Browse Topic: Aircraft

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Bullfrog: AI Powered Counter Unmanned Aerial System2026-01-75199/22/2026
The proliferation of small unmanned aircraft systems (sUAS) presents an asymmetric threat to ground maneuver forces operating in contested and gray-zone environments. The Bullfrog Autonomous Weapon Station (AWS) addresses this operational gap through a passive, AI-powered counter-UAS system employing computer vision and machine learning for autonomous detection, tracking, classification, and engagement. Field testing at Technology Readiness Experimentation (T-REX) 26-1 demonstrated 100% probability of defeat against Group 1 UAS targets with a mean engagement time of 6 seconds and 10 rounds per kill at ranges exceeding 160 meters. Operating in both autonomous and human-in-the-loop modes, Bullfrog achieved 99.45% operational availability while leveraging service-common M240B weapons and Modular Open Systems Architecture for rapid integration with Joint All-Domain Command and Control (JADC2) networks. At $300,000 per unit with $10 cost-per-engagement, Bullfrog demonstrates operational relevance, speed-to-field, and alignment with Army and Marine Corps autonomy priorities.
Cunningham, Jason, Clark, Alex
Beyond Detection: Zero-Shot UAS Payload Identification, Passive Ranging, and Pose Estimation2026-01-75079/22/2026
Unmanned Aerial Systems (UAS) pose a growing threat on the modern battlefield, demanding rapid detection and characterization capabilities for the warfighter. Existing single-model solutions are inadequate for Counter-UAS (C-UAS), as they struggle across varying ranges and cannot provide detailed contextual information beyond bounding boxes. We present ZEUS (Zero-shot Explainable Universal Segmentation), a multi-model detection and recognition system that integrates several machine learning approaches. ZEUS employs a high-performance UAS detector trained on synthetic, internally collected, and open-source datasets, with real-time capability demonstrated on edge hardware across both electro-optical and infrared modalities. For classification, ZEUS uses a zero-shot approach: detected UAS are segmented and compared against a library of 3D reference models rendered at various poses, enabling identification of new UAS types without retraining. This methodology additionally provides UAS pose and range estimates critical for threat assessment and engagement decisions.
Matousek, Gregory, Varberg, Nathan, Torrione, Pete, Brandon, Namdi, Inkawhich, Matt, Camilo, Joe
Development of a UAV Platform for Remote Inspection and Visualization2026-01-75119/22/2026
This paper details the development of an intelligence and inspection platform consisting of an attritable sub-250g UAV, a ground control station, and a visualization interface for users. The UAV architecture combines onboard obstacle detection and avoidance along with simultaneous localization and mapping to have full autonomous navigation inside of complicated GPS-denied environments. The ROS 2-to-Unreal Engine data pipeline allows for sensor fusion, data cleansing, and initial analysis as well as creation of a high-fidelity real-time 3D digital twin. The visualization interface allows users to easily identify critical features and turn data into intelligence to support decision making by soldiers and first responders.
Lee, Yeen K., Bainard, Sean, Shaughnessy, Michael, Bolger, Matt, Koepp, R. Tucker, Salehzadeh, Roya, Mallory, Stephen, Mynderse, James A., Guillen, Pedro, Hernandez, Margarita
Shrike Nano: On-Body AI-Enabled Digital Fires from Unmanned Aircraft Feeds2026-01-75049/22/2026
Shrike Nano provides forward observers and small unmanned aerial system (sUAS) operators with an integrated solution to enhance target prosecution using sUAS video feeds and indirect fire systems. Operable within the Android Tactical Assault Kit (ATAK) ecosystem, Shrike Nano functions as a software plugin that interacts seamlessly with existing tools, including UAS Tool, Robot Picker, and Network Monitor. By utilizing either aided threat recognition (AiTR) or manual targeting workflows, along with passive single-camera geolocation, operators can nominate targets and correct shot placement via digital messaging to enterprise fires terminals such as the Advanced Field Artillery Tactical Data System (AFATDS). The system offers key advantages, including operator standoff capabilities, accurate geolocation, and streamlined fires messaging workflows, all while leveraging low-observable platforms. Shrike Nano seeks to bridge gaps in traditional targeting processes by providing a cohesive and efficient sensor-to-shooter workflow that reduces cognitive load and enables faster, more reliable fire missions at the tactical edge.
Baharanyi, Ali I., Tozzi, Gregory M.
Flight Deck Layout and FacilitiesARP4101A (Current)9/22/2026
This document recommends criteria for the layout and for the design, installation, and operation of flight deck facilities for transport aircraft.
S-7 Flight Deck Handling Qualities Stds for Trans Aircraft
Carbon Fiber Fabric Repair Prepreg, 120 °C (250 °F) Vacuum Curing, Part 6 - Material Specification: Carbon Fiber Fabric Reinforced Epoxy Prepreg for Repair, Plain Weave Fabric, 193 g/m2, Adhesive Film for Repair and Non-Structural Glass Fiber Fabric Reinforced Epoxy Prepreg, 105 g/m2AMS3970/6A (Current)9/22/2026
AMS3970/6 Material Specification (MS) defines the requirements of carbon fiber plain weave fabric, 193 g/m2, reinforced epoxy structural prepreg for repair, curing under vacuum at 120 °C (250 °F), and a companion non-structural glass fiber fabric reinforced epoxy prepreg, 105 g/m2, used in repair of carbon fiber reinforced epoxy structures and qualified according to AMS3970/1 and AMS3970/2 for aerospace applications. The prepreg system may include an epoxy film adhesive to be applied in a co-curing process with the prepreg for joint and sandwich bonding. The need for a film adhesive shall be established during screening tests. If included, the requirements to be met by the adhesive are also defined in this document.
