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Reconfiguration of Multiple Spacecraftsfor Deflecting an Asteroid with Gravity Tractor Method

Molazadeh, Vahid Reza | 2015

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  1. Type of Document: M.Sc. Thesis
  2. Language: Farsi
  3. Document No: 47622 (08)
  4. University: Sharif University of Technology
  5. Department: Aerospace Engineering
  6. Advisor(s): Pourtakdoust, Hossein
  7. Abstract:
  8. In this work the problem of optimal spacecrafts reconfiguration and formation keeping is investigated for Asteroid attraction. Due to potential impact probability of the Apophis asteroid with Earth in 2036, the study is focused on optimal intercept avoidance via gravity attraction of multiple spacecrafts suitably arranged on halo orbits of Apophis. In this regard, a space mission is defined in which initially several spacecrafts are optimally reconfigured onspecial Halo orbits of the asteroid via several techniques that include pseudospectral, linear quadratic regulator as well as the integral sliding mode control. The utility of three methods is for verification purposes as well as comparison of results. Subsequently, the problem of optimal formation keeping has been performed on six spacecrafts suitably arranged on two Halo orbits. The Results are promising as it is demonstrated that thedesignee mission has been successful in displacing the asteroid path thus effectively removing the impact potential. It is also noted that the method of pseudospectral is preferable in terms of fuel consumption as compare with other methodologies used for verification. The effect of measurement noise and environmental disturbances on the mission and control effectiveness has also been studied
  9. Keywords:
  10. Trajectory Optimization ; Linear Quadratic Requlator (LQR) ; Halo Orbits ; Asteroid Deflection ; Pseudo Spectral Method

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