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This SAE Aerospace Information Report (AIR) defines the materials, strength, and finishes utilized in linear hydraulic flight control actuators.
A-6B1 Hydraulic Servo Actuation Committee
The purpose of this document is to provide information regarding performance, use, and quality of the Quick Donning Crew Oxygen Mask assembly with an integrated Regulator (QDCOMR). This document is intended to guide the user through a selection of requirements and validation and verification methods for the QDCOMR. This document lists minimum standards, but it is not intended to be exhaustive. The QDCOMR is in use on the flight deck of civil aviation aircraft and protects the flight deck crew from hypobaric hypoxia and could protect from smoke and toxic gases. The QDCOMR is distinct from the continuous flow oxygen masks. Firefighting, therapeutic, and military applications are excluded. The device can be of the oronasal type and comprises at least the following components: A facepiece, including an integrated demand regulator A flexible oxygen supply hose An attachment harness Separated or integrated goggles, or without goggles Provisions for installation Some designs may include additional components (for example, a microphone).
A-10 Aircraft Oxygen Equipment Committee
This SAE Aerospace Recommended Practice (ARP) describes a procedure for determining the insoluble contamination level of the downstream side of cleanable filter elements. The results may be used for comparative evaluation of the effectiveness of various cleaning methods or the cleanliness of elements after cleaning or as received from manufacturers.
A-6C1 Fluids and Contamination Control Committee
This SAE Standard applies to all self-propelled machines with a gross vehicle mass greater than 5000 kg that are utilized to clean material from highways, parking lots, airfield runways, outside paved areas that are principally exposed to vehicular traffic. These machines can also be involved with road construction or repaving work. Primary methods for material removal and cleaning can be by mechanical, pneumatic, washing and flushing systems, or in a combination of any system.
MTC2, Sweeper, Cleaner, and Machinery
This SAE Recommended Practice applies to fifth wheel kingpins for heavy-duty commercial trailers and semitrailers, used for off-highway operation or in hauling heavy loads (see Figure 1).
Truck and Bus Total Vehicle Steering Committee
This SAE Standard applies to the fuel consumption of non-propulsion engines used to drive exclusively the sweeping and cleaning functions of multi-engine sweepers and scrubbers as defined in SAE J2130-1 and SAE J2130-2.
MTC2, Sweeper, Cleaner, and Machinery
This SAE Standard applies to all self-propelled machines with a gross vehicle mass up to 5000 kg that are utilized to clean material from outside paved areas, parkland, floors in non-residential buildings and areas principally exposed to pedestrian traffic. Primary methods for material removal can be by mechanical, pneumatic, washing and flushing systems, or in a combination of any system.
MTC2, Sweeper, Cleaner, and Machinery
This specification covers an aluminum alloy in the form of sheet and plate 0.020 to 2.000 inches (0.51 to 50.80 mm), inclusive, in nominal thickness, supplied in the annealed (-O) condition. When specified, product shall be supplied in the “as fabricated” (-F) temper (see 8.6).
AMS D Nonferrous Alloys Committee
This specification covers an aluminum alloy in the form of sheet less than 0.250 inch (6.35 mm) thick (see 8.5).
AMS D Nonferrous Alloys Committee
This specification covers a titanium alloy in the form of bars and hand forgings up through 10.000 inches (254.00 mm), inclusive, in diameter or least distance between parallel sides and forging stock of any size. Bar over 6.000 inches (152.40 mm) in nominal thickness has a maximum cross-sectional area of 288 square inches (1858 square cm). Hand forgings with nominal thickness over 6.000 inches (152.40 mm) have a maximum cross-sectional area of 79 square inches (509 square cm) (see 8.7).
AMS G Titanium and Refractory Metals Committee
This specification defines the requirements for in-process and temporary marking material used on nickel, iron, cobalt, and titanium-based turbine engine components during processing or manufacture. Control is required as marking material may contain deleterious or low melting point elements that could negatively affect performance.