AMS CACRC Commercial Aircraft Composite Repair Committee
Passive Thermal Management Through Vapor Chamber Integration of a PMSM E-Motor installed on UAV for Urban Mobility Applications2026-24-00109/21/2026
Thermal management is a critical design challenge for Permanent Magnet Synchronous Motors (PMSMs) employed in Unmanned Aerial Vehicle (UAV) propulsion systems, where high power density and compact integration lead to significant heat generation. Excessive temperatures can compromise efficiency, reliability, and component lifetime, making the development of effective and lightweight cooling solutions essential. This study investigates the integration of a vapor chamber as a passive thermal management solution for a commercially available PMSM intended for UAV applications, whose thermal performance is evaluated under external airflow conditions representative of low-speed flight and hovering. Unlike conventional active cooling systems, the proposed approach does not require moving parts, external power input, or additional control devices. Heat transfer is driven by phase-change mechanisms within a sealed enclosure: as the local thermal load increases, the working fluid evaporates in the hotter regions and condenses in the cooler ones, redistributing heat autonomously without external intervention — a self-regulating behavior particularly suited to the constraints of UAV propulsion systems. A simplified three-dimensional model of the motor housing was developed, and steady-state conjugate heat transfer simulations were performed in ANSYS Fluent to evaluate the thermal performance of the system. Three configurations were analyzed: a baseline motor without vapor chamber, a configuration with an integrated vapor chamber, and a configuration combining the vapor chamber with an external copper fin array. The vapor chamber was modeled using an equivalent porous-medium approach for the wick structure, coupled with a multiphase formulation to capture liquid–vapor interactions within the core. The results demonstrate that vapor chamber integration significantly reduces peak pole temperature, with reductions ranging from 38K to 159K (approximately 10% to 31% relative to the baseline configuration) depending on operating conditions. At higher thermal loads, the device transitions from a liquid-filled regime to an active two-phase operation, enhancing heat transfer through evaporation and condensation. The addition of an external copper fin array further improves thermal performance, achieving a maximum pole temperature reduction of 203K (approximately 33% relative to the baseline) under low-airflow, high-load conditions. A key finding of this study is the strong coupling between the external fin array and the internal phase-change behavior of the vapor chamber: by lowering the condensation-side temperature, the fins promote a more active two-phase regime, enhancing overall heat transfer performance beyond what either component achieves independently. These results highlight the potential of vapor chamber technology, particularly when combined with extended surfaces optimized for the dominant flight regime, as a lightweight, passive, and self-regulating cooling strategy for compact UAV electric propulsion systems.
Benedetti, Silvia, Lombardi, Simone, Federici, Leonardo, Chiappini, Daniele
A Computational Study of High Efficiency Wankel Rotary Engines using a Passive Pre-Chamber2026-24-00019/21/2026
Wankel rotary engines are renowned as compact machines with high power-to-weight ratios, which make them suitable for use as range extenders for battery electric vehicles or as propulsion systems for unmanned aerial vehicles. However, their overall efficiency and emissions still need significant improvement to meet to the stringent regulations comparable with classical reciprocating 4-stroke engines. With the aim of improving these shortcomings, this work focuses on the application of a passive pre-chamber in order to enhance the combustion phase and the overall efficiency and emissions of such engines. Computational fluid dynamics (CFD) simulations were conducted for the commercial AIE 225CS rotary engine, configured with port fuel injection and fully-premixed gasoline combustion. The engine was extensively tested in a previous project while different CFD models were validated against experimental data in previous studies by the same authors. In particular, the present work examines the engine performance with two pre-chamber configurations with different volumes. The volume and nozzle specifications were determined to have geometrical characteristics similar to those of the theory of Gussak, with volumes directly comparable with that of the two spark park plug recesses of the original engine, leading to significantly large nozzle diameters in the pre-chambers. In addition, the effect of spark advance was investigated to capture the development of the flame and jets and the resulting effects on the indicated pressure cycle. Consistent with previous findings, heat losses were found to be a critical aspect for the different configurations of engine. Nevertheless, the application of pre-chamber shows some potential to improve efficiency by accelerating combustion phase, leading to a relative increase of 7.4% on the indicated efficiency. This suggests an important new path in the development of Wankel engines as a viable solution to efficient utilisation of decarbonised and innovative future fuels in compact systems.
Vorraro, Giovanni, Im, Hong G., Turner, James
Preconditioned Air (PCA) Unit Air Quality, Humidity Management, and Cabin ConnectionARP6986 (Current)9/11/2026
The provisions of this SAE Aerospace Recommended Practice (ARP) cover minimum performance requirements and design parameters for preconditioned air (PCA) devices supplying air to the aircraft cabin. It identifies the need for interim and future performance improvement for ground equipment delivery systems, to meet industry requirements for reducing airborne compounds or particulates (“source types”) in the aircraft cabin and flight deck. This ARP will guide SAE, IATA, airline operators, and airframe and PCA manufacturers to meet new requirements. This ARP defines: Minimum performance and maintenance requirements for filtration, hose assemblies, operations, and maintenance. Level of humidity supplied by the ground equipment to the aircraft cabin. Minimum performance and maintenance requirements for digital communication of cabin parameters between the cabin and the PCA. Installation of the sensor unit within the aircraft cabin. The data collected by these sensors is not intended to assess impacts on aircraft occupant health and shall not be used to make a finding of airworthiness.
AGE-3 Aircraft Ground Support Equipment Committee
Oxygen Considerations for High Elevation Airport Operations (HEAO)AIR6829A (Current)9/11/2026
This document covers information concerning the use of oxygen when flying into and out of high elevation airports for both pressurized and non-pressurized aircraft. Oxygen requirements for pressurized aircraft operating at high altitudes have for decades emphasized the potential failures that could lead to a loss of cabin pressurization coupled with the potential severe hypoxic hazard that decompressions represent. This document is intended to address the case where the relationship between cabin and ambient pressures are complicated by operations at high terrestrial altitudes. Operators who fly into these high-altitude airports should address the issues related to this environment because it carries the potential for insidious hypoxia and other conditions which can affect safety. It provides information to consider in developing operational procedures to address hypoxia concerns consistent with regulatory mandates. In some sections, procedures are discussed that may mitigate the deleterious effects of hypoxia in a non-flight regime yet still have the potential to represent risk factors associated with flight operations. All the information is provided as a framework for potential oxygen management and other procedures to facilitate responsible practices and facilitate compliance with existing regulatory requirements. This document cannot address every type of aircraft pressurization system, oxygen system, or operational condition the flight may encounter. Any threat or hazard not discussed in AIR6829 should be brought to the attention of the OEM, the regulatory authority, and the flight operations department for proper guidance.
A-10 Aircraft Oxygen Equipment Committee
Research on the Design of Reconfigurable Assembly Fixture Frame for Aircraft Based on Rapid Manufacturing2026-99-14099/11/2026
With the increasing demand for efficiency, flexibility, and cost-effectiveness in the aviation manufacturing industry, the prototyping cycles of aircraft development have significantly shortened. Traditional assembly fixtures, due to their high degree of customization and poor reconfigurability, struggle to meet the requirements for rapid prototyping of multiple aircraft models. To address this issue, research has been conducted on reconfigurable framework structures for aircraft assembly fixtures, and finite element analyses have been performed on different types of reconfigurable fixture frameworks. The study indicates that although the stiffness of reconfigurable frameworks is slightly lower than that of traditional welded framework structures, it still meets the requirements for rapid prototyping of development aircraft. By adopting standardized, low-cost reconfigurable assembly fixtures, the design and manufacturing cycle of tooling can be significantly shortened, and the reusability of tooling components can be enhanced, thus facilitating rapid and cost-effective development of prototype aircraft.
