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International Journal of Space Science and Engineering    [4 followers]  Follow    
  Hybrid Journal Hybrid journal (It can contain Open Access articles)
     ISSN (Print) 2048-8459 - ISSN (Online) 2048-8467
     Published by Inderscience Publishers Homepage  [381 journals]
  • DelFFi: formation flying of two CubeSats for technology, education and
    • Authors: Jian Guo, Eberhard Gill
      Pages: 113 - 127
      Abstract: Under the QB50 framework, the Delft University of Technology are developing a formation flying mission called DelFFi. The objectives of the DelFFi mission are to demonstrate advanced formation flying technologies with CubeSats, provide an educational framework for students and enable enhanced science return from the QB50. Both satellites will be identical triple-unit CubeSats, each being equipped with a highly miniaturised propulsion system in addition to the science payload. This configuration will allow to demonstrate advanced formation flying as well as scientific data collection. Based on an analysis of guidance, navigation and control needs for formation flying in very low altitude orbits, a staggered approach of increasingly complex operational scenarios for formation flying is developed, analysed and discussed. Implementation options for critical enabling formation flying technology and platform subsystems are presented.
      Keywords: Cubesat; satellite formation flying; satellite propulsion; satellites; miniaturised propulsion systems; scientific data collection; satellite guidance; satellite navigation; satellite control; low altitude orbits; higher education
      Citation: International Journal of Space Science and Engineering, Vol. 1, No. 2 (2013) pp. 113 - 127
      PubDate: 2013-06-12T23:20:50-05:00
      DOI: 10.1504/IJSPACESE.2013.054452
      Issue No: Vol. 1, No. 2 (2013)
  • Optimal trajectory design of a deorbiting electrodynamic tether system
    • Authors: Rui Zhong, Zheng H. Zhu
      Pages: 128 - 141
      Abstract: This paper studies the optimal control problem of a nano-satellite deorbiting by a short electrodynamic tether. The optimal control theory is introduced by forming the control problem as a cost index minimisation subjected to several constraints. A direct method based on Hermite-Simpson discretisation is adopted to solve the constraint cost minimisation problem, resulting in an optimal trajectory including the time history of the states and control input, which achieves best deorbiting efficiency and libration stability simultaneously under the given mission requirements. In order to reduce the computation efforts, the continuous deorbiting process of an electrodynamic tether is discretised into a sequential time intervals, where during each interval the slowly varying orbital parameters of the electrodynamic tether are assumed constant. Thus, the whole optimal trajectory is obtained by combining the solutions to the optimal control problems in the intervals. Numerical simulations are performed to test the performance of the optimal trajectory by applying the control input profile to an electrodynamic tether under complex environment perturbations.
      Keywords: electrodynamic tethers; EDTs; attitude control; optimal control; direct method; Hermite-Simpson discretisation; space science; optimal design; trajectory design; deorbiting tether systems; nanosatellites; numerical simulation
      Citation: International Journal of Space Science and Engineering, Vol. 1, No. 2 (2013) pp. 128 - 141
      PubDate: 2013-06-12T23:20:50-05:00
      DOI: 10.1504/IJSPACESE.2013.054459
      Issue No: Vol. 1, No. 2 (2013)
  • Multiple-target analysis of adaptive detection of partially correlated
           χ² targets
    • Authors: Rui Zhong, Zheng H. Zhu
      Pages: 142 - 176
      Abstract: Target radar characteristics are the driving force in the design and performance analysis of all radar systems. The fluctuation rate of a radar target may vary from essentially independent return amplitudes from pulse-to-pulse to significant variation only on a scan-to-scan basis. An important class of targets is represented by the so-called moderately fluctuating Rayleigh and χ² targets, which, when illuminated by a coherent pulse train, return a train of correlated pulses with a correlation coefficient in the range 0 < ρ < 1 (intermediate between SWII and SWI models in the case of Rayleigh targets) and (intermediate between SWIV and SWIII models in the case of χ² targets). The detection of partially correlated χ² targets with two and four degrees of freedom is therefore of great importance. This paper describes the detection performance analysis of the ordered-statistics (OS) based constant false alarm rate (CFAR) detectors for the case where the radar receiver post-detection integrates M pulses of an exponentially correlated signal from targets which exhibit χ² statistics with two and four degrees of freedom. Exact formulas for the detection probabilities are derived, in the absence as well as in the presence of spurious targets, which are assumed to be fluctuating in accordance with the χ² fluctuation model with the same degrees of freedom.
