CN-121990184-A - Solar sailboard connecting frame structure in bionic spiral layering mode

CN121990184ACN 121990184 ACN121990184 ACN 121990184ACN-121990184-A

Abstract

The invention discloses a solar sailboard connecting frame structure in a bionic spiral layering form, which comprises a joint, a main beam, a secondary beam and a sleeve, wherein the four components are made of carbon fiber composite materials, the joint is of a solid structure, and the main beam, the sleeve and the secondary beam are of square thin-wall structures. The invention provides a damage failure analysis and layering angle optimization method of a solar sailboard connecting frame structure in a bionic spiral layering mode, and the invention improves the connecting frame structure by adopting the bionic spiral layering mode, obviously enhances the shock resistance of the connecting frame structure on the premise of not increasing the quality, and can effectively improve the reliability and safety of a spacecraft.

Inventors

NIE YUNQING
LI PEIPEI
DUAN ZEWEN
DI HAOXUAN
WANG XINRU
ZHANG YI

Assignees

内蒙古大学

Dates

Publication Date: 20260508
Application Date: 20260119

Claims (10)

1. The solar sailboard connecting frame structure in the form of a bionic spiral layering comprises a connector and a sailboard, wherein the connector is used for being arranged on a star structure of a spacecraft and is a connecting unit with the star structure, and the solar sailboard connecting frame structure is characterized by also comprising sleeves, wherein the sleeves are arranged on two sides of the connector, the connectors are fixedly connected with a main beam through the sleeves, and the sleeves are used for being connected with the sailboard structure and mainly bear bending moment and torque and are main bearing structures for bearing impact loads of the sailboard; The side beams are used for connecting the two sleeves to strengthen the stability of the whole structure; the main beam, the sleeve and the side beam are all square thin-wall structures, the square thin-wall structures are formed by layering single-layer carbon fiber reinforced composite materials along the thickness direction, and interlayer fibers have the same helix angle and are in a bionic spiral layering mode.
2. The bionic spiral-paved solar sailboard connecting frame structure of claim 1, wherein the connector is of a solid structure and is formed by paving a single-layer carbon fiber reinforced composite material along the thickness direction, and the fiber directions in all layers are the same.
3. The solar panel connection frame structure in the form of a bionic spiral lay according to claim 1, wherein the four components of the joint, the main beam, the sleeve and the side beam are all made of carbon fiber reinforced composite materials.
4. The bionic spiral-paved solar sailboard connecting frame structure of claim 1, wherein the spiral angle of interlayer fibers of the single-layer carbon fiber reinforced composite material of the square thin-wall structure in the square thin-wall structure of the main beam, the sleeve and the side beam is 30 degrees.
5. The method for determining the helix angle of a solar sailboard connector structure in the form of a bionic spiral lay according to claim 1, comprising the steps of: s51, determining structural parameters aiming at the connecting frame structure, wherein the structural parameters comprise the length of a main beam, the length of a side beam, the length of a sleeve, the length of a joint, the side lengths, the thickness and the number of layers of the main beam, the sleeve and the side beam, and the single-layer thickness of the carbon fiber reinforced composite material; S52, determining relevant material parameters, wherein the parameters comprise longitudinal elastic modulus, transverse elastic modulus, in-plane Poisson' S ratio, shear modulus, longitudinal tensile strength, longitudinal compressive strength, transverse tensile strength, transverse compressive strength and shear strength of the carbon fiber reinforced composite material; S53, giving initial spiral angle of bionic spiral solar panel connecting frame structure ; S54, establishing a finite element model of the solar sailboard connecting frame structure in a bionic spiral layering mode according to the parameters; S55, applying equivalent impact load to the solar sailboard connecting frame structure, and performing failure analysis on the solar sailboard connecting frame structure in the bionic spiral layering mode by using a progressive damage analysis method; s56, obtaining the end displacement of the main beam from the damage analysis result, and calculating the spiral angle as Equivalent energy consumption of time connection frame structure ; S57, if Step S58 is executed, otherwise, the process is executed Repeatedly executing S53-S56; S58, constructing the ordinate as equivalent energy consumption The abscissa is the helix angle From which the helix angle corresponding to the maximum value of equivalent energy consumption is selected Is the optimal layering angle.
6. The bionic spiral-paved solar sailboard connecting frame structure of claim 1, wherein the progressive damage analysis method comprises the following specific analysis steps: S61, applying an initial load step to the finite element model; s62, solving stress strain by utilizing constitutive relation considering damage; S63, judging whether initial damage occurs or not based on Hashin failure criteria, if the damage failure criteria are not met, increasing the load, and executing S62; s65, calculating a damage variable, carrying out reduction degradation treatment on the rigidity of the damage variable, and calculating a damage rigidity matrix; And S66, judging whether the material is completely failed, if so, ending the analysis, and if not, increasing the load, and repeating the step S62.
7. The biomimetic spiral-layered solar array connector structure of claim 6, wherein the constitutive relation of considering the damage of S62 is as follows: ; In the middle of As a function of the stress tensor, In order to be a strain tensor, For the damage stiffness matrix, it can be expressed as follows ; In the formula, For the modulus of elasticity in the machine direction, For the modulus of elasticity in the transverse direction, And In the form of a poisson's ratio, In order to achieve a shear modulus, the polymer is, In order to represent the variable of the damaged state of the fiber, In order to represent a variable of the damaged state of the substrate, Is a variable representing the state of shear damage.
8. The biomimetic spiral-clad form solar array connector structure of claim 7, wherein the Hashin failure criteria for four failure modes of S63 are as follows: (1) Fiber tensile failure ): ; (2) Fiber compression failure ): ; (3) Failure of matrix in stretching ): ; (4) Matrix compression failure ): ; In the above-mentioned method, the step of, For in-plane normal stresses along the principal direction of the fiber, Is in-plane normal stress perpendicular to the principal direction of the fiber, As the in-plane shear force, For the longitudinal tensile strength, the tensile strength of the steel sheet, In order to achieve a compressive strength in the machine direction, In order to achieve a tensile strength in the transverse direction, In order to achieve a compressive strength in the transverse direction, Is shear strength.
9. The biomimetic spiral-clad solar array connector structure of claim 7, wherein the S65 damage variables include the following: Variable of fiber damage : ; Matrix damage variable : ; Variable of shear damage : ; In the formula, As a variable of the tensile damage of the fiber, As a variable of the compression injury of the fiber, As a variable of the tensile damage of the matrix, Is a variable of basal compression injury.
10. The biomimetic spiral-clad form solar array connector structure of claim 9, wherein the fiber stretch damage variable, fiber compression damage variable, matrix stretch damage variable, matrix compression damage variable can be calculated by the following formula: ; In the subscript Indicating the type of damaged material, which may be a fiber Damage or substrate Injury, superscript Indicating the damage pattern, which may be stretching Injury or compression Damage; the initial equivalent displacement corresponding to the initial damage of the failure mode is satisfied, Is the displacement corresponding to the complete damage of the material in the failure mode, For equivalent displacement in each failure mode, the following equation can be used to solve: (1) Fiber tensile failure ): ; (2) Fiber compression failure ): ; (3) Failure of matrix in stretching ): ; (4) Matrix compression failure ): ; In the above-mentioned method, the step of, , For positive in-plane strain along the fiber direction, Is an in-plane positive strain perpendicular to the fiber direction, In-plane shear strain is used to provide a high degree of in-plane shear strain, Is the cell characteristic length.

