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UID:506@cran.univ-lorraine.fr
DTSTART;TZID=Europe/Paris:20240905T100000
DTEND;TZID=Europe/Paris:20240905T130000
DTSTAMP:20240710T062027Z
URL:https://www.cran.univ-lorraine.fr/events/soutenance-de-these-de-sofian
 e-pineau/
SUMMARY:Soutenance de thèse de Sofiane Pineau
DESCRIPTION:\n\nTitre de la thèse :Dynamique de vol et commande non-linéa
 ire adaptative pour projectiles guidés\n\nRésumé :\n\n\n155 mm spin-sta
 bilized ammunitions commonly used in artillery\, suffer from a high ballis
 tic dispersion\ntoward the target due to uncertain launch conditions and w
 ind disturbances. To reduce this lack of\nprecision\, a concept of a dual-
 spin guided projectile geared with a course-correction fuse is investigate
 d.\nThis is an innovative and low-cost solution which consist of equipping
  existing shells with a roll-decoupled\nguidance fuse embedding up to four
  aerodynamic control surfaces called canards. The fuse embeds also\nall ne
 cessary sensors (IMU\, magnetometers\, and GNSS)\, a control law and a gui
 dance law.\nThe main control strategy used in the literature for dual-spin
  guided projectiles is called gain-scheduling.\nThis methodology is based 
 on the local linearization of the projectile dynamics around a fixed numbe
 r of\nflight points in order to synthetize a nonlinear scheduled controlle
 r. Gain-scheduling is time-consuming\ndue to the large number of local con
 trollers to be tuned\, and does not guarantee global performance and\nstab
 ility over the entire flight envelope.\nTherefore\, the main objective of 
 this thesis is to establish a generic and rapid design methodology\nfor gu
 ided projectiles autopilots with guaranteed performance and robustness to 
 parameter uncertainties\nthrough the whole flight envelope.\nTo achieve th
 is objective\, first\, the nonlinear modelling of the projectile was condu
 cted and a ballistic\nsimulator was designed in the Matlab/Simulink enviro
 nment. Then\, the Incremental Nonlinear Dynamic\nInversion (INDI) control 
 method was used to design the roll\, pitch\, yaw and load factor autopilot
 s required\nto correct the projectile’s trajectory. A tuning methodology
  was designed using digital control analysis\ntools and mixed-sensitivity 
 synthesis to meet the tuning requirements. Finally\, to deal with the para
 metric\nuncertainties of the projectile model and guarantee the overall pe
 rformance of the control system\, the\nINDI autopilots were augmented with
  an adaptive layer. Non-linear simulations of guided trajectories\nwere us
 ed to validate the nominal behavior of the INDI control law and the increa
 sed robustness provided\nby the adaptive augmentation
CATEGORIES:Département CID
LOCATION:CRAN - Longwy\, 186 Rue de Lorraine\, Cosnes-et-Romain\, 54400\, F
 rance
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