PLANTATION HIGH PDR PRESENTATION Team 1

VEHICLE DIMENSION & MATERIALS

VEHICLE DIMENSIONS & MATERIALS

VEHICLE JUSTIFICATIONS  Airframe/coupler/Motor mount  Fins  Nosecone/Bulkhead/Centering Ring  Recovery Harness BlueTube Carbon Fiber Sheets G10 Fiberglass Tubular Kevlar

STATIC STABILITY MARGIN Without motor: 3.69 cal With motor: 1.58 cal

STATIC STABILITY MARGIN - CHART

VEHICLE SAFETY Hazard Analysis Overview  Team members will obey all hazard mitigations of tool and material use, as outlined in the hazard analysis chart within the PDR  These matrices generally require the use of proper PPE's in conjunction with proper material/tool handling to prevent dangerous situations.  For example any power tools require the use of a face mask, safety goggles and awareness of team members around the user.  Team members as a whole will be given a lab rundown to ensure all team members are aware of the proper use and PPE's associated with tools and materials found within the lab.  All materials and tools will be put away properly after use.

VEHICLE SAFETY TESTING PLAN Ejection/vehicle safety test plan Prepare the rocket as the team would for a normal launch (as explained in the team's preliminary launch checklist); however, without a motor loaded. At a system level, ensure all components of the rocket are sound. Complete electrical test of the payload and altimeter bay, ensuring both the altimeters and redundant "fall- back" altimeters have power and are functioning. Wire the ejection charges and redundant back-up charges directly to the launch stand. The launch stand will have redundant safety switches and a key-turned, spring-loaded "on" switch that turns back to the "off" position if released. Announce, in a loud enough voice that all team members can hear, a 5 second countdown before performing the ejection test. After the test, the team will wait 60 seconds in case one of the charges did not fire. The team safety officer will then approach and assess if the rocket properly and safely separated. All electrical systems and the launch stand will be disarmed if none of the charges fire. The standard 60 seconds will be waited before approaching the rocket to disarm the internal electrical systems.

VEHICLE SAFETY TESTING PLAN The team will follow the preliminary flight checklist. All black powder charge creation prior to flight will be completed by the team NAR certified mentor. The charges will be created with the use of a face mask and latex gloves. No sparks, flames or heat sources (including cell phones) will be allowed within 25 feet of the black powder. Once on the launch stand, following the preliminary launch checklist, the electrical system will be armed and the team will retreat to outside the minimum safe distance away from the rocket, as outlined in the NAR's minimum safe distance table. The rocket will be launched with a launch controller that utilizes redundant safety switches and a key-turned, spring-loaded "on" switch that turns back to the "off" position if released. Should the rocket motor fail to ignite on the launch stand when the range officer pushes the ignition switch, the launch controller will be disarmed and the team will wait a minimum of 60 seconds before the range officer will approach the rocket. The electrical systems will be disarmed and the rocket's igniter and motor will be evaluated. After the flight, the team will not directly approach the rocket and will wait 60 seconds after landing before assessing the rocket. The team will never climb trees or other large obstacles to retrieve a rocket or try to pull the rocket out of powerlines

BASELINE MOTOR SELECTION Motor: Aerotech K695

BASELINE MOTOR JUSTIFICATION Most commercially available motor Allows motor vehicle to reach above projected altitude Allows more mass

THRUST-TO-WEIGHT RATIO & RAIL EXIT VELOCITY 695N/61N = Thrust to Weight Approximately 12/1

LAUNCH VEHICLE VERIFICATION RequirementFeature to satisfy requirementVerification 1.1. The vehicle shall deliver the science or engineering payload to an apogee altitude of 5,280 feet above ground level (AGL). A combination of the design of the rocket and appropriate rocket motor, as designed in RockSim will provide the appropriate thrust, weight and drag relationship to allow the rocket to attain but not exceed 5,280 feet. The rocket will be test flown to ensure all components of the rocket will work in conjunction to attain but not exceed the altitude of 5,280 feet The vehicle shall carry one commercially available, barometric altimeter for recording the official altitude used in determining the altitude award winner. Teams will receive the maximum number of altitude points (5,280) if the official scoring altimeter reads a value of exactly 5,280 feet AGL. The team will lose two points for every foot above the required altitude, and one point for every foot below the required altitude. Any team is eligible for the award as long as their rocket remains below an altitude of 5,600 feet AGL. Within the payload bay of the rocket, a section will be provided to contain the barometric pressure altimeter. The rocket will be test flown to ensure it does not exceed 5,600 feet. During the design phase of the payload project, a separate section of the bay will be designed specifically carry a barometric pressure altimeter. The rocket will be designed to reach but not exceed 5,280 feet The launch vehicle shall be designed to be recoverable and reusable. Reusable is defined as being able to launch again on the same day without repairs or modifications. The rocket will utilize a parachute recovery. The team will be able to quickly "re-build" the rocket and prep it for another immediate flight. Ground tests and application of a post- launch checklist will ensure that the parachute can safely recover the rocket and that the team can quickly re-prep the rocket for flight.

