Parameterized Design and Dynamic Analysis of a Reusable Launch Vehicle Landing System with Semi-Active Control

Reusable launch vehicles (RLVs) are a solution for effective and economic transportation in future aerospace exploration. However, RLVs are limited to being used under simple landing conditions (small landing velocity and angle) due to their poor adaptability and the high rocket acceleration of curr...
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Autor*in:	Chen Wang [verfasserIn] Jinbao Chen [verfasserIn] Shan Jia [verfasserIn] Heng Chen [verfasserIn]

Format:	E-Artikel
Sprache:	Englisch

Erschienen:	2020

Schlagwörter:	reusable launch vehicles soft landing magnetorheological fluid numerical simulation multibody systems with flexible elements

Übergeordnetes Werk:	In: Symmetry - MDPI AG, 2009, 12(2020), 9, p 1572
Übergeordnetes Werk:	volume:12 ; year:2020 ; number:9, p 1572

Links:	Link aufrufen Link aufrufen Link aufrufen Journal toc

DOI / URN:	10.3390/sym12091572

Katalog-ID:	DOAJ086575139

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language	English
source	In Symmetry 12(2020), 9, p 1572 volume:12 year:2020 number:9, p 1572
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topic_facet	reusable launch vehicles soft landing magnetorheological fluid numerical simulation multibody systems with flexible elements Mathematics
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authorswithroles_txt_mv	Chen Wang @@aut@@ Jinbao Chen @@aut@@ Shan Jia @@aut@@ Heng Chen @@aut@@
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callnumber-first	Q - Science
author	Chen Wang
spellingShingle	Chen Wang misc QA1-939 misc reusable launch vehicles misc soft landing misc magnetorheological fluid misc numerical simulation misc multibody systems with flexible elements misc Mathematics Parameterized Design and Dynamic Analysis of a Reusable Launch Vehicle Landing System with Semi-Active Control
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topic_title	QA1-939 Parameterized Design and Dynamic Analysis of a Reusable Launch Vehicle Landing System with Semi-Active Control reusable launch vehicles soft landing magnetorheological fluid numerical simulation multibody systems with flexible elements
topic	misc QA1-939 misc reusable launch vehicles misc soft landing misc magnetorheological fluid misc numerical simulation misc multibody systems with flexible elements misc Mathematics
topic_unstemmed	misc QA1-939 misc reusable launch vehicles misc soft landing misc magnetorheological fluid misc numerical simulation misc multibody systems with flexible elements misc Mathematics
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title	Parameterized Design and Dynamic Analysis of a Reusable Launch Vehicle Landing System with Semi-Active Control
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title_full	Parameterized Design and Dynamic Analysis of a Reusable Launch Vehicle Landing System with Semi-Active Control
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author_browse	Chen Wang Jinbao Chen Shan Jia Heng Chen
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title_sort	parameterized design and dynamic analysis of a reusable launch vehicle landing system with semi-active control
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title_auth	Parameterized Design and Dynamic Analysis of a Reusable Launch Vehicle Landing System with Semi-Active Control
abstract	Reusable launch vehicles (RLVs) are a solution for effective and economic transportation in future aerospace exploration. However, RLVs are limited to being used under simple landing conditions (small landing velocity and angle) due to their poor adaptability and the high rocket acceleration of current landing systems. In this paper, an adaptive RLV landing system with semi-active control is proposed. The proposed landing system can adjust the damping forces of primary strut dampers through semi-actively controlled currents in accordance with practical landing conditions. A landing dynamic model of the proposed landing system is built. According to the dynamic model, an light and effective RLV landing system is parametrically designed based on the response surface methodology. Dynamic simulations validate the proposed landing system under landing conditions including the highest rocket acceleration and the greatest damper compressions. The simulation results show that the proposed landing system with semi-active control has better landing performance than current landing systems that use passive liquid or liquid–honeycomb dampers. Additionally, the flexibility and friction of the structure are discussed in the simulations. Compared to rigid models, flexible models decrease rocket acceleration by 51% and 54% at the touch down moments under these two landing conditions, respectively. The friction increases rocket acceleration by less than 1%. However, both flexibility and friction have little influence on the distance between the rocket and ground, or the compression strokes of the dampers.
abstractGer	Reusable launch vehicles (RLVs) are a solution for effective and economic transportation in future aerospace exploration. However, RLVs are limited to being used under simple landing conditions (small landing velocity and angle) due to their poor adaptability and the high rocket acceleration of current landing systems. In this paper, an adaptive RLV landing system with semi-active control is proposed. The proposed landing system can adjust the damping forces of primary strut dampers through semi-actively controlled currents in accordance with practical landing conditions. A landing dynamic model of the proposed landing system is built. According to the dynamic model, an light and effective RLV landing system is parametrically designed based on the response surface methodology. Dynamic simulations validate the proposed landing system under landing conditions including the highest rocket acceleration and the greatest damper compressions. The simulation results show that the proposed landing system with semi-active control has better landing performance than current landing systems that use passive liquid or liquid–honeycomb dampers. Additionally, the flexibility and friction of the structure are discussed in the simulations. Compared to rigid models, flexible models decrease rocket acceleration by 51% and 54% at the touch down moments under these two landing conditions, respectively. The friction increases rocket acceleration by less than 1%. However, both flexibility and friction have little influence on the distance between the rocket and ground, or the compression strokes of the dampers.
abstract_unstemmed	Reusable launch vehicles (RLVs) are a solution for effective and economic transportation in future aerospace exploration. However, RLVs are limited to being used under simple landing conditions (small landing velocity and angle) due to their poor adaptability and the high rocket acceleration of current landing systems. In this paper, an adaptive RLV landing system with semi-active control is proposed. The proposed landing system can adjust the damping forces of primary strut dampers through semi-actively controlled currents in accordance with practical landing conditions. A landing dynamic model of the proposed landing system is built. According to the dynamic model, an light and effective RLV landing system is parametrically designed based on the response surface methodology. Dynamic simulations validate the proposed landing system under landing conditions including the highest rocket acceleration and the greatest damper compressions. The simulation results show that the proposed landing system with semi-active control has better landing performance than current landing systems that use passive liquid or liquid–honeycomb dampers. Additionally, the flexibility and friction of the structure are discussed in the simulations. Compared to rigid models, flexible models decrease rocket acceleration by 51% and 54% at the touch down moments under these two landing conditions, respectively. The friction increases rocket acceleration by less than 1%. However, both flexibility and friction have little influence on the distance between the rocket and ground, or the compression strokes of the dampers.
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container_issue	9, p 1572
title_short	Parameterized Design and Dynamic Analysis of a Reusable Launch Vehicle Landing System with Semi-Active Control
url	https://doi.org/10.3390/sym12091572 https://doaj.org/article/6ff5253fe80c4f32bfbc2b6e589d2b43 https://www.mdpi.com/2073-8994/12/9/1572 https://doaj.org/toc/2073-8994
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doi_str	10.3390/sym12091572
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up_date	2024-07-03T21:30:04.846Z
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Parameterized Design and Dynamic Analysis of a Reusable Launch Vehicle Landing System with Semi-Active Control

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