NASA SL Preliminary Design Review
|
|
- Homer Allen
- 6 years ago
- Views:
Transcription
1 NASA SL Preliminary Design Review University of Alabama in Huntsville 1
2 Mission Summary Design, fabricate, test and fly a rocket and payload to 1 mile in altitude Deploy a rover upon landing to autonomously travel and unfold solar panels Conduct STEM outreach with students *Throughout the presentation, all dimensions are in inches 2
3 VEHICLE DESIGN 3
4 Vehicle Summary Launch Vehicle Dimensions Fairing Diameter: 6 in. Body Tube Diameter: 4 in. Mass at lift off: 39.7 lbm. Length: 96 in. Concept L-Class Solid Commercial Motor Rover Delivery Electronic Dual Deployment Fiberglass Airframe 4
5 Vehicle System Locations Tracking/Rover Deployment Avionics Rover Piston Main Parachute Recovery Avionics Drogue Parachute Fins (x4) CG 51 in. CP 63 in. Payload Fairing 36 in. Forward Airframe 24 in. Coupler 12 in. Aft Airframe 41 in. 5
6 Vehicle CONOPS Deploy Drogue: 19 seconds 5,282 ft. Powered Ascent: seconds 0 1,050 ft. Deploy Main: 50 seconds 600 ft. Landing: 100 seconds 0 ft. Deploy Rover: Team Command 6
7 Flight Simulation OpenRocket Sim: A 1-D in house Monte Carlo simulation will be used to verify results Results will also be compared to flight tests for verification Attribute Value Apogee (ft.) 5282 Length (in.) 96 Max. Mach Number 0.56 Rail Exit Velocity (ft./s) 55.7 Static Stability (cal.) 2.0 Motor Designation AT L1520T - P Thrust-to-Weight Ratio 8.7 CG 51 in. CP 63 in. 7
8 Simulation Results Apogee of approximately 5282 ft. at 19 sec. Motor burnout at approximately 1050 ft. at 3.2 sec. Burnout at 3.2 sec. Apogee of 5282 ft. (19 sec.) 50 sec. Main deploy (600 ft.) 8
9 Stability Analysis Stability of 2.06 cal. at rail exit Calculated with no wind conditions Stability of 2.74 cal. at motor burnout Maximum Stability: 2.74 Takeoff Stability:
10 UPPER AIRFRAME Nose Cone Payload Fairing Transition Forward Body Tube 10
11 Objectives Forward System Overview Protect and deploy the payload House assembly for tracking vehicle location Transition upper airframe to payload fairing Payload Piston Avionics Bay 11
12 Nose Cone and Fairing 6.0 in. 2.0 in. 6.0 in. 3D printed High Strength ABS Ejected with rover deployment Room to store ballast for stability No electronics housed inside Shear pin interface Bulkhead at base 6 in. ellipsoid shape 2 in. shoulder 24.0 in. Responsible for housing the rover and rover deployment system Filament wound fiberglass 12
13 Piston Overview Used to deploy rover from fairing Spring driven spike punctures cartridge Spring released by hotwire upon command; redundant arming Plunger Ø 6.0 in. Cylinder Ø 6.0 in. Machined from aluminum Powered by 8 or 12 gram CO 2 cartridge Plunger tethered to base Standard Operating Procedure in development 13
14 Fairing Transition Aerodynamic transition between upper airframe and fairing, load path supplemented with aluminum insert 3-D printed with ABS plastic, single piece design Threaded rod in tension connecting to aft bulkhead to built in forward coupler 14
15 Fairing Transition Problems with ABS single piece design Mass: 4.7 lbm Complicated FEA Structurally weak without aluminum insert Aluminum insert could pose manufacturing difficulties Other options considered: Aluminum brace with direct bulkhead connection, purely aerodynamic cover 15
16 CENTRAL SUBSYSTEM 16
17 Central Subsystem Overview Central Subsystem responsibilities: Primary coupler between airframes Flight Avionics Ejection System Tracking and Ground Station Recovery System 17
18 Coupler U Bolt (2 Places) Aluminum Bulkheads Stratologger CF Altimeter (2 Places) 9V Battery (2 Places) Switch/Pressure Equalization holes (2 Places) 9 in. 1 in in. All-Thread (2 Places) 3D Printed Avionics Sled 1 in. Switchband Black Powder Housing (4 Places) 18
19 Avionics Recovery Avionics Subsystem 2 PerfectFlite StratoLoggerCF altimeters; each with a 9V battery and SPDT momentary activation switch 4 Safe Touch terminals, E-matches, and black powder charges Full redundancy in avionics and ignition 19
20 Recovery Deployment Avionics Normally Closed SPDT Pull Pin Microswitch Prevents detonation during assembly Helps preserve battery life Primary Drogue charge fired at apogee Secondary fired one second after Primary Main fired at 600 ft. Secondary fired at 550 ft. Primary charges are roughly 4 g of black powder Secondary charges are 2 g larger than primary 20
21 GPS Tracking Subsystem System CRW will reuse a previously designed PCB that contains an Xbee Pro- PRO 900HP RF module, and an Antenova GPS Chip PCB will includes traces for all relevant connections including battery sources. Xbee transmits GPS coordinates to a receiver connected to the ground station laptop. Tests will be performed prior to the full scale launch to verify operation success Structure Integration 3D printed mount to secure tracker and its essentials within the transition section of the rocket. Three axis security and battery retention to ensure components are kept in tact 21
22 Recovery System Drogue Parachute Deployment: Deployment at apogee Fruity Chute CFC-18 (C D = 1.5) Shock Cords: 1 inch Nylon (50 ft.) Connected between forward motor retention bulkhead in lower airframe and avionics bay housing. Descent speed under drogue: 62.2 ft/s Main Parachute Deployment: Deployment at 700 ft. above ground level Fruity Chute 60 in. Iris Ultra (C D = 2.2) Shock Cords: 1 inch Nylon (50 ft.) Connected between fairing bulkhead and avionics bay housing. Descent speed under main: ft/s Open Rocket Simulation between 0 and 20 mph winds showed a maximum drift at 15 mph of about 1,700 ft. 22
23 Recovery System Calculations Required that each individual section will have a maximum kinetic energy of 75 ft-lbf For initial calculations, a conservative estimate of 75 ftlbf was used for the heaviest section KE = 1 2 mv2 m = mass of the section, lbm v = velocity, ft/s The largest independent section is 15 lbm, so the safe descent speed was determined to be 17.9 ft/s D = 8mg πρc D v 2 D = diameter of parachute, ft. m = mass of vehicle, lbm g = force of gravity, ft/s 2 ρ = density of the air, lbm/ft 3 C D = Coefficient of Drag v = previously calculated velocity, ft/s Minimum Diameter must be 93.3 inches 23
24 Load Path (Drogue and Main) 3 2 The load in 1, 2, and 3 are causing tension under Drogue and Main. Shock cord applies load to eyebolt in the coupler bulkhead. The load in 4 is transferred through the all thread and down to the motor casing then back up the tube. 1 4 represents force due to drag represents the force due to mass 24
