Airplane tailplane and method of forming same

Abstract

The application provides an aircraft stabilizer and a forming method thereof, and belongs to the technical field of aircraft component manufacturing. The aircraft stabilizer comprises a lower skin, a framework, filling foams and an upper skin. The upper skin is fixedly connected with the edge of the lower skin, and a cavity is formed between the upper skin and the lower skin. The framework is located between the upper skin and the lower skin, and the framework is integrally formed with the upper skin. The framework divides the cavity into a plurality of unit cells. The filling foams are provided in plurality, are located between the upper skin and the lower skin, and are respectively filled in the plurality of unit cells. The filling foams are bonded with the inner surfaces of the upper skin and the lower skin. The framework is integrally formed with the skin, and compared with the bonding of the framework with the skin after the framework is formed, the mechanical properties of the product are greatly increased, and the manufacturing cost and time period are greatly shortened.

Description

Technical Field

[0001] This invention belongs to the technical field of aircraft component manufacturing, and in particular relates to aircraft stabilizers and their forming methods. Background Technology

[0002] Static stability is the initial tendency of an aircraft after it deviates from its equilibrium position. Aircraft static stability is divided into longitudinal static stability, lateral static stability, and directional static stability. If the aircraft tends to return to its previous position, it is said to be statically stable; if the aircraft continues to deviate, it is said to be statically unstable. Finally, if the aircraft tends to remain in its disturbed position, it is said to be neutrally stable. An increase in aircraft stability leads to a decrease in controllability; therefore, the upper limit of aircraft stability is the lower limit of controllability.

[0003] Aircraft stabilizers are the horizontal surfaces of the aircraft's tail section, generally classified into fixed and fully movable types. The function of stabilizers is to provide the aircraft with appropriate static stability. When an aircraft flies in near-uniform linear motion, it is often affected by various updrafts or crosswinds, causing changes in its flight attitude. The aircraft will yaw, pitch, and roll around its center of gravity. Before each takeoff, the downward tilt angle of the horizontal stabilizer is appropriately adjusted based on the aircraft's takeoff weight and center of gravity position, determining whether the aircraft can take off safely. If the aircraft is statically unstable, it cannot automatically return to its original flight attitude. That is, if the aircraft is disturbed by wind and pitches up, it will remain pitched up, and even after the disturbance disappears, the aircraft will maintain this pitched attitude and will not be able to return to its original attitude. Therefore, the stabilizer on an aircraft is crucial for its static stability.

[0004] Aircraft stabilizers mainly consist of skin, frame, and foam filling. Currently, the frame needs to be molded first and then bonded to the skin. The mechanical properties of stabilizers need to be further improved, and the manufacturing cost is high and the production cycle is long. Summary of the Invention

[0005] In view of this, the present invention aims to provide an aircraft stabilizer and a method for forming the stabilizer, so as to alleviate the above-mentioned technical problems.

[0006] To achieve the above objectives, the technical solution of the present invention is implemented as follows:

[0007] A first aspect: an aircraft stabilizer, comprising a lower skin, a frame, a filling foam, and an upper skin; the upper skin and the lower skin are fixedly connected at their edges, forming a cavity between them; the frame is located between the upper skin and the lower skin, and is integrally formed with the upper skin, the frame dividing the cavity into multiple cell sections; multiple filling foams are present, each located between the upper skin and the lower skin, and each filling one of the multiple cell sections, the filling foams being bonded to the inner surfaces of the upper skin and the lower skin.

[0008] Secondly, the above-mentioned method for forming aircraft stabilizers includes the following steps:

[0009] Lower skin layering: First, lay the first layer of the lower skin in its entirety, then lay the first layer of the reinforced area, then lay the seven layers of the lower skin in its entirety, and finally lay the second layer.

