# Purpose
The Texas A&M Sounding Rocketry Team designs, builds, and flies its own hybrid rocket. 
As part of its design cycle, static cold flows and static engine tests are performed to chacterize the engine's oxidizer tank,
fluid system, and combustion process.

# Overall System Design
During a static engine test, we load solid HTPB fuel into the combustion chamber. As part of the test procedure, we load nitrous oxide into the run tank via the fluid panel. We then ignite the starter, and open the ball valve actuation system (BVAS) to begin our combustion cycle.

## Concept of Operation
![](readme_media/conops_without_av.png)

## Control Box
The control box is responsible for taking in operator inputs and sending them to the actuator box over CAN. The control box also receives feedback from the actuator box and updates the assortment of LEDs and the LCD screen on the indicator panel.

### Logic Diagram
![](readme_media/control_box/control_logic.png)

### Power Diagram
![](readme_media/control_box/control_power.png)

## Actuator Box
The actuator box is responsible for actuating valves on the oxidizer fluid panel, main throttle valve on the engine, and igniting the starter system. During a test when avionics is deployed, the avionics stack handles engine control while the actuator box controls ground support systems.

### Logic Diagram
![](readme_media/actuator_box/actuator_logic.png)

### Power Diagram
![](readme_media/actuator_box/actuator_power.png)

# Physical Design
## Control Box
### Display PCB

### Main PCB

### Housing and Switch Panel

## Actuator Box
### Actuator PCB

### Actuator Box Housing

# Arduino Software
## Control Box

## Actuator Box

# System Upgrades After Initial Design
## Servo Motor Main Valve for Throttling

## MODBUS TCP Communication for Integration in Ignition SCADA