25 AFT SUBSYSTEM 25
26 Aft System Objectives Objectives/Responsibilities Fin Design Optimize dimensions and materials for flight stability Centering Ring/Thrust Plate Carry load path from the vehicle Centering and fin integration ability Forward/Recovery Retention Provide method for recovery attachment Carry thrust through the vehicle via forward retention 26
27 Aft System Components Design Overview Through the wall design/slotted body tube Slots allow for fin mounting integration G10 Fiberglass fins attached with seven 4-40 bolts per fin Fins will be mounted to centering ring 3-D printed centering ring/fin mounting bracket Can be removed from body tube for repair/inspection Aluminum Forward/Recovery retention bulkhead Uses U bolt for recovery system Motor case tapped to allow for forward retention Trapezoidal Fin(s) (4) Forward/Recovery Retention Bulkhead Secondary Centering Ring Motor/Motor Casing Fin Can/Centering Ring Thrust Ring 27
28 Motor Selection Other motors considered: L1150 Too little total impulse L850 Too slow off the rail L1390 Too much total impulse Aerotech L1520R-P Specifications Motor Designation L1520T-P Apogee 5,282 ft. Stability 2.0 cal. Ballast 51 in. Diameter 75 mm. (3 in.) Length 25.7 in. Propellant Mass 8.0 lbm Total Impulse 835 lbf.-s Max Acceleration 289 ft./s 2 Velocity off the Rail 55.7 ft./s Burn Time 2.5 sec 28
29 Motor Retention Forward Retention Bulkhead Screwed onto top of motor Recovery retention is fixed on U-bolt 3.9 in. diameter 0.5 in. thick Aluminum Fixed to body tube with four ¼-20 screws 29
30 Fin Can Requirements fulfilled by part: motor centering, fin mounting, thrust takeout from motor Material: 3D printed high strength ABS plastic Location: inserted in the bottom of the aft body tube Fin Can 30
31 Fin Can Dimensions 31
32 Secondary Centering Ring Purpose: align motor as it is inserted into the rocket Bolted to the aft body tube using 4-40 bolts Material: Polycarbonate 32
33 Fin Design Trapezoidal Fin Design Allows more freedom in fin design Adjust fin shape to shift CP Fin Dimensions 8 in base 3.5 in height with extended base for body tube insertion Seven holes allow integrated mounting to centering ring located inside body tube Rounded leading edge Fin Material G10 Fiberglass Will be fabricated/designed in house Fin Mounting Fins mounted through the body tube to centering ring Replaceable upon breakage/damage Flutter speed Calculated to be mph (Mach 1.88) 33
34 Fin Material Fins made out of G-10 fiberglass This material was chosen for its high strength to weight ratio Tensile Strength: Crosswise: 38 ksi Lengthwise: 45 ksi Flexural Strength: Crosswise: 65 ksi Lengthwise: 75 ksi Flexural Modulus: Crosswise: 2400 ksi Lengthwise: 2700 ksi Compressive Strength: 65 ksi Its density is lbm/in^3. 34
35 Fin Retention Each fin mounted with seven 4-40 bolts; normal to fin face Four sets of ten 4-40 bolts normal to body tube surface used to maintain body tube shape under motor thrust 35
36 Subscale Rocket 3.0 in Subscale Rocket 6.0 in Full-Scale Rocket Approximately half-scale 4 in. body in. body 6 in. fairing 3 in. fairing Mach in. motor 1.5 in. motor 96 in. length 49 in. length 9.0 G 15.2 G 36
37 PAYLOAD DESIGN 37
38 Payload Summary Objective: Design an autonomous rover that will deploy from the interior of the rocket, move a minimum of 5 ft. away from the rocket, and deploy solar panels The rover s design consists of a rectangular chassis, two expandable wheels, and a stabilizing arm The rover measures temperature, pressure, location, and transmits this data with images to a ground station 38
39 Rover Assembly The tail will be wrapped around the chassis while inside the fairing. Rover will be kept collapsed passively by the fairing. The collapsed diameter is 5.7 in with 0.15 in of clearance. 39
40 Rover Assembly Rover wheels will expand to in. diameter when deployed Wheels rotate independently. Allows for steering via differential Lid will slide open via linear gear driven by a DC motor Solar panel will increase its effective area from 0 to 100% Solar panel will charge battery for distance extension 40
41 Rover Chassis Trade Study Aluminum Unibody 3D Printed ABS Unibody Aluminum Base/3D Printed ABS Walls Ease of Manufacturing Strength to Weight Environmental Protection Total Score Aluminum Unibody selected Highest strength to weight design Resistant to drastic changes in temperature Least deflection under load protects motors and electronics 3D Printed ABS Unibody is secondary selection Will be used if aluminum unibody is too difficult to manufacture 41
42 Rover Chassis Design The chassis will be milled out of a single block of 6061-T6 aluminum The chassis will house all electronics The drive motors will be mounted directly to the sidewalls The tail will be mounted to the bottom of the chassis 42
43 Rover Chassis Stress Analysis The chassis can sustain a 30G (210 lbf) load to the sidewall, simulating a load from the wheel during adverse deployment conditions (left) The chassis can sustain a 30G (210 lbf) load to the base, simulating loading from inside the rocket upon landing (right) 43
44 Rover Tail Trade Study Ease of Manufacturing 18 inch Measuring Tape (Wrapped around) 11 inch Sideways Hinged Aluminum Tail 5 2 Strength 3 5 Tail Length 5 3 Total Score Wheel Rotation Counter moment from tail Measuring Tape selected Ease of manufacturing Results in a longer tail and moment arm Sideways Hinged Aluminum is secondary selection Will be used if measuring tape fails integration and deployment tests 44
45 Main Goals for design: Expanding wheels 6 in. diameter constraint while inside rocket > 6 in. diameter desired for handing terrain Chosen Design: Umbrella wheel Desired for handling terrain Trade Study: Wheel Design All designs similarly decent in other categories Telescoping Wheels Foam Umbrella wheel Cost Design Complexity Low Risk of Damage Terrain Effectiveness Total
46 Main Considerations: Pushing wheels out of rocket without taking damage Ease of manufacturing wheel shapes Chosen Material: Aluminum Highest strength while maintaining low weight Easiest to manufacture wheels Trade Study: Wheel Material Aluminum ABS Polycarbonate Cost Design Complexity Weight Strength of Material Total