[0010] Foam positioning and bonding: First, adapt the foam, then position the foam, and then lay the twist strip;

[0011] Lay out the framework;

[0012] Upper skin paving;

[0013] Mold closing and curing: Position and fasten the upper skin mold and the lower skin mold, and transfer the mold and the product to the hot press for hot pressing and curing.

[0014] Furthermore, prior to the "lower skin layer" step, the following steps are also included:

[0015] Production preparation: Take the prepreg for making composite materials out of the cold storage and put it into the clean room. Let it air dry in a sealed bag for ≥6 hours. After there is no condensation on the surface of the bag film, take out the prepreg and unload it; clean the mold and apply release agent.

[0016] Material cutting: Cut the materials, classify them according to their usage location and angle, and label them accordingly.

[0017] Furthermore, the step "lower skin layup" includes:

[0018] Lower skin layup 1: Before laying the first layer, apply a layer of pressure-sensitive adhesive tape to the non-product area and apply primer to the product area; lay the first layer, align with the outer edge of the product area and leave a certain distance before laying the prepreg; treat the joints of adjacent sheets to be butt-fitted, and the butt joints should not have a gap or overlap greater than 1mm; turn the prepreg outside the scribed line onto the pressure-sensitive adhesive tape in the non-product area, and lay the release film aligned with the scribed line;

[0019] Reinforced Zone Layer 1: This layer is laid after the first layer of the lower skin is laid, with a thickness of 2mm.

[0020] Lower skin layer 2: A total of 7 layers are laid in one piece. Each layer of material is larger on one side than the previous layer. After each layer is laid, the release film is laid in alignment with the scribed lines. The joints of adjacent material pieces are treated. Each layer of outward-turned prepreg with the release film is turned into the product area. It is required to be as flat as possible. The release film is added at the corner overlap to prevent the outward-turned prepreg from sticking together.

[0021] Reinforced layer 2: The sheet material is cut to net size and laid up according to the positioning fixture, with a layer thickness of 1.2mm.

[0022] Furthermore, the step "foam positioning and bonding" includes:

[0023] Foam fitting: The foam needs to be dehumidified in advance. The dehumidified foam needs to be sealed and stored. Test fit each piece of foam with the frame. If the foam is too small, add an extra layer of adhesive film when laying the film. If the foam is too large, grind off the excess foam. All foam needs to be tested. You can use a feeler gauge to measure the gap between the foam and the frame to determine whether the foam is too large or too small.

[0024] Foam positioning: Wipe the prepared foam twice with acetone to clean the surface. Apply a layer of adhesive film to the laid-up lower skin. After cleaning the positioning fixture, apply a layer of pressure-sensitive tape to the contact surface with the lower skin and place it on the lower skin. Adjust the placement position so that the positions of each end of the positioning fixture match the product area markings. Place each piece of foam in the corresponding position of the skeleton in sequence. Press the positioned foam firmly from top to bottom for 5 seconds to increase the bonding strength between the foam and the lower skin. Remove the positioning fixture and apply a layer of adhesive film to all surfaces of the foam except the contact surface with the lower skin.

[0025] Laying the tack strips: Insert the tack strips into the corners and edges of all the contact surfaces between the foam core material and the lower skin, and press them firmly.

[0026] Furthermore, the step of "laying out the skeleton" includes:

[0027] Layer 1: Lay the first main beam, the second main beam, the first longitudinal rib, and the second longitudinal rib. The prepreg is laid from the first transverse rib to the second transverse rib, and then broken at the main beam and the longitudinal rib. Lay the third transverse rib and the fourth transverse rib, and the fourth transverse rib is broken at the main beam and the longitudinal rib.

[0028] Layer 2: Prepreg is laid continuously from the first transverse rib to the third transverse rib. Prepreg is laid on the second and fourth transverse ribs. The first longitudinal rib, the second longitudinal rib, the first main beam, and the second main beam are then laid. The longitudinal ribs and main beams are disconnected at the transverse ribs.

