Aerospace Systems最新文献

{"title":"Constraint-driven design methodology of super pressure balloons for planetary exploration","authors":"K. M. Kiran Babu,&nbsp;Rajkumar S. Pant","doi":"10.1007/s42401-026-00521-x","DOIUrl":"10.1007/s42401-026-00521-x","url":null,"abstract":"<div><p>Super Pressure Balloons (SPBs) for atmospheric exploration of planetary bodies offer a unique capability for long-duration in-situ studies. The design requirements that drive the trade-off between the SPB diameter and film thickness are Float Altitude (FA) in m, Launch Altitude (LA) in m, Rate of Ascent/Descent (<span>(mathbf {V_z})</span>) in m/s, and Payload-System Mass Ratio (PSMR). This paper discusses a novel Constraint-Driven design methodology specifically tailored for planetary SPBs. The methodology integrates an iterative sizing procedure with a comprehensive constraint analysis to systematically generate feasible design points that satisfy the mission requirements. The approach was successfully applied to develop preliminary design parameters for atmospheric exploration missions to Venus, Mars, and Titan, confirming the engineering feasibility for all three targets. Furthermore, the design methodology is validated against historical data from the VEGA Balloon missions on Venus. For Mars and Titan, the methodology is benchmarked against conceptual studies from established literature.</p></div>","PeriodicalId":36309,"journal":{"name":"Aerospace Systems","volume":"9 3","pages":"521 - 537"},"PeriodicalIF":0.0,"publicationDate":"2026-08-05","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"148871676","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

{"title":"Dry friction dampers for gravity-stabilized satellites","authors":"Anton V. Doroshin","doi":"10.1007/s42401-026-00473-2","DOIUrl":"10.1007/s42401-026-00473-2","url":null,"abstract":"<div><p>This paper investigates the feasibility of employing dry friction dampers for the attitude dynamics of microsatellites and nanosatellites during gravity-gradient stabilization in circular orbits. In this configuration, the gravitational dampers consist of rigid bodies with general inertia tensors, placed inside spherical capsules that rotate with dry friction within external rings fixed to the satellite’s main body. This rotational motion dissipates kinetic energy and angular momentum associated with attitude motion in the gravitational field; consequently, under the influence of central gravity forces, the satellite proceeds to a stable attitude position along its orbit. Classical gravitational dampers for satellites typically employ rigid bodies with spherical inertia tensors rotating within cavities filled with viscous liquids. The dry friction-based gravitational damper proposed in this paper offers several practical advantages. Specifically, it becomes preferable when the damper's rigid body can also serve as a functional component of the satellite, and when hermetic sealing of the spherical capsule is unnecessary. These advantages enable the use of such dry friction dampers in microsatellites and nanosatellites as simple passive actuators for attitude stabilization and control, while simultaneously fulfilling their own function as satellite components. Mechanical and mathematical models are developed, and corresponding simulation results are obtained to demonstrate the dynamics of satellites equipped with dry friction dampers during gravity-gradient stabilization.</p></div>","PeriodicalId":36309,"journal":{"name":"Aerospace Systems","volume":"9 3","pages":"621 - 637"},"PeriodicalIF":0.0,"publicationDate":"2026-07-31","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"148871601","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

{"title":"T2MC: timed and compositional task-to-motion-to-control for space robotic operations with executable motion references and phase-aligned tracking","authors":"Hongji Zhuang,&nbsp;Qiang Shen,&nbsp;Shufan Wu,&nbsp;Vladimir Yu. Razoumny,&nbsp;Yury N. Razoumny","doi":"10.1007/s42401-026-00520-y","DOIUrl":"10.1007/s42401-026-00520-y","url":null,"abstract":"<div><p>Space robotic operations increasingly require long-horizon execution of timed, multi-stage tasks rather than isolated pre-scripted maneuvers. However, closed-loop deployment of generated references remains challenging because temporal structure is often implicit, local artifacts may reduce executability, and retimed execution can induce cumulative phase drift. This paper proposes Task-to-Motion-to-Control (T2MC), a unified framework for timed task-stream reference synthesis and retiming-robust tracking. A timed task stream specifies primitive identity, commanded duration, and optional tempo modulation, enabling reproducible task construction and direct evaluation of duration and boundary fidelity. The streamed generative backend combines a structured-prior variational autoencoder with conditional latent diffusion for stable segment-wise synthesis with bounded per-segment cost. A lightweight Contact-Preserving Correction projection is applied consistently during training and inference to improve reference executability while avoiding train–test mismatch. A plug-in online phase-alignment module further corrects reference indexing during execution, improving robustness to non-uniform retiming without retraining the tracker. Experiments on a physics-based robotic tracking benchmark demonstrate that T2MC improves timed-task fidelity, reference executability, closed-loop robustness, and execution fidelity under retimed execution. These results show that the proposed framework effectively supports long-horizon, space-operation-motivated robotic execution by jointly addressing explicit timing, executable reference synthesis, and robust online synchronization.\u0000</p></div>","PeriodicalId":36309,"journal":{"name":"Aerospace Systems","volume":"9 3","pages":"539 - 553"},"PeriodicalIF":0.0,"publicationDate":"2026-07-29","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"148871494","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

