CN113071163B - Bionic aircraft control surface preparation method - Google Patents
Bionic aircraft control surface preparation method Download PDFInfo
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- CN113071163B CN113071163B CN202110443669.8A CN202110443669A CN113071163B CN 113071163 B CN113071163 B CN 113071163B CN 202110443669 A CN202110443669 A CN 202110443669A CN 113071163 B CN113071163 B CN 113071163B
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B15/00—Layered products comprising a layer of metal
- B32B15/01—Layered products comprising a layer of metal all layers being exclusively metallic
- B32B15/017—Layered products comprising a layer of metal all layers being exclusively metallic one layer being formed of aluminium or an aluminium alloy, another layer being formed of an alloy based on a non ferrous metal other than aluminium
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B15/00—Layered products comprising a layer of metal
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B37/00—Methods or apparatus for laminating, e.g. by curing or by ultrasonic bonding
- B32B37/06—Methods or apparatus for laminating, e.g. by curing or by ultrasonic bonding characterised by the heating method
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B37/00—Methods or apparatus for laminating, e.g. by curing or by ultrasonic bonding
- B32B37/10—Methods or apparatus for laminating, e.g. by curing or by ultrasonic bonding characterised by the pressing technique, e.g. using action of vacuum or fluid pressure
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B38/00—Ancillary operations in connection with laminating processes
- B32B38/18—Handling of layers or the laminate
- B32B38/1866—Handling of layers or the laminate conforming the layers or laminate to a convex or concave profile
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
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Abstract
The invention provides a preparation method of a control surface of a bionic aircraft, which comprises the steps of carrying out die pressing deformation on a titanium plate and an aluminum plate in advance to form a plurality of layers of titanium and aluminum alternate layering plates, carrying out reaction heat treatment in a forming mould of a control skin to prepare a TiAl-based alloy skin, then connecting the TiAl-based alloy skin with a framework, and heating and pressurizing in the mould to form the control surface of the bionic aircraft; or embedding the unreacted titanium and aluminum alternate laminate plates after the mould pressing deformation to the two sides of the rudder framework, and heating and pressurizing the titanium and aluminum alternate laminate plates in the mould to form the control surface of the bionic aircraft. The invention can effectively reduce the thickness of the heat-proof layer, reduce the use of high-temperature alloy, obviously reduce the structural weight of the aircraft and improve the range index of the aircraft.
Description
Technical Field
The invention relates to a preparation method of an aircraft air control surface, and belongs to the technical field of aircraft structure design.
Background
During reentry across or flight within the atmosphere, the aircraft needs to undergo prolonged continuous aerodynamic heating, while at the same time, as aircraft speeds become faster and faster, the aircraft needs to be of lower structural weight. The air control surface of the aircraft has higher requirements, and the air control surface needs to bear complex air load and pneumatic heating while providing flight lift force and deflection force for the aircraft, so that the control surface needs to meet the requirements of low weight, high strength and high temperature resistance.
Most of the control surfaces of the traditional aircrafts are made of materials suitable for non-high-temperature environments, such as aluminum alloy, titanium alloy and the like, high-density materials such as high-temperature alloy and the like are used on high-speed aircrafts, the former are not suitable for high-temperature environments, and the latter are too heavy, so that the weight of the aircraft is too high, and the range of the aircraft is influenced. The TiAl-based alloy in the new material has the advantages of light weight, high strength, high temperature resistance and the like, and becomes an important alternative material for the air control surface of a high-speed aircraft, but the TiAl-based alloy has intrinsic brittleness, and the difficulty in preparing the TiAl plate is high, and the preparation is difficult to realize under the condition of not increasing high-density elements.
The technology for synthesizing the shell-like TiAl plate by multilayer alternating reaction of a titanium plate and an aluminum plate in recent years provides hope for the structural design and preparation of a full TiAl control surface. The bionic TiAl plate is applied to the technical field of control surfaces of high-speed aircrafts, so that the control surfaces of the bionic aircrafts are designed and prepared, the design level of the aircrafts is improved, and the bionic TiAl plate is an important direction for future development.