[0029] Layer 3: Prepreg is laid continuously from the first transverse rib to the third transverse rib. Prepreg is laid on the second and fourth transverse ribs. The first longitudinal rib, the second longitudinal rib, the first main beam, and the second main beam are then laid. The longitudinal ribs and main beams are disconnected at the transverse ribs.

[0030] Layer 4: Lay the first main beam, the second main beam, the first longitudinal rib, and the second longitudinal rib. The prepreg is laid from the first transverse rib to the second transverse rib, and is broken at the main beam and the longitudinal rib. Lay the third transverse rib and the fourth transverse rib. The fourth transverse rib is broken at the main beam and the longitudinal rib.

[0031] Layers 1-4 constitute one cycle, and this cycle is repeated 30 times.

[0032] Furthermore, the steps between "laying the skeleton" and "applying the skin layer" include the following steps:

[0033] Exterior trimming:

[0034] Make adjustments to the external appearance;

[0035] 1.2mm reinforcement layer 2: The material sheet is cut to net size and laid up according to the markings on the foam;

[0036] Folding the lower skin: Remove the lower skin release film layer by layer to complete all folding and lay-up. Only one layer can be folded at a time. When folding, pull the prepreg tightly to make each edge press firmly against the foam core. Open the corners of each edge along the fiber direction and lay up the layers. The seam should not have a gap or overlap greater than 1mm.

[0037] Finishing: Assemble the upper skin mold onto the lower skin mold, cold press with the upper press, remove the upper skin mold, observe the condition of the product, cut the high points, fill the low points, and repeat the above steps until the product is evenly compacted.

[0038] Furthermore, the step "upper skin layup" includes: laying 7 layers of prepreg on the window formed by the flange of the lower skin, vacuuming and compacting every 3 to 5 layers, laying a full layer of prepreg in the product area of ​​the upper skin mold, placing a release film between the lower skin mold and the upper skin mold, closing the mold, cold pressing once, removing the upper skin mold, and leveling again.

[0039] Furthermore, after the "mold closing and curing" step, the following steps are included:

[0040] Demolding test: After curing is complete and the mold surface cools to room temperature, remove the inserts with an Allen wrench and pin puller, take out the product, and remove burrs from the surface; use an ultrasonic flaw detector to test the internal quality of the product.

[0041] Compared with existing technologies, the aircraft stabilizer and its forming method provided by this invention have the following advantages:

[0042] (1) The stabilizer of the present invention is mainly composed of three parts: skin, foam, and skeleton. During molding, the skin and skeleton are co-cured. It is produced by compression molding. First, the lower skin is laid up, then the foam is positioned by positioning fixtures. After the foam is positioned, the skeleton is filled, and then the outer skin is wrapped and cured by press. The skeleton and skin are integrally formed. Compared with bonding the skeleton to the skin after molding, the integral molding of the skeleton and skin greatly increases the mechanical properties of the product, and the manufacturing cost and time cycle are greatly shortened.

[0043] (2) The method for forming a stabilized surface of the present invention includes the stabilized surface described above and has the above-mentioned beneficial effects. Attached Figure Description

[0044] The accompanying drawings, which form part of this invention, are used to provide a further understanding of the invention. The illustrative embodiments of the invention and their descriptions are used to explain the invention and do not constitute an undue limitation of the invention. In the drawings:

[0045] Figure 1 This is a schematic diagram of the overall structure of the aircraft stabilizer according to an embodiment of the present invention;

[0046] Figure 2 This is a schematic diagram of the foam-filled structure according to an embodiment of the present invention;

[0047] Figure 3 This is a schematic diagram of the skeleton structure described in an embodiment of the present invention;

[0048] Figure 4 This is a flowchart of the aircraft stabilizer forming method according to an embodiment of the present invention.