{"title":"Theoretical prediction of dynamic loads on the upper stage structure during the longitudinal instability of a multi-stage launch vehicle","authors":"Olexiy Nikolayev,&nbsp;Inna Bashlii,&nbsp;Sergey Dolgopolov,&nbsp;Nataliia Khoriak","doi":"10.1007/s42401-026-00507-9","DOIUrl":"10.1007/s42401-026-00507-9","url":null,"abstract":"<div><p>This paper presents a novel nonlinear method for the theoretical prediction of Pogo dynamic loads on a multi-stage launch vehicle, with emphasis on the structural response of complex upper-stage configuration. The methodology is based on nonlinear mathematical modeling of the dynamic interaction between the liquid-propulsion system and the rocket structure. The model accounts for the non-stationarity of dynamic processes in vehicle systems, nonlinearities arising from cavitation phenomena in the main engine pumps, and the amplitude-dependent damping of rocket structure vibrations. A detailed finite element approach is employed to capture the specific features of the upper stage’s spatial layout. The proposed method was applied to predict Pogo dynamic loads for a three-stage liquid launch vehicle equipped with a new sphero-conical upper stage under flight conditions. The results indicate that the predicted Pogo acceleration amplitudes at the upper-stage mounting interface exceed the flight oscillations of a two-stage prototype: reaching 0.4 <i>g</i> during the first interval of Pogo instability and 0.5 <i>g</i> during the second.</p></div>","PeriodicalId":36309,"journal":{"name":"Aerospace Systems","volume":"9 3","pages":"675 - 692"},"PeriodicalIF":0.0,"publicationDate":"2026-06-29","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"148871501","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

{"title":"A novelty-driven hybrid CNN+NN model for remaining useful life prediction of satellite battery","authors":"Ahmed Adam,&nbsp;Ahmed Mokhtar,&nbsp;Mohamed Abdrahman,&nbsp;Sherif Helmy","doi":"10.1007/s42401-026-00491-0","DOIUrl":"10.1007/s42401-026-00491-0","url":null,"abstract":"<div><p>An accurate estimation of the Remaining Useful Life (RUL) is crucial for ensuring operational safety and mission success. This study proposes a hybrid deep learning approach that combines Convolutional Neural Networks (CNN) and Neural Networks (NN) to predict the RUL of batteries. The model was trained and evaluated on a telemetry dataset across two years of satellite operation of a nickel–hydrogen (NiH<span>(_2)</span>) battery, including various operational modes (charging, discharging, and idle). The proposed CNN+NN framework was benchmarked against several standalone models, including XGBoost, Support Vector Regression (SVR), CNN, NN, and Long Short-Term Memory (LSTM), as well as hybrid LSTM-based combinations (LSTM+CNN, LSTM+NN, and LSTM+XGBoost). The hybrid CNN+NN model consistently outperformed the comparative approaches in terms of predictive accuracy and stability. To further evaluate generalization capability, the model was validated on an additional NiH<span>(_2)</span> battery from the same mission and subsequently tested on the NASA lithium-ion battery dataset (B0005, B0006, B0007, and B0018). Moreover, a combined dataset evaluation using Leave-One-Battery-Out (LOBO) cross-validation was conducted to assess robustness across batteries. The proposed approach achieved competitive MAE and strong <span>(R^2)</span> values across both nickel–hydrogen and lithium-ion datasets, demonstrating reliable cross-chemistry generalization and stable forecasting performance. This study highlights CNN+NN as a promising contribution to space battery prognostics, enabling reliable RUL estimation for LEO remote sensing satellites.</p></div>","PeriodicalId":36309,"journal":{"name":"Aerospace Systems","volume":"9 3","pages":"585 - 606"},"PeriodicalIF":0.0,"publicationDate":"2026-06-16","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"148871592","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

