Rocket Based Deployable Data Network

Transcription

1 Rocket Based Deployable Data Network University of New Hampshire Rocket Cats USLI Proposal Submission Deadline: August 31, 2012

2 Contents 1 General Information School Information Adult Educators Safety Officer Team Leader Team Organization Local NAR Resources Facilities Workspace Computer Equipment EIT Accessibility Standards Safety Safety Plan General Safety Practices Construction Launch Operations Flight Materials NAR Personnel Procedures Hazard Briefing Caution Statements Regulation Compliance Motor Logistics Safety Regulation Adherence Technical Design Vehicle Design Recovery Motor Selection Payload Requirements Vehicle Recovery Payload Technical Challenges i

3 5 Educational Engagement 13 6 Project Plan Time line Budget Plan Vehicle Components Payload Funding Plan Programmatic Challenges Sustainability Appendix Safety Agreement NAR High Power Rocket Safety Code Materials Safety Data Sheets ii

4 1 General Information 1.1 School Information School Name: Team Name: Project Title: Team Educator: Team Leader: Safety Officer: NAR Mentor: NAR Section: Mailing Address: University of New Hampshire UNH Rocket Cats Rocket Based Deployable Data Network Dr. May-Win Thein Dr. Marc Lessard Collin Amy Robert DeHate Maine Missile Math & Science Club 33 Academic Way Durham, NH Adult Educators Dr. May-Win Thein Dr. Thein will be the faculty adviser for the project. Dr. Thein is a UNH professor in the mechanical engineering department. Her field of specialization is in the area of System Dynamics and Control. Dr. Thein is an adviser for the NASA Lunabots competition team and has been a primary investigator on several NASA sponsored projects. Dr. Marc Lessard marc.lessard@unh.edu Dr. Lessard will be the technical adviser for the project. Dr. Lessard is a UNH professor in the physics department and worked as an engineer on 12+ rocket missions and then worked as Principal Investigator or Co-Investigator on another 8 or so missions. His most recent launch was this past winter. 1.3 Safety Officer Amy (alm548@wildcats.unh.edu) will be the appointed safety officer for the UNH Rocket Cats project team. Amy is a senior mechanical engineering student also working towards an applied mathematics minor, expecting to graduate in She is a member of Air Force ROTC and is currently serving as Wing Commander at her detachment. When she graduates, she wants to serve as an engineer in the Air Force. 1.4 Team Leader Collin (caq83@unh.edu) will be the leader of the UNH Rocket Cats project team. As team leader Collin will handle team management, project direction and assist with all aspects of the design and construction. Collin is pursuing a mechanical engineering degree with expected graduation in He obtained his NAR Level 1 certification at the Advanced Rocketry Workshop and currently pursuing Level 2 certification. Collin is actively involved in the open source 3D printing community and is interested in pursuing future research in space based additive manufacturing. 1

5 1.5 Team Organization Due to the timing of the proposal deadline relative to the start of the academic school year, a complete team roster has not yet been determined. The team will have, at minimum, 6 engineering members with room in the organization for additional members. The team will also seek the involvement of students in the from the electrical engineering, computer science and other university departments. The UNH Rocket Cats project will be used by some of these students as their capstone or senior project. In order to efficiently achieve the project objectives the team is divide into smaller student groups. The team leader and safety officer will preside over all of these groups to ensure that team objectives are being met and safety procedures are being adhered to. The four team groups are: payload, vehicle, operations and public relations. This team structure is presented as an organizational flow chart in Figure 1. The team organization provides a central focus for different group members but involvement in all realms is encouraged. Figure 1: UNH Rocket Cats team organization flow chart. Payload Team The payload team is responsible for the design and construction of the vehicle payload. The team will have at least three student members. In order to achieve proper integration and function with the vehicle, this team will work closely with the vehicle team. Given the heavy electronics base of the payload, this team will have the greatest contingent of electrical engineering and physics students. Vehicle Team Joe (jam254@wildcats.unh.edu) will be the leader of the Vehicle Team. Joe is a senior mechanical engineering major, expecting to graduate in He is currently pursuing his NAR level 1 certification, and is interested in engineering design and manufacturing. The vehicle team is responsible for the design and construction of the launch vehicle used for the competition. This team will also have at least three student members. Avionics, recovery and structures are included in this team s responsibility. In order to ensure mission success, this team will work with operations and payload to establish design criteria. 2