Wang, Xingzhong, Wang, Hongtao, Liu, Bing, Bi, Xinying, Liu, Zhanzhan
Integration of Configuration Management into the RFLP Process in the Development of Civil Aircraft2026-99-14179/11/2026
In the forward development process of civil aircraft, traditional configuration management, which primarily focuses on the physical implementation end, often leads to inconsistencies between functions, requirements, design configurations, and physical realizations. This study optimized the principles of configuration item identification by refining the logic, timing, and sequence for identifying different types of configuration items. It proposed a product structure centered on the Logical Identification Number (LIN), which explicitly represents the mapping relationships from functional to physical elements. Additionally, the research established the logic for change propagation and validity calculation. Using an air-conditioning refrigeration system as a case study, the model was validated, demonstrating its advantages for improving the efficiency of change-impact analysis, enhancing compliance verification, and ensuring scenario reproducibility.
Xie, Xiang, Meng, Xu, Zhang, Xinyuan, Wu, Binbin
Design and Validation of Lightweight Composite Load-Bearing Structures for Aircraft Using Topology Optimization and Multiscale Verification2026-99-14089/11/2026
Composite materials have become widespread for use in aircraft load bearing structures due to their ability of reducing structural mass without compromising the required stiffness, strength and safety requirements in the face of aerodynamic, inertial and thermal service loads. This work has addressed with success the development and validation of such an integrated lightweight-design framework applied to a representative composite aircraft load-carrying structure. The workflow exploits SIMP topology optimization and parametric modelling as well as Kriging and support vector regression surrogate models, Latin hypercube sampling and a multi-island genetic algorithm, to screen the low mass design space subject to stress, deformation, buckling and manufacture ability constraints. The optimized FE model contained 2.15M elements. It predicts a max prinicpal stress of 263.4MPa,a stress margin of 4.18, and a tip deflection of 1.24 mm under the 2.0 mm limit, and the minimum buckling factor was 3.47. The prototype test recorded maximum stress at 257.6 MPa, and thermal deflection of 1.27 mm while deviation between simulations and testing remained below 6%. In general, the above results indicate that the surrogate model based optimization coupled by the manufacturing feedback will be able to relate the aircraft composite structure design, fabrication and validation, and can be used as a realistic benchmark for digital engineering analysis of light-weight aircraft structures.
He, Haoming
Study on Water Hammer Effect of an Aircraft Composite Fuel Tank under High-Speed Impact of Multiple Fragments2026-99-14209/11/2026
The investigation examines the damage mechanisms of composite fuel tanks under high-speed impact by multiple fragments utilizing a fluid-solid coupling finite element approach. The Arbitrary Lagrangian Eulerian (ALE) algorithm is used to simulate the single-box composite fuel tank under the impact of different distribution distances of fragments by using the software LS-DYNA. The cavity evolution and the panel deformation of the composite fuel tank are analyzed in detail. The findings indicate that the water hammer effect amplifies the extent of damage to the composite fuel tank structure. During the initial phase following fragment impact, a cavity forms within the tank. The resulting rise in the pressure difference between the interior and exterior of the tank causes the liquid to impinge on the impacted panel, leading to its deformation. In the later stage, due to the large degree of damage to the incident panel, there is a certain degree of pressure relief inside the fuel tank, the degree of water hammer effect is obviously reduced, and the cavity in the fuel tank gradually disappears. The distribution distance of the fragments has a great influence on the damage effect of the fuel tank. As the spacing between fragments diminishes, their effects become more concentrated. This results in increased force from the liquid on the fuel tank panel, leading to greater deformation and more severe damage to the panel.
Wang, Ruiwen, Song, Yahui, Li, Chengwang
Transition Mode Control for Electric Vertical Take-Off and Landing Drones Based on Improved Self-Disturbance Suppression2026-99-14239/11/2026
To address the tilt transition control issue in electric vertical take-off and landing (eVTOL) drones, this paper proposes a cooperative control strategy combining an adaptive tilt scheme with an improved adaptive disturbance rejection control (ADRC). First, based on the eVTOL drone’s dynamic characteristics, a motion model suitable for control design is established. Second, a real-time state-based adaptive tilt strategy is designed by achieving decoupled mapping between motor speed and tilt angle through a dynamic control allocation matrix. Furthermore, a novel Sanf function is proposed for the extended state observer (ESO) within the ADRC framework. The global convergence of the improved ESO is demonstrated, enhancing disturbance estimation accuracy and stability. Finally, simulation experiments validate the effectiveness of the adaptive tilt scheme based on dynamic control allocation, along with the robustness and reliability of the altitude, velocity, and attitude loops.
Zhang, Junyang, Wang, Xiangyang, Yang, Mingyuan, Zhang, Huanhuan
Large-Scale Helicopter Medical Rescue Task Allocation Method Based on Improved NSGA-II Algorithm2026-99-15769/11/2026
Helicopter-based medical rescue can provide quick response and a wide coverage area; these two points are important in large-scale disaster rescue operations. Scientific helicopter scheduling affects both rescue efficiency and operating cost. To address the helicopter scheduling problems under large-scale disaster scenarios for aerial medical rescue, this paper studies the process and features of aerial medical rescue and establishes a helicopter scheduling model. The goal is to minimize both the time taken for the mission and the amount of money spent on it, and at the same time, make sure that everyone who needs help gets rescued. To solve the shortcomings of the traditional NSGA-II algorithm, such as being prone to falling into local optimum and low efficiency, a feasibility-first NSGA-II algorithm is proposed to assist with helicopter scheduling. This approach uses Latin Hypercube Sampling (LHS) for initialization to improve its global search capability and performs a feasibility check before sorting to reduce redundancy in the solution space and improve the optimality of the outcomes and the speed of computation. The simulated experiment shows that the proposed algorithm has higher efficiency, stability, and better performance than the traditional heuristic algorithm.
Lu, Xun, Liu, Hu, Tian, Yongliang, Zhang, Nan
Aerodynamic Design and Optimization Study of a Ma 0-5 Two-Dimensional Wide-Range Adjustable Nozzle2026-99-14039/11/2026
To address the thrust requirements across multiple operating conditions of hypersonic vehicles during wide-speed-range flight (Ma 0–5), this paper presents the design of a two-dimensional adjustable nozzle with a circular-to-rectangular cross-section. A maximum-thrust contour was constructed using the method of characteristics, and the aerodynamic performance and structural features of this rotation-based adjustment approach were systematically analyzed. The results demonstrate that the nozzle achieves a thrust coefficient between 0.951 and 0.992 across the entire flight envelope, with a thrust vector angle consistently maintained at 0°, indicating excellent thrust performance and flow-field symmetry. Furthermore, by introducing a biaxial transition segment and optimizing its tangent angle (θ = 130°) alongside fillet rounding (R = 30 mm), unsteady flow oscillations and separation at high Mach numbers were effectively eliminated, enhancing both structural durability and aerodynamic stability.