Disclosure of Invention
The invention aims to solve the technical problem of providing a preparation method for applying a light-weight and high-temperature-resistant bionic TiAl plate to an aircraft control surface, and solves the problems that the existing aircraft control surface is heavy in structure and is not suitable for being used in a long-range high-temperature environment.
In order to solve the technical problems, the invention provides a bionic aircraft control surface preparation method, which adopts the following technical scheme:
the titanium plate and the aluminum plate are pre-molded and deformed into a multilayer titanium and aluminum alternate paving plate,
placing the titanium and aluminum alternately-paved plates after mould pressing deformation into a forming mould of a rudder skin, performing reaction heat treatment to prepare a TiAl-based alloy skin, connecting the TiAl-based alloy skin with a framework, and heating and pressurizing in the mould to form a control surface of the bionic aircraft; or embedding the unreacted titanium and aluminum alternate laminate plates after the mould pressing deformation to the two sides of the rudder framework, and heating and pressurizing the titanium and aluminum alternate laminate plates in the mould to form the control surface of the bionic aircraft.
Further, the method for forming the multilayer titanium and aluminum alternate laminated plate comprises the following steps:
designing an inner die and an outer die according to the profile of the rudder skin, and performing compression molding on each titanium plate through the dies at the temperature of 0-1000 ℃ according to the contour of the rudder skin; each aluminum plate is molded under the condition of 0-600 ℃ according to the contour of rudder skin; and (4) alternately laying and placing the titanium plates and the aluminum plates after plastic deformation to form a multilayer titanium and aluminum alternate laying plate.
Or alternately laying the titanium plates and the aluminum plates, and carrying out hot pressing treatment at the temperature of 20-600 ℃/1-200 MPa so that the titanium plates and the aluminum plates are not layered and fall off; designing an inner mold and an outer mold according to the profile of the rudder skin, and performing hot pressing deformation on the titanium plate and the aluminum plate alternately paved plate through the molds, wherein the pressure range is 1MPa to 200MPa, and the temperature range is 20 ℃ to 600 ℃.
Further, placing a plurality of layers of titanium and aluminum alternately-laminated plates into a forming die of the rudder skin for reaction heat treatment under pressure, wherein the pressure range is 1MPa to 200MPa, and the temperature range is 600 ℃ to 1400 ℃, so that the TiAl-based alloy plate skin is prepared.
And further, the connection of the rudder skin and the framework is performed by selecting a welding, riveting, screwing or combined connection process mode, then heating and pressurizing are performed through a die, the load range is 1MPa to 200MPa, the temperature range is 600 ℃ to 1400 ℃, after air cooling is performed to room temperature, the framework and the skin of the rudder are subjected to auxiliary connection by using screws and nuts made of high-temperature alloy materials, the screws and the nuts do not protrude out of the surface of the skin, and the preparation of the bionic rudder surface is completed.
Further, through tool clamp equipment, embedding the deformed unreacted titanium and aluminum alternate laying plates on two sides of the rudder skeleton, then placing the titanium and aluminum alternate laying plates into a die for heating and pressurizing reaction and synthesis, wherein the pressurizing position of the tool is the contact part of the skin and the skeleton, the load range is 1-200 MPa, and the temperature range is 600-1400 ℃.
Furthermore, after the rudder framework and the skin are installed in place, no counter airflow step exists at the butt joint gap along the airflow direction, and the range of the counter airflow step is 0-2 mm.
Further, the thickness ratio of the titanium plate to the aluminum plate of the same product is 1.8 to 1.2.
Compared with the prior art, the invention has the following beneficial effects:
the invention provides a method for preparing a structure of a control surface made of a bionic TiAl material for a high-speed aircraft according to the forming principle of a bionic TiAl material plate aiming at the application requirement of the control surface made of the TiAl material of the high-speed aircraft, and can solve the problem that the structure of the control surface of the existing aircraft is heavier, thereby increasing the range of the aircraft.
By applying the technical scheme of the invention, the preparation method of the bionic light high-temperature-resistant control surface for the aircraft is provided, the control surface main body is made of the TiAl-based alloy material, the coordinated deformation of the control surface can be met under various use temperature conditions, and the structural damage failure caused by obvious thermal deformation mismatching can not be generated. The skeleton of the rudder is used for bearing load, and the skin appearance structure of the rudder is matched with the appearance structure of the aircraft.
