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The mission includes development of standardized payload subsystems and manuals that facilitate increasingly complex future payloads and the maximum transfer of corporate knowledge to future student participants. Additionally, the mission will provide opportunities for students to design, implement, and test innovative systems through hands-on experience and collaboration between disciplines, universities and practicing aerospace engineers and scientists.

Project DIONISYS: Mechanical Components

Nosecone Payload tube Payload frame Umbilical block Drag plate Radax joint Parachute recovery sys. Separation system

Drag Plate

A picture of SRP-4 Nose coneRequirements:
RF transparent
Light-weight
Maintain integrity to 700
degrees F at tip and 350 F at base
Mate to payload tube
Withstand aerodynamic loading
Be constructed to minimum tolerances

Description:

A 4 to 1 tangent ogive has been chosen for the nose cone. This shape will provide superior aerodynamic performance at speeds of > mach 1.
Due to extreme aerodynamic heating, the top 2" of the nose tip will be made of mild steel. To reduce this heating as much as possible the tip will have a 3/16" radius. This will project the shock wave approximately 15" in front of the rocket’s nosetip.
The nose cone will also support TPU’s RF antenna. This will be attached with four screws that run through the nose cone and into the antenna support.

Materials:

The nosecone is to be constructed of a RF transparent material, probably glass reinforced epoxy approximately 1/8" thick.
A commercial supplier will be located if the nosecone cannot be fabricated “in house”.

Interfaces:

The nose cone will be attached to the payload tube by a 4" aluminum ring. The ring will extend 2" into the nose cone and 2” into the payload tube. It will be connected by two rows of 10 screws in both the payload and nose cone. These will be flat head screws set flush to the surface.