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Design Overview: KISS T006

While our final rocket for space will be the Ambition-III, Keep It Simple Stupid (KISS) has been our design motto. We think it makes a great name for our prototype rockets. 

Major Systems

Click on a system for more information

Technical Specifications

Propellant
Type: Ammonium Perchlorate Composite Propellant
Mass: 95.50 kg (210.54 lbs)

Materials
Nozzle: Graphite
Thrust Chamber: S-2 Fiberglass
Nose Cone: Fiberglass reinforced polymer
Nose Cone Tip: Inconel Alloy

Masses
Gross Lift-Off Mass (GLOM): 184.00 kg (405.65 lbs)
Burnout Mass: 88.50 kg (195.11 lbs)



 

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Nose Cone

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Fast Facts:

  • Nose Cone Profile: Von Karman Ogive

  • Material: Fiberglass reinforced polymer

The nose cone has been optimized to minimize both mass and drag. The nose cone body is made of radio-transparent fiberglass for our avionics systems and tipped with a "bluffed" Inconel tip to survive aerodynamic heating.  

 

Propellant

Fast Facts:

  • Propellant Type: Ammonium Perchlorate Composite Propellant (APCP)

  • The Space Shuttle Solid Rocket Boosters (SRB) used a type of APCP

The propellant has Ammonium perchlorate as an oxygen source, aluminum powder as fuel, and HTBP (polymer resin) as fuel and binding material. The "grain" has a hollow core to burn from the inside out. 

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Thrust Chamber

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Fast Facts:

  • Material: S-2 Fiberglass

The thrust chamber must be strong and rigid to contain the heat and pressure developed during the motor burn. It also provides the primary structure of the rocket. 

 

Nozzle

Fast Facts:

  • De Laval Convergent-Divergent nozzle

  • Material: Medium and Fine grain graphite

The nozzle facilitates a thermodynamic trade off, accelerating the hot and high temperature gasses to an ambient pressure high velocity stream. The two grades of graphite provide a balance of cost effectiveness and high stress performance.

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Composite Fins

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Fast Facts:

  • Material: G10

  • Number of Fins: 4

  • Fin Shape: Trapezoidal

The fins keep the rocket flying straight. They are placed in the rear of the rocket, moving the center of pressure well behind the center of gravity, ensuring flight stability.