Analysis of Trim Characteristics and Control Performance for the Single-Engine Failed Civil Aircraft During Landing and Approaching

Research output: Chapter in Book/Report/Conference proceedingConference contributionpeer-review

Abstract

This paper presents the research on the trim characteristics and the controllability for the single-engine failed flight during landing and approaching. First, the dynamic model is established for the single-engine failed flight. Second, The lateral and directional trim characteristics of the single-engine failed aircraft are theoretically analyzed and verified through simulation. Third, the lateral and directional controllability is evaluated by the criteria of CCAR-25 through simu lation. In the end, the minimum control speed during landing and approaching is determined according to the trim characteristics aforementioned, and the control lable speed range under low-altitude (9 m–500 m) conditions is calculated for the single-engine failed aircraft.

Original languageEnglish
Title of host publicationAdvances in Guidance, Navigation and Control - Proceedings of 2024 International Conference on Guidance, Navigation and Control Volume 3
EditorsLiang Yan, Haibin Duan, Yimin Deng
PublisherSpringer Science and Business Media Deutschland GmbH
Pages382-391
Number of pages10
ISBN (Print)9789819622078
DOIs
StatePublished - 2025
EventInternational Conference on Guidance, Navigation and Control, ICGNC 2024 - Changsha, China
Duration: 9 Aug 202411 Aug 2024

Publication series

NameLecture Notes in Electrical Engineering
Volume1339 LNEE
ISSN (Print)1876-1100
ISSN (Electronic)1876-1119

Conference

ConferenceInternational Conference on Guidance, Navigation and Control, ICGNC 2024
Country/TerritoryChina
CityChangsha
Period9/08/2411/08/24

Keywords

  • Controllability
  • Minimum Control Speed during Landing Approach
  • Single-Engine Failure
  • Trim Characteristics

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