In addition, the high-temperature strength characteristic of the light high-temperature TiAl material can be well utilized, the use of a heat-proof layer is reduced, the structural weight of the aircraft is further reduced, and the range of the aircraft is further increased. Meanwhile, the preparation method is not limited, so the method has strong adaptability and can be suitable for control surface structures of various aircrafts.
The invention has the beneficial effects that:
(1) The method for preparing the control surface of the brand-new bionic material provided by the invention realizes the feasible application of the bionic TiAl material on an aircraft;
(2) The special structure and the preparation method of the invention can effectively reduce the thickness of the heat-proof layer, reduce the use of high-temperature alloy, obviously reduce the structural weight of the aircraft and improve the range index of the aircraft. The traditional high-temperature alloy control surface adopts the technical scheme that a high-temperature alloy skin and a framework are combined together through welding, and the structure is heavier. The TiAl material has poor plasticity, the skin is difficult to form, and the sheet structure can be prepared only by increasing a large amount of alloy elements to improve the plasticity of the material at the cost of improving the TiAl density. Increasing these costs reduces the advantage of lightweight construction of TiAl control surfaces. According to the invention, the TiAl control surface is prepared by pre-molding and deforming a pure metal plate and directly generating TiAl through in-situ reaction, so that the preparation problem of the traditional TiAl curved plate is solved, and a TiAl control surface combined preparation method is further provided in an innovative way;
(3) The fully TiAl control surface structure adopted by the invention avoids thermal deformation mismatching caused by different thermal expansion coefficients of dissimilar materials, so that the structure is damaged and fails;
(4) The rudder skin can be embedded on the rudder framework in the form of a titanium plate and an aluminum plate multilayer plate which are used as raw materials, and then the preparation of the rudder skin and the connection of the skin and the framework are completed in one step through a heating and pressurizing process, so that the use of a die is reduced, and the preparation procedures of a rudder surface are also reduced;
(5) The pressure load and the temperature interval are selected and matched for application, so that no air holes are generated in the TiAl in-situ reaction process, and the density of the final TiAl plate is improved. Meanwhile, under the conditions of temperature and pressure, the preparation of the rudder skin and the connection of the skin and the framework can be completed in one step.
Drawings
FIG. 1 shows a schematic structural diagram of a control surface made of a bionic TiAl material for an aircraft according to embodiment 1 of the present invention;
fig. 2 is a schematic diagram showing a skeleton structure of an aircraft rudder provided in embodiment 1 of the present invention;
FIG. 3 illustrates a schematic view of a skin structure for an aircraft provided in accordance with embodiment 1 of the present invention;
FIG. 4 shows a schematic structural diagram of a control surface made of a biomimetic TiAl material for an aircraft according to embodiment 2 of the present invention;
fig. 5 is a schematic diagram showing a skeleton structure of an aircraft rudder provided in embodiment 2 of the present invention;
FIG. 6 is a schematic view of a skin structure for an aircraft provided in accordance with embodiment 2 of the present invention;
in the figure, 1 is a screw
Detailed Description
The present invention is described in detail below with reference to the attached drawings and specific examples.
The invention provides a method for preparing a control surface for an aircraft, which mainly comprises the following steps: a skeleton and a skin.
The framework is a structure mainly bearing the force load of the control surface and is positioned in the control surface, two sides of the framework of the control surface are designed into skin structures, and the framework and the skin of the control surface jointly form a main structure of the control surface.
The control surface skin appearance structure is matched with the appearance of the aircraft. The rudder framework can be in a transverse and longitudinal beam structure, a radial structure and the like, and is selected according to a specific load form and a working environment.
The rudder skeleton preparation process includes but is not limited to: casting, powder metallurgy, welding, machining, and the like. The process format is selected as is well known in the art.
In some embodiments of the present invention, the method for preparing the control surface of the bionic aircraft specifically comprises the following steps:
The main raw materials of the rudder skin are titanium plates and aluminum plates (alloy elements, particles, fibers and other additives can be added according to requirements). The rudder has a skin thickness in the range of 0.3mm to 10mm. The thickness of the raw materials of the titanium plate and the aluminum plate ranges from 0.03mm to 2mm. The thickness ratio of the titanium plate to the aluminum plate of the same product is 1.
