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Journal Cover International Journal of Space Science and Engineering
  [6 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  [420 journals]
  • Guaranteed ellipsoidal estimation for satellite formation flying collision
    • Authors: G. Vukovich, Y. Kim
      Pages: 77 - 90
      Abstract: Collision avoidance among satellites flying in formation is a subject of great current interest. Approaches to this problem have been based primarily on probabilistic considerations. In this paper, we present a method based on guaranteed ellipsoid estimation, which is applied to a low earth orbit leader-follower satellite formation illustrating the evolution of bounding ellipsoids. This is compared with the results of deterministic inputs acting on the system.
      Keywords: formation flying; collision avoidance; guaranteed ellipsoidal estimation; satellite formations; satellites; low earth orbit; LEO; leader-follower formation; bounding ellipsoids
      Citation: International Journal of Space Science and Engineering, Vol. 4, No. 2 (2016) pp. 77 - 90
      PubDate: 2017-01-13T23:20:50-05:00
      DOI: 10.1504/IJSPACESE.2016.081560
      Issue No: Vol. 4, No. 2 (2017)
  • Tether deployment with in-plane angular and explicit velocity constraints
           by barrier Lyapunov function
    • Authors: Ming Liu, Xingqun Zhan, Bing Zhu
      Pages: 91 - 105
      Abstract: Space tethers have been used for many space applications for decades. However, how to deploy a tethered system in a non-overshooting and stable way is still an unsolved issue up to now. Especially for passive deployment devices where positive deploy velocity is an essential requirement. In addition, in-plane angular amplitude is another issue that we should restrict to prevent tether become slack when it transgress 45°. This paper proposes a new control method to satisfy the two main constraints. First, we use a modified barrier Lyapunov Function method to design a deploy trajectory, which could ensure the in-plane angular stable and restrict into a small range as well as a positive deploy velocity. Second, we employ a feedback linearisation to realise a non-overshooting tracking. Simulations demonstrate that the scenario is successful in keeping a small in-plane angular within 0.25 radian, and positive deploy velocity and tension, meanwhile guaranteeing the non-overshooting tether length state.
      Keywords: tetherd space systems; non-overshooting deployment; barrier Lyapunov function; BLF; feedback linearisation; tether deployment; in-plane angular constraints; velocity constraints; space tethers; simulation; tether satellites; spacecraft
      Citation: International Journal of Space Science and Engineering, Vol. 4, No. 2 (2016) pp. 91 - 105
      PubDate: 2017-01-13T23:20:50-05:00
      DOI: 10.1504/IJSPACESE.2016.081562
      Issue No: Vol. 4, No. 2 (2017)
  • Orbital design and optimal control of cislunar transport mission using
           spinning tether system
    • Authors: Hong-Shi Lu, Chang-Qing Wang, Ai-Jun Li, Zabolotnov Yuriy
      Pages: 106 - 120
      Abstract: To transport payload into lunar transfer orbit using spinning tether system, reusable payload transport design were proposed and analysed. When final design was decided, open-loop reference control of payload transport stage was developed using optimal control theories. For the insufficient thrust case in LEO orbit, Hamiltonian on/off control was used to solve the problem. Numerical results indicate that the final transport design is able to transport payload into desired orbit, and the control law could satisfy mission requirement. Compared to conventional rocket transport, much less propellant is required by the spinning system with system reusability.
      Keywords: tether satellites; tethered space systems; TSS; payload transport; optimal control; Hamiltonian energy; orbital design; optimal control; cislunar transport missions; spinning tether systems; space tethers; low earth orbit; LEO; system reusability; propellant use
      Citation: International Journal of Space Science and Engineering, Vol. 4, No. 2 (2016) pp. 106 - 120
      PubDate: 2017-01-13T23:20:50-05:00
      DOI: 10.1504/IJSPACESE.2016.081567
      Issue No: Vol. 4, No. 2 (2017)
  • Post Newtonian gravity, a new simpler approach
    • Authors: Hong-Shi Lu, Chang-Qing Wang, Ai-Jun Li, Zabolotnov Yuriy
      Pages: 121 - 137
      Abstract: Galileo and Tycho Brahe made extensive astronomical observations which led Kepler to formulate his laws of planetary motion. All these observations were of relative motion. This led Newton to propose his theory of gravity, which could just as well have been expressed in a form that does not involve the concept of force. The approach in this paper extends the Newtonian theory and the special theory of relativity by including relative velocity based on the form of the measured data and also by comparison with electromagnetic effects. Application of the new single equation to the precession of the perihelion of Mercury, the gravitational deflection of light, the Shapiro time delay, the Schwarzschild radius and the last stable orbit gives results which agree with those of general relativity. Gravitational waves are also discussed. This approach could be used to determine non-Newtonian variations in the trajectories of satellites.
      Keywords: gravity; gravitomagnetics; special theory of relativity; satellite orbits; last stable orbit; Shapiro time delay; gravitational waves; Newtonian theory; relative velocity; precession; perihelion of Mercury; light deflection; Schwarzschild radius; satellite trajec
      Citation: International Journal of Space Science and Engineering, Vol. 4, No. 2 (2016) pp. 121 - 137
      PubDate: 2017-01-13T23:20:50-05:00
      DOI: 10.1504/IJSPACESE.2016.081569
      Issue No: Vol. 4, No. 2 (2017)
  • Optimal control of satellite formations due to oblateness perturbations
    • Authors: Hong-Shi Lu, Chang-Qing Wang, Ai-Jun Li, Zabolotnov Yuriy
      Pages: 138 - 165
      Abstract: The nonlinear satellite dynamics, including gravitational perturbations of zonal harmonics up to is utilised to search for the optimal fuel cost for maintaining a formation is investigated. The system dynamics were developed in an Earth-centred inertial coordinate frame using the methods of Hamiltonian dynamics. Continuous dynamic optimisation theory was used to minimise fuel requirements, resulting in a continuous thrust. The uncontrolled reference trajectory of the formation was restricted to a circular inclined orbit. Additionally, further fuel savings are discussed with possible modifications to orbit altitude, formation radius, and variations in the defined performance index.
      Keywords: optimal control; satellite formations; nonlinear dynamics; gravitational perturbations; oblateness perturbations; formation flying; zonal harmonics; fuel costs; system dynamics; Hamiltonian dynamics; continuous dynamic optimisation; continuous thrust; circular i
      Citation: International Journal of Space Science and Engineering, Vol. 4, No. 2 (2016) pp. 138 - 165
      PubDate: 2017-01-13T23:20:50-05:00
      DOI: 10.1504/IJSPACESE.2016.081571
      Issue No: Vol. 4, No. 2 (2017)
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