THE UNIVERSITY OF AKRON

Transcription

1 THE UNIVERSITY OF AKRON College of Engineering 302 E Buchtel Ave Akron, OH September 20, 2017 NASA Student Launch Initiative

2 Table of Contents 1. Adult Educators and Advisors Team Officials Mentor Project Team Facilities and Equipment Main Team Facility Available University Facilities Necessary Personnel Computers and Software Testing Sites Team Website Safety Safety Plan Risk Assessment Proper Practices NAR/TRA Procedure Description NAR Safety Code and Compliance Rocket Motors and Energetic Devices Written Member Agreement Safety Inspections Flight Readiness Compliance with Standards Technical Design Vehicle Summary Material Selection and Justification Projected Altitude Parachute System Design Projected Motor Brand and Designation Projected Payload Design Requirements Major technical challenges and solution Educational Engagement Page 2 of 53

3 8.1. Hope Always Lives On Cents for Flight National Inventors Hall of Fame STEM Middle School Boy Scout Troop 1 and Cub Scout Pack University of Akron Ex[L] Center Judith Resnik Community Learning Center Project Plan Projected Budget Recovery Avionics Structure Payload Propulsion Subscale Rocket Travel Expenses Total Expenses Funding Plan Plan for Sustainability Page 3 of 53

4 1. Adult Educators and Advisors Dr. Francis Loth Title: F. Theodore Harrington Professor Department: Mechanical Engineering Office: ASEC 57N Phone: Dr. Scott Sawyer Title: Associate Professor and Associate Chair for Undergraduate Programs Department/Program: Mechanical Engineering Office: ASEC 110A Phone: Team Officials Thomas Wheeler Title: Safety Officer Organization: Phone: (412) Victoria Jackson Title: President Organization: Phone: (330) Mentor Jerry Appenzeller Level 2 NAR Certification Holder Phone: (704) jpappenzeller@gmail.com Page 4 of 53

5 4. Project Team There will be approximately 20 or more individuals committed to this project. The team consists of five officers dealing with administrative tasks of the team. The positions are as follows: President, Vice President, Project Manager, Chief Engineer, and Safety Officer. The team also consists of system leads for the following systems: Aerostructure, Electronics, Recovery, Propulsion, and Payload. Each system has at least three members; some members have multiple duties on the team. See the figure below for a detailed depiction of the team structure and duties of each system. Figure 1 Team structure and system duties Page 5 of 53

6 5. Facilities and Equipment 5.1. Main Team Facility The team s laboratory is located in the Student Design Center on campus. The Akronauts are granted 24-hour access to this facility which serves as the main area for assembling the rocket and for storage of the team s materials and supplies. Figure 2 Student Design Center 5.2. Available University Facilities The Auburn Science and Engineering Center (ASEC) has a separate laboratory for using composite materials, epoxying, and power tools. There are also two machine shops within ASEC. Both require students to complete safety and personal training prior to using any machines. The first shop has advanced equipment and is open to all graduate students and design teams on campus. The second shop is used for all undergraduate work. The two shops contain the following: Shop 1 (Monday Friday 7:00am 4:00pm) Manual Lathe Manual Mill CNC Lathe CNC Mill Band Saw Table Saw Grinding Wheel Router Various hand tools Shop 2 (Monday Friday 7:00am 4:00pm) Manual Lathe Manual Mill CNC Lathe CNC Mill Band Saw Drill Press Grinding Wheel Various hand tools Miscellaneous (Available with Appointment) Five 3D Printers Foam CNC Router Subsonic Wind Tunnel Page 6 of 53

7 5.3. Necessary Personnel Both machine shops require at least one of the shop managers to be on campus when in use. No member will use these machine shops by themselves. All members must be accompanied by another trained member or the machine shop manager Computers and Software All engineering students have access to computer labs at the University depending on their major. Most labs are open from 6:00am - 11:00pm. The Akronauts, among other University of Akron design teams, are granted special permission for 24-hour access. Most computers have many useful programs such as: MATLAB Solidworks Autodesk Inventor Creo ANSYS Abaqus AutoCAD COMSOL Multiphysics Microsoft Visual Studio pspice LabVIEW Fluent Simio OpenRocket RASAero BurnSim CES EduPack MasterCAM Microsoft Office Adobe Page 7 of 53

8 5.5. Testing Sites Field Location Amherst, Ohio Sandusky, Ohio Springfield, Ohio Penn Yan, New York Uses Launch Ceiling of 4,800 ft. One hour from the Akron campus Used for sub-scale flights and motor tests Launch Ceiling of 2,000 ft. Two hours from the Akron campus Used for level 1 and level 2 certification Flights Used for K12 Outreach launches Launch Ceiling of 16,000 ft. Three hours from the Akron campus Only available during Fall Semesters Option for full-scale flight tests Launch Ceiling of 18,000 ft. Five hours from the Akron campus Back up for full-scale flight testing Table 1 Launch locations accessible by the Akronauts 5.6. Team Website The team website is which is used to showcase the history, achievement, and progress of the while attempting to grow the team through media posts and pictures. The website also hosts team documents for competitions from past years and competitions currently being pursued. Some of the information included on the website: Team Projects with pictures, videos, models, and team documents Team Leadership, Advisors, and Mentors Educational Outreach Information Application to Join Links to social media Contact information for team members Current and Past Sponsors Contact form Most recent photos from social media FAQs page Figure 3 Akronauts moto via Page 8 of 53

9 6. Safety 6.1. Safety Plan The Safety Officer of the, Thomas Wheeler, is responsible for all participants safety; this includes but is not limited to team members, onlookers, and bystanders during potentially hazardous activities held throughout the design cycle. The Safety Officer is also responsible for the compliance to any laws, regulations or guidelines set forth by all governing bodies, i.e.: NASA, FAA, NAR, TRA, etc. The Akronauts Safety Officer is the key player when addressing the safety of the materials used and facilities involved. Thus, the safety officer is responsible for, but not limited to the following: Monitors the team activities with an emphasis on safety during: The Design of the vehicle and payload Construction of the vehicle and payload Assembly of the vehicle and payload Ground testing of the vehicle and payload Sub-scale launch test(s) Full-scale launch test(s) Launch day Recovery activities Educational Engagement Activities Implements procedures developed by the team for construction, assembly, launch, and recovery activities. Manages and maintain current revisions of the team s hazard analyses, failure modes analyses, procedures, and MSDS/chemical inventory data. Assists in the writing and development of the team s hazard analyses, failure modes analyses, and procedures. Ensures compliance with NASA, NAR, TRA, and FAA guidelines and regulations. Briefs and train team members on the safety plans for applicable environments, materials, or actions before beginning work. Partakes in design reviews of major rocket components to assess the quality and safety of the rocket and suggest changes as necessary before manufacture. Superintends and survey all testing to ensure predetermined safety procedures are followed properly. Implements a risk matrix detailing the likelihood and consequence level of each possible hazardous event. Enforces the use of required PPE in fabrication, launch, test, and any other instance required and make safe operating procedures and any material/machine information available before the use or manufacture of any part. Identifies safety risks and violations and take corrective and preventative actions to prevent future violations. Ensures compliance with all local, state, and federal laws. Plans for storage and transportation of all hazardous and energetic materials. Page 9 of 53

10 6.2. Risk Assessment Throughout the design cycle, the officers will revisit and if necessary, revise the risk matrix. The risk matrix was adopted after the sample Risk Assessment Matrix in the NASA Student Launch College and University Handbook. This risk matrix was modified to fit the unique needs of the Akronauts. The modified risk matrix will be used where any of the following may come into play: personal interaction with dangerous equipment, potentially dangerous environments, rocket component manufacture, test procedures, and any other actions that may pose a risk to teammates. Risk assessments have been completed for all hazards identified at this stage in the design as well as past designs. This brings attention to potential system and machine failures. As the design process continues, these will be revisited and potentially revised to address new and potentially dangerous actions. Consequences Likelihood Minimal 1 Marginal 2 Critical 3 Catastrophic 4 Rare - 1 Low Low Low Low Unlikely - 2 Low Low Low Moderate Probable - 3 Low Low Moderate Moderate Likely - 4 Low Moderate Moderate High Almost certain - 5 Moderate Moderate High High Table 2 Risk Matrix Page 10 of 53

11 The matrix is formatted where the likelihood of an event is portrayed on the y axis and the consequence level is on the x-axis. The likelihood is described values are described on a 1-5 scale as seen in the below table Likelihood value Value meaning Description 1 Rare 0-5% chance of any incident will occur 2 Unlikely 5-25% chance that an incident will occur 3 Possible 25-50% chance that an incident will occur 4 Likely 50-75% chance that an incident will occur 5 Almost Certain >75% chance that an incident will occur Table 3 Liklihood values used in the risk matrix Then, the consequence levels will be on a 1-4 scale as seen in the below table Consequence level Value meaning Description 1 Catastrophic Potential for significant injury or death, detrimental environmental effects, system failure, or significant monetary loss greater than $ Critical Could result in significant injury, partial system failure, or monetary loss less than $2000 but greater than $500 3 Marginal Could result in minor injuries, failure of non-critical components, or monetary loss of less than $500 but greater than $100 4 Minimal Small chances of minor injuries, partial failure of non-critical systems, or monetary loss of less than $100 Table 4 Consequences as seen in the risk matrix Page 11 of 53

