CN-122008595-A - Near zero warping forming method and system for resin matrix composite plane part

CN122008595ACN 122008595 ACN122008595 ACN 122008595ACN-122008595-A

Abstract

The invention discloses a near zero warping forming method and system for a resin matrix composite plane part, and belongs to the technical field of composite forming. Aiming at the problem that a large-size composite material plane part for a satellite is easy to generate buckling deformation in the curing process, the method proposes to actively construct a dynamic temperature field to regulate and control the curing reaction sequence so as to localize stress, thereby reducing long-range stress superposition and further reducing buckling deformation to realize near-zero buckling molding. The method comprises the steps of designing dynamic temperature field distribution based on multi-physical field coupling simulation, arranging a heating unit array capable of controlling temperature independently and a thermocouple monitoring system on the surface of a die, layering a part to be formed and the die, packaging a vacuum bag, vacuumizing, solidifying according to a set temperature curve, and cooling and demoulding after solidification is finished. According to the invention, the stress is localized through active regulation and control of the temperature field, the long-range superposition of the stress is reduced, and the buckling deformation in the curing process is obviously restrained.

Inventors

HOU JIABIN
ZHAO WENJUN
ZHANG WENCONG
CHEN MENGKAI
CUI GUORONG

Assignees

哈尔滨工业大学（威海）

Dates

Publication Date: 20260512
Application Date: 20260211

Claims (10)

1. A near zero warping forming method of a resin matrix composite plane part is characterized by comprising the following steps: Step S1, dynamic temperature field distribution is designed based on multi-physical field coupling simulation, and a heating unit array capable of independently controlling temperature in a partitioned manner and a corresponding temperature monitoring unit are arranged on the lower surface of a forming die; S2, paving a composite material layer on the die; S3, vacuum bag packaging and vacuumizing are carried out on the layering system, and each heating partition is controlled to be heated and cured according to preset different dynamic temperature curves; and S4, cooling and demolding after solidification is completed, so as to obtain the resin-based composite material planar piece.
2. The method for forming the near-zero warpage of the resin matrix composite planar member according to claim 1, wherein the method further comprises a dynamic temperature field design step of designing a plurality of heating units with independent temperature control and a distribution mode thereof according to the size and the structural characteristics of a component before arranging the heating unit array with the independent temperature control in a partitioning manner and the corresponding temperature monitoring units, and determining a dynamic temperature curve of each heating unit through multi-physical field coupling simulation by combining a curing process; In the step S1, a heating unit and a temperature monitoring unit are disposed on the lower surface of the mold, and the temperature monitoring unit is disposed in the central area of each heating unit and connects each unit to a multi-channel temperature control system for real-time monitoring and controlling of temperature.
3. The method for forming the resin matrix composite planar member near zero warpage according to claim 2, wherein in the step S1, a thermal-curing-mechanical coupling model is built by adopting multi-physical field coupling simulation software, the distribution of a temperature field, a curing degree field and a residual stress field in the curing process is simulated, the temperature setting curve of each heating unit is optimized, and the temperature difference range of each optimized partition temperature curve is 5-30 ℃.
4. The method for forming the resin matrix composite planar piece near zero warping according to claim 2, wherein the heating units are sheet heaters and are arranged on the lower surface of the die in an array mode, the temperature of each heating unit is independently controlled, the temperature monitoring units are thermocouples, the thermocouples are connected with the multi-channel temperature control system, and the thermocouples are arranged at the center or characteristic points of the corresponding heating zones and realize closed-loop temperature control.
5. The method for forming a planar member of resin matrix composite material according to claim 2, wherein in the step S1, the dynamic temperature field includes at least one of a center symmetrical temperature field, a length symmetrical temperature field, and a width symmetrical temperature field.
6. The method for forming the resin-based composite material planar piece near zero warping is characterized in that in the step S2, the layering structure is a sandwich structure comprising a foam core material, specifically, a panel layer formed by resin-based prepregs is paved on the upper surface and the lower surface of the foam core material, the resin of the resin-based prepregs is one of epoxy resin, cyanate resin, bismaleimide resin or polyimide resin, and the reinforcing fiber is one or more of carbon fiber, glass fiber, quartz fiber or aramid fiber; And placing the layered composite material into a mould, sequentially covering release cloth and airfelt up and down, and placing an isolating film between the mould and the lower release cloth.
7. The method for forming a planar piece of resin matrix composite material according to claim 6, wherein in the step S3, all the layers completed in the step S2 are filled into a vacuum bag and sealed, a vacuum system is connected for vacuumizing, the pressurizing size is determined according to the thickness of the layers and the curing process, and a heating system is connected for heating and curing according to a set curing temperature curve.
8. The method for forming the resin matrix composite planar member near zero warpage according to claim 1, wherein in the step S3, the pressure in the vacuum bag is maintained below-0.1 MPa, so that the composite is ensured to be in a uniform pressure environment in the curing process; According to the different thickness of the layer and the requirements of different curing processes, the material can be placed into a pressure tank for pressurizing, and the pressurizing size is in the range of 0.1MPa-1MPa.
9. The method for forming a resin matrix composite planar member with near zero warpage according to claim 1, wherein in the step S4, after solidification is completed, the resin matrix composite planar member with near zero warpage is obtained by naturally cooling to room temperature in a vacuum environment, releasing the vacuum, and demolding.
10. The resin matrix composite plane part near zero warping forming system is characterized by comprising a heating unit array capable of controlling temperature in a partitioning and independent mode, a multichannel temperature control system, a vacuum bag packaging system and a temperature monitoring system, wherein the near zero warping forming system is used for realizing the resin matrix composite plane part near zero warping forming method according to any one of claims 1-9; the heating unit array is led out through a vacuum bag sealing area by a high-temperature-resistant wire and is respectively and independently connected to the power output ends of the multichannel temperature control system; the temperature monitoring system comprises thermocouples which are arranged in each heating zone, the thermocouples are led out through the vacuum bag sealing zone through compensation wires and are respectively connected to the signal input ends of the multichannel temperature control system to form a closed-loop temperature control loop for each zone.

