University of South Alabama NASA Student Launch Proposal

Transcription

1 University of South Alabama NASA Student Launch Proposal University Student Launch Initiative (USLI) Edited by CONNER DENTON DREW FAULK NGHIA HUYNH KENT LINO ANDREW TINDELL The University of South Alabama Mobile, Alabama 1

2 Contents 1 General Information University Mailing Address List of Payloads Landing Hazard Detection Camera Vertical Housed Turbines Advisor Information Safety Officer Information Student Team Leader Information Participants NAR Section Team Structure Team Advisor and Mentor Team Supplier Team Consultants Team Outreach Facilities and Equipment Propulsion Labratory D Printer Computer Software Sakai SHARELaTeX OpenRocket SolidWorks LabVIEW ANSYS MATLAB Fabrication Shop Meeting WebEx Requirements Technical Standards Safety Mission NAR/TRA Personnel Facilities & Equipment Handling of Hazardous Materials University, State, & Local Laws & Regulations Student Briefings on Hazard Recognition & Accident Avoidance Mission Statement Mission Motivation Mission Requirements Vehicle Requirements

3 4.2.2 Recovery System Requirements Technical Design Rocket Schematic Payload Elements Hazard Detection System Vertical Housed Turbines Challenges & Solutions Project Plan Gantt Chart Budget Plan Outreach Budget Budget for Trips to Samson, Alabama Huntsville Budget Plan Total Project Cost Funding Plan Sustainability Plan Engaging Successive Classmen Performing Outreach Establishing Partnerships, Funding Educational Outreach Purpose Community Engagement Campus Outreach A Appendix: Safety Code 36 B Appendix: Technical Standards 39 3

4 List of Figures 1 The Aerospace Propulsion Lab in Shelby Hall The 3-D printer in the Aerospace Propulsion Lab Screenshot of the USA Launch Society Sakai page Screenshot of an example SHARELaTeX report Screenshot of rocket template from OpenRocket Screenshot of cylinder created in SolidWorks Sample of the dataflow visual programming language LabVIEW Schematic of proposed rocket design Simulation results from OpenRocket of the proposed design ANSYS model of proposed rocket PiCam used for hazard detection, compared to the size of a quarter [1] Example of miniature turbine compared to a coin Gantt chart displaying timeline for general project component completion dates Table provided by NAR showing the Minimum Personnel Distance for different motor types Technical standards from Architectural and Transportation Barriers Compliance Board Electronic and Information Technology Accessibility Standards Subpart B-Technical Standards List of Tables 1 Rocket structure budgeting Recovery components budgeting Altimeter bay budgeting Certification budgeting Outreach budgeting Budget for traveling to Samson, AL Budget for trip to Huntsville, AL Total project budgeting Event and submission schedule

5 1 General Information Decision of the group has concluded that this project will be named Montalvos Minion, in recognition of the primary advisor Dr. Carlos Montalvo. In addition to the name of the project, the rocket will carry the same name. 1.1 University Mailing Address University of South Alabama Shelby Hall Room Jaguar Drive Mobile, Alabama Phone: (251) Fax: (251) List of Payloads Landing Hazard Detection Camera Camera using Selective Laser Sintering (SLS) technology that is able to scan the ground during descent for landing hazards and relay data to the ground in real time Vertical Housed Turbines Interior turbines that will use air to generate rotation. This rotation will be used to produce a current, which, in turn, will power the drogue parachute deployment at apogee. 1.3 Advisor Information Several faculty members will be involved with Team South Alabama; however, the primary advisors information has been listed below. Dr. Carlos Montalvo cmontalvo@southalabama.edu 5

6 1.4 Safety Officer Information Nghia Huynh 1.5 Student Team Leader Information Andrew Tindell 1.6 Participants Team South Alabama currently consists of 8 team members - comprised of 5 students, 1 high school intern, 1 faculty advisor, and 1 team mentor. More students are expected to join, possibly totaling an overall approximate capacity of 15 members. 1.7 NAR Section Team South Alabama currently is associating with National Association of Rocketry (NAR) section number 572. The team will receive launch assistance from the section advisor John Hansel, who is also the team s mentor. 1.8 Team Structure Team Member Title Role Department 1 Andrew Tindell President Team Lead Mechanical 2 Nghia Huynh Vice President Safety Officer Mechanical 3 Kent Lino Secretary Mathematical Model Lead Mechanical 4 Conner Denton Treasurer Payload Design Lead Mechanical 5 John Faulk Web Master Payload Analyst Mechanical 6 Kayla Bell Intern Recovery Officer High School Senior 7 Dr. Carlos Montalvo Professor Faculty Advisor Mechanical 8 Mr. John Hansel Team Mentor Team Mentor 6

