FIELD: machine building.
SUBSTANCE: method consists in following stages: making imitation model of panel; determination of variables of design of panel reinforced with stiffeners; determination of restricting condition which design solution of panel reinforced with stiffeners should meet; creation of imitation expert module of family of kinds of damages for panel reinforced with stiffeners; iteration change of variables at designing imitation model (9) reinforced with stiffeners to optimise target variable.
EFFECT: raised specific strength of panel due to consideration of changes at distribution of loads and to confirmation of compliance to restricting conditions and requirements of safety factor related to preliminary specified kinds of damages with usage of imitation expert modules.
5 cl, 6 dwg, 4 tbl
Title | Year | Author | Number |
---|---|---|---|
INTEGRAL AIRCRAFT AIRFRAME FROM COMPOSITE | 2011 |
|
RU2573692C2 |
TORSION BOX OF WING FROM COMPOSITE | 2013 |
|
RU2532254C2 |
AIRCRAFT FUSELAGE MADE OF COMPOSITE AND METHOD OF ITS FABRICATION | 2011 |
|
RU2564476C2 |
TORSION BOX OF WING FROM COMPOSITE | 2013 |
|
RU2532255C1 |
REINFORCED WING MULTI-FRAME TORSION BOX | 2008 |
|
RU2500574C2 |
AIRCRAFT WING, AIRCRAFT WINGS CAISSON, CENTER WING, SPAR (VERSIONS) | 2019 |
|
RU2709976C1 |
LIGHT-WEIGHT INTEGRAL PANEL OF POLYMER COMPOSITES FOR AIRCRAFT CONTOURING COMPONENTS | 2013 |
|
RU2542801C2 |
METHOD TO MANUFACTURE MULTILAYER COMPONENT | 2007 |
|
RU2453436C2 |
AIRCRAFT WING | 2014 |
|
RU2557638C1 |
PANEL DESIGN AND CORRESPONDING METHOD | 2015 |
|
RU2693141C2 |
Authors
Dates
2011-10-10—Published
2006-10-31—Filed