Milestone Review Flysheet

Transcription

1 Review Flysheet Vehicle Properties Motor Properties Total Length (in) 115 Motor Manufacturer Cesaroni Diameter (in) 7.5 Motor Designation L1115 Gross Lift Off Weigh (lb) 40.9 Max/Average Thrust (lb) 385.1/251.6 Airframe Material Blue Tube Total Impulse (lbf-s) Fin Material G10 Fiberglass Mass Before/After Burn (lb) 40.9/30.1 Drag 189 N Liftoff Thrust (lb) Stability Analysis Ascent Analysis Center of Pressure (in from nose) 92 Maximum Veloxity (ft/s) 676 Center of Gravity (in from nose) Maximum Mach Number Static Stability Margin 2.24 Maximum Acceleration (ft/s^2) 272 Static Stability Margin (off launch rail) 2.24 Target Apogee (From Simulations) 5664 Thrust-to-Weight Ratio 12.3 Stable Velocity (ft/s) 42.2 Rail Size and Length (in) 1.5/120 Distance to Stable Velocity (ft) 425 Rail Exit Velocity (ft/s) 42.2 Drogue Parachutes Manufacturer/Model Fruity Chutes Manufacturer/Model Fruity Chutes Size 18" Size 72" Altitude at Deployment (ft) Apogee Altitude at Deployment (ft) 750 Velocity at Deployment (ft/s) 0 Velocity at Deployment (ft/s) 66.2 Terminal Velocity (ft/s) 14.9 Terminal Velocity (ft/s) 14.9 Recovery Harness Material Kevlar Shock Cord Recovery Harness Material Kevlar Shock Cord Harness Size/Thickness (in) 0.23 Harness Size/Thickness (in) 0.23 Recovery Harness Length (ft) 15 Recovery Harness Length (ft) 40 Harness/Airframe Interfaces Tied to seperate U-bolts secured to bottom of the launch vehicle. Harness/Airframe Interfaces Tied to U-bolts secured to bulkheads in the sheath and motor section. Section 1 Section 2 Section 3 Section 4 Section 1 Section 2 Section 3 Section

2 Manufacturer/Model Fruity Chutes Manufacturer/Model Fruity Chutes Size 12" Size 48" Altitude at Deployment (ft) Apogee Altitude at Deployment (ft) N/A (emergency signal) Velocity at Deployment (ft/s) 0 Velocity at Deployment (ft/s) 0 Terminal Velocity (ft/s) 35.1 Terminal Velocity (ft/s) 35.1 Recovery Harness Material Kevlar Shock Cord Recovery Harness Material Kevlar Shock Cord Harness Size/Thickness (in) 0.23 Harness Size/Thickness (in) 0.23 Recovery Harness Length (ft) 20 Recovery Harness Length (ft) 30 Harness/Airframe Interfaces Tied to U-bolt secured to bulkhead Harness/Airframe Interfaces Tied to U-bolt secured to bulkhead (Ft-lbs) Section 1 Section 2 Section 3 Section 4 Section 1 Section 2 Section 3 Section (Ft-lbs) 48.4 Recovery Electonics Recovery Electonics Altimeter(s)/Timer(s) (Make/Model) StratoLogger SL100 Altimeter Rocket Locators (Make/Model) BigRedBee GPS Redundancy Plan We will employ two stratologgers in the motor section to ensure the deployment of the two droguges. In addition, one of these stratologgers will also act as our redundancy plan to ensure the deployment of 72"main parachute. We will use two batteries per subsystem. Transmitting Frequencies Black Powder Mass Drogue Chute (grams) 915MHz 3 Pad Stay Time (Launch Configuration) 2 hours Black Powder Mass Main Chute (grams) 3 Review Flysheet Capture Autonomous Ground Support Equipment (MAV Teams Only)

3 Container Launch Rail Igniter Installation ***Include Description of rail locking mechanism*** Payload Payload 1 The ATMOS is the Atmospheric and Topographical Measurements Optics Suite. The ATMOS will measure, record, and transmit data on temperature, pressure, altitude, relative humidity, solar irradiance, and ultraviolet radiation. It will also collect images of the horizon in the visible spectrum and of the ground in the infrared (IR) spectrum. The ATMOS is comprised of two main data collecting systems: an Arduino Uno and a Raspberry Pi. All numerical atmospheric data collected by the ATMOS is under the domain of the Arduino Uno while any image processing (both visible and infrared) is handled by the Raspberry Pi. Any and all data or images will be stored on an SD card on-board the ATMOS, and will be transmitted upon landing. Payload 2 The CDLE is a custom quadcopter that integrates both the science and engineering payloads into a single functional unit. The CDLE integrates the ATMOS systems into its own frame and allows for the ATMOS to interface with the ground control station independently of the Pixhawk Flight Controller that controls the flight logic for the CDLE. The CDLE works as a deployable mechanism from the rocket, capable of rapidly separating from the launch vehicle and deploying on its own means of powered and controlled descent. Once deployed, the CDLE will initiate an autonomous landing sequence, allowing for ATMOS to collect scientific data as it completes a powered descent towards a predefined landing site. Test Plans, Status, and Results Ejection Charge Tests We performed static ground tests to investigate the motor section of the launch vehicle, since the motor section of our design was the most complex. Using the PerfectFlite DataCap Software, we were able to control ejection tests from a single laptop, allowing for insightful conclusions on the Stratologgers hardware and performance. To test its performance, the Stratologger gathered pertinent information on the ambient atmosphere; reading off the voltage input, air pressure, and temperature. To test the validity of the Stratologgers that we employed throughout the launch vehicle, the team performed static ground tests. This was accomplished by wiring an e-match to the Stratologger and sending a direct command to the Stratologger. These ground tests were successful. Sub-scale Test Flights Full-scale Test The first launch vehicle had the following specifications: 12 lbs., in. length, 5.5 in. OD, and flying off of a J530-IM-8 XL. According to flight simulations, the launch vehicle had an expected apogee of 3099 ft. with a velocity of about 56.7 ft/s off of the rod. This first launch vehicle served as a vessel for the ATMOS payload, various beta electronics testing the telemetry between the rocket and the ground station, and a unique recovery system from the motor system. We lost this launch vehicle, due to an error in the deployment of the four Fruity Chutes 12 drogues from the motor section. The second launch vehicle shared marked similarities with the first; however, this was flown off of a J400SS-16. According to flight simulations, the launch vehicle had an expected apogee of 1809 ft. with a velocity of about 42.9 ft/s off of the rod. The third launch vehicle flew excellently. To test the motor section, a component that we knew would present difficulty, we simplified our design to have: (1) the complex motor section comprised of four 12 fruity chutes drogues and (2) one 36 main parachute. Thus, there would only be two independent sections. The full scale launch is planned for February 27th, 2016.

4 Review Flysheet Additional Comments

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