Feng, Fan, Lv, Zheng, Xu, Jinglei
Nc5-PCS Based Heterogeneous Point Cloud Matching for Roads2026-99-15339/11/2026
Point cloud registration represents a fundamental task in geospatial informatics and 3D computer vision, aiming to align heterogeneous point clouds through rigid transformation estimation. While Super-4PCS serves as an efficient coarse registration method, it exhibits limitations when handling large-scale datasets, planar-distributed point clouds, and scenarios with unknown scale differences. To overcome these challenges, this paper proposes the Nc-5PCS (Neighborhood-constrained 5-Point Congruent Sets) algorithm. Nc-5PCS first performs approximate scale estimation through concavity-convexity similarity analysis within coarse overlap regions, addressing the inherent scale limitation in 4PCS-based approaches. Subsequently, the algorithm employs 3D Harris feature point extraction to significantly reduce data volume while preserving critical geometric characteristics. The core innovation lies in designing a non-coplanar 5-point basis with a corresponding hash-based retrieval mechanism, effectively resolving the feature degradation problem caused by coplanar 4-point bases. Furthermore, normal vector angular constraints are incorporated to enhance consensus evaluation during correspondence selection, substantially improving registration accuracy. Experimental validation demonstrates that Nc-5PCS achieves a point-to-point RMS error of ≤ 0.227 m, outperforming Super-4PCS to provide superior initial alignment for subsequent ICP refinement.
Liu, Lei, Yu, Keguang, Li, Xinyi, Sun, Guangde, Zhao, Xinyuan, Zhu, Dongni, Fan, Yabo, Guo, Shihao
Research on Location Selection of Logistics UAV Takeoff and Landing Points for Uncertain Demands2026-99-15799/11/2026
In order to solve the problem of sharp fluctuations in demand in the terminal delivery of logistics drones and the situation that traditional positioning models lack robustness, this paper puts forward a robust positioning model (RFL-LU) that takes into consideration the demand uncertainties and the physical constraints of drones (such as endurance and no-fly zones, and so on). This model aims at minimizing the total cost of construction, transportation, and maintenance, and also combines the advantages of the set covering model and the P - median model. It incorporates an uncertainty budget Γ to adjust the degree of robustness, and then transforms the nonlinear robust constraints into linear ones through dual transformation, ensuring that the capacity of the take - off and landing points can cover both the nominal demand and the fluctuating increment. In order to efficiently address the model issues, an improved tabu search (ITS) algorithm that we have developed is presented. This algorithm, which makes use of adaptive neighborhood operations, double-objective taboo lists, and elite solution crossover learning methods, optimizes the 0 - 1 position assignment variables and continuous capacity variables in two phases. We carried out simulations with LRP standard instances and made comparative verifications under different uncertainty budgets Γ (3, 6, 9, 12), and demand fluctuation ranges (from 30% to 80%), and also carried out sensitivity analysis at the same time. The results show that the uncertainty budget Γ has a rather significant impact on the number of take-off and landing points and load balancing: a high Γ can ensure a 100% service level, but the construction cost will be higher. There is a non - monotonic positive correlation between the demand fluctuation range and the total cost, and this model can balance costs and services by adaptively adjusting the scale of facilities. In this research, in the situation of uncertain demands, it offers the scientific decision-making basis for the layout of the take-off and landing points of logistics drones, and also enhances the network’s elastic and adaptive capabilities.
Ding, Zihao, Li, Xiaojin
Study on Brake Efficiency Airworthiness Requirements and Verification of Transport Category Aircraft2026-99-14049/11/2026
Braking efficiency is one of the key indicators for evaluating the performance of braking systems on transport category aircraft. The value of braking efficiency is directly related to the safety of aircraft deceleration processes, especially during landing, and it is also critical for civil aircraft operators to improve operational efficiency on routes. This paper presents the airworthiness regulation requirements related to braking efficiency, requirements for aircraft wheels and tires, requirements for runway pavement types, major sources of contaminants, and specific requirements for simulating wet runway conditions using different contaminants. This paper analyzes effective methods for calculating braking efficiency, including the pressure method, torque method, and slip ratio method, and introduces the approaches for acquiring data of relevant parameters. Combining experience from braking efficiency verification work, the paper demonstrates the specific test procedures for the actual measurement of braking efficiency. Based on measured data such as braking pressure, wheel speed, and aircraft speed during braking, as well as the wheel dimensions and rotational inertia of wheels and brakes, the specific braking efficiency values under different calculation methods are derived. The paper compares the differences in braking efficiency values obtained by various calculation methods for similar braking processes, analyzes the causes of these differences, and demonstrates that the accuracy of braking efficiency calculated by different methods is acceptable. Additionally, the same calculation method is applied to compute the braking efficiency of multiple braking deceleration processes, which demonstrates that the method has good repeatability and can be stably used for braking efficiency calculation. This verification method provides a reference for the certification work to ensure that the braking efficiency of transport category aircraft complies with airworthiness and performance requirements.
Feng, Yibo
2025 International Conference on Aerospace and Electronic Information2026-99-14009/11/2026
TOC
Tobolski, Sue
Study on Rapid Formation Generation Method for Multi-UAV Swarms2026-99-14219/11/2026
This paper presents a generalizable geometric framework for rapid on-demand generation of multi-UAV formations with arbitrary 2D geometries and user-specified scalable scales. First, vertices, edge intersections and edges are extracted from a user-defined formation template to enable parametric description of both simple and composite formation geometries. Second, boundary interpolation, edge expansion and recursive internal expansion are integrated to synthesize hierarchical multi-layer UAV deployment point sets under a controllable expansion ratio. Third, a geometric distortion metric is proposed to optimize UAV node indexing and formation reconstruction while preserving inter-node topological consistency. Algorithmic derivations, complexity analysis and simulation assumptions are further elaborated. Simulation results verify that the proposed method preserves geometric fidelity of target formations while delivering superior scalability and spatial coverage, rendering it well-suited for emergency transport, aerial surveying and low-altitude cooperative missions in dense urban environments.
Fu, Mingyi, Zeng, Guoqi, Gu, XinZhu, Wang, Jia
A Simple and Efficient THINC Scheme for Multiphase Flow via Dominant-Material Selective Reconstruction2026-99-12299/4/2026
Multiphase compressible flow problems are widespread in aviation, aerospace, transportation, military, and industrial fields, for instance, in underwater explosion bubble dynamics, fuel injection for hypersonic vehicles, liquid sloshing in propellant tanks, and supercavitating underwater vehicles. This paper proposes an improved THINC (Tangent of Hyperbola for Interface Capturing) method for multiphase flow simulations, based on a selective reconstruction strategy for the dominant material. The core of the strategy is to apply the THINC reconstruction exclusively to the material with the largest volume fraction within a multiphase mixed cell, which numerically governs the local interface evolution. The volume fractions of non-dominant materials are then obtained through a proportional distribution that inherently ensures the summation (Σαk = 1) and boundedness (0 ≤ αk> ≤ 1) constraints are met without explicit corrections. This approach reduces the number of THINC reconstructions for each time step in a multiphase mixed cell from Nm (the number of materials) to one, significantly simplifying the algorithm and lowering computational cost. It thereby avoids the error accumulation and complex renormalization procedures associated with conventional schemes that reconstruct all materials. While strictly maintaining volume fraction conservation, the proposed method preserves interface sharpness through the underlying THINC framework. The method is implemented in a diffuse-interface, multiphase Eulerian framework and validated with a series of challenging benchmarks, including shock-helium bubble interaction, triple-point problem, gas impact, and the more complex modified gas impact. Numerical results show that, compared with conventional multiphase THINC approaches that reconstruct every material, the proposed scheme can reduce CPU time by about 40.0% without compromising the accuracy of key physical quantities.
