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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

Separation System

Requirements:

Mate to payload tube/frame
Hold payload to motor within acceptable deviation at > 100,000 in-lbs torque
Have > 9.5” hole in center for recovery system deployment
Provide positive separation in zero g and zero drag environments

Description:

The separation system needs to perform two opposing functions:

Hold the rocket together rigidly during boost
Release the payload from the motor quickly and cleanly

Systems Under Consideration

There are two separation systems that we are considering for SRP 4:
A student built separation system from UAF
An “off the shelf” separation system from NASA

The student built system is still in the early design phase. It will be evaluated for acceptance when a prototype is presented.

Interfaces:

The separation system will attach to the payload tube by the radex joint described aboveand attachment to the Orion motor will be according to NASA specifications. The separation system’s triggering device will also need to interface with the EED board.