47 Wheel Design Current Chosen Design: Umbrella Wheel lbm 5.7 in. diameter wheel expands to 14 in. diameter wheel Linear extension spring for compression and expansion Keeps compressed while in rocket, expands naturally once out Spring located on the exterior, pulls in to bring spoke vertical Rod used for assembly of main wheel to spokes 47
48 Wheel Design Main Wheel Made of Aluminum 6061 T6 Eight notches for eight spokes, holes for attaching spokes with rod 48
49 Wheel Design Spoke 6061 T6 Aluminum 0.75 in. extrusion for grip with expanded wheel Circular piece for attaching to wheel base 49
50 6061 T6 Aluminum Attaches to wheel base Wheel Design Motor Mount 50
51 Main Wheel Can withstand 120 lbf before yielding Load: Pushed out by piston, no more than few pounds Will likely be more distributed to entire wheel base 51
52 Spoke Can withstand 35 lbf before yielding to 40 ksi Max Stress 15 ksi Full weight of rover and motor torque 52
53 Motor Mount Can withstand 900 lbf before yielding Load: Pushed out by piston, absorbed by other parts Max load by piston no more than a few pounds 53
54 Solar Deployment Sliding solar panel lid utilizing remote servo gear Solar panels will remain static Solar panels recharge battery Gear System Hinge Simplicity 3 4 Functionality 5 3 Weight 2 2 Cost 1 1 Total Score Two different designs considered for solar panel deployment mechanism Gear system lid Hinged lid Lid with gear system was selected Hinge mechanism would be harder to close once opened Gear system would be easier to bring the cover back over the solar panels 54
55 Rover Mass Budget Component Mass (lbm) Chassis 2.5 Wheel Assembly 1.4 Lid/Solar Deployment 1.0 Tail 0.1 Electronics % Margin 0.6 Total 7.0 The mass of all components totaled 6.4 lbm. A 10% Margin was added to the total weight to account for fasteners, adhesives, and design changes 55
56 Battery Trade Study Three different batteries considered 3x Li-Ion in series 4x CR123a Surefire in series 8x Energizer Recharge Power in series Trade studies conducted by rating each battery s benefits on a scale of 1 5 Li-Ion was selected based on criteria Li-Ion CR123A Surefire Energizer Recharge Power Plus Power Capacity Weight Safety Reusability Power Density Total
57 MCU Trade Study Arduino Mega Arduino Uno PCB with ATMega 2560 Beaglebone Raspberry Pi 3 Clock Speed I/O Pins Operating Voltage Power Draw Complexity Volume Mass Cost Total
58 Component Selection Component Selection Features MCU Arduino Mega (7 12) Vin I2C, SPI, UART, GPIO 16 MHz IMU Temperature and Pressure Sensor Motor Adafruit LSM9DS0 Adafruit BMP280 Cytron DC Geared Motor SPG30-300K Accelerometer Gyroscope Magnetometer 3 Axis I2C, SPI Press range: ( ) hpa Temp range: (-40 85) C SPI, I2C 0.8" x 0.7" x 0.1" 12 V At load 410 ma Stall torque 1.18 Nm Mass: 160 g Brushed 58
59 Selection cont. Component Selection Features Solar Cell GPS Radio Lid Motor DC/DC converter OSEPP Monocrystalline Solar Cell Adafruit MTK3339 X-Bee PRO NMB Technologies PPN7PA12C1 LM3671 Buck Converter 100mA 5 V 4 x 3 x 0.2 5V 20 ma 10 Hz updates -165 dbm sensitivity 28 mile range (with high gain antenna) 900 MHz Data rate 200 kbps UART, SPI 5V DC Brushed lbm 3.3 V output 600mA draw 0.6" x 0.4" x 0.1" Camera ArduCam CMOS OV VGA 3.3V supply needed 59
60 Power Budget Required battery capacity = I ma V V DC Time hr Efficiency 11.1 V Component Current (ma) Voltage (V) Time (hr) Duty Cycle (%) Efficiency (%) Necessary Capacity (mahr) Arduino Mega Pressure/ Temp IMU Wheel Motors Lid Motors Radio Camera GPS Voltage Regulator Required Capacity (mahr) Available Capacity (mahr) Safety Factor
61 Component Block Diagram 61
62 Payload Software Flow Diagram Remove RBF; Payload detects launch via acceleration Takes acceleration data throughout flight, calculates changes Once acceleration is zero for several iterations, waits for deployment signal from ground station Rover transmits acknowledgement, waits for confirmation signal Receives confirmation signal; Delays 30 seconds Supplies power to motor, begins taking temperature, pressure, and IMU data Get position data via GPS and accelerometer; Sample 2 times per second Transmit data back to ground station, save on board to eeprom If position change by a certain margin, back up, turn motor, begin moving again Once distance traveled, deploy solar panels, end data collection Measure battery voltage Transmit data back to ground station, save on board to eeprom 62
63 REQUIREMENTS COMPLIANCE 63
64 Requirements Compliance Plan All requirements, both USLI and derived, will be complied with, and verified using the following methods The requirements may be found in the PDR Document Inspection Nondestructive/passive examination of the system No numerical data collected Design components present, use of checklists, follow safety guidelines Analysis Calculation of performance prior to any physical testing Completely theoretical based on expected performance Simulation software, FEA, hand calculations, CAD Demonstration System verification through repeatable exhibition of the design feature Pre-determined pass/fail criteria Parachute deployment, repeat flight tests, capability to launch within an hour Testing Demonstration of system with known input and output values Numerical data feedback as well as demonstrative verification Static motor fire, flight test with altimeters, recovery location tracking 64
65 NAR and FAA Compliance Test launches will only occur at NAR or TRA sponsored launch events. Only the mentor is allowed to handle rocket motors The rocket will use an L motors and will not exceed the impulse limit set by NASA 65
66 Launch Vehicle Verification Recovery Ejection Coupler Strength Motor Thrust/ Load Path Simulation/ Aerodynamics Overall System Performance Will the parachutes eject properly with the planned explosives? Will the rocket buckle at the coupler under max. thrust? Is the load path sufficiently strong/how does the motor behave when fired? Is the simulation accurate/is the rocket stable? Does the rocket reach the expected altitude/does every component work properly? Multiple ground ejections of each component Apply calculated moment to coupler Static fire of the motor, measuring thrust through the high-risk loadpath components Launch a subscale version of the rocket multiple times Launch the full-scale (final) rocket multiple times 66
