Forthcoming and Online First Articles

International Journal of Space Science and Engineering

International Journal of Space Science and Engineering (IJSpaceSE)

Forthcoming articles have been peer-reviewed and accepted for publication but are pending final changes, are not yet published and may not appear here in their final order of publication until they are assigned to issues. Therefore, the content conforms to our standards but the presentation (e.g. typesetting and proof-reading) is not necessarily up to the Inderscience standard. Additionally, titles, authors, abstracts and keywords may change before publication. Articles will not be published until the final proofs are validated by their authors.

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International Journal of Space Science and Engineering (3 papers in press)

Regular Issues

  • Numerical study of flow over blunt bodies moving at supersonic speed   Order a copy of this article
    by Devabrata Sahoo, Mohini U. Kamble, Kiran A. Dadhale 
    Abstract: In the present study, shock waves produced over different blunt bodies moving at Mach 2.0 at zero angle of attack have been captured and analysed using computational investigations. Forebodies of distinct bluntness (hemisphere, ellipse, and ogive) are adopted, and the effect of the forebody geometry on the flow parameters is investigated. The flow parameters such as shock stand-off distance and shock strength have been captured over various forebody geometries and correlated with the forebody drag coefficient. With the reduction in the forebody bluntness, the shock stand-off distance and the shock strength are found to be decreasing, resulting in a decrease in the forebody drag coefficient values. The effect of the free-stream supersonic Mach number over a typical blunt body (hemisphere) was also investigated. With increasing freestream Mach number, the shock wave generated ahead the blunt hemisphere moved closer to the forebody and an increase in the forebody drag was observed.
    Keywords: supersonic; blunt bodies; drag reduction; shock stand-off distance.
    DOI: 10.1504/IJSPACESE.2021.10039595
     
  • Feasibility assessment of a small Earth observation satellite mission propelled with hydrogen peroxide system on a very low Earth orbit   Order a copy of this article
    by Tomasz Noga, Tomasz Zawistowski, Adrian Parzybut, Maciej Kalarus 
    Abstract: Earth observation (EO) is a popular mission objective of satellite systems. A typical optical EO satellite occupies a LEO orbit which allows to achieve resolutions required for their applications with optics that fits in a medium-sized bus. One of the alternatives is a small satellite with a propulsion module operating on a very low Earth orbit (VLEO.) While this approach has a number of challenges, it can result in small, low-price satellites capable of achieving resolutions comparable with standard EO satellites on LEO orbit. This paper describes the satellite platform that can potentially be used in the VLEO orbit. Image quality and observation instrument aspects as well as an impact of VLEO orbit on a mission design and its cost are discussed. Justification of a propulsion concept follows, and a parametric model of propulsion module is described. A mission analysis estimating mission durations at VLEO is described and results are discussed.
    Keywords: very low Earth orbit; VLEO; Earth observation; propulsion; satellite; hydrogen peroxide; mission concept.
    DOI: 10.1504/IJSPACESE.2022.10050729
     
  • Conceptual design of remote sensing microsatellite for Martian surface   Order a copy of this article
    by M. Rudresh, S. Preethi, A. Anjali, S. Akshaya, H. Aishwarya 
    Abstract: The project aims to develop a remote sensing satellite for observing Mars. Microsatellites will be incompetent to traverse Mars autonomously; hence an alternate fail-proof is to deploy multiple microsatellites using a mothership with adequate fuel. The microsatellite performs its operation in a polar orbit that integrates Mars Colour Camera and Thermal Infrared Imaging Spectrometers as payloads and utilises components off the shelf to serve individual subsystem requirements. The chemical propulsion subsystem utilises a monopropellant employing a 1-N thruster. The power subsystem generates and distributes the necessary power to function efficiently using its 18 solar panels. The communication subsystem enables signal transmission between Earth and Mars through its short and long-range broadcast equipment. The unique structural frame of the microsatellite offers a high strength-to-weight ratio during the entirety of the mission. The microsatellite proposes an opportunity for university students to observe Mars at an economically low cost by employing current technology.
    Keywords: microsatellite; Mars; design; interplanetary; rendezvous; subsystems; propulsion; attitude control; structure; remote sensing.
    DOI: 10.1504/IJSPACESE.2022.10044502
     

 

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