bottom block and flat vertical rope clamping top block, horizontal rope clamping bottom strip and horizontal rope clamping top strip, inner surface V-shaped clamping block and V-shaped clamping block fixing strip;

[0079] Both the inclined vertical rope clamping base block and the planar vertical rope clamping base block are provided with a semi-circular lower groove and a semi-circular upper groove;

[0080] Both the inclined vertical rope clamping top block and the planar vertical rope clamping top block are equipped with U-shaped convex semi-cylinders;

[0081] Clamping assembly for outer surface forming: including inclined vertical rope clamping bottom block and inclined vertical rope clamping top block, flat vertical rope clamping bottom block and flat vertical rope clamping top block, flat vertical rope top clamping block, horizontal rope clamping top bar and V-shaped clamping block fixing bar;

[0082] The horizontal shape memory alloy steel wire rope in the mesh braided steel wire rope is first installed on the inner surface V-shaped clamping block 308 in sequence, and then the horizontal rope 101 and the inner surface V-shaped clamping block 308 are attached to the composite material composite thin-walled plate 201 by bolts through the threaded holes on the V-shaped clamping block fixing strip 309.

[0083] The horizontal shape memory alloy steel wire rope in the mesh braided steel wire rope first passes through the semi-circular lower groove of the horizontal rope clamping bottom bar 306, and then passes through the V-shaped upper groove of the horizontal rope clamping bottom bar 306 in the opposite direction. Then, it clamps the V-shaped convex prism on the horizontal rope clamping top bar 307. After clamping, the inner surface horizontal steel wire rope clamping assembly is installed on the inner surface integral forming mold 301 by bolts.

[0084] The outer surface integral molding mold 401 is used to lay carbon fiber prepreg on the outside of the mold. After the laying is completed, the outer surface of the carbon fiber prepreg is an open surface, which can be used to install the mesh braided steel wire rope vibration damping device, thus forming the outer surface installation. After molding, the mesh braided steel wire rope vibration damping device can be installed on the outside of the vertical stabilizer of the obtained composite material electric aircraft.

[0085] The vertical shape memory alloy steel wire rope in the mesh braided steel wire rope first passes through the semi-circular lower groove of the inclined vertical rope clamping base block 402, and then passes through the semi-circular upper groove of the inclined vertical rope clamping base block 402 in the opposite direction. Then, it is clamped by the V-shaped convex prism on the inclined vertical rope clamping top block 403. After clamping, the entire outer surface inclined vertical steel wire rope clamping assembly is installed on the outer surface integral molding base plate 410 by bolts. The top of the steel wire rope is placed on the groove at the top of the outer surface integral molding mold 401, and then clamped by the U-shaped convex semi-circular prism on the V-shaped vertical rope top block 404. Finally, the V-shaped vertical rope top block 404 is bolted to the outer surface integral molding mold 401.

[0086] The outer surface planar vertical steel wire rope clamping assembly includes a planar vertical rope clamping bottom block 405, a planar vertical rope clamping top block 406, and a planar vertical rope top clamping block 407. The vertical shape memory alloy steel wire rope in the mesh braided steel wire rope first passes through the semi-circular lower groove of the planar vertical rope clamping bottom block 405, and then passes through the semi-circular upper groove of the planar vertical rope clamping bottom block 405 in the opposite direction. Then, it is clamped by the V-shaped convex prism on the planar vertical rope clamping top block 406. After clamping, the outer surface planar vertical steel wire rope clamping assembly is installed on the outer surface integral molding base plate 410 by bolts. The top of the steel wire rope is placed on the groove at the top of the outer surface integral molding mold 401, and then clamped by the U-shaped convex semi-circular prism on the planar vertical rope top clamping block 407. Finally, the planar vertical rope top clamping block 407 is bolted to the outer surface integral molding mold 401.

