Hybrid journal (It can contain Open Access articles) ISSN (Print) 2048-8459 - ISSN (Online) 2048-8467 Published by Inderscience Publishers[439 journals]
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Authors:Tomasz Noga, Tomasz Zawistowski, Adrian Parzybut, Maciej Kalarus Pages: 293 - 321 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 Citation: International Journal of Space Science and Engineering, Vol. 6, No. 4 (2023) pp. 293 - 321 PubDate: 2023-05-22T23:20:50-05:00 DOI: 10.1504/IJSPACESE.2023.131041 Issue No:Vol. 6, No. 4 (2023)
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Authors:Devabrata Sahoo, Mohini U. Kamble, Kiran A. Dadhale Pages: 322 - 334 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 Citation: International Journal of Space Science and Engineering, Vol. 6, No. 4 (2023) pp. 322 - 334 PubDate: 2023-05-22T23:20:50-05:00 DOI: 10.1504/IJSPACESE.2023.131040 Issue No:Vol. 6, No. 4 (2023)
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Authors:M. Rudresh, S. Preethi, A. Anjali, S. Akshaya, H. Aishwarya Pages: 335 - 349 Abstract: This 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 Citation: International Journal of Space Science and Engineering, Vol. 6, No. 4 (2023) pp. 335 - 349 PubDate: 2023-05-22T23:20:50-05:00 DOI: 10.1504/IJSPACESE.2023.131047 Issue No:Vol. 6, No. 4 (2023)
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Authors:Manav Kumar, Sharifuddin Mondal Pages: 350 - 371 Abstract: In this work, well known existing estimation algorithms like extended Kalman filter (EKF) and unscented Kalman filter (UKF) with different adaptive extensions are implemented on target tracking problem for passive tracking. To deal with model uncertainty and uncertain noises, the process and measurement noise covariances are adapted based on innovation and residual sequences. Different adaptation rules for adjusting the noise covariance are examined. For the robustness performance analysis of each algorithm, target loss that occurred at last time of simulation is accounted for with consideration of a 2% estimation error. The effectiveness of filter performance is evaluated on the basis of root mean square error, average target loss and relative computational time with Monte Carlo simulation. Simulation results demonstrate that adaptive version of traditional filters have improved tracking performance with a significant computational burden in terms of estimation accuracy and track loss. Keywords: extended Kalman filter; EKF; unscented Kalman filter; UKF; KF-UKF; adaptive estimation; passive tracking; target loss Citation: International Journal of Space Science and Engineering, Vol. 6, No. 4 (2023) pp. 350 - 371 PubDate: 2023-05-22T23:20:50-05:00 DOI: 10.1504/IJSPACESE.2023.131058 Issue No:Vol. 6, No. 4 (2023)
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Authors:Muhammad Rizki Zuhri, Mazi Prima Reza, Luqman Faturrohim Pages: 372 - 392 Abstract: Inclination change manoeuvre is widely performed to correct the inclination to the desired value. However, inclination manoeuvres studied or performed so far assumed that the thrust profile is constant maximum. In fact, for inclination change manoeuvre, the satellite position in orbit affects the Δ<i>i</i>/Δ<i>t</i> efficiency and the manoeuvre will be best performed at nodes. This research investigated the optimum profile thrust for inclination change manoeuvre for small inclination changes only on a case study of LAPAN-A4 satellite. The optimisation involved several methods: using GMAT software and using genetic algorithm which is divided further into general and special perturbation. The results showed a good agreement that the most optimum thrust profile for this case is a constant maximum thrust profile. Keywords: thrust profile; optimisation; LAPAN-A4; inclination manoeuvre Citation: International Journal of Space Science and Engineering, Vol. 6, No. 4 (2023) pp. 372 - 392 PubDate: 2023-05-22T23:20:50-05:00 DOI: 10.1504/IJSPACESE.2023.131059 Issue No:Vol. 6, No. 4 (2023)
Hybrid journal (It can contain Open Access articles)
