Journal of Aircraft and Spacecraft Technology最新文献_第2页

Spectral and Luminescence Properties of Manganese Doped Sodium Lead Alumino Borosilicate Glass System 锰掺杂钠铅铝硼硅酸盐玻璃体系的光谱和发光特性

Journal of Aircraft and Spacecraft Technology Pub Date : 2019-01-01 DOI: 10.3844/jastsp.2019.248.255

K. V. Babu, A. S. Rao, K. N. Kumar, M. Rao

引用次数: 8

Corrigendum: Airlander

Journal of Aircraft and Spacecraft Technology Pub Date : 2019-01-01 DOI: 10.3844/jastsp.2019.55

Antonio Apicella, Relly Victoria Petrescu, Florian Ion Petrescu, Taher M. Abu-Lebdeh, Samuel P. Kozaitis, Juan Corchado, Bilal Akash, Raffaella Aversa

引用次数: 0

Hardening Effects of In-Situ Aging for a Laser Welded Maraging Steel 激光焊接马氏体时效钢的原位时效硬化效应

Journal of Aircraft and Spacecraft Technology Pub Date : 2019-01-01 DOI: 10.3844/jastsp.2019.237.247

M. Lima, R. Siqueira, S. Carvalho, A. J. Abdalla

{"title":"Hardening Effects of In-Situ Aging for a Laser Welded Maraging Steel","authors":"M. Lima, R. Siqueira, S. Carvalho, A. J. Abdalla","doi":"10.3844/jastsp.2019.237.247","DOIUrl":"https://doi.org/10.3844/jastsp.2019.237.247","url":null,"abstract":"Maraging steels are ultra-high strength alloys which have been successfully laser welded to obtain structural components. For most of the applications these steels are in an aged state to attain tensile strength up to 1.5 GPa, although welding induces local softening due to dissolution of precipitates. This paper aims to investigate the effect of in-situ aging of the maraging steel plates after laser welding to reduce the local softening. For a preheating at 40?C, just below the martensite finish line, the hardness of the Fusion Zone (FZ) attained between 440 and 490 HV and the Heat-Affected Zone (HAZ) attained a maximum of 570 HV compared to 300 HV of the Base Material (BM) for aging temperatures between 450?C and 520?C and periods between 10 and 30 min. The intercritical aging (570?C/1 h) also promoted an increase in local hardness of FZ 320 HV and HAZ 400 HV. Using an intercritical aging, the hardness situated between room temperature and quenched and aged coupons and was more homogeneous considering FZ, HAZ and BM. The microstructure of the intercritical aged welds is marked by duplex-ferrite and martensite micro-constituents","PeriodicalId":319209,"journal":{"name":"Journal of Aircraft and Spacecraft Technology","volume":"66 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2019-01-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"132260857","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 5

Overview of Space Debris Mitigation Activities in ISRO 印度空间研究组织空间碎片减缓活动概述

Journal of Aircraft and Spacecraft Technology Pub Date : 2019-01-01 DOI: 10.3844/jastsp.2019.197.210

Santosh Kosambe

{"title":"Overview of Space Debris Mitigation Activities in ISRO","authors":"Santosh Kosambe","doi":"10.3844/jastsp.2019.197.210","DOIUrl":"https://doi.org/10.3844/jastsp.2019.197.210","url":null,"abstract":"For several decades orbital debris has been identified as a serious concern by all space-faring agencies and nations as it potentially threatens the current and future space endeavors. The Indian Space Research Organization (ISRO) is well aware of the current space debris scenario and is committed to achieving the goal of preserving outer-space for humanity. ISRO works on different aspects to effectively manage the threats due to space debris. This paper provides an overview of past activities carried out in ISRO towards the implementation of space debris mitigation guidelines. One of the significant step taken is the end of life passivation of the cryogenic upper stage of ISRO’s Geosynchronous Satellite Launch Vehicle (GSLV). Another one is the successful design and development of propellant venting system for the upper stage of ISRO’s Polar Satellite Launch Vehicle (PSLV). ISRO’s constellation of communication satellites orbiting in GSO’s is designed with adequate propellant so that it can re-orbit to the higher graveyard orbit at the end of their operational lifetime. A typical successful re-orbiting and decommissioning operation of INSAT-3E is described in detail here. ISRO has successfully designed and developed the models and software to predict the atmospheric re-entry of satellites and launch vehicle upper stages, also to compute the collision risk between the debris and the operational satellites. ISRO has also developed models to study the evolution of the space debris environment in LEO and GEO. ISRO actively support the efforts of the United Nations Committee on the Peaceful Uses of Outer Space (UNCOPUOS) and Inter-Agency Space Debris Coordination Committee (IADC) to develop and adopt the space debris mitigation guidelines.","PeriodicalId":319209,"journal":{"name":"Journal of Aircraft and Spacecraft Technology","volume":"21 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2019-01-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"133838615","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 4

NASA and the Conquest of Cosmic Space by Man NASA和人类对宇宙空间的征服

Journal of Aircraft and Spacecraft Technology Pub Date : 2019-01-01 DOI: 10.3844/JASTSP.2019.78.91

