In this paper, a ground‐based experimental system for solar array active vibration suppression has been established. Firstly, in order to establish an accurate model of the solar array, the solar array is regarded as a flexible cantilevered thin plate, and the corresponding dynamical equations are derived using the absolute nodal coordinate method. In addition, in this paper, the more advanced MFC piezoelectric patch is used instead of the traditional PZT piezoelectric ceramic patch. The electromechanical coupling finite element model of the P1‐type MFC patch is established and substituted into the kinetic equation of the solar array. Finally, the accuracy of the electromechanical coupling modeling and the control effect of active vibration suppression were verified using the PID control. A set of experimental frameworks for evaluating the active vibration suppression effect, including the free vibration test, sinusoidal perturbation test, and white noise perturbation test, as well as the analysis strategy of the test data, are established.

Rubber shock absorbers are widely used to reduce vibration in aerospace load devices due to their high damping characteristics. However, due to the material nonlinearity of rubber and high temperature, the accurate numerical simulation and practical application of rubber shock absorbers face difficulties and challenges. In this paper, taking a T-type rubber shock absorber as an example, according to the correlation data obtained from the performance test of rubber materials, a constitutive model of rubber materials is established for its hyperelasticity-viscoelasticity simulation analysis. On this basis, the rubber shock absorber was used to carry out the numerical simulation and experimental verification of an Unmanned Aerial Vehicle (UAV) Light Detection And Ranging (LiDAR). The results show that when the rubber constitutive model is used for simulation analysis, the obtained acceleration response curve on the UAV LiDAR is in good agreement with the test results, which effectively confirms the accuracy of the numerical simulation, and successfully verifies that the rubber shock absorber is suitable for vibration reduction of UAV LiDAR. At the same time, this method also provides a practical and effective solution for the vibration reduction design of rubber shock absorbers.

The Microgravity Platform (MP) of the Chinese Space Station is locked and released by Lock-or-Release (L/R) mechanism on both sides. In order to ensure the safety and reliability of the MP under the vibration environment during the rocket launch, the L/R mechanism must output the appropriate locking torque value. Based on the structural characteristics of the Scientific Experiment Cabinet (SEC), this paper proposes a method of evaluating locking torque by combining theory with experiment, and the relationship between locking force and locking torque of L/R mechanism is proved that the locking force on both sides can reach 2000 N at 25 Nm driving torque. Finally, it is verified by vibration test that the locking torque obtained by this method can effectively guarantee the safety and reliability of the MP under vibration environment.

High‐speed penetrators carrying detection equipment impact planetary bodies at high speeds, and they are therefore buried at depths of up to several meters beneath the surface. During the friction and collision with the crust of the planet, the acceleration of the scientific instrumentation is significantly large. The vibration protection structure for scientific instrumentation is necessary for the reduction of the peak value of the acceleration response and the improvement of the survival rate. In this study, a penetrator with a multilayered energy absorbing structure was developed to improve the survival rate of the penetrator, of which the foam‐filled thin‐walled structure (FTS) was applied to the penetrating vibration‐damping structure. The penetration process of the penetrator into the planetary medium was simulated using the LS‐DYNA software platform. The results obtained using empirical formulas and theoretical derivations were compared with the results of the numerical analysis. The reliability of the penetrator limit element model was then verified by conducting an impulse response experiment and simulation. The results suggest that FTS has a positive influence on the isolation impact and energy absorption. Moreover, the vibration isolation effects of nine different FTSs were evaluated with respect to the following six factors: impact isolation efficiency, load efficiency, peak of acceleration, peak impact force, total energy absorption, and specific energy absorption. Furthermore, the design of the damping structure provides an indispensable solution for penetrator detection.