12 The tables defining the consequences and likelihoods are under the following assumptions: All operators have been properly trained on the equipment in use. All operators have read and proven that they understand the Safe Operating Procedure, required data sheets, and safety manuals. Operators are using all required Personal Protective Equipment (PPE). All components were assessed to assure that they were in proper working condition before operation. The hazards can be outlined in the Risk matrix. Hazard Analyses are designed to link potential risks to all operations during development stages including using the labs and machine shop, stability, propulsion and recovery systems, and vehicle assembly. They are measured by likelihood and consequence level Proper Practices In order to put the practice of using Personal Protective Equipment (PPE) in place, there will be safety stickers placed on all power tools color coded to the risk matrix as well as a list of necessary PPE. For tool cabinets, there will be a binder containing an inventory of all tools and required PPE listed next to each tool. Safety manuals and safe operating procedures will be kept at each machine for reference as needed NAR/TRA Procedure Description NAR/TRA personnel are members of the team who have been certified to the level required to perform the following: Responsible for purchasing, handling, storing, and assembly of all rocket motors. Responsible for handling and wiring all ejection charge igniters. Responsible for handling ejection charges and loading ejection charges. Responsible for making sure team is adhering to NAR/TAR Safety regulations. Overall, the NAR/TAR personal will be in charge of ensuring that all safety precautions are taken into account. The High-Power Safety Code of the National Association of Rocketry (NAR) provides a summary of safe practices for launch high power rocketry from NFPA It is a requirement of both the NAR and TRA safety codes that NFPA 1127 is obeyed. Page 12 of 53

13 6.5. NAR Safety Code and Compliance Below is the s Compliances to the National Association of Rocketry High Power Rocket Safety Code, effective as of August The Akronauts agree to comply with all NAR safety codes and regulations as listed in the table below. NAR High Power Rocketry Safety Code NAR Code Certification: I will only fly high power rockets or possess high power rocket motors that are within the scope of my user certification and required licensing. Materials: I will use only lightweight materials such as paper, wood, rubber, plastic, fiberglass, or when necessary ductile metal, for the construction of my rocket. Motors: I will use only certified, commercially made rocket motors, and will not tamper with these motors or use them for any purposes except those recommended by the manufacturer. I will not allow smoking, open flames, or heat sources within 25 feet of these motors. Compliance Only Jerry Appenzeller and certified team members are permitted to handle the rocket motors. All parts of the rocket will be made according to this standard. Team leads and officers will approve every addition to the rocket. Only certified motors will be purchased and motors will only be handled by TRA/NAR personnel. Motors will be stored properly. Ignition System: I will launch my rockets with an electrical launch system, and with electrical motor igniters that are installed in the motor only after my rocket is at the launch pad or in a designated prepping area. My launch system will have a safety interlock that is in series with the launch switch that is not installed until my rocket is ready for launch, and will use a launch switch that returns to the "off" position when released. The function of onboard energetics and firing circuits will be inhibited except when my rocket is in the launching position. At launch, the Range Safety Officer will have say over all safety issues. The Team Safety Officer, Thomas Wheeler and Team President, Victoria Jackson are responsible for ensuring the integration at the launch site is done following the TRA Safety Code. All launches will be at NAR/TRA certified events. Page 13 of 53

14 NAR Code Misfires: If my rocket does not launch when I press the button of my electrical launch system, I will remove the launcher's safety interlock or disconnect its battery, and will wait 60 seconds after the last launch attempt before allowing anyone to approach the rocket. Compliance This requirement will be followed and the Range Safety Officer will have final say on all misfires. Launch Safety: I will use a 5-second countdown before launch. I will ensure that a means is available to warn participants and spectators in the event of a problem. I will ensure that no person is closer to the launch pad than allowed by the accompanying Minimum Distance Table. When arming onboard energetics and firing circuits I will ensure that no person is at the pad except safety personnel and those required for arming and disarming operations. I will check the stability of my rocket before flight and will not fly it if it cannot be determined to be stable. When conducting a simultaneous launch of more than one high power rocket I will observe the additional requirements of NFPA Flight Safety: I will not launch my rocket at targets, into clouds, near airplanes, nor on trajectories that take it directly over the heads of spectators or beyond the boundaries of the launch site, and will not put any flammable or explosive payload in my rocket. I will not launch my rockets if wind speeds exceed 20 miles per hour. I will comply with Federal Aviation Administration airspace regulations when flying, and will ensure that my rocket will not exceed any applicable altitude limit in effect at that launch site. This requirement will be followed and the Range Safety Officer will have final say on all Launch Safety. This requirement will be followed and the Range Safety Officer will have a final say on flight safety. Page 14 of 53

15 NAR Code Launch Site: I will launch my rocket outdoors, in an open area where trees, power lines, occupied buildings, and persons not involved in the launch do not present a hazard, and that is at least as large on its smallest dimension as one half of the maximum altitude to which rockets are allowed to be flown at that site or 1500 feet, whichever is greater, or 1000 feet for rockets with a combined total impulse of less than 160 N- sec, a total liftoff weight of less than 1500 grams, and a maximum expected altitude of less than 610 meters (2000 feet). Compliance All team launches will be at NAR/TRA certified events. The Range Safety Officer will have the final say over any rocketry safety issues. Launcher Location: My launcher will be 1500 feet from any occupied building or from any public highway on which traffic flow exceeds 10 vehicles per hour, not including traffic flow related to the launch. It will also be no closer than the appropriate Minimum Personnel Distance from the accompanying table from any boundary of the launch site. Recovery System: I will use a recovery system such as a parachute in my rocket so that all parts of my rocket return safely and undamaged and can be flown again, and I will use only flame-resistant or fireproof recovery system wadding in my rocket. Recovery Safety: I will not attempt to recover my rocket from power lines, tall trees, or other dangerous places, fly it under conditions where it is likely to recover in spectator areas or outside the launch site, nor attempt to catch it as it approaches the ground This requirement will be followed and the Range Safety Officer will have a final say on launcher location. The Safety Officer Tom Wheeler and Team President Victoria Jackson will make sure that all designs adhere to this requirement. Range Safety Officer will have final say on the recovery system. The recovery team will be responsible for designing and building a safe recovery system for the rocket. A safety checklist will be used on launch day to ensure that all steps in preparing and packing the recovery system are followed according to procedure. Table 5 NAR Safety Codes and Compliances Page 15 of 53

16 6.6. Rocket Motors and Energetic Devices Only motors certified by the National Association of Rocketry or the Tripoli Rocketry Association will be purchased. The active ingredient in high power rocket motors is solid Ammonium Perchlorate Composite Propellant (APCP) Storage and Handling Motors will remain disassembled and in original packaging until immediately prior to launch. Motors will also be stored at a temperature between 45 degrees Fahrenheit and 100 degrees Fahrenheit and away from external sources of flame or heat. Igniters will be stored separate from the motor. All purchases, storage, transportation, and use of rocket motors and energetic devices will be done by the proper NAR/TRA personnel. Motors casings and reloads will be purchased and handled by Team Mentor, Jerry Appenzeller who is a level 3 certified member by TRA. The rocket engines will be stored in the rocket design room at, where they will be kept in suitable conditions. All ejection charges will be properly stored in the rocket design room as well Transportation In the United States, APCP is excluded from the Department of Alcohol, Firearms, and Tobacco s list of explosive materials. Therefore, it will be shipped to a designated location so it is there upon the team s arrival prior to launch, or transported by car. During transport, extra precaution will be taken to ensure hazardous materials are kept away from sources of flame or heat. Since the fuel is not being used for commercial purposes, no special permits or licenses will be required Use of High Power Motors A high power motor will not be used in a rocket without prior simulation of the flight using that motor. Only NAR/TRA members are allowed to handle motors. Only the motors which the team NAR/TRA members are certified to handle will be used. Page 16 of 53

17 6.7. Written Member Agreement The figure below depicts the written statement that all team members sign to indicate the understanding and willingness to abide by the safety regulations set forth by the 2018 NASA Student Launch Initiative Committee Figure 4 Akronauts Safety Covenant signed by all members of the Akronauts Page 17 of 53

