View in EDS

Analytical 3D proportional navigation guidance for field-of-view constrained impact time control.

Saved in:
Bibliographic Details
Title: Analytical 3D proportional navigation guidance for field-of-view constrained impact time control.
Authors: Cao, Ruihao1 (AUTHOR), Han, Tuo2 (AUTHOR), Li, Chaoyong3 (AUTHOR), He, Shaoming1 (AUTHOR) shaoming.he@bit.edu.cn
Source: Aerospace Science & Technology. May2026, Vol. 172, pN.PAG-N.PAG. 1p.
Subjects: Proportional navigation, Missile guidance systems
Abstract: • A 3D FOV-constrained ITCG law is proposed in PNG form with a range- varying gain, inheriting the advantage of simple structure and eliminating multistage switching logic and provides an exact yet concise trajectory- to-go solution independent of velocity variations. • The proposed guidance law yields analytical solutions for both guidance parameters and their safe ranges, circumventing linearization, numerical parameter solving, and over-conservative monotonic decreasing pro les. • The proposed law can provide an analytical achievable impact time region under permissible FOV limits, thus avoiding blind selection of the desired interception time in advance. This paper presents a novel 3D proportional navigation guidance (PNG) law with a range-varying gain, which achieves impact time control under the seeker's restricted field-of-view (FOV) for both stationary and maneuvering targets, even with time-varying missile speeds. Originating from the lead angle-shaping philosophy, this proposed nonlinear guidance method, unlike existing studies, features the novelty that the trajectory-to-go solution, as well as the achievable impact time domain under FOV limit, is formulated as concise and precise analytical expression. Moreover, it circumvents multistage switching logic, linearization procedures, numerical solving guidance parameters, and conservative monotonic decreasing shaping profiles. Additionally, by introducing a 3D relative reference frame, the proposed approach is extended to the scenarios involving maneuvering targets and varying-speed missile model. Notably, the transformed condition for satisfying the FOV constraint within the 3D relative reference frame is rigorously derived in this work, laying a theoretical foundation for addressing the FOV issue through the direct application of 3D relative engagement kinematics. Numerical simulations for different scenarios including a time-varying velocity missile model are performed to validate the effectiveness and superiority of the proposed guidance law. [ABSTRACT FROM AUTHOR]
Copyright of Aerospace Science & Technology is the property of Elsevier B.V. and its content may not be copied or emailed to multiple sites without the copyright holder's express written permission. Additionally, content may not be used with any artificial intelligence tools or machine learning technologies. However, users may print, download, or email articles for individual use. This abstract may be abridged. No warranty is given about the accuracy of the copy. Users should refer to the original published version of the material for the full abstract. (Copyright applies to all Abstracts.)
Database: Engineering Source
FullText Text:
  Availability: 0
Header DbId: egs
DbLabel: Engineering Source
An: 192174540
AccessLevel: 6
PubType: Academic Journal
PubTypeId: academicJournal
PreciseRelevancyScore: 0
IllustrationInfo
Items – Name: Title
  Label: Title
  Group: Ti
  Data: Analytical 3D proportional navigation guidance for field-of-view constrained impact time control.
– Name: Author
  Label: Authors
  Group: Au
  Data: <searchLink fieldCode="AR" term="%22Cao%2C+Ruihao%22">Cao, Ruihao</searchLink><relatesTo>1</relatesTo> (AUTHOR)<br /><searchLink fieldCode="AR" term="%22Han%2C+Tuo%22">Han, Tuo</searchLink><relatesTo>2</relatesTo> (AUTHOR)<br /><searchLink fieldCode="AR" term="%22Li%2C+Chaoyong%22">Li, Chaoyong</searchLink><relatesTo>3</relatesTo> (AUTHOR)<br /><searchLink fieldCode="AR" term="%22He%2C+Shaoming%22">He, Shaoming</searchLink><relatesTo>1</relatesTo> (AUTHOR)<i> shaoming.he@bit.edu.cn</i>
– Name: TitleSource
  Label: Source
  Group: Src
  Data: <searchLink fieldCode="JN" term="%22Aerospace+Science+%26+Technology%22">Aerospace Science & Technology</searchLink>. May2026, Vol. 172, pN.PAG-N.PAG. 1p.
