The vibration generated by the inflatable structure after deployment has a great impact on the performance of the payloads. In this paper, the influence of the control moment gyroscope (CMG) on the dynamic responses and characteristics of an inflatable space structure is studied, based on the flexible multibody dynamics in combination of the absolute nodal coordinate formulation (ANCF) and the natural coordinate formulation (NCF). Firstly, the ANCF and NCF are used to accurately describe the large deformations and large overall motions of flexible inflatable tubes and rigid satellites, respectively. Afterwards, by using the Lagrange equation, a rigid body dynamic model of the CMG is established in detail, which can be attached to and coupled with any flexible bodies without any assumptions. Then, the orbital dynamic equations of the inflatable space structure coupled with distributed CMGs are obtained by considering the effects of Coriolis force, centrifugal force, and gravity gradient through coordinate transformation. The dynamic characteristics of the inflatable space structure are also analyzed by deriving the eigenvalue problem of a flexible multibody system. Finally, the accuracy of the CMG dynamic model is verified via a classic heavy top example. And several numerical examples are presented to study the influence of the magnitudes and directions of the rotor angular momentum of the CMG on the dynamic responses and characteristics of the inflatable space structure.

The perpendicularity error of the holes is prone to occur in the process of manual hole making or robot hole making, which leaves a safety hazard for the composite structure. In this study, the fatigue tests are carried out on the Carbon Fibre-reinforced Polymer (CFRP) single-lap single-bolt joints and effects of the perpendicularity error on the fatigue behaviors are studied. By combining the permanent displacement and stiffness of the joints, the evolution of fatigue damage is analyzed. The results show that the perpendicularity error causes stress concentration and hole fastener clearance near the hole entrance under the preload. The perpendicularity error in the 0° direction will greatly reduce the high-cycle fatigue and the impact on the low-cycle fatigue is relatively small, while the error in the 180° direction is just the opposite. The fatigue life is negatively correlated with the angle of the perpendicularity error. The effect of perpendicularity error in 0° direction on the fatigue damage evolution is to speed up the accumulation of damage, while the effect of error in 180° direction is mainly to cause more damage in the early stage of cyclic loading. The effect of perpendicularity error on the stiffness during fatigue loading is relatively insignificant.

The vibration generated by the inflatable structure after deployment has a great impact on the performance of the payloads. In this paper, the influence of the control moment gyroscope (CMG) on the dynamic responses and characteristics of an inflatable space structure is studied, based on the flexible multibody dynamics in combination of the absolute nodal coordinate formulation (ANCF) and the natural coordinate formulation (NCF). Firstly, the ANCF and NCF are used to accurately describe the large deformations and large overall motions of flexible inflatable tubes and rigid satellites, respectively. Afterwards, by using the Lagrange equation, a rigid body dynamic model of the CMG is established in detail, which can be attached to and coupled with any flexible bodies without any assumptions. Then, the orbital dynamic equations of the inflatable space structure coupled with distributed CMGs are obtained by considering the effects of Coriolis force, centrifugal force, and gravity gradient through coordinate transformation. The dynamic characteristics of the inflatable space structure are also analyzed by deriving the eigenvalue problem of a flexible multibody system. Finally, the accuracy of the CMG dynamic model is verified via a classic heavy top example. And several numerical examples are presented to study the influence of the magnitudes and directions of the rotor angular momentum of the CMG on the dynamic responses and characteristics of the inflatable space structure.