18 6.8. Safety Inspections On top of all the stringent safety inspections performed by The Akronauts, its mentors, and advisors; The will participate in the Launch Readiness Review prior to launch in which members of the NAR assess the launch vehicle and determine its safety and readiness to fly. The Akronauts will also participate in any other safety inspection deemed necessary by the NASA SLI council. The Akronauts will comply with all decisions made by inspectors and Range Safety Officers (RSO) 6.9. Flight Readiness The Akronauts understand that that all decisions made by the Range Safety Officer are final. If the RSO determines that the rocket is unfit for flight, the Akronauts will work with the RSO to find a solution deemed acceptable by the RSO. If the launch vehicle is still found unfit for flight, the Akronauts realize that they must accept and respect this decision Compliance with Standards The Akronauts will make their best effort to comply to all standards set for them. The Akronauts understand there are consequences if these standards are not met and if it is determined that they are not met, it will be determined that the rocket will not fly. 7. Technical Design 7.1. Vehicle Summary The launch vehicle was designed based on experience from previous competitions as well as the 2018 NASA Student Launch Handbook requirements. In spring of 2017, the team successfully launched a 147 tall rocket to 5,135 feet using fiberglass and carbon fiber body tubes, 3D printed nose cone and fiberglass fins at the 2017 NASA Student Launch. The target altitude was 5,280 feet. Open Rocket was used as the primary flight simulation software, but this year the team hopes to utilize other simulation softwares such as RASAero to improve our flight projections. The proposed rocket for the 2018 NASA Student Launch competition can be seen in Figure 5 below. Figure 5 Vehicle Dimensions All dimensions in inches Page 18 of 53

19 The launch vehicle was designed based on previous competition experience as well as the requirements outlined in the 2018 NASA Student Launch Handbook. In spring of 2017, the team successfully launched an 147 tall rocket 5,135 feet at the NASA student launch competition. The rocket was composed of a fiberglass and carbon fiber body, carbon fiber and 3-D printed nosecone, and fiberglass fins. OpenRocket and RASAero were the primary simulation software used. The combined use of both programs will be used for modeling and simulation. The proposed rocket for the 2018 NASA Student Launch competition can be seen in Figure 5 Total length of the proposed 2018 NASA Student launch rocket is roughly inches (8ft. 3 1/4 in.). The lengths and widths designated for each component within the rocket are shown in Table 6. Component Length (inches) Thickness (inches) Nosecone 26 1/4 1/8 Main Chute 15 - Avionics Bay 12 - Payload (Rover) 12 - Drogue Chute 4 - Engine Bay 24 1/4 Fins Root Chord: 11 Tip Chord: 4 Height: 4 3/4 Sweep Length: 7 1/8 Aluminum Thrust Plate Wood Centering Rings Aluminum Recovery Bulkheads Aluminum Motor Mount Fiberglass Couplers 1/2 1 1/2 1/2 3 1/4-1/ /8 Table 6 - Vehicle component length and width approximations Page 19 of 53

20 Once the general dimensions and layout of the rocket were decided, the weights designated for each rocket system were estimated and displayed in the following table. The total estimated dry weight is 31.5 pounds. A breakdown of the approximated component weights can be found below. At this stage of the design phase, these are only approximations and are estimated according to the team s past experience and knowledge. The weight estimations were based on the requirements designated in the 2018 NASA SL Handbook and from the expected dimensions of the rocket. A 20% tolerance was incorporated into this estimate to account for any future changes in the design. Component weight (total) Total Weight (pounds) Nose Cone 3 Body Tubes 10 Avionics Bay 3 Payload 5 Main Chute 1 1/2 Drogue Chute 1/4 Engine Bay 14 Fins 1/2 Aluminum Thrust Plate 1 Wood Centering Rings 1/2 Aluminum Recovery Bulkheads 1 1/2 Aluminum Motor Mount 1/2 Fiberglass Couplers 2 Table 7 Launch vehicle component weights Page 20 of 53

21 7.2. Material Selection and Justification The rocket will be subjected to about 403 pounds of force from thrust during flight. In order to achieve a stable, successful launch these forces during flight need to be addressed to determine the type of material for the rocket s construction. Differing materials were considered for each vehicle component. Material decisions were made regarding the body tubes and couplers, bulkheads, centering rings, thrust plate, and the nose cone. The main materials considered are listed below in the following tables along with their respective pros and cons. Body Tube, Coupler, and Nose Cone Materials Material Pro Con Fiberglass Carbon Fiber Cardboard Tensile Strength of 300 ksi Affordable Student Wound Flexible Tensile Strength of 600 ksi Reflective of Heat Lightweight Student Wound Low Cost Lightweight Heavy Hand Cut Rigid Conductive Blocks Avionics Communication Hand Cut High Cost Low Tensile Strength Highest Necessary Thickness Not Readily Available in Needed Sizing Flammable After comparing the three available materials, the body tubes and couplers will be composed of fiberglass and carbon fiber will make up the nose cone. Fiberglass was chosen for the body tubes and couplers because it easily met the necessary strength requirements for flight while also being affordable. The fiberglass will also have a negligible effect on communication with the avionics. Carbon fiber was chosen for the nose cone, because of its high strength and lightweight characteristics. Avionics will not be located in the nose cone and will not be affected by the use of carbon fiber. Page 21 of 53

22 Bulkheads, Centering Rings, and Thrust Plate Materials Material Pro Con Aluminum Wood High Tensile Strength Flame Resistant Precisely machined Low density Lightweight Low Cost Heavy Conductive High Cost Flammable Low Tensile strength Hand Cut The thrust plate will experience 403 pounds of thrust during flight and the bulkheads will need to absorb high amounts of instantaneous force as the parachutes are deployed. Aluminum will be used for the bulkheads and thrust plate because of its high tensile strength and ability to be accurately machined. The centering rings will only experience low amounts of force during flight and recovery. Therefore, wood will be used for the centering rings due to its lightweight and low-cost characteristics Projected Altitude The launch vehicle s projected altitude at apogee was calculated using OpenRocket. General dimensions, weight designations, and atmospheric data of where the rocket will be launching (Huntsville, Alabama) were put into the software where multiple simulations were performed. The most accurate simulation launched the rocket to an altitude of 5,472 feet. As seen in Figure 6, the rocket is well above the minimum launch velocity and the minimum static stability margin requirements. The minimum launch velocity is 61.4 ft/s and the static stability margin is 2.6. Figure 6 Screenshot of the simulated flight characteristics using OpenRocket software As the team continues to refine the design, the general dimensions and weight designations may change. Any changes will be input into OpenRocket as well as other flight projection softwares in an attempt to bring the launch vehicle s altitude at apogee closer to 5,280 feet, the competition altitude goal. Page 22 of 53

23 Figure 7 Simulated vehicle Altitude (red), Velocity (blue), and Acceleration (green) throughout flight Figure 7 shows vehicle altitude, velocity, and acceleration throughout flight. This figure also depicts when main events occur, such as motor burnout, apogee, and main chute deployment Parachute System Design The launch vehicle will be a single compartment, dual deployment recovery system using black powder for the ejection. At apogee (5,280 ft.), a drogue parachute will be deployed from the lower body tube. Upon reaching an altitude that is safe for main parachute deployment (800 ft.), the drogue will be detached from the lower bulkhead and function as a pilot parachute for the main. The main and drogue parachutes will be connected to the upper and lower bulkheads of the launch vehicle. Upon reaching the main deployment altitude, the drogue will be unlinked from the bulkheads and used as a pilot parachute to pull out the main. Eyebolts will be used as fasteners for each parachute in order to maintain a firm connection to the bulkheads. The linked deployment system will be a redundant system in order to ensure that the main parachute is deployed at the determined altitude. The gores of both parachutes, as well as their shock cords, will be made of ripstop nylon. The material will be purchased from vendors, then assembled into two separate parachutes. This method has been immensely successful at previous team launches. Page 23 of 53

24 The recovery system will follow a strict sequence of events. Refer to Table 8 for the sequence of events and the altitudes at which they will occur. Note that the Main Deployment altitude is subject to change on launch day to a viable altitude as deemed necessary by either the Akronauts Safety Officer or RSO due to wind and weather constraints or other issues that may cause caution Sequence Event Altitude 1 Drogue Deployment 5,280 ft. 2 Main Deployment 800 ft. Table 8 Recovery System Event List 7.5. Projected Motor Brand and Designation With a target altitude of 5,280 feet and a limiting specific impulse of 5120 N/s, in order to stay under this limit and reach the target altitude, simulations showed that a Cesaroni L1355 Motor will satisfy the conditions in place. The 75mm. motor has a total impulse of Ns and will use Smokey Sam propellant. The thrust curve for the selected motor can be seen in the figure below. Figure 8 Thrust over time of a Cesaroni L1355 motor Page 24 of 53

