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Actuators
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Aerospace Mechanisms and Actuation—Second Edition
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Aerospace Mechanisms and Actuation—Second Edition

A special issue of Actuators (ISSN 2076-0825). This special issue belongs to the section "Aerospace Actuators".

Deadline for manuscript submissions: 31 August 2025 | Viewed by 4517

Special Issue Editor

Dr. Ignazio Dimino

E-Mail Website
Guest Editor
Strategic Planning and Institutional Relations, CIRA, The Italian Aerospace Research Centre, 81043 Capua, CE, Italy
Interests: morphing technology; smart structures; active control; topology optimization
Special Issues, Collections and Topics in MDPI journals

Special Issue Information

Dear Colleagues,

After a successful first edition, this Special Issue on “Aerospace Mechanisms and Actuation—Second Edition” is dedicated to moveable mechanical assemblies and actuation architectures for both aeronautic and space applications under different configurations and categories. This platform focuses on various applications of both rigid-body linkages and compliant mechanisms in aerospace, where high reliability, accuracy, and demanding performance are addressed by a multidisciplinary and multi-objective design process. They range from aircraft morphing wing devices, such as morphing flaps and winglets, to adaptive structures that include deployable space systems, reconfigurable reflectors, and atmospheric re-entry vehicles. The focus is also given to the evolution of actuation in aerospace, ranging from conventional hydraulic to electromechanical actuators and related control systems.

This Special Issue will publish original research articles and review articles submitted by academics in a wide range of professions, including researchers, academicians, and industry experts.

Dr. Ignazio Dimino
Guest Editor

Manuscript Submission Information

Manuscripts should be submitted online at www.mdpi.com by registering and logging in to this website. Once you are registered, click here to go to the submission form. Manuscripts can be submitted until the deadline. All submissions that pass pre-check are peer-reviewed. Accepted papers will be published continuously in the journal (as soon as accepted) and will be listed together on the special issue website. Research articles, review articles as well as short communications are invited. For planned papers, a title and short abstract (about 100 words) can be sent to the Editorial Office for announcement on this website.

Submitted manuscripts should not have been published previously, nor be under consideration for publication elsewhere (except conference proceedings papers). All manuscripts are thoroughly refereed through a single-blind peer-review process. A guide for authors and other relevant information for submission of manuscripts is available on the Instructions for Authors page. Actuators is an international peer-reviewed open access monthly journal published by MDPI.

Please visit the Instructions for Authors page before submitting a manuscript. The Article Processing Charge (APC) for publication in this open access journal is 2400 CHF (Swiss Francs). Submitted papers should be well formatted and use good English. Authors may use MDPI's English editing service prior to publication or during author revisions.

Keywords

  • rigid-body mechanisms for aerospace
  • compliant mechanisms for aerospace
  • centralized and distributed actuation architectures
  • conventional actuators (mechanically signaled and hydraulically supplied)
  • EMA and full electrical actuation
  • mechanism design and optimization
  • multibody simulations
  • non-linear mechanics
  • manufacturing, integration, and maintenance
  • safety and reliability
  • high-lift devices and other aerospace applications

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Further information on MDPI's Special Issue policies can be found here.

Related Special Issue

Published Papers (4 papers)