[0087] The outer surface horizontal steel wire rope clamping assembly includes a horizontal rope clamping top bar 408 and a V-shaped clamping block fixing bar 409. The horizontal shape memory alloy steel wire rope in the mesh braided steel wire rope is first installed on the V-shaped clamping block fixing bar 409 in sequence and then pressed against the composite material composite thin-walled plate 201. The V-shaped clamping block fixing bar 409 is then installed on the outer surface integral molding base plate 410 by bolts. The other end of the steel wire rope is placed in the groove on the side of the outer surface integral molding mold 401 and then clamped by the U-shaped convex semi-cylinder on the horizontal rope clamping top bar 408. Finally, the horizontal rope clamping top bar 408 is bolted to the outer surface integral molding mold 401.

[0088] Furthermore, the composite material thin-walled panel uses T700 carbon fiber prepreg, with an even number of layers (≥4), a single layer thickness of 0.1 mm, and a symmetrical design of layup angles of [0 / 90 / 0 / 90 / 0] or [0 / 45 / 90 / -45 / 0].

[0089] Furthermore, the epoxy resin adhesive comprises bisphenol A type E51 epoxy resin and polyetheramine D230 curing agent in a mass ratio of 3.3:1, with a single coating amount of 5-10g.

[0090] An aircraft vertical tail vibration damping device based on shape memory alloy mesh non-planar braiding and its integrated molding method are characterized by the following steps:

[0091] Step 1: Lay a release cloth on the surface of the mold;

[0092] Step 2: Lay the carbon fiber prepreg according to the designed angle;

[0093] Step 3: Secure the horizontal portion of the mesh wire rope using the clamping device;

[0094] Step 4: Weave and fix the vertical part of the mesh steel wire rope;

[0095] Step 5: Apply epoxy resin and cure at room temperature for 4-6 hours;

[0096] Step 6: After removing the clamping device, autoclave molding is performed with the parameters set to 4 standard atmospheres, 120-150℃, and 3-6 hours.

[0097] Furthermore, in step 3, the horizontal shape memory alloy steel wire rope is positioned by the inner surface V-shaped clamping block and the V-shaped clamping block fixing strip, and the clamping force is provided by the bolt connection.

[0098] Furthermore, in step 4, the vertical shape memory alloy steel wire rope is positioned on the curved surface by means of a combination of a semi-circular groove and a U-shaped convex semi-cylinder clamping structure using a "threading the needle" method.

[0099] Furthermore, the autoclave is vacuum-sealed during molding, and the vacuum bag is made of Teflon-based release fabric with a thickness of 0.18 mm.

[0100] Furthermore, the non-planar mesh-woven shape memory alloy steel wire rope vibration damping unit provides a nonlinear damping force Fnet=Δnet(k1x+k3x) 3 +c1 ), where Δnet is the position weight function, preferably the Dirac function, and k1, k3, c1, r 21 r 12 The parameters are taken from Table 1.

[0101] Furthermore, the value of k1 ranges from 1167.8 to 1265.4 N / m, and the value of k3 ranges from 1.42 × 10⁻⁶ N / m. 8 -7.57×10 8 N / m 3 c1 ranges from 21.12 to 28.76 N·s / m;

[0102] The design of a vibration damping device based on a mesh-like non-planar braided structure using shape memory alloy steel wire rope demonstrates its vibration damping effect. During flight, the vertical stabilizer of the composite material is subjected to external forces, causing vibrations. Its dynamic equation can be expressed as:

[0103]

[0104] Where M, C, and K are the mass matrix, damping matrix, and stiffness matrix of the vertical stabilized surface of the composite material, which are determined by the vertical stabilized surface structure itself; F is the external force or external excitation acting on the structure; x is the vibration displacement generated by the external excitation of the vertical stabilized surface; and '..' and '.' represent the vibration acceleration and vibration velocity, respectively.