25 7.6. Projected Payload Design Rover Design Summary Our current payload design is an autonomous, two-wheeled self-balancing vehicle. The vehicle will be remotely deployed from the nose cone using a system of energy storing devices. A black powder system will eject the nosecone from the rest of the rocket body after landing and coming to rest. The payload bay will be spring loaded; where the ejection of the nose cone will release the compression of the spring, then deploying the rover with a light ejection. Once the rover has come to rest after deployment, it will employ obstacle avoidance software and drive away from the vehicle. The requirements state a minimum travel distance of 5 feet from the rest of the rocket, we plan to have the rover travel at least feet. Once the rover determines that it has traveled the required distance, the panels will be deployed from the inside of a spring-loaded bay door on the rover body. The rover will then go into a hibernation mode to charge until recovered Rover Deployment To deploy the rover, we will begin by ejecting the nose cone from the rest of the rocket body using a system similar to that of previous rocket s recovery system. This system will utilize a black powder cartridge to pressurize the payload bay and eject the nose cone. This ejection will release the force compressing the spring beneath the rover, allowing the spring coils to quickly depress and deploy (push) the rover horizontally out of the payload bay. This spring system may be either a single spring, or a nested spring system. This will be determined by the final weight of the rover assembly, and ejection testing. The rover will be ejected with a force no smaller than required to have the second wheel fully clear the payload bay and body tube. Page 25 of 53

26 Traverse terrain A majority of the design phase will be focused on the autonomous aspect of the rover itself. This will require an array of depth sensors, communications and processing power, and the ability for the rover to identify its own location relative to the rocket. More specifically, relative to the electronics bay of the rocket. Having the minimum rover travel distance far surpass the requirement of 5 feet ensures that the rover is at least 5 feet from the closest section of the landed vehicle. The rover itself will be a self-balancing, 2 wheeled all-terrain bot. This will be controlled with an Arduino Microcontroller Board, with a high-accuracy 6-axis motion control chip. This chip will have a 3-axis gyroscope and accelerometer, embedded temperature sensor, as well as the ability to govern and communicate with additional external sensors. This chip will allow the rover to self-balance and communicate commands to the motor encoder with a high degree of accuracy. Using IR sensors and transmitters to continuously map terrain and measure distances, the rover will travel in a general away direction from the electronics bay transmitter along the what the rover deems the flattest surface terrain. This could be limited via coding to a maximum degree of deviation from a straight,180 degree travel path away. The rover is designed to have a clearance of about 2 inches from flat ground to the bottom of the rover body, which will allow the rover to travel over the variable terrain of the recovery zone and over any small debris. Anything larger the IR sensors will pick up and the rover will navigate around the obstacle Solar Panel Deployment & Hibernation The deployment of the solar panels will begin when the rover determines it has traveled the required distance from the rest of the rocket body. Once the rover comes to a complete stop, it will release the latch for the spring-loaded solar panel bay door. The bay door would swing 180 degrees fully open, mechanically stopped by a plate. The rover will then wait until physically recovered and returned to the judges table. A possible feature of the rover code is a solar panel optimization sequence, which would require an additional light sensor on the top of the rover body. Once the rover determined it has traveled the required distance, it would rotate a full 360 degrees while taking readings with the onboard light sensor. The rover would then orientate itself at the angle which had the highest lumen value reading from the light sensor. At that point the latch would be released, allowing the spring-loaded deployment of the solar panels. Page 26 of 53

27 7.7. Requirements Vehicle Requirements Vehicle Requirements Solutions The vehicle will deliver the payload to an apogee altitude of 5,280 feet above ground level (AGL). The vehicle will 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 5280 feet AGL. The team will lose one point for every foot above or below the required altitude. Each altimeter will be armed by a dedicated arming switch that is accessible from the exterior of the rocket airframe when the rocket is in the launch configuration on the launch pad. Each altimeter will have a dedicated power supply. Each arming switch will be capable of being locked in the ON position for launch (i.e. cannot be disarmed due to flight forces). The launch vehicle will be designed to be recoverable and reusable. Reusable is defined as being able to launch again on the same day without repairs or modifications. Document all weights for all parts of the launch vehicle for center of gravity calculations. Team will use hand calculations along with OpenRocket and RASAero for accurate flight simulations. Test flights will aid in verifying the precision. The option of air brakes will be researched and considered in effort to minimize the error in achieving the target apogee. Launch vehicle will carry at least two commercial barometric altimeters for redundancy. Launch vehicle will be designed with the goal of achieving the desired altitude of 5,280 feet AGL. Launch vehicle will have opening on the body tube in line with the internally mounted switches to arm the altimeters while in the launch configuration on the launch pad. Each altimeter will have its own 9 volt battery. The arming switches will be able to be locked to prevent flight forces from changing their orientation. Launch vehicle will utilize GPS trackers to aid in recovery during flight and landing. Parachutes will be designed to allow a low speed damage free landing that would allow the launch vehicle to be reused without repairs or modifications. Page 27 of 53

28 Vehicle Requirements The launch vehicle will 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. Solutions The launch vehicle will comprise of two independent sections. payload section and booster section. These two sections will be tethered together. The nose cone will separate upon landing to allow the payload to eject from the upper body of the rocket. The launch vehicle will be limited to a single stage. The launch vehicle will be capable of being prepared for flight at the launch site within 3 hours of the time the Federal Aviation Administration flight waiver opens. Launch vehicle motor selection will allow for target altitude of 5280 feet AGL to be reached with only one stage. A clear launch procedure checklist will be created and practiced to ensure that the launch vehicle setup can be completed within the required amount of time. The launch vehicle will 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 components. All batteries and power supplies will be selected to allow for successful powering of all electronic systems for an extended period of time. The launch vehicle will 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. Launch vehicle will use commercial igniters provided by Cesaroni utilizing a standard 12 volt direct current firing system. The launch vehicle will require no external circuitry or special ground support equipment to initiate launch (other than what is provided by Range Services). Launch vehicle will be designed without the requirement of external circuitry or special ground support equipment to initiate launch. The launch vehicle will use a commercially available solid motor propulsion system using ammonium perchlorate composite propellant (APCP) which is approved and certified by the National Association of Rocketry (NAR), Tripoli Rocketry Association (TRA), and/or the Canadian Association of Rocketry (CAR). Launch vehicle will use a Cesaroni L1355 motor for its full-scale launch vehicle. Page 28 of 53

29 Vehicle Requirements Pressure vessels on the vehicle will be approved by the RSO and will meet the following criteria: The minimum factor of safety (Burst or Ultimate pressure versus Max Expected Operating Pressure) will be 4:1 with supporting design documentation included in all milestone reviews. Solutions The current vehicle design does not include any pressure vessels. If the design is modified to include a pressure vessel in the future, NASA and the RSO will be notified and the outlined criteria will be met. Each pressure vessel will include a pressure relief valve that sees the full pressure of the valve that is capable of withstanding the maximum pressure and flow rate of the tank. Full pedigree of the tank will be described, including the application for which the tank was designed, and the history of the tank, including the number of pressure cycles put on the tank, by whom, and when. The total impulse provided by a College and/or University launch vehicle will not exceed 5,120 Newton-seconds (L-class). Launch vehicle will utilize L1355 motor with total impulse of Newton seconds. The launch vehicle will have a minimum static stability margin of 2.0 at the point of rail exit. Rail exit is defined at the point where the forward rail button loses contact with the rail. Launch vehicle static stability margins of at least 2.0 will be verified with hand calculations, OpenRocket and RASAero. The current launch vehicle design has a static stability margin of 2.6. The launch vehicle will accelerate to a minimum velocity of 52 fps at rail exit. The current estimated 8ft rail exit velocity is 61.4 fps using OpenRocket. All teams will successfully launch and recover a subscale model of their rocket prior to CDR. Subscales are not required to be high power rockets. The team plans to design a 1:2 scaled model of the full scale launch vehicle for verification of stability and integration of systems. Page 29 of 53

30 Vehicle Requirements All teams will successfully launch and recover their full-scale rocket prior to FRR in its final flight configuration. The rocket flown at FRR must be the same rocket to be flown on launch day. The purpose of the full-scale demonstration flight is to demonstrate the launch vehicle s stability, structural integrity, recovery systems, and the team s ability to prepare the launch vehicle for flight. A successful flight is defined as a launch in which all hardware is functioning properly (i.e. drogue chute at apogee, main chute at a lower altitude, functioning tracking devices, etc.). Any structural protuberance on the rocket will be located aft of the burnout center of gravity. Vehicle Prohibitions: The launch vehicle will not utilize forward canards. The launch vehicle will not utilize forward firing motors. The launch vehicle will not utilize motors that expel titanium sponges (Sparky, Skidmark, MetalStorm, etc.) The launch vehicle will not utilize hybrid motors. The launch vehicle will not utilize a cluster of motors. The launch vehicle will not utilize friction fitting for motors. The launch vehicle will not exceed Mach 1 at any point during flight. Vehicle ballast will not exceed 10% of the total weight of the rocket. Solutions The full-scale rocket test flight will be flown with all final flight configuration systems and payload with the goal of a successful flight as outlined. This test flight will be treated exactly like the competition flight. The launch vehicle will be designed so that any protuberance will be located aft of the burnout center of gravity. The burnout center of gravity will be verified using hand calculations, OpenRocket and RASAero. The launch vehicle will be designed while adhering to the list of Vehicle Prohibitions. Page 30 of 53

