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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  [396 journals]
  • Methods of the analysis of motion of small space vehicles around the
           centre of masses at deployment of space tether system
    • Authors: Yuriy Zabolotnov, Oleg Naumov
      Pages: 305 - 326
      Abstract: This paper studies analytical and numerical methods of the analysis of spatial motion concerning centre of mass of small space vehicles at deployment of space tether system. Deployment of space tether system is executed from the base space vehicle. The set angular orientation of the base space vehicle concerning a local vertical is provided by means of own system of stabilisation. The small space vehicle (or freight) represents a descent capsule returned to the Earth or the space vehicle transferred into higher orbit. It is supposed that the weight of the base space vehicle is much more than weight of freight. The angular position of freight is described by classical Euler's angles determined concerning a direction of a tether. Analytical methods of the analysis of angular motion are based on an averaging method (for small angles of nutation) and on a method integral of manifolds which allows to investigate the nonlinear equations of angular motion of freight. The major factors influencing stability of angular motion of freight concerning a direction of a tether are considered. Results of numerical modelling of angular motion of the small space vehicle are presented.
      Keywords: small space vehicles; space tether systems; STS deployment; averaging method; stability; disturbances; spacecraft motion; centre of mass; angular motion; freight; numerical simulation; modelling
      Citation: International Journal of Space Science and Engineering, Vol. 2, No. 4 (2014) pp. 305 - 326
      PubDate: 2015-01-18T23:20:50-05:00
      DOI: 10.1504/IJSPACESE.2014.066964
      Issue No: Vol. 2, No. 4 (2015)
       
  • The small reconnaissance of atmospheres mission platform concept, part
           1: motivations and outline for a swarm of scientific microprobes to
           the clouds of Jupiter in 2030
    • Authors: John E. Moores, Kieran A. Carroll, Isaac DeSouza, Kartheephan Sathiyanathan, Barry Stoute, Jinjun Shan, Regina S. Lee, Ben Quine
      Pages: 327 - 344
      Abstract: A mission concept is presented for several small atmospheric entry vehicles at Jupiter. By relaxing the requirement for substantial penetration into the Jovian atmosphere, the size of the atmospheric entry probes shrinks dramatically. Such atmospheric entry probes would experience much less heating than previous concepts of much larger (∼300kg) spacecraft presented as minimum concepts and no parachutes are necessary. This reduces complexity while still permitting over 15 minutes of useable science under free-fall from above the 0.41 bar level to near the 10 bar level of the Jovian Atmosphere during which up to 20 Mbits of data could be returned per probe. By dividing the payload, the risk to the mission is substantially mitigated and ground truth may be obtained from a large part of the entire planetary atmosphere using a single launch.
      Keywords: mission concept; spacecraft design; planetary science; atmospheric science; Jupiter; microprobe swarms; atmospheric entry probes; small entry vehicles; scientific microprobes; Jovian atmosphere; payload division
      Citation: International Journal of Space Science and Engineering, Vol. 2, No. 4 (2014) pp. 327 - 344
      PubDate: 2015-01-18T23:20:50-05:00
      DOI: 10.1504/IJSPACESE.2014.066960
      Issue No: Vol. 2, No. 4 (2015)
       
  • The small reconnaissance of atmospheres mission platform concept, part
           2: design of carrier spacecraft and atmospheric entry probes
    • Authors: John E. Moores, Kieran A. Carroll, Isaac DeSouza, Kartheephan Sathiyanathan, Barry Stoute, Jinjun Shan, Regina S. Lee, Ben Quine
      Pages: 345 - 364
      Abstract: Constraints and potential hardware are described outlining both elements of the SMARA scientific microprobe mission to Jupiter. Individual atmospheric probes are possible at masses of 12.5 kg. Such probes would be 0.6 m across and would be capable of carrying at least 1.6 kg of scientific payload. This would enable a broad range of instrumentation to be deployed at Jupiter, though mass spectroscopy would require a slightly more massive probe or some additional miniaturisation. The carrier spacecraft are each responsible for delivering six of the individual atmospheric probes to Jupiter. This requires carrier spacecraft with a mass of at least 60 kg. The entire spacecraft is sufficiently small and modular that upwards of 60 atmospheric entry vehicles could be deployed by a single medium launch to examine 10 distinct locations at Jupiter. Nearly identical probes would be suitable for Saturn, Uranus, Neptune or Venus by modification of the carrier.
      Keywords: mission concept; spacecraft design; planetary science; atmospheric science; Jupiter; microprobe swarms; atmospheric entry probes; small entry vehicles; scientific microprobes; Jovian atmosphere; payload division
      Citation: International Journal of Space Science and Engineering, Vol. 2, No. 4 (2014) pp. 345 - 364
      PubDate: 2015-01-18T23:20:50-05:00
      DOI: 10.1504/IJSPACESE.2014.066961
      Issue No: Vol. 2, No. 4 (2015)
       
  • Satellite relative motion determination during separation using image
           processing
    • Authors: Danil Ivanov, Stanislav Karpenko, Mikhail Ovchinnikov, Marianna Sakovich
      Pages: 365 - 379
      Abstract: Satellite relative position and attitude determination algorithm by video processing is developed. The algorithm is numerically simulated and studied. Relative state determination accuracy depending on a distance and pre-defined points image size is investigated. Microsatellite 'Chibis-M' and spaceship 'Progress-13M' relative motion after separation is determined by the algorithm.
      Keywords: formation flying; relative motion; image processing; satellite motion; satellite separation; satellite position determination; satellite attitude determination; video processing; numerical simulation; microsatellites; spacecraft
      Citation: International Journal of Space Science and Engineering, Vol. 2, No. 4 (2014) pp. 365 - 379
      PubDate: 2015-01-18T23:20:50-05:00
      DOI: 10.1504/IJSPACESE.2014.066963
      Issue No: Vol. 2, No. 4 (2015)
       
  • An analytical approach for the design of carbon-fibre-reinforced
           polymer laminates with minimised thermal expansion
    • Authors: Danil Ivanov, Stanislav Karpenko, Mikhail Ovchinnikov, Marianna Sakovich
      Pages: 380 - 395
      Abstract: The potential of carbon-fibre-reinforced polymers (CFRP) for the design of structures with extremely small coefficients of thermal expansion (CTE) is commonly known. Such structures play an important role in space applications, like earth observation satellites and space telescopes. But they also have a high potential for earthbound applications, for example, for precise mechanical and optical measurement devices. This paper demonstrates that orthotropic and quasi-isotropic laminates are most suitable for the design of laminates with minimised CTE. The derivation of a shortcut equation to the tensor calculations of the classical lamination theory is presented. Its purpose is to assist engineers in the selection of suitable carbon fibres and matrix polymers for the design of a laminate with high thermomechanical stability. The application of the equation is discussed and demonstrated on examples with practical relevance.
      Keywords: coefficient of thermal expansion; carbon fibre reinforced polymers; CFRP; thermomechanical properties; thermomechanical stability; space structures; laminate theory; reinforced polymer laminates; laminate design
      Citation: International Journal of Space Science and Engineering, Vol. 2, No. 4 (2014) pp. 380 - 395
      PubDate: 2015-01-18T23:20:50-05:00
      DOI: 10.1504/IJSPACESE.2014.066959
      Issue No: Vol. 2, No. 4 (2015)
       
 
 
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