Hysteresis poses a significant challenge for control of smart material actuators. If unaccommodated, the hysteresis can result in oscillation, poor tracking performance, and potential instability when the actuators are incorporated in control design. To overcome these problems, a fundamental idea in coping with hysteresis is inverse compensation based on the Preisach model. In this paper, we address systematically the problem of Preisach model inversion and its properties, employing the technique of three-step composition mapping and geometric interpretation of the Preisach model. A Preisach right inverse is achieved via the iterative algorithm proposed, which possesses same properties with the Preisach model. Finally, comparative experiments are performed on a piezoelectric stack actuator (PEA) to test the efficacy of the compensation scheme based on the Preisach right inverse.

Piezoelectric Stack Actuators (PEAs) have been widely used in high-precision positioning system because of its fast response. However, under different excitation voltages and external loads with dynamic frequencies, the width and inclination of PEAs hysteresis curves verified correspondingly, and exhibit asymmetry phenomenon. The main contribution of this paper is to present a two-input asymmetric dynamic cross-coupled hysteresis (TADCH) model to describe the complex nonlinear hysteresis of PEAs in dynamic excitation and loading engineering applications. Moreover, we also develop the corresponding identification method of TADCH model. Finally, several experiments are carried out to verify the accuracy of the proposed model.

The new‐generation manned spacecraft employs a new recovery system of parachutes and airbags. In order to realize the effective cushion of the return capsule airbag, the conversion of the single‐point hanging to the double points for the spacecraft is necessary. In the conversion process, the long hanging rope and the height of the return capsule will cause a large impact and disturbance to the cabin, but the traditional dynamic modeling method is not suitable for those with complex boundary conditions. In order to solve these problems, a finite element model is proposed to analyze the suspension conversion process and simplify the parachute model based on the aerodynamic load dynamic matching control method to analyze the dynamic response characteristics, such as overload, speed, and force of the cabin, quantifying the conditions of the rope in the process. Results are generally consistent with experimental data. This study provides guidance for future optimization work and will greatly support the safe‐return technology of the new‐generation manned spacecraft.

The advancement of deep space exploration, which aims to establish permanent extraterrestrial bases, urgently demands reusable landing buffer systems, a capability beyond the reach of traditional, single‐use buffers like aluminum honeycombs. To address this challenge, this study proposes a novel reusable buffer system based on buffered metamaterials. We introduce a design framework that integrates material development, structural configuration, and system validation. Firstly, we developed a NiTi shape memory alloy suitable for additive manufacturing. By optimizing the laser scanning strategy, we achieved a 3D‐printed NiTi alloy with a fracture strain of 12% and a fracture stress exceeding 700 MPa, meeting the requirements for high strength and large deformation. Subsequently, a zero‐Poisson’s ratio triangular unit‐cell metamaterial configuration was designed, and its platform stress was accurately predicted using a theoretical model. This structure was then fabricated directly using the 4D printing technique with the developed NiTi alloy. Quasi‐static compression tests revealed that the metamaterial could be compressed to 70% strain without fracture, exhibited a stable platform force, and demonstrated a superior shape recovery rate of over 94% after heating. Finally, a prototype three‐legged lander was constructed and subjected to landing impact tests. The results confirmed that the system effectively maintained the impact overload below 12 g and could be fully recovered for repeated use via thermal activation. This work successfully demonstrates a viable pathway for developing reusable landing buffer systems by synergizing 4D‐printed shape memory alloys with rational metamaterial design.