The skin of the rudder is formed by one of the following two forming modes:
in a first mode
And selecting corresponding titanium plates and aluminum plates according to the thickness requirement of the skin. Each titanium plate is molded under the condition of 0-1000 ℃ according to the contour of rudder skin; and each aluminum plate is molded and formed under the condition of 0-600 ℃ according to the contour of rudder skin. And then, alternately laying the titanium plates and the aluminum plates after plastic deformation, placing the titanium plates and the aluminum plates into a forming die of a rudder skin, and carrying out reaction heat treatment under pressure, wherein the pressure range is 1MPa to 200MPa, and the temperature range is 600 ℃ to 1400 ℃, so as to prepare the TiAl-based alloy plate skin.
Mode two
According to the requirement of skin thickness, alternately laying and placing titanium plates and aluminum plates, and carrying out hot pressing treatment on the multilayer plate at the temperature of 20-600 ℃/1-200 MPa so as to prevent the multilayer plate from layering and falling off; then designing an inner mold and an outer mold according to the profile of the rudder skin, performing hot-pressing deformation (the pressure range is 1MPa to 200MPa, the temperature range is 20 ℃ to 600 ℃) on the titanium plate and aluminum plate alternately laminated plates through the molds, then placing the multiple layers of titanium and aluminum alternately laminated plates after the hot-pressing deformation into a forming mold of the rudder skin, and performing reaction heat treatment to prepare the TiAl-based alloy skin, wherein the pressure range is 1MPa to 200MPa, and the temperature range is 600 ℃ to 1400 ℃.
Step 2, connecting rudder skin with framework
Firstly, the rudder skin is connected with the framework, and the connection mode can select the processes of welding, riveting, screwing and the like, and also can select the combined connection process mode of welding, riveting, welding and screwing. The welding is mainly in two modes of brazing and diffusion welding, and electron beam welding and laser welding can be adopted for auxiliary connection according to needs. Then heating and pressurizing by a die, wherein the load range is 1MPa to 200MPa, and the temperature range is 600 ℃ to 1400 ℃. After the air cooling is carried out to the room temperature, the screw and the nut made of the high-temperature alloy material are used for carrying out auxiliary connection on the framework and the skin of the rudder, the screw and the nut are required to be ensured not to protrude out of the surface of the skin, and the preparation of the bionic rudder surface is completed.
When the skin of the rudder is connected with the framework, welding, riveting and screwing parts are all positioned in the contact area of the skin and the framework, the melting point of brazing filler metal selected during brazing connection is not lower than 800 ℃, and nickel-based brazing filler metal is recommended to be selected. The selected screw is made of high-temperature alloy or TiAl material. The selected rivet is preferably made of high-temperature alloy or high-temperature titanium alloy material.
After the rudder skeleton and the skin are installed in place, a counter airflow step does not exist at the butt joint gap along the airflow direction, and the range of the counter airflow step is 0-2 mm.
In some embodiments of the present invention, a method for manufacturing an integrated aircraft control surface is provided, which includes:
and (3) alternately laying the titanium plates and the aluminum plates according to the thickness requirement of the skin, wherein the thickness range of the skin is 0.3mm to 10mm. The thickness range of the raw materials of the titanium plate and the aluminum plate is 0.03mm to 2mm. The thickness ratio of the titanium plate to the aluminum plate of the same product is 1.8 to 1.2.
And performing hot-pressing deformation by a mould according to the shape of the rudder skin (the pressure range is 1MPa to 200MPa, the temperature range is 20 ℃ to 600 ℃, and the detail is shown in the second mode).
And embedding the unreacted titanium plate and the aluminum plate multilayer plate after deformation to two sides of the rudder skeleton through equipment such as a tool clamp, and the like, and then putting the titanium plate and the aluminum plate multilayer plate into a die for heating and pressurizing reaction and synthesis to prepare the TiAl-based alloy skin which is directly connected with the rudder skeleton structure into a whole. The pressurizing position of the tool is the contact part of the skin and the framework, the load range is 1MPa to 200MPa, and the temperature range is 600 ℃ to 1400 ℃.
