Abstract
In order to study the stress state and stability of a spiral tube and actuator for controlled extension and retraction (STACER) during the launching process of a satellite, finite element software was applied to establish a finite element model of STACER via the explicit dynamics analysis method. The influence of top rod’s radius on the gathering or so called packaging process of STACER was analyzed. The effects of surface friction coefficient and acceleration on the stability were studied during the gathering process. It was found that the top rod radius directly affects the gathering load and the deformation around the rivet of the STACER. When the spring reel is gathered, the friction coefficient between contact surfaces, and the acceleration, work on the stability of STACER. The stability of STACER can be maintained by a friction coefficient with small fluctuations. An unstable state occurs after the STACER is gathered when the direction of acceleration is parallel to the axial direction of the rivet. A mechanical test on the STACER is conducted to verify the reliability and accuracy of the model. The force trend is similar between the finite element result and experimental result. This work will contribute to the theoretical development for designing the radius of the top rod of the spring reel, the surface friction coefficient of the STACER and the position of the spring reel during the launch process of satellites.
Highlights
In the aerospace sector, there is an increasing demand for a deployment mechanism that can be used in areas such as satellite communications, space science and deep space exploration [1,2,3,4].The spiral tube and actuator for controlled extension and retraction (STACER) mechanism is widely used in the aerospace industry due to its advantages, such as a large exhibition ratio, strong thermal symmetry along the ring, and a equipped structure
The differences may determine whether the deployment mechanism can a nonlinear dynamics element model for studying the process finite of storable tubular extendible member (STEM)
Based on the work mentioned above with thin-walled deployable mechanism, the finite of the forming process of the STACER cylinder is proposed. It aims to provide a general method for element model of nonlinear explicit dynamics of STACER mechanism is established by finite element the design and production of a STACER from a theoretical perspective
Summary
There is an increasing demand for a deployment mechanism that can be used in areas such as satellite communications, space science and deep space exploration [1,2,3,4]. The differences may determine whether the deployment mechanism can a nonlinear dynamics element model for studying the process finite of STEM expansion. STACER to complete the process of packaging and deploying due mechanism shows theneeds characteristics of large deformation, large displacement, andalternately large rotation, to different working conditions [29,30]. Based on the work mentioned above with thin-walled deployable mechanism, the finite of the forming process of the STACER cylinder is proposed. It aims to provide a general method for element model of nonlinear explicit dynamics of STACER mechanism is established by finite element the design and production of a STACER from a theoretical perspective. Gradual diameter D and the pitch L are influenced by various factors, including material and forming process parameters
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