67 General Requirements Compliance Most of the General Requirements are fulfilled through inspection of the schedule and design documents The TRA Mentor s (Jason Winningham) credentials have been confirmed Outreach will be demonstrated through the Outreach Reports The team will demonstrate the ability to teleconference during the review Rocket rail launch capability, reusability, and readiness will be demonstrated at the test flight 67
68 SAFETY 68
69 CRW Safety Commitment Training and Communications are key Weekly Safety Briefings on relevant current activities Create Hazard analysis and Standard operating procedures Team work and proper supervision are how risks and hazards can be minimized No team member shall work alone when manufacturing and testing the rocket and its components. CRW members double and triple check each other s work to ensure that all steps of manuals and standard procedures are followed Supervision from experienced mentors and staff ensures all procedures are done correctly. 69
70 ATF, DOT, and NPFA Compliance Rocket motors, e-match, igniters are purchased by the mentor or appropriate PRC staff with the proper license to ensure legality and compliance. Motors will be stored in Type 2 Magazine and transported in Type 3 magazines. 70
71 Safety Plan Hold weekly Safety Briefings with the entire CRW team Each sub-team will designate a Safety Representative to work with the Safety Officer Aid in Hazard and failure mode analysis for their respective sub-section of the rocket A Component Description Sheet will be created for each component used in the rocket Analyze failure modes Track evolution of the component to aid in verification process CRW has identified the required success criteria and a method of verification for each (as outlined in the PDR report) A Test Plan has been created based on the verification of all identified success criteria (as outlined in the PDR report) 71
72 Safety Representatives Bao H. Safety Officer Davis H. Launch Vehicle Lead Andrew W. Payload Lead The Safety Officer will be responsible for the overall safety outlined by the SLI Handbook The Launch Vehicle lead and the Payload lead will be responsible for the reliability and risk assessment of their systems. 72
73 Safety Briefings and Trainings Training Activity Date Red Cross First Aid CPR/AED/FA 10/13/2017 Basic Emergency Procedures 10/17/2017 Process Hazard Analysis 10/18/2017 Safe Testing Procedures 10/24/2017 Root-Cause Analysis 10/24/2017 Outreach Safety Procedures 11/7/2017 Sub-scale Launch Safety Procedures 11/14/2017 Hazardous Material Handling/Disposal 11/21/2017 Fire Extinguisher training 11/21/2017 TBD TBD The Red Team have completed training for First Aid and CPR/AED Additional training content will be added based on relevance to the stages in the development cycle. 73
74 Launch and Assembly Procedures The Test Plan and Verification Processes will be used to optimize the final design, assembly, and launch procedures Final rocket assembly procedures have been developed to fit the design concept Any changes to the design that require updating the assembly or launch procedures will be coordinated through the team safety officer Simulated runs of all procedures will take place at least one week prior to any launch 74
75 Published Information For the convenience of all team members, the following items will be located on the CRW team website: Material Safety Data Sheets Operators Manuals CRW Safety Regulations Safety Briefing slides Standard Operating Procedures The Safety Officer will work to keep this information relevant and up to date 75
76 PROGRAM MANAGEMENT 76
77 Work Breakdown Structure Payload Mechanical Structure Wheel Design Chassis Design Vehicle fabrication Electrical Design Component Selection Schematic Development Software Rover software Ground Station CRW Launch Vehicle Aft Motor Selection Fins Lower Body Tube Simulation Central Avionics Recovery Forward Upper Body Tube Nosecone Payload Fairing Management Website Updates Outreach Coordination Schedule and budget tracking Requirements Verification Interface management Safety Risk Identification and Analysis Mitigation Strategy Development Safety Briefing Manufacturing and Testing supervision 77
78 Schedule Schedule Philosophy Work around finals and Winter Break Internal deadlines 2 weeks ahead of NASA deadline for all documents Identify backup dates for critical test launches Upcoming Events Launch Opportunities: Nov 18, Dec 16, Jan 20, Feb 17 CDR Internal due date: Dec 22 78
79 Budget/Funding Summary Launch vehicle- two subscales (6 flights) and two full scales (6 flights) - $5,760 Payload- two fully operation rovers -$1,010 $750 margin for shipping/unexpected expenses Proposed to ASGC and UAH Propulsion Research Center for funding and Recovery 22% Motors 50% Rover Frame 4% Rover Electronics 11% Airframe 13% Rover Frame Rover Electronics Airframe Motors Recovery 79
80 Outreach Girls Science and Engineering Day Before project started, but good practice 80 middle school girls participated FIRST Robotics Boy Scout STEM Winter Camp Invited to teach space, robotics, and maker culture Science Olympiad at UAH, February
81 Web Presence Website updated and reformatted to highlight current content while preserving 2017 team documents Facebook and Instagram kept current Press release posted 81
82 Questions 82
83 Picture Credits NASA USLI Wikipedia Portrait_by_Curiosity_Rover_Arm_Camera.jpg NASA Thrustcurve.org Wonderfulengineering.com Professionalgrantwriter.org National Association of Rocketry Youtube Emotionalhealth.net 83
84 Component Mass (g) Number per rover Total Mass (g) Total Mass (lbm) Arduino Mega BMP SPG30 geared motor Appendix A: Electronics Mass Budget Motor Shield LSM9DS Solar cell Camera MHz Xbee Brushed DC motor Battery GPS Voltage regulator Total mass
NASA SL Critical Design Review
NASA SL Critical Design Review University of Alabama in Huntsville 1 LAUNCH VEHICLE 2 Vehicle Summary Launch Vehicle Dimensions Fairing Diameter: 6 in. Body Tube Diameter: 4 in. Mass at lift off: 43.8
More informationNASA SL Flight Readiness Review
NASA SL Flight Readiness Review University of Alabama in Huntsville 1 LAUNCH VEHICLE 2 Vehicle Overview Vehicle Dimensions Diameter: 6 fairing/4 aft Length: 106 inches Wet Mass: 41.1 lbs. Center of Pressure:
More informationCRITICAL DESIGN REVIEW. University of South Florida Society of Aeronautics and Rocketry
CRITICAL DESIGN REVIEW University of South Florida Society of Aeronautics and Rocketry 2017-2018 AGENDA 1. Launch Vehicle 2. Recovery 3. Testing 4. Subscale Vehicle 5. Payload 6. Educational Outreach 7.
