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Journal Cover International Journal of Space Science and Engineering
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   Hybrid Journal Hybrid journal (It can contain Open Access articles)
   ISSN (Print) 2048-8459 - ISSN (Online) 2048-8467
   Published by Inderscience Publishers Homepage  [416 journals]
  • Ground based testing of space tether deployment using an air bearing
           inclinable turntable
    • Authors: Udai Bindra, Zheng H. Zhu
      Pages: 1 - 17
      Abstract: This paper discusses the development of a ground based experimental environment that can mimic the deployment dynamics of tethered satellites in orbit. The setup consists of an air-bearing inclinable turntable, whose inclination and rotation rate can be adjusted individually. Appropriate scaling factors are developed for the various forces acting on the daughter satellite as well as for physical experimental parameters including the length of the tether, the mass of the daughter satellite, the deployment speed and the tension along the tether. The scaling factors are used to compare the behaviour of the tethered system in the experiment to that in orbit.
      Keywords: space tethers; air bearing tables; inclinable turntables; ground based testing; scaling factors; tether deployment; tether dynamics; tethered satellites; inclination; rotation rate
      Citation: International Journal of Space Science and Engineering, Vol. 4, No. 1 (2016) pp. 1 - 17
      PubDate: 2016-08-24T23:20:50-05:00
      DOI: 10.1504/IJSPACESE.2016.078571
      Issue No: Vol. 4, No. 1 (2016)
  • Convergence evaluation of quaternion-based attitude estimation using
           MEMS sensors
    • Authors: Mohammad Samani, Masod Mirzaei Teshnizi
      Pages: 18 - 30
      Abstract: In this study, the extended Kalman filter was firstly explicated on the basis of quaternion. In order for the attitude estimation to be improved, multiplicative quaternion-based Kalman filter was presented. This filter helps to increase the convergence, and decrease sensitivity to the primitive conditions. In this research, inertia and reference sensors have been utilised for attitude estimation. Also, modelling and simulation of quaternion-based attitude estimation is initially performed and partially verified. Subsequently, an approximate statistical method was utilised to evaluate filter convergence. According to the simulation result, attitude and bias gyroscope fall in a safe region. Finally, a Mont Carlo simulation was also performed. The comparison and verification of statistical results indicated a small and acceptable deviation between the two approaches, thus, it can be concluded that the simpler approximate statistical approach is also valid for elevation filter convergence and can provide valuable knowledge needed in the filter design.
      Keywords: attitude estimation; multiplicative quaternion based Kalman filter; MQKF; Monte Carlo simulation; statistical methods; filter convergence; MEMS sensors; modelling; microelectromechanical systems; extended Kalman filter; EKF; filter design; satellite attitude; sat
      Citation: International Journal of Space Science and Engineering, Vol. 4, No. 1 (2016) pp. 18 - 30
      PubDate: 2016-08-24T23:20:50-05:00
      DOI: 10.1504/IJSPACESE.2016.078576
      Issue No: Vol. 4, No. 1 (2016)
  • The analytical methods for gravity field measurement performance of
           satellite formation
    • Authors: Hongwei Liu, Zhaokui Wang, Yulin Zhang
      Pages: 31 - 44
      Abstract: Compared with gravity field measurement missions of low-low satellite-to-satellite tracking, for example GRACE, and GRACE follow-on, satellite formation can greatly improve the resolution and accuracy of gravity field measurement because of adding inter-satellite range-rate measurements in radial and normal direction. So it is important to pay more attentions on gravity field measurement of satellite formation. The physical mechanism of obtaining gravity signals via satellite payloads is a fundamental question in satellite formation gravity measurement. Because of multiple gravity satellite payloads and strong coupling between these payloads, mission design strongly depends on computer simulations, with suboptimal designs only achieved. The effective way of optimisation design of satellite formation mission has not been found. To solve this problem, firstly the analytical model of gravity field measurement of satellite formation is established by combining gravity field measurement performance of low-low satellite-to-satellite tracking in three orthogonal directions, i.e., the radial, tracking and normal direction. Secondly, based on this analytical model, the influences of orbital altitude, satellite formation configuration parameters, and payload capacities are analysed. Then the optimisation design method of formation configuration and payload capacities are proposed, which provides theoretical basis for mission analysis and design of gravity field measurement.
      Keywords: satellite formation; mission analysis; gravity field measurement; optimisation design; mission parameters; space missions; gravity signals; satellite payloads; simulation; analytical modelling; orbital altitude; formation configurations; payload capacities; satel
      Citation: International Journal of Space Science and Engineering, Vol. 4, No. 1 (2016) pp. 31 - 44
      PubDate: 2016-08-24T23:20:50-05:00
      DOI: 10.1504/IJSPACESE.2016.078577
      Issue No: Vol. 4, No. 1 (2016)
  • Euphoria-filter: a robust H2/H∞ technique amenable to the
           Lisa-Pathfinder thruster faults
    • Authors: Nikolaos Tantouris, Kleanthis Dellios
      Pages: 45 - 63
      Abstract: The main purpose of the fault detection and isolation (FDI) function is to maintain the spacecraft (S/C) or any other unnamed aerial vehicle (UAVs) operational and safe (healthy) as required by the mission. Thus, robust FDI is the key property for all aerospace missions and applications, wherever autonomy is of paramount importance. Current work provides a focused insight and lessons learned of the euphoria-filter, a robust H<SUB align="right">2/H∞ model-based FDI technique, with specific application to the Lisa-Pathfinder thruster failures.
      Keywords: euphoria filter; fault detection; fault isolation; satellites; actuators; thrusters; Lisa Pathfinder; LPF; autonomy; robustness; thruster faults; spacecraft; unnamed aerial vehicles; UAVs; Monte Carlo simulation
      Citation: International Journal of Space Science and Engineering, Vol. 4, No. 1 (2016) pp. 45 - 63
      PubDate: 2016-08-24T23:20:50-05:00
      DOI: 10.1504/IJSPACESE.2016.078578
      Issue No: Vol. 4, No. 1 (2016)
  • Robust linear PID controller for satellite attitude stabilisation and
           attitude tracking control
    • Authors: You Li, Zhaowei Sun, Dong Ye
      Pages: 64 - 75
      Abstract: In this paper, a linear robust PID controller is presented for satellite attitude stabilisation and attitude tracking control. The PID controller presented in this paper has the advantage that: 1) the Lyapunov function is modified thus the stability of the system is easier to prove; 2) the constraints of the parameters are broadened thus parameters are easier to choose comparing with existing methods; 3) the controller is robust to bounded disturbance torque and the satellite inertia matrix; 4) the controller is linear thus it is convenient for practical application. The proof of the stability and the constraints of the parameters are given in this paper. The simulation results verify the feasibility of the controller presented in this paper.
      Keywords: PID control; robust control; linear control; controller design; attitude stabilisation control; attitude tracking control; satellite attitude; satellites; simulation; bounded disturbance torque; satellite inertia matrix
      Citation: International Journal of Space Science and Engineering, Vol. 4, No. 1 (2016) pp. 64 - 75
      PubDate: 2016-08-24T23:20:50-05:00
      DOI: 10.1504/IJSPACESE.2016.078581
      Issue No: Vol. 4, No. 1 (2016)
School of Mathematical and Computer Sciences
Heriot-Watt University
Edinburgh, EH14 4AS, UK
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Fax: +00 44 (0)131 4513327
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