6 Operations Team The operations team will handle development of ground support and telemetry software. Depending on launch rail availability at the team launch site, this team will also be responsible for the development of a launch platform. In addition to development tasks, this team is also responsible for handling logistics of launch event scheduling and launch procedures. This team will have at least two members. Public Relations Team The public relations team is responsible for organizing all communication with the public. This includes fund raising, website development, educational outreach and procurement. For the fund raising and outreach tasks, this team will provide an organizational structure but it will be the responsibility of all project members to engage in these activities. This team will have at least two members. The UNH Rocket Cats will encourage the involvement education, business and communication majors for this portion of the team. 1.6 Local NAR Resources NAR Club The UNH Rocket Cats will be associating with the Maine Missile Math and Science Club (MMMSC). This NAR chapter has launch facilities located 30 minutes from the University campus and provides year round launch events every other weekend with a 10,000 FAA waiver. Due to lack of availability in finding a club mentor with the necessary requirements from the MMMSC, the team will also associate with the Central Massachusetts Spacemodeling Society (CMASS). NAR Mentor Robert DeHate has agreed to be the mentor for the UNH Rocket Cats. Robert is NAR Level 3 certified and the owner of Animal Motor Works. Mr. DeHate will provide assistance with report and design reviews, motor procurement and launch logistics. He has served in the mentor capacity for a number of previous USLI teams. 2 Facilities 2.1 Workspace Project Room The team will be provided with two student project rooms located in the Kingsbury Hall Engineering Building. These workspaces will available to team members 24 hours a day, every day of the week. One project room will be for electrical and computer science tasks and the other will be for vehicle and construction tasks. The workspace will provide work surfaces, storage lockers and computers for team use. Weekly meetings, construction, assembly and organization will all occur in this room. 3

7 Support Facilities In addition the the project space the team will also have access to the following facilities: Two on campus machine shops which include cutting, milling, turning and welding abilities. Electrical engineering labs for soldering, signal measurement and PCB etching. Full time access to a RepRap 3D printer and part time access to a Stratasys 3D printer. Small scale wind tunnel with a 4 x 4 x 8 test section. Access to clean room facilities. 2.2 Computer Equipment Students have 24-7 access to computer equipment in the project workspace as well as in the mechanical engineering student computing cluster. These computers will have all software necessary to perform work on the project. Each computer will be equipped with the following: High Speed Internet Access Windows 7 Professional MATLAB/Simulink SolidWorks 2011 MathCAD Microsoft Office 2010 L Y X/L A T E X RockSim and WinRocket Marc FEA Software For teleconferencing the team will utilize the Mechanical Engineering Conference Room. This room has speakerphone and web cam functionality with an internet enabled Windows computer as well as space to seat the entire team. The website will be hosted using the UNH Pubpages hosting service. This service is provided free to all students. A private domain will be purchased for a more professional web presence. 2.3 EIT Accessibility Standards The team has read and will implement the Architectural and Transportation Barriers Compliance Board Electronic Information Technology Accessibility Standards in all aspects of computing use and development pursuant to standards , and

8 3 Safety 3.1 Safety Plan Safety, in all aspects of the USLI competition, is of utmost concern for the UNH Rocket Cats. In order to reduce potential risk, a safety plan has been developed and it will be the responsibility of the appointed safety officer to ensure adherence to this plan. In order to increase range safety and awareness, it is the goal of the team that each member become NAR Level 1 certified by the start of the spring semester. The team will work with the safety officer and the NAR mentor, Robert DeHate (Level 3), to assist with teaching construction and range safety through this process General Safety Practices 1. All design changes and decisions will be reviewed by the safety officer to ensure that they can be executed safely and in accordance with the safety plan. 2. When on UNH property the safety officer has the authority to supersede any decision if deemed unsafe. 3. When at the range, the safety officer is responsible for ensuring that the range procedure and safety plan are carried out. The team NAR mentor will supersede the safety officer in any safety decisions. The Range Safety Officer shall have ultimate authority over team procedure and rocket safety. 4. Use of personal protective equipment (PPE) and any other safety is required in all necessary situations. 5. Institution rules, state, local and federal laws must be adhered to at all times. 6. Tool use must never occur alone Construction The following table explains the risks foreseen in the construction of the rocket as well as the steps to mitigate this risk. Risk Cuts, burns, general injury Mitigation Steps PPE must be worn at all times Ensure knowledge of tool operation Never operate tools alone Equipment Damage Ensure knowledge of tool operation Never operate tools alone Verify new processes with safety officer Launch Operations The following table details potential risks and mitigation steps for all aspects of range operations. The team will work closely with the NAR mentor and Range Safety Officer (RSO) to ensure that all range operations occur safely. 5

