Dynamics and Control of Aerospace Systems
A special issue of Actuators (ISSN 2076-0825). This special issue belongs to the section "Aircraft Actuators".
Deadline for manuscript submissions: 31 August 2024 | Viewed by 16260
Special Issue Editors
Interests: dynamics modelling; cooperative control; drone systems; attitude control; on-orbit assembly; vibration control
Interests: dynamics and control of spacecraft; space tether; debris removal; vibration control; nonlinear control
Interests: space-tethered systems; on-orbit autonomous assembly; space robots; advanced control methods; aerospace systems
Interests: optimal estimation; multi-sensor fusion; mobile robot localization; attitude measurement; inertial navigation; star tracker
Special Issue Information
Dear Colleagues,
The dynamics and control of aerospace systems have attracted growing interest due to being a key problem in the development of aerospace vehicles, such as space stations, space telescopes and advanced aircraft. The purpose of dynamics is to study system behaviours using time and force, while the purpose of control is to develop the control effect with error feedback under various working conditions. Knowledge of aerospace systems is critical for the design of control systems. Newly designed aerospace systems raise novel challenges for the dynamics and control techniques. We invite investigators to contribute original research and review articles addressing dynamics modelling, the stability analysis and controller design of aerospace systems.
Potential topics include, but are not limited to:
- Control system design of aircraft and spacecraft;
- System modelling, analysis and identification of aerospace systems;
- System stability of aerospace vehicles;
- Sensors and control actuators of aircraft, rockets and spacecraft;
- Orbit and attitude dynamics and control;
- Drone dynamics and control;
- Experimental investigation of aerospace systems;
- Novel sensors and actuators of aerospace vehicles.
Dr. Ti Chen
Dr. Junjie Kang
Dr. Shidong Xu
Dr. Shuo Zhang
Dr. Dongdong Li
Guest Editors
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
- system dynamics
- system identification
- control system design
- stability analysis
- dynamics and control
- aerospace vehicles
- experimental investigation
Planned Papers
The below list represents only planned manuscripts. Some of these manuscripts have not been received by the Editorial Office yet. Papers submitted to MDPI journals are subject to peer-review.
Title: Trajectory optimization of an interplanetary CubeSat with a hybrid propulsion system
Authors: Alessandro Antonio Quarta
Affiliation: University of Pisa, Italy.
Abstract: The trajectory design and transfer performance of an interplanetary spacecraft are closely linked to the design characteristics of the propulsion system installed on board. In this context, the choice of the type of propulsion system is usually a compromise between conflicting requirements such as, for example, the possibility of having a continuous, steerable thrust of sufficiently high magnitude, and then being able to use it for a long period of time in order to complete deep space missions that require a high velocity change. In this regard, a potential solution is a Hybrid Propulsion System (HPS), which combines two different types of thrusters in the same spacecraft. This paper analyzes the transfer performance of an interplanetary CubeSat equipped with an HPS consisting of a low-performance solar sail and a typical electric thruster. In particular, the characteristics of the electric thruster are modeled using a recent mathematical approach that describes the performance of the engine that will be installed on board the proposed ESA's M-ARGO CubeSat. The latter will hopefully be the first CubeSat to complete an interplanetary transfer using its own propulsion system. In order to simplify the design of the CubeSat attitude control subsystem, we assume that the orientation of the low-performance solar sail is kept Sun-facing. That condition is obtained, passively, by using an appropriate design of the shape of the reflective surface. The performance of a HPS-based CubeSat are analyzed by optimizing the propelled trajectory in a classical orbit-to-orbit, three-dimensional, heliocentric transfer which also considers the effects of the degradation of the sail reflective film.