University of Florida Rocket Team Critical Design Review Presentation

Outline Overview Vehicle Design Motor Choice Flight Dynamics and Simulations Recovery Payloads Electronics Component Testing Future Work

Design Overview Total Length: inches Total Mass: 76 lbs Target Altitude: 10,000 ft

Outline Overview Vehicle Design Motor Choice Flight Dynamics and Simulations Recovery Payloads Electronics Component Testing Future Work

Airframes Rolled with 6 oz E-class Fiberglass 7 wraps; approximately 0.07 in wall thickness 5 airframes: Upper, UEB, Middle, Lower Extension, Lower

Upper Airframe Houses the piston and main parachute 32.5 inches long Separation occurs above it, at nosecone

Upper Electronics Bay L-shaped bay to maximize space Hatch allows easy access Aluminum bulkheads for precision Bay Length: 19.8 inches Airframe Length: inches

Middle Airframe Houses the baffles and drogue parachute Separation occurs below it Length: 20 inches Location of upper launch lug

Lower Airframe Lower extension connects to coupler and lower airframe Internal components assemble as one piece Lower extension length: 24 inches Lower Airframe length: 32 inches

Motor Centering and Thrust Transfer

Fins Tapered swept Height: 6 inches Root chord: 11 inches Tip chord: 3.5 inches G10 fiberglass Same attachment method as subscale

Outline Overview Vehicle Design Motor Choice Flight Dynamics and Simulations Recovery Payloads Electronics Component Testing Future Work

Motor Choice Cesaroni N2600-SK-P Specifications Total Impulse (lbf*s)2489 Average Thrust (lbf)584 Max Thrust (lbf)668 Burn Time (s)4.26 Launch Mass (lb)25.3 Empty Mass (lb)10.4

Outline Overview Vehicle Design Motor Choice Flight Dynamics and Simulations Recovery Payloads Electronics Future Work

Stability Characteristics Rail Exit Velocity = 72.5 ft/sec Thrust to Weight Ratio = 7.6

Altitude versus Time Maximum altitude of 10,842 feet Drogue parachute deployment at 25 seconds (apogee) Main parachute deployment at 237 seconds, 700 feet of altitude

Velocity and Acceleration versus Time Peak velocity of 955 ft/s at 4 seconds Shows drogue and main parachute deployment at 25 and 237 seconds respectively Peak acceleration of 269 ft/s 2 at 1.5 seconds Shows acceleration from drag and gravity up to apogee at 25 seconds Constant velocity under drogue, zero acceleration

Outline Overview Vehicle Design Motor Choice Flight Dynamics and Simulations Recovery Payloads Electronics Component Testing Future Work

Recovery Objectives Reusable without repairs Kinetic Energy each piece is less than 75 ft-lbf Main and drogue parachute manufactured by team GPS tracking device Crosswind drift less than 5,000ft

Recovery System Drogue Deployment at apogee 60 inches in diameter Semi-ellipsoid canopy shape Charge baffle ejection system Descent velocity: 45.4 ft/s Main Deployment at 700ft 168 inches in diameter Semi-ellipsoid canopy shape Piston ejection system Descent velocity: 12.5ft/s

Attachment Scheme

Parachute Manufacturing Ripstop nylon Gore design Nylon upholstery thread Nylon shroud lines

Parachute Testing

Charge Baffle Two discs with non overlapping circular patters of holes Cools gasses from ejection charges and removes particulates Used to protect drogue parachute

Kinetic Energy ComponentDescent Rate (ft/s)Mass (slugs)Kinetic Energy (ft-lbf) Nosecone Piston Upper Airframe Lower Airframe

Outline Overview Vehicle Design Motor Choice Flight Dynamics and Simulations Recovery Payloads Electronics Component Testing Future Work

Ground Scanning System Ground Scanning System to detect hazards in the landing area Take an image of landing area Scan for potential hazards in real-time Send scanned image to Ground Station in real-time

Camera Module

Camera Integration

Electronics Mapping

Centering RingsBulk Head Motor Tube Strain Gages Temperature Compensation Strain Gages Boost System Analysis

Von Mises Strain

URES Strain

Triboelectric Effect Analysis Payload Triboelectric Effect Capacitive Sensing Technique Experimental Setup Payload Objectives

Triboelectric Effect The triboelectric effect (also known as triboelectric charging) is a type of contact electrification in which certain materials become electrically charged after they come into contact with another different material through friction.

Capacitive Sensing Technique Theory C = Q/V σ = Q/A Voltage measurement circuit

Experimental Setup Placement of capacitive sensors Data collection and recovery Precision Analog-to-Digital Converter (ADC) with 8051 Microcontroller and Flash Memory Texas Instruments - MSC1210Y5PAGT

Payload Objective Obtain nose cone map of voltage vs. time Calculate charge buildup Relate to friction models from computational fluid dynamics simulation data

Outline Overview Vehicle Design Motor Choice Flight Dynamics and Simulations Recovery Payloads Electronics Component Testing Future Work

Electronics Power Inputs Communications and data processing Recovery Lower Bay Image processing Boost systems analysis

Power Provides power to entire Upper Electronics Bay

Inputs

Communications and Data Processing ODROID Communications board

Recovery

Lower Bay Handles image processing Midway point for Boost Systems Analysis

Image Processing

Boost Systems Analysis

Outline Overview Vehicle Design Motor Choice Flight Dynamics and Simulations Recovery Payloads Electronics Component Testing Future Work

Testing Recovery Testing  Parachute Testing Complete Structural Testing  Compression and Shear Stress Testing Complete  Subscale Testing Complete Electronics Testing Motor Testing Payload Testing

Subscale Results Design  Length: in.  Max. Diameter: 3.2 in.  Weight: 15.4 lbs.  Stability Margin: 1.36  Predicted Apogee: 1675 ft. Results  Actual Apogee: 1865 ft.  Drogue Deployment: Successful  Main Deployment: Failure

Status of Requirements Verification Completed  11 Requirements  Project Plan  Safety Requirements  Component Testing In Progress  18 Requirements  Design Analysis Complete  Inspection and Testing In Progress Not Started  25 Requirements

Outline Overview Vehicle Design Motor Choice Flight Dynamics and Simulations Recovery Payloads Electronics Component Testing Future Work

Manufacture full scale Update mass estimates Acquire travel funding Full scale Launch, April 5th