Abstract
Micro satellites must survive severe mechanical conditions during their launch phase. One design requirement for rockets is the stiffness requirement, i.e. the natural frequencies requirement. In the early stages of satellite development, presumption of the natural frequency of a satellite may be difficult. The material used for the structure of many micro satellites is an aluminum alloy. The structure subsystem occupies a large portion of the satellite mass, and the elastic modulus of this aluminum alloy is larger than that of other subsystems. Therefore, the mechanical property of the aluminum alloy cannot be used to represent the mechanical property of the whole satellite. The density of an actual satellite differs from the density of the aluminum alloy. Therefore, when estimating the minimum natural frequency, the size and the elastic modules of an actual satellite structure must be used. When using an actual satellite structure, the estimated minimum natural frequencies of the lateral direction and the longitudinal direction during the ascent phase are in agreement with the measured values acquired by the vibration tests. In order to shorten a process of satellite development, this paper describes a practical method for estimating the natural frequency of a cube-shaped micro satellite This paper is a modified version of the previous paper [1] using new measurement results.
Highlights
When a spacecraft such as a probe, which explores a planet or the sun, or a satellite which goes the around the earth, is launched with a rocket, they are exposed to severe mechanical conditions
Micro satellite design is performed through a procedure which designs and manufactures a bread board model, an engineering model. These models used for evaluation have satisfied the strength requirement and the stiffness requirement by using a vibration test. The design of these models is performed by CAD and the internal stress analysis and the natural frequency analysis of a micro satellite structure during the ascent phase are conducted in a finite-element-method analysis
In order to shorten the process of satellite development, this paper describes a practical estimation method of the natural frequency of a cube form micro satellite
Summary
When a spacecraft such as a probe, which explores a planet or the sun, or a satellite which goes the around the earth, is launched with a rocket, they are exposed to severe mechanical conditions. Significant stresses are generated on a micro satellite structure according to the static loads and the dynamic loads during the ascent phase These stresses must not deviate from the allowable yield strength or the ultimate strength of the structure materials. Micro satellite design is performed through a procedure which designs and manufactures a bread board model, an engineering model These models used for evaluation have satisfied the strength requirement and the stiffness requirement by using a vibration test. The design of these models is performed by CAD and the internal stress analysis and the natural frequency analysis of a micro satellite structure during the ascent phase are conducted in a finite-element-method analysis. This paper is a modified version of the previous paper [1] using new measurement results
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