7 1.9 Team Advisor and Mentor Dr. Carlos Montalvo is the primary advisor for Team South Alabama. He is an assistant professor in mechanical engineering at the University of South Alabama. Mr. John Hansel has volunteered to be the team mentor for Team South Alabama. He is a retired electrical engineer from the department of defense, NAR/TRA level 3 certified, and he is also on the NAR Level 3 Certification Committee (L3CC). He has been flying model rockets for over 15 years Team Supplier Mr. Chris Short is the team supplier and is both a NAR and TRA member. He is also on the level 3 certification committee for the South East Alabama Rocketry Society Team Consultants Dr. Joseph Richardson is an assistant professor in mechanical engineering at the University of South Alabama. He is a consultant for the team members in the development of the mathematical model. Dr. Edmund Spencer is an assistant professor in electrical engineering at the University of South Alabama. He is a consultant for the team members in the development of the research payload Team Outreach Team South Alabama works closely with Kelly Jackson to attend and organize outreach events. Kelly Jackson is the educational outreach specialist for The University of South Alabamas College of Engineering. 7

8 2 Facilities and Equipment The University of South Alabama offers sufficient facilities and resources to help Team South Alabama. 2.1 Propulsion Labratory The team has access to the propulsion laboratory, shown in Figure (1) located at the Shelby Hall College of Engineering at the University of South Alabama. The College of Engineering is open from Monday to Friday from 6:00 am to 10:00 pm and the lab is available for the team to use during the entire time of the project. The laboratory provides access to a large space for design, construction, and assembly of the rocket. Figure 1: The Aerospace Propulsion Lab in Shelby Hall. The propulsion laboratory brings access to a three dimensional fabrication machine (3-D printer) forming acrylonitrile butadiene styrene (ABS) plastic parts for the altimeter bay and other components. It also provides access to safe air HUD, three negative pressure snorkels for space ventilation, eye wash stations, and safety shower. 8

9 2.2 3-D Printer Figure 2: The 3-D printer in the Aerospace Propulsion Lab. The lab also serves as a storage room for the tools, payload, recovery, and manufacture components. The equipment that is available in the lab includes an electronic sander, reciprocating saw, circular saw, electric generator, two tool boxes, cabinets containing electronic components, airframes, parachutes and miscellaneous equipment. 2.3 Computer Software In the university, the team has access to two computer labs with a vast number of programs. Some of the software that Team South Alabama members have access to (and are likely to take advantage of) include: OpenRocket, SolidWorks, LaTeX, MATLAB, LabVIEW, 9

10 ANSYS, and Sakai. The team also has access to the University of South Alabamas Microwave and Antenna lab that houses several embedded system development platforms including Arduino and Atmel programmers.team South Alabama plans to make use of several software packages located both online and in the computer labs at the University of South Alabama. Below, several of these packages are listed along with how the team will take advantage of their capabilities Sakai Figure 3: Screenshot of the USA Launch Society Sakai page. The University of South Alabama provides an online web package called Sakai, shown in Figure (3). While Sakai is primarily used by instructors to host online/web-assisted courses, it can also be used as an excellent document-sharing and contact interface. Team South Alabama uses Sakai primarily for its excellent mass- ing capabilities, and for private document sharing. This software is only available to students at the University of South Alabama SHARELaTeX To generate the milestone documents, the team has opted to use LaTeX, a completely free software which is capable of producing extremely elegant and professional documents. Pro- 10

11 ducing a single document written by multiple team members can be a daunting task which requires quite a bit of communication and coordination. Thankfully there exists an online software called SHARELaTeX ( Figure (4) shows the sharelatex.com interface. Figure 4: Screenshot of an example SHARELaTeX report. SHARELaTeX allows for the simultaneous editing of a single document by multiple team members. This program is essentially a LaTeX version of the popular GOOGLE DOCS online software. The advantages that this software offers are both vast and obvious. The document producing process speeds up considerably when multiple members have access to the document at once. This essentially removes the compiling process and also offers instant gratification for the proofreaders. Included on this program is a chat-box feature that reduces the possibility of miscommunication between team members. Essentially, SHARELaTeX increases the accessibility of the team documents and provides immediate insight for each team members on the progress of the rest of the team. This program is readily accessible from any computer with access to the internet. Hence, the team members can interact with each other from different locations. 11

12 2.3.3 OpenRocket Figure 5: Screenshot of rocket template from OpenRocket. OpenRocket, shown in Figure(5), is a software program that provides simulations of model rockets. This program can be used to both design the rocket and determine various values and parameters which are relevant to determining the rocket s behavior. Team South Alabama primarily plans to use OpenRocket to determine the location of the rocket s center of pressure. In addition, the mathematical model that Team South Alabama is developing will be compared against the results of OpenRocket. This program can be downloaded from but it is available on campus computers in the engineering computer labs. 12

