CN102882008B - Low-expansion mesh reflector using composite material connectors - Google Patents

Abstract

The invention relates to a low-expansion mesh reflector using composite material connectors, and belongs to the technical field of space antenna reflectors. Including back ribs, reflective surfaces and connectors; the reflective surface is a quasi-isotropic TWF fabric reflective surface, and the back ribs are back ribs of composite laminates, which are in the shape of a "well" and have a symmetrical structure; The angle between the back ribs, so that the connecting piece is fixedly connected with the two intersecting back ribs; the embedded part of the connecting piece is located on the bottom surface of the connecting piece, and the reflector is fixed or installed through the embedded piece of the connecting piece for transportation or storage. The reflective surface in the present invention adopts quasi-isotropic TWF fabric, which has very high light transmittance and small thermal expansion coefficient, can effectively reduce the influence of space light pressure on the reflective surface profile, and can reduce the impact of the reflective surface on the reflective surface. The temperature gradient generated in the space thermal environment, and the reduction of the temperature gradient can reduce the thermal deformation of the reflective surface.

Description

A low-expansion mesh reflector using composite connectors

technical field

The invention relates to a low-expansion mesh reflector using composite material connectors, and belongs to the technical field of space antenna reflectors.

Background technique

At present, with the rapid development of space technology, space antenna technology, which is an important payload of spacecraft, has also made great progress. There are more and more types of antennas and more and more complex structures. The reflector antenna has gradually developed into an antenna with a deployable reflector that can be deployed in space, and the antenna reflector is required to have small mass, high rigidity and strength, and small thermal deformation in space. The traditional antenna reflector form can no longer meet the requirements of the reflector with small mass, high stiffness and strength, and small thermal deformation in space. It is necessary to design a reflector structure with small mass, high stiffness and strength, and small thermal deformation in space.

Contents of the invention

The purpose of the present invention is to overcome the shortcomings of traditional reflectors such as large mass and large thermal deformation in space, and provide a low-expansion mesh reflector using composite material connectors.

The purpose of the present invention is achieved through the following technical solutions.

A low-expansion mesh reflector using carbon fiber composite material connectors of the present invention includes back ribs, reflective surfaces and connectors; the reflective surface is a quasi-isotropic carbon fiber woven mesh cloth (TWF) fabric reflective surface, and the back ribs are composite The back rib of the material laminate is in the shape of a "well" and has a symmetrical structure; the connector is located at the angle between the two intersecting ribs in the back rib, so that the connector and the two intersecting ribs are fixedly connected; the connector is a belt A hollow hexahedral cylinder with a bottom surface, the cross-section of the cylinder is a hexagon, in which the length of three sides is long and the length of the other three sides is short; the lengths of the three non-adjacent sides are the same, and in addition The lengths of the three non-adjacent sides are the same; there is a trapezoidal groove on the surface corresponding to one of the long sides; the connector embedded part is located on the bottom surface of the connector, and the reflector is fixed or installed through the connector embedded part for easy transport or storage.

The advantage of the present invention compared with prior art is:

The reflective surface in the present invention adopts quasi-isotropic TWF fabric, which has very high light transmittance and small thermal expansion coefficient, can effectively reduce the influence of space light pressure on the reflective surface profile, and can reduce the impact of the reflective surface on the reflective surface. The temperature gradient generated in the space thermal environment, and the reduction of the temperature gradient can reduce the thermal deformation of the reflective surface;

The structurally symmetrical "well" shaped composite material laminate back reinforcement used in the present invention has higher specific rigidity, less thermal expansion coefficient, and is equivalent to the thermal expansion coefficient of the TWF fabric mesh reflective surface simultaneously, and the two are combined like this It has good thermal matching, which can reduce the thermal deformation of the reflector and improve the overall rigidity of the reflector at the same time;

The composite material connecting piece adopted in the present invention has good structural strength for carrying launch loads, and at the same time has a small coefficient of thermal expansion, which is thermally matched with the mesh reflective surface and can effectively reduce local thermal deformation of the reflective surface.

Calculation of thermal deformation of low expansion mesh reflector:

In order to verify the on-orbit thermal deformation of this low-expansion reflector structure using composite material connectors, the corresponding thermal deformation analysis calculations were carried out. The temperature field used in the analysis is the temperature field of the worst working condition selected according to the results of the on-orbit thermal analysis. is 30°C. The maximum thermal deformation in the antenna mesh reflector surface calculated according to the worst temperature field working condition of the antenna in orbit fully meets the requirements of the antenna for the accuracy of the reflector surface.

