In order to obtain the lunar lander soft landing performance impact caused by the body gravity centerline shift, a seven-degree-of-freedom dynamic model is established based on the inertia force, and a dynamics and kinematics equation is deduced. The dynamic model was verified by the lunar lander scale model and soft landing impact experimental platform. Soft landing performance effects caused by the lander body gravity centerline shifts are analyzed according to the displacement of the body, the body overload, primary/secondary pillar load, and buffer processes. The research results show that the gravity centerline shift has a significant influence on the lunar lander soft landing performance; when the lunar lander lands on the lunar slope—in a downward direction along the slope—the appropriate shift of the position of the gravity centerline can effectively improve the soft landing performance and stability.

The dynamic analysis of the soft landing of the lunar probe is very important to the design of the probe. The initial movement and attitude parameters of the probe during landing have a direct influence on the landing impact. In order to investigate the lunar probe soft-landing dynamic impact by different initial horizontal velocities, pitch angles, and inclinations of the lunar slope, an inertial force-based 7-DOF soft-landing dynamic model is applied under two conditions: the upward and downward slope landing surfaces. The impact on the dynamic characteristics of soft landing is analyzed in terms of body displacement, body overload, and the forces of the primary and secondary buffer struts due to the change of initial horizontal velocity and initial pitch angle of the probe. The result shows that, in 2-2 landing mode, the stress conditions on the primary and secondary struts are obviously impacted by initial horizontal velocity, and the initial pitch angle affects the body overload and the loading state of the secondary buffer strut. The body overload and landing impact could be significantly mitigated if the lunar probe’s horizontal landing speed is limited within 1 m/s, the pitch angle is limited within 12°, and the landing is along the uphill terrain with the inclination of the lunar slope less and equal to 9°. The analysis can directly determine the range of the horizontal speed and pitch attitude angle to ensure the safety of landing, and provide a reference for the reasonable control design of the lander’s horizontal speed and pitch attitude.

To meet the in-orbit maintenance requirements of malfunctioning satellites and maintenance satellites rigid connections, a new type of latching mechanism based on satellite-rocket docking ring is proposed, which has light weight, good structural stiffness, simple motion and locking mechanism, simple control logic, high reliability and large range of docking ring size adaptation. A multi-body dynamic model of the docking ring latch mechanism, malfunctioning satellite and maintenance satellite were established, the maximum locking force and maximum friction of the latch mechanism and the maximum stress of the latching joint and crank of the direct force component were analyzed, and the change of locking force and friction under the three typical in-orbit maneuvering conditions were studied. The results show that: the maximum locking force and maximum friction of the latch mechanism on the docking ring is 1300N and 320N, respectively, stable locking force and friction are 300N and 80N, respectively, the maximum stress occurs on connecting rod which is 865 MPa; In-orbit maneuvering has little effect on the locking force and friction of the docking ring latch mechanism, and the docking ring latch mechanism can always lock the malfunctioning satellite steadily and reliably.

According to the dynamic characteristics of the adhesion desorption process between gecko-like polyurethane setae and the contact surface, the microcontact principle of an elastic sphere and plane is established based on the Johnson–Kendall–Robert model. On this basis, combined with the cantilever beam model, microscale adhesive contact models in the case of a single and an array of setae are obtained. The contact process is numerically simulated and verified by the adhesion desorption test. After that, the effects of external preload, the elastic modulus of setae material, the surface energy, and the surface roughness on the contact force and depth during the dynamic contact process of setae are studied. The results show that the error between the simulation and test is 15.9%, and the simulation model could reflect the real contact procedure. With the increase in preload, the push-off force of the setae array would grow and remain basically constant after reaching saturation. Increasing the elastic modulus of setae material would reduce the contact depth, but have little effect on the maximum push-off force; with the increase in the surface energy of the contact object, both the push-off force between the objects and the contact depth during desorption would increase. With the increase in wall roughness, the push-off force curve of the setae array becomes smoother, but the maximum push-off force would decrease. By exploring the dynamic mechanical characteristics of the micro angle of setae, the corresponding theoretical basis is provided for the numerical simulation of the adsorption force of macro materials.