Purpose

The structure of the vehicle is the primary load bearing and aerodynamic which holds everything together. It must be strong enough to survive the flight, but as light as possible in order to allow completion of mission goals.

Requirements

The following requirements come from the DTEG.

Requirement	Description	Component	Compliance
6.1	Adequate Venting	Nose Cone	Attachment sufficient to allow nose cone to be unvented
6.1	Adequate Venting	Avionics Bay	Venting sufficient for good barometer performance.
6.1	Adequate Venting	Airframe	Venting sufficient to prevent premature separation
6.2	Structural Integrity	Fin Can	Doesn't Break in flight.
6.2	Structural Integrity	Airframe	Doesn't Break in flight.
6.2	Structural Integrity	Avionics Bulkhead	Doesn't Break in flight
6.2	Structural Integrity	Payload Bulkhead	Doesn't Break in flight
6.2	Structural Integrity	Nosecone	Doesn't Break in flight
6.2.1	Material Selection	Architecture	No PVC or Stainless Steel is used on the rocket.
6.2.3	Coupler Length	Avionics Bay	Exemption Obtained for Nose Cone interface. Airframe interface is compliant
8.2	Launch Stability	Architecture	Demonstrate Vehicle stability off the rail
8.3	Aerodynamic Stability	Architecture	Minimum vehicle stability margin is greater than 1.5
8.4	Aerodynamic Stability	Architecture	Maximum vehicle stability margin is less than 6