– Name: Subject
  Label: Subjects
  Group: Su
  Data: <searchLink fieldCode="DE" term="%22Proportional+navigation%22">Proportional navigation</searchLink><br /><searchLink fieldCode="DE" term="%22Missile+guidance+systems%22">Missile guidance systems</searchLink>
– Name: Abstract
  Label: Abstract
  Group: Ab
  Data: • A 3D FOV-constrained ITCG law is proposed in PNG form with a range- varying gain, inheriting the advantage of simple structure and eliminating multistage switching logic and provides an exact yet concise trajectory- to-go solution independent of velocity variations. • The proposed guidance law yields analytical solutions for both guidance parameters and their safe ranges, circumventing linearization, numerical parameter solving, and over-conservative monotonic decreasing pro les. • The proposed law can provide an analytical achievable impact time region under permissible FOV limits, thus avoiding blind selection of the desired interception time in advance. This paper presents a novel 3D proportional navigation guidance (PNG) law with a range-varying gain, which achieves impact time control under the seeker's restricted field-of-view (FOV) for both stationary and maneuvering targets, even with time-varying missile speeds. Originating from the lead angle-shaping philosophy, this proposed nonlinear guidance method, unlike existing studies, features the novelty that the trajectory-to-go solution, as well as the achievable impact time domain under FOV limit, is formulated as concise and precise analytical expression. Moreover, it circumvents multistage switching logic, linearization procedures, numerical solving guidance parameters, and conservative monotonic decreasing shaping profiles. Additionally, by introducing a 3D relative reference frame, the proposed approach is extended to the scenarios involving maneuvering targets and varying-speed missile model. Notably, the transformed condition for satisfying the FOV constraint within the 3D relative reference frame is rigorously derived in this work, laying a theoretical foundation for addressing the FOV issue through the direct application of 3D relative engagement kinematics. Numerical simulations for different scenarios including a time-varying velocity missile model are performed to validate the effectiveness and superiority of the proposed guidance law. [ABSTRACT FROM AUTHOR]
– Name: AbstractSuppliedCopyright
  Label:
  Group: Ab
  Data: <i>Copyright of Aerospace Science & Technology is the property of Elsevier B.V. and its content may not be copied or emailed to multiple sites without the copyright holder's express written permission. Additionally, content may not be used with any artificial intelligence tools or machine learning technologies. However, users may print, download, or email articles for individual use. This abstract may be abridged. No warranty is given about the accuracy of the copy. Users should refer to the original published version of the material for the full abstract.</i> (Copyright applies to all Abstracts.)
PLink https://search.ebscohost.com/login.aspx?direct=true&site=eds-live&db=egs&AN=192174540
RecordInfo BibRecord:
  BibEntity:
    Identifiers:
      – Type: doi
        Value: 10.1016/j.ast.2026.111680
    Languages:
      – Code: eng
        Text: English
    PhysicalDescription:
      Pagination:
        PageCount: 1
        StartPage: N.PAG
    Subjects:
      – SubjectFull: Proportional navigation
        Type: general
      – SubjectFull: Missile guidance systems
        Type: general
    Titles:
      – TitleFull: Analytical 3D proportional navigation guidance for field-of-view constrained impact time control.
        Type: main
  BibRelationships:
    HasContributorRelationships:
      – PersonEntity:
          Name:
            NameFull: Cao, Ruihao
      – PersonEntity:
          Name:
            NameFull: Han, Tuo
      – PersonEntity:
          Name:
            NameFull: Li, Chaoyong
      – PersonEntity:
          Name:
            NameFull: He, Shaoming
    IsPartOfRelationships:
      – BibEntity:
          Dates:
            – D: 01
              M: 05
              Text: May2026
              Type: published
              Y: 2026
          Identifiers:
            – Type: issn-print
              Value: 12709638
          Numbering:
            – Type: volume
              Value: 172
          Titles:
            – TitleFull: Aerospace Science & Technology
              Type: main
ResultId 1