LAUNCH VEHICLE VERIFICATION 1.4. The launch vehicle shall have a maximum of four (4) independent sections. An independent section is defined as a section that is either tethered to the main vehicle or is recovered separately from the main vehicle using its own parachute. The rocket is made of three independent sections: an upper body tube, a coupler, and a lower body tube, all tethered together. Before construction, the design team will create a design consisting of only three independent sections of the rocket The launch vehicle shall be limited to a single stage. The rocket will use an Aerotech K695R motor for propulsion; a single stage motor. The team will research the Aerotech K695R motor to ensure it is single stage The launch vehicle shall be capable of being prepared for flight at the launch site within 2 hours, from the time the Federal Aviation Administration flight waiver opens. The team will be able to prepare the rocket for launch within two hours and will be ready for launch. Practice drills of the preparation of the rocket before flight will be held until the team can complete the preparation of the rocket in under two hours 1.7. The launch vehicle shall be capable of remaining in launch- ready configuration at the pad for a minimum of 1 hour without losing the functionality of any critical on-board component. The rocket will use a power source that can last at least double the required inert time on the pad and time in the air Designs of the rocket in conjunction with ground tests will ensure that the electrical systems on board can function after two hours of waiting on the pad The launch vehicle shall be capable of being launched by a standard 12 volt direct current firing system. The firing system will be provided by the NASA- designated Range Services Provider. The rocket will utilize an igniter that can be lit with a 12 volt direct current firing system. Ground tests will ensure that the igniter is capable of being lit with a 12 volt direct current firing system.

TEST PLAN OVERVIEW Ejection ground test Subscale launch Static tests Bunnell, FL test launch – full- scale Component testing Payload ground test Vista View Park, Davie, FL

MAJOR COMPONENTS & SUBSYSTEMS - FINS

MAJOR COMPONENTS - NOSECONE

MAJOR COMPONENTS – TAIL CONE

MAJOR COMPONENTS – UPPER AIRFRAME

MAJOR COMPONENTS – LOWER AIRFRAME

MAJOR COMPONENTS - COUPLER BlueTube Length: 9 in. Outer Diameter: 3.9 in. Houses altimeter bay Closed off by bulkheads

SUBSYSTEM - RECOVERY

SUBSYSTEM - PROPULSION

SUBSYSTEM – WHOLE ROCKET

BASELINE PAYLOAD DESIGN

PAYLOAD VERIFICATION & TEST PLAN OVERVIEW Plan Overview On the launch pad all the instruments are calibrated and zeroed to launch pad conditions. As the rocket ascends data from the barometric pressure sensor (BMP180), triple axis accelerometer (ADXL335), and GPS module is sent to the central flight computer. The flight computer takes this data and sends it through an The flight computer takes this data and sends it through an Xbee Pro 900 RPSMA to a corresponding Xbee AGL. The data received from the flight computer is then logged on the receiving computer for further analysis.

Payload RequirementsDesign Feature/SolutionMeans of Verification The launch vehicle shall carry a science or engineering payload. A team member will watch the insertion of the payload. A team member will check off that the payload was inserted properly. Data from the science or engineering payload shall be collected, analyzed, and reported by the team following the scientific method. The data streamed from the payload to the ground will be logged and saved as a hard copy. A team member will read the log saved to the computer and analyze its’ findings. Unmanned aerial vehicle (UAV) payloads of any type shall be tethered to the vehicle with a remotely controlled release mechanism until the RSO has given the authority to release the UAV. There will be no release mechanism of the payload system. The launch vehicle will be constructed with no release mechanism. Any payload element that is jettisoned during the recovery phase, or after the launch vehicle lands, shall receive real-time RSO permission prior to initiating the jettison event. The payload system will not be jettisoned. A team member will verify that the payload is tethered properly and will not exit the launch vehicle during flight. The payload shall be designed to be recoverable and reusable. The payload system’s start values data can be calibrated to launch pad conditions at the beginning of each launch. A team member will verify that the payload is calibrated to launch pad conditions and is ready for another flight. Payload Verification Matrix

EDUCATIONAL ENGAGEMENT Open lab nights at Plantation High School Boy/cub scout Workshop Women in Engineering Seminars Parkway launch day & Seminar