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This SAE Aerospace Recommended Practice (ARP) provides a framework for establishing methods and stakeholder responsibilities to ensure that seats with integrated electronic components (e.g., actuation system, reading light, inflatable restraint, in-flight entertainment equipment, etc.) meet the seat technical standard order (TSO) minimum performance standards (MPS). These agreements will allow seat suppliers to build and ship TSO-approved seats with integrated electronic components. The document presents the roles and accountabilities of the electronics manufacturer (EM), the seat supplier, and the TC/ATC/STC applicant/holder in the context of AC 21-49, Section 7.b (“Type Certification Using TSO-Approved Seat with Electronic Components Defined in TSO Design”). This document applies to all FAA seat TSOs C39( ), C127( ), etc. The document defines the roles and responsibilities of each party involved in the procurement of electronics, their integration on a TSO-approved seat, and the seat’s installation on an aircraft. Requirements for design and quality control and the methods for communicating design and change data between EMs and seat suppliers are defined such that standardization is possible across the industry to ensure continued airworthiness of TSO-approved seats with integrated electronic components. This document primarily focuses on correspondence between the seat supplier and the EM. Appendix A: Presents key characteristics of electronic components and guidance on how changes are classified per the requirements of Table 1 of AC 21-49. Appendix B: Provides an outline of a typical data approval process and the change management process between EMs and seat suppliers. Appendix C: While the responsibility rests solely with the seat supplier to ensure all TSO attributes identified in Table 1 of AC 21-49 are acceptable, Appendix C has been included to outline the process for delegating EMs authorization to assess the impact of changes on their equipment with respect to seat TSO attributes. This authorization will allow the classification of the change and the appropriate administration of the change by the EM via seat supplier delegation. Appendix D: Given the mix of business arrangements that can exist in the seat, in-flight, and aircraft procurement life cycle (buyer-furnished equipment, supplier-furnished equipment, customer-furnished equipment), there is discussion on the potential need for separate agreements between the EMs and seat suppliers to ensure binding flow down of design and quality control requirements. As such, a working together agreement (WTA) template is provided as Appendix D.
Aircraft Seat Committee
E-25 General Standards for Aerospace and Propulsion Systems
This document (Technical Specification) gives information about qualification rules and the relation between the different specification parts involved, such as the Technical Specification (TS), Material Specification (MS), and Purchasing Specification (PS). The link to the material qualification and qualified products is presented.
AMS CACRC Commercial Aircraft Composite Repair Committee
ACBG Rolling Element Bearing Committee
This specification covers a corrosion-resistant steel in the form of wire 0.007 to 0.625 inch (0.18 to 15.88 mm), inclusive, in nominal diameter, cold drawn to Condition C, and capable of being precipitation heat treated to Condition CH900.
AMS F Corrosion and Heat Resistant Alloys Committee
NASA Tech Briefs: August 202626AERP088/8/2026
How Electrification is Reshaping Motion Control in Flight Systems Charting the Flight Path of the Aerospace & Defense Industry with Digitalization Introducing the Modern Virtual Test Environment: Reducing Friction in RDT&E How Modular Tooling Accelerates Thermoplastic Composite Prototyping for Advanced Air Mobility and Defense Aerospace-Grade Thin Film Substrates: The Foundation of Electronics Reliability This New Quantum Sensor Measures 3D Direction of RF Electromagnetic Fields SAE International Publishes New Technical Information Report to Advance Battery Interoperability for Small Uncrewed Aerial Systems SAE JA1016 establishes common specifications for lithium-ion pouch cells for small uncrewed systems in both ground and aerial applications. Engineering Actuators for Extreme Environments A holistic approach to protective design can greatly reduce or eliminate the harmful effects of harsh environmental conditions on electric actuators. Texas A&M Researchers Work to Find Jet Fuel Alternatives Through a NATO sponsorship, a team of aerospace engineering researchers will start testing hydrogen-based alternatives that produce vapor and steam instead of carbon dioxide when they burn. Prototype Reflectarray Antenna Demonstrates Low-SWaP Anti-Jam Tactical SATCOM This prototype array uses a small, lightweight, low-power, and low-cost aperture. How Airbus is Developing Artificial Intelligence for Future Cockpits Computer vision, automated landing and embedded AI for tomorrow's cockpits.
As a high-precision transmission core component, the RV reducer’s performance depends on the time-varying stiffness of its core components. Building a time-varying stiffness model is essential for studying its dynamic characteristics. This paper addresses the lack of key factors in existing dynamic studies by creating a multi-factor coupled dynamic model. It analyzes the time-varying stiffness of the crankshaft bearing, involute gear, and cycloid gear-pin gear. The study also focuses on building a dynamic analysis model for the crankshaft bearing. By measuring changes in oil film thickness and initial assembly clearance caused by temperature rise, it explains how combined clearance affects bearing performance. To verify the model, a domestic RV reducer is modeled and assembled in SolidWorks. The simplified model is imported into ADAMS for simulation. Under set load and speed conditions, dynamic parameters like angular velocity and acceleration of core components are obtained. This provides a more scientific analysis method and data support for understanding the dynamic characteristics and improving the transmission performance of RV reducers.