31 Recovery System Requirements Recovery System Requirements The launch vehicle will stage the deployment of its recovery devices, where a drogue parachute is deployed at apogee and a main parachute is deployed at a lower altitude. Each team must perform a successful ground ejection test for both the drogue and main parachutes. This must be done prior to the initial subscale and full-scale launches. At landing, each independent sections of the launch vehicle will have a maximum kinetic energy of 75 ft-lbf. The recovery system electrical circuits will be completely independent of any payload electrical circuits. All recovery electronics will be powered by commercially available batteries. The recovery system will contain redundant, commercially available altimeters. The term altimeters includes both simple altimeters and more sophisticated flight computers. Motor ejection is not a permissible form of primary or secondary deployment. Removable shear pins will be used for both the main parachute compartment and the drogue parachute compartment. Recovery area will be limited to a 2500 ft. radius from the launch pads. Solutions The launch vehicle will use redundant Stratologgers which are capable of dual deployment. Both parachutes will be located in a single compartment in the rocket and will undergo a linked deployment. The team will ejection test the launch vehicle in flight configuration, without motor, prior to both initial subscale and full-scale launches. All tests will be documented. Parachutes will be designed such that all independent sections of the launch vehicle have a maximum kinetic energy of 75 ft-lbf. The recovery system will not be combined with the payload electrical circuit. Two Stratologger altimeters will be used as redundant recovery systems, each having its own 9-volt battery. Both Stratologgers will utilize two arming switches each. The first arming switch will be used to power on the Stratologger, and once the device has completed its boot sequence, the second arming switch connects the igniters to the Stratologger. All arming switches will be located on the exterior at a height that is accessible from a person standing on the ground. Motor will be mechanically fastened to the launch vehicle and unable to move for duration of flight. Black powder will be used as the deployment mechanism for the drogue parachute and also used to separate the two parachutes. The design will utilize removable shear pins to allow for proper pressurization of the parachute compartment before ejection. The parachute will be of a reasonable size such that the launch vehicle remains within the recovery area. Page 31 of 53

32 Recovery System Requirements An electronic tracking device will be installed in the launch vehicle and will transmit the position of the tethered vehicle or any independent section to a ground receiver. Any rocket section, or payload component, which lands untethered to the launch vehicle, will also carry an active electronic tracking device. The electronic tracking device will be fully functional during the official flight on launch day. The recovery system electronics will not be adversely affected by any other on-board electronic devices during flight (from launch until landing). The recovery system altimeters will be physically located in a separate compartment within the vehicle from any other radio frequency transmitting device and/or magnetic wave producing device. The recovery system electronics will be shielded from all onboard transmitting devices, to avoid inadvertent excitation of the recovery system electronics. The recovery system electronics will be shielded from all onboard devices which may generate magnetic waves (such as generators, solenoid valves, and Tesla coils) to avoid inadvertent excitation of the recovery system. The recovery system electronics will be shielded from any other onboard devices which may adversely affect the proper operation of the recovery system electronics. Solutions GPS and radio beacons will be installed in launch vehicle and will be transmitted back to a ground receiver to allow for position tracking for each independent section. The current design does not have any section, or payload component, that is untethered from the launch vehicle. If the design changes NASA and the RSO will be notified and the requirement will be met. A launch procedure will be utilized to check that all systems are fully functional. The recovery system electronics is located within the launch vehicle such that any other on-board electronic devices do not adversely affect them. Any radio frequency transmitting device and/or magnetic producing device are located in separate compartment(s) from the recovery system altimeters. The recovery system electronics are shielded from all on-board transmitting devices. The recovery system will be shielded from all on-board devices which may generate magnetic waves if they are included in design. The recovery system is shielded from any other onboard devices that may adversely affect them. Page 32 of 53

33 Experiment Requirements Experiment Requirements Each team will choose one design experiment option from the following list: Target Detection Deployable Rover Landing Coordinates via Triangulation Teams will design a custom rover that will deploy from the internal structure of the launch vehicle. At landing, the team will remotely activate a trigger to deploy the rover from the rocket After deployment, the rover will autonomously move at least 5 ft. (in any direction) from the launch vehicle Once the rover has reached its final destination, it will deploy a set of foldable solar cell panels. Solutions The rocket will be carrying a deployable rover through launch and recovery. The team will design a rover that will deploy from the internal structure of the launch vehicle. Black powder charges will be used to pressurize the payload cavity, separating the upper body and nose cone. A spring will decompress, further pushing the payload out of the rocket. After deployment, the rover will activate and use infrared navigation to avoid objects and travel a predetermined distance of at least 10 feet to ensure it travels the minimum required distance from the rocket. Once the rover has traveled the predetermined distance, a latch will be retracted. This will allow the spring-loaded solar panel to open Major technical challenges and solution Launch Vehicle Challenges Launch Vehicle Challenge Maintaining launch vehicle/payload statement of work while reducing total weight. Aligning Fins Properly Nose Cone Fabrication Solution The use of composites and structural reinforcements will aid in reducing total material used for similar strength and function. Design fin alignment jig to hold fins at correct position for attachment to rocket. Seek guidance from mentor, and outside companies, on proper techniques to creating a nose cone. Table 9 Launch Vehicle Challenges and Solutions Page 33 of 53

34 Recovery System Challenges Recovery System Challenge Implementing linked deployment of the parachutes Changing our method of separation from CO 2 to black powder ejection Preventing the vehicle from drifting outside of the ½ mile launch zone Ensuring the vehicle launch system lands with less than the maximum allowed landing kinetic energy Solution Use a redundant system of cable-cutters linked in parallel to ensure that the main and drogue chute are deployed Incorporate fireproofing and Nomex fabrics to prevent any detrimental damage to the recovery system. Create a calculator that may be used on launch day to assess the wind speeds and adjust the main parachute ejection altitude Ensuring that the weight of the rocket and the anticipated landing velocity are within the restrictions deemed by the Akronauts to ensure a lowered landing kinetic energy. Table 10 Recovery System Challenges and Solutions Experiment Challenges Experiment Challenge Reduced diameter of the vehicle limits payload design options Remote deployment of the payload after the vehicle has landed Unknown terrain upon landing, increasing difficulty of navigation to target distance from vehicle Once the rover is remotely activated, a two-wheel design will be unable to extract itself from the vehicle. Solution Went through rapid research for miniaturizing electronics and decided upon a two wheeled self-balancing rover design Use a fiberglass body tube and long-distance radio controllers to allow for signal reception within the landing distance Infrared sensor to detect obstacles and allow for autonomous object avoidance once the rover has been activated remotely. Spring-loaded mechanism that will be triggered by the ejection of the nose cone will allow for the rover to be extracted at a controlled rate. Table 11 Payload Experiment Challenges and Solutions Page 34 of 53

35 8. Educational Engagement Over the next year, the Akronauts anticipate engaging the local community in a variety of STEM activities. The Akronauts members are passionate about instilling a love for science in the minds of young people. As a team, members have regularly participated in community outreach events for local inner-city schools by hosting design competitions for the students to foster STEM education within the school. Schools that the Akronauts have visited include North Middle School, St. Vincent-St. Mary s High School, and Washington Park Community Elementary School. The current educational outreach plan includes programming with students ranging from first grade to college. Figure 9 Akronauts Electronics Lead, David, teaching high school students about telemetry and GPS tracking 8.1. Hope Always Lives On Over the past summer, the Akronauts partnered with a local disaster relief non-profit called Hope Always Lives On (HALO). Within this local organization is the LEADR Program. LEADR stands for Leadership, Education, And Development Retreat. This 3 day, 2 night retreat is designed to educate high school and middle school students from the Akron area on the importance of being a leader in their communities and to also inform them of the historical initiative, 93 Cents for Flight 93. This is a youth-based educational initiative and outreach program based around the inspiring messages of bravery, leadership, and sacrifice personified by the passengers and crewmembers of Flight 93. One of the projects the students participated in this past summer through the Akronauts was a parachute egg drop challenge in which the students designed and fabricated their own parachutes (similar to that of the Akronauts student fabricated 2017 NASA Student Launch Parachute). The parachutes then had to safely carry a raw egg during a descent of 7ft. Afterwards, the Akronauts discussed their competition rocket with the LEADRs and taught them some of the fundamentals of rocketry, such as the significance of Center of Pressure and Center of Gravity. Page 35 of 53