13 2.3.4 SolidWorks Figure 6: Screenshot of cylinder created in SolidWorks. SolidWorks, shown in Figure (6), is a 3-dimensionsal CAD program that Team South Alabama will use to model various components and assemblies relative to the rocket. Despite being a CAD program, SolidWorks also offers the use of computational fluid dynamics (CFD) and finite element analysis (FEA) packages. Presently, Team South Alabama plans to (primarily) use ANSYS for FEA calculations, but using SolidWorks to perform this type of analysis remains a possibility. Additionally, SolidWorks is the primary CAD program used in the mechanical engineering program at the University of South Alabama. 13

14 2.3.5 LabVIEW Figure 7: Sample of the dataflow visual programming language LabVIEW. LabVIEW, shown in Figure (7), is a graphical control environment built for engineering and science that is designed to simulate signal processing, control communications, and electronics. LabVIEW will be used to assist the design of the payload ANSYS ANSYS is a computer-aided engineering software (CAE) which specializes in performing FEA on CAD drawn geometries. Team South Alabama plans to primarily use this software to determine the rocket s stiffness matrix, which can then be used to determine the rockets natural frequencies. ANSYS is an FEA package, but it can be used to perform other types of analysis as well. Additionally, ANSYS is the primary software used for mechanical design and stress analysis in the University of South Alabama s Mechanical Engineering Department MATLAB MATLAB is a computational software used for writing/running iterative code. MATLAB is the main software used by the University of South Alabamas Mechanical Engineering Department for developing numerical solutions to various engineering problems. Team South Alabama plans to combine numerical solution techniques with the calculation power of MAT- LAB in order to generate a solution for differential equations relating to the mathematical 14

15 model. Additionally, MATLAB s random number generator(s) will be used to model wind velocity. 2.4 Fabrication Shop In addition to the above facilities, Shelby Hall also has a fabrication shop with various tools such as generators, table saws, sanding equipment and other general tools. Mr. Terry Pritchett and Mr. John Lyons are the engineering technicians that run the fabrication shop. Team South Alabama can take advantage of their resources and expertise if necessary. 2.5 Meeting WebEx Requirements A few points below have been verified in order for Team South Alabama to meet all necessary WebEx requirements listed in the NASA call for proposal: Team South Alabama members each have personal computers with the Windows operating system. Additionally, the University of South Alabama has an extremely reliable wireless broadband internet connection available at all times. The College of Engineering Dean s office has a webcam and speakerphone available to Team South Alabama that the team can use for WebEx video conferences. Team South Alabama has access to multiple teleconference phones, located throughout Shelby Hall. A (registered) WebEx account such that their name and contact information is readily available. Additionally, the team will have a trial run with the software in order to increase familiarity; this will reduce the risk of connectivity issues. Stan Cotton is the Engineering Technician for the College of Engineering, and will provide assistance if technical issues arise. An additional note: Team South Alabama will not have to purchase its own WebEx seat. 15

16 2.6 Technical Standards Team South Alabama will implement the Architectural and Transportation Barriers Compliance Board Electronic and Information Technology (EIT) Accessibility standards (36 CFR Part 1194). These standards will be read by every member of the team and are included in Appendix B. 3 Safety 3.1 Mission The University of South Alabama Launch Society holds safety at the highest priority in building and launching rockets. With this notion, taking the proper safety protocols is essential for each launch to be successful. This safety process must be enforced at all times and places when handling such materials. Tripoli Rocketry Association (TRA) memberships will be earned by the team members [2]. Also, all rocket operations will be supervised by a professional mentor or one with proper certifications. John Hansel and Chris Short will be deemed our launch teams mentor and supplier, respectively. Both of whom are TRA, National Association of Rocketry (NAR), and Southeast Alabama Rocketry Society (SEARS) certified [3]. Our mission is to be able to influence rising underclassmen in the field of rocketry and aerodynamic studies while providing hands-on experience and application. 3.2 NAR/TRA Personnel Along with the teams mentor and supplier, the TRA certified student team member and safety officer, Nghia Huynh, will be responsible in leading the necessary safety protocols in launch operations and motor handling. Nghia will also be responsible for keeping inventory on all chemicals, have all necessary data sheets, keep the team updated on any potentially dangerous situations, perform inspections on the rocket components, and to make and follow checklists for pre and post flight of the rocket. The team will abide by any of the safety officer s rules, guidelines, or checklists. The team shall comply with the NAR high power safety code requirements as well [3]. More specifically, Nghia will be in charge of handling the 16