Xuan, LiangTeng, ShaoweiHuang, RuizheWan, ZefuShao, MengqiYu, ZhishenWang, Ziyue
With the complexity of chemical warfare threats and the diversification of battlefield environments, traditional toxic agent detection methods are facing bottlenecks such as response delays, coverage blind spots, and personnel safety risks. This research focuses on the application of unmanned aerial vehicle (UAV) carried toxic agent sensor systems, aiming to analyze the methods of mounting and deploying the sensors on the UAVs, and to construct a rapid response, high-precision, and highly resistant toxic agent monitoring system. Its significance lies in two aspects: 1. Tactical value: It breaks through the time and space limitations of manual reconnaissance, realizes real-time dynamic perception and early warning of toxic agent contamination, and provides key decision-making support for battlefield command; 2. Application expansion: The research results can be transferred to counter-terrorism, nuclear, biological, and chemical emergency response fields, providing theoretical support and engineering paradigms for the development of unmanned and intelligent chemical defense equipment.
Liang, TingWen, HaoQi, YelinYan, RuiMa, TengboYang, Wen
Steel structures subjected to complex loading conditions undergo various types of damage, including fatigue, crack propagation, plastic deformation, and corrosion. As time and loads accumulate, these damages may lead to structural failure. The investigation of the damage mechanisms and constitutive models for special equipment steel structures under complex loading has been a significant challenge in engineering. This study develops a constitutive model for steel structure damage under static and dynamic loads, as well as vibration disturbances, through a normalization approach. The proposed model is validated via simulation to assess its feasibility. The findings offer a theoretical foundation for the design, life prediction, and health monitoring of steel structures in special equipment, aiming to enhance their safety and reliability. This research provides critical insights into damage analysis, failure prediction, and the optimization of repair strategies for steel structures, with significant practical implications in engineering applications.
Wang, JunYu, ZhenHuang, Yong-qiangChen, Wei-bi
In this work, molecular dynamics simulations are applied to systematically examine the influence of varying temperatures (300 K, 500 K, and 700 K) on the Elevated-temperature compression behavior and micromechanical characteristics of polycrystalline Al-Mg-Si aluminum alloy. A nanopolycrystalline model was established to analyze the stress–strain response, dislocation evolution, and crystal structure changes occurring during the deformation process. The simulation results show that the yield strength and elastic modulus both decline as temperature increases, indicating a pronounced thermal softening effect. During the early stage of plastic deformation, dislocations mainly have their nucleation sites at grain boundaries and then propagate into the grain interiors, where they form interconnected networks along with stacking faults and twin structures. This work reveals the thermal deformation mechanisms of Al-Mg-Si aluminum alloy at the atomic scale and provides theoretical guidance for the optimization of its hot-working processes.
Sun, RuifengLiu, ShoukuiWang, RuiSun, XuemeiDing, ShuliMa, Xiaofei
This study proposes an intelligent automotive roof frame design method based on the middle layer and component technology on CATIA. It aims to solve core roof modeling issues: determining geometric input quantity but uncertain attributes (tangent vectors, normal vectors, number of curve segments, number of surface patches, and boundaries), high manual interaction dependence, and poor knowledge reuse, to realize efficient design knowledge reuse. Methodologically, it builds a feature-driven parametric template, develops a knowledge rule-embedded componentized UDF library (reducing repeated modeling and geometric reconstruction needs), and integrates knowledge engineering for geometric input verification and operation direction control, eliminating curve/surface attribute uncertainty impacts. Verification shows the template stably generates roof crossbeams under simple/complex inputs, improving model robustness and reuse rate, reducing design workload, shortening verification cycles, and providing an extensible solution for white body design.