9 Risk Accidental or Premature Motor Discharge Blast Induced Fire Igniter Failure Unstable Launch Rail Exit Mitigation Steps All motor handling is carried out by NAR mentor Motor is not loaded until necessary Verification that launch support hardware is off when connecting igniter A suitably large blast deflector will be used All dry grass and potentially flammable items removed from the blast radius Fire suppression equipment will be located near the launch site Ensure igniter is properly inserted Wait at least 60 seconds or until RSO all clear to approach rocket Ensure a motor with sufficient thrust curve is selected Ensure launch rails of adequate length are used Flight During flight, a number of safety concerns present themselves. These risks are presented in the following table. Risk Explosion Caused by Pressure Buildup Mitigation Steps Ensure that rocket motor is in proper condition before launch Verify that any necessary vent holes are clear Maintain a safe distance during launch Recovery Deployment Failure (Charge failure, separation failure, parachute deployment failure) Test recovery system multiple times prior to launch Verify avionics function using test lamps on launch day Use redundant separation charges Verify that the parachute is packed and protected properly Ensure that all harness fixing points are secure Maintain a safe distance during flight Materials While the explosive handling will be left to the NAR mentor, risks associated with these explosives as well as other construction materials are presented in the following table. 6

10 Risk Vapor Inhalation Skin Contact Lifting Injures Eye Contact Mitigation Steps Operate in well ventilated space Wear dust mask or respirator Refer to MSDS for any other necessary vapor related precautions Wear gloves and other necessary safety equipment Maintain an organized work space/system Refer to MSDS for proper handling Always follow proper lifting procedures Use more than one person if necessary Always wear safety glasses and other necessary safety equipment Refer to MSDS for eye related precautions. 3.2 NAR Personnel Procedures NAR personnel will assist the team in a number of project related tasks. Most of this assistance will occur at launches and on the range. The team has the benefit of having its NAR mentor also be a motor vendor. The mentor will assist with the motor handling and also the launching of the rocket so that rockets flown will be in the flier s NAR scope. The mentor will review all technical designs and constructions to verify that the rocket is safe to fly. The team will use the Maine Missile Math & Science Club launch site for all test flights. The NAR personnel (including range safety officer) will be responsible for maintaining that the launch site is safe and to NAR safety code. This includes supplying a launcher with suitable minimum distance requirements met, an ignition system and a launch site. The RSO will provide the launch countdown and verify that the flight complies with the FAA regulations Hazard Briefing Prior to any construction or hazardous material handling operation, the team will be briefed on potential hazards through each step of the operation. All team members will be made familiar with the risk and mitigation charts, material MSDS s, NAR safety code, local and federal law as well as any addition specific safety information. On launch day, the team will be briefed on the agenda for the launch. Launch day risks will be determined and team members will be made familiar with mitigation steps. 3.4 Caution Statements Any plans or documents created to describe a process which is determined to have associated risks will also include a section of risk mitigation and safety information. This information will include relevant MSDS information, tool safety rules as well as necessary personal protective equipment. The safety officer will maintain two binders of all of these safety procedures. One of these binders will always remain in an easily accessible location in the team project room and the other will travel with the team to launch events or off site work. Relevant MSDS information can be found in Section