17 rocket motors and energetic devices.this handling will include the purchase, transportation, storage, and usage of these motors and devices. 3.3 Facilities & Equipment The storage location of hazardous materials will be kept in an appropriate Flammable and Combustible Storage Cabinet. This cabinet will be equipped with separate locks and keys and will only be able to be opened with the presence of the TRA certified personnel. All black powder charges, motors, igniters will be stored in a flammable and combustible safety cabinet outside the university campus. This cabinet will be locked at all times with separate keys and will only be accessed by the safety officer [4]. The specific location of the safety cabinet is at the residence of the TRA certified team member, Nghia Huynh. 3.4 Handling of Hazardous Materials All materials and chemicals will be documented as they enter or exit the Aerospace Propulsion Laboratory. The safety officer, Nghia, will input this data as each transaction happens; otherwise, any member handling certain chemicals will be required to keep the inventory of these chemicals. The Launch Society will be able to access the material data sheets (MSDS) of each chemical that is located within the laboratory. In handling of these chemicals, the proper Personal Protective Equipment (PPE) shall be used. The team members will also adhere to the University laboratory safety guidelines for proper clothing, eye protection, and skin protection. 3.5 University, State, & Local Laws & Regulations The University of South Alabama Launch Society will obey all rules, regulations, and laws set forth by the University of South Alabama, city of Mobile, state of Alabama, federal government, and any states encountered during travel. It should also be noted that the team will abide by all laws relating to airspace, Federal Aviation Regulations 14 CFR, Subchapter F, Part 101, Subpart C; Amateur Rockets, Code of Federal Regulation 27 Part 55: Commerce in Explosives; and fire prevention, handling and use of low-explosives, and 17

18 Tripoli guidelines which follow NFPA 1127 Code for High Power Rocket Motors. The Range Safety Officer (RSO) will ultimately decide if the rocket is prepared for flight in which the team will comply with. He will also approve the target altitude of the team with a review panel by the time the Preliminary Design Review is submitted. His decisions and instructions will be respectfully followed. All FAA waiver requirements will be met in accordance with the time schedule. 3.6 Student Briefings on Hazard Recognition & Accident Avoidance The safety officer, Nghia, must keep everyone informed of any hazards they may face during the construction, testing, and launch of the team rocket. At each meeting, time will be devoted to discussing chemical safety of any new chemicals that may have arrived since the last meeting. Questions and concerns will also be observed. On testing and launch days, checklists will be designated to groups of two members each. From those groups, one member will read the checklist as the other performs the task. Once all tasks are completed, the safety officer then reviews the checklists with the groups, and then the team as a whole. When everything has been completed, only then will the rocket be prepared for a safe launch. Dividing the checklist amongst the group helps to ensure that the team achieves the Federal Aviation Administration s (FAA) requirement that the rocket can be prepared to fly within two hours of their waiver opening and stay set for launch for a minimum of one hour. Post flight checklists will also be implemented as well, using this same technique. Issuing this factor of safety by repeatedly checking and rechecking will help to reduce the chance of failure. 4 Mission Statement 4.1 Mission Motivation In todays world, there is a large push for vehicles of all kinds to use green technology to power the onboard systems. Rockets are no exception to this technological push. The USA Launch 18

19 Society is developing a system using housed vertical turbines in order to generate a current. The current will be converted from its raw form into potential energy that will power the drogue parachute deployment. By using a system with these capabilities, the rocket can reduce its impact on the environment. Also, with the increased interest in Martian missions, hazard detection has become a pressing issue. As modules descend onto a rugged planet like Mars, hazards create a dangerous situation. Damage to these modules can mean mission failure, depending on the severity. This is an obvious concern for both the lives of the astronauts as well as the economic impact of a failed mission. South Alabama s rocket will have a hazard detection camera on board so that on its descent, questionable structures can be relayed to the users. 4.2 Mission Requirements Vehicle Requirements The payloads shall be carried to an apogee of 5,280 feet above ground level. One barometric altimeter shall be carried to record the official altitude. The launch vehicle shall be recoverable and reusable. A maximum of four independent sections is permissible. The vehicle must be single stage. There will be a two hour time limit for vehicle flight preparation on site. The vehicle must remain in launch-ready configuration for a minimum of one hour on the pad without losing component functionality. A 12 volt direct current firing system will be used to ignite the motor. A commercially available, solid propellant motor must be used in the competition rocket. The maximum total impulse of the launch vehicle is 5,120 N-s (L class). 19

20 The RSO shall approve all pressure vessels on board the vehicle. A subscale model of the full-scale rocket must be successfully launched and recovered before the CDR. The full-scale rocket must be successfully launched and recovered prior to the FFR. Also, the same rocket must be launched on the competition launch day. Each teams maximum budget on the launch pad shall be $7, Recovery System Requirements The launch vehicle shall have deployable recovery devices consisting of a drogue and a main parachute. Before the subscale and full-scale launches, the team shall successfully perform a ground ejection test. A maximum kinetic energy of 75 ft-lb is allowable when the vehicle reaches the ground after its flight. Payload and recovery system electronics shall be separate. Commercially available altimeters must be used on board the rocket. Motor ejection may not be used as primary or secondary deployment. An arming switch that is accessible from the exterior of the rocket must be utilized to arm each altimeter. Each altimeter must have an independent power source. Each arming switch must be able to be locked in the on position. Removable shear pins must be used for the main and drogue parachutes. The vehicle must contain an electronic tracking device. This device also must relay its location to a ground user. 20