Wang, Wei, Zhong, Yanxu, Hu, Qinghua, Yang, Canqun
Aerodynamic Load Calculation and Prediction Method for Folded Wing Mechanism2026-99-12899/4/2026
The folding wing mechanism is widely used in aircraft design. Whether the folding wing surface can unfold smoothly determines whether the aircraft can fly normally. Therefore, studying the aerodynamic loads and structural deformations during the unfolding process of folded wing surfaces is very important. The motion process of a folded wing mechanism is a typical fluid-structure interaction (FSI) process. During deployment, the wing surface moves under the combined action of the actuator’s pull and the aerodynamic loads from the incoming flow, while the large deformation of the wing surface during its movement, in turn, affects the aerodynamic loads on the mechanism from the flow field. Considering the FSI effects during the unfolded motion process of the folded wing, simulation was conducted using the ALE algorithm in LS-DYNA to obtain the kinematic and dynamic parameters in the unfolded motion process, and also to get the aerodynamic torque on the wing under different angles and angular velocities. In practical engineering applications, the actuation force of the deployment mechanism can vary due to factors such as the amount and performance of the pyrotechnic material. Consequently, the final velocity and the whole motion process of the wing mechanism will also change. For the calculation of aerodynamic external loads under multiple operating conditions, using the ALE algorithm will consume a large amount of computational time and cost. Given the high computational cost and long computation time of finite element simulations, a BP neural network was established to calculate the aerodynamic loads on the wing surface under different actuation forces. This allows for a rapid assessment of whether significant deformation or damage will occur to the folding mechanism or nearby components during the deployment process.
Wei, Ting, Li, Naitian, Tong, Zongkai
Development of Engine Nozzle Characteristic Determination System2026-99-12429/4/2026
The determination of flight thrust for aircraft engines is an important means of evaluating engine and aircraft performance. The characteristics of the tail nozzle of the tested engine are an important data support for calculating flight thrust. In order to accurately evaluate the flight thrust of a certain type of engine, an “engine nozzle characteristic determination test system” is developed to obtain the thrust characteristic curve and flow characteristic curve of the nozzle. A calibration device and calibration process were designed for the experimental system to achieve in-situ calibration of the system.
Ren, Boyang, Jia, Wenjie, Song, Jiangtao
CFD-Based Aerodynamic Stability Analysis of a Quadrotor UAV2026-99-12539/4/2026
This study analyzes the aerodynamic stability of a typical quadrotor UAV during hover and vertical flight using Computational Fluid Dynamics (CFD). A fitted relationship between single propeller rotational speed versus lift and torque was obtained through simulation. Rotor speed input parameters were determined by combining this relationship with force analysis under ideal conditions. Lift and torque variation data for each rotor under two typical flight conditions were subsequently acquired. The research examines changes in lift and torque caused by aerodynamic interference between rotors, which induces UAV instability. To address the additional rotor lift from airframe obstruction of airflow, a “Reduction Value Method” is proposed to correct the lift data. Kinematic simulations conducted in Adams show significant displacement and angular displacement fluctuations in both hover and vertical flight states. Instability is more pronounced during vertical motion. This research provides a theoretical basis for understanding UAV flight stability mechanisms and optimizing control strategies.
Zhao, Haiyuan, Li, Jia, Song, Jiafeng
Research on Scalelike Adaptive Suction Flow for Wide-Speed Range Hypersonic Inlets2026-99-12529/4/2026
As critical components of aircraft, hypersonic inlets utilize shock wave compression effects to pressurize incoming flow. The interaction between shock waves and the boundary layer tends to generate separation zones, and it adversely affects inlet performance. As a method to significantly enhance inlet performance, suction technology can substantially reduce the size of separation zones when they form in the inlet. However, when the inlet is started and operating normally, suction configurations may cause mainstream leakage and make it difficult to meet the requirements of inlets with wider speed ranges. This paper designs an adaptive scaliform suction structure that utilizes a lift-generating design to induce a slight upward deflection of high-speed near-wall flow. It can reduce high-speed mainstream leakage without compromising the effectiveness in low-speed separation zones. Numerical simulations are employed to evaluate its suction performance in both inlet separation zone flow fields and supersonic mainstream flow fields. The internal flow mechanisms of the scaliform suction structure are investigated, and differences in its behavior across various suction flow fields, as well as its interference with the mainstream, are discussed. The study reveals that when the height of the scaliform suction structure is approximately 1/8 of the incoming flow’s velocity boundary layer height, the suction flow coefficient in the separation zone is twice that in the hypersonic mainstream. Furthermore, the loss in Mach number and total pressure recovery coefficient of the near-wall supersonic mainstream is controlled within 5%. This structure exhibits an adaptive suction capability for separation zones, thereby extending the starting speed range of the inlet.
Zhao, Xuening, Zhao, Yilong
Study on the “Vibration-Differential Pressure” Coupled Environment Test Technology for Airborne Equipment Vibration Isolation Systems2026-99-12519/4/2026
The stable operation of airborne equipment determines the functionality and performance standards of aircraft. Installing vibration isolation systems on such equipment aims to improve its performance. With the advancement of aircraft capabilities, future evaluations of airborne equipment’s vibration isolation systems will require increasingly real-world experimental assessment. Achieving a ground-based simulation of the complex coupling environment encountered by airborne equipment at high altitudes presents a huge challenge. This paper proposes a method utilizing air springs to simulate differential pressure forces, successfully enabling ground-based testing of “vibration-differential pressure” coupled environments for airborne equipment. The results verify the effectiveness of this approach, and it can be used for this type of environmental testing.
