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Journal Cover 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  [386 journals]
  • Advantages of small satellite carrier concepts for LEO/GEO inspection
           and debris removal missions
    • Authors: David K. Geller, Derick Crocket, Randy Christensen, Adam Shelley
      Pages: 115 - 134
      Abstract: This work focuses on two important types of space missions: close-in satellite inspection of LEO/GEO high-value assets to detect and/or resolve anomalies, and LEO/GEO debris disposal missions to reduce space hazards. To demonstrate the efficiency of using reusable SmallSats, two mission architectures are analysed: 1) a SmallSat carrier-based system with an in-space refuelling capability; 2) a traditional carrier-less SmallSat. For each architecture the number of potential SmallSat satellite inspection and debris disposal mission sorties is determined as a function of the required initial launch mass. The analysis shows that reusable SmallSats can efficiently conduct multiple satellite inspection and debris removal sorties. For LEO missions, the carrier-based architecture enables a significantly lower launch mass than the carrier-less system. For GEO missions, the advantages of a carrier-based system are less clear and more mission specific. To accomplish these missions, key enabling SmallSat technologies are identified.
      Keywords: satellite inspection; space debris; mission design; trajectory design; small satellites; satellite carriers; debris removal; space missions; space hazards; reusable satellites; in-space refuelling
      Citation: International Journal of Space Science and Engineering, Vol. 2, No. 2 (2014) pp. 115 - 134
      PubDate: 2014-04-22T23:20:50-05:00
      DOI: 10.1504/IJSPACESE.2014.060595
      Issue No: Vol. 2, No. 2 (2014)
       
  • Relative mission analysis for PROBA-3: safe orbits and CAM
    • Authors: Thomas Vincent Peters, Diego Escorial
      Pages: 135 - 156
      Abstract: This paper reports the phase B mission analysis work performed for the safe orbit and the collision avoidance manoeuvres (CAM) of the PROBA-3 formation flying mission, including the recovery to nominal conditions. PROBA-3 will perform formation flying in a highly elliptical orbit, and perform solar coronagraphy and formation manoeuvring demonstrations in a six-hour arc around apogee. Mission analysis in this paper addresses the safe orbit and the CAM and focuses on safety and ΔV requirements. Important constraints on the mission analysis are the absence of an omnidirectional sensor, and the requirement that the spacecraft cannot turn more than 30° away from the Sun due to thermal and power constraints. In addition, no on-board action can be taken after safe orbit entry or after a CAM, which means that the recovery needs to be performed under ground control.
      Keywords: PROBA-3; spacecraft formation flying; mission analysis; safe orbit; collision avoidance manoeuvres; CAM; elliptical orbits; safety
      Citation: International Journal of Space Science and Engineering, Vol. 2, No. 2 (2014) pp. 135 - 156
      PubDate: 2014-04-22T23:20:50-05:00
      DOI: 10.1504/IJSPACESE.2014.060599
      Issue No: Vol. 2, No. 2 (2014)
       
  • In-flight performance validation of the TanDEM-X autonomous
           formation flying system
    • Authors: Jean-Sébastien Ardaens, Ralph Kahle, Daniel Schulze
      Pages: 157 - 170
      Abstract: The in-flight performance validation of the experimental autonomous formation keeping system embarked by the German TanDEM-X formation has been performed during a 12-day-long closed-loop campaign conducted in June 2012. Relative control performance better than 10 m was achieved, demonstrating that a significant gain of performance can be achieved when the control of the formation is done autonomously on-board instead of on-ground. Furthermore, the formation keeping system was shown to be operationally robust, easy to operate and fully predictable, i.e., fully suited for routine mission operations. This campaign concludes successfully a series of validation activities, opening new doors to future innovative scientific TanDEM-X experiments for which enhanced formation control is required.
      Keywords: TanDEM-X; TAFF; autonomy; formation keeping; along-track interferometry; in-flight performance validation; autonomous formation flying; satellites; spacecraft formation flying; formation control
      Citation: International Journal of Space Science and Engineering, Vol. 2, No. 2 (2014) pp. 157 - 170
      PubDate: 2014-04-22T23:20:50-05:00
      DOI: 10.1504/IJSPACESE.2014.060596
      Issue No: Vol. 2, No. 2 (2014)
       
