The stability of join-wing

configuration within optimization

procedure MADO - Multidisciplinary Aircraft Design and Optimization

software suite

(PANUKL, SDSA, OptoM)

Naples 12-14.10.2015

Tomasz Goetzendorf-Grabowski,

Jacek Mieloszyk Warsaw University of Technology, Poland

5th Symposium on Collaboration in Aircraft Design

Outline

• Objective

• Analysis tools -MADO – Aerodynamics – PANUKL

– FEM – CalculiX

– Stability – SDSA

• Tools connection

• Interfaces

• Optimization

• Results – Joined Wing case

• Summary

MADO - Multidisciplinary Aircraft Design and Optimization

MOSUPS by C.Galiński,

Dynamic analysis: M.Lis

Join-wing as example MADO using

(>180 optimization variables)

MADO - Multidisciplinary Aircraft Design and Optimization

SDSA architecture

Panukl

Project

Interface PANUKL-SDSA

SDSA Output

to OptoM

MADO - Multidisciplinary Aircraft Design and Optimization

Export from PANUKL to SDSA

Optimization

schema

Objective function & constrains

0Cm

15.0dCz

dCm

maxCzCz

CxSVP 3

min2

1

CzSVgm 2

2

1

Aerodynamic optimization

- 183 variables – shell thickness

- material - aluminum alloy

minm

max

dop

Strength optimization

Objective function & constrains

Dynamic constrains

04.0phugoid

3.135.0_

periodshort

19.0_

rolldutch

1_

rolldutch

20_2

spiral

T 0.0_2

spiral

T

Dynamics optimization

μ3

μ2

μ1

μ3 < μ2 < μ1

)(2

1 2 xcFF CELUNEWCELU

]0,max[ xgc

where

g – constraint value

Penalty function constrains

feasible solutions

5th Symposium on

Collaboration in Aircraft Design

0

500

1000

1500

2000

2500

3000

0 5 10 15 20 25 30

P[W

]

Iterations

4th Symposium on

Collaboration in Aircraft Design

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

-2.5 -2 -1.5 -1 -0.5 0 0.5 1 1.5 2 2.5

b[m]

CL

Up wing

Down wing

0

0.2

0.4

0.6

0.8

1

1.2

1.4

1.6

-2.5 -2 -1.5 -1 -0.5 0 0.5 1 1.5 2 2.5

b[m]

CL

Up wing

Down wing

Cruise conditions

Close to stall

5th Symposium on

Collaboration in Aircraft Design

CalculiX

results

5th Symposium on

Collaboration in Aircraft Design

0

5

10

15

20

25

30

35

40

45

0 5 10 15 20 25 30

m_w

ing[

kg]

Iterations

Weight of wing

5th Symposium on

Collaboration in Aircraft Design

Phugoid mode - damping ratio

5th Symposium on

Collaboration in Aircraft Design

Short Period mode - damping ratio

5th Symposium on

Collaboration in Aircraft Design

Dutch roll mode – CS-23 criterion

5th Symposium on

Collaboration in Aircraft Design

Dutch roll mode – MIL criterion

5th Symposium on

Collaboration in Aircraft Design

Spiral mode – MIL criterion

5th Symposium on

Collaboration in Aircraft Design

Final solution baseline

25th iteration

Future work Coming soon:

• C++ API functions for Panukl and SDSA batch operations (almost done)

• Structure moments of inertia

• FEM export

- 8 node shell panels

- composite definition as orthotropic material

- internal FEM analysis execution

Long term: • Propeller influence as actuator disc

• Export to other FEM solvers (?)

• GUI for aircraft mass properties

• Parallelization of computation

MADO - Multidisciplinary Aircraft Design and Optimization

Thank you

for attention