[0049] Explanation of reference numerals in the attached figures:

[0050] 1-Foam filling; 2-First main beam; 3-Second main beam; 4-First longitudinal rib; 5-Second longitudinal rib; 6-First transverse rib; 7-Second transverse rib; 8-Third transverse rib; 9-Fourth transverse rib. Detailed Implementation

[0051] It should be noted that, unless otherwise specified, the embodiments and features described in the present invention can be combined with each other.

[0052] In the description of this invention, it should be understood that the terms "center," "longitudinal," "lateral," "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," and "outer," etc., indicating orientations or positional relationships based on the orientations or positional relationships shown in the accompanying drawings, are only for the convenience of describing the invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation, and therefore should not be construed as a limitation of the invention. Furthermore, the terms "first," "second," etc., are used for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the number of indicated technical features. Thus, a feature defined with "first," "second," etc., may explicitly or implicitly include one or more of that feature. In the description of this invention, unless otherwise stated, "a plurality of" means two or more.

[0053] In the description of this invention, it should be noted that, unless otherwise explicitly specified and limited, the terms "installation," "connection," and "linking" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral connection; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium; and they can refer to the connection between units within two components. Those skilled in the art will understand the specific meaning of the above terms in this invention based on the specific circumstances.

[0054] The present invention will now be described in detail with reference to the accompanying drawings and embodiments.

[0055] like Figure 1-3 As shown, the present invention provides an aircraft stabilizer and a method for forming the same.

[0056] A first aspect: an aircraft stabilizer, comprising a lower skin, a frame, a filling foam 1, and an upper skin; the upper skin and the lower skin are fixedly connected at their edges, forming a cavity between them; the frame is located between the upper skin and the lower skin, and is integrally formed with the upper skin, the frame dividing the cavity into multiple cell sections; multiple filling foam 1s are present, each located between the upper skin and the lower skin, and each filling one of the multiple cell sections, the filling foam 1s being bonded to the inner surfaces of the upper skin and the lower skin.

[0057] Secondly, the above-mentioned method for forming aircraft stabilizers includes the following steps:

[0058] Lower skin layering: First, lay the first layer of the lower skin in its entirety, then lay the first layer of the reinforced area, then lay the seven layers of the lower skin in its entirety, and finally lay the second layer.

[0059] Foam positioning and bonding: First, adapt the foam, then position the foam, and then lay the twist strip;

[0060] Lay out the framework;

[0061] Upper skin paving;

[0062] Mold closing and curing: Position and fasten the upper skin mold and the lower skin mold, and transfer the mold and the product to the hot press for hot pressing and curing.

[0063] More preferably, before the step of "lower skin layup", the following steps are also included:

[0064] Production preparation: Take the prepreg for making composite materials out of the cold storage and put it into the clean room. Let it air dry in a sealed bag for ≥6 hours. After there is no condensation on the surface of the bag film, take out the prepreg and unload it; clean the mold and apply release agent.

[0065] Material cutting: Cut the materials, classify them according to their usage location and angle, and label them accordingly.

[0066] More preferably, the step "lower skin layup" includes:

[0067] Lower skin layup 1: Before laying the first layer, apply a layer of pressure-sensitive adhesive tape to the non-product area and apply primer to the product area; lay the first layer, align with the outer edge of the product area and leave a certain distance before laying the prepreg; treat the joints of adjacent sheets to be butt-fitted, and the butt joints should not have a gap or overlap greater than 1mm; turn the prepreg outside the scribed line onto the pressure-sensitive adhesive tape in the non-product area, and lay the release film aligned with the scribed line;

[0068] Reinforced Zone Layer 1: This layer is laid after the first layer of the lower skin is laid, with a thickness of 2mm.

[0069] Lower skin layer 2: A total of 7 layers are laid in one piece. Each layer of material is larger than the previous layer on one side. After each layer is laid, the release film is laid in alignment with the scribed lines. The joints of adjacent material pieces are treated to be butt-fitted. The butt joints should not have a gap or overlap greater than 1mm. Each layer of outward-turned prepreg with the release film is turned into the product area. It should be flattened as much as possible. The release film is added at the corner overlaps to prevent the outward-turned prepreg from sticking together.

