Landing System Design in Aerospace

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

Deadline for manuscript submissions: 30 April 2024 | Viewed by 3455

Special Issue Editors


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Guest Editor
College of Aerospace Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China
Interests: aircraft landing gear design; lunar lander design; aerospace vehicle structural dynamics

E-Mail Website
Guest Editor
College of Aerospace Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China
Interests: aircraft landing gear design; UAV launch and recovery technology; aircraft structural dynamics
Special Issues, Collections and Topics in MDPI journals

E-Mail Website
Guest Editor
College of Aerospace Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China
Interests: lunar lander design; soft landing technology; spacecraft structural dynamics

Special Issue Information

Dear Colleagues,

For many years, mankind has desired to fly into the sky. However, no matter how high or far you go, you have to come back to the ground. With the rapid development of aerospace vehicles, they have become heavier and able to fly higher and farther, the outcomes being higher landing speeds and larger landing impact loads. The landing environment of aerospace vehicles is also becoming more severe. All of these factors pose new challenges to the design of landing systems. This Special Issue aims to provide an overview of recent advances in landing system design in aerospace. Authors are invited to submit full research articles and review manuscripts addressing (but not limited to) the following topics:

  • Novel concepts and methods for multistage multiphase landing buffers
  • Novel methods for shimmying nose landing gear on the runway
  • Novel methods for landing gear walking while braking
  • Stability or reliability analysis of landing system retraction mechanisms in aerospace
  • Carrier-based aircraft catapulting off and landing with arresting
  • Soft-landing dynamics of four-legged lunar landers
  • Launch and recovery of UAVs
  • Aircraft taxiing dynamics and stability
  • Adaptive take-off and landing

Prof. Dr. Hong Nie
Prof. Dr. Xiaohui Wei
Prof. Dr. Jinbao Chen
Guest Editors

Manuscript Submission Information

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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

  • landing system
  • landing gear
  • lunar/mars lander
  • asteroid attached landing
  • soft landing
  • shock absorber
  • retraction mechanism
  • nose gear shimmy
  • gear walk
  • the arresting hook/cable
  • dynamics and control

Published Papers (2 papers)

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Research

20 pages, 6966 KiB  
Article
Research on the Stability and Bifurcation Characteristics of a Landing Gear Shimming Dynamics System
by Shuang Ruan, Ming Zhang, Shaofei Yang, Xiaohang Hu and Hong Nie
Aerospace 2024, 11(2), 104; https://doi.org/10.3390/aerospace11020104 - 23 Jan 2024
Viewed by 762
Abstract
A dynamic model is established to investigate the shimmy instability of a landing gear system, considering the influence of nonlinear damping. The stability criterion is utilized to determine the critical speed at which the landing gear system becomes unstable. The central manifold theorem [...] Read more.
A dynamic model is established to investigate the shimmy instability of a landing gear system, considering the influence of nonlinear damping. The stability criterion is utilized to determine the critical speed at which the landing gear system becomes unstable. The central manifold theorem and canonical method are employed to simplify the dynamic model of the landing gear. The first Lyapunov coefficient of the system is theoretically derived and verified using numerical simulation. Further investigation on the Hopf bifurcation characteristics and stability of the shimmy in the landing gear system is conducted. The results indicate that above a certain threshold speed, with a tire stability distance greater than half the tire length in contact with the ground plus the slack length, the aircraft remains stable during taxiing. At critical speeds, a shimmy system with higher-order nonlinear damping will undergo supercritical Hopf bifurcation. Quantitative analysis suggests an increase in the linear damping coefficient within a range that ensures a stability margin to mitigate undesired oscillation, while the nonlinear damping coefficient should be designed within a reasonable range to decrease the amplitude of the limit cycle. Full article
(This article belongs to the Special Issue Landing System Design in Aerospace)
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13 pages, 3879 KiB  
Article
Landing Impact Load Analysis and Validation of a Civil Aircraft Nose Landing Gear
by Wenbin Liu, Youshan Wang and Yuchen Ji
Aerospace 2023, 10(11), 953; https://doi.org/10.3390/aerospace10110953 - 12 Nov 2023
Viewed by 2112
Abstract
Landing impact load design is essential, but the process has rarely been fully described, and some designers have even neglected the differences between wheel-axle and ground-contact loads, as well as loads in the longitudinal direction, especially in experimental validations. In this paper, the [...] Read more.
Landing impact load design is essential, but the process has rarely been fully described, and some designers have even neglected the differences between wheel-axle and ground-contact loads, as well as loads in the longitudinal direction, especially in experimental validations. In this paper, the entire design process of a nose landing gear is addressed, including a theoretical analysis of the unit and its experimental validation. In the theoretical analysis, a mathematical model of a two-mass system with four degrees of freedom was adopted, a computer simulation model was built accordingly, and a preliminary analysis was subsequently conducted to analyze the landing impact loads, verify the landing gear performance, and gauge the difference between the wheel-axle and ground-contact loads. For the experimental validation of the gear, a landing gear drop test was conducted in an optimized manner that emphasized pre-test preparation and during-test wheel-axle load measurement. The test results showed that both the vertical and less studied longitudinal loads, as well as the wheel-axle and ground-contact loads, had good agreement with the analysis; thus, the model, the tool, and the preliminary design were considered to be experimentally validated. Full article
(This article belongs to the Special Issue Landing System Design in Aerospace)
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