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Abstract
In this work, experimental and numerical investigation on the deployment of solar panels with tape spring (TS) hinges showing complex nonlinear hysteresis behavior caused by the snap-through buckling was conducted. Subsequently, it was verified by comparing simulation results by multi-body dynamics (MBD) analysis with test results on ground-based deployment testing considering gravity compensation, termed zero-gravity (Zero-G) device. It has been difficult to predict the folding and unfolding behavior of TS hinges because their moment–rotation relationship showed a nonlinear hysteresis behavior. To realize this attribute, an algorithm that checks the sign of angular velocity of the revolute joints was used to distinguish folding from unfolding. The nonlinear hysteresis was implemented in terms of two path-dependent nonlinear moment–rotation curves with the aid of the expression function (a kind of user subroutine) in MBD software RecurDyn. Finally, it was found that the results of the deployment analysis were in excellent agreement with those of the test when the friction torques of the revolute joints were properly identified by an inverse analysis with the test frames, thus validating the MBD model.
Highlights
Several appendages of satellites were stowed inside the launch vehicle (LV) fairing during the launch phase and has to be deployed in orbit using various deployment mechanisms [1,2,3,4]
There were various friction sources such as the slight misalignment of the deployment test device, the resistance forces caused by the air drag and air-bearing of the dummy panels were needed in the multi-body dynamics (MBD) model to compensate such deviation
The nonlinear and path-dependent behavior of tape spring (TS) hinges were realized by the expression function RecurDyn by distinguishing the folding/unfolding status by the sign of angular velocity of the revolute joints with the moment–rotation curves measured by the four-point bending test and push–pull test
Summary
Several appendages of satellites were stowed inside the launch vehicle (LV) fairing during the launch phase and has to be deployed in orbit using various deployment mechanisms [1,2,3,4]. TS were hinges showed a path-dependent moment–rotation profile according job in FE simulation, which were the expression function in RecurDyn. The expression to folding and unfolding that wererealized hardly by tractable in MBD modeling and a time-consuming job function distinguished the folding from unfolding by the sign of angularinvelocity of theThe revolute joints, in FE simulation, which were realized by the expression function expression and it determined the stiffness according the sign of similar to approaches in the function distinguished the folding from to unfolding byangular the signvelocity of angular velocity of the revolute references joints, and[26,27,28]. To the best of our knowledge, this kind of integrated approach, including the modeling of TS hinges, deployment testing of panels on the Zero-G device, and simulation and validation with friction compensation, has rarely tried before due to complexity of this work despite its importance in the relevant industry.
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