Dynamics equivalent continuum modeling method of truss antenna

Abstract

The invention discloses a dynamics equivalent continuum modeling method of a truss antenna. The method comprises the following steps: extracting an antenna subunit from a periodic truss antenna for analysis; equalizing shape memory composite materials of longitudinal beams in the antenna subunits to isotropic materials, considering connection characteristics of hinges, and calculating strain energy and kinetic energy of the antenna subunits; establishing a kinetic equivalent continuum model of the truss antenna based on an energy equivalence principle; and verifying the effectiveness of the truss antenna dynamics equivalent continuum model, and correcting equivalent material parameters of the longitudinal beam shape memory composite material. According to the invention, the material characteristics of the longitudinal beam shape memory composite material and the connection characteristics of the hinge are considered; the equivalent continuum model of the truss antenna is more accurate,the engineering practical method for correcting the equivalent material parameters of the shape memory composite material is provided, and meanwhile, the modeling method disclosed by the invention isclear in process, convenient and fast in algorithm implementation and suitable for application and popularization in engineering.

Description

technical field [0001] The invention relates to the research field of dynamic modeling of flexible spacecraft, in particular to a dynamic equivalent modeling of a large-scale complex high-dimensional deployable truss antenna structure. Background technique [0002] The mass and moment of inertia of the traditional central rigid body of the spacecraft have an absolute advantage in the proportion of the entire system, and it is a typical rigid-flexible coupling system in which the central rigid body dominates. With the development of aerospace technology, large flexible spacecraft with the typical characteristics of large size, light weight and flexibility have become an important trend in the development of a new generation of spacecraft. For example, an ultra-long truss antenna is installed on the US ISAT (OCS) satellite, and its length reaches nearly 300m. [0003] The large-scale spatial deployable truss antenna structure is a typical periodic structure with several ident...

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Problems solved by technology

At present, most researches on the equivalent continuum modeling of large flexible spacecraft focus on the flexible structure with ideal geometric configuration, but it is difficult to realize the complex flexible truss antenna combination structure; the current equivalent modeling The methods are all aimed at the spacecraft structure with a single homogeneous material, but not for the heterogeneous material structure with shape memory composite materials. The difficulty comes; the current equivalent modeling only considers the ideal connection, and the spacecraft truss and the area array are connected by hinges, and the overall connection of the spacecraft has many hinges, and the connection stiffness of the hinges will affect the dynamics of the truss antenna structure. characteristics have a greater impact on

In view of this, the current equivalent continuum modeling technology cannot well solve these problems of large flexible spacecraft

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