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Research

19 pages, 2550 KiB  
Article
Analytical Modeling of Shrouded Rotors in Hover with Experimental and Computational Validation
by Abdallah Dayhoum, Alejandro Ramirez-Serrano and Robert J. Martinuzzi
Actuators 2025, 14(3), 138; https://doi.org/10.3390/act14030138 - 11 Mar 2025
Cited by 1 | Viewed by 693
Abstract
Rotors have been utilized for aircraft propulsion since the dawn of aviation, but their performance can degrade significantly if not properly designed. This study focuses on developing an accurate design tool and model validation for shrouded rotors. An experimental test rig was designed [...] Read more.
Rotors have been utilized for aircraft propulsion since the dawn of aviation, but their performance can degrade significantly if not properly designed. This study focuses on developing an accurate design tool and model validation for shrouded rotors. An experimental test rig was designed and manufactured to measure the rotor thrust and total thrust separately as well as the rotor torque. A key aspect was to account for the impact of a test rig on experimental results using computational simulations for the shrouded rotor configuration with and without the test rig. The findings indicate that the effects of the test rig were minimal and could be neglected, ensuring the validity of the experimental data compared to the analytical model. The analytical model employs a hybrid approach combining blade element momentum theory (BEMT) and the sphere-cap model which are used in conjunction with the shrouded rotor inflow ratio, as well as post-stall and tip gap clearance models. BEMT is used to calculate rotor performance, while the sphere-cap model addresses the aerodynamic influence of the shroud. The results demonstrate that the analytical model predicts shrouded rotor performance with considerable accuracy, addressing both the rotor dynamics and the shroud’s contribution to performance. Full article
(This article belongs to the Special Issue Aerospace Mechanisms and Actuation—Second Edition)
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25 pages, 4799 KiB  
Article
Optimized Structural Design of a Reciprocating Wing for the Reciprocating Airfoil (RA)-Driven Vertical Take-Off and Landing (VTOL) Aircraft
by Johnson Imumbhon Okoduwa, Osezua Obehi Ibhadode and Yiding Cao
Actuators 2025, 14(3), 104; https://doi.org/10.3390/act14030104 - 20 Feb 2025
Viewed by 783
Abstract
The development of unconventional and hybrid unoccupied aerial vehicles (UAVs) has gained significant momentum in recent years, with many designs utilizing small fans or rotary blades for vertical take-off and landing (VTOL). However, these systems often inherit the limitations of traditional helicopter rotors, [...] Read more.
The development of unconventional and hybrid unoccupied aerial vehicles (UAVs) has gained significant momentum in recent years, with many designs utilizing small fans or rotary blades for vertical take-off and landing (VTOL). However, these systems often inherit the limitations of traditional helicopter rotors, including susceptibility to aerodynamic inefficiencies and mechanical issues. Additionally, achieving a seamless transition from VTOL to fixed-wing flight mode remains a significant challenge for hybrid UAVs. A novel approach is the reciprocating airfoil (RA) or reciprocating wing (RW) VTOL aircraft, which employs a fixed-wing configuration driven by a reciprocating mechanism to generate lift. The RA wing is uniquely designed to mimic a fixed-wing while leveraging its reciprocating motion for efficient lift production and a smooth transition between VTOL and forward flight. Despite its advantages, the RA wing endures substantial stress due to the high inertial forces involved in its operation. This study presents an optimized structural design of the RA wing through wing topology optimization and finite element analysis (FEA) to enhance its load-bearing capacity and stress performance. A comparative analysis with existing RA wing configurations at maximum operating velocities highlights significant improvements in the safety margin, failure criteria, and overall stress distribution. The key results of this study show an 80.4% reduction in deformation, a 43.8% reduction in stress, and a 78% improvement in safety margin. The results underscore the RA wing’s potential as an effective and structurally stable lift mechanism for RA-driven VTOL aircraft, demonstrating its capability to enhance the performance and reliability of next-generation UAVs. Full article
(This article belongs to the Special Issue Aerospace Mechanisms and Actuation—Second Edition)
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17 pages, 3062 KiB  
Article
A Hinge Moment Alleviation Control Strategy for Morphing Tail Aircraft Based on a Data-Driven Method
by Rui Cao and Huitao Lyu
Actuators 2024, 13(9), 369; https://doi.org/10.3390/act13090369 - 19 Sep 2024
Viewed by 1201
Abstract
Morphing airplane technology is currently a focal point of research. For morphing airplanes, besides effective morphing strategies and control schemes, the hinge moment at the root of the vertical tail during morphing is a critical factor influencing flight safety. To prevent failure in [...] Read more.
Morphing airplane technology is currently a focal point of research. For morphing airplanes, besides effective morphing strategies and control schemes, the hinge moment at the root of the vertical tail during morphing is a critical factor influencing flight safety. To prevent failure in tail morphing due to excessive hinge moments, this paper analyzes the hinge moment characteristics of the variable vertical tail structure in high-speed flight, based on a flying wing model from the China Aerodynamics Research and Development Center. The proposed adaptive morphing tail hinge moment reduction (AMTHR) method is model-free, utilizing real-time data to dynamically adjust the rudder and reduce hinge moments without requiring prior knowledge of system dynamics. This method utilizes the concept of extremum-seeking control by introducing periodic perturbations to the system and adjusting the control input based on their impact on the output. This approach drives the output toward an extremum point, enabling real-time reduction of the vertical tail hinge moment. Finally, the simulation analysis is carried out under the conditions of no wind and gust disturbance, and the effect of this method on the load reduction of the tail hinge moment is verified. Full article
(This article belongs to the Special Issue Aerospace Mechanisms and Actuation—Second Edition)
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21 pages, 4897 KiB  
Article
Research on Spatial Developable Mechanism Considering Revolute Clearance Joints with Irregular Rough Surfaces
by Junyu Wang, Huibo Zhang, Wenyu Wang, Chaoqun Qi, Jianan Xu, Yang Zhao, Chao Ma and Jian Tian
Actuators 2024, 13(7), 274; https://doi.org/10.3390/act13070274 - 21 Jul 2024
Viewed by 1228
Abstract
Due to assembling, manufacturing errors, and wear, irregular rough surfaces inevitably exist in joints, which will increase the contact stiffness nonlinearity at the joint of the spatial developable mechanism, and the traditional contact force model is difficult to accurately predict the contact force [...] Read more.
Due to assembling, manufacturing errors, and wear, irregular rough surfaces inevitably exist in joints, which will increase the contact stiffness nonlinearity at the joint of the spatial developable mechanism, and the traditional contact force model is difficult to accurately predict the contact force change of irregular rough surface clearance. Aiming at the difficulty of accurately predicting the dynamic behavior of the spatial developable mechanism caused by rough joint clearance, an improved clearance contact force modeling method based on an uncoordinated contact model is proposed in this paper. The influence of rough peak distribution on the contact area is analyzed. The stiffness of the traditional Hertz model is modified based on the probability distribution density function of the rough peak, and an improved contact force model based on dynamic contact stiffness is established. Based on the Lagrange multiplier method, the dynamics model of spatial developable mechanism is constructed. Based on the model, the dynamic analysis of the spatial expansion mechanism is carried out, and the influence of the roughness of the contact surface and the size of the clearance on the dynamic characteristics of the system are explored; as well, the influence of different clearance parameters on the dynamic characteristics of the development mechanism is revealed. Through the analysis, this paper provides a theoretical basis for predicting the effect of a spatial revolute clearance joint on the dynamic characteristics of the mechanism and lays a good foundation for the manufacture and application of the mechanism. Full article
(This article belongs to the Special Issue Aerospace Mechanisms and Actuation—Second Edition)
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