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Journal Cover   International Journal of Space Science and Engineering
  [2 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  [401 journals]
  • Nonlinear mechanical system on board the international space station:
           the IVIDIL experiment
    • Pages: 1 - 15
      Abstract: The aim of this work is to study the vibrational impact of the shaker during a past European Space Agency (ESA) experiment. To do so, we have analysed four accelerometric signals downloaded from the National Aeronautics and Space Administration (NASA) and Principal Investigator Microgravity Services (PIMS) website. The first two ones came from the sensor located in the Columbus module and correspond to time periods in which the shaker is inactive or active respectively. The other two came from the Destiny Laboratory and covers the above mentioned different time intervals. The results obtained indicate that the spectral fingerprints of the shaker are weakly present in the signals gathered from Destiny Laboratory. In addition, the consideration of all histograms shows that the shaker modifies the normal distribution of the accelerometric data introducing nonlinearities in the distribution of energy. The possible quadratic origin of these mechanic nonlinearities is studied using the corresponding bispectrum and bicoherence of the accelerometric signals.
      Keywords: accelerometric analyses; microgravity; spectrum; higher order spectra; bispectrum; bicoherence; nonlinear mechanical systems; international space station; vibration impact
      Citation: International Journal of Space Science and Engineering, Vol. 3, No. 1 (2015) pp. 1 - 15
      PubDate: 2015-05-13T23:20:50-05:00
      DOI: 10.1504/IJSPACESE.2015.069347
      Issue No: Vol. 3, No. 1 (2015)
  • Manoeuvres of spacecraft with flexible appendage in obstacle environment
    • Authors: Xiaojian Wu, Hao Wen, Ti Chen
      Pages: 16 - 30
      Abstract: This paper presents a collision avoidance control scheme for position and large angle manoeuvres of spacecraft with flexible appendage in obstacle environment. Firstly, the method of Lagrange equation is used to model the spacecraft with beam-type appendage. Secondly, independent position and attitude controllers are designed by only using the state of spacecraft as feedback information, without any need to measure the elastic deformation of the beam-type appendage. And then, collision avoidance based on real-time distance information is achieved by applying additional artificial repulsive force and torque to the spacecraft. Bounding boxes in the form of superquadric surfaces are exploited to compute the distance between bodies, and the scheme accounts for not only the geometric shape of the obstacle but also that of the spacecraft with flexible appendage. Finally, the effectiveness of proposed control scheme is demonstrated by numerical case studies.
      Keywords: spacecraft manoeuvres; spacecraft flexible appendages; obstacle avoidance; position control; attitude control; superquadric surfaces; collision avoidance; controller design
      Citation: International Journal of Space Science and Engineering, Vol. 3, No. 1 (2015) pp. 16 - 30
      PubDate: 2015-05-13T23:20:50-05:00
      DOI: 10.1504/IJSPACESE.2015.069356
      Issue No: Vol. 3, No. 1 (2015)
  • Characterisation of operational amplifier performance as a function of
           total ionising dose at both room and cryogenic operating temperatures for
           space applications
    • Authors: Jared Johnson, Michael G. Daly, David M. Hiemstra
      Pages: 31 - 49
      Abstract: Commercial off the shelf operational amplifiers based on junction field-effect transistors and bipolar transistors were tested under gamma radiation at both room temperature and 77 K in parallel to determine their suitability for space applications. The irradiation while under cryogenic conditions simulates the environment that these devices would experience on small planetary missions where environmental control is not possible due to lack of energy generation capacity. The performance characteristics studied were: offset voltage, total harmonic distortion, change in open loop gain, and noise voltage. A single amplifier remained in specification through 100 krad(Si) and at 77 K. Differences in radiation tolerance were found between room temperature and cryogenic operation for the operational amplifiers under test. In some cases, the best performance was obtained at low temperatures while for others it was obtained at room temperature. The results highlight the need to perform these tests under operational conditions when extreme environment operation is required.