{"title":"Missile roll and acceleration autopilot design based on linear active disturbance rejection control","authors":"Rizal Maulani,&nbsp;Zulkifli Hidayat,&nbsp;Abdullah Alkaff","doi":"10.1007/s42401-026-00488-9","DOIUrl":"10.1007/s42401-026-00488-9","url":null,"abstract":"<div><p>In this paper, a linear active disturbance rejection controller is proposed for roll and acceleration autopilot control of nonlinear missile systems to address the presence of disturbances due to unknown system parameters. The controller design uses the linearized roll and normal acceleration models of a six-degree-of-freedom missile model. The linear extended state observer is then applied to the linearized model to estimate and compensate for the disturbances. In the roll channel, a second-order controller is applied to stabilize the roll and decouple the pitch and yaw channels. A double-loop acceleration controller is applied to the pitch and yaw channels. Several comparative simulations demonstrate the effectiveness of the proposed method. The simulation results showed that the proposed controller exhibits better control performance in both simple and extreme maneuvers while requiring fewer system parameters.</p></div>","PeriodicalId":36309,"journal":{"name":"Aerospace Systems","volume":"9 2","pages":"439 - 452"},"PeriodicalIF":0.0,"publicationDate":"2026-05-18","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"148261872","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

{"title":"Jackknife ARAIM: Efficient GNSS Integrity Monitoring for Simultaneous Faults under Non-Gaussian Errors","authors":"Penggao Yan,&nbsp;Ronghe Jin,&nbsp;Junyi Zhang,&nbsp;Cheng-Wei Wang,&nbsp;Li-Ta Hsu","doi":"10.1007/s42401-026-00457-2","DOIUrl":"10.1007/s42401-026-00457-2","url":null,"abstract":"<div><p>Global navigation satellite systems (GNSS) require strict integrity monitoring for aviation safety, where legacy and advanced receiver autonomous integrity monitoring (RAIM/ARAIM) rely on Gaussian error models that can be overly conservative for real-world non-Gaussian errors. This paper proposes an extended jackknife detector capable of detecting multiple simultaneous faults with non-Gaussian nominal errors. The proposed detector adopts a hybrid monitoring strategy: scalar jackknife residual tests for single-fault modes and triple-axis (East/North/Up) tests for multi-fault modes. Furthermore, an integrity monitoring algorithm, jackknife ARAIM, is developed by systematically exploiting the properties of the jackknife detector in the range domain. We prove that the proposed method has equivalent monitoring performance with the solution separation (SS) ARAIM, but is significantly computationally efficient for single-fault cases with non-Gaussian nominal errors, while maintaining similar efficiency to SS ARAIM for multiple-fault cases. The proposed method is examined in worldwide simulations, with the nominal measurement error simulated based on authentic experimental data, which reveals different findings in existing research. In a single Global Positioning System (GPS) constellation setting, the proposed method can reduce the 99.5 percentile vertical protection level (VPL) below 45 m, outperforming 50 m VPL produced by the ARAIM algorithm using Gaussian nominal error models. In GPS-Galileo dual-constellation setting, while these Gaussian-based ARAIM algorithms suffer VPL inflation over 60 m due to Galileo’s heavy-tailed errors, the proposed method maintains VPL below 40 m, achieving over 92 % normal operations for 35 m Vertical Alert Limit. Moreover, we tentatively implement the SS ARAIM using non-Gaussian overbounds and compare it with the proposed Jackknife ARAIM method regarding computation efficiency. The proposed method achieves up to 59.4 % reduction in median processing time compared to SS ARAIM in single-constellation scenarios. In dual-constellation scenarios, where multiple-fault cases are more prevalent, both algorithms exhibit similar computational efficiency. These improvements enable potential support for localizer performance with vertical guidance (LPV) with a decision height of 200 ft, enhancing integrity and computation efficiency for multi-constellation GNSS applications.</p></div>","PeriodicalId":36309,"journal":{"name":"Aerospace Systems","volume":"9 2","pages":"413 - 437"},"PeriodicalIF":0.0,"publicationDate":"2026-05-12","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"https://link.springer.com/content/pdf/10.1007/s42401-026-00457-2.pdf","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"148261855","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"OA","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

