Light Aircraft Design

5/20/2018 Light Aircraft Design

1/29

New: Sport Pilot (LSA)

The Light Aircraft Design Computer Program Package - based on MS-Excel-application !as no! extented !ith the ne! Sport Pilots "LSA# loadsmodule$ !hich includes compliance for the %Standard Specifiation for

Design and Performance of a Light Sport Airplane ASTM & ''()-*(+ loadssection,

Light Aircraft Design

- Loads and Static Tests

- Structure Calculations

- Aerodynamic

The Loads may be calculated according to the following regulations:

UL Germany (LTFUL!

FA" #$ % &LA

E.***

Sport Pilots "LSA#***

E.
http://www.aircraft-certification.de/lightaircraftdesign.htmhttp://www.aircraft-certification.de/lightaircraftdesign.htm


2/29

All 'rograms are S)*C)L modules some of them using S &isual+asic calculation modules in bac,ground-

Summary descri'tions of the methods are included in the

s'readsheets-

ost of the results are 'resented in gra'hic form-

The /L 0erman1 "LT&-/L#$ Sport Pilots "LSA# and &A2'345LA includes thefollo!ing modules6

o Data Sheet

o .eight and +alance

o Flight )n/elo'e

o Design Cases

o Landing Gear Loads

o )ngine ount Loads

o Control Surfaces and Flight Control Loads

o Fuselage Load Distributions (calculated and tested!

o .ing Load Distributions (calculated and tested!

Prices6 7

LTFUL : 0112

LSA 3 S'ort 4ilots : 5112

FA" #$%&LA: 6112

S'ecial 7ffer: LTFUL 8 LSAS'ort 4ilots 8 FA" #$%&LA: 9112


3/29

;add su''lementary 96< ta=es (.St-!

Supplementar1 the follo!ing modules ma1 be ordered6 7

Flight Controls >inematics (62!

4ro'eller Layout % Design (62!

anoeu/re and Gust Flight Simulation (662!

Structure Calculation: .ing Sections (metal and com'osite! (62!

Landing Gear Strut- Calculation (662!

Fuselage Design (662!

;add su''lementary 96< ta=es (.St-!

Data Sheet

All geometric and aerodynamic data of the aircraft are defined or calculated: meanaerodynamic chords? as'ect ratios? tail /olumes? lift cur/e slo'es? hinge lift and

moment coefficients for control surfaces and tabs? neutral 'oint wing? tails andfuselage influence? 'ro'eller sli'stream effect-


4/29

.eight and +alance

Calculates the mass distribution of the aircraft? CG 'osition and inertial moments-


5/29

Flight )n/elo'e

Calculates the design s'eeds and the corres'onding load factors for manoeu/re andgusts-

(gra'hic!


6/29

Design Cases

The critical design cases according to the LSA (S'ort 4ilots!? LTFUL (UltralightGermany! or FA" #$ are defined and the corres'onding forces on the wing? tail arecalculated-


7/29

Landing Gear Loads

The design cases and corres'onding forces on the main and nose gear arecalculated-

)ngine ount Loads

Forces and moments in the engine mount CG (including gyrosco'ic effects arecalculated!-

Control Surfaces%Flight Control Loads

The total critical loads and hinge moments (aileron? ele/ator? rudder? fla's! on the

control surface of the aircraft are calculated-

Fuselage Load Distributions (calculated and tested!

The fuselage bending and shear force diagrams for the critical fuselage loading arecalculated-

4osition for the 'oints where the fuselage will be loaded during the static test aredefined- The corres'onding test load diagrams are com'uted and com'ared with the

calculated ones-


8/29

(gra'hic!


9/29

.ing Load Distributions (calculated and tested!

The wing aerodynamic load distribution for critical design cases is calcualted with thewell ,nown ultho' lifting line method-

The effect of fla'%aileron is considered-

The mass load distribution (structure? fuel? lum'ed masses li,e landing gear! due to

/ertical and roll acceleration is considered-

The total shear (T=?Ty?T@ ! and moment diagrams (bending=? torsion y and in'lane bending 3@! moments are calculated-

The static test loading may be also defined and com'ared with the calcualted one-

(gra'hic!


10/29


11/29

Flight Controls >inematics ( 6 )U"!

This 'rogram calculates the forces in a $D 'ush'ull control system for differentcontrol system deflections-

Cross sections of the rods are defined-

The safety factors for buc,ling are calculated-

(gra'hic!