[0105] After the composite vertical stabilizer is fitted with a vibration damping device consisting of a mesh-woven shape memory alloy steel wire rope, the vibration damping device will provide a damping force to the system, the equation of which can be expressed as:

[0106]

[0107] Among them, F net The damping force provided by the mesh damping device, Δ n `et` is the position weight function for the mesh embedding locations, preferably a Dirac function, whose magnitude is determined by the embedding locations and the number of embeddings. `k1` and `k3` are the linear and nonlinear properties of the shape memory alloy wire rope.

[0108] Stiffness parameters, c1, r 21 and r 12 The linear and nonlinear damping parameters of the shape memory alloy steel wire rope are given in Table 1.

[0109] Table 1 Material parameters of nickel-titanium shape memory alloy steel wire rope

[0110]

[0111] Because the vibration damping device of the mesh-woven shape memory alloy steel wire rope provides vibration damping force to the system, it can attenuate the vibration of the structure (including displacement, velocity and acceleration), thereby achieving vibration control.

[0112] Those skilled in the art will be able to operate the technology in this case sequentially, and the specific operating sequence should refer to the following working principle. The detailed connection means are well-known in the art. The following mainly introduces the working principle and process.

[0113] Example:

[0114] Step 1: Place the inner surface integral molding mold 301 on the horizontal base plate, and wrap the release cloth around the inner surface integral molding mold 301 and the wire rope clamping device;

[0115] Step 2: According to the design scheme of composite thin-walled panel 201, T700 carbon fiber prepreg is laid on the inner surface integral molding mold 301 in sequence according to the layup angle and layup number.

[0116] Step 3: Place the horizontal portion 101 of the mesh non-planar braided shape memory alloy steel wire rope into the inner surface V-shaped clamping block 308, and press the inner surface V-shaped clamping block 308 tightly against the inner surface of the composite material composite thin-walled plate 201. Then, use bolts to pass through the threaded holes on the V-shaped clamping block fixing strip 309, and tighten the inner surface V-shaped clamping block 308 with the bolts;

[0117] Step 4: Pass the horizontal portion 101 of the mesh non-planar braided shape memory alloy steel wire rope through the semi-circular lower groove of the horizontal rope clamping bottom bar 306, then pass it back through the V-shaped upper groove of the horizontal rope clamping bottom bar 306, and tighten the steel wire rope. Then, clamp the V-shaped convex prism on the horizontal rope clamping top bar 307, and after clamping, install the entire inner surface horizontal steel wire rope clamping assembly onto the threaded hole of the inner surface integral molding mold 301 using bolts. Further, repeat the operation of Step 4 on the other side of the inner surface integral molding mold 301.

[0118] Step 5: The vertical shape memory alloy steel wire rope 102 in the mesh braided steel wire rope first passes through the semi-circular lower groove of the inclined vertical rope clamping block 302, then passes through the semi-circular upper groove of the inclined vertical rope clamping block 302 in the opposite direction. Next, it clamps the U-shaped convex semi-cylinder on the top block 303 through the inclined vertical rope clamping block. After clamping, the entire inner surface inclined vertical steel wire rope clamping assembly is installed on the upper threaded hole of the inner surface integral molding mold 301 using bolts. Then, the other end of the vertical shape memory alloy steel wire rope 102 is placed on the inner surface of the composite material composite thin-walled plate and passes through the horizontal steel wire rope 101 in a braided manner (like threading a needle). Further, the clamping block installation in Step 5 is repeated, installing the inner surface inclined vertical steel wire rope clamping assembly on the lower threaded hole of the inner surface integral molding mold 301, and clamping the other end of the vertical shape memory alloy steel wire rope 102.