{"title":"Null-space control allocation for generalized load reduction in eVTOL aircraft","authors":"Jiannan Zhang,&nbsp;Zhidong Lu,&nbsp;Florian Holzapfel","doi":"10.1007/s42401-026-00483-0","DOIUrl":"10.1007/s42401-026-00483-0","url":null,"abstract":"<div><p>Electric Vertical Takeoff and Landing (eVTOL) aircraft rely on distributed electric propulsion systems to generate lift and control forces during low-speed flight. Under external disturbances or internal faults, some rotors may experience disproportionately high loads, leading to thermal stress and long-term reliability degradation. To mitigate such risks, this paper proposes a control allocation method guided by Lyapunov stability theory that minimizes a generalized <i>p</i>-norm of the control load. By exploiting the null space of the control effectiveness matrix, the proposed method asymptotically reduces either overall or peak control load without altering the achieved virtual control. This null-space update supports both conventional and incremental control allocation architectures. In contrast to optimization-based approaches that require solving constrained problems online, the proposed null-space update is lightweight and well-suited for safety-critical flight control systems. Simulation results on a high-fidelity lift-plus-cruise eVTOL platform demonstrate the effectiveness of the method in reducing both overall and peak rotor loads, even in the presence of rotor failures.</p></div>","PeriodicalId":36309,"journal":{"name":"Aerospace Systems","volume":"9 2","pages":"397 - 411"},"PeriodicalIF":0.0,"publicationDate":"2026-05-08","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"https://link.springer.com/content/pdf/10.1007/s42401-026-00483-0.pdf","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"148261891","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"OA","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

{"title":"Reliability-driven DC-link optimization for fault-tolerant 3L T-type eVTOL propulsion inverters","authors":"Niklas Krug,&nbsp;Marek Galek,&nbsp;Florian Holzapfel","doi":"10.1007/s42401-026-00477-y","DOIUrl":"10.1007/s42401-026-00477-y","url":null,"abstract":"<div><p>This article proposes a mission-profile-based sizing methodology for DC-link capacitors in eVTOL propulsion inverters. While DC-link capacitors contribute significantly to converter volume, traditional design relies on conservative worst-case operating points, leading to significant oversizing. To address this, an electro-thermal modelling approach is developed to evaluate capacitor lifetime based on core temperature fluctuations throughout a dynamic flight profile. The methodology accounts for thermal properties, modulation strategies, and the effects of fault-tolerant operation. Although the method is applicable to various inverter topologies and capacitor technologies, the three-level T-type (3L-TT) fault-tolerant converter benefits most, as demonstrated by an exemplary design achieving a 37.5% reduction in DC-link volume compared to conventional methods while for a specified life-time goal.</p></div>","PeriodicalId":36309,"journal":{"name":"Aerospace Systems","volume":"9 2","pages":"383 - 395"},"PeriodicalIF":0.0,"publicationDate":"2026-04-28","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"https://link.springer.com/content/pdf/10.1007/s42401-026-00477-y.pdf","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"148261782","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"OA","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

{"title":"Intelligent fault detection of UAV propellers through time-domain vibration analysis and ensemble learning","authors":"Karam J. Mohammed,&nbsp;Ahmed Ali Farhan Ogaili,&nbsp;Abdul-Rasool Kareem Jweri,&nbsp;Alaa Abdulhady Jaber,&nbsp;Luttfi A. Al-Haddad","doi":"10.1007/s42401-026-00460-7","DOIUrl":"10.1007/s42401-026-00460-7","url":null,"abstract":"<div><p>The structural integrity of the propellers is a prime factor in UAV flight safety, but reliable real-time fault detection is problematic on resource-constrained hardware. In this effort, a lightweight diagnostic framework is developed that is capable of identifying edge cuts, cracks, and surface cuts using only standard onboard IMU data. The vibration signature from five flight trajectories in the DronePropA dataset was employed to carry out the analysis. Since onboard processing latency is a key issue, computationally intensive deep learning architectures are avoided. A 180-dimensional feature vector is created by extracting 30 statistical time-domain descriptors from the dual-IMU system. Validation using a Leave-One-Trajectory-Out protocol show that the proposed stacked ensemble classifier results in an accuracy of 97.9% and a macro-F1 score of 0.978. Interestingly, the whole system has an average inference time of 2.1 ms, which proves that we can use it for real-time edge computing on common CF flight controllers.</p></div>","PeriodicalId":36309,"journal":{"name":"Aerospace Systems","volume":"9 2","pages":"365 - 381"},"PeriodicalIF":0.0,"publicationDate":"2026-04-17","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"148261860","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}