R. Petrescu

引用次数: 4

Novel Approach for Characterizing Solid Rocket Motor (SRM) 固体火箭发动机(SRM)特性的新方法

Journal of Aircraft and Spacecraft Technology Pub Date : 2019-01-01 DOI: 10.3844/JASTSP.2019.119.127

A. B. Kisabo, N. Nwokolo, Aliyu Funmilayo Adebimpe, Sholiyi Olusegun Samuel

{"title":"Novel Approach for Characterizing Solid Rocket Motor (SRM)","authors":"A. B. Kisabo, N. Nwokolo, Aliyu Funmilayo Adebimpe, Sholiyi Olusegun Samuel","doi":"10.3844/JASTSP.2019.119.127","DOIUrl":"https://doi.org/10.3844/JASTSP.2019.119.127","url":null,"abstract":"To characterize SRM, the motor needs to be tested on a static test rig and certain performers indicators evaluated. In this study, the thrust with time from the SRM was acquired via a Digital Acquisition (DAQ) System and saved in Microsoft Excel® format(.csv). These thrust and time of the tested motor were then imported into MATLAB® for the purpose of computing burn time, maximum thrust, average thrust, total impulse, specific impulse and chamber pressure of the motor. The specific impulse and combustion chamber pressure for the SRM were computed in a novel approach which we call Pseudo-numerical approach (combination of experimental result with numerical computation). In this approach, first, we modelled the depleting propellant mass in the combustion chamber with a novel mathematical expression. This novel expression was then used in computing specific impulse of the SRM. Second, the total surface area of the propellant grain was modelled as a hollow cylinder with depleting dynamics during motor operation, in a similar manner with the propellant mass. Third, multiplying the reciprocal of the propellant grain surface area with the experimental force gave use the pseudo-numerically computed chamber pressure. The pressure trend of the SRM obtained was also compared to those in well-established literature, thus, the pseudo-numerical approach put forward proves to be effective.","PeriodicalId":319209,"journal":{"name":"Journal of Aircraft and Spacecraft Technology","volume":"80 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2019-01-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"130712025","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 4

Corrigendum: History of Aviation-A Short Review 勘误表:航空史-简短回顾

Journal of Aircraft and Spacecraft Technology Pub Date : 2019-01-01 DOI: 10.3844/JASTSP.2019.60

F. Petrescu, A. Apicella, J. Corchado, R. Bucinell, B. Akash, R. Aversa, R. Petrescu

引用次数: 0

Control of Twin Rotor MIMO System using PID and LQR Controller 基于PID和LQR控制器的双转子MIMO系统控制

Journal of Aircraft and Spacecraft Technology Pub Date : 2019-01-01 DOI: 10.3844/jastsp.2019.211.220

Seema R. Chaudhary, Adarsh Kumar

引用次数: 3

Chandrayaan-2: India’s Second Lunar Exploration Mission 月船2号:印度的第二次月球探测任务

Journal of Aircraft and Spacecraft Technology Pub Date : 2019-01-01 DOI: 10.3844/jastsp.2019.221.236

Santosh Kosambe

{"title":"Chandrayaan-2: India’s Second Lunar Exploration Mission","authors":"Santosh Kosambe","doi":"10.3844/jastsp.2019.221.236","DOIUrl":"https://doi.org/10.3844/jastsp.2019.221.236","url":null,"abstract":"The Moon has always been the center of attention for mankind, more than any other heavenly body in the night sky. With the early history of the solar system etched on it, the Moon challenges mankind from time immemorial to discover its secrets and admire its marvels. Understanding the Moon will provide us a pathway to unravel the early evolution of the solar system and that of planet Earth. Almost twelve years after its first lunar exploration mission, India bounced back towards Moon with Chandrayaan-2. India’s most advanced engineering marvel Chandrayaan-2 is on a mission unlike any before. Leveraging nearly a decade of scientific research and engineering development, India’s second lunar expedition will shed light on a completely unexplored region of the Moon, its South Polar Region. The indigenously built Chandrayaan-2 consists of an orbiter, a lander (Vikram) along with a rover (Pragyan). With the payload of completely home-grown technologies, it will help us to gain a better understanding of the origin and evolution of the Moon by conducting detailed topographical studies, comprehensive mineralogical analysis and a host of other experiments. The Chandrayaan-2 is India’s first robotic exploration mission to attempt a soft landing on the South Polar Region of the Moon. With the success of this mission, India became the fifth country ever to attempt a soft landing on the lunar surface. This paper provides an insight into the Chandrayaan-2 Mission. Additionally, an overview of the mission profile, challenges involved, launch vehicle architecture, spacecraft configuration and scientific payloads are also presented.","PeriodicalId":319209,"journal":{"name":"Journal of Aircraft and Spacecraft Technology","volume":"198 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2019-01-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"132401399","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 6

Corrigendum: Lockheed Martin-A Short Review 更正:洛克希德马丁公司——简短回顾

Journal of Aircraft and Spacecraft Technology Pub Date : 2019-01-01 DOI: 10.3844/JASTSP.2019.61

R. Petrescu, F. Petrescu, A. Apicella, J. Corchado, R. Bucinell, B. Akash, R. Aversa

引用次数: 0