7109 Team Work Page
Table of Contents
Project DescriptionThe objective of this team is to research, design and construct a working, flyable rocket body incorporating components developed by fellow Senior Design teams within the METEOR family. These components include a rocket body consisting of an HTPB fuel grain, pre and post combustion chambers and a nozzle, a guidance package including inertial and visual position tracking hardware and software, course correction jets, and a processor that controls those functions, and a satellite: RIT 1, which will send data back down to Earth for analysis.
All design files can be accessed through the /public/ link at the top of the page.
- 1-2:10 structure to propellant ratio
- Withstand differing temperatures and pressures of flight
- Statically hold all components within rocket
Final Design DescriptionThe overall geometry of the rocket can be broken down into three shells. Starting from the bottom of the rocket, they are:
A thin grade 5 (TI-6Al-4V) titanium shell overwound in polymer matrix carbon composite encases the combustion assembly. Grade 5 titanium was chosen because it is lighter than steel, and retains its strength properties at elevated temperatures better than aluminum. The composite is there to provide extra hoop strength and to reduce shrapnel ejection in the event of an explosion. At the top of the shell, an injection plate, made from grade 2 titanium, is welded to the shell.
A 6061 aluminum shell is fastened to the injector plate above the combustion assembly. This shell encases the plumbing system between the nitrous oxide pressure vessel and the injection plate. It also transfers structural loads between the upper and lower shells. The fuel system uses a servo-actuated ball valve to provide nitrous oxide flow to the guidance team's cold jet propulsion system, and the main engine. It also has a quick release valve for filling the pressure vessel, a check valve to prevent back pressure, and ports for temperature and pressure readings.
The upper aluminum shell houses the nitrous oxide pressure vessel, which is to be a custom made composite tank. The shell provides protection for the tank and also provides a cylindrical base for the guidance systems and satellite to attach.
ConclusionsThe titanium brackets and injector plates have both been machined out of grade 5, and grade 2 titanium, respectively. The lower shell and injector plates have been shipped to Excelco Developments Inc. in Silver Creek, NY for forming and welding.
Formable ceramic insulation was used to encase the exit nozzle and isolate its heat from the structure. In order to correctly form the ceramic, a four-piece mold was machined out of HDPE. The nozzle insulation was molded using this setup.
The exit nozzle's internal geometry is still being finalized by the steel rocket team. A nozzle hasn't been fabricated.
The team acquired quotes for the top and middle shells (aluminum). We were told not to order them for the time being.
The fuel system has been designed, and tested sucessfully under operating pressures. It exceeds all functional requirements. A goal for future projects could be to shorten the design, and custom design & fabricate components (Most components are rated for 2000-3000psi operating pressure).
We are awaiting delivery of the nitrous oxide pressure vessel. The team was unable to acquire a tank rated for our operating pressure (750psi max), and had to settle for a commercially available tank rated for ~12000psi burst pressure. Finding a properly designed tank will be critical for the success of the METEOR project.