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Aerospace
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Aircraft Trajectory Design and Optimization (Volume II)
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Aircraft Trajectory Design and Optimization (Volume II)

A special issue of Aerospace (ISSN 2226-4310). This special issue belongs to the section "Aeronautics".

Deadline for manuscript submissions: closed (28 February 2023) | Viewed by 4111

Special Issue Editor

Dr. Alejandro Murrieta-Mendoza

E-Mail Website
Guest Editor
Research Group for Aviation, Centre for Applied Research on Education, Amsterdam University of Applied Science, Amstelcampus, Weesperzijde 190, 1097 DZ Amsterdam, The Netherlands
Interests: avionics; trajectory optimization; metaheuristic algorithms; graph search; control systems
Special Issues, Collections and Topics in MDPI journals

Special Issue Information

Dear Colleagues,

Air traffic is expected to recover to pre-COVID-19 levels in the following years. The presence of more aircraft in the sky has drawbacks such as an increased use of fuel to power these flights, an increase in pollution, and increasing chances of contrail formation. These problems are expected to amplify due to the forecasted increase in traffic in developing areas such as Latin America and Asia.

Aircraft trajectory design and optimization could mitigate these effects by guiding aircraft to airspace zones (airborne and taxing) where flight conditions minimize the amount of fuel burnt and the chances of contrail formation. Commercial aircraft, military aircraft, and drones would benefit from trajectory optimization.

Typical ways of solving this problem involve the use of conventional optimization algorithms. Nevertheless, new developments in machine learning and artificial intelligence can be helpful, especially in airspace capacity prediction, trajectory prediction, collision avoidance, among others.

The Special Issue addresses the broad topics related to aircraft trajectory design and welcomes papers dealing with, but not limited to:

  • aircraft trajectory design;
  • aircraft trajectory optimization;
  • trajectories pollution computation;
  • aircraft trajectory negotiation;
  • landing and/or take-off runaway optimization;
  • airspace management;
  • weather predictions and big data;
  • trajectory options sets and rerouting;
  • drones and UAVs trajectories;
  • trajectory prediction;
  • trajectory collision avoidance;
  • machine learning and artificial intelligence applications for trajectories.

Dr. Alejandro Murrieta-Mendoza
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. Aerospace 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.

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Related Special Issue

Published Papers (2 papers)

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Research

27 pages, 1028 KiB  
Article
On the Size of the Safety Area around the Launch Trajectory of a Rocket
by Luiz M. B. C. Campos and Manuel J. S. Silva
Aerospace 2023, 10(9), 760; https://doi.org/10.3390/aerospace10090760 - 28 Aug 2023
Cited by 1 | Viewed by 1487
Abstract
The safety zone around the flight path of a rocket is determined by the fall of debris in the case of an accidental explosion or commanded termination. The trajectory of a tumbling body in a vertical plane is determined by specifying the velocity, [...] Read more.
The safety zone around the flight path of a rocket is determined by the fall of debris in the case of an accidental explosion or commanded termination. The trajectory of a tumbling body in a vertical plane is determined by specifying the velocity, flight path angle and angle of attack as functions of time. This involves the lift, drag and pitching moment coefficients as functions of the angle of attack over a full circle—0 to 360 degrees—to account for the tumbling motion. The problem is reduced to a third-order non-linear differential equation for the angle of attack by using the approximation of free fall coordinates. The analytical and numerical solutions show that two types of tumbling fall are possible, one with rotation and the other with oscillation. The tumbling trajectories are plotted and discussed for a variety of initial conditions, mass and aerodynamic properties of the tumbling body. Full article
(This article belongs to the Special Issue Aircraft Trajectory Design and Optimization (Volume II))
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18 pages, 2961 KiB  
Article
Receding Horizon Trajectory Generation of Stratospheric Airship in Low-Altitude Return Phase
by Yuhao Jing, Yang Wu, Jiwei Tang, Pingfang Zhou and Dengping Duan
Aerospace 2022, 9(11), 670; https://doi.org/10.3390/aerospace9110670 - 29 Oct 2022
Cited by 4 | Viewed by 1823
Abstract
The contribution of this paper is the proposal of a new receding horizon trajectory generation method for stratospheric airships’ return phase. Since the energy consumption, wind field and path constraints are restrictions during the return phase of airships at low altitude, it is [...] Read more.
The contribution of this paper is the proposal of a new receding horizon trajectory generation method for stratospheric airships’ return phase. Since the energy consumption, wind field and path constraints are restrictions during the return phase of airships at low altitude, it is crucial to develop novel trajectory optimization methods to ensure that the airship returns to the landing site. In this article, optimization objects and conditions of the return trajectory were constructed, considering the energy consumption and wind field. Then, a modified interior point method (MIP) was used to transform the inequality constraint, which is a simple and adaptable method used to improve the solving efficiency on the basis of a modified multiple shooting method (MMS). In addition, an adaptive gradient descent regulator was improved to reduce the influence on the optimization result due to different selections of the initial search point, and the convergence was made faster and more stable. Finally, considering the performance and path constraints of the airship, the effectiveness of the scheme was verified by numerical experiments under wind effects and a comparison of different methods. Full article
(This article belongs to the Special Issue Aircraft Trajectory Design and Optimization (Volume II))
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