
The Structure sub-system is responsible for maintaining the structural integrity of Firehorn I while also ensuring the seamless integration of all other sub-systems.


The internal structure aims to ensure the structural integrity of the rocket. For this, it must both keep all the subsystems together and withstand all the loads applied to it.

Couplers are used to assemble the various modules of the Firehorn rocket.
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The airframe is mounted on the internal structure, sealing the vehicle.

The nosecone minimizes aerodynamic resistance during launch by reducing drag while, hosting the payload.
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2024_C_ST_NOSECONE_DJF Design Justification File (Preliminary Design)
Zina Randriamanantena
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2024_C_ST_NOSECONE_DDF Design Definition File (Critical Design)
Gabriel Mollet
Thomas Sancenot
Emma Gerart
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2024_C_ST_NOSECONE_FEA Finite Element Analysis (Critical Design)
Zina Randriamanantena
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2024_C_ST_NOSECONE_TOOLING_DJF Design Justification File (Preliminary Design)
Zina Randriamanantena
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2024_C_ST_PAYLOAD-BAY_DJF Design Justification File (Preliminary Design)
Cyril Barthelet
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2024_C_ST_PAYLOAD-BAY_DDF Design Definition File (Critical Design)
Paul Pedelaborde
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2024_C_ST_NOSECONE_PREPREG_MAP Manufacturing Procedure (Attempt)
Yannick Hansen
β 2024_C_ST_NOSECONE_INFUSION_MAP Manufacturing Procedure (Infusion version)
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2025_C_ST_PREPREG_MAP Manufacturing Procedure (Prepreg version)
Thomas Sancenot
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2024_C_ST_PAYLOAD-BAY_MAP Manufacturing Procedure
Paul Pedelaborde

The recovery bay hosts the parachute system.
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The separation mechanism triggers at apogee, splitting the vehicle in two parts and allows the release of the parachute.

The avionics bay hosts the main part of the avionics, including the main PCBs, antennas and battery pack.

The pressurant bay hosts the pressurization system

Ethanol and LOX tanks with a capacity of 16L and a working pressure of 60 bar.

The mid bay is the transition structure between the two tanks and their respective plumbings.

The engine bay hosts the engine system as well as the fins.