36 Figure 10 HALO Members holding the Akronauts 2016 Intercollegiate Rocket Engineering Challenge rocket, Project Daedalus Cents for Flight 93 During the LEADR retreat with HALO, the participating high schoolers and middle schoolers are educated on the personality and gifts that each brings to the table. These natural traits and talents are developed through team-building exercises and leadership training, and then they are put into action through business plans created to impact the community. One business plan that the LEADR students presented is to sell wooden planes (as seen below) for $0.93 to the public to raise funds for a memorial for the 40 lives lost on Flight 93 during the September 11th attacks. The public will then have the chance to decorate the planes. Figure 11 One of the wooden planes sold to public for 93 cents that will be secured and launched in an Akronauts rocket. After recovery, all 40 planes will be assembled into a plane-mobile and hung from the Akronauts rocket in the MAPS Museum. The top 40 designs will be fastened and launched inside of one of the Akronauts rockets as a beautiful, symbolic gesture to allow the passengers of Flight 93 to fly again. After launching, the launched rocket may be put on display in the Military Aviation Preservation Society (MAPS) Museum and will have the 40 launched planes assembled into a mobile and hung from the displayed rocket as a lasting memory of the lives lost on Flight 93. Page 36 of 53

37 8.3. National Inventors Hall of Fame STEM Middle School This year, the Akronauts are partnering with NIHF STEM middle school, where 5th graders will be building rockets. Team members will demonstrate the concepts of physics, more specifically, how forces and motion in flight affect rockets. Members will also engage the students in specific fields of engineering, by providing them with technical challenges in mechanical, electrical, and chemical engineering that are relevant to rocket technology. Specific aspects of the team s high-powered rocket will be presented to the students over the course of five class periods. Questions intended to lead to critical thinking will be posed to the students. The school itself will provide the necessary funding for materials to carry out education on rocketry. Figure 12 NIHF Student running with one of the Akronauts fabricated parachutes In evaluating the educational engagement activities, a case study shall be completed, detailing the Akronauts time with the 5th grade students from the National Inventors Hall of Fame STEM Middle School. The Akronauts will visit the school a minimum of five times and present material in conjunction with the forces and motion unit that the students will be studying. Students will engage in various activities that will increase their knowledge of basic principles in engineering fields as they contribute to rocketry. During three of the classroom sessions, students will design and build their own model rockets. Participation in each of the three sessions will earn the students level certifications. The levels will be labeled as silver, gold and platinum. If the students achieve all three levels, they will earn the title of Junior Akronauts. Our goal is to encourage students to actively participate during each session as they apply concepts to the rockets they build. During the silver level, the students will assemble and launch model rockets that have been supplied. During the gold level, students will design and build a launch pad with which to launch the previous model rocket off of. During the platinum level, the students will design and build a model rocket from provided recycled materials. The recycled rocket will be launched from the launch pad the students designed and built during the gold level. The case study will detail the mile marker skills or activities involved in each level of achievement. The team s goal will be to have each student achieve platinum by the end of the program. Page 37 of 53

38 An additional workshop period will focus on payload concepts and designs. The team members will present several payload concepts to students. Students will then develop their own payloads, keeping in mind how the experiment will be incorporated into a rocket. Dimensions provided will be sized to fit a future Akronauts project. While the students will not physically construct their payload experiments, they will draw their designs and in groups, discuss functions and potential challenges the designs might pose. Students will be encouraged to polish their designs for consideration for incorporation into a future Akronauts project Boy Scout Troop 1 and Cub Scout Pack 3001 Local Scout Troop 1 and Pack 3001 also plan to participate in the Akronauts educational programming. A similar curriculum to the NIHF STEM Middle School will be used with the troop and pack, however, necessary modifications will be made to account for the diverse age groups present. The scouts range from first grade to high school. The Akronauts are also working to make similar arrangement with one of the Northeastern Ohio Girl Scout Troops University of Akron Ex[L] Center One of the University of Akron s most recent additions is the Experiential Learning Center for Entrepreneurial & Civic Engagement. The Ex[L] Center provides students with unique education opportunities often not available in a traditional classroom environment. Their goal is to enable students to emerge as civically engaged, skilled and adaptable leaders, ready to take on real world challenges. Part of the Ex[L] Center s program offerings include what are known as Unclasses. These special topic offerings are university and community focused. Recent Unclasses have included Skills for Community Engagement and Consequences of Caring. The Akronauts have proposed an Unclass that would promote the partnership of university engineering design teams with other departments on campus. A frequent need that design teams have faced is the need for management of communications and public relations. The Akronauts are one of the first of their kind to include a public relations manager on their officer board. After interacting with the other engineering design teams on campus, the Akronauts have initiated the next steps in promoting a relationship with the School of Communication. Through the Ex[L] Center, the team aims to support the development and execution of an Unclass that would connect design teams with other departments on campus. The School of Communication will be the first partnership, as there are currently no classes within the curriculum that teach public relations within STEM fields. Participating students, through the Unclass program, will be able to receive course credit for their work with the design teams. The Akronauts will also pursue similar courses for partnership with the College of Business, School of Art and Department of Finance. Page 38 of 53

39 While this partnership will evolve over multiple semesters, for the purpose of this proposal, the Akronauts intend to work with the Ex[L] Center and School of Communication to continue developing the first Unclass Judith Resnik Community Learning Center Located in West Akron, the Judith Resnik CLC is a well-known Akron elementary school. The CLC was named for astronaut Judy Resnik, an Akron native killed on the Challenger explosion. The Akronauts are currently seeking to partner with the Judith Resnik CLC to coordinate a similar program that will be carried out at the NIHF Middle School. Evaluation will be conducted as students achieve silver, gold and platinum status. A case study will be completed along with the Educational Engagement Activity Report. Figure 13 A 5 th Grader takes distance measurements for her catapult design Page 39 of 53

40 9. Project Plan NASA Student Launch Task Name Duration Start Finish 156 days Mon 9/11/17 Mon 4/16/18 Safety 156 days Fri 9/15/17 Fri 4/20/18 Compliance/Requirements 2 days Fri 9/15/17 Mon 9/18/17 Unmanned Rocket Launches Procedures for NAR/TRA Personnel NAR Safety Requirements Hazard Recognition 112 days Thu 9/14/17 Fri 2/16/18 Accident Avoidance 2 days Fri 9/15/17 Sun 9/17/17 Pre-Launch Briefings 3 days Thu 9/14/17 Sun 9/17/17 Personnel Hazard Analysis 6 days Mon 9/18/17 Mon 9/25/17 Hazards Ranking w/likelihood and Severity 11 days Mon 10/2/17 Mon 10/16/17 MSDSs 11 days Mon 10/2/17 Mon 10/16/17 Data Justifying Rankings 11 days Mon 10/2/17 Mon 10/16/17 FMEA of Proposed Design 6 days Mon 10/16/17 Mon 10/23/17 Warning of Hazards from Missing a Step 47 days Wed 11/1/17 Thu 1/4/18 Update Fail Modes and Effects Analysis 25 days Mon 1/15/18 Fri 2/16/18 Environmental Concerns 111 days Mon 9/18/17 Mon 2/19/18 List all Environmental Concerns 26 days Mon 9/18/17 Mon 10/23/17 Final Hazards 6 days Mon 2/12/18 Mon 2/19/18 Functional Risks 21 days Mon 9/18/17 Mon 10/16/17 Time Risk Resource Risk Budget Risks Mitigation Technique for each Risk Launch Procedures 49 days Mon 10/30/17 Thu 1/4/18 Recovery Preparation Motor Preparation Setup on Launcher Igniter Installation Page 40 of 53

41 Troubleshooting Post-Flight Inspection Task Name Duration Start Finish PPE 3 days Thu 9/14/17 Sun 9/17/17 General PPE 3 days Thu 9/14/17 Sun 9/17/17 PPE for Each Step in Procedure 47 days Wed 11/1/17 Thu 1/4/18 Motor Transportation Plan 3 days Thu 9/14/17 Sun 9/17/17 Methods for Verifying Controls/Mitigations 20 days Mon 1/29/18 Fri 2/23/18 Aerostructure 156 days Fri 9/15/17 Fri 4/20/18 Vehicle Dimensions 137 days Wed 9/13/17 Thu 3/22/18 General Vehicle Dimensions 4 days Wed 9/13/17 Sun 9/17/17 Material Selection 4 days Wed 9/13/17 Mon 9/18/17 Final Vehicle Design 49 days? Mon 10/30/17 Thu 1/4/18 Size and Mass 47 days Wed 11/1/17 Thu 1/4/18 Rail Size 47 days Wed 11/1/17 Thu 1/4/18 Suitability of Fin Design CAD Drawings of Final Launch Video Integrity Discussion Materials for Bulkheads Justification for Material Selection Provide Justification for Design Selection Final Motor Choice 49 days Mon 10/30/17 Thu 1/4/18 Launch Vehicle Summary 20 days Fri 9/22/17 Thu 10/19/17 Describe Each Subsystem/Components Estimated Masses for Each Subsystem Motor Mounting and Retention Provide a CAD Drawings 26 days Mon 9/18/17 Mon 10/23/17 Design Review 18 days Thu 9/21/17 Mon 10/16/17 Discuss Alternative Designs Evaluate Pros/Cons of each Alternative Flight Simulations 136 days Thu 9/14/17 Thu 3/22/18 PDR Simulations 6 days Sun 10/1/17 Fri 10/6/17 Page 41 of 53

