As a type of transmission actuator commonly used in mechanical structures, high-speed rotary mechanisms are widely used in the machinery, energy, civil engineering, and military industries. The main working part of the mechanism is the end face, and the vibration characteristics of the end face directly affect the accuracy and completeness of the whole mechanism. In terms of performance, the end face vibration characteristics reflect the degree of change in the machine’s end face displacement. The traditional end face displacement test method uses a single contact sensor for measurement, but the degree of error in the system is large. It is also difficult to adapt this method to the current high-precision working conditions under the requirements for accurate vibration prediction and control technology. Therefore, this work proposes a test method based on multi-sensor acquisition and data fusion, using different sensors to form a sensor test network. It seeks to address the limitations of the conventional test method that relies on a single-frequency domain, using high-frequency domain impact signals, medium-frequency domain vibration signals, and low-frequency domain rotational speed signals for multi-sensor data fusion to achieve a complete high-speed rotating mechanism with a particular focus on full-area coverage. In order to better obtain the test data, the sensor layout network is optimized through the optimization design method, and the optimal sensor installation scheme is proposed. Finally, the data fusion algorithm and sensor layout scheme are experimentally verified with a typical high-speed rotating mechanism.

Multi-missile cooperative guidance is an important way to improve the strike effect of missiles, and the fast convergence of guidance commands can effectively ensure the stability of multi-missile systems. The cooperative guidance method based on the fixed-time consistency theory has been proved to be suitable for multi-missile coordinated attack, but the non-singularity problem of the controller itself will have a large impact on the striking effect of the multi-missile system, so this paper designs a fixed-time fast non-singular distributed cooperative guidance law to solve the above problem. First, a fixed-time cooperative guidance law with fast convergence is designed in the line-of-sight (LOS) direction and an auxiliary function is designed to solve the singularity problem; after that, a cooperative guidance law in the LOS normal direction is designed to ensure that each missile attacks the target simultaneously at the desired attack angle. Finally, the effectiveness, superiority and robustness of the designed guidance law are demonstrated by numerical simulations.

Cooperative interception by multiple aircraft requires coordination of physical event times and terminal line-of-sight (LOS) directions under strongly coupled three-dimensional motion. A limitation of predictor-based designs is that agreement of estimated terminal times is often interpreted as simultaneous interception without an explicit predictor-to-event error bound. This paper develops a distributed mixed-power fixed-time guidance framework that comprises point-mass kinematics and ideal inner-loop tracking. An exact spherical-coordinate model retains the azimuth–elevation coupling terms. The radial predicted terminal time (RPTT) is used as the distributed coordination state, and a local bound links RPTT to independently detected interception events. A mixed-power consensus protocol is analyzed for a fixed graph and a finite set of connected undirected switching graphs using a common Lyapunov function. An inertial-frame fixed-time observer estimates the unmeasured target acceleration, while a C²-regularized nonsingular fast terminal sliding-mode law regulates the terminal LOS azimuth and elevation. The analysis distinguishes nominal exact fixed-time consensus, perturbed practical fixed-time reachability, and exponential convergence inside the regularization layer. Four-aircraft simulations produced a 0.435 ms independent event-time spread and terminal LOS errors below 0.046°. Relative to a peak-matched single-power protocol, the RPTT agreement time was reduced by 34.3%, with a 0.58% increase in total control effort. The results support the method’s use as a guidance-layer coordination design within the stated sensing, communication, and inner-loop assumptions.

This letter presents a hardware-efficient antenna polarization measurement technique based on time modulation (TM). By multiplexing orthogonal field components into a single RF channel, the proposed method leverages the power and phase characteristics of spectral harmonics to resolve the incident polarization state. To address the critical challenge of synchronization latency, an asymmetric quarter-period modulation sequence is introduced to generate a second-order harmonic as an intrinsic phase reference. This strategy enables the autonomous compensation of switching delays without external synchronization hardware, ensuring precise reconstruction in asynchronous sampling scenarios. Experimental validation across 2–7 GHz using a dual-polarized Vivaldi antenna (DPVA) yields a root-mean-square error (RMSE) of 1.15°–1.92°, demonstrating the system's robustness for broadband antenna characterization.