METEOR Flying RocketP07109

METEOR

Microsystems Engineering and Technology for the Exploration of Outer space Regions

Project P07109 – Flying Rocket

Andrew Scarlata – ME -- Team Leader

Geoff Cassell – ME -- Lead Engineer

David Hall – ME -- Lead Engineer

Luke Cadin – ME

Zack Mott – ME

Garett Pickett – EE

Brian Whitbeck – ME

Team Guide – Dr. Jeffrey Kozak

Team Advisor – Dr. Dorin Patru

Table of Contents

** Possible organizational structure, very open to suggestion** ljc 2/3/07

Abstract

Introduction

  • Why hybrid rockets?
  • How do hybrid rockets go?
  • How do we launch our rocket?**Launch Profile Picture?** ljc2/3/07
  • List of terminology/definitions **Maybe at the beginning?** ljc 2/3/07

History

  • 2004
  • 2005
  • 2006

Current Projects

Needs Assessment

Design Objectives

Concept Development

  • Semi-detailed design models
  • Classic
  • Chalice
  • Embedded Fuel Grain
  • Annular Tank
  • External Tank

Concept Selection

  • Pugh’s matrix
  • Pros Cons, etc…
  • Final design selection

Engineering analysis of Final design

  • ANSYS analysis
  • Detailed solidworks model
  • Material selection
  • Ignition system design
  • Weight calculation

Conclusions

References

Abstract

Introduction

It is now apparent that the future of any global business is dependent on geosynchronous satellites; however the cost for launching an object into space is reaching near astronomical levels. As a result, teams of engineers are developing cheaper and safer means of launching objects into space. The future of this endeavor seems to be on the shoulders of hybrid rockets. In addition to many other universities, Rochester Institute of Technology has implemented a project devoted to the study of hybrid rockets, and as a result, project METEOR was born. Project METEOR consists of a four stage hybrid rocket and launching platform. Though the initial goal of this project is launching small payloads into a low-Earth orbit, the final objective is landing these payloads on the moon or near Earth asteroids to gather and transmit data.

The hybrid rocket is driven by both a solid fuel and a liquid oxidizer. In the case of METEOR, the solid fuel is HTPB, while the oxidizer is N2O. The hybrid rocket propellant system has many advantages over its antiquated counterpart, the solid propulsion system. Hybrid designs are safer, cheaper, and have improved throttling, restart ability, and environmental cleanliness. On the other hand, hybrid rockets can be more technically challenging.

The launch profile for the METEOR project is a unique airborne approach. The process begins with the launch platform being raised to 100,000ft using a helium weather balloon. Once the altitude has been reached, the platform stabilizes itself and the rocket is aligned. After stabilization, the rocket is launched. The platform then deploys a parachute and descends to Earth to be recovered and reused. The main benefit of this airborne launch is that the atmosphere at 100,000ft is roughly 1% of sea level atmosphere, so aerodynamic drag is negligible. This method is also considerably cheaper than a traditional ground level launch approach.

***I am not sure how much technical information we want to put here. I think as long as the reader has a good idea of what hybrid rockets are and how we intend to launch them we will be fine. I’m sure we will cover all the really detailed technical information in the sections to come*** ljc 2/3/07