  • Pose estimation of an uncooperative spacecraft from actual space imagery
    • Authors: Simone D'Amico, Mathias Benn, John L. Jørgensen
      Pages: 171 - 189
      Abstract: This paper addresses the preliminary design of a spaceborne monocular vision-based navigation system for on-orbit-servicing and formation-flying applications. The aim is to estimate the pose of a passive space resident object using its known three-dimensional model and single low-resolution two-dimensional images collected on-board the active spacecraft. In contrast to previous work, no supportive means are available on the target satellite (e.g., light emitting diodes) and no a-priori knowledge of the relative position and attitude is available (i.e., lost-in-space scenario). Three fundamental mechanisms - perceptual organisation, true perspective projection, and random sample consensus - are exploited to overcome the limitations of monocular passive optical navigation in space. The preliminary design is conducted and validated making use of actual images collected in the frame of the PRISMA mission at about 700 km altitude and 10 m inter-spacecraft separation.
      Keywords: pose estimation; optical navigation; monocular vision; uncooperative spacecraft; flight results; PRISMA; space imagery; on-orbit servicing; spacecraft formation flying; 3D modelling
      Citation: International Journal of Space Science and Engineering, Vol. 2, No. 2 (2014) pp. 171 - 189
      PubDate: 2014-04-22T23:20:50-05:00
      DOI: 10.1504/IJSPACESE.2014.060600
      Issue No: Vol. 2, No. 2 (2014)
       
  • Real-time terminal guidance for autonomous spacecraft capture of free
           floating objects using model predictive control
    • Authors: Peng Li, Xiaokui Yue, Honghua Dai, Xianbin Chi
      Pages: 190 - 204
      Abstract: This paper investigates the optimal rendezvous with collision avoidance constraint. The classic Hill-Clohessy-Wiltshire (HCW) dynamic model is applied here to effectively describe the relative translation motion. Collisions are prevented through setting a safety sphere centred at the mass centre of the target. The rendezvous scenario of approaching with a three-axis attitude stabilised target is considered in this paper. A light-of-sight (LOS) tetrahedral path constraint is imposed for vision-based sensing and safety considerations. Then, the optimal-fuel rendezvous is transformed into a quadratic programming problem (QPP) using the model predictive control (MPC). Numerical simulations demonstrate that the proposed method can guarantee the safety of the autonomous rendezvous and to minimise the fuel consumption. In addition, this algorithm can be numerically solved rapidly.
      Keywords: optimal rendezvous; online trajectory planning; model predictive control; MPC; real-time guidance; terminal guidance; autonomous spacecraft capture; free floating objects; collision avoidance; dynamic modelling; relative translation motion; vision based sen
      Citation: International Journal of Space Science and Engineering, Vol. 2, No. 2 (2014) pp. 190 - 204
      PubDate: 2014-04-22T23:20:50-05:00
      DOI: 10.1504/IJSPACESE.2014.060607
      Issue No: Vol. 2, No. 2 (2014)
       
  • Distributed asynchronous planning and task allocation algorithm for
           autonomous cluster flight of fractionated spacecraft
    • Authors: Jing Chu, Jian Guo, Eberhard Gill
      Pages: 205 - 223
      Abstract: For autonomous cluster flight of fractionated spacecraft, planning and task allocation are important as they bridge the gap between the top-level layer (interpreting inputs from the environment) and the bottom-level layer (local controllers) of the distributed space system. This paper presents an asynchronous distributed algorithm that is able to implement planning and task allocation concurrently, instead of one-by-one. First of all, the planning and task allocation problem is formulated in a generalised way. Then the core algorithm is presented, which consists of iterations between two parts. One is the construction of the list of tasks to be allocated and the assignment on-board each module. The other is the consensus process among different constructions of modules by exchanging local information between neighbours, where deconfliction rules are tailored for asynchronous situations. The former part is based on an auction algorithm, while the latter one takes advantage of a consensus algorithm. The entire process iterates asynchronously between those two parts until the planning and task allocation are agreed by all modules. In this paper simulation results are presented, which demonstrate the performance of the asynchronous algorithm not only when fractionated spacecraft operate under nominal conditions, but also when it experiences network disconnects or new tasks.
      Keywords: asynchronous algorithm; task allocation; autonomous cluster flight; fractionated spacecraft; multi-agent systems; MAS; agent-based systems; distributed planning; simulation
      Citation: International Journal of Space Science and Engineering, Vol. 2, No. 2 (2014) pp. 205 - 223
      PubDate: 2014-04-22T23:20:50-05:00
      DOI: 10.1504/IJSPACESE.2014.060597
      Issue No: Vol. 2, No. 2 (2014)
       
 
 
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