After the rudder skeleton and the skin are installed in place, no counter airflow step exists at the butt joint gap along the airflow direction, and the range of the counter airflow step is 0-2 mm.
The method is applicable to TiAl materials, and the skeleton and the skin of the rudder can also be but are not limited to: niAl, feAl and the like.
The following further describes the embodiments of the present invention in connection with a control surface structure of an aircraft.
Example 1:
taking the control surface structure of an aircraft shown in fig. 1 as an example, the structure mainly comprises a skeleton (fig. 2) and a skin (fig. 3) of a rudder. The frame of the rudder is TiAl alloy, the maximum thickness is 60mm, the rudder is composed of ribbed plates, the front edge of the rudder, the rear edge of the rudder and the upper and lower bottom plates of the rudder, the thickness of the ribbed plates is 3-10 mm, and the front edge, the rear edge, the upper and lower bottom plates are tightly attached to the structural section surface of the skin. The skin of the rudder is TiAl alloy, the thickness is 1mm, the outer surface is a pneumatic profile, the inner profile is tightly attached to the rib plate of the framework of the rudder, and the periphery of the inner profile is tightly attached to the front edge, the rear edge, the upper bottom plate and the lower bottom plate of the rudder. The skin of the rudder consists of a left piece and a right piece. After the rudder skeleton and the skin are installed in place, a reverse airflow step does not exist at the butt joint gap along the airflow direction, the forward airflow step is not larger than 0.5mm, and tolerance control of the rudder skeleton and the skin at the butt joint face is required to be guaranteed.
The specific manufacturing and forming process route of the embodiment is that the rudder skeleton is manufactured firstly, and then the rudder skin is manufactured and assembled to be integrally formed.
According to the rudder skeleton structure form, adopting the envelope of 3mm allowance to perform TiAl alloy casting blank forming; and then, machining is carried out to meet the design requirement of a drawing.
The rudder skin preparation process comprises the following steps: alternately laying 6 titanium plates with the thickness of 0.1mm and 5 aluminum plates with the thickness of 0.1mm, wherein the titanium plates are arranged on the two sides of the outer surface of the multilayer plate; carrying out hot pressing treatment on the multilayer board at the temperature of 500 ℃/50MPa so that the multilayer board cannot be layered and fall off; then designing an inner die and an outer die according to the profile of the rudder skin, carrying out hot bending deformation on the multilayer board through the inner die and the outer die at 500 ℃, and carrying out pressure maintaining treatment for 1-3 times according to the rebound condition of a product; and machining the periphery of the multi-layer board deformed in place, so that the butt joint gap between the periphery and the framework is not more than 0.3mm, no adverse airflow step difference exists, and the consequent airflow step difference is not more than 0.3mm.
The connection process of the rudder skin and the skeleton is as follows: laying high-temperature-resistant brazing filler metal at the joint face of the rudder skeleton and the rudder skin, embedding the multilayer board on the rudder skeleton, heating and pressurizing through a die, keeping the temperature at 600 ℃ for 30min +1200 ℃ for 60min, keeping the pressure at 50MPa unchanged, and cooling in air to room temperature to finish the preparation of the bionic rudder face.
Example 2:
the rudder surface structure of an aircraft shown in fig. 4 mainly comprises a skeleton (fig. 5) and a skin (fig. 6) of a rudder, and is assisted by screw connection. The frame of the rudder is TiAl alloy, the maximum thickness is 30mm, the rudder is composed of ribbed plates, the front edge of the rudder, the rear edge of the rudder and the upper and lower bottom plates of the rudder, the thickness of the ribbed plates is 2-5 mm, and the front edge, the rear edge, the upper and lower bottom plates are tightly attached to the structural section surface of the skin. The skin of the rudder is TiAl alloy, the thickness of the skin is 0.5mm, the outer surface of the skin is a pneumatic profile, the inner profile is tightly attached to a rib plate of the skeleton of the rudder, and the periphery of the inner profile is tightly attached to the front edge, the rear edge, the upper bottom plate and the lower bottom plate of the rudder. The skin of the rudder consists of a left piece and a right piece. The rudder skeleton and the skin are in auxiliary connection through screws. After the rudder skeleton and the skin are installed in place, no counter airflow step exists at the butt joint gap along the airflow direction, the forward airflow step is not more than 0.4mm, the tolerance control of the rudder skeleton and the skin at the butt joint surface is required to be ensured,
the specific manufacturing and forming process route of the embodiment is that the rudder framework is manufactured firstly, then the rudder skin is manufactured, and finally the rudder framework and the skin are installed and connected.