[0070] Reinforced layer 2: The sheet material is cut to net size and laid up according to the positioning fixture, with a layer thickness of 1.2mm.

[0071] More preferably, the step "foam positioning and bonding" includes:

[0072] Foam fitting: The foam needs to be dehumidified in advance. The dehumidified foam needs to be sealed and stored. Test fit each piece of foam with the frame. If the foam is too small, add an extra layer of adhesive film when laying the film. If the foam is too large, grind off the excess foam. All foam needs to be tested. You can use a feeler gauge to measure the gap between the foam and the frame to determine whether the foam is too large or too small.

[0073] Foam positioning: Wipe the prepared foam with acetone to clean the surface. Stick a layer of adhesive film on the laid-up lower skin. After cleaning the positioning fixture, stick a layer of pressure-sensitive tape on the contact surface with the lower skin and place it on the lower skin. Adjust the placement position so that the positions of each end of the positioning fixture match the product area markings. Place each piece of foam in the corresponding position of the skeleton in sequence. Press the positioned foam firmly from top to bottom to increase the bonding strength between the foam and the lower skin. Remove the positioning fixture and stick a layer of adhesive film on all surfaces of the foam except the contact surface with the lower skin.

[0074] Laying the tack strips: Insert the tack strips into the corners and edges of all the contact surfaces between the foam core material and the lower skin, and press them firmly.

[0075] More preferably, the step "laying the skeleton" includes:

[0076] Layer 1: Lay the first main beam 2, the second main beam 3, the first longitudinal rib 4, and the second longitudinal rib 5. The prepreg is laid from the first transverse rib 6 to the second transverse rib 7, and is broken at the main beam and longitudinal rib. Lay the third transverse rib 8 and the fourth transverse rib 9. The fourth transverse rib 9 is broken at the main beam and longitudinal rib.

[0077] Layer 2: Prepreg is laid continuously from the first transverse rib 6 to the third transverse rib 8. Prepreg is laid on the second transverse rib 7 and the fourth transverse rib 9. The first longitudinal rib 4, the second longitudinal rib 5, the first main beam 2, and the second main beam 3 are laid. The longitudinal ribs and main beams are disconnected at the transverse ribs.

[0078] Layer 3: Prepreg is laid continuously from the first transverse rib 6 to the third transverse rib 8. Prepreg is laid on the second transverse rib 7 and the fourth transverse rib 9. The first longitudinal rib 4, the second longitudinal rib 5, the first main beam 2, and the second main beam 3 are laid. The longitudinal ribs and main beams are disconnected at the transverse ribs.

[0079] Layer 4: Lay the first main beam 2, the second main beam 3, the first longitudinal rib 4, and the second longitudinal rib 5. The prepreg is laid from the first transverse rib 6 to the second transverse rib 7, and is broken at the main beam and longitudinal rib. Lay the third transverse rib 8 and the fourth transverse rib 9. The fourth transverse rib is broken at the main beam and longitudinal rib.

[0080] Layers 1-4 constitute one cycle, and this cycle is repeated 30 times.

[0081] More preferably, the step between "laying the skeleton" and "upper skin layering" further includes the following steps:

[0082] Exterior trimming:

[0083] Make adjustments to the external appearance;

[0084] 1.2mm reinforcement layer 2: The material sheet is cut to net size and laid up according to the markings on the foam;

[0085] Folding the lower skin: peel off the lower skin release film layer by layer to complete all the folding and laying. Only one layer can be folded at a time. When folding, pull the prepreg tightly to make the edges press firmly against the foam core. Open the corners of each edge along the fiber direction and assemble the layers.

