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Light Aircraft Design - 29 Pages

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Light Aircraft Design
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Catalogue excerpts

The Light Aircraft Design Computer Program Package - based on MS-Excel-application - was now extented with the new Sport Pilots (LSA) loads module, which includes compliance for the "Standard Specifiation for Design and Performance of a Light Sport Airplane - ASTM F 2245-04" loads section. Light Aircraft Design -    Loads and Static Tests -    Structure Calculations The Loads may be calculated according to the following regulations: •    UL Germany (LTF-UL) NEW***Sport Pilots (LSA)***NEW

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> All programs are MS-EXCEL modules some of them using MS Visual Basic calculation modules in background. > Summary descriptions of the methods are included in the spreadsheets. > Most of the results are presented in graphic form. The UL Germany (LTF-UL), Sport Pilots (LSA) and FAR23/VLA includes the following modules: o Data Sheet o Weight and Balance o Flight Envelope o Design Cases o Landing Gear Loads o Engine Mount Loads o Control Surfaces and Flight Control Loads o Fuselage Load Distributions (calculated and tested) o Wing Load Distributions (calculated and tested) Prices: * LTF-UL : 500€ LSA...

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*add supplementary 19% taxes (MWSt.) Supplementary the following modules may be ordered: * Flight Controls Kinematics (49€) Propeller Layout / Design (49€) Manoeuvre and Gust Flight Simulation (99€) Structure Calculation: Wing Sections (metal and composite) (49€) Landing Gear Strut. Calculation (99€) Fuselage Design (99€) *add supplementary 19% taxes (MWSt.) Data Sheet All geometric and aerodynamic data of the aircraft are defined or calculated: mean aerodynamic chords, aspect ratios, tail volumes, lift curve slopes, hinge lift and moment coefficients for control surfaces and tabs, neutral point...

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eps’alphaf - Afcvund HLW ( dtjwnwaah at hare tail) le - Bezugefluge tie's I mean aerodynamic chord ) General coordinate system NeiiialpunM (Neutral point)

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Flight Envelope Calculates the design speeds and the corresponding load factors for manoeuvre and gusts. kmfh km(h km(h kmfh

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Gust Diagram, max. weight • Design Cases The critical design cases according to the LSA (Sport Pilots), LTF-UL (Ultralight Germany) or FAR 23 are defined and the corresponding forces on the wing, tail are calculated.

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Landing Gear Loads The design cases and corresponding forces on the main and nose gear are calculated. Engine Mount Loads Forces and moments in the engine mount CG (including gyroscopic effects are calculated). Control Surfaces/Flight Control Loads The total critical loads and hinge moments (aileron, elevator, rudder, flaps) 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 are calculated. Position for the points where the fuselage will be loaded during the static...

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Knickstrebe(wmg strut) Stutzpunkt fur Belastungsversucn (support for static test)

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Wing Load Distributions (calculated and tested) The wing aerodynamic load distribution for critical design cases is calcualted with the well known Multhop lifting line method. The effect of flap/aileron is considered. The mass load distribution (structure, fuel, lumped masses like landing gear) due to vertical and roll acceleration is considered. The total shear (Tx,Ty,Tz ) and moment diagrams (bending-Mx, torsion - My and in plane bending –Mz) moments are calculated. The static test loading may be also defined and compared with the calcualted one.

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Flight Controls Kinematics ( 49 EUR) This program calculates the forces in a 3D push-pull control system for different control system deflections. Cross sections of the rods are defined. The safety factors for buckling are calculated.

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1 Introduce the X. V aid Z coordinates of points A, El C, D Note: Point D is needed if perils A 6,C are on ms same line and cann't define a plane Otherwise point D»C. Mots The program is configurated for 5 pointer A1,AS, ...} including Ihe pilot input (control sick or rudder ps dalj and the hinge F or the I ast nal used points i if Ihsrs are less men 6 poi ntsi tne "used indej ■ should be sel 1o "O' 2 Introduce Ihs nod diameters (external and internal| and E module 3 Introduce ms pilol lorce and me rotation angle in mis point ialpha lor point no l| A Use the EXCEL Solver (Menu Taoist to minimus...

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Manoeuvre and Gust Flight Simulation (99 EUR) Regulations (FAR/JAR/CS,VLA, LTF-UL) provide simplified formulas for gust. The resulted forces and load factors are normally conservative. A more detailed calculation may be performed by means of a flight simulation of the gust/manoeuvre in which the vertical translation and pitch rotation of the aircraft are considered. A differential equation system defines the A/C motion. By means of this method a time history of all A/C parameters (angle of incidence,

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(graphic) Theoretical Description: The pitc"ing moment and lift equation of motio n were integrated. In order to avoid errors due to integration a very low integration step was used (0.02 sec.) The inertial massic forces due to the HT local load factor will be also considered The standard JAR 23 "cos" vertical gust was introduced: U= Ude/2* (1 -005(2* 3.141 !25!t)) The gust penetration delay between wing and horizontal tail was considered. Two second order differential equations of motion will be nlegrated q"=MtotfJyy ( diff. Equation for the rotation } z"=Fz/V''m ( diff. Equation for vertical...

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• Wing Sections (metal and composite) (49 EUR) A library of composite material layers is defined including all material properties. This library is used to define the layout of a wing cross section (type and no. of layers, 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). Lay out definition ( Schichtendefmition)    Table 1

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(scale factor for profile length) (N*m) (N*m) (N*m) • Landing Gear Strut. Calculation ( 99 EUR) This program simulates the landing of an elastic landing gear leaf (strut) by means of an iterative method. Large geometrical deformations are considered. The force-deformation diagram and the deflected form of the leaf are plotted. The form of the landing gear strut is defined: rectangular or round section. The safety factors for each cross sections are calculated (bending, torsion and total loading). Half struts or cross one piece) struts may be calculated. The tire elastic characteristic is considered.

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