AMS F Corrosion and Heat Resistant Alloys Committee
This specification covers a titanium alloy in the form of bars, wire, and forgings up through 4.000 inches (101.60 mm), inclusive, in diameter or least distance between parallel sides and forging stock of any size (see 8.6).
AMS G Titanium and Refractory Metals Committee
In marine combustion engines, it is important to minimize fuel consumption and reduce toxic emissions. One method to achieve this is minimizing friction losses in the injection subsystem, which is why measuring them is necessary. Some friction force values in precision pairs are so high that they require specialized methods and measurement stations. This article presents innovative methods and devices for measuring high friction and high power forces between the body and the needle of injector nozzles in the presence of a lubricant. The scientific method consists of increasing the load applied to the needle pin located in the nozzle body until it is completely ejected from the body. The devices that determine the course and maximum value of the friction force utilize test benches for dynamic tensile strength testing samples, employing specially designed and manufactured holders. When the fastening of the pin holder proved insufficient due to slippage, a semicircular groove was made around the circumferential needle pin. Round balls were inserted into the pin’s innovative mounting screw holes, recessed into the circumferential groove by about half their diameter, which is an important contribution by the authors. The maximum friction force was determined from the recorded signal, depending on the displacement or time waveform. The friction force depends on the needle’s position relative to the nozzle body; therefore, it is recommended to take measurements in at least four planes and compute the average. Different friction force values are caused by errors in the roundness and concentricity of the injector nozzle body guide part relative to the needle, as well as deposit formation. This article presents the influence of the state of the friction surfaces, as determined by modern geometric measurements of the cooperating elements, including computed tomography scans and silicone casts, on the maximum friction force value and modeling.
Monieta, Jan, Komorowski, Adam
Methyl-terminated oxymethylene ethers (OMEs) have garnered significant attention as promising low-carbon alternatives to conventional petroleum-based diesel fuels. Nevertheless, their physicochemical properties frequently fail to satisfy the stringent specifications of current diesel fuel standards, which impedes their direct adoption in modern compression ignition engines. Structural modification of OMEs, particularly through the variation of terminal alkyl moieties, provides a viable strategy for tuning their properties to meet the required performance criteria. This review consolidates and critically evaluates the available literature on the physicochemical and performance characteristics of OMEs featuring diverse molecular architectures. In addition, it delineates existing knowledge gaps and identifies key areas warranting more in-depth future research. The number of published studies in this area is extremely limited, as research in this field is still essentially at an early stage; therefore, the present review has been classified as a mini-review.
Cherepanova, Anna D., Ukhanov, Denis A., Khrapov, Alexander G., Dement’ev, Konstantin I.
Traffic oscillations degrade the operational efficiency and safety of vehicular platoons. This study proposes a predecessor-following platoon with periodically assigned feedback gains and investigates its frequency-selective disturbance attenuation mechanism. An auxiliary second-order undamped periodic model is first established, and the Bloch–Floquet formulation is used to derive the nominal dispersion relation and bandgap boundaries. Closed-loop disturbance attenuation is then evaluated separately using spacing-error transfer matrices that retain positive velocity feedback and actuator-response lag. Frequency-domain transmission analysis and time-domain simulations show that, under nominal homogeneous and fully controllable connected and automated vehicle (CAV) assumptions, the periodic gain configuration creates tunable attenuation bands and provides stronger downstream attenuation than a homogeneous-gain configuration. The results clarify the relationship among periodic gain assignment, bandgap formation, periodic-cell string stability, and finite-length traffic-wave suppression. The effects of vehicle heterogeneity, sensing delay, and mixed traffic remain topics for future investigation.
