Transcript Document
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: 164.56 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: 23.125 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 Altitude vs Time 15000 12500 Altittide (ft) 10000 7500 5000 2500 0 0 25 50 75 100 125 150 175 200 225 250 Time (s) • 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 Velocity vs Time • Peak velocity of 955 ft/s at 4 seconds • Shows drogue and main parachute deployment at 25 and 237 seconds respectively 1000 900 800 Velocity (ft/s) 700 600 500 400 300 200 100 0 -100 0 25 50 75 100 125 150 175 200 225 250 Acceleration vs Time Time (s) 300 • Peak acceleration of 269 ft/s2 at 1.5 seconds • Shows acceleration from drag and gravity up to apogee at 25 seconds • Constant velocity under drogue, zero acceleration Acceleration (ft/s2) 250 200 150 100 50 0 -50 0 5 10 15 20 Time (s) 25 30 35 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 Component Descent Rate (ft/s) Mass (slugs) Kinetic Energy (ft-lbf) Nosecone 12.5 0.0979 7.744 Piston 12.5 0.0310 2.457 Upper Airframe 12.5 0.539 42.66 Lower Airframe 12.5 0.874 69.14 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 Boost System Analysis Temperature Compensation Motor Tube Strain Gages Strain Gages Centering Rings Bulk Head 𝐹𝑔 𝑡 + 𝐹𝐷 (𝑡) 𝐹𝑇_1 𝑡 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: 91.13 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 Future Work Manufacture full scale Update mass estimates Acquire travel funding Full scale Launch, April 5th