21 The recovery system electronics must not be negatively affected by the other electronics on the vehicle. 5 Technical Design 5.1 Rocket Schematic Constructing a fully developed rocket design requires intensive and meticulous preparations. Some aspects of the rocket that needs punctual detail are the required payloads, body structures, materials used, and many more. With the given budget for the team, a cost efficient and effective rocket will then be designed. Along with the budget constraint, time is also a key factor in designing the rockets due to the building and constructing process of each component. Each and every single component is reviewed cautiously before proceeding since one miniscule mistake in one section could potentially be hazardous as a whole for the rocket. Below, in Figure (8), is the basic schematic of the rocket that was designed in OpenRocket for six-degree-of-freedom (6DOF) flight simulation purposes. Figure 8: Schematic of proposed rocket design. In Figure (8), the total mass of the rocket, including payloads, was concluded to be approximately 206 oz. including the motor. OpenRocket also dispenses the values of the approximate apogee, the maximum velocity, and maximum acceleration. As displayed in Figure (8), the length is 90.2 inches or 7.5 ft. in length, with the outer diameter being 4 inches. The inner diameter is inches and will be able to pack a K960 Loki White motor, resulting in the motor mount to be inches. The center of gravity and center of pressure is also displayed in Figure (8), which is measured from the tip of the nose cone. The values 21

22 for the center of gravity and center of pressure are preferably measured from the base of the rocket where the motor lies. Therefore, the values for the center of gravity and pressure are inches and inches, respectively. The rocket material is almost entirely made of cardboard which includes the body and the motor mount. However, the fins will be made of fiberglass. The nosecone used is a thermosetting plastic ogive shape because it illustrates very good drag characteristics for general model rocketry use [5]. The drogue parachute is roughly 18 inches in diameter and the main parachute will be roughly 74 inches in diameter as well. These values are chosen due to the inventory available and past university team experience. To further utilize OpenRocket, a non-linear simulation was conducted in order to observe the behavior of the flight. Figure (9) is the resulting curve from the simulation. Figure 9: Simulation results from OpenRocket of the proposed design. The plot is formatted to display altitude vs. time with three functions being altitude, vertical velocity, and the vertical acceleration. The simulation is done by considering a K960 Loki White motor because it will supplement the sufficient amount of thrust and total impulse in order for the rocket to reach the required altitude of 5,280 ft. Due to the experience of the team, the Loki Research motors are preferred since the current team has 22

23 experience only in Loki motors. Even so, they are cost efficient and the supplied kit is reloadable. The PerfectFlite Stratologger altimeter is responsible for the deployment of the stages of the rocket, which the Arduino/Raspberry Pi will be responsible for the electronics used in the payload. The deployment will be using a black powder charge provided at the launch site. 5.2 Payload Elements When deciding on a payload, careful consideration and research took place. There were up to eight different options available upon selection, but was then narrowed down to two specific payloads. The considerations that accounted for the finalized selection included limitations of money available, degree of difficulty, and the usefulness beyond launching the rocket itself. Figure (10) shows the proposed rocket design in ANSYS. The payloads will be within the rocket body. The Vertical Housed Turbines will be housed in the chamber displayed in Figure (10). Figure 10: ANSYS model of proposed rocket. 23

24 5.2.1 Hazard Detection System At the nosecone, there will be a PiCam attached to be able to detect the surroundings through SLS technology as it is descending throughout the atmosphere. The camera will be able to scan the surface of the Earth continuously during descent in order to detect potential landing hazards. A PiCam is an ultra-thin high performance monolithic camera array, that captures light fields and synthesizes high resolution images along with a range image through integrated parallax detection [1]. In order for the PiCam to detect the surroundings, a Raspberry Pi will be programmed through Python so the PiCam will function correctly. Of course, these two parts must be connected to one another in order for succession. The camera board as a whole is equivalent to the size of a quarter, and a high resolution camera equivalent to the quality of an iphone 5 camera. Figure (11) is a representation of the size of the PiCam for visual purposes. Figure 11: PiCam used for hazard detection, compared to the size of a quarter [1]. The PiCam has the aptitude of being able to capture the varying light rays based on the wavelengths of each color. The hazard detection will take place whenever the camera detects a drastic change in color. The detection of light is a relatively narrow spectral sensitivity of each camera. For example, blue is approximately 400 nm to 500 nm, green is 470 nm to 600 nm, and red is 570 nm to 700 nm [1]. As a requirement, the data from the hazard detection camera shall be analyzed in real time by a custom designed on-board software package that shall determine if landing hazards are present [6]. The ground station will then 24