History

The METEOR project is entering its third year of development. Teams of fourth and fifth year engineering students have been working on the project as part of Rochester Institute of Technology’s multi-disciplinary senior design program. The first METEOR team started in 2004 (04-036). This team was composed of mechanical and electrical engineers. Since this was the first project in the METEOR track, the main focus of this assignment was finding a way to conduct near space launches and experiments. Essentially, the team was drafted to design a test platform that could be carried up to 80,000ft on a helium balloon. The main objectives of this project were eliminating ground launch equipment, having the ability to change latitude that the launch occurs, and to reduce overall air resistance and drag. The next team in the METEOR track began in 2005 (05-005). This team was composed of just two electrical engineers, both of which were enrolled in the BS/MS program. The task of this team was to improve the 2004 team’s design. In addition to optimizing the previous design, they were asked to improve power consumption and decrease the overall weight. The year 2006 saw a surge in interest for the METEOR project. As a result, two teams were assigned to the project, a rocket design team (06-006), which was composed entirely of mechanical engineers, and a platform design team (06-005), a combination of mechanical and electrical engineers. The rocket design team was asked to create a rocket that was safe for ground testing. The team was responsible for laying the groundwork for the following: overall hybrid rocket layout, fuel grain design, oxidizer feed system, rocket nozzle design, ignition, test stand, and instrumentation/data acquisition. The information gathered from this ground test would be integral to the rocket design teams that would come later.The platform design team was responsible for further optimizing the test platform, as well as taking the platform to 100,000ft.

Current Projects

The most recent evolution of the METEOR project involves many different teams. As of 2007, there are eight different teams focusing on different aspects of the project. A team has started looking into RIT’s first satellite, the RITSAT 1 team (07104). Two teams have been assigned to the launch platform, one to place sensors on the platform, the instrumentation platform team (07103), and one to return those sensors to Earth so they may be used again, the gliding instrument platform team (07108). A pair of industrial engineers has been given the task of writing a mission control procedure (07107). Three teams, comprised of both mechanical and electrical engineers, have been assigned the task of designing and testing the rocket: the steel rocket team (07105), the guidance team (07106) and the flying rocket team (07109). These teams are all the offspring of the original rocket design team, but instead of one team taking on the responsibility for the entire rocket design, the workload has been split into different sections. The steel rocket team is responsible for optimization of nozzle geometry, fuel grain, and the oxidizer flow rate. In addition, they are responsible for the ignition system. The guidance team is focusing their efforts on the design, manufacture, and testing of an inertial navigation system and thrust vector control. The flying rocket team involves the design, manufacturing, and ground testing of the rocket body and components. In addition, the test stand team (07110) iscommitted to designing and building a test stand system that holds the rocket, including physical configuration, structural design, and data acquisition. All of these teams have to work together to produce the final result, a single stage rocket that is ready for launch in the summer of 2007.

**I was also thinking of just discussing steel rocket, guidance, flying rocket, and the test stand. Mentioning all the teams may be overkill.** ljc 2/3/07

Needs Assessment

The scope of this project involves designing and manufacturing a fully functioning hybrid rocket stage. The body of the rocket must be structurally sound and capable of withstanding the forces and pressures associated with the rocket launch. The rocket weight must be kept to a minimum. The weight is the most significant factor that our team is to consider, and as such, alternative materials, such as composites and lightweight aerospace grade metals, need to be fully researched and used. Also, our team is working cooperatively with the guidance and steel rocket teams, so our design must incorporate the guidance team’s equipment and the steel rocket team’s engine components. Once the design phase is complete, two versions of the rocket stage must be fully manufactured, so ease of manufacture is another critical aspect of the project. One rocket may be manufactured of comparable but cheaper and heavier metal to ease proof of performance testing and the connection to the vertical test stand. The second rocket will, of course, be made to the design specifications to be launched. Cost is another important factor, and since most elements of the rocket will have to be custom made, the budget is an important component to consider.

Design Objectives

  • Maintain structural integrity
  • Structure to propellant ratio of 1:10
  • Safe containment of combustion process and fuels
  • Accurate theoretical model
  • Accommodation of other systems
  • Manufacturing feasibility
  • Stay within the $10,000 budget

Concept Development

Coinciding with our needs assessment, individual team members came up with preliminary concepts for overall system level designs for the rocket. Those concepts were combined into five final concepts that would continue on to be evaluated against each other and assumed standards to find the best design to pursue. The five designs were as follows: the Classic, Chalice, Embedded fuel grain, Annular oxidizer tank, and External Oxidizer tanks.