Platinum (Pt) resistance temperature detectors (RTDs) are extensively employed as thin film temperature sensors. However, agglomeration of Pt thin films occurs above 800°C due to grain boundary grooving on the free surface, ultimately limiting its application at high temperatures. In this work, a Pt RTD was prepared by depositing multilayer Al ₂ O ₃ protective layer on Pt thin films using electrodynamic jet printing (EJP) technology. The surface morphology and energy dispersive spectroscopy spectrum of Pt thin films indicated that the voids on the surface are reduced, the grains growth are inhibited, the movement and grooving of grain boundaries are limited. The test results indicate that the Pt RTD has not failed after 6 cycles of repeated warming and cooling from 800°C to 1300°C. After repeated cycles, the initial resistance of the Pt RTD with a rate of change of less than 0.5%. In addition, the maximum relative deviation of the resistance in a single cycle is less than 1.6%. The Pt RTD with an 18-layer Al ₂ O ₃ protective layers has undergone 12 cycles without failure, indicating a cycle life exceeding 10 h. Pt RTDs are stable over the range of 25°C to 1400°C with correlation coefficients R ² greater than 0.999, showing good linear correlation. It can withstand temperatures up to 1440°C when printed with 18 protective layers. Compared to a Pt RTD without protective layers, the operating temperature is increased by 40%. This advancement provides a viable solution for the high-temperature monitoring of hot end components in aerospace applications.

Typical wind tunnel testing involves a series of configuration changes (to the angles of control surfaces) to simulate the lift and resistance characteristics of control surfaces in different flight conditions. It is very time-consuming and labor-intensive to manually change the angles of control surfaces, especially in the large continuous reflux wind tunnel. Thus, there is a demand for a morphing system design within the wind tunnel model that can deflect the control surfaces remotely and automatically. The basic design flow and characteristics of different actuator techniques for the morphing systems were summarized in this paper, including electromechanical actuator, pneumatic actuator, shape memory material actuator and piezoelectric actuator. In the case study, the accuracy of the control surface angle and aerodynamic performance of the ultrasonic-driven automatic control surface system reached the level of traditional fixed control surface systems, while its efficiency was much higher than that of the traditional fixed control surface systems.

The strain measurement accuracy of aerospace hot end components is severely affected by the change of environmental temperature. How to reduce the apparent strain derived from temperature variation within a wide range still is of a great challenge hitherto. In this work, a self-compensated thin film strain gauge (SC-TFSG) with sensing resistor and suspended compensation resistor is developed. These two resistors are orthogonal to each other and form a half bridge measurement structure, which is used to reduce the apparent strain introduced by temperature changes. Results show that the temperature coefficient of resistance (TCR) of the SC-TFSG is only -136 ppm/°C within a wide temperature range from room temperature to 1200 °C. The thermal output is 89.52% lower than the strain gauges without compensation resistor. Furthermore, the results of the standard strain cyclic loading test at 600 °C, 800 °C, 1000 °C and 1200 °C indicate that the maximum error between the SC-TFSG measured values and the standard loading strain can be controlled within 6%. The work provides an effective method for strain measurement and accuracy compensation of hot end components in a wide temperature range.

To address the issues of low processing efficiency, poor forming accuracy, and internal damage in glass material processing, this study proposes the use of flame jet forming. However, the mechanism of flame jet processing requires further elucidation. This research investigates the relationship between the indentation morphology on the glass surface and the inlet velocity of the flame jet. A theoretical model was established through mathematical analysis to reflect this relationship. The model’s accuracy was validated using numerical simulation methods. By comparing experimental data with theoretical model results, surface tension was incorporated, and the model was iteratively optimized using MATLAB R2024a. The final optimized model demonstrated an absolute error range of 0.009 to 0.069 mm. This study confirms the feasibility of flame jet processing and enriches the understanding of its mechanism, providing a novel, efficient, and precise method for processing glass materials.