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Author:Fagerström, Christoffer
Title:Tuulitunnelin monikomponenttivaa'an mekaaninen suunnittelu
The mechanical development of a multi-component wind tunnel balance
Publication type:Master's thesis
Publication year:2010
Pages:(6) + 64 s. + liitt.      Language:   fin
Department/School:Koneenrakennustekniikan laitos
Main subject:Koneensuunnitteluoppi   (Kon-41)
Supervisor:Pietola, Matti
Instructor:Korhonen, Mikko
OEVS:
Electronic archive copy is available via Aalto Thesis Database.
Instructions

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Location:P1 Ark Aalto  4839   | Archive
Keywords:wind-tunnel
multi-component balance
strain gauge
FEM
CAD
tuulitunneli
monikomponenttivaaka
venymäliuska
FEM
CAD
Abstract (eng): This thesis is part of a project concluded by the Finnish air force.
The goal of the thesis is to study the effect of external objects, such as missiles and containers, on the aerodynamic loads of a fighter aircraft.

A wind tunnel balance is used to determine the aerodynamic forces and moments of the wind tunnel model being tested.
The main content of this thesis is the mechanical design of a five component strain gauge balance to be used in a series of wind tunnel tests in the transonic speed regime.
Events at these flow speeds close to the Mach number 1 are hard to predict.
The balance is implemented as an external one, but using a monolithic design typical for internal balances.
The wind tunnel model used is a fighter aircraft half model.

In this thesis, four different balance concepts are compared and judged based upon six different criteria, with the help of parametric 3D-CAD models and FEM-analysis.
A principle solution for fastening the balance to the structures of the wind-tunnel and the model is also presented with the help of parametric CAD-models and FEM-analysis.

A manufacturing drawing of the balance is made, according to which, the balance is manufactured.
The manufactured balance is calibrated utilizing the specialized equipment and software of the Laboratory of Aerodynamics.
Abstract (fin): Tuulitunnelikokeen aikana testattavaan tuulitunnelimalliin vaikuttavia aerodynaamisia voimia ja momentteja mittaavaa laitetta kutsutaan tuulitunnelivaa'aksi.
Tässä diplomityössä suunnitellaan ulkoinen viiden komponentin tuulitunnelivaaka käyttäen sisäisen monoliittisen venymäliuskavaa'an tekniikkaa.

Vaakaprojekti liittyy ilmavoimien hankkeeseen, jossa halutaan tutkia hävittäjälentokoneeseen aiheutuvia voimia, kun siihen kiinnitetään ulkopuolisia esineitä kuten ohjuksia ja säiliöitä.
Erityisesti halutaan selvittää tapahtumia transsoonisella virtausnopeuden alueella eli lähellä Machin lukua 1, sillä tapahtumia tällä nopeusalueella on vaikea ennustaa.
Käytetty tuulitunnelimalli on lentokoneen puolimalli.

Tässä diplomityössä vertaillaan neljää eri vaakakonseptia, joita arvostellaan kuuden kriteerin perusteella.
Konseptien ja lopullisen vaa'an suunnittelussa käytettään apuna parametrisiä 3D-CAD malleja sekä FEM-analyysia.
Vaa'an ripustuksesta tuulitunnelin rakenteisiin sekä kiinnityksestä lentokoneen pienoismalliin esitetään perusratkaisu, josta myös tehdään 3D-CAD mallit ja suoritetaan FEM-analyyseja.

Vaa'asta tehdään työpiirustus, jonka perusteella vaaka valmistetaan.
Valmiille vaa'alle suoritetaan kalibrointi aerodynamiikan laboratorion kalibrointilaitteistolla laboratorion itse kehittämän ohjelmiston avulla.
ED:2010-10-15
INSSI record number: 41098
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