Description

Near zero warping forming method and system for resin matrix composite plane part Technical Field The application belongs to the technical field of composite material molding, and particularly relates to a near-zero warping molding method and system for a resin matrix composite material planar piece. Background Resin-based composite materials, particularly fiber reinforced resin-based composite materials, are extremely widely used in the aerospace field due to their excellent specific strength, specific modulus, fatigue resistance and designability. The application range of the device is expanded from satellite structures to fairings, instrument deck plates and partition plates of carrier rockets and exploring rockets, and large radomes, fairings, high-performance platform panels and the like in spacecraft ground equipment and carrier rocket ground equipment. Many of the key components in these spacecraft and ground equipment, such as satellite communications radomes, rocket radomes, instrument mounting plates, etc., are large-sized planar or low-curvature curved surface members. In the service process, the ceramic composite material not only bears a severe mechanical environment, but also has nearly severe requirements on the geometrical precision (flatness and profile precision) and the dimensional stability of the ceramic composite material. However, the stress of the composite material is uneven due to temperature distribution in the curing process, so that internal stress is concentrated, and further the problems of buckling deformation and the like of a product are caused, and the usability and the assembly precision of the composite material are affected. For example, warping of the wave-transparent cover can directly affect the transmission performance of electromagnetic waves, deformation of the instrument mounting plate can affect alignment and mounting of precision equipment, and splicing accuracy of the large-scale fairing can directly affect aerodynamic appearance. In addition, for a sandwich structure having a foam core, warpage is more likely to occur during curing due to a large difference in thermal expansion coefficient between the core and the panel material. Meanwhile, in the curing process of the composite material, the product generates buckling deformation due to the factors such as material anisotropy and mismatch of thermal expansion coefficients of the core material and the panel, so that the assembly precision and the service performance of the composite material are seriously affected. The traditional uniform temperature field curing method is difficult to effectively control the warping problem of the structure, and restricts the large-scale production of high-precision planar composite products. For the new generation of large-sized, thin-walled and highly integrated space components, such as large-sized plane components of solar cell panel substrates, antenna reflecting surfaces and the like, the requirements on the shape surface precision and flatness are extremely high, and the traditional autoclave curing process is difficult to realize the effective control of warping due to single heating mode and poor temperature field uniformity. The existing researches focus on process parameter optimization or mold compensation, and a method for reconstructing residual stress and realizing near zero warping by actively regulating and controlling temperature field distribution is still lacking. Therefore, the development of the high-precision forming method capable of actively regulating and controlling from the stress generation source and realizing near zero warping has urgent demands and great significance in improving the manufacturing level and performance of products such as carrier rockets, satellites, aerospace ground equipment and the like. Disclosure of Invention The invention aims to provide a near-zero warping forming method of a resin matrix composite plane part, which is particularly suitable for forming a multilayer composite structure with a foam core material, solves the technical problem of warping deformation of a composite product, and realizes high-precision forming of the resin matrix composite plane part by constructing a zoned dynamic temperature field, adopting a plurality of heating units with independent temperature control, accurately controlling the temperature distribution of the composite in the curing process, regulating and controlling the curing sequence, localizing stress, reducing long-range stress accumulation, effectively inhibiting warping deformation. A near zero warping forming method of a resin matrix composite plane part comprises the following steps: Step S1, dynamic temperature field distribution is designed based on multi-physical field coupling simulation, and a heating unit array capable of independently controlling temperature in a partitioned manner and a corresponding temperature monitoring unit are arranged on the lower surface of a f