Jul 2026· Aeronautical Journal· pp. 1-31· 0 citations· 13 references
Abstract
Small fixed-wing unmanned air vehicles (UAVs) weighting under 20 kg are typically not protected against icing. Yet, commercial and military users find interest in operating this class of platform under cold climates where encounters with icing conditions are likely. This paper introduces a new concept named sense-and-egress that aims at safeguarding small UAVs in case of an inadvertent icing encounter. A short overview of the system’s operating principles and a plausible architecture candidate are given. Then, the benefits and drawbacks of the proposed solution are assessed with respect to both unprotected (no ice detection or deicing devices active) and fully ice-protected vehicles. Enabling technologies and knowledge gaps are briefly explored in order to gauge the maturity of the concept. The non-linear flight dynamics model of an existing UAV is built up using results from numerical aerodynamics software. The model is then improved and validated using system identification from existing flight test data. A bespoke path-following autopilot is designed to control the UAV during the escape manoeuvre. The selected control system structure and the tuning procedures for both the attitude controller and the total energy control system are detailed. The ability of the baseline autopilot to perform a simple egress manoeuvre with both clean and iced airframes is assessed in simulation. Simple yet effective solutions are implemented to improve the autopilot performance in icing while preserving its gust resistance capabilities.
Today (mid-2026) UASs are a mature technology, quickly expanding, with two distinct tracks: a civil/commercial ecosystem that is moving from hobbyist and line-of-sight ops toward scaled commercial BVLOS and logistics, and an advanced industrial ecosystem that is rapidly adopting increasingly autonomous, networked, and innovative drone types (from tactical ISR to loitering, delivery, and swarm concepts). Regulators (FAA, EASA, and national authorities) are actively updating rules to enable safe BVLOS and integrated operations; at the same time, demand for counter-UAS capabilities is surging. This study presents an extensive review of UAV technologies, outlining their applications in both civilian and industrial domains. It further analyzes principal use cases alongside the related technical and operational challenges. Moreover, prospective research directions are proposed with the aim of advancing the technology framework. The insights provided are intended to offer meaningful guidance and inspiration for researchers in this area. The paper also emphasizes the existing framework while discussing potential future developments.
Atmospheric icing is one of the most critical meteorological hazards for unmanned aerial vehicles (UAV), whose operation under adverse conditions—high latitudes, elevated altitudes, long-endurance missions without pilot intervention—particularly exposes them to ice accumulation on aerodynamic surfaces and propellers. Unlike manned aviation, where this phenomenon has been extensively studied and regulated, a significant knowledge gap exists in the UAV domain that limits the development of effective protection systems adapted to energy constraints. This article provides an integrative review—conducted with a systematic search strategy following PRISMA reporting guidelines—of atmospheric ice formation mechanisms, their specific effects on UAV propellers, and the two most promising mitigation approaches: electrothermal modelling for the optimisation of electric heating systems and the development of functional surface materials including superhydrophobic coatings (SHC); composites with conductive nanofillers (graphene, carbon nanotubes); and piezoelectric actuators. The analysis demonstrates that hybrid systems combining passive and active strategies managed by intelligent control represent the most viable solution for extending UAV operational envelopes under known icing conditions, with a projected reduction in anti-icing system energy consumption of at least 40% relative to conventional continuous heating. This estimate is based on the most conservative published evidence: pulsed electrothermal de-icing achieves 40–60% savings versus continuous anti-icingSHC-assisted hybrid heating reduces IPS power by more than 80% on static aerofoils; and rotary-wing pulsed systems reduce mean consumption by 60–75% relative to continuous operation. Key research gaps are identified, and a prioritised future research agenda is proposed to support the development of certifiable anti-icing systems for rotary-wing UAV platforms.
R. Avella, Camila A. González, Paula N. López· Drones· 0 citations
This paper presents the design, aerodynamic analysis, manufacturing, and energy feasibility assessment of DELICE 1A, a 5 m-wingspan solar-electric unmanned aerial vehicle (UAV) developed as a technology demonstrator toward high-altitude pseudo-satellite (HAPS) operation. The MO6070 airfoil is evaluated using XFLR5 batch analysis and ANSYS Fluent CFD at Reynolds numbers between 100,000 and 500,000, yielding L/D = 19.7 at the design cruise point. Propulsion performance is characterised at sea-level conditions, giving a required power of 89.25W at 14.9ms−1. A sinusoidal irradiance model calibrated for the summer solstice at Ankara (Tday = 14.84 h, Imax = 945Wm−2) is used to evaluate two solar coverage scenarios. In Scenario A, 80 SunPower C60 cells on the main wing (A = 1.20m2) extend endurance from 4.06 h to 5.94 h, a 46.2% gain. In Scenario B, 180 cells covering the main wing and horizontal tail (A = 2.70m2) reduce the irradiance threshold to 248Wm−2 and yield 4.58 h endurance. These findings showcases that not only panel area is the critical constraint for perpetual flight at this scale, but higher battery energy density and more efficient solar cells, and lighter structures should also be provided. These findingd establishes quantitative energy targets for the next design iteration on DELİCE-2.