42 Task Name Duration Start Finish Thrust to Weight Ratio Rail Exit Velocity Altitude Predictions with Vehicle Data Stability Margin Simulated CP/CG Locations Calculated Kinetic Energy Altitude Predictions CDR Simulations 49 days Mon 10/30/17 Thu 1/4/18 Simulated Motor Thrust Curve Altitude Prediction Final Design Sims 37 days Thu 1/4/18 Fri 2/23/18 Flight Profile Altitude Predictions Stability Margin Landing Kinetic Energy Thrust to Weight Ratio Rail Exit Velocity Key Phase KE Construction 47 days Wed 11/1/17 Thu 1/4/18 Construction Methods 49 days Mon 10/30/17 Thu 1/4/18 Final Assembly Description 31 days Fri 1/5/18 Fri 2/16/18 Discussion on Deviations 6 days Mon 2/19/18 Mon 2/26/18 Mass Statement Safety 11 days Mon 1/1/18 Mon 1/15/18 Recovery 156 days Fri 9/15/17 Fri 4/20/18 Final Recovery System 49 days Mon 10/30/17 Thu 1/4/18 Identify/Justify Final Design Describe Parachute Describe Harness Describe Bulkheads/Attachment Hardware Mass Statement and Mass Margin Parachute Sizes Page 42 of 53

43 Task Name Duration Start Finish Recovery Harness Type Size, Length, Descent Rates Tests of Staged Recovery Parachute Design 156 days Fri 9/15/17 Fri 4/20/18 Projected Parachute System Design 4 days Wed 9/13/17 Mon 9/18/17 Preliminary Design Review 21 days Wed 9/20/17 Wed 10/18/17 Review Each Component's Design/Alternatives Evaluate Pros/Cons of Alternatives Chose Leading Components/Explain Prove Redundancy Exists within the System Parachute Dimensions 90 days Fri 9/15/17 Thu 1/18/18 Preliminary Analysis on Parachute Sizing 21 days Wed 9/20/17 Wed 10/18/17 Size Required for Safe Descent 21 days Wed 9/20/17 Wed 10/18/17 As Built Parachute Sizes 17 days Thu 1/4/18 Fri 1/26/18 Descent Rates 6 days Fri 1/26/18 Fri 2/2/18 Calculations 84 days Mon 9/11/17 Thu 1/4/18 Drift Calculations 6 days Wed 10/18/17 Wed 10/25/17 Adjacent Drift Calculations 6 days Wed 10/18/17 Wed 10/25/17 Kinetic Energy at Landing 50 days Sun 10/29/17 Thu 1/4/18 CDR Drift Calculations 27 days Sun 10/29/17 Mon 12/4/17 Final Drift Calculations 20 days Mon 1/29/18 Fri 2/23/18 System Defense 27 days Thu 1/4/18 Fri 2/9/18 Recovery Preparation 15 days Mon 2/5/18 Fri 2/23/18 Propulsion 156 days Fri 9/15/17 Fri 4/20/18 Motor 83 days Mon 9/18/17 Wed 1/10/18 Motor Choice 21 days Mon 9/18/17 Mon 10/16/17 Review Motor Choices 21 days Mon 9/18/17 Mon 10/16/17 Final Motor Choice 22 days Wed 11/1/17 Thu 11/30/17 Simulated Motor Thrust Curve 9 days Mon 10/16/17 Thu 10/26/17 Motor Preparation 1 day Fri 9/22/17 Fri 9/22/17 Set-up Plan on Launcher 5 days Mon 2/12/18 Fri 2/16/18 Igniter Installation 27 days Thu 1/4/18 Fri 2/9/18 Launch Procedure 15 days Mon 2/5/18 Fri 2/23/18 Page 43 of 53

44 Task Name Duration Start Finish Payload 156 days Fri 9/15/17 Fri 4/20/18 Payload Description 4 days Fri 9/15/17 Wed 9/20/17 Payload Summary 26 days Mon 9/18/17 Mon 10/23/17 Objective/Experiment Description Design Review Alternatives Review Mass Estimate of all Payload Components Electronics Schematics 3D Drawings 51 days Fri 10/27/17 Fri 1/5/18 Drawings and Specs for Each Component Entire Payload Assembly Payload Integration into Launch Vehicle Payload Optimization 31 days Thu 1/4/18 Thu 2/15/18 Final Ejection Testing Changes to Assembly Final Dimensions/Drawings Electronics 156 days Fri 9/15/17 Fri 4/20/18 Established Member Skills 6 days Fri 9/15/17 Fri 9/22/17 Onboard System to Collect Flight Data 21 days Thu 1/4/18 Thu 2/1/18 Recovery 49 days Mon 10/30/17 Thu 1/4/18 Critical Design Review 49 days Mon 10/30/17 Thu 1/4/18 Electrical Components Drawings of all Electrical Component Block Diagrams and Electrical Schematics Operating Frequency of Locating Tracker FRR 40 days Mon 1/1/18 Fri 2/23/18 Altimeters/computers/switches/connectors 21 days Mon 1/8/18 Mon 2/5/18 Complete Redundancy Features 30 days Mon 1/8/18 Fri 2/16/18 Transmitters Discussion 17 days Fri 1/19/18 Mon 2/12/18 Drawings/Schematics 40 days Mon 1/1/18 Fri 2/23/18 Electronics/Recovery Interference 36 days Mon 1/1/18 Mon 2/19/18 Payload 130 days Fri 9/15/17 Thu 3/15/18 Page 44 of 53

45 Task Name Duration Start Finish Preliminary Design Review 26 days Mon 9/18/17 Mon 10/23/17 Electrical Schematics for All Elements of Preliminary Payload Estimated Masses for Electrical Components Justify Electrical Component Selection Preliminary Interfaces between Payload and Launch Vehicle Critical Design Review 49 days Mon 10/30/17 Thu 1/4/18 Discussion of Electronics/Safety Switches/Indicators Drawings/Block Diagrams Battery Choice/Justification Switch/Indicator Wattage and Location Justification for Electronics Selection Aerostructure 31 days Mon 1/8/18 Mon 2/19/18 Wiring Switches Retention of Avionics Boards Post-Flight Inspection Safety Plan 31 days Mon 1/8/18 Mon 2/19/18 Communication of Electronics 21 days Thu 1/25/18 Thu 2/22/18 Educational Engagement 156 days Fri 9/15/17 Fri 4/20/18 Outreach to Schools 95 days Mon 9/18/17 Fri 1/26/18 STEM After-School 60 days Mon 9/18/17 Fri 12/8/17 Activity Development 14 days Mon 9/18/17 Thu 10/5/17 Background Clearances 7 days Thu 10/5/17 Fri 10/13/17 Team Training 10 days Mon 10/16/17 Fri 10/27/17 Program Execution 15 days Mon 11/20/17 Fri 12/8/17 Physics Discussions 15 days Mon 1/8/18 Fri 1/26/18 Various Event Outreach 105 days Mon 10/2/17 Fri 2/23/18 Page 45 of 53

46 10. Projected Budget Recovery Description Manufacturer Quantity Unit Cost Total Cost Ripstop Nylon Material JoAnn Fabrics 3 yd. In Stock $0 Ripstop Nylon Material Performance Textiles 20 yd. Donated $0 Sewing Kit (Needles, Thread, Etc.) JoAnn Fabrics 1 $10 $10 Paracord Dick's Sporting Goods 100 ft. $30/100ft. $30 Black Powder Bass Pro Shop 1 $30 $30 1 Nylon Shock-Resistant Cord McMaster-Carr 50 ft. $4/ft $200 Total $390 Table 12 Recovery System Budget Avionics Description Manufacturer Quantity Unit Price Total Price StratoLogger Altimeter Module PerfectFlight 2 $60 $120 Total $120 Table 13 Avionics System Budget Page 46 of 53