Qin, Xiaomeng, Xing, Xiaoming, Mou, Haowen, Wang, Jianzhong
Numerical Investigation of Spiral Tubes and Turbulators for Enhanced Metal Hydride Reactors2026-99-12589/4/2026
Solid-state hydrogen storage is severely limited by poor thermal performance of storage reactors, which leads to non-uniform temperature fields and slow reaction kinetics. A numerical model for metal hydride hydrogen storage technology was implemented by means of COMSOL Multiphysics 6.3, based on hydrogen sorption behavior for LaNi5-based material. After experimental validation, a spiral-wound tube with embedded turbulators was introduced into the reactor. The influence of turbulator cross-sectional ratio and shape on hydrogen-absorption performance was then investigated. When the turbu-lator occupied 1/40 of the cross-section, the temperature distribution became more uniform and the reaction rate increased markedly; the time to achieve 80% conversion was reduced by approximately 9.29%. The study demonstrates that tailoring the turbulator geometry (circular vs. square) and exploiting its synergy with the spiral tube accelerates reaction kinetics and balances the temperature field. Under 0.8 MPa and 313 K, a hydrogen uptake of 1.4 wt% was achieved. The simple structure can be mass-produced by CNC (Computer Numerical Control) tube-bending, making it attractive as a portable hydrogen source for mobile devices such as unmanned aerial vehicles.
Lin, Jiangnan, Jin, Tingxiang
Ant Colony-Artificial Potential Field Fusion Path Planning Algorithm Based on a Maneuver Action Library2026-99-12579/4/2026
The traditional Ant Colony Algorithm has defects such as easy entrapment in local optima due to a simplistic heuristic function and slow convergence due to excessive search directions. A fusion path planning algorithm integrating ant colony optimization and artificial potential field based on a maneuver action library is proposed. Firstly, a mathematical model for UCAV path planning is established. Considering the maneuverability constraints of UCAVs, and drawing on the concept of basic maneuver action libraries for fighter aircraft, an ant colony-potential field fusion path planning algorithm based on a maneuver action library is introduced. Simulation results demonstrate that compared to two other algorithms, the proposed method significantly improves the number of waypoints and planning completion time.
Li, Ruishen, Chen, Xiaogang
Research and Analysis of Civil Aircraft Radio Altimeter Malfunction2026-99-12359/4/2026
The radio altimeter is an important navigation instrument on an aircraft, capable of accurately measuring the aircraft's true height above the ground or sea to ensure safe flight. This capability is crucial for ensuring normal flight operations, especially during critical phases such as takeoff, approach, and landing. Polar terrain is complex and continually changing. The vast, endless ice fields, crisscrossing glacier crevasses, towering icebergs, and weather conditions all add significant uncertainty to air travel. In such environments, the aircraft's navigation system is particularly important as a core device to ensure flight safety. This article provides a brief overview of the aircraft radio altimeter system. Using data and observations from production flight tests, it studies the specific challenges posed by radio altimeter failures encountered during these critical validation flights. The study synthesizes these findings and proposes a relatively general troubleshooting approach to address such issues. Furthermore, the effectiveness of this method has been rigorously validated through its application in solving a complex real-world radar altimeter failure case.
Song, Mingming, Mi, Yujie
A Computing Method of Splitting Factor for 3D Non-Compatible Generalised Mixed Hexahedral Element2026-99-12119/4/2026
With the rapid development of the aerospace industry, FEM has been widely applied as a key tool. However, the high complexity of aircraft and spacecraft geometries and structures often leads to unavoidable distorted meshes in FEM, which significantly degrades the accuracy of analysis results. Both the splitting factor and the mesh distortion significantly affect the accuracy of the generalised mixed elements. The coefficient matrix deviation between the distorted element and the standard element was quantified. Thus, the computing equation for a three-dimensional (3D) hexahedral distorted element’s splitting factor was constructed. Examples were used to validate the proposed method. For distorted meshes, the accuracy of NCGME has been improved.
Shen, Ao, Qing, Guanghui
Dynamic Characteristics Analysis of Conical-Cylindrical Shell Structure2026-99-12789/4/2026
In the context of aerospace development towards lightweight, high reliability, and long life directions, such materials have become the core materials of key load-bearing structures for advanced aircraft, and their structural dynamic characteristics are directly related to the flight safety and service stability of the aircraft. This article uses uniform artificial springs to simulate the stiffness coupling effect and boundary conditions of the entire structure. In the stage of theoretical modeling, classical shell theory is used, and orthogonal polynomials are introduced as displacement functions. Is solved by the Lagrange energy equation. On this basis, the effect of external size parameters on structural vibration frequency is deeply discussed. With the change in structural natural frequency with the taper of the conical shell, the ratio of cylindrical shell length to diameter and the ratio of diameter to thickness are analyzed.
Zhao, Yunhao, Chen, Jie
Navy Flight-Tests 3D-Printed Composite Repairs for F/A-18 Super HornetsTBMG-558259/1/2026
Naval Air Warfare Center Aircraft Division Patuxent River, MD
Influence of Restraint System Angles on Impact Response and Protection of Child Occupants in Vertical Crash Conditions2026-99-04138/28/2026
Focusing on the protection needs of child occupants in the scenario of aircraft vertical crashes, a finite element calculation model based on the cabin structure of a certain type of small electric aircraft was established. The child seat restraint system was coupled with the THUMS 3YO human body model, and the vertical 15 g condition meeting the requirements of Article 23.562 of CCAR-23-R3 was simulated. The influence law of the safety belt restraint angles (formed by different safety belt routing positions) on the dynamic response and injury indicators of child occupants was explored. To verify the rationality of the simulation results, a physical impact experiment was conducted using a Hybrid III 3YO child dummy and the same type of child seat, with key indicators (e.g., head acceleration, lumbar load) measured and compared with simulation data. The analysis results show that the effect of the safety belt restraint angle on the overall protective performance is less pronounced under vertical conditions, but a clear trend is observed: when the angle is in the range of 76°~84°, the head acceleration is relatively low and the brain tissue injury indicators are in the optimal state, which can effectively reduce the risk of head and neck injuries; when the restraint angle increases to 92°, the lumbar axial load and lung strain increase significantly, indicating a detrimental effect. The results of this study clarify the differences in the protective performance of child seats under different restraint angles, and provide a theoretical basis and technical guidance for the layout of safety belt anchors of aircraft seats and the optimal design of child seats.
Wang, Yafeng, Guo, Pan, Li, Weiliang, Shi, Xiaopeng
Vinylene-Linked Covalent Organic Frameworks as Superior Photocatalysts for Hydrogen Evolution over Imine-Linked Counterparts2026-99-04148/28/2026
The scheme of photocatalysis of water, a way of hydrogen generation as a clean, high-efficiency fuel source for aircraft and long-range transport systems has received considerable interest. The development of the covalent organic framework (COF) - derived materials for hydrogen evolution reaction (HER) has since become a research highlight. Compared to traditional methods, photocatalytic hydrogen evolution systems based on COFs can provide ways of generating hydrogen gas without depending upon noble metal catalysts, thereby enhancing the sustainability and prospects of this technology for future aerospace energy applications.In this work, two covalent organic frameworks (COFs) with distinct linkages—a vinylene-linked COF A (via Knoevenagel condensation) and an imine-linked COF B (via Schiff-base reaction)—were designed and synthesized to compare their performance in the photocatalystic hydrogen evolution reaction (HER). Structural and electrochemical characterizations confirmed that, despite lower crystallinity and specific surface area due to pore blockage, COF A exhibited a suitable band structure for photocatalysis and achieved an HER rate of 56 μmol h^–1 g^–1 under simulated sunlight. In contrast, COF B was ineffective. This study experimentally validates the superior photocatalytic potential of vinylene-linked COFs over imine-linked counterparts for HER, highlighting their potential as non-noble-metal catalysts for aerospace and transport-oriented fuel generation.
