Nadzvučna mlaznica raketnog motora

Bošković, Siniša (2013) Nadzvučna mlaznica raketnog motora. = Supersonic nozzle of the rocket engine. Master's thesis (Bologna) , Sveučilište u Zagrebu, Fakultet strojarstva i brodogradnje, UNSPECIFIED. Mentor: Guzović, Zvonimir.

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04_07_2013_Diplomski_rad_Boskovic.pdf Jezik dokumenta:Croatian

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Abstract (Croatian)

Predmet ovog rada je projektiranje raketnog motora s posebnim naglaskom na proces projektiranja nadzvučne mlaznice raketnog motora. U radu je predstavljen proračunski model za projektiranje raketnih motora, ukazalo se na složenost metode te potrebu za brojnim empirijskim koeficijentima koji se dobivaju iz eksperimentalnih tabličnih podataka i grafikonima. Isti model je uz upotrebu dopunskih emprijskih relacija primijenjen za proračun jednog malog raketnog motora koji je izrađen kroz studentski projekt „RM-1“. U nastavku je opisana problematika testiranja raketnih motora te izrada ispitne stanice, također u okviru studentskog projekta „RM-1“. \Na kraju je pokazana teoretska podloga za projektiranje nadzvučne mlaznice raketnog motora koja koristi analitički model raspodjele tlaka duž osi simetrije mlaznice uz pomoć funkcije tangensa hiperbolnog. Iako projektiranje nije dovršeno dane su smjernice za njegovo dovršenje.

Abstract

The subject of this thesis is the design of a rocket motor with special attention to the design of the supersonic nozzle. In this thesis a presentation of a calculation method for designing a rocket motor was given, emphasizing the complexity of the method and the need for empirical coefficients that are derived from experimental table data and graphic representations. The same model was used to design a small rocket motor with the aid of additional empirical equations. The rocket motor was build within a student project called „RM-1“. In the continuation of the work a problem of designing and building a rocket motor test bed was described and the construction of the test bed was presented, also within the same student project „RM-1“. In the end a theoretical solution was given to the problem of designing a supersonic nozzle of the rocket motor that uses an analitical model of pressure distribution along the axis of simmetry of the nozzle using the function of hyperbolic tangens. Although the design was not finished a direction towards the solution was given.

Item Type: Thesis (Master's thesis (Bologna))
Uncontrolled Keywords: raketni motor; ispitna stanica raketnog motora; nadzvučna mlaznica raketnog motora; nadzvučno strujanje; hiperbolna funkcija
Keywords (Croatian): Rocket motor, Rocket engine, Rocket motor test bed, Supersonic nozzle of the rocket motor, Supersonic flow, Hyperbolic function
Divisions: 500 Department of Energy, Power Engineering and Environment > 530 Chair of Turbomachinery
Date Deposited: 22 Sep 2014 18:00
Last Modified: 16 Oct 2015 12:50
URI: http://repozitorij.fsb.hr/id/eprint/2335

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