According to the rudder skeleton structure form, adopting the envelope with 3mm allowance to perform TiAl alloy casting blank forming; and then, machining is carried out to meet the design requirement of a drawing.
The rudder skin preparation process comprises the following steps: alternately laying 6 titanium plates with the thickness of 0.05mm and 5 aluminum plates with the thickness of 0.05mm, wherein the titanium plates are arranged on the two sides of the outer surface of the multilayer plate; carrying out hot pressing treatment on the multilayer board at 500 ℃ so that the multilayer board cannot be layered and fall off; then designing an inner die and an outer die according to the shape surface of the rudder skin, carrying out hot bending deformation on the multilayer board through the inner die and the outer die at 500 ℃, and carrying out pressure maintaining treatment for 1-3 times according to the rebound condition of a product; then, the subsequent reaction synthesis is carried out continuously without cooling: preserving heat at 600 ℃ for 30min and 1200 ℃ for 60min, and cooling to room temperature in air cooling to finish the preparation of the bionic TiAl material skin. The periphery of the skin is machined, the screw mounting holes are machined, the requirement that the peripheral butt joint gap with the framework is not more than 0.3mm is met, the adverse airflow step difference does not exist, and the downdraft airflow step difference is not more than 0.2mm.
Connecting rudder skin and skeleton: laying high temperature resistant brazing filler metal in rudder skeleton and rudder covering faying surface department, then inlaying the multiply wood on the rudder skeleton, the rethread mould heats the pressurization, 900 ℃ keeps warm for 60min, and after the air cooling cooled to the room temperature, carry out the auxiliary connection to the skeleton and the covering of rudder with screw 1, the nut of superalloy material, need guarantee that screw 1 and nut do not bulge the covering surface, the preparation of bionical rudder face is accomplished.
The invention has not been described in detail and is in part known to those of skill in the art.
Although embodiments of the present invention have been shown and described, it will be appreciated by those skilled in the art that changes, modifications, substitutions and alterations can be made in these embodiments without departing from the principles and spirit of the invention, the scope of which is defined in the appended claims and their equivalents.
Claims (6)
1. A method for preparing a control surface of a bionic aircraft, which is characterized in that,
the method comprises the following steps of pre-die pressing and deforming a titanium plate and an aluminum plate into a multilayer titanium and aluminum alternate paving plate, wherein the method comprises the following steps:
performing compression molding on each titanium plate at 0 to 1000 ℃ according to the contour of a rudder skin, performing compression molding on each aluminum plate at 0 to 600 ℃ according to the contour of the rudder skin, and alternately laying and placing the titanium plates and the aluminum plates after plastic deformation to form a multilayer titanium and aluminum alternate laying plate;
or alternately laying the titanium plates and the aluminum plates, performing hot pressing treatment under the conditions that the temperature range is 20-600 ℃ and the pressure range is 1-200 MPa to prevent the titanium plates and the aluminum plates from being layered and falling off, designing an inner die and an outer die according to the shape surface of the rudder skin, and performing hot pressing deformation on the alternately laid titanium plates and the aluminum plates through the dies, wherein the pressure range is 1-200 MPa and the temperature range is 20-600 ℃;
placing the titanium and aluminum alternately-layered plate after mould pressing deformation into a forming mould of a rudder skin, carrying out reaction heat treatment to prepare a TiAl-based alloy skin, connecting the TiAl-based alloy skin with a framework at the pressure ranging from 1MPa to 200MPa and the temperature ranging from 600 ℃ to 1400 ℃, and heating and pressurizing in the mould to form a bionic aircraft rudder surface; or embedding the deformed unreacted titanium plate and aluminum plate multilayer plates on two sides of the rudder skeleton through tool fixture equipment, then placing the titanium plate and the aluminum plate multilayer plates into a die for heating and pressurizing reaction and synthesis to prepare a TiAl-based alloy skin which is directly connected with the rudder skeleton structure into a whole, wherein the pressurizing position of the tool is the contact part of the skin and the skeleton, the load range is 1MPa to 200MPa, and the temperature range is 600 ℃ to 1400 ℃.
