Automated optimization of supersonic missile performance taking into account design uncertainties

A. Gaiddon, J. N. Greard, D. Pagan, D. D. Knight

Research output: Chapter in Book/Report/Conference proceedingConference contribution

3 Scopus citations

Abstract

The flight performance of a supersonic air-breathing missile is optimized with an automated loop taking into account design uncertainties through a statistical approach. Each characteristic of the missile (aerodynamic coefficient, inlet performance, mass) is altered with scale factors following a Gaussian distribution. A specific module performs statistical computations in order to predict the mean value and standard deviation of the performance. The optimization process is conducted only on the geometrical parameters of the inlet, which is one of the key elements of the aeropropulsive system. A representative mission is modelized leading to three performance objectives: the longitudinal acceleration factor after the boost phase, the maneuverability factor during counter-defense maneuvers and the fuel consumption during cruise.

Original languageEnglish (US)
Title of host publication33rd AIAA Fluid Dynamics Conference and Exhibit
StatePublished - 2003
Event33rd AIAA Fluid Dynamics Conference and Exhibit 2003 - Orlando, FL, United States
Duration: Jun 23 2003Jun 26 2003

Publication series

Name33rd AIAA Fluid Dynamics Conference and Exhibit

Other

Other33rd AIAA Fluid Dynamics Conference and Exhibit 2003
CountryUnited States
CityOrlando, FL
Period6/23/036/26/03

All Science Journal Classification (ASJC) codes

  • Fluid Flow and Transfer Processes
  • Energy Engineering and Power Technology
  • Aerospace Engineering
  • Mechanical Engineering

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