47 10.3. Structure Description Manufacturer Quantity Unit Price Total Price 5.5 Cardboard Body Tubes LOC Precision 2 $38.50 $77.00 Cardboard Couplers for 5.5 Airframe LOC Precision 2 $9.08 $18.16 PR2032/PH3660 Resin & Hardener Kit Aircraft Spruce 1 $ $ K Carbon Fiber Tow Solar Composites 8 $24.00 $ K Fiberglass Tow Solar Composites 4 In Stock $0.00 3D printed nose cone mandrel University Facilities N/A $0.00 $0.00 Button Head Screws McMaster-Carr 1 $8.71 $8.71 Threaded Inserts McMaster-Carr 2 In Stock $0.00 Loctite McMaster-Carr 2 In Stock $0.00 ⅜ 36 x48 Plywood Sheets or Balsa?? McMaster-Carr 1 $68.27 $ Dia. 6 Lg Aluminum round stock McMaster-Carr 1 In Stock $0.00 Soldering Iron Tips Amazon 1 (3 tips) $5.48 $5.48 Duct Tape Home Depot 2 $4.00 $8.00 Misc. Extras $100 Total $ Table 14 Structure System Budget Page 47 of 53

48 10.4. Payload Description Manufacturer Quantity Unit Price Total Price Arduino Leonardo Microcontroller Board MPU Axis Motion Tracker Arduino 1 $19.80 $19.80 InvenSense 1 $5.25 $5.25 Gear Motor With Encoder Cytron 2 $21.32 $42.64 Infrared Receiver Sensor Adafruit 2 $1.95 $3.90 IR Transmitter Assembly Kit Parallax 2 $2.40 $4.80 Resistors, Wires, Other Miscellaneous Parts Spring 3 Diameter, 5 length, 2.31lb/in N/A N/A N/A $20 Lee Spring 1 $23.76 $23.76 Solar Panels Sundance Solar 4 $6.95 $ D Printed Wheels University Facilities 2 $0.00 $0.00 3D Printed Casing(s) University Facilities N/A $0.00 $ g CO2 Cartridges Peregrine 2 In Stock $0.00 CO2 Ejection System Peregrine 2 In Stock $0.00 Black Powder Bass Pro Shop 1 gram In Stock (Recovery) $0.00 Rechargeable AA Batteries Energizer 1 (4pack) $9.59 $9.59 Total $ Table 15 Payload System Budget Page 48 of 53

49 10.5. Propulsion Description Manufacturer Quantity Unit Price Total Price 4025L1355-P Motor Cesaroni Technologies 1 $ $ mm Propellant Grains White Lightning 6 $59.99 $ Total $ Table 16 Propulsion System Budget Subscale Rocket Description Manufacturer Quantity Unit Price Total Price Cesaroni Pro 38-3 grain Cesaroni Technologies 1 $ $ Cardboard body tubes LOC Precision 2 $10.44 $20.88 Cardboard Couplers for 3 Airframe LOC Precision 2 $4.13 $8.26 Button Head Screws McMaster-Carr 1 $8.71 $8.71 Threaded Inserts McMaster-Carr 2 In Stock $0.00 Loctite McMaster-Carr 2 In Stock $0.00 ⅜ 36 x48 Plywood Sheets McMaster-Carr 1 $68.27 $ Dia. 6 Lg Aluminum round stock McMaster-Carr 1 In Stock $0.00 6K Carbon Fiber Tow Solar Composites 4 In Stock $0.00 PR2032 Resin Aircraft Spruce 1 $99.75 $99.75 PH3660 Hardener Aircraft Spruce 1 In Stock $0.00 3D printed Nose Cone mandrel University Facilities N/A $0.00 $0.00 Total $ Table 17 Subscale Rocket Budget Page 49 of 53

50 10.7. Travel Expenses Description Price Hotel Expenses $2,500 Fuel $1,000 Food $250 Rental Cars/Vans $3,000 Shipping $100 Total $6,850 Table 18 Travel Expenses Total Expenses System Total Recovery $390 Avionics $120 Structure $620 Payload $178 Propulsion $607 Subscale Rocket $316 Travel $6,850 Total $9,100 Table 19 Total Expenses Page 50 of 53

51 11. Funding Plan The required funding for the NASA rocket is going to be an estimated $9,100. The Akronauts will be presenting the requested funding to the College Board of Engineering at the beginning of October. During last year s launch for the NASA competition, the proposed budget was $12,500. During , the university awarded $8,500 for the team s budget. The team also has a number of sponsors including: PCC Airfoils, Schaeffler, Performance Textiles, Advanced Circuits, Ronyak Paving, NASA Glenn Research Center, Tallmadge Collision Centers, Outback Steakhouse, and X-Winder. With the Rocket Team attempting to complete additional competitions this year, it is important to obtain additional funding from sponsors and the university. Students on Co-Op work with the Human Resources Department and management to negotiate possible sponsorships with sponsorship packets. Leadership and Akronauts personnel are also working on fundraising through the community, University of Akron, and online platforms to raise additional money. Organization Contribution College of Engineering $13,000 Mechanical Engineering Department $14,000 Electrical Engineering Department $4,600 PCC Airfoils $1,000 Schaeffler $2,500 Aetos Systems Inc. $400 Parker Hannifin Corp $500 Ronyak Paving $2,000 Akronauts Fundraising Events $2,200 Total $40,200 Table: List of Past Sponsors Page 51 of 53

52 12. Plan for Sustainability The Akronauts understand the importance of sustainability, especially as a young team. Each group of officers puts serious consideration into how to best set up future teams for success. A current goal for the season is to increase community awareness within both and the City of Akron. The team intends to continue to utilize social media accounts to further connect with team members and also with various publics. The Akronauts have begun speaking with the Great Lakes Science Center (GLSC) about collaborating by creating a camp for middle school and high school students. The GLSC has expressed interest in allowing the Akronauts to host a booth on the weekends as well to engage and encourage the public. In the spring of 2017, the Akronauts brought their previous year s NASA SLI Rocket to the Soap Box Derby, a popular event for young students in the Akron community, where children build their own car and aspire to race against other kids their age. The Akronauts successfully engaged the public and inspired young minds to consider rocketry and STEM related careers through answering questions, demonstrating the ingenuity behind the payload design, and giving encouraging advice. Figure 14 Akronauts President, Victoria, listening to an eager young student discuss her love of science at the Soap Box Derby The Akronauts are actively involved on the university campus. The team has participated in New Roo Weekend- a welcome weekend for incoming freshman and transfer students- as well as events like the new student engineering fair. As stated in in the Educational Outreach section of this report, the Akronauts are partnering with the Ex[L] Center to develop a class and long term program to unite student engineering design teams with communication, finance, business and design students. Page 52 of 53

53 Figure 15 Akronauts members recruiting new members at the University of Akron s New Roo Weekend With currently more than 40 active team members, the Akronauts continue to demonstrate success in recruiting new members. This year alone, the Akronauts recieved over 260 requests to join the team. The team s project focused structure enables and encourages members to participate in various projects, even while still working within the same subsystem. Such projects include getting level 1 and level 2 certified as well as participating in the Battle of the Rocket Competition. For recruitment this year, the Akronauts had all of the new members create their own rockets limited to the materials they were provided and within the time allotted. At the end of the event, over 10 rockets were created with a surprising amount of creativity. Figure 16 Some of the supplies the new members were limited to use for their rocket Figure 17 New member brainstorming designs for their rocket Page 53 of 53

54 Figure 18 Akronauts member prepares the compressed air launcher to launch a rocket Figure 19 Akronauts member eagerly waits to launch his rocket During the event, the members had the chance to launch their rocket and were scored on three criteria: Design, Altitude, and Rocket Name. Each rocket was launched using a student built air compressor and was launched under 15psi. The rocket that hit the highest altitude won a prize. The Akronauts have incorporated surveys throughout the year, providing team members with an opportunity to give additional feedback. Along with surveys, one-on-one meetings with members and officers have yielded constructive feedback that has been taken into consideration and implemented. Sustainability must be achieved through active listening. Community partners have included local businesses, locally based and nationally regarded engineering companies, schools, and local aerospace professionals. Maintaining an open line of communication with all partners is key to sustainability and growth. Communication methods range from s, to newsletters to social media updates. Several partners have provided use of machines not accessible at the university. Others have provided materials or fabrication of student designs. The Akronauts regularly update a sponsorship proposal, discussing team and current project details. Team members are encouraged to deliver addressed sponsor proposal to the companies where the students are on co-op rotation. The Akronauts have received financial support from several companies and continue to seek additional sponsorships. In the first year of operation, the team was awarded the Ohio Space Grant, an application that is again underway for the coming season. Aside from company sponsorships, additional funding will be raised through campus fundraisers such as dine-in events at various restaurant chains. Educational engagement continues to be at the forefront of the Akronaut s mission. As an increasing number of people across the globe return their attention to concepts of space travel and life on other planets, research and education have become increasingly critical to steady progress. In the city of Akron, a city founded and grown on innovation, the Akronauts value the opportunity to continue a thriving STEM tradition. The team seeks to inspire and equip future generations with the knowledge and passionate curiosity to continue to move the aerospace industry forward. Page 54 of 53