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Conceptual Design of a Solid Propellant Nanolauncher

Ghadiri, Sajjad | 2020

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  1. Type of Document: M.Sc. Thesis
  2. Language: Farsi
  3. Document No: 53027 (45)
  4. University: Sharif University of Technology
  5. Department: Aerospace Engineering
  6. Advisor(s): Farahani, Mohammad; Mohammadi, Alireza
  7. Abstract:
  8. Nanolaunchers are launch vehicles capable of carring light payloads (under 50 kg) to Low Earth orbit and received much attention in the few past years. Launching the nanosatellites grown about 30 times from 2008 to 2017. Since this category of launch vehicles has fewer developing costs and lower thechnology level, they fit developing space technology in our country. Conversely, the demand of high propellant mass fraction and specific impulse may be a serious difficulty to attain this technology.The only operating nanolauncher in the world is SS-520-5 which belongs to Japan and is a three-stage solid propellant launcher. The goal of this project is also the conceptual design and feasiblity study of a solid propellant nanolauncher. To optimize the design, Multi-Disciplinary Design Optimization approach is used. The effect of components material and the mass of avionics on the payload delivery capability is examined. The results show that a key step toward the development of nanolauncher is to attain lightweight and safe avionics.During this project, the author conducted a deep study in the erosive burning aera and finally succeeded in developing two new correlations to quantify this effect. Also, an accurate mass model is developed for SRMs and a unified environment is stablished to optimize the SRM design and its trajectory. In addition, a one-dimensional steady internal ballistics solver code is developed
  9. Keywords:
  10. Erosive Burning ; Conceptual Design ; Solid Propellants ; Launch Vehicle ; Multidisciplinary Optimization ; Multi-Disciplinary Design Optimization ; Solid Propellant Rocket

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