Multi-disciplinary design optimization with fuzzy uncertainties and its application in hybrid rocket motor powered launch vehicle

Wang, Pengcheng; Tian, Hui; Zhu, Hao; Cai, Guobiao

doi:10.1016/j.cja.2019.11.002

Cited by 24 publications

(7 citation statements)

References 23 publications

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“…4 shows the range of design variables, where DV is the abbreviation of design variable. The lower bound and upper bound of the design variables are given according to engineering experience and previous works [14], which cover the general operating states of HPSLV.…”

Section: Design Optimizationmentioning

confidence: 99%

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Design Optimization and Parameter Analysis of a Hybrid Rocket Motor-Powered Small LEO Launch Vehicle

Zhu

Wang

et al. 2021

International Journal of Aerospace Engineering

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In this paper, the effects of different grain shapes of a hybrid rocket motor (HRM) and different payload mass/orbit heights on the design of small launch vehicles (SLVs) are systematically discussed. An integrated overall design model for the hybrid rocket motor-powered small launch vehicle (HPSLV) is established, and two groups of three-stage SLVs capable of sending small payloads to the low earth orbit (LEO) are designed and optimized. In the first group, the SLVs with different grain shapes and different numbers of chambers in HRMs at the 1st and the 2nd stages are optimized and analyzed. In the second group, the SLVs capable of sending different payload mass to different orbit heights are optimized and analyzed. Pareto graphs of the design results show that the design of HRM at the 1st stage has the greatest impact on the take-off mass, total velocity increment, and maximum axial overload of the SLV. Self-organizing maps show that the take-off mass, maximum diameter, overall length, and velocity increment of the SLVs have the same variation tendency. For the 1-chamber HRM at the 1st stage, the wheel-shaped grain is better than circle-shaped and star-shaped grains in terms of reducing the total mass and length of the SLV, and the 4-chamber parallel HRM has more advantages over all 1-chamber designs for the same reason. The theoretical velocity increments are calculated by the Tsiolkovsky formula, and the actual velocity increments are obtained based on the trajectory simulation data. The results indicate that the HPSLV has a regular distribution in terms of the ratio of theoretical (actual) velocity increments at three different stages, and the estimated distribution ratio is around 1 : 1.55 : 1.69 (1 : 1.9 : 2.39), which can provide some reference for future development of HPSLV.

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Section: Design Optimizationmentioning

confidence: 99%

“…Rhee et al have conducted research on application of the HRM with HTPB/LOX combination to the first stage of an air launch system [13]. A three-stage launch vehicle is designed using the HRM with H 2 O 2 /HTPB propellant [14].…”

Section: Introductionmentioning

confidence: 99%

Design Optimization and Parameter Analysis of a Hybrid Rocket Motor-Powered Small LEO Launch Vehicle

Zhu

Wang

et al. 2021

International Journal of Aerospace Engineering

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“…Multi-Disciplinary means combining or involving more than one discipline or field of study. Wang et al [31] developed an Uncertainty-based Multi-Disciplinary Design Optimization (UMDO) method to analyze the conceptual design of powered Launch Vehicles (LV). Zhang and Huang [32] proposed formulations of Mixed Variables Multidisciplinary Design Optimization (MVMDO) and its dedicated framework to enable designers in solving MDO problems.…”

Section: Multi-disciplinary Bommentioning

confidence: 99%

Development of Multi-Disciplinary Green-BOM to Maintain Sustainability in Reconfigurable Manufacturing Systems

Kurniadi

Ryu

2021

Sustainability

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The reconfigurable manufacturing system (RMS) appears to be eco-friendly while coping with rapidly changing market demands. However, there remains a lack of discussion or research regarding sustainability or environment-friendly functions within RMS. In this study, the reconfiguration planning problem is introduced to represent the core issues within the RMS. Reconfiguration occurs depending on new demands or conditions in the company by reconfiguring machines, such as removing, adding, or changing parts, giving considerable consideration to arrangement of machines, known as configurations in RMS. Therefore, reconfiguration process is always strongly connected to cost, energy consumption, and, more importantly, data management. The complexity of reconfiguration, product variation, and development processes requires tools that are capable of managing multi-disciplinary bill-of-material(BOM) or product data and providing a better collaboration support for data/information tracking while maintaining sustainability. This paper proposes a multi-disciplinary green bill-of-material (MDG-BOM)—an improved Green-BOM concept—with an additional multi-disciplinary feature to minimize emissions and hazardous materials during product development, as well as manage product information across multiple disciplines during the reconfiguration process. A smart spreadsheet for managing MDG-BOM was developed to allow multiple departments to integrate multiple sources of CAD design data and monitor/track changes throughout each step of the process.

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“…The concepts and applications of MRV will be introduced later with detailed analysis of combining different propulsion systems for certain applications. Examples of existing designs and productions will be presented to support author's concepts [4].…”

Section: Introductionmentioning

confidence: 99%

Principles of Multistage Rocket Vehicle and Concepts of Propulsion Methods for Rocket Applications

Liang¹

2022

HSET

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The variety of propulsion methods will reach their peak efficiencies under certain conditions. This paper will focus on the propulsion methods and different propellant choices for certain usage when designing a vehicle or a stage of a rocket with some altitude limitations, their working principles, applications and challenges. The advantages of multistage design for rocket vehicles and the prospects of advanced engine technology using electricity or solar radiation as its main power source will also be discussed. The cost, payload and other attributes such as the thrust-to-weight ratio of every propulsion concept are the main factors for determining the general performance. MRV is the ideal design for rocket vehicles that are launched from the surface of a planet consider the massive amount of energy it requires to get into the orbit or escape the gravity, but the propulsion system can be various depends on the applications under certain conditions of launching and space travel.

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Multi-disciplinary design optimization with fuzzy uncertainties and its application in hybrid rocket motor powered launch vehicle

Cited by 24 publications

References 23 publications

Design Optimization and Parameter Analysis of a Hybrid Rocket Motor-Powered Small LEO Launch Vehicle

Design Optimization and Parameter Analysis of a Hybrid Rocket Motor-Powered Small LEO Launch Vehicle

Development of Multi-Disciplinary Green-BOM to Maintain Sustainability in Reconfigurable Manufacturing Systems

Principles of Multistage Rocket Vehicle and Concepts of Propulsion Methods for Rocket Applications

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