[0119] Step Six: The vertical shape memory alloy steel wire rope 102 in the mesh braided steel wire rope first passes through the semi-circular lower groove of the planar vertical rope clamping base block 304, then passes through the semi-circular upper groove of the planar vertical rope clamping base block 304 in the opposite direction. Next, it clamps the U-shaped convex semi-cylinder on the planar vertical rope clamping top block 305. After clamping, the entire inner surface planar vertical steel wire rope clamping assembly is installed on the upper threaded hole of the inner surface integral molding mold 301 using bolts. Then, the other end of the vertical shape memory alloy steel wire rope 102 is placed on the inner surface of the composite material composite thin-walled plate and passes through the horizontal steel wire rope 101 in a braided manner (like threading a needle). Further, the clamping block installation in Step Six is ​​repeated, installing the inner surface planar vertical steel wire rope clamping assembly on the lower threaded hole of the inner surface integral molding mold 301, and clamping the other end of the vertical shape memory alloy steel wire rope 102.

[0120] Step 7: After the mesh non-planar braided shape memory alloy steel wire rope is processed, epoxy resin adhesive is evenly applied to the mesh braided steel wire rope, and then cured at room temperature until the mesh non-planar braided shape memory alloy steel wire rope is completely cured on the inner surface of the composite material composite thin-walled plate 201. Further, the room temperature curing time is 4-6 hours.

[0121] Step 8: After curing at room temperature, remove the clamping device of the inner mesh non-planar braided shape memory alloy steel wire rope and cut off the excess shape memory alloy steel wire rope.

[0122] Step Nine: High-temperature and high-pressure processing and molding. The composite material composite thin-walled plate 201 and the integrated molding mold 301 are placed in a vacuum bag for processing and molding. The pressure is set at 4 standard atmospheres, the temperature at 120-150℃, and the processing time is 3-6 hours. After processing and molding is completed, the mold is removed, and the composite material electric aircraft vertical stabilizer with a non-planar woven steel wire rope mesh on the inner surface is completed.

[0123] After completing the above steps, the integrated molding process of the non-planar braided steel wire rope mesh on the inner surface of the vertical stabilizer of the composite material new energy aircraft provided in this example has been completed.

[0124] Example 2: (Integrated molding process for non-planar braided steel wire rope mesh on the outer surface of the vertical stabilizer of a new energy aircraft made of composite materials)

[0125] like Figure 3 As shown, this invention provides a specific process for an integral molding process. For example... Figure 7 As shown, this invention provides a schematic diagram of the integral molding process for the outer surface. (As illustrated...) Figure 8 As shown in the figure, the present invention illustrates the schematic diagrams of the components of the integral molding device for the outer surface, wherein the components of the integral molding device for the outer surface include a mesh non-planar braided shape memory alloy steel wire rope, a composite material composite thin-walled plate, and the integral molding device for the outer surface.

[0126] A mesh-like non-planar braided shape memory alloy steel wire rope includes a horizontal portion 101 and a vertical portion 102 of the mesh-like braided rope.

[0127] The composite thin-walled panel 201 is designed based on the vertical stabilizer of a new energy aircraft.

[0128] The outer surface integral molding device includes an outer surface integral molding mold 401, a clamping device for an outer mesh non-planar braided shape memory alloy steel wire rope, and a base plate 410.

[0129] A clamping device for an outer mesh non-planar braided shape memory alloy steel wire rope includes an outer surface inclined vertical steel wire rope clamping group, an outer surface planar vertical steel wire rope clamping group, and an outer surface horizontal steel wire rope clamping group.

[0130] The inclined vertical wire rope clamping assembly includes an inclined vertical rope clamping bottom block 402, an inclined vertical rope clamping top block 403, and a V-shaped vertical rope top block 404.

[0131] The outer surface planar vertical wire rope clamping assembly includes a planar vertical rope clamping bottom block 405, a planar vertical rope clamping top block 406, and a planar vertical rope top clamping block 407.

[0132] The inner surface horizontal wire rope clamping assembly includes a horizontal rope clamping top bar 408 and a V-shaped clamping block fixing bar 409.