Cao, Yijie, Luo, Xin
SAE TOMORROW TODAY - Is Megawatt Charging the Missing Link to EV Scalability?135828/27/2026
As electrification expands beyond passenger vehicles to commercial trucks, mining equipment, marine vessels, and even aircraft, the challenge is no longer whether megawatt charging is possible, it's how to scale it safely and efficiently. Fortunately, industry standards are making that future possible. Listen in as we sit down with Ted Bohn, Principal Electrical Engineer at Argonne National Laboratory and Chair of the SAE J3271 Committee, to discuss the Megawatt Charging System (MCS) and how collaboration across industries is laying the foundation for high-power charging that works across multiple transportation sectors. This conversation offers a behind-the-scenes look at how standards are developed, tested, and validated, and why scalable charging depends on much more than the connector itself. Whether you're designing commercial EVs, deploying charging infrastructure, or following the future of heavy-duty Class 8 electrification, this episode provides valuable insight into the technologies and standards that will shape the next generation of mobility. Have your own thoughts on this topic? We'd love to hear from you! Share your comments, questions and ideas for future topics and guests to podcast@sae.org. Don't forget to take a moment to follow SAE Tomorrow Today--a podcast where we discuss emerging technology and trends in mobility with the leaders, innovators and strategists making it all happen--and give us a review on your preferred podcasting platform. Follow SAE on LinkedIn, Instagram, Facebook, X, and YouTube. Follow host Grayson Brulte on LinkedIn, X, and Instagram.
Patterson, Lori
Research and Practice of Emergency Rescue Unmanned Patrol Flying Equipment2026-99-03378/14/2026
To enhance China’s disaster and accident emergency response capabilities and strengthen the digital battlefield system for emergency rescue, an integrated multi-payload unmanned aerial surveillance and communication support system has been developed for extreme weather conditions and ‘triple-disconnection’ disaster scenarios. This paper sets out to address the limitations of traditional emergency drones, including poor environmental adaptability, weak payload capacity, and operational inconvenience. The system’s resistance to wind and rain has been significantly enhanced through the optimization of its airframe design. The innovative design incorporates dual-station symmetric conjugate antennas with planar blind-spot coverage systems, integrating public and self-organizing network base stations to achieve three-dimensional signal coverage and heterogeneous network integration. This enhances ground cellular network resilience. Multi-functional reconnaissance payloads are integrated and compatible with day/night and smoke/rain scenarios, thus overcoming the limitations of single-source visual information perception. The system employs zero-length deployment and parachute recovery methods, thereby facilitating rapid deployment and terrain-independent take-off and landing capabilities. The simulation results obtained demonstrate excellent aerodynamic performance, thus permitting safe operation in wind conditions up to Force 8. The antenna system under discussion is innovative in nature and has been developed to achieve 360° three-dimensional signal coverage. The primary function of this system is to ensure sustained communication link integrity. The field trials further corroborate the aircraft’s stable low-altitude cruising capability in Force 8 winds, thereby averting congestion in constrained rescue airspace. The dual-base station design, incorporating symmetric conjugate antennas and blind-spot compensation antennas, has been demonstrated to reliably restore public ground network signals within a 6.7-kilometre radius. The development of this unmanned aerial patrol system addresses a significant gap in low-altitude rescue capabilities for intelligent unmanned equipment in harsh environments. It underpins the integrated emergency command and operations system for intelligence, command, and execution, as well as the integrated emergency communication support system spanning the air, land, and sea domains. This advancement has been demonstrated to enhance disaster response efficiency and auxiliary decision-making effectiveness under extreme conditions.
Bian, Lu, Fang, Yudong, Yang, Jixing, Zhang, Chen, Hu, Bin, Zhang, Mingyue
Research on the Assembly Sequence Planning Algorithm under Cabin and System Constraints2026-99-03458/14/2026
Assembly sequence planning is a crucial part of process preparation in aircraft final assembly. A scientifically designed assembly sequence can significantly improve assembly efficiency and reduce costs in aircraft production. Efficient planning not only streamlines the workflow but also minimizes potential errors and rework, which are critical in high-stakes aviation manufacturing. This paper examines the constraint relationships in aircraft assembly from the perspectives of cabin constraints and system constraints, covering both spatial layout restrictions and functional logical dependencies to ensure the comprehensiveness of constraint analysis. It establishes a directed graph for the aircraft assembly outline and generates the corresponding adjacency matrix, which converts the complex constraint relationships into a structured mathematical expression for easier subsequent algorithmic processing. The Warshall algorithm and Johnson algorithm are used to check and extract contradictory constraints from the directed graph. The adjacency matrix is then employed to calculate the reachability matrix, which helps identify redundant constraints and reduces the computational effort in assembly sequence planning. Finally, the optimized constraint relationships are used to calculate the aircraft’s final assembly sequence, which generates a Gantt chart for assembly sequence planning, guiding the on-site assembly order and accelerating aircraft development efficiency. The integrated approach effectively addresses the key challenges in complex aircraft assembly sequence planning.
Guo, Jingjing, Cun, Wenyuan, Zhao, Jiong, Yu, Yang, Yang, Rui, Yu, Long
Bi-Directional Evolutionary Topology Optimization Design for Rib Structures2026-99-03148/14/2026
The performance of modern high-speed aircraft is intrinsically linked to structural mass. As a key component that generates lift, the shape and lightweight of the wing are crucial for improving aircraft performance. This study employs the bi-directional evolutionary structural optimization (BESO) method to perform topology optimization on the wingrib structure of a modern high-speed fighter aircraft. Minimize the overall strain energy as the objective and use the wing rib volume fraction as the constraint to perform topology optimization design on the wing ribs. Based on element stress/strain energy density criteria, the method iteratively adds or removes material to efficiently construct optimal load-transfer paths within the rib configuration. Following the redesign according to the optimized topology, the structural mass was reduced by 39.236% while satisfying strength and stiffness constraints. Results demonstrate that the BESO methodology effectively generates high-efficiency load-bearing configurations for wing ribs, significantly improving material utilization efficiency and structural performance while substantially reducing wing mass. This research provides an effective approach for lightweight design and performance enhancement of critical load-bearing structures in modern high-speed aircraft.
