System integration

Work Process Detail

🛠️ Mechanical Integration

• Rocket Body Assembly
  • Nose cone, payload bay, parachute.

  

  

  

• Mounting of Components
  • barometer securely placed

  

  • Spring-loaded deployment bay with servo mechanism

    

    

  

• Airframe Finishing
  • Body tubes joined with precise couplers

  

  

  

  

  

  

  

  • Integration of fiber glass to reinforced parts

  

  

• Packaging
  • Mechanical components housed in durable compartments

  

  

  

  • Design ensures easy access for maintenance and assembly

    

🔌 Electrical Integration

• PCB Design and Mounting
  • Custom PCB with ESP32-C3, barometer (BME680), servo , buzzer.

  

  

  

  

  • Properly soldered components with labeled connectors

    

• Wiring and Connectors
  • connectors and headers for modularity

    

  • Heat-shrink tubing and cable management for durability and clarity

  

• Power Supply
  • 7.4V Li-Po battery with voltage regulation circuit

    

  • On/off switch and “Remove Before Flight” jumper trigger

    

💻 Software Integration

• Sensor
  • Barometric sensor used to detect apogee

  

• Flight Sequence
  • System Logic:

    1. Initialization (setup() function)

    • Serial communication starts for debugging.

    • Pin configuration is set:
      • RBF_PIN (Remove Before Flight pin) is input.
      • BUZZER_PIN is output.

    • Servo is attached and set to 180° (arming position).

    • BME680 barometric sensor is initialized and configured for accurate altitude readings.

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    2. Waiting for Launch Preparation (loop() function)

    RBF logic:

    • The system waits until the RBF_PIN (Remove Before Flight pin) is pulled LOW (i.e., shorted or pulled to GND).

    • Once detected:
      • The current time is recorded in rbfRemovedTime.
      • The buzzer beeps once to confirm the system is armed and entering delay.

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    3. 2-Minute Arming Delay

    • After RBF is removed, the system waits 2 minutes (120,000 ms).

    • During this time, nothing else happens—this is your safety delay before launch.

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    4. System Starts After 2 Minutes

    • After 2 minutes, the system:
      • Beeps again
      • Prints altitude to Serial Monitor for testing

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    5. Real-Time Flight Logging

    • On every loop:
      • The BME680 reads pressure.
      • Altitude is calculated using the standard barometric formula.
      • Altitude is printed on the serial monitor.

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    6. Apogee Detection (Key Logic)

    • The code checks if the rocket is still gaining altitude.

    • If altitude keeps increasing, it keeps updating apogeeAltitude and apogeeTime.

    • Once altitude stops increasing for more than 2 seconds:
      • Apogee is confirmed.
      • Servo is activated → rotates from 180° to 0°, releasing the parachute.
      • deployed = true is set.

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    7. Landing Detection

    After deployment:

    • The code monitors the altitude readings:
      • If the altitude is stable (±0.2 m) for over 5 seconds,
      • It assumes the rocket has landed.

    • The buzzer is triggered to continuously beep so you can find the rocket on the ground.

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    What the System Does (Full Timeline):

    1. Power ON → System waits for RBF pin to be pulled

    2. RBF pulled → 1 beep → 2-minute wait

    3. After 2 minutes → 2nd beep

    4. Rocket launches → Altitude increases

    5. Apogee detected (altitude stops increasing for 2 seconds) → Servo activates → parachute deploys

    6. Altitude stabilizes after landing → Continuous buzzer sound helps you locate it

📦 Packaging & Professional Finish

• Component Housing
  • All internal parts securely fastened and protected
  • Servo and deployment system integrated into central bay

  

• Cable Management
  • Clean and organized internal layout

  

• External Finish
  • Painted and labeled body, smooth aerodynamic surfaces