2. The method for preparing the control surface of the bionic aircraft according to claim 1, wherein the rudder skin and the frame are connected by selecting a welding, riveting, screwing or a combined connection process mode, heating and pressurizing are carried out through a die, the load range is 1MPa to 200MPa, the temperature range is 600 ℃ to 1400 ℃, after air cooling and temperature reduction to room temperature, the frame and the skin of the rudder are subjected to auxiliary connection through screws and nuts made of high-temperature alloy materials, and the screws and the nuts do not protrude out of the surface of the skin.
3. The method for preparing the control surface of the bionic aircraft according to claim 1,
alternately laying titanium plates and aluminum plates, wherein the two outermost sides are the titanium plates;
carrying out hot pressing treatment on the titanium plate and the aluminum plate alternately paved plate at 500 ℃ so as to prevent the titanium plate and the aluminum plate from being layered and falling off;
designing an inner die and an outer die according to the profile of a rudder skin, carrying out hot bending deformation on the titanium plate and the aluminum plate alternately laminated plates through the inner die and the outer die at 500 ℃, and carrying out pressure maintaining treatment for 1 to 3 times according to the rebound condition of a product;
continuously carrying out subsequent reaction synthesis without cooling: keeping the temperature at 600 ℃ for 30min, keeping the temperature at 1200 ℃ for 60min, and cooling to room temperature in an air cooling manner to finish the preparation of the bionic TiAl material skin;
machining the periphery of the skin to meet the requirement that the butt joint gap between the periphery and the framework is not more than 0.3mm, no adverse airflow step difference exists, and the downdraft airflow step difference is not more than 0.2mm;
the connection process of the rudder skin and the skeleton is as follows: will titanium board and aluminum plate spread the layer board in turn and inlay to the rudder skeleton, heat and pressurize through the mould, 900 ℃ keeps warm for 60min, and after the air cooling cooled to room temperature, carry out the auxiliary connection with screw, the nut of superalloy material to the skeleton and the covering of rudder, need guarantee that screw and nut do not bulge the covering surface, bionical rudder face preparation is accomplished.
4. The method for preparing the control surface of the bionic aircraft according to claim 1,
alternately laying titanium plates and aluminum plates, and carrying out hot pressing treatment at 500 ℃ and 50MPa to prevent the titanium plates and the aluminum plates from layering and falling off;
designing an inner die and an outer die according to the profile of a rudder skin, carrying out hot bending deformation on the titanium plate and the aluminum plate alternately laminated plates through the inner die and the outer die at 500 ℃, and carrying out pressure maintaining treatment for 1 to 3 times according to the rebound condition of a product;
machining the peripheries of the titanium plate and the aluminum plate which are deformed in place and are alternately paved into plates, wherein the butt joint gap between the peripheries and the framework is not more than 0.3mm, the reverse airflow step difference is avoided, and the forward airflow step difference is not more than 0.3mm;
connection of rudder skin and skeleton: and embedding the titanium plate and aluminum plate alternate layering plates on a rudder framework, heating and pressurizing through a mold, keeping the temperature at 600 ℃ for 30min, keeping the temperature at 1200 ℃ for 60min, keeping the pressure at 50MPa, and cooling in air to room temperature to finish the preparation of the bionic rudder surface.
5. The method for preparing the bionic aircraft control surface according to claim 1, wherein after the rudder skeleton and the skin are installed in place, no reverse airflow step exists in the butt joint gap along the airflow direction, and the range of the forward airflow step is 0-2mm.
6. The method for preparing the control surface of the bionic aircraft according to claim 1, wherein the thickness ratio of the titanium plate to the aluminum plate of the same product is 1.
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