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## Preliminary optimization algorithm of small rocket

### Krystian Kazimierz Olechowski

#### Abstract

The aim of the following thesis is to create an optimization algorithm of small launch rocket. The payload ratio is the optimized parameter. The payload ratio is defined as a ratio of payload mass to total mass. Input parameters are exact mission requirements along with created data base of engines used in small launch rockets. To optimize payload ratio, the algorithm performs series of calculations regarding input parameters. Calculations are computed iteratively, for each avaliable configuration of engines. The most optimal variant is chosen from the obtained results. First of all, using given mission requirements and celestial mechanics, the algorithm calculates the minimal velocity required to enter the target orbit. One of the assumptions used in this thesis is using the Hohmann transfer orbit i.e entering respectively low earth orbit with height 200 km, eliptical Hohmann orbit and target orbit. By calculating velocity changes required for Hohmann transfer and the aerodynamical velocity loss, the algorithm computes the minimal velocity required to enter the target orbit. Afterwards, by using method of Lagrange multipliers, algorithm computes the minimal total mass of the rocket required to speed up the given payload to the minimal velocity required to enter the orbit. After acquiring an information about total mass of the rocket, payload ratio is computed. Algorithm iterates foregoing calculations for each avaliable configurations of engines and chooses the one with highest payload ratio. It means that for this particular configuration the total mass required to send the payload to target orbit is the lowest. For the algorithm, there is created a graphical user interface which lets the user to input the data directly in the application window. Afterwards, user can display the results on screen. Correctness of the algorithm was verified by computing the procedure for a specific case.
Diploma type
Engineer's / Bachelor of Science
Diploma type
Engineer's thesis
Author
Krystian Kazimierz Olechowski (FPAE) Krystian Kazimierz Olechowski,, Faculty of Power and Aeronautical Engineering (FPAE)
Title in Polish
Wstępny algorytm optymalizacyjny małej rakiety nośnej
Supervisor
Łukasz Mężyk (FPAE/IHE) Łukasz Mężyk,, The Institute of Heat Engineering (FPAE/IHE)Faculty of Power and Aeronautical Engineering (FPAE)
Certifying unit
Faculty of Power and Aeronautical Engineering (FPAE)
Affiliation unit
The Institute of Aeronautics and Applied Mechanics (FPAE/IAAM)
Study subject / specialization
, Lotnictwo i Kosmonautyka (Aerospace Engineering)
Language
(pl) Polish
Status
Finished
Defense Date
25-03-2019
Issue date (year)
2019
Pages
37
Internal identifier
MEL; PD-5047
Reviewers
Jan Kindracki (FPAE/IHE) Jan Kindracki,, The Institute of Heat Engineering (FPAE/IHE)Faculty of Power and Aeronautical Engineering (FPAE) Łukasz Mężyk (FPAE/IHE) Łukasz Mężyk,, The Institute of Heat Engineering (FPAE/IHE)Faculty of Power and Aeronautical Engineering (FPAE)
Keywords in Polish
Rakieta, algorytm optymalizujący, silnik rakietowy
Keywords in English
Rocket, optimization algorithm, rocket engine
Abstract in Polish
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praca_inż_-_Olechowski_Krystian_-_276452.pdf
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Local fields
Identyfikator pracy APD: 32557

Uniform Resource Identifier
https://repo.pw.edu.pl/info/bachelor/WUT6562c6dc61b44a4db27e63f16b1fa2fe/
URN
urn:pw-repo:WUT6562c6dc61b44a4db27e63f16b1fa2fe

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