25 collect wirelessly transmitted data and store it on-board for further usage Vertical Housed Turbines Housed in a chamber built along the airframe and enclosing the center of gravity, multiple air turbines will be installed. Wind will be circulated through the chamber vertically due to scoops implemented along the outside walls of the chamber. The chamber will be installed as a transition tube with an approximate diameter of 5 inches. The circulated wind will in turn cause the turbines to spin in order to create a current. By producing a current, a battery will be charged to a desired voltage needed to deploy the drogue parachute. These turbines will serve as independent power sources necessary to supply adequate voltage to deploy the drogue autonomously. The mini turbines are tested in USA s wind tunnel that is located in the Design, Build, Fly laboratory. The wind tunnel will provide live testing to experiment the amount of charge that can be produced by the turbine. Figure 12: Example of miniature turbine compared to a coin. 5.3 Challenges & Solutions The goal of this design is to be able to reach an altitude of 5,280 ft. Being able to reach a specific altitude is a difficult task, so the utilization of simulation models in MATLAB and OpenRocket will be experimented. One challenge is the rocket must be recovered safely. As 25

26 aforementioned previously, safety is the main priority whenever any launch experiments are conducted. The drogue and main parachute deployment systems must be ground tested to ensure their reliability. 6 Project Plan 6.1 Event and Submission Schedule Table 1: Event and submission schedule. August 2015 Event 7 Request for Proposal (RFP) goes out to all teams. September Electronic copy of completed proposal due to project office by 5 P.M. Central Time. 11 Finalize Inventory for SEARS Launch. 12 SEARS Launch in Samson, AL. October Awarded proposals announced. 3 SEARS Launch in Samson, AL. 7 Kickoff and PDR Q&A. 23 Team web presence established. 24 SEARS Launch in Samson, AL. November Preliminary Design Review (PDR) reports, presentation slides, and flysheet posted on the team website by 8:00 A.M. Central Time. 14 SEARS Launch in Samson, AL PDR video teleconferences. December Critical Design Review (CDR) Q&A. 26

27 5 SEARS Launch in Samson, AL. January CDR reports, presentation slides, and flysheet posted on the team website by 8:00 A.M. Central Time. 16 SEARS Launch in Samson, AL CDR video teleconferences. February Flight Readiness Review (FRR) Q&A. 6 SEARS Launch in Samson, AL. 27 SEARS Launch in Samson, AL. March FRR reports, presentation slides, and flysheet posted to team website by 8:00 A.M. Central Time. 19 SEARS Launch in Samson, AL FRR video teleconferencses. April AIAA Student Conference in Starkville, MS. 13 Teams travel to Huntsville, AL. 13 Launch Readiness Reviews (LRR). 14 LRRs and safety briefing. 15 Rocket Fair and Tours of MSFC. 16 Launch Day. 17 Backup Launch Day. 29 Post-Launch Assessment Review (PLAR) posted on the team website by 8:00 A.M. Central Time. May Winning team announced. 27

28 6.2 Gantt Chart Figure 13: Gantt chart displaying timeline for general project component completion dates. 6.3 Budget Plan The budget for the success of the project is divided in five major areas: the structure of the rocket, recovery system, altimeter bay, payload, and certifications launches. Team South Alabama does not plan to merely complete the rocket project. Team South Alabama plans to exceed all expectations and do what is necessary to win the competition. A budget is necessary to ensure unnecessary spending is avoided. 28

29 Table 2: Rocket structure budgeting. Rocket Structure Price Reasoning Airframe $120 The team is budgeting $120 for the airframe including the nose cone. Fins $40 $40 will be budgeted for the construction of the fins. Motor Set $70 Complete motor - includes one casing, one nozzle, one forward bulkhead, two snap rings, and one nozzle washer. Center Rings $100 $100 will be used for the center rings. Miscellaneous $100 The team is adding $100 for miscellaneous items possibly needed for the airframe. Subtotal $530 $530 is the total cost of the airframe.this budget is currently tentative with respect to the material down selection which will be presented in the PDR. Table 3: Recovery components budgeting. Recovery Components Price Reasoning E-matches $80 There will be a set $80 budget for e-matches. Cable Cutters $80 Used for dual deployment purposes from teh same bay. Main Parachute $75 The team will manufacture the main parachute with the given budget. Drogue Parachute $25 The team will manufacture the drogue parachute with the given budget. Black Powder $20 There will be a budget of $20 for black powder. Shock Cord $0 No cost due to the team having an ample amount of shock cords from previous launches. Miscellaneous $100 Flexible amount in the event of emergency. Sewing Machine $0 Members of the team possess a sewing machine. Subtotal $380 The projected budget strictly for recovery components. 29