S¸ Akg¨un, M. Acar, Y. E. Acar et al.· Journal of Physics, Conferen...· 0 citations
Unmanned Air Vehicles (UAVs) are becoming increasingly popular and widely used in a variety of industries such as agriculture, construction, delivery, surveillance, rescue operations, mapping, wildlife tracking and many more. With the advancements in technology, UAVs are becoming more autonomous and able to perform tasks with minimal human intervention, rendering their use indispensable for military and law enforcement purposes. In terms of control surfaces, V-tail configurations are commonly used on UAVs due to their advantages in control and stability performance, as well as their ability to reduce drag and improve overall efficiency. However, research on V-tail design and sizing is limited, particularly for Class I mini-UAVs. The objective of this paper is to identify a methodology for the Conceptual and Preliminary sizing and design of a V-tail of a Class I Mini UAV (NATO classification). The methodology follows the design of a V-tail from the characteristics of the conventional tail of the UAV. Once the characteristics of the conventional tail are extracted, V-tail geometric characteristics are computed. The stability derivatives of the V-tail are then calculated. The methodology for the analytical aerodynamic characteristics and stability derivatives is a combination of two existing methodologies: one methodology for V-tail stability and control derivatives, which refers to the Preliminary or Detailed Design of an aircraft, and one methodology for a conventional tail design, which refers to the Conceptual and Preliminary design of an aircraft. With this combination, a V-tail Preliminary design methodology was achieved. Furthermore, the aerodynamic characteristics and stability derivatives of the designed V-tail were verified by Low Fidelity Aerodynamics simulation, and then by High Fidelity Aerodynamics by means of Computational Fluid Dynamics (CFD).
Eleftherios Nikolaou, S. Kilimtzidis, V. Lappas et al.· Aerospace· 0 citations
This paper examines the current applications and emerging development trends of
unmanned aerial vehicles (UAVs), with emphasis on the technological and operational evolution
of contemporary drone systems across civil and military domains. The study reviews the
expanding use of UAVs in precision agriculture, infrastructure inspection, logistics, emergency
response, urban air mobility, intelligence, surveillance and reconnaissance (ISR), electronic
warfare and tactical operations, highlighting the operational advantages offered by unmanned
platforms in diverse mission environments.
The principal challenges affecting future UAV deployment are also analyzed, including
battery endurance, cybersecurity, communication reliability, regulatory compliance, airspace
integration and environmental constraints. Attention is given also to the increasing role of
artificial intelligence, autonomous mission execution, swarm coordination, advanced propulsion
technologies and digital airspace management in shaping the next generation of unmanned
aircraft systems.
Current research directions indicate a transition from individually operated drones toward
interconnected, intelligent and highly autonomous aerial systems capable of cooperative decision-
making and large-scale deployment. The analysis shows that future progress in unmanned
aviation will depend not only on improvements in aircraft performance but also on advances in
systems integration, secure communications, resilient autonomy and regulatory frameworks that
enable the safe and efficient operation of increasingly complex UAV ecosystems.
Andrei Bencze· SCIENTIFIC RESEARCH AND EDUC...· 0 citations
In order to improve the crashworthiness of UAVs, this paper improves and designs a wheeled UAV structure from a traditional quadrotor platform, focusing on its drop impact response characteristics. Aiming at the drop impacts that wheeled UAVs may face during flight and landing, this paper systematically investigates the structural response of UAVs under different drop conditions based on the display dynamics theory. By establishing a refined finite element model containing a tyre cushioning system and using ANSYS/LS-DYNA finite element simulation, the maximum equivalent force distribution law with or without wheels, at different drop heights and multi-angle attitudes, is analysed. The simulation results show that the presence of wheels significantly changes the drop impact stress transfer path and reduces the risk of damage to critical parts of the fuselage. This study provides a theoretical basis and engineering guidance for the impact resistance design of wheeled UAVs.
Huanye Huang, Hui Shi, Ning Xu et al.· SAE technical paper series· 0 citations
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