Description

Solar sailboard connecting frame structure in bionic spiral layering mode Technical Field The invention belongs to the technical field, and particularly relates to a solar sailboard connecting frame structure in a bionic spiral layering mode. Background Composite materials are materials with new properties that consist of two or more component materials of different properties on a macroscopic scale. The fiber reinforced composite material has the advantages of light weight, high strength, high rigidity and the like, and is widely applied to structural components such as carrier rockets, missiles, spacecraft, satellites and the like. The spacecraft is subjected to extreme mechanical load environments such as high stress, impact and the like in the launching, on-orbit flight and landing processes, and the factors can cause brittle fracture of the fiber reinforced composite material, so that the safety of the spacecraft is threatened. After the solar sailboard of the spacecraft is unfolded, the solar sailboard of the spacecraft is connected with the cabin structure through the connecting frame. The connecting frame mainly plays a role in connecting the solar sailboard with the main structure of the spacecraft, and simultaneously transmits torque of the driving mechanism to realize the sun alignment of the solar sailboard. Therefore, the reliability and safety of the on-orbit operation of the connecting frame are important to ensure the overall performance of the solar sailboard and even the spacecraft. When the spacecraft is in orbit or attitude maneuver, impact load can be generated on the connecting frame, and fracture failure is easy to occur. Therefore, the requirements on the material strength, rigidity and toughness of the connecting frame are high. In order to reduce the quality of the solar panel connector, carbon fiber composite materials are generally selected as the preferred materials. The carbon fiber composite material has higher strength and rigidity, but has poorer toughness and is easy to break and lose efficacy. Disclosure of Invention The invention aims to provide a bionic spiral-layered solar sailboard connecting frame structure, which aims to solve the problems that a carbon fiber composite material has higher strength and rigidity, but has poorer toughness and is easy to break and lose efficacy. In order to achieve the aim, the invention provides the technical scheme that the solar sailboard connecting frame structure in the form of a bionic spiral layering comprises a connector and a sailboard, wherein the connector is used for being arranged on a star structure of a spacecraft and is a connecting unit with the star structure; the sleeve is arranged at two sides of the joint, the joint and the main beam are fixedly connected with each other through the sleeve, the sleeve is used for connecting a sailboard structure and mainly bears bending moment and torque, and the sleeve is a main bearing structure of the sailboard impact load; The side beams are used for connecting the two sleeves to strengthen the stability of the whole structure; the main beam, the sleeve and the side beam are all square thin-wall structures, the square thin-wall structures are formed by layering single-layer carbon fiber reinforced composite materials along the thickness direction, and interlayer fibers have the same helix angle and are in a bionic spiral layering mode. Preferably, the joint is of a solid structure and is formed by layering a single-layer carbon fiber reinforced composite material along the thickness direction, and the fiber directions in all layers are the same. Preferably, the joints, the main beams, the sleeves and the side beams are all made of carbon fiber reinforced composite materials. Preferably, in the square thin-wall structure of the main beam, the sleeve and the side beam, the helix angle of the interlayer fiber of the single-layer carbon fiber reinforced composite material of the square thin-wall structure is 30 degrees. The spiral angle determining method of the solar sailboard connecting frame structure in the bionic spiral layering form is characterized by comprising the following steps of: s51, determining structural parameters of the connecting frame structure, wherein the structural parameters comprise the length of a main beam, the length of a side beam, the length of a sleeve, the length of a joint, the side lengths, the thickness and the number of layers of the main beam, the sleeve and the side beam, and the single-layer thickness of the carbon fiber reinforced composite material (the parameters are determined when the model and the size of the solar sailboard are determined in the actual process); S52, determining relevant material parameters (namely parameters which can be directly determined after materials are selected) specifically including longitudinal elastic modulus, transverse elastic modulus, in-plane Poisson' S ratio, shear modulus, longitudinal tensile strength,