Journal of Aircraft and Spacecraft Technology最新文献

{"title":"Induction Clutch with the Ability to Generate Electricity, Brake, Start Fuel Engine and Electric Engine","authors":"Seyed Ali Akbar Mousavi","doi":"10.3844/jastsp.2023.1.7","DOIUrl":"https://doi.org/10.3844/jastsp.2023.1.7","url":null,"abstract":"The induction clutch is a device that acts like a friction clutch but there is no abrasion and it is more accurate. Because electric, solar, and fuel car convertible to boats, vertical aircraft flying supersonic has sealed body, for this reason, a friction clutch cannot be used, because the friction clutch does not work well and due to friction, it creates a bad smell and needs that the produced gas is exited from the vehicle. Part of the new induction clutch has electronic control and another part is mechanical control. Because the electric, solar, and fuel car convertible to the boat, vertical aircraft flying supersonic must be light, an induction clutch will be used because this new induction clutch has several functions and it causes the removal of several parts in this vehicle. I made a version of this clutch in small dimensions with difficulty and I did the necessary tests and drew input and output diagrams. In this article, the new induction clutch is compared with a simple induction clutch and friction clutch, and magnetic clutch.","PeriodicalId":319209,"journal":{"name":"Journal of Aircraft and Spacecraft Technology","volume":"99 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2023-01-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"135058024","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}

{"title":"Radar Cross Section Modelling and Analysis of Static and Dynamic Targets using MATLAB","authors":"Punam Pande, Sreemathy R, M. Turuk","doi":"10.3844/jastsp.2022.1.20","DOIUrl":"https://doi.org/10.3844/jastsp.2022.1.20","url":null,"abstract":": Radar Cross Section (RCS) is an important characteristic of the electromagnetic system for target detection. This study presents detailed modelling of Radar Cross Section (RCS) of static simple objects like sphere, cylinder, triangular plate, circular flat plate, truncated cone, and complex objects using MATLAB Radar toolbox. The RCS modelling of simple objects is also done with MATLAB POFACET GUI 4.3 and the results are compared with the MATLAB Radar toolbox. The RCS of complex objects are vectorially added in MATLAB and modelled in this work. Modelling includes 1. A cylinder with a circular flat plate on both ends 2. A circular cylinder with ellipsoid at front end 3. A truncated cone (frustum) with circular plates at both ends 4. The half ellipsoid with a frustum and the flat plate. The simulation and comparison of the RCS variations in DBSM with respect to aspect angle for parameters such as size and frequency of the simple and complex objects have been carried out in this study. RCS of a complex object with dynamic characteristics is also analysed using the Chi-square probability density function. ’The scope of this study is limited to the objects with deterministic shapes and the combined objects using those shapes. The detailed experimental study on the sphere shows that RCS remains constant in all directions for the sphere. The study also highlights the RCS return is maximum at 180 degrees when the cylinder is aligned horizontally with the RADAR and the minimum RCS is obtained at 90 degrees and 270 degrees. In the case of an ellipsoid, the RCS is maximum at 90 degrees and 270 degrees and minimum at 180 degrees. For the triangular flat plate, the RCS is maximum at 0 degrees and 180 degrees and minimum at 90 degrees. For the truncated cone the RCS has maximum and minimum values at aspect angles of zero degrees and 80 degrees. The model of the frustum with a flat plate at both ends provides maximum RCS due to the frustum and minimum due to flat plate and the normal incidence occurs at 73.3008 degrees. The Swerling models for the fluctuating RCS are also analysed in detail which will be used to measure the RCS of high-speed debris revolving around the earth's surface by the radar in Low Earth Orbit (LEO).","PeriodicalId":319209,"journal":{"name":"Journal of Aircraft and Spacecraft Technology","volume":"33 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2022-01-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"116794206","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}

{"title":"About Gateway","authors":"Relly Victoria Petrescu, F. I. T. Petrescu","doi":"10.3844/jastsp.2020.70.87","DOIUrl":"https://doi.org/10.3844/jastsp.2020.70.87","url":null,"abstract":"Corresponding Author: Relly Victoria Virgil Petrescu ARoTMM-IFToMM, Bucharest Polytechnic University, Bucharest, (CE) Romania Email: rvvpetrescu@gmail.com Abstract: After several postponements or even giving up, NASA finally decided to prepare and launch the long-delayed Moon space station Gateway, which had to be postponed for financial, technical reasons, but also for reasons and calculations about the possibility of assembling it in space and the way of transporting the main components in space, the main problem being the rockets capable of carrying such huge components in space. Today it seems that NASA has managed to solve all these problems and to finalize and in a real way all the details regarding such a complex undertaking.","PeriodicalId":319209,"journal":{"name":"Journal of Aircraft and Spacecraft Technology","volume":"32 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2020-01-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"122987268","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}