      Keywords: space applications; operational amplifiers; low-temperature op-amps; commercial op-amps; off-the-shelf op-amps; field-effect transistors; bipolar transistors; gamma radiation; simulation; small planetary missions; offset voltage; tot
      Citation: International Journal of Space Science and Engineering, Vol. 3, No. 1 (2015) pp. 31 - 49
      PubDate: 2015-05-13T23:20:50-05:00
      DOI: 10.1504/IJSPACESE.2015.069357
      Issue No: Vol. 3, No. 1 (2015)
  • Short arc radar observation considerations in covariance intersection
    • Authors: Gary Goff, Jonathan T. Black, Joseph A. Beck
      Pages: 50 - 67
      Abstract: Given limited observation data, an initial orbit fit is often inaccurate with a large associated error covariance. The affect of the quantity of observations on the error covariance and orbit fit is explored. This paper investigates the entire initial orbit determination estimation chain using simulated ground radar data and filter estimation techniques. A probabilistic approach is developed to determine a specific number of radar observations to estimate the future location of a non-cooperative object within an ellipsoidal error tolerance. Specifically, the article evaluates the estimation chain from observations to orbit fit for covariance realism and develops a numerical sampling technique to calculate the probability of meeting a covariance requirement given a set number of observations, orbit type, and radar performance.
      Keywords: orbit determination; covariance estimation; non-cooperative tracking; short-arc initial orbit; collision avoidance; covariance realism; short arc radar observation; covariance intersection; error covariance; orbit fit; simulation; ground radar; filter es
      Citation: International Journal of Space Science and Engineering, Vol. 3, No. 1 (2015) pp. 50 - 67
      PubDate: 2015-05-13T23:20:50-05:00
      DOI: 10.1504/IJSPACESE.2015.069358
      Issue No: Vol. 3, No. 1 (2015)
  • Generalised multi-impulsive manoeuvres for optimum spacecraft
           rendezvous in near-circular orbit
    • Pages: 68 - 88
      Abstract: This work describes the design of an impulsive manoeuvres' planner meant for onboard autonomous optimum formation flying reconfigurations in near-circular orbit. The whole variation of the relative orbit is stepwise achieved through intermediate configurations, so that passive safety and delta-v consumption minimisation are pursued. The description of the relative motion is accomplished in terms of relative orbital elements and the reconfiguration plan takes into account mean effects due to the Earth oblateness coefficient and differential drag. Manoeuvres consist of sets of triple tangential impulses and a single out-of-plane burn to establish each intermediate configuration. They are scheduled in time intervals compliant with the user-defined permissible time control windows.
      Keywords: formation flying; formation reconfiguration; autonomy; relative orbital elements; ROEs; impulsive manoeuvres; spacecraft manoeuvres; optimisation; spacecraft rendezvous; near-circular orbit; manoeuvre planning; relative motion; Earth oblateness coefficient; d
      Citation: International Journal of Space Science and Engineering, Vol. 3, No. 1 (2015) pp. 68 - 88
      PubDate: 2015-05-13T23:20:50-05:00
      DOI: 10.1504/IJSPACESE.2015.069361
      Issue No: Vol. 3, No. 1 (2015)
  • Conditional possibility of spacecraft propulsion at superluminal speeds
    • Pages: 89 - 92
      Abstract: The concept at hand deals primarily with the application of the conditional replacement technique (CRT) (Pais, 1991) to Special Relativity Theory. It is observed that under certain physical conditions, the singularity expressed by the relativistic stretch factor 'gamma' as the spacecraft's speed (v) approaches the speed of light (c), is no longer present in the physical picture. This involves the instantaneous removal of energy-mass from the system (spacecraft) when the spacecraft's speed reaches v = c/2. Hence under such conditions, faster than light spacecraft propulsion, is feasible. The original concept at hand does not violate the Special Theory of Relativity, it rather builds on its foundations.
      Keywords: faster than light travel; theory of special relativity; spacecraft propulsion; superluminal speeds; conditional replacement technique; CRT; spacecraft speed; space travel
      Citation: International Journal of Space Science and Engineering, Vol. 3, No. 1 (2015) pp. 89 - 92
      PubDate: 2015-05-13T23:20:50-05:00
      DOI: 10.1504/IJSPACESE.2015.069339
      Issue No: Vol. 3, No. 1 (2015)
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