[0086] Finishing: Assemble the upper skin mold onto the lower skin mold, cold press with the upper press, remove the upper skin mold, observe the condition of the product, cut the high points, fill the low points, and repeat the above steps until the product is evenly compacted.

[0087] More preferably, the step "upper skin layup" includes: laying 7 layers of prepreg on the window formed by the flange of the lower skin, vacuuming and compacting every 3 to 5 layers, laying a full layer of prepreg in the product area of ​​the upper skin mold, placing a release film between the lower skin mold and the upper skin mold, closing the mold, cold pressing once, removing the upper skin mold, and leveling again.

[0088] More preferably, after the "mold closing and curing" step, the following steps are included:

[0089] Demolding test: After curing is complete and the mold surface cools to room temperature, remove the inserts with an Allen wrench and pin puller, take out the product, and remove burrs from the surface; use an ultrasonic flaw detector to test the internal quality of the product.

[0090] The above are merely preferred embodiments of the present invention and are not intended to limit the present invention. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of the present invention should be included within the protection scope of the present invention.

Claims

1. A method for forming an aircraft stabilizer, the aircraft stabilizer comprising a lower skin, a frame, a foam filling, and an upper skin; The upper skin and the lower skin are fixedly connected at their edges, forming a cavity between them; The skeleton is located between the upper skin and the lower skin, and the skeleton is integrally formed with the upper skin. The skeleton divides the cavity into multiple cell units. The filling foam comprises multiple foams, all located between the upper skin and the lower skin, and respectively filling multiple cell sections. The filling foam is bonded to the inner surfaces of the upper skin and the lower skin. Its features are: The molding method includes the following steps: Lower skin layering: First, lay the first layer of the lower skin in its entirety, then lay the first layer of the reinforced area, then lay the seven layers of the lower skin in its entirety, and finally lay the second layer. Foam positioning and bonding: First, adapt the foam, then position the foam, and then lay the twist strip; Lay out the framework; Upper skin paving; Mold closing and curing: Position and snap the upper skin mold and the lower skin mold together, then transfer the mold and the product to a hot press for hot pressing and curing; Before the "lower skin layer" step, the following steps are also included: Production preparation: Take the prepreg for making composite materials out of the cold storage and put it into the clean room. Let it air dry in a sealed bag for ≥6 hours. After there is no condensation on the surface of the bag film, take out the prepreg and unload it. Clean the mold and apply a release agent; Material cutting: Cut materials according to their intended use and angle, and label them accordingly; The step "lower skin layup" includes: Lower skin layup 1: Before laying the first layer, apply a layer of pressure-sensitive adhesive tape to the non-product area and apply a base coat to the product area; Make the first layer of layup, align the outer edge of the product area with the scribing line and leave a certain distance before laying the prepreg. Turn the prepreg outside the scribing line onto the pressure-sensitive tape in the non-product area, and lay the release film with the scribing line in alignment. Reinforced Zone Layer 1: After laying each layer of the lower skin, each layer of material is larger on one side than the previous layer. After each layer is laid, align the scribed lines and lay the release film. Treat the joints of adjacent material pieces. Turn each layer of prepreg outward with the release film and lay the first layer in one go before laying this layer. The layer thickness is 2mm. Lower skin layer 2: A total of 7 layers are laid out in one piece. The "release film" is turned over into the product area. It is required to be as flat as possible. Release film is added at the corner overlap to prevent the outward prepreg from sticking together. Reinforced layer 2: The sheet material is cut to net size and laid up according to the positioning fixture, with a layer thickness of 1.2mm.

