Guidance and control law for automatic landing flight experiment of reentry space vehicle

Yoshikazu Miyazawa, Kazutoshi Lshikawa, Kenji Fujii

Research output: Contribution to conferencePaper

8 Citations (Scopus)

Abstract

An automatic landing flight experiment with a sub-scale model is being prepared for a planned future reentry space vehicle by the National Aerospace Laboratory and the National Space Development Agency of Japan. The sub-scale model is dropped from a helicopter at a 1500m altitude, and, controlled by an on-board navigation, guidance, and control system, it automatically lands on a 1000m runway. This paper discusses preliminary study results obtained from numerical simulation by the National Aerospace Laboratory. The guidance and control law was designed using a multiple delay model and multiple design point approach (MDM/MDP., Control system robustness against uncertain and time varying dynamics is especially considered in this approach. The control performances are evaluated with appropriately defined quadratic indices of tracking error. Simple control structures are assumed and parameters are obtained with numerical optimization. The approach was successfully applied to the design, and feasibility of the experiment has been verified with numerical simulations.

Original languageEnglish
Pages1057-1066
Number of pages10
DOIs
Publication statusPublished - 1993
EventGuidance, Navigation and Control Conference, 1993 - Monterey, United States
Duration: Aug 9 1993Aug 11 1993

Other

OtherGuidance, Navigation and Control Conference, 1993
CountryUnited States
CityMonterey
Period8/9/938/11/93

All Science Journal Classification (ASJC) codes

  • Aerospace Engineering
  • Control and Systems Engineering

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  • Cite this

    Miyazawa, Y., Lshikawa, K., & Fujii, K. (1993). Guidance and control law for automatic landing flight experiment of reentry space vehicle. 1057-1066. Paper presented at Guidance, Navigation and Control Conference, 1993, Monterey, United States. https://doi.org/10.2514/6.1993-3818