Design And Analysis Of Ground Zero Gravity Experimental System For Circular Solar Wing

With the issuing of the "the 13 th Five-year Plan on Technology and Innovation",the deep space detection has become an important part of China’s aerospace power strategy,which also becomes one of the landmark industry.The round flexible solar wing will be used on the future small celestial detectors in China.The wings keep the closing and pressing state in the launch phase.Once the probe is in orbit,the wing unlocks sequentially the hold-down and release mechanism as required.The spacecraft gains enough power to function properly only after the solar panels are properly deployed and locked.So the unfold and lock of the solar panels normally is one of the most important operations after entering orbit.Therefore,this paper studies the equivalence of circular membrane solar panel in the ground zero gravity deployment test system.The following is the main research work of this paper:Firstly,a zero-gravity compensation device for circular solar wing ground expansion is determined,which mainly unloads the gravity during the circular solar wing expansion by the means of passive following suspension.The conceptual design and composition of the experimental installation are introduced.The numerical analysis of the interference force and unloading rate during the first and second stages in the circular solar wing expansion is made.And the rationality of the zero-gravity unloading system is verified by comparing with the target requirements.Secondly,the modeling of circular membrane solar panel based on ADAMS is introduced,especially the modeling of solar blanket film.The ground expansion zerogravity compensation device is introduced into ADAMS.And various types of interference force data of zero-gravity compensation device experimentally are introduced into ADAMS models,which lays the foundation for the subsequent analysis.Following,round the wing of the different gravity environment dynamics,kinematics analysis,it is concluded that zero gravity environment,2% residual gravity,gravity residuals and 5% to 10% under the gravity residuals of circular solar wing launch dynamics,it is concluded that in the process of deployment time,maximum speed and the roots of hinge force,and according to the circular solar wing on the safety of the lock,It is concluded that the circular solar wing can be safely deployed and locked under various gravity residuals,and the influence degree of different gravity residuals on the circular solar wing deployment is analyzed,and the importance of the accuracy of the unloading rate of the zero-gravity unloading device is concluded.Finally,analysis of zero gravity test unit force inherent in each type of interference in the process of circular thin film solar wing on the weight ratio,based on the ADAMS for the introduction of zero gravity test apparatus and the disturbance of the analysis of the force model,through the system of similarity and equivalence principle of the test system can effectively simulate zero gravity environment situation to evaluate round the wing,The limitations of the zero-gravity test system are put forward to provide a direction for improvement in engineering practice.