Yang, Xiujian, Fan, Yanwen, Zhuang, Qingyuan, Qiao, Feiyu
Letter from the Guest Editors
Ivanov, Valentin, Gunji, Daisuke, Savitski, Dzmitry, Zhu, Yueying
In Earth-Moon low-energy transfers, the strict geometric constraints among the Sun, Earth, and Moon often complicate trajectory redesign when the original transfer window is missed. To address this issue, this paper presents a nominal-trajectory-based reconstruction method for Earth-Moon low-energy transfers. Using the original mission trajectory as the reference, the method fixes the middle arc and performs segmented reconstruction that combines position targeting with velocity matching, so that only the escape and lunar insertion phases are locally corrected. This approach enables rapid trajectory reconstruction, efficient search for feasible launch windows, and evaluation of the corresponding velocity increment. Following this strategy, the existence and distribution of feasible solutions are examined on the hour, day, month, and year timescales. Simulation results show that feasible transfer windows with relatively low cost still exist within approximately four to six hours before or after the nominal window. Once the departure time shifts by one day, the total velocity increment rises sharply, and local reconstruction is no longer engineering-feasible. After waiting for about one synodic month, feasible windows reappear, and the required velocity increment falls back within the 200 m/s threshold. Within a one-year range around the nominal epoch, the feasible windows exhibit an overall periodic pattern that repeats approximately every 27 days. The proposed method provides a reference for trajectory reconstruction after a missed transfer window.
Wang, Yuxia, Li, Xiangyu, Zhou, Xingyu, Wang, Shen
This paper addresses three main bottlenecks in commercial aerospace multimodal data: semantic alignment difficulties, rigid ontologies, and context loss. We propose a method to construct satellite multimodal knowledge graphs (KGs) using Large Language Model (LLM).The process begins with layout analysis. This step preprocesses interleaved text-image satellite documents to align cross-modal semantics. To resolve ambiguity in technical terms, we developed a triple-positioning entity extraction mechanism. This mechanism directly identifies the original text, summaries, and entity types. For event nodes, we use an event-centric modeling paradigm. This paradigm captures spatio-temporal elements and other meta informations to ensure the nodes are self-interpretable. Entity normalization and automatic schema recognition rely on deep vector embedding. This embedding can semantic clustering the entities for the KG, eliminates the need for prior ontologies. We tested the method on real satellite datasets. The experimental results show high logical integrity and confirm its practical value for aerospace failure analysis.
Chen, Yanyu, Yu, Yeluo, Zhang, Jiliang, Bao, Junpeng
With the large-scale construction of low Earth orbit (LEO) mega-constellations (such as Starlink, OneWeb, etc.) worldwide, due to the scarcity of frequency bands and the increasingly tight orbital space, the problems of mutual influence within constellations and between different constellations have become increasingly serious. To solve these problems, this paper studies a multi-level Walker-Delta layout method for LEO constellations. Based on the consideration of the relationship between time and space, a global interference calculation method is proposed. Combining orbital mechanics and the direction pattern of antennas, the interference amount generated by satellites at different orbital altitudes on ground relay stations is given. Simulations show that the interference is not the same everywhere, there are certain differences in latitude, and it also varies in time. Especially for high-latitude regions, the signal-to-interference-noise ratio will drop significantly and even fall below 5 dB; while in mid-low latitude regions, the situation is good. This has certain guiding significance for spectrum sharing coordination and anti-interference beam formation.
Zi, Xinyi, Li, Haiyang, Zhang, Jin, Li, Shengxi
Addressing the difficulties in logistics and transportation in Nujiang Prefecture’s rugged topography,where is primarily composed of high mountains and valleys. this study tackles the high expenses, the low transportation efficiency, and substantial cargo losses associated with conventional transport modes. The research adopts a dual-track approach: first, it develops integrated infrastructure frameworks and intelligent monitoring and dispatch systems; second, by conducting field research, performing cost factor analysis, constructing models, and carrying out on-site transportation verification, the research aims to optimize the end-to-end logistics efficiency of low-altitude delivery for A.tsaoko in the region. Through on-site verification, it is estimated that the low-altitude logistics of A.tsaoko in Nujiang Prefecture can save more than 30%, reduce labor hours by more than 80%, and decrease transportation losses by more than 10%.
