1 / 24

Advanced Rocket Motor System Design for Enhanced Flight Performance and Safety

This project presents the design and development of a rocket motor system incorporating a highly efficient fuel grain made of R-45M resin, cross-linked with diisocyanate. Key components include a lightweight 6061-T6 aluminum motor housing, a high-temperature ceramic composite nozzle, and an ignition system optimized for reliability. The motor is static-tested to 1200 psia and designed for a maximum altitude of 10,641 feet AGL with a burn time of 5.4 seconds. Safety protocols for fuel mixing, including dry and liquid chemicals, ensure optimal performance and minimize risks.

kiril
Télécharger la présentation

Advanced Rocket Motor System Design for Enhanced Flight Performance and Safety

An Image/Link below is provided (as is) to download presentation Download Policy: Content on the Website is provided to you AS IS for your information and personal use and may not be sold / licensed / shared on other websites without getting consent from its author. Content is provided to you AS IS for your information and personal use only. Download presentation by click this link. While downloading, if for some reason you are not able to download a presentation, the publisher may have deleted the file from their server. During download, if you can't get a presentation, the file might be deleted by the publisher.

E N D

Presentation Transcript


  1. University of Utah Unity IV Responsibilities • Motor System • Fuel • Nozzle • Ignition • Flight Profile • Maximum Energy Footprint

  2. Motor System • Fuel • HTPB: Fuel grain composed of R-45M resin • Cross- linked with diisocyanate • Motor Housing • 6061-T6 Aluminum • Static tested to 1200 psia • Nozzle • Ceramic Composite • Rated to 5000 F

  3. Ignition • Model Rocket Motors • 2, Estes C8-0 motors • Accessible on Launch Rail • Low power requirement • 4 AA Batteries • Reliable Performance

  4. NO2 inlet “O” Ring Seal Estes C8-0 Motor Injector HTPB HTPB Motor Cap Assembly

  5. Flight Profile • Maximum Altitude • 10,641 feet AGL, at T = 28 seconds • Burn Time • T = 5.4 seconds • Flight Velocity • Launch Rail Exit = 89.1 ft/s • Overall Flight = 0.71 Mach • FTS Failure Impact • 763 ft/s at T=58 seconds

  6. Maximum Energy Footprint • 5.40 Miles at q0=450 • No Critical Areas with in Range

  7. Motor Assembly

  8. Motor Cap

  9. Motor Housing

  10. Motor Nozzle

  11. Motor Nozzle

  12. Motor Nozzle Retainer

  13. Motor Assembly

  14. Fuel Mixing Procedure • Safety Equipment • Liquid Chemicals • Incorporate By Hand • Dry Chemicals • Incorporate By Hand • Mix For 30 Minutes

  15. Fuel Mixing Problems • Need More Mixing Time • Recipe • Catalyst

  16. 3” Motor Fuel Mixing

  17. 8” Motor Fuel Mixing

  18. Modified Fuel Mixing Tank

  19. Portable Oven Design 1

  20. Portable Oven Design 2

  21. Portable Oven Design 3

  22. Mandrel Configurations

  23. Mandrel Configurations

  24. Mandrel Configurations

More Related