Description of drawings

Fig. 1 is the structural representation of low-expansion mesh reflector;

Fig. 2 is the structural representation of connector;

Fig. 3 is a structural schematic diagram of a reflective surface;

Among them, 1-back rib, 2-reflecting surface, 3-connector, 4-embedded connector.

Detailed ways

The present invention will be further described below in conjunction with drawings and embodiments.

Example

A low-expansion mesh reflector using a composite material connector, including a back rib 1, a reflective surface 2, a connector 3, and a connector embedded part 4; the reflective surface 2 is a quasi-isotropic TWF fabric reflective surface, and the back rib 1 is a composite The back rib of the material laminate is in the shape of a "well" and has a symmetrical structure; the connector 3 is located at the angle between the two intersecting ribs in the back rib 1, so that the connector 3 is fixedly connected to the two intersecting ribs; the connection Part 3 is a hollow hexahedron cylinder with a bottom surface, and the cross-section of the cylinder is a hexagon, wherein the length of three sides is long, and the length of the other three sides is short; the sides of the three sides that are not adjacent The lengths are the same, and the lengths of the three non-adjacent sides are the same; there is a trapezoidal groove on the surface corresponding to one of the long sides; the connector embedded part 4 is located on the bottom surface of the connector 3, through the connector embedded part 4 Fix or mount the reflector for transport and storage.

The structure of the back rib 1 adopts composite material laminates to form a well-shaped symmetrical structure. Its structural rigidity is large, and the natural frequency in the folded state is greater than 70Hz, which greatly enhances the ability of the reflector structure to resist the vibration environment during the launch stage.

The reflective surface 2 is made of quasi-isotropic TWF fabric, and its light transmittance is above 60%, which can effectively reduce the influence of spatial light pressure on the antenna reflective surface. The coefficient of thermal expansion is less than 2.0×10 ^-6 , which greatly reduces the thermal deformation of the reflection surface structure on the track.

The connector 3 is made of carbon fiber composite material, and its thermal expansion coefficient is about 2.0×10-6, which is much smaller than that of the metal connector, which can effectively avoid local deformation of the structure in the space environment.

The connector embedded part 4 is used to fix or install the reflector for easy transportation and storage.

Calculation of thermal deformation of low expansion mesh reflector:

In order to verify the on-orbit thermal deformation of this low-expansion reflector structure using composite material connectors, the corresponding thermal deformation analysis calculations were carried out. The temperature field used in the analysis is the temperature field of the worst working condition selected according to the results of the on-orbit thermal analysis. The gradient is 30°C. The maximum thermal deformation of the antenna mesh reflector calculated according to the worst working condition of the antenna’s on-orbit temperature field; the corresponding thermal deformation analysis and calculation is carried out by using the finite element method, and the input temperature field is based on the maximum thermal deformation during the antenna’s on-orbit use Under harsh working conditions and temperature conditions, the calculated maximum thermal deformation in the antenna mesh reflector surface is 0.355mm, which fully meets the requirements of the antenna for the accuracy of the reflector surface.

Claims (1)

1. A low-expansion mesh reflector using carbon fiber composite material connectors, characterized in that: comprise back ribs (1), reflective surfaces (2) and connectors (3); reflective surfaces (2) are quasi-isotropic On the TWF fabric reflective surface, the back rib (1) is the back rib of a composite laminate, which is in the shape of a "well" and has a symmetrical structure; Part (3) is fixedly connected with the two back ribs crossed; Connector (3) is a hollow hexahedron cylinder with a bottom surface, and the cross section of the cylinder is a hexagon, wherein the lengths of three sides are long, The length of the other three sides is short; the lengths of the three non-adjacent sides are the same, and the lengths of the other three sides are the same; there is a trapezoidal groove on the surface corresponding to one of the long sides; the connector The embedded part (4) is located on the bottom surface of the connecting part (3), and the reflector is fixed or installed through the connecting part embedded part (4) to facilitate transportation or storage; The quasi-isotropic TWF fabric reflective surface contains mesh holes in two shapes: triangle and hexagon; "Well"-shaped back reinforcement (1) adopts composite material laminates without holes; The connecting piece (3) is formed by pressing carbon fiber composite material.