high powered rocket team fall 2015. project manager wesley m. harpster team members james lawrence...
DESCRIPTION
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 BudgetTRANSCRIPT
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?