Jin, ChunningFu, XinyuHou, Wenbin
Auxiliary fuel tank systems for civil aircraft are typically employed in extended-range aircraft. As a critical structure for fuel storage, the structural safety of auxiliary fuel tanks directly impacts aircraft safety. Such tanks are generally constructed from honeycomb sandwich composite panels. Owing to their outstanding advantages, including high specific strength, light weight, and corrosion resistance, honeycomb sandwich composite panels have become the material of choice for civil aircraft fuel tanks. However, to meet the safety requirements for ventilation and leakage drainage in the sandwich structure of fuel tanks, dedicated flow channels must be created by slotting inside the honeycomb composite panels to ensure timely discharge of fuel vapor and accumulated fluid from the tank sandwich. Conventional flow channels are symmetrically arranged on the end faces of the honeycomb core, making it difficult for ventilation airflow to penetrate the center of honeycomb cells. This results in ventilation and drainage blind spots within the cells, which tend to cause accumulation of fuel vapor and residual fluid over prolonged service. Consequently, the aging of the core layer is accelerated, compromising the structural integrity of the composite panel and the service life of the fuel tank. This paper proposes an asymmetric ventilation flow channel design. By optimizing the slotting position, size, and distribution pattern of the flow channels, the limitations of the traditional symmetric layout are overcome. To accurately investigate the effect of this design on the internal ventilation performance of honeycomb composite panels, a three-dimensional flow field model of the honeycomb sandwich composite panel is established using computational fluid dynamics (CFD). The ventilation airflow distribution, velocity, and flow rate characteristics under different flow channel designs are simulated and compared with those of the conventional symmetric flow channel design. The results demonstrate that the asymmetric ventilation flow channel design improves the ventilation uniformity inside the honeycomb cells and completely eliminates the ventilation and drainage blind spots at the cell center inherent in the traditional design. Meanwhile, the design significantly enhances the ventilation gas velocity and flow rate at the center of honeycomb cells, accelerating the discharge of fuel vapor and drainage of accumulated fluid. The overall ventilation efficiency is considerably higher than that of the traditional symmetric design. This study provides a theoretical basis and technical support for the safety design of honeycomb composite panels used in auxiliary fuel tanks of civil aircraft.
Yao, LijunChen, Jun
Impact testing utilizing instrumented hammers and accelerometers is a widely adopted technique in dynamic testing. The mass loading effect of the accelerometer alters the dynamic response of the test structure, leading to deviations between the measured frequency response functions (FRFs) and their true values. Furthermore, the effects on the FRFs are contingent upon the positioning of the accelerometer, thereby causing the measured FRFs between two points to fail to meet the principle of reciprocity. This paper investigates the compensation method for the mass of a single accelerometer in impact testing. Compensation formulas for both origin–FRF and cross–FRF are derived using the frequency domain substructure decoupling method. Numerical simulations on a cantilever beam and experimental tests with milling tools validate the proposed methodology. The compensation formulas for FRFs presented in this paper are expected to enhance the measurement accuracy of FRFs in modal testing of small structures, particularly relevant for lightweight components in aerospace, aircraft, and transportation systems, where precise dynamic characterization is critical.
Tang, ZhenrongYao, Zhenqiang
In response to the challenges of training and rehabilitation for patients with leg dysfunction, this research focuses on two core requirements: “bionic adaptation” and “safety assistance”. It introduces a novel exoskeleton leg rehabilitation robot designed to support diverse rehabilitation exercises for individuals with leg disabilities during therapy. The robot system consists of a lumbar support structure, thigh mechanical components, calf mechanical components, leg fixation straps, and foot mechanical structures, and achieves multi degree of freedom motion simulation through three main joints: hip joint, knee joint, and ankle joint. Each mechanical leg has three independent degrees of freedom, which can effectively simulate the natural movements of the human lower limb, such as flexion, extension, abduction, etc., during the gait cycle, thus meeting the functional needs of patients for different movement modes during rehabilitation training. On the basis of structural design, this study further utilizes multi-body dynamics simulation software ADAMS to conduct kinematic and dynamic analysis of the exoskeleton robot. By simulating the joint torque of the exoskeleton legs under ideal working conditions, the rationality and smoothness of the mechanism design are verified. The simulation results not only reflect the performance of the robot in typical rehabilitation actions, but also provide a theoretical basis and data support for the selection and parameter matching of key execution components (such as servo motors, reducers, etc.), laying an important foundation for the physical development and control strategy optimization of the robot system.
Mu, XiaoqiMa, ChaoLi, WeijiePu, ShuaiLiu, JiaqiWang, RuiyinZhang, Xiaodong
With the strategic expansion of low-altitude economies, there is a growing demand for unmanned aerial vehicles (UAVs) with enhanced structural reliability and performance. This study investigates the integrated design and precision manufacturing of a heavy-lift quadrotor UAV, focusing on developing a system capable of sustaining substantial payloads. The UAV features an innovative locking mechanism at the base of its arms, which facilitates easy disassembly—this design simplifies maintenance while improving operational flexibility. Structural integrity was evaluated using the Static Structural module in Ansys Workbench under three operational conditions: no-load, full-load, and extreme-load. Results demonstrate that the airframe meets strength requirements under all conditions, though localized nonlinear deformations were observed in the arms under extreme loads. In response to these findings, the Response Surface Optimization methodology was systematically applied to refine the UAV arm’s design parameters, with the dual goals of minimizing structural mass and reducing displacement. Experimental results show that under the most demanding operating condition, the maximum displacement was reduced by 43.6% compared to the pre-optimization state, while the arm’s weight was reduced by 20.2%. These findings provide critical insights for advancing UAV design, particularly in agricultural and logistics applications that require high payload capacity and robustness.
Huang, KanghuiLi, GuiyingYu, ZhigangYang, JingruWang, YongZhang, Chao