{"title":"Structural Colour from Optical Phenomena Caused by Interference with a Thin or Multilayer Film, Photonic Nanocrystals, Light Scattering and Diffraction Grating Effect","authors":"R. Petrescu, R. Aversa, A. Apicella","doi":"10.3844/jastsp.2020.117.143","DOIUrl":"https://doi.org/10.3844/jastsp.2020.117.143","url":null,"abstract":"The paper presents the Ion Plating Plasma Assisted technology that is applied in the area of surface functionalization with the purpose of preserving the structural colour and relics. The interferometric structural colours applied on titanium surfaces were used and tested together with nano-transparent and at the same time achromatic films on the very old ceramic artifact. In order to test the surface restoration, some titanium metal and ceramic supports were used: Firstly, an additive with a metallic beam constructed from titanium parts was used, but also an old tile from the 19th century, having the characteristic of a strong chromatic valence and of a mixed porous and glazed surface. In the experiment, a reactive device with ionic plate spray magnetron was used, capable of operating in Argon or Oxygen environments, for the purpose of depositing TiO2 and SiO2. First, several tests were performed using two plasma treatments in order to define the optimal methods for processing. By depositing TiO2 nano-film on irregular Ti surfaces it was possible to regenerate the light direction based on the surfaces that change its colour and the transparent achromatic quality coatings could be obtained with the help of SiO2 coating. Important in these procedures is the high flexibility of ion plating technology processing. It has been established after several attempts that the treatment of IPO SiO2 surfaces is better and therefore preferable in the case of restoration and preservation of ancient historical plates when the optimized procedure with Ion Beam Electron Microscopy, performed on the porous structure of the plates, was used for final testing, which confirmed the increased flexibility and efficiency of the innovative IPPA technology","PeriodicalId":319209,"journal":{"name":"Journal of Aircraft and Spacecraft Technology","volume":"119 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2020-01-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"116634496","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}

{"title":"Heat Generation/Absorption Effect on Natural Convection Flow in a Vertical Annulus with Time-Periodic Boundary Conditions","authors":"M. Oni, B. Jha","doi":"10.3844/JASTSP.2019.183.196","DOIUrl":"https://doi.org/10.3844/JASTSP.2019.183.196","url":null,"abstract":"The role of heat generation/absorption on natural convection flow formation in a vertical annulus with prescribed time-periodic heating is investigated in this article. The governing continuity, momentum and energy equations are converted into ordinary differential equation using suitable transformations and closed form expressions are obtained for temperature distribution, velocity profile, Nusselt number, skin friction and mass flow rate in terms of Bessel’s function and modified Bessel’s function of first and second kinds. Based on depicted line and contour graphs, results show that the inclusion of heat generation/absorption parameter removes the singularity point in periodic velocity and skin friction for unity Prandtl number. In addition, heat generation/absorption parameter respectively increase/decrease periodic temperature distribution, velocity profile, Nusselt number and skin-friction at the surfaces of the cylinders.","PeriodicalId":319209,"journal":{"name":"Journal of Aircraft and Spacecraft Technology","volume":"37 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2019-07-27","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"131659647","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}

{"title":"Mission Shakti aka Project XSV-1: India’s First Anti-Satellite Test (ASAT)","authors":"Santosh Kosambe","doi":"10.3844/JASTSP.2019.172.182","DOIUrl":"https://doi.org/10.3844/JASTSP.2019.172.182","url":null,"abstract":"The Mission Shakti, also called as Project XSV-1 was India’s first Anti-Satellite Test (ASAT) conducted successfully on 27 March 2019. The PDV-MK II interceptor missile designed and developed by Defence Research and Development Organisation (DRDO) was launched from Dr A.P.J. Abdul Kalam Island to intercept the Microsat-R satellite. The Microsat-R satellite, which acts as a prime target for the mission was India’s imaging satellite manufactured by DRDO and launched into the orbit eight weeks before the test by Indian Space Research Organisation (ISRO). The Project XSV-1 had been under planning since 2016. As India’s space programme is rapidly growing, its nation’s responsibility to safeguard the country’s assets present in outer space. Also, the nation is concerned about the threats it faces in outer space; the ASAT test was conducted to examine the capability of the nation to defend itself in space. The mission was planned at the lowest possible altitude to avoid any risk to the operational space assets. India has demonstrated its capability to legitimate deterrence against increasing threats to nations emerging space assets from various kinds of missiles. With this particular successful test, India becomes the fourth country among an exclusive group of space-faring nations to perform ASAT. The paper provides an overview of the overall Mission Shakti, aka Project XSV-1.","PeriodicalId":319209,"journal":{"name":"Journal of Aircraft and Spacecraft Technology","volume":"7 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2019-07-25","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"127917367","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}

