High Powered Rocket Team Fall 2015

High Powered Rocket Team Fall 2015

Project ManagerWesley M. Harpster

Team MembersJames Lawrence

Ryan HortonKarna Shah

James “Trey” SimmonsIrfan Shaukat

Project AdvisorDr. Thomas Alberts

Multi-Disciplinary Members

Cindique Simmonds (EET)Derek Hampton (IT)

Alexandre Misenheimer (Junior MAE)

Amanda Nolan (Soph. MAE)

Overview Project Scope Rocket Breakdown Avionics Bay Flight Simulation Commercial Motor Flights Fuel Preparation Research Motor Flight 1 Research Motor Flight 2 Research Motor Results Gantt Chart Budget

Project Scope

Objective Statement: To design and build a custom

engine to successfully launch a rocket to an altitude

of 10,000 feet with a payload of 5 pounds by the end

of the fall 2015 semester with a budget of $2,500.

Acceptable Criteria

Attain a 10,000 foot flight using a purchased

commercial motor with proper parachute deployment.

Successfully test and gather data for one custom motor

prepared by the ODU Rocket Team

Rocket Breakdown Nose Cone Forward Body Tube Avionics Bay Aft Body Tube Motor Housing Main Parachute Drogue Parachute

Avionics Bay Design Progression

Original Design Single Altimeter Board

mounted on an aluminum sled.

New Design Two boards implemented

for redundancy. GPS system was added to

locate rocket. Back to Back arrangement

to allow arming after rocket assembly.

Rail mounted for weight reduction.

Flight Simulation Each flight was simulated

using RASAero 2 and Open Rocket.

This produced 2 altitude levels from which an average could be taken.

The final research launch Open Rocket = 8,104 ft. RASAero = 8,254 ft. Average = 8,179 ft.

Actual Altitude = 8,111 ft. Error = 0.8314%

Commercial Motor Flights

Commercial Flight I Apogee: 4,029 feet Maximum velocity: 538

m/s Time to apogee: 15.5 sec Flight time: 93.15 sec

Commercial Flight II Apogee: 11,960 feet Maximum velocity: 352

m/s Time to apogee: 25.15

sec Flight time: 206 sec

Fuel Preparation

Necessary Components of a Research Motor Propellant Base, Mixing Agent,

Plasticizer, Curing Agent, Catalyst Mixing phases for fuel

1. Liquid components (binding agent, catalyst, plasticizer)

2. Metal oxide catalyst 3. Oxidizer

Allow the mixer to run for 3-4 hours

Apply mold release to all surfaces that are not propellant tubes

Shape and press propellant into tubes and allow to cure

Research Motor I Propellant Composition

Propellant Base: Ammonium Perchlorate – 76.90%

Mixing Agent: Aluminum – 5.0% Plasticizer: Dioctyl Adipate – 3.0% Curing Agent: R45HT-LO – 13.0% Curing Agent: E744 – 2.0% Catalyst: Iron Oxide – 0.1%

Comparisons to a commercial motor This motor would be similar to a

white propellant. Such as Aerotech’s White Thunder

Research Motor II

Propellant Composition Propellant Base: 74.75%

Ammonium Perchlorate Mixing Agent: 2.54% Aluminum

Powder Plasticizer: 3.5% Dioctyl Adipate Curing Agent: 11.74% R45HT-LO Catalyst: 0.75% Black Copper

Oxide Stabilizer: 4.5% Strontium

Carbonate Increase Strength: 0.3% Tepanol

Research Motor Results

Research Flight I Apogee: 3,156 feet Maximum Velocity: 157

m/s Time to apogee: 13.6 sec Flight Time: 84.9 sec

Research Flight II Apogee: 8,111 feet Maximum Velocity: 803

m/s Time to apogee: 21.65 sec Flight Time: 114.7 sec

Gantt Chart

Funding

Source MAE Dept. MAE Dept. NASAODU Grant

Dr. Bawab Loan Testing Miscellaneous Launch Prep Shipping Total

Received $354.00 $1,232.45$500.0

0 $1,000.00          $3,086.4

5

Spent         $1,500.00$971.5

6 $250.08 $696.51 $50.00$3,468.1

5

Total                   -$381.70

Questions?