Chen, Xiaoguang, Sun, Xiaoguang, Shu, Dan, Shi, Long, Sun, Liang, Feng, Chen, Liu, Haitao
The high-stability bracket is the primary component in remote sensing satellites responsible for carrying the camera and attitude control equipment; its dynamic behavior directly affects imaging quality and in-orbit service life. Welding-based connections introduce uncertainties during manufacturing and assembly, leading to significant discrepancies between finite element analysis results and experimental data. To quantitatively assess the impact of welding processes on the accuracy of the high-stability bracket’s finite element model(FEM), this study proposes a Bayesian parameter correction method based on Markov Chain Monte Carlo (MCMC) sampling and the Metropolis-Hastings (MH) algorithm. It employs a multilevel correction experimental framework—”material-level, component-level, and system-level”—to progressively refine material parameters and establish a high-fidelity FEM. First, the elastic modulus of the welded and non-welded regions were calculated using stress-strain curves obtained from static tensile tests on welded and non-welded plates; then, targeting the first two natural frequencies from dynamic impact tests on bar specimens, the material densities of the welded and non-welded regions were corrected using the Bayesian method; finally, the effectiveness of the correction method was verified through free vibration tests on the actual high-stability bracket. The results indicate that, compared to the undamaged region, the welded region exhibits a 13.87% loss in elastic modulus and a 55.32% loss in density. The relative errors in the first three natural frequencies of the corrected model were 0.59%, 0.01%, and 0.83%, respectively, verifying the high reliability of the proposed method in modal identification and providing a new technical approach for correcting spacecraft structural models.
Liu, Kun, Guo, Chongchong, Wu, Wenhua
Spacecraft flywheel systems are critical actuators for attitude control and stability maintenance, and their operating reliability is strongly affected by the health state of the supporting bearings. When local defects occur on the bearing raceway or rolling elements, the rolling contact state changes abruptly, which leads to time varying contact deformation, fluctuating support reaction force, and additional rotational resistance. Unlike many ground based rotating machines, spacecraft flywheel systems usually operate in compact and highly integrated configurations, where direct vibration measurement is difficult in practice. In contrast, motor current, voltage, and speed signals are easier to acquire and are therefore more suitable for condition monitoring. To describe how bearing defects propagate from the mechanical domain to electrical responses, a simplified electromechanical coupling model is developed for a flywheel rotor motor system with local bearing defects. First, a rolling element contact model is established using the defect induced deformation relation and Hertzian contact theory to derive the time varying bearing support force. Second, the fluctuating support force is mapped to an equivalent time varying load torque to represent the dominant pathway through which bearing defects influence the motor side. Third, the derived load torque disturbance is coupled with the transverse rotor dynamic equations, the rotational motion equation, and the motor dq axis model to obtain a simplified electromechanical coupling equation set. The proposed model preserves the main physical transmission chain from bearing defect to electrical response. The model provides a clear theoretical basis for analyzing fault propagation mechanisms and for developing current based diagnostic methods for spacecraft flywheel systems.
Wu, Haolong, Li, Yuqing
Large-scale satellite constellation on-orbit missions are characterized by multiple objectives, multiple constraints, and strong dynamism. Traditional ground control and management modes have become difficult to meet the requirements for autonomous real-time decision-making by satellites. This paper addresses the need for autonomous and rapid decision-making capabilities on-board satellites, and proposes a satellite autonomous task planning and decision-making method based on an attention pointer network, addressing issues such as limited on-orbit computing resources and insufficient generalization of planning methods. Firstly, by analyzing and mathematically describing the characteristics and constraints of satellite tasks, a Markov model for satellite autonomous task planning problems is constructed. Secondly, the pointer network is combined with a reinforcement learning framework, and an attention mechanism is introduced to perform probabilistic learning on the execution selection of satellite tasks, generating an optimized sequence of satellite task planning results. Finally, simulation experiments show that after training, this method exhibits certain generalization capabilities and significantly superior computational efficiency compared to traditional intelligent optimization algorithms such as genetic algorithms. It can adapt to the single-satellite autonomous dynamic planning requirements under large-scale constellation control and management, providing technical support for autonomous operation and online intelligent task planning of satellites in orbit.
Feng, Xiaoen, Li, Yuqing, Qiu, Jianbin, Li, Meicheng