High-overload testing equipment is a key platform for evaluating mechanical performance under extreme conditions, requiring specialized functional design to meet stringent operational demands. The current design process faces numerous challenges, including overreliance on designers’ experience, incomplete requirement analysis, and insufficient automation, resulting in suboptimal solutions. To address these issues, in this study, we propose an integrated method based on axiomatic design (AD) and the Theory of Inventive Problem Solving (TRIZ). This method systematically decomposes technical specifications, maps requirements to a structural framework, and resolves design conflicts using inventive principles. The method employs a comprehensive evaluation framework combining the analytic hierarchy process (AHP) and quality function deployment (QFD) to quantitatively assess candidate designs. It facilitates the development of efficient, standardized high-load testing equipment solutions, enhancing design reliability and innovation capabilities.

To address the insufficient prediction accuracy of traditional Arrhenius-type empirical correlations for hydrogen–oxygen combustion ignition delay time (IDT) over wide operating conditions, this paper proposes a data-driven prediction method based on Gaussian Process Regression (GPR). Based on 413 sets of shock tube and rapid compression machine experimental data, with temperature, pressure, and equivalence ratio as input features, an IDT prediction model was constructed. The GPR model adopts the Matérn 3/2 kernel function combined with the Automatic Relevance Determination (ARD) strategy for hyperparameter optimization. As a benchmark comparison, LASSO regression was employed for feature selection and parameter estimation of the Arrhenius empirical correlation. On a stratified sampling test set, the GPR model achieved a coefficient of determination R² of 0.8587 ($R_{ln}^2$ = 0.9271 on logarithmic scale), significantly outperforming the Arrhenius model’s R² of 0.5422 ($R_{ln}^2$ = 0.7027). In 50 random-split stability tests, GPR yielded a mean R² of 0.9180 with a standard deviation of only 0.0333, demonstrating excellent robustness. This study provides a valuable reference for ignition performance prediction of hydrogen–oxygen combustion systems.

Clearance-containing flexible oscillating mechanisms are widely used in aerospace systems, robotic manipulators, precision manufacturing systems, and intelligent machinery, where their nonlinear dynamic behavior directly affects motion accuracy, stability, and operational reliability. The combined effects of joint clearance, structural flexibility, contact–impact, and constraint nonlinearities can induce rigid–flexible coupled vibration, bifurcation, chaos, and nonsmooth responses. This review systematically summarizes recent advances in dynamic modeling, nonlinear dynamic analysis, vibration and chaos control, experimental validation, and engineering applications of such mechanisms. Particular attention is given to contact–impact models, rigid–flexible and clearance–flexibility coupled formulations, bifurcation and chaos analysis, active, passive, and semi-active control, Nonlinear Energy Sinks (NESs), hybrid control, and Digital Twin-enabled validation. Existing studies indicate that continuous contact force models and flexible multibody formulations remain widely adopted, while the bidirectional coupling between joint clearance and structural deformation is a primary source of complex nonlinear behavior. Hybrid active–passive control is receiving increasing attention, and NESs show strong potential for broadband vibration suppression. However, current research is still limited by insufficient multiphysics coupling, incomplete understanding of high-dimensional nonsmooth dynamics, underdeveloped motion-accuracy-oriented control frameworks, and limited long-term experimental validation. Future research should emphasize high-fidelity multiphysics modeling, data-driven dynamic prediction, intelligent vibration control, NES optimization, and Digital Twin-based online validation.

The cloud model provides a unified mathematical framework for representing both randomness and fuzziness simultaneously, offering an effective mathematical tool for modeling complex systems. This paper focuses on the emergent phenomenon of spontaneous synchronous flashing in fireflies and employs Gaussian cloud model theory to develop an initialization framework. Uncertainty is quantified using three core numerical characteristics of the cloud model—expectation, entropy, and hyperentropy—while a Gaussian potential function is adopted to characterize how interaction strength varies with spatial distance. A MATLAB-based simulation platform is developed to reproduce the emergent transition of fireflies from disordered flashing to synchronous behavior across different spatial domains. Our results demonstrate that group synchronization efficiency is strongly governed by the initial spatial configuration of individuals. Introducing driving nodes (special agents) can accelerate synchronization, but increasing their quantity yields diminishing marginal returns; the optimal strategy is a single special agent placed at the domain center. Collective emergence depends more strongly on the topological structure of inter-individual interactions than on the number of driving nodes. These findings confirm that interaction topology dominates synchronization performance over driving-node quantity, providing a theoretical basis for guiding unmanned swarm coordination with minimal control nodes.

To investigate the early-stage flame propagation and pressure response of premixed H₂-O₂ combustion under ultra-high-pressure constant-volume conditions, a transient CFD model was developed for a large-volume confined chamber. The numerical framework combines a density-based solver, the Peng–Robinson real equation of state, large eddy simulation, and a reduced H₂-O₂ chemical kinetic mechanism. Simulations were conducted at initial pressures of 30 and 40 MPa, H₂/O₂ molar ratios of 8:1 and 12:1, and three-, four-, and five-point ignition configurations. The results show that increasing the initial pressure from 30 MPa to 40 MPa advances the pressure rise onset from approximately 1.65 ms to 1.28 ms and increases the maximum pressure rise rate from 18.6 MPa·ms⁻¹ to 27.4 MPa·ms⁻¹ under the H₂/O₂ = 8:1 and three-point ignition condition. Under the investigated fuel-rich conditions, increasing the H₂/O₂ molar ratio from 8:1 to 12:1 delays the pressure rise onset from approximately 1.28 ms to 1.46 ms and reduces the maximum pressure rise rate from 27.4 MPa·ms⁻¹ to 21.1 MPa·ms⁻¹. For the 30 MPa and H₂/O₂ = 8:1 cases, the four-point ignition case produces the largest pressure rise rate of approximately 23.5 MPa·ms⁻¹, whereas the five-point ignition case shows a lower pressure fluctuation amplitude of approximately 3.6 MPa. The present conclusions are based on CFD quantitative engineering predictions and should be further validated using quantitative experimental measurements.

In response to the current limitation where conventional constant volume combustion apparatuses are generally confined to pressure ratings of 5–20 MPa, insufficient for the demands of ultra-high-pressure combustion fundamental research, this study designs and verifies a high-pressure-resistant constant volume combustion apparatus with a rated working pressure of 250 MPa. The strength design and safety factor calculation for the combustion chamber main body were conducted based on the Lame thick-walled cylinder elastic theory. A finite element numerical simulation method was systematically employed to perform static analysis, transient impact response analysis, and high-cycle fatigue-life assessment of the key components of the apparatus. The results indicate that under a 250 MPa design internal pressure load, the maximum circumferential stress at the inner wall of the combustion chamber main body is 328.0 MPa, with a safety factor greater than 1.5, complying with relevant safety codes for high-pressure vessels. Under transient loading simulating combustion impact, the maximum equivalent stress of all structural components is below the material yield strength, with a maximum elastic deformation of less than 0.06 mm, demonstrating excellent structural stiffness and impact resistance. Fatigue assessment with a design-life target of 1.0 × 10⁶ pressure cycles shows that the cumulative damage values for all components are significantly less than 1.0, meeting the reliability requirements for long-term cyclic service. This apparatus integrates functional modules such as high-pressure precision gas mixing, high-energy reliable ignition, high-speed transient parameter acquisition, and safe product collection, providing a stable, controllable, and safe experimental platform for in-depth research on the combustion mechanisms of gaseous fuels under ultra-high-pressure conditions.