30 Table 4: Altimeter bay budgeting. Altimeter Bay Price Reasoning Altimeter $0 The team will have access to MiniAlt/WD, Stratologger, Telemetrum, and Jolly Logic altimeters. Shear Pins $0 Both 2-56 and 4-40 shear pins are available in the Aerospace Propulsion Lab. Misc. Components $100 Extra parts and supplies such as switches, screws, bolts, batteries, glue, etc. E-match Material $100 Includes prefabricated wires or wires and ignition. Bay Casing $70 The team may build the altimeter bay from scratch. However, LOC/precision is being considered being that it is available in different diameter tubing. Ejection Charge $130 Ejection charging material needed to separate the sections of the rocket includes black powder, pyrodex, and CO 2 kits. Subtotal $400 The subtotal describes the range of price for the components and parts for the altimeter bay to be between $300-$500. Table 5: Certification budgeting. Certifications Price Reasoning Certification Kits (x2) $200 The team will budget $200 for certification kits to be flown September. Certification Motors (x2) $160 The team is budgeting $160 for certification motors. Subtotal $360 The total cost of the certification is $ Outreach Budget The team recognizes the involvement of young students as a fundamental part of the project. For this reason, the team is working together with Kelly Jackson to participate in events that can motivate students to study mathematics and science. Therefore, the team has prepared a budget to participate in this activities. The budget is illustrated below. 30

31 Table 6: Outreach budgeting. Outreach Price Reasoning Model Parachutes (x10) $75 The team is budgeting $75 that is divided into 4 yards of nylon and lines for the parachutes. Straws $10 $10 is budgeted to buy regular straws for a pressure rocket system. Gas per Visit (x7) $100 $100 is designated for gas to attend the outreach activities. Rocket Motors (x10) $200 $200 is budgeted for the mini rockets that will be launched at schools. Subtotal $385 The subtotal cost for the the outreach activities is $ Budget for Trips to Samson, Alabama The budget for the trips to Samson, AL is fundamental for both testing and evaluation of the rocket. The trips are going to allow the team to launch the rockets with the payload and perform the test for the entire time of the project. The budget overview relative to this is provided below: Table 7: Budget for traveling to Samson, AL. Travel to Samson, AL Price Reasoning Samson, AL (Driving x10) $900 The team is projected to attend a potential of 10 available launches. One will be held once every 3 weeks starting September 12, Subtotal $900 Total for transportation to launches in Samson, AL. 31

32 6.6 Huntsville Budget Plan In the following table, the team presents a budget plan to travel to Huntsville, AL. The team will drive approximately 5 hours to Huntsville, AL and stopping one time per trip. Hotel expenses are also budgeted for staying in Huntsville, AL for 3 to 4 days. Table 8: Budget for trip to Huntsville, AL. Travel to Huntsville, AL Price Reasoning Driving (3 cars) $405 In order to budget for the trip to Huntsville, AL, there will be 3 vehicles taken. It will be an estimate of $90 per car for round trip, and an additional $45 for travel within the city. Food (x5) $300 $300 is budgeted for the teams food expenses. Hotel (3 nights) $700 The team is budgeting $700 for hotel expenses for approximately 8 people. Subtotal $1405 The total for travel cost to Huntsville, AL considering all the gas, food, and lodging prices. 6.7 Total Project Cost Table 9: Total project budgeting. Total Project Cost Price Rocket Structure $530 Payload $800 Recovery Components $380 Altimeter Bay $400 Certifications $360 Outreach $385 Travel to Samson, AL $900 Travel to Huntsville, AL $1405 Total Project Cost $ Funding Plan The funding plan is fundamental for the success of the project. For this reason, the team has requested funding from three major areas. These areas are Student Government Associ- 32

33 ation, Alabama Space Grant Consortium (ASGC), and local companies in the area. Student Government Association will provide $2000 for the project, plus $1000 for travel. In addition, the team will apply for the Alabama Space Grant Consortium (Outreach Programs) to obtain $5000 to provide conference and seminars that can contribute with the promotion of science for young students in the area. At the same time, the team will contact local companies for sponsorships that can help the project to become a success. 6.9 Sustainability Plan Engaging Successive Classmen In order to drive sustainability of the rocket project, the college of engineering has offered to count significant contributions to the project as a technical elective for underclassmen. For seniors, the project may count as a Capstone Design project. These provide significant incentive for students to get involved with the project. While the project is quite enjoyable, it is a large task to take on. Students would prefer to receive college credits to take on such a task. However, more effort is necessary to ensure that future generations have members. To address this issue, Team South Alabama will plan visits to classes and host presentations of the team s results. It is the teams hope that these underclassmen will be impressed and intrigued by the results of the project. In turn, a few should be inspired and express desire to join the project. Some members of the current generation will likely continue the project next year and guide the new members toward a successful rocket launch Performing Outreach Additionally, the outreach performed by the team plays a significant role in the success and sustainability of the project. The more classrooms that Team South Alabama visits, the more support the team and project gain from the local community. Moreover, Team South Alabama is paced to set the bar for having the most successful outreach that has ever been achieved by the rocket team at USA. With the assistance of Kelly Jackson and local organizations the team is able to reach out to many young children, with a heavy focus 33