More informationNASA SL - NU FRONTIERS. PDR presentation to the NASA Student Launch Review Panel
NASA SL - NU FRONTIERS PDR presentation to the NASA Student Launch Review Panel 1 Agenda Launch Vehicle Overview Nose Cone Section Payload Section Lower Avionic Bay Section Booster Section Motor Selection
More informationCritical Design Review
Critical Design Review University of Illinois at Urbana-Champaign NASA Student Launch 2017-2018 Illinois Space Society 1 Overview Illinois Space Society 2 Launch Vehicle Summary Javier Brown Illinois Space
More informationFLIGHT READINESS REVIEW TEAM OPTICS
FLIGHT READINESS REVIEW TEAM OPTICS LAUNCH VEHICLE AND PAYLOAD DESIGN AND DIMENSIONS Vehicle Diameter 4 Upper Airframe Length 40 Lower Airframe Length 46 Coupler Band Length 1.5 Coupler Length 12 Nose
More informationAuburn University. Project Wall-Eagle FRR
Auburn University Project Wall-Eagle FRR Rocket Design Rocket Model Mass Estimates Booster Section Mass(lb.) Estimated Upper Section Mass(lb.) Actual Component Mass(lb.) Estimated Mass(lb.) Actual Component
More informationFlight Readiness Review
Flight Readiness Review University of Illinois at Urbana-Champaign NASA Student Launch 2017-2018 Illinois Space Society 1 Overview Illinois Space Society 2 Launch Vehicle Summary Javier Brown Illinois
More informationCRITICAL DESIGN PRESENTATION
CRITICAL DESIGN PRESENTATION UNIVERSITY OF SOUTH ALABAMA LAUNCH SOCIETY BILL BROWN, BEECHER FAUST, ROCKWELL GARRIDO, CARSON SCHAFF, MICHAEL WIESNETH, MATTHEW WOJCIECHOWSKI ADVISOR: CARLOS MONTALVO MENTOR:
More informationAuburn University Student Launch. PDR Presentation November 16, 2015
Auburn University Student Launch PDR Presentation November 16, 2015 Project Aquila Vehicle Dimensions Total Length of 69.125 inches Inner Diameter of 5 inches Outer Diameter of 5.25 inches Estimated mass
More informationNASA USLI PRELIMINARY DESIGN REVIEW. University of California, Davis SpaceED Rockets Team
NASA USLI 2012-13 PRELIMINARY DESIGN REVIEW University of California, Davis SpaceED Rockets Team OUTLINE School Information Launch Vehicle Summary Motor Selection Mission Performance and Predictions Structures
More informationGeorgia Tech NASA Critical Design Review Teleconference Presented By: Georgia Tech Team ARES
Georgia Tech NASA Critical Design Review Teleconference Presented By: Georgia Tech Team ARES 1 Agenda 1. Team Overview (1 Min) 2. 3. 4. 5. 6. 7. Changes Since Proposal (1 Min) Educational Outreach (1 Min)
More informationIllinois Space Society Flight Readiness Review. University of Illinois Urbana-Champaign NASA Student Launch March 30, 2016
Illinois Space Society Flight Readiness Review University of Illinois Urbana-Champaign NASA Student Launch 2015-2016 March 30, 2016 Team Managers Project Manager: Ian Charter Structures and Recovery Manager:
More informationPresentation Outline. # Title # Title
CDR Presentation 1 Presentation Outline # Title # Title 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18 19 20 21 22 23 24 25 26 Team Introduction Vehicle Overview Vehicle Dimensions Upper Body Section Payload
More informationUC Berkeley Space Technologies and Rocketry Preliminary Design Review Presentation. Access Control: CalSTAR Public Access
UC Berkeley Space Technologies and Rocketry Preliminary Design Review Presentation Access Control: CalSTAR Public Access Agenda Airframe Propulsion Payload Recovery Safety Outreach Project Plan Airframe
More informationGIT LIT NASA STUDENT LAUNCH PRELIMINARY DESIGN REVIEW NOVEMBER 13TH, 2017
GIT LIT 07-08 NASA STUDENT LAUNCH PRELIMINARY DESIGN REVIEW NOVEMBER TH, 07 AGENDA. Team Overview (5 Min). Educational Outreach ( Min). Safety ( Min) 4. Project Budget ( Min) 5. Launch Vehicle (0 min)
More informationProject NOVA
Project NOVA 2017-2018 Our Mission Design a Rocket Capable of: Apogee of 5280 ft Deploying an autonomous Rover Vehicle REILLY B. Vehicle Dimensions Total Length of 108 inches Inner Diameter of 6 inches
More informationJordan High School Rocketry Team. A Roll Stabilized Video Platform and Inflatable Location Device
Jordan High School Rocketry Team A Roll Stabilized Video Platform and Inflatable Location Device Mission Success Criteria No damage done to any person or property. The recovery system deploys as expected.
More informationNASA - USLI Presentation 1/23/2013. University of Minnesota: USLI CDR 1
NASA - USLI Presentation 1/23/2013 2013 USLI CDR 1 Final design Key features Final motor choice Flight profile Stability Mass Drift Parachute Kinetic Energy Staged recovery Payload Integration Interface
More informationPresentation Outline. # Title
FRR Presentation 1 Presentation Outline # Title 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18 19 20 21 22 23 24 Team Introduction Mission Summary Vehicle Overview Vehicle Dimensions Upper Body Section Elliptical
More informationTeam Air Mail Preliminary Design Review
Team Air Mail Preliminary Design Review 2014-2015 Space Grant Midwest High-Power Rocket Competition UAH Space Hardware Club Huntsville, AL Top: Will Hill, Davis Hunter, Beth Dutour, Bradley Henderson,
More informationStatement of Work Requirements Verification Table - Addendum
Statement of Work Requirements Verification Table - Addendum Vehicle Requirements Requirement Success Criteria Verification 1.1 No specific design requirement exists for the altitude. The altitude is a
More informationPreliminary Design Review. California State University, Long Beach USLI November 13th, 2017
Preliminary Design Review California State University, Long Beach USLI November 13th, 2017 System Overview Launch Vehicle Dimensions Total Length 108in Airframe OD 6.17in. ID 6.00in. Couplers OD 5.998in.
More informationPreliminary Design Review. Cyclone Student Launch Initiative
Preliminary Design Review Cyclone Student Launch Initiative Overview Team Overview Mission Statement Vehicle Overview Avionics Overview Safety Overview Payload Overview Requirements Compliance Plan Team
More informationWichita State Launch Project K.I.S.S.
Wichita State Launch Project K.I.S.S. Benjamin Russell Jublain Wohler Mohamed Moustafa Tarun Bandemagala Outline 1. 2. 3. 4. 5. 6. 7. Introduction Vehicle Overview Mission Predictions Payload Design Requirement
More informationNASA s Student Launch Initiative :
NASA s Student Launch Initiative : Critical Design Review Payload: Fragile Material Protection 1 Agenda 1. Design Overview 2. Payload 3. Recovery 4. 5. I. Sub-Scale Predictions II. Sub-Scale Test III.
More informationFlight Readiness Review Addendum: Full-Scale Re-Flight. Roll Induction and Counter Roll NASA University Student Launch.
Flight Readiness Review Addendum: Full-Scale Re-Flight Roll Induction and Counter Roll 2016-2017 NASA University Student Launch 27 March 2017 Propulsion Research Center, 301 Sparkman Dr. NW, Huntsville
More informationOverview. Mission Overview Payload and Subsystems Rocket and Subsystems Management
MIT ROCKET TEAM Overview Mission Overview Payload and Subsystems Rocket and Subsystems Management Purpose and Mission Statement Our Mission: Use a rocket to rapidly deploy a UAV capable of completing search
More informationFlight Readiness Review March 16, Agenda. California State Polytechnic University, Pomona W. Temple Ave, Pomona, CA 91768
Flight Readiness Review March 16, 2018 Agenda California State Polytechnic University, Pomona 3801 W. Temple Ave, Pomona, CA 91768 Agenda 1.0 Changes made Since CDR 2.0 Launch Vehicle Criteria 3.0 Mission
More informationPRELIMINARY DESIGN REVIEW
PRELIMINARY DESIGN REVIEW 1 1 Team Structure - Team Leader: Michael Blackwood NAR #101098L2 Certified - Safety Officer: Jay Nagy - Team Mentor: Art Upton NAR #26255L3 Certified - NAR Section: Jackson Model
More informationAUBURN UNIVERSITY STUDENT LAUNCH. Project Nova. 211 Davis Hall AUBURN, AL Post Launch Assessment Review
AUBURN UNIVERSITY STUDENT LAUNCH Project Nova 211 Davis Hall AUBURN, AL 36849 Post Launch Assessment Review April 19, 2018 Table of Contents Table of Contents...2 List of Tables...3 Section 1: Launch Vehicle
More informationTacho Lycos 2017 NASA Student Launch Critical Design Review
Tacho Lycos 2017 NASA Student Launch Critical Design Review High-Powered Rocketry Team 911 Oval Drive Raleigh NC, 27695 January 13, 2017 Table of Contents Table of Figures:... 8 Table of Appendices:...