Zhou, Lei, Wang, Wei, Gong, Quanwei, Zhou, Jingchao, Guan, Shenxiaoge
Research on Flexible Positioning Technology for Airplane Pipe2026-99-03088/14/2026
Airplane pipe assembly is an important part of the aircraft manufacturing process. There are some limitations, such as poor adaptability and a long manufacturing cycle, in conventional clamps used for clamping pipes. To avoid these limitations, this paper developed a pipe clamping system with the capability of adapting pipes with different shapes and diameters. The least squares method was used to build a coordinate system for the pipe and pipe clamp system. The kinematical model of the pipe clamp system was analyzed. A method of finding the inverse solution of mechanical kinematical parameters was proposed, and was utilized to drive a mechanism performing a positioning function. The experiment, detailed in this paper, authenticated that the positioning precision of the pipe clamp system satisfies the requirements of airplane manufacture.
Xu, Jun, Zhao, Xi, Wang, Wei
SAE TOMORROW TODAY - How Aerospace Safety Standards Enable the Future of Flight135808/12/2026
Whether it's supersonic travel, commercial space, or AI-enabled aircraft, one message remains constant: safety standards are the common language that enable the future of flight. Listen in as we sit down with Craig McMillan, Model Based Systems Engineering (MBSE) Growth Leader at GE Aerospace, to discuss the intersection of AI, digital engineering, and the growing complexity of modern aircraft. The conversation examines why independent verification, rigorous systems engineering, and collaboration across the aerospace industry remain essential as aircraft become more software-driven and interconnected. We'd love to hear from you! Share your comments, questions and ideas for future topics and guests to podcast@sae.org. Don't forget to take a moment to follow SAE Tomorrow Today--a podcast where we discuss emerging technology and trends in mobility with the leaders, innovators and strategists making it all happen--and give us a review on your preferred podcasting platform. Follow SAE on LinkedIn, Instagram, Facebook, X, and YouTube. Follow host Grayson Brulte on LinkedIn, X, and Instagram.
Patterson, Lori
Perspectives on Integrating Structural Health Monitoring Systems into Fixed-Wing Military AircraftAIR6245A (Current)8/11/2026
This SAE Aerospace Information Report (AIR) is prepared for stakeholders seeking information about the evolution, integration, and approval of SHM technologies for military aircraft systems. The report provides this information in the form of (a) two military organizations’ perspectives on requirements, and (b) general SHM challenges and industry perspectives. The report only provides information to generate awareness of perspectives for military aircraft and, hence, assists those who are involved in developing SHM systems understanding the broad range of regulations, requirements, and standards published by military organizations that are available in the public domain from the military organizations.
Aerospace Industry Steering Committee on Structural Health
Analysis of Critical Issues in the Assembly and Deployment Techniques of Unmanned Aerial Vehicles2026-99-09068/7/2026
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, Ting, Wen, Hao, Qi, Yelin, Yan, Rui, Ma, Tengbo, Yang, Wen
Accelerometer Mass Compensation on Frequency Response Functions in Impact Testing Based on the Substructure Method2026-99-09118/7/2026
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, Zhenrong, Yao, Zhenqiang
Structural Design and Optimization of Heavy-Duty2026-99-09108/7/2026
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, Kanghui, Li, Guiying, Yu, Zhigang, Yang, Jingru, Wang, Yong, Zhang, Chao
SAE TOMORROW TODAY - SAE JA1016: Scaling the Future of UAVs with Battery Interoperability135798/6/2026
From drone delivery to public safety and defense, the next generation of uncrewed aerial vehicles (UAVs) will be powered not just by better batteries, but by better battery standards. Listen in as we sit down with Jeff Yambrick, Chair of the SAE Battery Cell Size Standardization Committee, and Lisa King, Director of Advanced Battery Strategy at Leap Manufacturing, to discuss SAE JA1016 -- a new standard designed to simplify battery integration, accelerate commercialization, and strengthen the UAV supply chain. During this conversation, you'll learn why common battery formats are essential for reducing development costs and creating greater interoperability across commercial and defense applications. We also explore the importance of domestic battery manufacturing, supply chain resilience, and how standardization can accelerate innovation without limiting future battery technologies. To join the SAE Battery Cell Size Standardization Committee, email Dante Rahdar at Dante.Rahdar@sae.org. We'd love to hear from you! Share your comments, questions and ideas for future topics and guests to podcast@sae.org. Don't forget to take a moment to follow SAE Tomorrow Today--a podcast where we discuss emerging technology and trends in mobility with the leaders, innovators and strategists making it all happen--and give us a review on your preferred podcasting platform. Follow SAE on LinkedIn, Instagram, Facebook, X, and YouTube. Follow host Grayson Brulte on LinkedIn, X, and Instagram.
Patterson, Lori
Charting the Flight Path of the Aerospace & Defense Industry with Digitalization26AERP08_028/1/2026
New technologies, advanced materials, evolving mission profiles and fast-changing requirements are forcing the aerospace and defense (A&D) industry to dramatically increase the speed of engineering. Companies must design, validate and bring more complex products to market faster than ever, even as software, electronics and autonomy continue to reshape what aircraft, spacecraft and defense systems can do. At the same time, a growing production challenge is emerging. Workforce shortages, supply chain disruption and pressure to reduce cost and cycle time are converging with new demands for greater volume and flexibility. Defense programs are seeing increasing need for larger quantities of lower-cost systems such as drones, while commercial aerospace companies continue to work through backlogs and reinforce their fleets. To keep pace, the industry must accelerate innovation while also scaling production with greater speed, resilience and adaptability.
How Airbus is Developing Artificial Intelligence for Future Cockpits26AERP08_118/1/2026
Computer vision, automated landing and embedded AI for tomorrow's cockpits. Airbus, Toulouse, France At the VivaTech forum in June, Airbus showcased a demonstration highlighting the use of computer vision to enhance automated landing procedures and operational efficiency. The “Vision Landing Application” utilizes artificial intelligence to analyze runway features in real-time using onboard cameras. The goal of this research is to create an additional and independent positioning source to guide pilots and/or their aircraft reliably, opening up the perspective of bringing autoland (fully automated landing procedure) capabilities to airports that lack advanced ground infrastructure. While the technology is still in the research phase and far from commercial certification, this technical exploration aligns directly with Airbus' global roadmap for Smart Automation. Airbus already has a head start, since it has already conducted numerous research projects during the last decade, which have led to the demonstrator at Airbus' stand at this year's show.
How Electrification is Reshaping Motion Control in Flight Systems26AERP08_018/1/2026
For decades, hydraulic systems have been relied upon to do all the heavy lifting in aerospace. They are powerful, reliable, and deeply embedded in how aircraft are designed, to the extent that - for many engineers - they are simply part of the landscape. Now, however, things are beginning to change. From advanced air mobility platforms now entering certification to next-generation commercial aircraft on 10-year horizons, electric and electro-hydraulic actuation is steadily replacing the heavy, centralized hydraulic architectures that have defined flight control for decades. Understanding why means stepping back from the actuator itself and looking at the aircraft as a whole system - and, increasingly, as an integrated motion control challenge.
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