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Journal Cover International Journal of Space Science and Engineering
   Journal TOC RSS feeds Export to Zotero [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  [388 journals]
  • Command of a multi-tier robotic network with local decision-making
    • Authors: Ines Hakim Hbaieb, Mohamed Ali Omri
      Pages: 225 - 247
      Abstract: This paper presents a distributed system for commanding a collection of multiple heterogeneous craft which have various levels of mobility (orbital, aerial and surface) and visibility. Under this model, goals are defined at a high level and goal-fulfilment is delegated to subordinate craft (or groups of subordinate craft). Each craft is responsible for its own decision-making (based on heuristics and incorporating local information) to determine how to best effect the completion of the goals that it is delegated. A scenario for a resource location and assessment mission is used to demonstrate the utility of the approach presented. This scenario starts with the capture of simulated orbital imagery. Prospective targets are identified and tasked to UAV units for additional data collection and assessment. With this additional data collected, surface robots are deployed to conduct final verification activities. This approach is compared to a top-down command approach, where all decisions are made by the orbital tier. Metrics used for evaluation include data transmission requirements and the level of coverage generated.
      Keywords: heterogeneous craft; artificial intelligence; UAV command; robotic command; spacecraft command; autonomous control; autonomous robots; space robotics; multi-tier robotic networks; local decision making; unmanned aerial vehicles; resource location; resource a
      Citation: International Journal of Space Science and Engineering, Vol. 2, No. 3 (2014) pp. 225 - 247
      PubDate: 2014-08-07T23:20:50-05:00
      DOI: 10.1504/IJSPACESE.2014.064194
      Issue No: Vol. 2, No. 3 (2014)
  • Calculating and analysis of re-entry condition for space
           tethered-assisted return system in elliptic orbit
    • Authors: Changqing Wang, Hanlin Wei, Aijun Li
      Pages: 248 - 258
      Abstract: The calculation of re-entry condition and the analysis of influencing factors based on space tethered-assisted deorbit system are provided. Firstly, the process of space tethered-assisted return is described, then the dynamical model of this system and the backswing model of capsule in elliptic orbit coordinate system are established, according to Pontryagin's maximum principle the optimal control law is presented, and the calculation of re-entry condition is given. The influence on re-entry conditions from tether mass, eccentricity, true anomaly and the altitude of the orbit are analysed. Based on the above calculation and analysis, the correlation parameters that meet the re-entry condition under the elliptic orbit are obtained. Through the study of this article, we give a reference for choosing the parameters of future tethered-assisted return system and a theoretical reference for the calculation of re-entry condition in future space tether-assisted return technology.
      Keywords: space tether systems; tethered assisted re-entry; re-entry conditions; eccentricity; true anomaly; elliptical orbit; space vehicle re-entry; spacecraft re-entry; dynamic modelling; capsule backswing model; optimal control; tether mass
      Citation: International Journal of Space Science and Engineering, Vol. 2, No. 3 (2014) pp. 248 - 258
      PubDate: 2014-08-07T23:20:50-05:00
      DOI: 10.1504/IJSPACESE.2014.064196
      Issue No: Vol. 2, No. 3 (2014)
  • Robust attitude control of nano-satellite using control moment gyros
           based on higher order sliding modes
    • Authors: Ting Hao, Saburo Matunaga
      Pages: 259 - 275
      Abstract: Rapid attitude orientation and stable pointing accuracy are critical characteristics for observation missions of nano-satellite nowadays. This paper focuses on analysis of attitude control law for nano-satellite TSUBAME which is developed by Laboratory of Space System at Tokyo Institute of Technology. In recent years, the higher order sliding mode control (HOSMC) is considered, which is more useful in handling the chattering effect against external disturbance and unknown friction effects. Furthermore, HOSMC can remove the chattering effect if appropriate relative degree was chosen. To overcome the singularity problem inherent in the control moment gyros, a modified steering law for single gimbal control moment gyros (SGCMG), which aims at precisely exporting commanded torque is discussed based on the optimal output torque capability principle. This paper includes a comparison between two different control algorithms in the attitude controlling system which used control moment gyro (CMG) as the actuator for TSUBAME. The numerical simulation results demonstrate the efficiency and feasibility of the proposed HOSMC algorithm.
      Keywords: higher order SMC; sliding mode control; control moment gyros; CMGs; chatter effect; robust control; attitude control; nanosatellites; satellite control; singularity; output torque capability; numerical simulation
      Citation: International Journal of Space Science and Engineering, Vol. 2, No. 3 (2014) pp. 259 - 275
      PubDate: 2014-08-07T23:20:50-05:00
      DOI: 10.1504/IJSPACESE.2014.064200
      Issue No: Vol. 2, No. 3 (2014)
  • Satellite orbit and attitude estimation using three-axis magnetometer
    • Authors: Y. Kim, G. Vukovich
      Pages: 276 - 304
      Abstract: The determination of satellite orbital and attitude position and velocity from measurement of a single earth magnetic field (emf) vector without additional measurements, but using a state estimator, is a challenging problem. It is not obvious from first glance whether a solution exists at all - whether the problem is observable with the measurement of only a single emf vector, and an analysis is necessary. This paper performs this analysis for a simple linear system model. Almost circular low earth nearly polar orbits and a dipole emf model are considered. Although these are rather restrictive assumptions they nevertheless provide considerable insight. Both a purely algebraic situation as well as dynamic estimation are studied. It is shown that if the emf induction vector magnitude is used to estimate satellite orbit (position and velocity) and its three projections are used to estimate the attitude, that the situation is sufficiently observable for orbit and attitude determination using just magnetometer measurements. However, for nearly polar orbits, longitude and east velocity are difficult to estimate due to weak observability, and estimation convergence time can be lengthy with poor accuracy.
      Keywords: satellite orbit estimation; satellite attitude estimation; magnetometer; Earth magnetic field; EMF induction vector magnitude; satellite navigation; low Earth orbit; linear system modelling; satellite velocity; satellite position; satellite orbits
      Citation: International Journal of Space Science and Engineering, Vol. 2, No. 3 (2014) pp. 276 - 304
      PubDate: 2014-08-07T23:20:50-05:00
      DOI: 10.1504/IJSPACESE.2014.064202
      Issue No: Vol. 2, No. 3 (2014)
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