More informationUniversity of Illinois at Urbana-Champaign Illinois Space Society Student Launch Preliminary Design Review November 3, 2017
University of Illinois at Urbana-Champaign Illinois Space Society Student Launch 2017-2018 Preliminary Design Review November 3, 2017 Illinois Space Society 104 S. Wright Street Room 18C Urbana, Illinois
More informationCritical Design Review Report
Critical Design Review Report I) Summary of PDR report Team Name: The Rocket Men Mailing Address: Spring Grove Area High School 1490 Roth s Church Road Spring Grove, PA 17362 Mentor: Tom Aument NAR Number
More informationNUMAV. AIAA at Northeastern University
NUMAV AIAA at Northeastern University Team Officials Andrew Buggee, President, Northeastern AIAA chapter Dr. Andrew Goldstone, Faculty Advisor John Hume, Safety Officer Rob DeHate, Team Mentor Team Roster
More informationNotre Dame Rocketry Team. Flight Readiness Review March 8, :00 PM CST
Notre Dame Rocketry Team Flight Readiness Review March 8, 2018 2:00 PM CST Contents Overview Vehicle Design Recovery Subsystem Experimental Payloads Deployable Rover Payload Air Braking System Safety and
More informationUniversity of Notre Dame
University of Notre Dame 2016-2017 Notre Dame Rocketry Team Critical Design Review NASA Student Launch Competition Roll Control and Fragile Object Protection Payloads Submitted January 13, 2017 365 Fitzpatrick
More informationNASA Student Launch College and University. Preliminary Design Review
2017-2018 NASA Student Launch College and University Preliminary Design Review Institution: United States Naval Academy Mailing Address: Aerospace Engineering Department United States Naval Academy ATTN:
More informationRover Delivery NASA University Student Launch Initiative Post-Launch Assessment Review. Charger Rocket Works.
Rover Delivery 2017-2018 NASA University Student Launch Initiative Post-Launch Assessment Review Charger Rocket Works April 27 th, 2018 Propulsion Research Center 1030 John Wright Drive NW, Huntsville,
More informationThe University of Toledo
The University of Toledo Project Kronos Preliminary Design Review 11/03/2017 University of Toledo UT Rocketry Club 2801 W Bancroft St. MS 105 Toledo, OH 43606 Contents 1 Summary of Proposal... 6 1.1 Team
More informationStudent Launch. Enclosed: Preliminary Design Review. Submitted by: Rocket Team Project Lead: David Eilken
University of Evansville Student Launch Enclosed: Preliminary Design Review Submitted by: 2016 2017 Rocket Team Project Lead: David Eilken Submission Date: November 04, 2016 Payload: Fragile Material Protection
More informationPreliminary Design Review November 15, Agenda. California State Polytechnic University, Pomona W. Temple Ave, Pomona, CA 91768
Preliminary Design Review November 15, 2017 Agenda California State Polytechnic University, Pomona 3801 W. Temple Ave, Pomona, CA 91768 Agenda 1.0 General Information 2.0 Launch Vehicle System Overview
More informationTacho Lycos 2017 NASA Student Launch Flight Readiness Review
Tacho Lycos 2017 NASA Student Launch Flight Readiness Review High-Powered Rocketry Team 911 Oval Drive Raleigh NC, 27695 March 6, 2017 Table of Contents Table of Figures... 9 Table of Appendices... 11
More informationAUBURN UNIVERSITY STUDENT LAUNCH PROJECT NOVA II. 211 Davis Hall AUBURN, AL CDR
AUBURN UNIVERSITY STUDENT LAUNCH PROJECT NOVA II 211 Davis Hall AUBURN, AL 36849 CDR January 10, 2019 Contents List of Tables...7 List of Figures...9 1 CDR Report Summary...12 1.1 Payload Deployable Rover...12
More informationFlorida A & M University. Flight Readiness Review. 11/19/2010 Preliminary Design Review
Florida A & M University Flight Readiness Review 11/19/2010 Preliminary Design Review 1 Overview Team Summary ~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~ ~~~~~~~~ Vehicle Criteria ~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~ ~~~~~~~~
More informationIllinois Space Society University of Illinois Urbana Champaign Student Launch Maxi-MAV Preliminary Design Review November 5, 2014
Illinois Space Society University of Illinois Urbana Champaign Student Launch 2014-2015 Maxi-MAV Preliminary Design Review November 5, 2014 Illinois Space Society 104 S. Wright Street Room 321D Urbana,
More informationPresentation 3 Vehicle Systems - Phoenix
Presentation 3 Vehicle Systems - Phoenix 1 Outline Structures Nosecone Body tubes Bulkheads Fins Tailcone Recovery System Layout Testing Propulsion Ox Tank Plumbing Injector Chamber Nozzle Testing Hydrostatic
More informationNASA USLI Flight Readiness Review (FRR) Rensselaer Rocket Society (RRS)
2016-2017 NASA USLI Flight Readiness Review (FRR) Rensselaer Rocket Society (RRS) Rensselaer Polytechnic Institute 110 8th St Troy, NY 12180 Project Name: Andromeda Task 3.3: Roll Induction and Counter
More informationNORTHEASTERN UNIVERSITY
NORTHEASTERN UNIVERSITY POST-LAUNCH ASSESSMENT REVIEW NORTHEASTERN UNIVERSITY USLI TEAM APRIL 27TH 2018 Table of Contents 1. Summary 2 1.1 Team Summary 2 1.2 Launch Summary 2 2. Launch Vehicle Assessment
More informationCritical Design Review
Critical Design Review 1/27/2017 NASA Student Launch Competition 2016-2017 California State Polytechnic University, Pomona 3801 W Temple Ave, Pomona, CA 91768 1/27/2017 California State Polytechnic University,
More informationPreliminary Design Review
Preliminary Design Review November 16, 2016 11/2016 California State Polytechnic University, Pomona 3801 W Temple Ave, Pomona, CA 91768 Student Launch Competition 2016-2017 1 Agenda 1.0 General Information
More informationNASA University Student Launch Initiative (Sensor Payload) Final Design Review. Payload Name: G.A.M.B.L.S.
NASA University Student Launch Initiative (Sensor Payload) Final Design Review Payload Name: G.A.M.B.L.S. CPE496-01 Computer Engineering Design II Electrical and Computer Engineering The University of
More informationNASA Student Launch W. Foothill Blvd. Glendora, CA Artemis. Deployable Rover. November 3rd, Preliminary Design Review
2017 2018 NASA Student Launch Preliminary Design Review 1000 W. Foothill Blvd. Glendora, CA 91741 Artemis Deployable Rover November 3rd, 2017 Table of Contents General Information... 9 1. School Information...
More informationThe University of Toledo
The University of Toledo Project Cairo Preliminary Design Review 10/08/2016 University of Toledo UT Rocketry Club 2801 W Bancroft St. MS 105 Toledo, OH 43606 Contents 1 Summary of Preliminary Design Review...