[0133] In practical implementation, the integral molding process for the non-planar braided steel wire rope mesh on the outer surface of the vertical stabilizer of the composite material new energy aircraft can be carried out according to the following steps:

[0134] Step 1: Place the outer surface integral molding mold 401 on the horizontal base plate, and wrap the release cloth around the outer surface integral molding mold 401 and the wire rope clamping device;

[0135] Step 2: According to the design scheme of composite thin-walled panel 201, T700 carbon fiber prepreg is laid on the outer surface integral molding mold 401 in sequence according to the layup angle and layup number;

[0136] Step 3: Place the horizontal part 101 of the mesh non-planar braided shape memory alloy steel wire rope into the V-shaped clamping block fixing strip 409 in sequence, and then attach the V-shaped clamping block fixing strip 409 tightly to the outer surface of the composite material composite thin wall plate 201. Then, install the V-shaped clamping block fixing strip 409 on the outer surface integrally formed base plate 410 with bolts.

[0137] Step 4: Place the other end of the horizontal steel wire rope 101 into the groove on the side of the outer surface integral molding mold 401, then clamp the U-shaped convex semi-cylinder on the top bar 408 with the horizontal rope, and then bolt the top bar 408 to the outer surface integral molding mold 401. Repeat the operation of Step 4, and tighten the horizontal steel wire rope 101. After tightening, bolt the other horizontal rope to the top bar 408 to the outer surface integral molding mold 401.

[0138] Step 5: The vertical shape memory alloy steel wire rope 102 in the mesh braided steel wire rope first passes through the semi-circular lower groove of the inclined vertical rope clamping base block 402, then passes through the semi-circular upper groove of the inclined vertical rope clamping base block 402 in the opposite direction. Next, it clamps the V-shaped convex prism on the top block 403 through the inclined vertical rope clamp. After clamping, the entire outer surface inclined vertical steel wire rope clamping assembly is installed on the outer surface integrally formed base plate 410 using bolts. Then, the other end of the vertical shape memory alloy steel wire rope 102 is placed on the outer surface of the composite material composite thin-walled plate and passes through the horizontal steel wire rope 101 in a braided manner (like threading a needle).

[0139] Step 6: Place the other end of the vertical steel wire rope 102 on the groove at the top of the outer surface integral molding mold 401, tighten it, and then clamp it with the U-shaped convex semi-cylinder on the V-shaped vertical rope top block 404. Then bolt the V-shaped vertical rope top block 404 to the outer surface integral molding mold 401.

[0140] Step 7: The vertical shape memory alloy steel wire rope 102 in the mesh braided steel wire rope first passes through the semi-circular lower groove of the planar vertical rope clamping base block 405, then passes through the semi-circular upper groove of the planar vertical rope clamping base block 405 in the opposite direction. Next, it clamps the V-shaped convex prism on the planar vertical rope clamping top block 406. After clamping, the entire outer surface planar vertical steel wire rope clamping assembly is installed on the outer surface integrally formed base plate 410 using bolts. Then, the other end of the vertical shape memory alloy steel wire rope 102 is placed on the outer surface of the composite material composite thin-walled plate and passes through the horizontal steel wire rope 101 in a braided manner (like threading a needle).

[0141] Step 8: Place the other end of the vertical steel wire rope 102 on the groove at the top of the outer surface integral molding mold 401, tighten it, and then clamp it with the U-shaped convex semi-cylinder on the planar vertical rope top clamping block 407. Then bolt the planar vertical rope top clamping block 407 to the outer surface integral molding mold 401.

[0142] Step 9: After the mesh non-planar braided shape memory alloy steel wire rope is processed, epoxy resin adhesive is evenly applied to the mesh braided steel wire rope, and then cured at room temperature until the mesh non-planar braided shape memory alloy steel wire rope is completely cured on the outer surface of the composite material composite thin-walled plate 201. Further, the room temperature curing time is 4-6 hours.

