Abstract
Petal-type Deployable Solid-surface Reflector (PDSR) is a kind of important structure widely applied in deployable reflector antennas in aerospace engineering. The dynamic properties of this reflector structure in deployed state are significant to the reflector accuracy for antennas. However, the study of the dynamic evaluation of deployable structure with revolute joints is difficult and seldom concerned by researchers. In order to study dynamic properties of the PDSR, the Cable Replacement Method (CRM) was utilized to equivalently simulate the nonlinear structural stiffness of the revolute joint for numerical analyses. The Finite Element Model (FEM) of this reflector structure was established by commercial software ANSYS (ANSYS Inc., Canonsburg, PA, USA) and verified by the theoretical analysis and dynamic test of actual prototype model. The natural frequencies and mode shapes of deployed reflector were computed to study the influence of drag spring design parameters as stiffness, pre-tensioned force, and distance of two adjacent linkage butts. Finally, the analysis results were concluded that the drag springs between two adjacent petals can essentially improve the dynamic performance of reflector structure in deployed state. It can be a useful technical system for future engineering applications of PDSR antennas.
Highlights
Deployable structures have been widely applied to the aerospace industry [1,2,3], such as aperture antennas [4,5,6,7,8], solar arrays [9,10], space masts [11,12], and so on
The Petal-type Deployable Solid-surface Reflector was researched from a perspective of its structural dynamic properties
The Finite Element Model (FEM) of this reflector structure were established on the basis of ANSYS and verified by the theoretical analysis and dynamic test of actual prototype model
Summary
Deployable structures have been widely applied to the aerospace industry [1,2,3], such as aperture antennas [4,5,6,7,8], solar arrays [9,10], space masts [11,12], and so on. One of the most important advantages is the perfect package property [13] of deployable structures so as to store in the fairing of launch vehicle and deploy into structures in orbit. This way can enormously reduce the weight and enlarge the size of these pay-load structures. In order to fulfill this function, the deployable mechanism is necessarily employed by segmented bodies, kinematic pairs, and driving devices. These components may damage the structural integrity or lead to the nonlinear response and weaken
Sign-in/Register to view highlights & summary Talk to us
Join us for a 30 min session where you can share your feedback and ask us any queries you have
Schedule a callDisclaimer: All third-party content on this website/platform is and will remain the property of their respective owners and is provided on "as is" basis without any warranties, express or implied. Use of third-party content does not indicate any affiliation, sponsorship with or endorsement by them. Any references to third-party content is to identify the corresponding services and shall be considered fair use under The CopyrightLaw.
