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Sisepõlemismootoriga drooni rootori reduktori projekteerimine

Rei, Olev (2016) Sisepõlemismootoriga drooni rootori reduktori projekteerimine. [thesis] [en] Designing the rotor's reducer for a drone with internal combustion engine.

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Abstract

Käesoleva lõputöö eesmärgiks oli projekteerida rootori reduktor sisepõlemismootoriga droonile. Multikopteri energiaallikaks on radiaalmootor Moki 400. Lõputöö teema on välja pakutud ettevõtte Teamwork Engineering OÜ poolt. Reduktor projekteeriti baasettevõtte poolt antud lähteülesande järgi. Esimeses peatükis tutvustati baasettevõtet. Toodi välja ettevõtte tegevusvaldkonnad ning üldinfo. Tehnilise ülesande peatükk kirjeldab ettevõtte poolt antud nõudeid projekteeritava toote kohta. Kolmandas peatükis käsitletud turu-uuringu käigus uuriti turul olevaid reduktoreid. Uuringust selgus, et soovitud parameetritele vastavad reduktorid pole laialdaselt kättesaadavad või nende olemasolu on puudulik. Neljandas peatükis teostati insenertehnilised arvutused. Leiti sobivad koonusspiraalhammasrattad, milleks valiti ettevõtte KHK toodang. Hammasrataste jaotusringjoone läbimõõt on 30 mm, moodul on 1,5 mm ning ülekandearv on 1. Hambumisest tekkinud ringjõu suuruseks saadi 549 N. Laagriteks valiti radiaaltugikuullaager SKF 7202 BE-2RZP, radiaalkuullaager SKF 6000-Z ning kaherealine radiaalkuullaager SKF 4202 ATN9. Majanduslikus osas leiti reduktori omahind. Toodi välja neli erinevat kuluartiklit, milleks olid projekteerimine, koostamine, ostutooted ning tellimustööd. Tellimustööde hinnaks ühe reduktori kohta saadi 3180 €, projekteerimise hinnaks 3000 €, ostutoodete hinnaks 2088 € ning koostamise hinnaks 160 €. Omahinnaks saadi ühe toote kohta 1405 €. Projekteeritud reduktori maksimaalne pöörlemissagedus on 3800 p/min ning pöördemoment on 7,2 N∙m. Projekteeritud toote massiks tuli ligikaudu 2,5 kg, millega on eesmärgiks seatud 3 kg täidetud. Lõputöö käigus saadi erinevaid teadmisi reduktori projekteerimisest. Projekteeritud prototüübi arendamise vajalikkus selgub katselendude käigus. Arendamist vajab tulevikus kindlasti reduktori korpus, mille massi peab kuju muutmisega optimeerima.

Abstract [en]

The aim of the thesis was to design a rotor’s reducer for a drone with internal combustion engine drone. The energy source of the multicopter is a radial engine Moki 400. The topic of the thesis was suggested by Teamwork Engineering OÜ. The reducer was designed according to the terms of reference given by the enterprise. In the first chapter, the enterprise itself was introduced – including its spheres of activity and general information about the enterprise. The technical assignment chapter describes the different requirements given by the enterprise concerning the designed product. The third chapter encompasses a market survey which analysed the different reducers available on the market. The survey illustrated that reducers, which meet the necessary requirements, are not widely available or their availability is inadequate. General engineering calculations were made in the fourth chapter. Suitable spiral bevel gears, manufactured by KHK Enterprises, were chosen – the pitch diameter is 30 mm, the module is 1.5 mm and the gear ratio is 1. The tangential force caused by gearing is 549 N. Bearings are angular contact ball bearing SKF 7202 BE-2RZP, deep groove ball bearing SKF 6000-Z and deep groove ball bearing, double row SKF 4202 ATN9. The reducer’s manufacturing cost was calculated in the economic chapter. Four expense items were highlighted: designing, assembling, purchased products and contract work. The contract work of a single reducer is 3180 €, the designing cost is 3000 €, purchased products account for 2088 € and assembling costs 160 €. The manufacturing cost of a product is 1405 €. The designed prototype’s maximum speed is 3800 rpm and maximum torque is 7,2 N∙m. Its mass is around 2,5 kilograms which meets the set criterion of 3 kilograms. Different knowledge concerning the designing of a reducer was accumulated during the thesis. The designed prototype can be developed in the future, the necessity of which will be revealed during the test flights. The body of the reducer will definitely be developed, as its mass must be optimized by modifying the shape.

Item Type: thesis
Advisor: Tavo Kangru
Subjects: Mechanical Engineering > Production Engineering and Technology > Machine Elements
Mechanical Engineering > Strength of Materials
Divisions: Institute of Engineering > Machine Building
Depositing User: Olev Rei
Date Deposited: 09 Jun 2016 11:01
Last Modified: 09 Jun 2016 11:01
URI: http://eprints.tktk.ee/id/eprint/2094

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