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Synthesis of control system by approximation method for switching surface

Keywords:

A.I. Diveev, E.Y. Shmalko


The problem of control synthesis of spacecraft decent in Martian atmosphere is considered. The optimal control is to deliver minimum to maximal G-force and direct hit into terminal conditions allowing some variations in initial conditions. For various initial conditions an optimal control is shown to have similar shape and one switch in sign that depends on initial conditions. The moment of switching is suggested to be approximated depending on initial conditions. An example of control synthesis is given.
References:

  1. Braun R.D., Manning R.M. Mars Exploration Entry, Descent and Landing Challenges // IEEE Aerospace Conference. Big Sky Montana. March 2006.
  2. Mendeck G.F., Carman G.L. Guidance Design for Mars Smart Landers Using the Entry Terminal Point Controller. AIAA 2002-4502. Atmospheric Flight Mechanics Conference and Exhibit. Monterey, CA. August 2002.
  3. Carman G., Ives D., Geller D. Apollo-Derived Mars Precision Lander Guidance // AIAA Paper 98-4570. August 1998.
  4. Diveev A.I., Shmal'ko E.Ju. Mnogokriterial'ny'j strukturno-parametricheskij sintez sistemy' upravleniya spuskom kosmicheskogo apparata na osnove metoda setevogo operatora // Vestnik Rossijskogo universiteta druzhby' narodov. Ser. Inzhenerny'e issledovaniya (informaczionny'e texnologii i upravlenie). 2008. № 4. S. 86–93.
  5. Diveev A.I., Shmal'ko E.Ju. Sintez sistemy' upravleniya posadkoj na Mars // Trudy' instituta sistemnogo analiza RAN. Dinamika neodnorodny'x sistem. 2010. T. 53(1). S. 275–281.

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