[0143] Step 10: After curing at room temperature, remove the clamping device of the outer mesh non-planar braided shape memory alloy steel wire rope and cut off the excess shape memory alloy steel wire rope.

[0144] Step 11: High-temperature and high-pressure processing and molding. The composite material composite thin-walled plate 201 and the integrated molding mold 401 are placed in a vacuum bag for processing and molding. The pressure is set at 4 standard atmospheres, the temperature at 120-150℃, and the processing time is 3-6 hours. After processing and molding, the mold is removed, and the vertical stabilizer of the electric aircraft with the outer surface of the composite material steel wire rope mesh non-planar woven structure is completed.

[0145] After completing the above steps, the integrated molding process for the non-planar braided steel wire rope mesh on the outer surface of the vertical stabilizer of the composite material new energy aircraft provided in this example has been completed.

[0146] It should be noted that, in this document, relational terms such as "first" and "second" are used merely to distinguish one entity or operation from another, and do not necessarily require or imply any such actual relationship or order between these entities or operations. Furthermore, the terms "comprising," "including," or any other variations thereof are intended to cover non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements includes not only those elements but also other elements not expressly listed, or elements inherent to such a process, method, article, or apparatus. Without further limitations, the phrase "comprising an element defined as..." does not exclude the presence of other identical elements in the process, method, article, or apparatus that includes said element.

[0147] Although embodiments of the invention have been shown and described, it will be understood by those skilled in the art that various changes, modifications, substitutions and alterations can be made to these embodiments without departing from the principles and spirit of the invention, the scope of which is defined by the appended claims and their equivalents.

Claims

1. An aircraft vertical tail vibration damping device based on shape memory alloy mesh non-planar weaving, characterized in that, include: Composite thin-walled panel (201): Its shape is adapted to the curved structure of the vertical stabilizer of new energy aircraft; Non-planar mesh braided shape memory alloy steel wire rope vibration damping unit: It is composed of horizontal shape memory alloy steel wire rope (101) and vertical shape memory alloy steel wire rope (102) crisscrossed; Integrated molding system: includes an inner surface molding die (301), an outer surface molding die (401), a base plate (410) and a wire rope clamping device; Epoxy resin adhesive: used to bond and cure vibration damping units to composite thin-walled panels; The non-planar mesh braided shape memory alloy steel wire rope vibration damping unit is integrally formed with a composite material composite thin-walled plate (201) through a molding process and is perpendicular to the inner surface forming mold (301) or the outer surface forming mold (401).

2. The aircraft vertical tail vibration damping device based on shape memory alloy mesh non-planar weaving according to claim 1, characterized in that, The horizontal shape memory alloy wire rope (101) and the vertical shape memory alloy wire rope (102) are made of one nickel-titanium alloy wire twisted together with six stainless steel wires, with a diameter of 0.6 mm, wherein the nickel-titanium mass ratio of the nickel-titanium alloy is 60:

40.

3. The aircraft vertical tail vibration damping device based on shape memory alloy mesh non-planar weaving according to claim 1, characterized in that, The non-planar mesh woven shape memory alloy steel wire rope vibration damping unit includes a combination structure of an inclined parallelogram plate and a straight right-angled trapezoid plate. The inclined parallelogram plate has a width of 200mm and an inclined angle of 86°. The straight right-angled trapezoid plate has a long side of 300mm and a short side of 200mm. The widest part of the combined plate is 60mm.