34 on at-risk schools in the local area. It is the team s hope that Kelly Jackson will be able to recruit a number of at-risk students from these high schools and steer them toward a successful path in life Establishing Partnerships, Funding Presently, Team South Alabama is in the process of generating proposals to local companies such as Airbus, Continental Motors, Inc., and Hargrove. It is the teams hope to obtain some sort of funding/sponsor relationship with each of these companies. These companies are particularly fond of local community support, which the team has been offering with numerous off-campus outreach activities. The team feels that the community involvement will give an edge in obtaining these sponsorships - which will assist in various funding for the current and future generations of this team. 7 Educational Outreach 7.1 Purpose Our goal, as actively involved members of our surrounding community, is to share our knowledge, interests, and experience to the collective body of the Gulf Coast and South regional area. With the expansion of intellectual knowledge as our motivation, we seek to engage middle school through high school students in learning to promote higher education in the fields of arts and sciences. To correspond with USLI competition, our outreach events will focus on the various aspects of rocket science, including its history and technological detail, to enhance the minds of younger intellectuals. 7.2 Community Engagement The USA Rocket Team organizes highly successful outreach events with regional middle schools and high schools. Our team participates in traveling to each officer s respective middle and high school at least once a month to conduct hands-on rocket launches with Class A motors to promote interests in rocketry among the youth. This activity will assist 34

35 in teaching younger students the basics of projectile motion and how rocket propulsion works. Our team also sets up presentations and workshops to engage younger students in learning the mathematics and science that goes into rocket design and simulation, as well as ensure a basic understanding of rocketry history. Another aspect that we include in our presentation is how the technology and innovation that stems from rocketry has positively affected our everyday lives, such as advancing our telecommunication, provide prototypical concepts to NASA for larger scale rocket missions, and future research purposes. We also actively participate in having high school interns involved in every aspect of the USA Rocket Team activities. 7.3 Campus Outreach The USA Rocket Team stems from the USA Launch Society, which is active throughout educational engagement programs and events. Our focus is on expanding undergraduate student groups with interests in aerospace and space-related fields. Particular events that the USA Launch Society participates in are as follows: Freshman Orientation, Get on Board Day, Welcome to The Jungle, and Tailgating. To promote each of these events, posters and flyers are distributed throughout the campus and information is posted on student websites. For each event, presentations, hands-on activities, and discussions are held to spark an interest in undergraduate students in rocket science and design. Another particular event that we will be promoting is a movie night featuring October Sky on a yet to be determined date in October. We believe that this event will assist in providing a basic understanding of rocketry, as well as motivate students to become more involved with the USA Launch Society. The USA Rocket Team also promotes educational engagement by having an Open Lab Policy four hours per week, where undergraduate and graduate students are welcome to participate in activities involving rocket design, simulation, and discussion. 35

36 A Appendix: Safety Code 1. 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. 2. 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. 3. 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, nor heat sources within 25 feet of these motors. 4. 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. 5. Misfires. If my rocket does not launch when I press the button of my electrical launch system, I will remove the launchers safety interlock or disconnect its battery, and will wait 60 seconds after the last launch attempt before allowing anyone to approach the rocket. 6. 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 36

37 launch of more than one high power rocket I will observe the additional requirements of NFPA Launcher. I will launch my rocket from a stable device that provides rigid guidance until the rocket has attained a speed that ensures a stable flight, and that is pointed to within 20 degrees of vertical. If the wind speed exceeds 5 miles per hour I will use a launcher length that permits the rocket to attain a safe velocity before separation from the launcher. I will use a blast deflector to prevent the motors exhaust from hitting the ground. I will ensure that dry grass is cleared around each launch pad in accordance with the accompanying Minimum Distance table, and will increase this distance by a factor of 1.5 and clear that area of all combustible material if the rocket motor being launched uses titanium sponge in the propellant. 8. Size. My rocket will not contain any combination of motors that total more than 40,960 N-sec (9208 pound-seconds) of total impulse. My rocket will not weigh more at liftoff than one-third of the certified average thrust of the high power rocket motor(s) intended to be ignited at launch. 9. 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. 10. 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 37

38 than 610 meters (2000 feet). 11. 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. 12. 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. 13. 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. Figure 14: Table provided by NAR showing the Minimum Personnel Distance for different motor types. 38

39 B Appendix: Technical Standards 39

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