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Integrated Guidance and Control for Aerospace Vehicles

Special Issue Information

Dear Colleagues,

Traditionally, the guidance and control systems of aerospace vehicles are designed independently, and their basic premise is based on the assumption of the spectrum separation principle. In recent decades, with the enhanced maneuverability and flight speed of aerospace vehicles, this assumption does not always make sense. In particular, the independent design becomes powerless under the fast dynamic performance and high precision requirements during high-speed flights with large maneuvers. To this end, the integrated guidance and control (IGC) design concept appeared and has attracted significant attention recently. The basic line of the IGC concept is to consider the relative motion and the dynamic characteristics as an integrated model governed by the guidance and control goals to be achieved. The IGC algorithm is capable of avoiding the delay between the inner and outer loops, simplifying the design cost, and improving the guidance and control performance from the perspective of all of the flight indicator requirements. Numerous techniques, including optimal control, sliding mode control, intelligent control, adaptive control, etc., have been employed to investigate the IGC system design problem. Although the recent progress in this field has witnessed various contributions, the design problem of IGC using various advanced control theories under multiple physical constraints or requirements remains open. To promote the development of aerospace technology, highlight the most recent advances, and provide a wide range of state-of-the-art trends in the IGC designs, as well as their applications, this Special Issue aims to collect the recent development of IGC design and share the latest results in relation to the theoretical and experimental investigations of the IGC concept for aerospace vehicles. It mainly invites articles from technical areas including but not limited to the new IGC design concept, modeling, analysis, and experimental verification.

Dr. Bin Zhao
Dr. Tuo Han
Prof. Dr. Pengyu Wang
Dr. Wei Dong
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 250 words) can be sent to the Editorial Office for assessment.

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.

Keywords

  • integrated guidance and control
  • guidance and control modelling
  • constrained guidance and control
  • field-of-view limit
  • terminal impact constraint
  • actuator saturation
  • intelligent control

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Aerospace - ISSN 2226-4310