More informationPROJECT AQUILA 211 ENGINEERING DRIVE AUBURN, AL POST LAUNCH ASSESSMENT REVIEW
PROJECT AQUILA 211 ENGINEERING DRIVE AUBURN, AL 36849 POST LAUNCH ASSESSMENT REVIEW APRIL 29, 2016 Motor Specifications The team originally planned to use an Aerotech L-1520T motor and attempted four full
More informationUSLI Flight Readiness Review
UNIVERSITY OF MINNESOTA TWIN CITIES 2011 2012 USLI Flight Readiness Review University Of Minnesota Team Artemis 3/26/2012 Flight Readiness Report prepared by University of Minnesota Team Artemis for 2011-2012
More informationUniversity Student Launch Initiative
University Student Launch Initiative HARDING UNIVERSITY Critical Design Review February 4, 2008 The Team Dr. Edmond Wilson Brett Keller Team Official Project Leader, Safety Officer Professor of Chemistry
More informationUniversity Student Launch Initiative
University Student Launch Initiative HARDING UNIVERSITY Flight Readiness Review March 31, 2008 Launch Vehicle Summary Size: 97.7 (2.5 meters long), 3.1 diameter Motor: Contrail Rockets 54mm J-234 Recovery
More informationCritical Design Review
AIAA Orange County Section Student Launch Initiative 2011-2012 Critical Design Review Rocket Deployment of a Bendable Wing Micro-UAV for Data Collection Submitted by: AIAA Orange County Section NASA Student
More informationPost Launch Assessment Review
AIAA Orange County Section Student Launch Initiative 2011-2012 Post Launch Assessment Review Rocket Deployment of a Bendable Wing Micro-UAV for Data Collection Submitted by: AIAA Orange County Section
More informationNorthwest Indian College Space Center USLI Critical Design Review
2012-2013 Northwest Indian College Space Center USLI Critical Design Review Table of Contents, Tables, and Figures I.0 CDR Report Summary... 1 I.1 Team Summary... 1 I.2 Launch Vehicle Summary... 1 I.2a
More informationUSLI Critical Design Report
UNIVERSITY OF MINNESOTA TWIN CITIES 2011 2012 USLI Critical Design Report University Of Minnesota Team Artemis 1/23/2012 Critical Design Report by University of Minnesota Team Artemis for 2011-2012 NASA
More informationRocket Design. Tripoli Minnesota Gary Stroick. February 2010
Rocket Design Tripoli Minnesota Gary Stroick February 2010 Purpose Focus is on designing aerodynamically stable rockets not drag optimization nor construction techniques! Copyright 2010 by Gary Stroick
More informationRocketry Projects Conducted at the University of Cincinnati
Rocketry Projects Conducted at the University of Cincinnati 2009-2010 Grant Schaffner, Ph.D. (Advisor) Rob Charvat (Student) 17 September 2010 1 Spacecraft Design Course Objectives Students gain experience
More informationStudent Launch. Enclosed: Proposal. Submitted by: Rocket Team Project Lead: David Eilken. Submission Date: September 30, 2016
University of Evansville Student Launch Enclosed: Proposal Submitted by: 2016 2017 Rocket Team Project Lead: David Eilken Submission Date: September 30, 2016 Payload: Fragile Material Protection Submitted
More informationCritical Design Review Report NASA Student Launch Florida International University American Society of Mechanical Engineers (FIU-ASME)
Critical Design Review Report 2014-2015 NASA Student Launch Florida International University American Society of Mechanical Engineers (FIU-ASME) Florida International University Engineering Center College
More informationMASSACHUSETTS INSTITUTE OF TECHNOLOGY Department of Aeronautics and Astronautics
MASSACHUSETTS INSTITUTE OF TECHNOLOGY Department of Aeronautics and Astronautics 16.00 Introduction to Aerospace and Design Problem Set #4 Issued: February 28, 2002 Due: March 19, 2002 ROCKET PERFORMANCE
More informationTable of Content 1) General Information ) Summary of PDR Report ) Changes Made Since Proposal ) Safety... 8
Table of Content 1) General Information... 3 1.1 Student Leader... 3 1.2 Safety Officer... 3 1.3 Team Structure... 3 1.4 NAR/TRA Sections... 4 2) Summary of PDR Report... 5 2.1 Team Summary... 5 2.2 Launch
More informationCornell Rocketry Team. NASA Student Launch Competition CORNELL ROCKETRY TEAM
2015-2016 CORNELL ROCKETRY TEAM Presentation Centennial Challenge MAV Participant NASA Student Launch Competition LAUNCH VEHICLE GENERAL DIMENSIONS Airframe Tubing: OD = 3.98 in ID = 3.9 in Couplers: OD
More informationHPR Staging & Air Starting By Gary Stroick
Complex Rocket Design Considerations HPR Staging & Air Starting By Gary Stroick 1. Tripoli Safety Code 2. Technical Considerations 3. Clusters/Air Starts 4. Staging 5. Summary 2 1. Complex High Power Rocket.
More informationTuskegee University Rocketry Club
Tuskegee University Rocketry Club National Aeronautics and Space Administration Student Launch Initiative Preliminary Design Review Atmospheric Measurement and Aerodynamic Analysis TURC 2015-2016 NASA
More informationCNY Rocket Team Challenge. Basics of Using RockSim 9 to Predict Altitude for the Central New York Rocket Team Challenge
CNY Rocket Team Challenge Basics of Using RockSim 9 to Predict Altitude for the Central New York Rocket Team Challenge RockSim 9 Basics 2 Table of Contents A. Introduction.p. 3 B. Designing Your Rocket.p.