4. The aircraft vertical tail vibration damping device based on shape memory alloy mesh non-planar weaving according to claim 1, characterized in that, The wire rope clamping device includes: The clamping assembly for inner surface forming includes a sloping vertical rope clamping bottom block (302) and a sloping vertical rope clamping top block (303), a planar vertical rope clamping bottom block (304) and a planar vertical rope clamping top block (305), a horizontal rope clamping bottom strip (306) and a horizontal rope clamping top strip (307), an inner surface V-shaped clamping block (308) and a V-shaped clamping block fixing strip (309); Both the inclined vertical rope clamping base block (302) and the planar vertical rope clamping base block (304) are provided with a semi-circular lower groove and a semi-circular upper groove; Both the inclined vertical rope clamping top block (303) and the planar vertical rope clamping top block (305) are provided with U-shaped convex semi-cylinders; The clamping assembly for outer surface forming includes a sloping vertical rope clamping bottom block (402) and a sloping vertical rope clamping top block (403), a planar vertical rope clamping bottom block (405) and a planar vertical rope clamping top block (406), a planar vertical rope top clamping block (407), a horizontal rope clamping top bar (408), and a V-shaped clamping block fixing bar (409).

5. The aircraft vertical tail vibration damping device based on shape memory alloy mesh non-planar weaving according to claim 1, characterized in that, The composite thin-walled panel (201) uses T700 carbon fiber prepreg, with an even number of layers (≥4), a single layer thickness of 0.1 mm, and a symmetrical design of layup angles of [0 / 90 / 0 / 90 / 0] or [0 / 45 / 90 / -45 / 0].

6. The aircraft vertical tail vibration damping device based on shape memory alloy mesh non-planar weaving according to claim 1, characterized in that, The epoxy resin adhesive comprises bisphenol A type E51 epoxy resin and polyetheramine D230 curing agent in a mass ratio of 3.3:1, with a single coating amount of 5-10g.

7. The integrated molding method for an aircraft vertical tail vibration damping device based on shape memory alloy mesh non-planar weaving according to any one of claims 1-6, characterized in that, Includes the following steps: Step 1: Lay a release cloth on the surface of the mold; Step 2: Lay the carbon fiber prepreg according to the designed angle; Step 3: Secure the horizontal portion of the mesh wire rope using the clamping device; Step 4: Weave and fix the vertical part of the mesh steel wire rope; Step 5: Apply epoxy resin and cure at room temperature for 4-6 hours; Step 6: After removing the clamping device, autoclave molding is performed with the parameters set to 4 standard atmospheres, 120-150℃, and 3-6 hours.

8. The integrated molding method for an aircraft vertical tail vibration damping device based on shape memory alloy mesh non-planar weaving according to claim 7, characterized in that, In step 3, the horizontal shape memory alloy steel wire rope (101) is positioned by the inner surface V-shaped clamping block (308) and the V-shaped clamping block fixing strip (409), and the clamping force is provided by the bolt connection.

9. The integrated molding method for an aircraft vertical tail vibration damping device based on shape memory alloy mesh non-planar weaving according to claim 7, characterized in that, In step 4, the vertical shape memory alloy steel wire rope (102) is positioned on the curved surface by means of a combination of a semi-circular groove and a U-shaped convex semi-cylinder clamping structure.

10. The integrated molding method for an aircraft vertical tail vibration damping device based on shape memory alloy mesh non-planar weaving according to claim 7, characterized in that, The autoclave is vacuum-sealed during molding, and the vacuum bag is made of Teflon-based release fabric with a thickness of 0.18 mm.

11. The integrated molding method for an aircraft vertical tail vibration damping device based on shape memory alloy mesh non-planar weaving according to claim 7, characterized in that, The non-planar mesh-woven shape memory alloy steel wire rope vibration damping unit provides non-linear vibration damping force. Where Δnet is the position weight function, preferably the Dirac function, and k1, k3, c1, r 21 r 12 The parameters are taken from Table 1.

12. The integrated molding method for an aircraft vertical tail vibration damping device based on shape memory alloy mesh non-planar weaving according to claim 11, characterized in that, The value of k1 ranges from 1167.8 to 1265.4 N / m, and the value of k3 ranges from 1.42 × 10⁻⁶ N / m. 8 -7.57×10 8 N / m 3 The value of c1 ranges from 21.12 to 28.76 N·s / m.

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