HIGH POWERED ROCKET TEAM FALL 2015

HIGH POWERED ROCKET TEAM FALL 2015

HIGH POWERED ROCKET TEAM FALL 2015 Project Advisor Dr. Thomas Alberts Project Manager Wesley M. Harpster Team Members James Lawrence Ryan Horton Karna Shah James Trey Simmons Irfan Shaukat Cindique Q Simmonds (EET) Derek Hampton (IT) Alexandre Misenheimer (Junior MAE) Amanda Nolan (Soph. MAE)

OVERVIEW Project Schedule Goals Rocket Preparation Avionics Bay Commercial Motor Test Custom Motor Test Fuel Characterization Future Work

GANTT CHART UPDATED 10.14.15

PROJECT GOALS Objectives Reach an altitude of 10,000 feet with a custom built rocket motor. Acceptable Criteria Successfully Complete a static test of a custom motor with data collected. Achieve an altitude of 10,000 feet with proper parachute deployment using a commercial motor. Accomplishments Reached an altitude of ~11,960 feet using a commercial motor with fully successful recovery. Completed a successful flight of a custom motor to an altitude of ~2,500 feet and data was collected. Future Plans Build a custom rocket motor capable of achieving an altitude of ~8,000 feet and launch in November.

ROCKET MODELING AND SIMULATION (K695R)

K695R SIMULATION

ROCKET MODELING AND SIMULATION (L1250DM)

L1250DM SIMULATION

AVIONICS BAY DESIGN Avionics Bay was redesigned to reduce weight. Redundancy was added to ensure a backup incase the primary charges failed. GPS system was added incase rocket drifted too far from launch site. Boards were mounted back to back to allow for arming on launch pad.

AVIONICS BAY DESIGN

AVIONICS BAY DESIGN GPS plate for avionics bay Bulk Heads

EJECTION CHARGE TESTING Certification Rocket: Forward Body Tube: 1.3g Aft Body Tube: 1.48g Forward Bay Ejection Charge Aft Bay Ejection Charge Big Rocket Forward Body Tube: 1.68g Aft Body Tube: 2.57g

OCTOBER 10/11 LAUNCH PLAN Launch 1: GPS Test Launch 2: Test to reach 10,000 feet Launch 3: Flight test for custom motor

PRE-LAUNCH ROCKET PREPARATION Shock Cord Attachment and Length Parachute Folding Nomex Continuity Tests Avionics Bay Test Power Up Assembly Shear Pins

LAUNCH PAD PREPARATIONS Launch lugs lined up and rocket slid on rail. Avionics bay armed and continuity test ran. Igniter inserted and capped Or Igniter taped to rod and inserted (motor size)

K695R-P MOTOR RESULTS Simulation Results Apogee: 3,675 feet Maximum velocity: 171 m/s Time to apogee: 14.9 sec Flight time: 93.6 sec Testing Results Apogee: 4,029 feet Maximum velocity: 163.982 m/s Time to apogee: 15.5 sec Flight time: 93.15 sec Video: K695 Launch

COMMERCIAL MOTOR ROCKET PERFORMANCE

L1250-DM MOTOR RESULTS Simulation Results Apogee: 9,360 feet Maximum velocity: 334 m/s Time to apogee: 22.4 sec Flight time: 174 sec Testing Results Apogee: 11,960 feet Maximum velocity: 352 m/s Time to apogee: 25.15 sec Flight time: 206 sec Video: Dark Matter Launch

COMMERCIAL MOTOR ROCKET PERFORMANCE

FUEL SELECTION Propellant base Ammonium Perchlorate: focus on specific impulse and high burn rate Mixing Agent Aluminum Plasticizer: agent used to thin the mixture, however also lowers performance Dioctyl Adipate Curing Agent: necessary in order for the mixture to cure properly R45HT-LO Catalysts: used to increase burn rate Iron Oxide

PROPELLANT MIXTURE Ingredient THIS BATCH (g) Weight Percent Ammonium perchlorate 200 um 1755.22 77.00 76.90% Aluminum atomized 345 mesh 113.98 5.00 5.0 Red Iron Oxide 2.28 0.10 0.1 R45HTLO 296.34 13.00 13 Dioctyl adipate 68.39 3.00 3 E744 45.59 2.00 2 Total wt 2281.78 Percent solids 95.00%

MAKING THE APCP FUEL 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

CUSTOM MOTOR RESULTS Simulation Results Apogee: 3,156 feet Maximum velocity: 157 m/s Time to apogee: 13.6 sec Flight time: 84.9 sec Testing Results Apogee: 2,503 feet Maximum velocity: 122 m/s Time to apogee: 12.3 sec Flight time: 72.4 sec Video: Research Motor Launch

FUEL CHARACTERIZATION The fuel used was O.1% Catalyst Red Iron Oxide APCP. This Fuel while widely used is very difficult to find data on. The launch on October 11, 2015 flight data is being sent around the HPR Community for fuel Characterization.

BUDGET STATUS L1250DM Motor Housing. K695R Motor Housing. Components used to make custom rocket motor. Custom Rocket Motor Housing

Launch custom motor to 8,0000 feet FUTURE TASKS

ODU ROCKET CLUB Constitution has be approved. The Organization has an established OrgSync page. There ae currently three officers President Wes Harpster Vice President Trey Simmons Director of Underclassmen Amanda Nolan