More informationPreliminary Detailed Design Review
Preliminary Detailed Design Review Project Review Project Status Timekeeping and Setback Management Manufacturing techniques Drawing formats Design Features Phase Objectives Task Assignment Justification
More informationFirst Nations Launch Rocket Competition 2016
First Nations Launch Rocket Competition 2016 Competition Date April 21-22, 2016 Carthage College Kenosha, WI April 23, 2016 Richard Bong Recreational Park Kansasville, WI Meet the Team Wisconsin Space
More informationPre-Flight Checklist for SLIPSTICK III
Advanced Planning 1 Schedule a Check that waivers are available at the intended launch site and date. b Check weather forecast for wind and temperature conditions at the site. c Have TAP members approved
More informationMadison West High School Green Team
Madison West High School Green Team The Effect of Gravitational Forces on Arabidopsis Thaliana Development Flight Readiness Review The Vehicle Mission Performance Criteria Successful two stage flight Altitude
More informationTripoli Rocketry Association Level 3 Certification Attempt
Tripoli Rocketry Association Level 3 Certification Attempt Kevin O Classen 1101 Dutton Brook Road Goshen, VT 05733 (802) 247-4205 kevin@back2bed.com Doctor Fill Doctor Fill General Specifications Airframe:
More informationPost Launch Assessment Review
Post Launch Assessment Review University of South Alabama Launch Society Conner Denton, John Faulk, Nghia Huynh, Kent Lino, Phillip Ruschmyer, Andrew Tindell Department of Mechanical Engineering 150 Jaguar
More informationProject WALL-Eagle Maxi-Mav Flight Readiness Review
S A M U E L G I N N C O L L E G E O F E N G I N E E R I N G Auburn University Project WALL-Eagle Maxi-Mav Flight Readiness Review 2 Engineering Dr. Auburn, AL 36849 March 6th, 205 Table of Contents Section
More informationCritical Design Review
Harding University University Student Launch Initiative Team Critical Design Review January 29, 2007 The Flying Bison Sarah Christensen Project Leader Dr. Ed Wilson Faculty Supervisor Dr. James Mackey
More informationPegasus II. Tripoli Level 3 Project Documentation. Brian Wheeler
Pegasus II Tripoli Level 3 Project Documentation Brian Wheeler Contents: A. Design Overview B. Booster Construction C. Electronics Bay (Mechanical) Construction D. Nose Cone Construction E. Recovery System
More informationProject WALL-Eagle Maxi-Mav Critical Design Review
S A M U E L G I N N C O L L E G E O F E N G I N E E R I N G Auburn University Project WALL-Eagle Maxi-Mav Critical Design Review 2 Engineering Dr. Auburn, AL 36849 January 6th, 205 Table of Contents SECTION
More informationCal Poly Pomona Rocketry NASA Student Launch Competition POST LAUNCH ASSESMENT REVIEW April 24, 2017
Cal Poly Pomona Rocketry NASA Student Launch Competition 2016-2017 POST LAUNCH ASSESMENT REVIEW April 24, 2017 California State Polytechnic University, Pomona 3801 W Temple Ave, Pomona, CA 91768 Department
More informationDemoSat-B User s Guide
January 5, 2013 Authors: Chris Koehler & Shawn Carroll Revisions Revision Description Date Approval DRAFT Initial release 7/31/2009 1 Updated for 2011 2012 program dates, added revision page 9/27/11 LEM
More informationUniversity Student Launch Initiative Preliminary Design Review
UNIVERSITY OF MINNESOTA TWIN CITIES 2012 2013 University Student Launch Initiative Preliminary Design Review Department of Aerospace Engineering and Mechanics 3/18/2013 2012-2013 University of Minnesota
More informationNWIC Space Center s 2017 First Nations Launch Achievements
NWIC Space Center s 2017 First Nations Launch Achievements On April 18, 2017, we were on two airplanes to Milwaukee, Wisconsin by 6:30 am for a long flight. There were 12 students, 3 mentors, 2 toddlers
More informationHow Does a Rocket Engine Work?
Propulsion How Does a Rocket Engine Work? Solid Rocket Engines Propellant is a mixture of fuel and oxidizer in a solid grain form. Pros: Stable Simple, fewer failure points. Reliable output. Cons: Burns
More informationTeam America Rocketry Challenge Launching Students into Aerospace Careers Miles Lifson, TARC Manger, AIA September 8, 2016
Team America Rocketry Challenge Launching Students into Aerospace Careers Miles Lifson, TARC Manger, AIA September 8, 2016 TARC Video https://youtu.be/tzzmcnh-wa8 What is the Team America Rocketry Challenge
More informationBy: Georgia Institute of Technology Team Autonomous Rocket Equipment System (A.R.E.S.) Georgia Institute of Technology North Avenue NW Atlanta GA,
By: Georgia Institute of Technology Team Autonomous Rocket Equipment System (A.R.E.S.) Georgia Institute of Technology North Avenue NW Atlanta GA, 30332 Project Name: Hermes MAXI-MAV Competition Friday,
More informationCYCLONE STUDENT LAUNCH INITIATIVE
NSL PROPOSAL September 19, 2018 CYCLONE STUDENT LAUNCH INITIATIVE 2018-19 Iowa State University 537 Bissell Rd. 1200 Howe Hall Ames, IA 50011 Table of Contents Table of Contents... 2 Table of Figures...
More informationUniversity of North Dakota Department of Physics Frozen Fury Rocketry Team
University of North Dakota Department of Physics Frozen Fury Rocketry Team NASA Student Launch Initiative Flight Readiness Review - Report Submitted by: The University of North Dakota Frozen Fury Rocketry
More informationInnovating the future of disaster relief
Innovating the future of disaster relief American Helicopter Society International 33rd Annual Student Design Competition Graduate Student Team Submission VEHICLE OVERVIEW FOUR VIEW DRAWING INTERNAL COMPONENTS
More informationUC Berkeley Space Technologies and Rocketry NASA Student Launch Proposal Project Arktos. 432 Eshleman Hall, MC 4500 Berkeley, CA
UC Berkeley Space Technologies and Rocketry NASA Student Launch Proposal Project Arktos 432 Eshleman Hall, MC 4500 Berkeley, CA 94720-4500 September 20, 2017 Contents 1 General Team Information 3 1.1 Key
More informationISS Space Grant Team Exocoetidae
ISS Space Grant Team Exocoetidae Illinois Space Society University of Illinois at Champaign-Urbana March 9, 2018 Faculty Advisor: Diane Jeffers (dejeffer@illinois.edu, 217-898-5888) Team Lead: Shivani
More informationFlight Readiness Review Report NASA Student Launch Florida International University American Society of Mechanical Engineers (FIU-ASME)
Flight Readiness Review Report 2014-2015 NASA Student Launch Florida International University American Society of Mechanical Engineers (FIU-ASME) Florida International University Engineering Center College
More informationTHE UNIVERSITY OF AKRON
THE UNIVERSITY OF AKRON College of Engineering 302 E Buchtel Ave Akron, OH 44325 September 20, 2017 NASA Student Launch Initiative Table of Contents 1. Adult Educators and Advisors... 4 2. Team Officials...
More informationLEVEL 3 BUILD YELLOW BIRD. Dan Schwartz
LEVEL 3 BUILD YELLOW BIRD Dan Schwartz This entire rocket is built using the same techniques I use for my nose cones, a central airframe tube for compression strength and rings of high compression styrofoam
More informationThis Week. Next Week 4/7/15
E80 Spring 2015 This Week! Transfer breadboard circuit to PC board.! Verify everything still works.! Get data logger working.! Pass off consists of: " Power PC board with data logger & start logging. "
More informationJay Gundlach AIAA EDUCATION SERIES. Manassas, Virginia. Joseph A. Schetz, Editor-in-Chief. Blacksburg, Virginia. Aurora Flight Sciences
Jay Gundlach Aurora Flight Sciences Manassas, Virginia AIAA EDUCATION SERIES Joseph A. Schetz, Editor-in-Chief Virginia Polytechnic Institute and State University Blacksburg, Virginia Published by the
More information267 Snell Engineering Northeastern University Boston, MA 02115
NUMAV 267 Snell Engineering Northeastern University Boston, MA 02115 Mentor Robert DeHate President, AMW/ProX NAR L3CC 75198 TRA TAP 9956 robert@amwprox.com (978)766-9271 1 Table of Contents 1. Summary.3
More information