2. The method for forming an aircraft stabilizer according to claim 1, characterized in that, The step "foam positioning and bonding" includes: Foam fitting: The foam needs to be dehumidified in advance. The dehumidified foam needs to be sealed and stored. Test fit each piece of foam with the frame. If the foam is too small, add an extra layer of adhesive film when laying the film. If the foam is too large, grind off the excess foam. All foam needs to be tested. You can use a feeler gauge to measure the gap between the foam and the frame to determine whether the foam is too large or too small. Foam positioning: Wipe the prepared foam with acetone to clean the surface. Stick a layer of adhesive film on the laid-up lower skin. After cleaning the positioning fixture, stick a layer of pressure-sensitive tape on the contact surface with the lower skin and place it on the lower skin. Adjust the placement position so that the positions of each end of the positioning fixture match the product area markings. Place each piece of foam in the corresponding position of the skeleton in sequence. Press the positioned foam firmly from top to bottom to increase the bonding strength between the foam and the lower skin. Remove the positioning fixture and stick a layer of adhesive film on all surfaces of the foam except the contact surface with the lower skin. Laying the twist strips: Insert the twist strips into the corners and edges of all the surfaces where the filling foam contacts the lower skin and press them firmly.

3. The method for forming an aircraft stabilizer according to claim 2, characterized in that, The step "laying out the skeleton" includes: Layer 1: Lay the first main beam, the second main beam, the first longitudinal rib, and the second longitudinal rib. The prepreg is laid from the first transverse rib to the second transverse rib, and is broken at the main beam and the longitudinal rib. Lay the third transverse rib and the fourth transverse rib. The fourth transverse rib is broken at the main beam and the longitudinal rib. Layer 2: The prepreg is laid continuously from the first transverse rib to the third transverse rib. The prepreg is laid on the second and fourth transverse ribs. The first longitudinal rib, the second longitudinal rib, the first main beam, and the second main beam are laid. The longitudinal ribs and the main beams are broken at the transverse ribs. Layer 3: Prepreg is laid continuously from the first transverse rib to the third transverse rib. Prepreg is laid on the second and fourth transverse ribs. The first longitudinal rib, the second longitudinal rib, the first main beam, and the second main beam are laid. The longitudinal ribs and the main beams are broken at the transverse ribs. Layer 4: Lay the first main beam, the second main beam, the first longitudinal rib, and the second longitudinal rib. The prepreg is laid from the first transverse rib to the second transverse rib, and is broken at the main beam and the longitudinal rib. Lay the third transverse rib and the fourth transverse rib. The fourth transverse rib is broken at the main beam and the longitudinal rib. Layers 1-4 constitute one cycle, and this cycle is repeated 30 times.

4. The method for forming an aircraft stabilizer according to claim 3, characterized in that, The steps between "laying the skeleton" and "attaching the skin layers" also include the following steps: Exterior trimming: Make adjustments to the external appearance; 1.2mm reinforcement layer 2: The material sheet is cut to net size and laid up according to the markings on the foam; Folding the lower skin: peel off the lower skin release film layer by layer to complete all the folding and lay-up layers. Only one layer can be folded at a time. When folding, pull the prepreg tightly to make each edge press firmly against the foam core. Open the corners of each edge along the fiber direction and assemble the lay-up layers. Finishing: Assemble the upper skin mold onto the lower skin mold, cold press with the upper press, remove the upper skin mold, observe the condition of the product, cut the high points, fill the low points, and repeat the above steps until the product is evenly compacted.

5. The method for forming an aircraft stabilizer according to claim 4, characterized in that, The step "upper skin layup" includes: laying 7 layers of prepreg on the window formed by the flange of the lower skin, vacuuming and compacting every 3 to 5 layers, laying 1 layer of prepreg on the product area of ​​the upper skin mold, placing a release film between the lower skin mold and the upper skin mold, closing the mold, cold pressing once, removing the upper skin mold, and leveling again.

6. The method for forming an aircraft stabilizer according to claim 4, characterized in that, After the "mold closing and curing" step, the following steps are included: Demolding inspection: After curing is complete and the mold surface has cooled to room temperature, remove the inserts with an Allen wrench and pin puller, take out the product, and remove burrs from the surface; use an ultrasonic flaw detector to inspect the internal quality of the product.

Images