{"title":"State-Space Modelling of a Rocket for Optimal Control System Design","authors":"A. B. Kisabo, Aliyu Funmilayo Adebimpe, Odooh Clement Okwo, Sholiyi Olusegun Samuel","doi":"10.3844/JASTSP.2019.128.137","DOIUrl":"https://doi.org/10.3844/JASTSP.2019.128.137","url":null,"abstract":"In this study, we present the derivation of the mathematical model for a rocket’s autopilot in state-space. The basic equations defining the airframe dynamics of a typical six-Degree-of-Freedom (6DoF) are non-linear and coupled. Separation of these nonlinear coupled dynamics is presented as lateral and longitudinal dynamic equations. The need to determine aerodynamic coefficients and there derivative components are brought to light here, which is the crux of the equations. Methods of obtaining such coefficients and their derivatives in a sequential form are also put forward. After the aerodynamic coefficients and their derivatives are obtained, the next step is to trim and linearize the decoupled non-linear 6DoFs. In a novel way, we presented the linearization of the decoupled 6DoF equations in a generalized form. This provides a lucid and easy way to implement trim and linearization using any computer program.","PeriodicalId":319209,"journal":{"name":"Journal of Aircraft and Spacecraft Technology","volume":"34 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2019-05-25","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"127738694","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}

{"title":"Corrigendum: What is a UFO?","authors":"F. Petrescu, A. Apicella, J. Corchado, B. Akash, R. Aversa, R. Petrescu","doi":"10.3844/JASTSP.2019.58","DOIUrl":"https://doi.org/10.3844/JASTSP.2019.58","url":null,"abstract":"Correction to: Journal of Aircraft and Spacecraft Technology http://doi.org/10.3844/10.3844/jastsp.2017.80.90, published online June 25, 2017; updated April 29, 2019\u0000 The original version of this Article contained Mr. MirMilad Mirsayar as a co-author. Mr. Mirsayar has not contributed to the preparation and publication of this manuscript.\u0000 These errors have now been corrected in the HTML and PDF versions of the Article. http://doi.org/10.3844/10.3844/jastsp.2017.80.90.","PeriodicalId":319209,"journal":{"name":"Journal of Aircraft and Spacecraft Technology","volume":"31 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":"117129681","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}

{"title":"Giant Success for NASA when the InSight Probe has Reached \"Safety\" on Mars","authors":"Relly Victoria Virgil Petrescu","doi":"10.3844/jastsp.2019.1.10","DOIUrl":"https://doi.org/10.3844/jastsp.2019.1.10","url":null,"abstract":"","PeriodicalId":319209,"journal":{"name":"Journal of Aircraft and Spacecraft Technology","volume":"16 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":"121241018","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}

{"title":"Corrigendum: Our Universe","authors":"F. Petrescu, A. Apicella, J. Corchado, B. Akash, R. Aversa, R. Petrescu","doi":"10.3844/JASTSP.2019.59","DOIUrl":"https://doi.org/10.3844/JASTSP.2019.59","url":null,"abstract":"Correction to: Journal of Aircraft and Spacecraft Technology http://doi.org/10.3844/10.3844/jastsp.2017.69.79, published online June 21, 2017; updated April 29, 2019\u0000 The original version of this Article contained Mr. MirMilad Mirsayar as a co-author. Mr. Mirsayar has not contributed to the preparation and publication of this manuscript.\u0000 These errors have now been corrected in the HTML and PDF versions of the Article. http://doi.org/10.3844/10.3844/jastsp.2017.69.79.","PeriodicalId":319209,"journal":{"name":"Journal of Aircraft and Spacecraft Technology","volume":"47 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":"115263646","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}