      Keywords: partially-correlated chi² targets; constant false alarm rate; CFAR detectors; multiple target environments; post detection integration; ordered-statistics processors; multiple targets; radar targets; Rayleigh targets; detection performance; fluctua
      Citation: International Journal of Space Science and Engineering, Vol. 1, No. 2 (2013) pp. 142 - 176
      PubDate: 2013-06-12T23:20:50-05:00
      DOI: 10.1504/IJSPACESE.2013.054450
      Issue No: Vol. 1, No. 2 (2013)
  • Computation of free space capacitance of cylinder and truncated cone for
           spacecraft circuit modelling
    • Authors: B. Karthikeyan, V.K. Hariharan
      Pages: 177 - 189
      Abstract: Absolute free space capacitance of cylinder and truncated cone is computed for spacecraft equivalent circuit modelling. The method of moment with triangular patch modelling based on the pulse basis function is employed. The curved triangular surfaces are represented by parametric geometric transformation. The moment integral is evaluated numerically in a parameter space using Gaussian quadrature algorithm and Duffy transformation method. The results are good matching with the previously published results. The derived expressions are simple and also fit for the spacecraft charging analysis software. Since this approach is more general, any curved surfaces that are encountered during spacecraft modelling, free space capacitance of that surface can be easily evaluated and hence, spacecraft potential can be predicted accurately.
      Keywords: free space capacitance; electrostatic discharge; spacecraft charging; space environment; cylinders; truncated cones; spacecraft circuit modelling; triangular patch modelling; moment integral; curved surfaces; spacecraft modelling
      Citation: International Journal of Space Science and Engineering, Vol. 1, No. 2 (2013) pp. 177 - 189
      PubDate: 2013-06-12T23:20:50-05:00
      DOI: 10.1504/IJSPACESE.2013.054455
      Issue No: Vol. 1, No. 2 (2013)
  • Controllable-structure semi-ballistic reentry vehicle tracking
           with hybrid-level multiple-model estimation
    • Authors: Yongqi Liang, Jianping Liu, Jing Li, Meiqin Liu
      Pages: 190 - 204
      Abstract: Tracking of a high manoeuvring reentry vehicle has become a key problem in interception. The vehicle is characterised by a lift force generated by the vehicle's unbalanced structure or form, and the controllable structure and form complicate the vehicle's manoeuvre. Therefore, the paper deals the vehicle with the lift-drag ratio model; characteristic of the vehicle's uncertain mode is analysed, and the multiple-model estimator is constructed on the representative mode. To have a stable estimator, we proposed the hybrid-level multiple-model estimator that is consistent with the manoeuvring vehicle's uncertain mode. The key parameter of the vehicle's model is refined to decrease the mismatch of the set of models and the true mode. The effectiveness of the proposed algorithm is checked by numerical simulation.
      Keywords: reentry vehicle interception; hybrid-level model sets; space filling model sets; high manoeuvring reentry vehicles; state estimation; hybrid estimation; multiple-model estimation; modelling; controllable structure; semi-ballistic reentry vehicles;
      Citation: International Journal of Space Science and Engineering, Vol. 1, No. 2 (2013) pp. 190 - 204
      PubDate: 2013-06-12T23:20:50-05:00
      DOI: 10.1504/IJSPACESE.2013.054462
      Issue No: Vol. 1, No. 2 (2013)
  • Pressure induced active control mechanism for a pneumatically supported
           space tower
    • Authors: R.K. Seth, B.M. Quine, Z.H. Zhu
      Pages: 205 - 214
      Abstract: This paper presents the development of an active control system based upon pressure induced control mechanisms to maintain the structural stability of an inflatable space tower. A pneumatically supported space tower comprises high structural strength fabric beams inflated at an appropriate pressure to maintain strength and structural configuration requires an active control mechanism to control attitude. A pressure control mechanism that utilises the differential change of pressure inside the inflated multiple-beam structure is investigated experimentally to determine its ability to maintain vertical orientation. Results indicate that the pressure induced control mechanisms can efficiently control the attitude of the large inflated structure such as pneumatically supported space tower.
      Keywords: active control; inflatable space towers; pneumatic beams; pneumatic structures; structural stability; inflatable towers; pressure control; vertical orientation; attitude control; inflated structures
      Citation: International Journal of Space Science and Engineering, Vol. 1, No. 2 (2013) pp. 205 - 214
      PubDate: 2013-06-12T23:20:50-05:00
      DOI: 10.1504/IJSPACESE.2013.054464
      Issue No: Vol. 1, No. 2 (2013)
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