12/29


13/29

4ro'eller Layout%Design (6 )U"!

This module calculates the 'ro'eller cur/es using a /ery efficient energy method-

The 'ro'eller 'lanform and torsion is defined as in'ut-

Using the S7L&)"B o'timi@ation algorithm from S)*C)L some 'arameters maybe o'timi@ed (form? torsion! in order to get the best efficiency in a gi/en wor,ing'oint-

+ending and torsion moments in 'ro'eller cross sections are calculated-

(gra'hic!


14/29


15/29


16/29

anoeu/re and Gust Flight Simulation (66 )U"!

"egulations (FA"%A"%CS?&LA? LTFUL! 'ro/ide sim'lified formulas for gust- Theresulted forces and load factors are normally conser/ati/e-

A more detailed calculation may be 'erformed by means of a flight simulation of thegust%manoeu/re in which the /ertical translation and 'itch rotation of the aircraft are

considered- A differential euation system defines the A%C motion-

+y means of this method a time history of all A%C 'arameters (angle of incidence?


17/29

'itch rate? 'itch acceleration? A%C load factor? wing load? ET load! is calculated-

(gra'hic!


18/29


19/29


20/29

.ing Sections (metal and com'osite! (6 )U"!

A library of com'osite material layers is defined including all material 'ro'erties-

This library is used to define the layout of a wing cross section (ty'e and no- oflayers? layer direction!-

The section bending and torsion moment are defined-

The bending and shear stresses are calculated-

Finaly the safety factors for each layer is defines (Tsai criteria!-

(gra'hic!


21/29


22/29

Landing Gear Strut- Calculation ( 66 )U"!

This 'rogram simulates the landing of an elastic landing gear leaf (strut! by meansof an iterati/e method- Large geometrical deformations are considered- The forcedeformation diagram and the deflected form of the leaf are 'lotted-

The form of the landing gear strut is defined: rectangular or round section- Thesafety factors for each cross sections are calculated (bending? torsion and total

loading!- Ealf struts or cross one 'iece! struts may be calculated-

The tire elastic characteristic is considered-

(gra'hic!


23/29


24/29


25/29

Fuselage Design (66 )U"!


26/29

The main fuselage contour lines are defined: u''er and lower from the side /iew?line of ma=- width? 'osition of the ma=- width line-

The cross sections of the fuselage are defined by means of conical cur/es (one cur/e

for the u''er side and one for the lower side!- A conical coefficient defines the formof the cross section-

A -D*FB file may be e='orted and read directly in CAD 'rograms in order to define a

/ery smooth surface form of the fuselage-

The whole 'rocedure may be done in less then one hour-

(gra'hic!


27/29


28/29

Coming Soon: Lifting Surface Aerodynamic Load Distribution (S)*C)L a''lication!

Calculates the lift and induced drag distribution for com'le= aircraft $D configurationsli,e canard? winglets- Control surface deflections are included-

The lifting surface theory is used to define the 'ressure distributions-

Coming Soon: S'readsheets:

.eight +alance

&ertical Climbing S'eed

4ro'eller 4erformance and oise easurements

Standard Atmos'hera

Urheber und ut@ungsrechte

Co'yright H #110 4CAero%Di'l- Ing- Calin Gologan- All rights reser/ed-

4rograms written by 4CAero%Di'l- Ing- Calin Gologan- All rights reser/ed by 4C

Aero%Di'l- Ing- Calin Gologan-

The 'assing on of the 'rograms of third is e='ressly forbidden- The 'rograms weree=amined with large care for errors? lac, are howe/er ne/ertheless not com'letelyto be e=cluded- .e cannot ta,e o/er therefore for the correctness and


29/29

conseuences? which can result from the use of the 'rogram? adhesion-

If you download our 'rogram modules of these website? acce't the following rightsto use:

All co'yrights remain with the right owners 4C Aero%Di'l- )ngineer Calin Gologan-Any commercial use of the files (in addition among other things the 'ublication in

brochures counts? the use in announcements or on .ebsites of enter'rise etc-! isnot 'ermitted? also not in changed form-

.ithout 're/ious written agreement of the owners of co'yrights you may use thefiles only for your 'ersonal use- They may not bring it in the Internet or on CD "7in circulation-

Further Juestions to:Eead of Co'orate Communications:

Dr- +irgit .eiKenbach)ail: dr-birgit-weissenbach'caero-de
mailto:[email protected]:[email protected]

Documents

Light Aircraft Design