P18102: RIT Launch Initiative Hybrid Rocket
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Engine Specifications

Table of Contents

Overall Engine Summary

The main goal of this project is to develop a hybrid engine capable of carrying a 120-140lb rocket to an altitude of precisely 30,000 ft. A hybrid engine consists of a solid fuel grain and a liquid or gaseous oxidizer. In order to meet IREC's stability requirements, the rocket will need to reach a velocity of at least 100 ft/s off of the launch rail. This equates to our engine needing to produce a maximum thrust of 1300 lbs. In order to achive this, the engine has been broken down into 6 main subsystems: Propulsion, Feed System, Controls, Power Distribution, Structures, and Thermal.

Main Engine Requirements

For our engine, some of the most iportant requirmeents that it meets include:
  1. The engine shall be able to produce 1300 lbs of thrust
  2. The engine shall be capable of burning for a maximum of 10 seconds
  3. The engine shall have a total wet mass under 100 lbs
  4. The engine shall integrate onto and transfer all thrust to a 6" diameter rocket
  5. The engine shall be capable of surviving up to 20 fires with minimal replacement of parts
  6. The engine shall operate independently on its own internal power
  7. The engine shall receive commands from an external flight/test computer
  8. The engine shall send telemetry data back to the flight/test computer
  9. The engine shall have an extended safe mode of up to 1 hour (TBR)

Propulsion

Feed System

Controller

Power

Structures

Thermal

Thrust

System Architecture

Figure 1: System Architecture

Figure 1: System Architecture

Mass Budget

The total mass of the engine is require to be under 100 lbm wet mass. The popellants are expected to contribute about TBD lbm of this mass, leaing the engine with TBD lbm of dry mass. This mass is broken up by subsystem in the table below:

Cost Estimate

Prop