11 3.5 Regulation Compliance All team members will comply with federal, state and local laws regarding motor handling and rocket launches. To comply with Federal Aviation Regulations 14 CFR, Sub chapter F, Part 101, Sub part C, the team will launch only with appropriate FAA waiver. This waiver will be obtained by the Maine Missile Math & Science Club during their bi-monthly launch events. The team will attend these launch events in order to fly in accordance with this waiver. All motor and explosive handling procedures will be developed for compliance with Federal Regulation 27 Part 55. This will be assisted by the team NAR mentor. Technical design, motor, deployment and launch site will all be chosen to comply with NFPA Motor Logistics The team does not plan to store rocket motors on site at the University of New Hampshire. The team s NAR mentor is a rocket motor vendor who is qualified to transport and sell rocket motors across state lines. The mentor is at the majority of launch events so the motors will be obtained from the mentor at the launch site. The mentor will be traveling to Huntsville, AL for competition, transporting the motors there for the team. The team finds this to be the safest and easiest approach to motor transport, storage and use. 3.7 Safety Regulation Adherence For the USLI launch event, the team will abide by the following regulations. A written agreement is found in Section 7.1 of this document. 1. Range safety inspections of each rocket before it is flown. Each team shall comply with the determination of the safety inspection 2. The range safety officer has the final say on all rocket safety issues. Therefore, the Range Safety officer has the right to deny the launch of any rocket for safety reasons. 3. Any team that does not comply with the safety requirements will not be allowed to launch their rocket. 4 Technical Design 4.1 Vehicle Design In the current design stage the rocket will use 4 diameter fiberglass tubing and be 86 in length. The diameter was chosen because it is a readily available tube size and is the smallest diameter which can fit the desired payload. The length was chosen out of necessity for containing the recovery and payload equipment. Despite the increased weight, fiberglass tubing was chosen for its added durability. Carbon fiber will be considered as budget and design plans evolve. The nose cone will be a commercially available LOC Precision ogive nose cone. This nose cone and brand were chosen for the availability and due to the fact that the team adviser is LOC vendor. As project needs evolve, a custom built nose cone will be considered. GPS tracking of the vehicle will be performed using a GPS receiver and a XBee Pro wireless transmitter. The ZigBee protocol will be used for the payload communication and is a natural choice for the tracking needs to the vehicle. Proposed vehicle dimensions are as follows, a RockSim design is presented in Figure 2. 8

12 Structures Overall Length 86 inches Body Diameter 4 inches Span Diameter inches Mass (unloaded) oz Mass (loaded) oz Stability Margin (unloaded) 3.88 Stability Margin (loaded) 1.97 Figure 2: Proposed vehicle design, generated using RockSim. 4.2 Recovery The recovery system control will be performed by two redundant Adept22 altimeters. These altimeters are chosen for their low cost and team member familiarity. Because the payload will handle altitude logging it was decided that the recovery system altimeters do not need this functionality. Recovery components will be located in the tube coupling the motor and payload rocket sections. To avoid unintentional deployment nylon shear pins will be used to secure sections. FFFF black powder will be activated by a low current electric match to initiate deployment events. During flight, three major recovery events will occur: 1. At apogee, the drogue chute will be deployed with a black powder ejection charge. This deployment will also carry the payload components (2) out of the rocket. The payload components will be tethered to the recovery harness in a ready to release state. In the event of a failure in both altimeter deployment systems, the motor ejection charge will be timed for a deployment at apogee. 9

13 2. When the RSO has given permission to jettison the payload components, these will be released and come down independent via parachute. 3. At 500 ft (AGL) the recovery system will fire an ejection charge to deploy the main parachute. This will slow the rocket for a landing with less than 75 ft-lbf of kinetic energy. 4.3 Motor Selection The criteria for the motor is that it delivers the launch vehicle to 5,280 ft (AGL), is commercially available and has less than 5,120 Newton-seconds of total impulse. The team also imposed the limitation that the rocket be a Cessaroni brand rocket because the team mentor is Cessaroni dealer. Using an iterative approach and RockSim launch simulations, a motor was selected that meets the needs of the team. The currently selected motor is the CTI 1196J745 motor. This motor gives a predicted altitude of 5304 ft. Motor Specification Brand Model Diameter Length Maximum Thrust Average Thrust Cessaroni Technology Incorporated (CTI) 1196J745-P 54mm (2.13in) in N N Project: Thrust File: gra J741 (87.5%J) Thrust (lb.) Thrust (N) Action Time Total Impulse: N.s [ lb.s] Action Time: sec. Action Time Average Thrust= N [ lb.] TE-> Maximum Thrust= N [ lb.] Classification= 87.5%J <-TS Time (Seconds) Wed 28-Oct :30 PM Page 1 of 1 Figure 3: Cessaroni 1196J745 motor thrust curve. 10

14 6000 Apogee Altitude (Feet) Altitude (Feet) 3000 Burnout t Time Figure 4: RockSim flight simulation using 1196J745 motor. 4.4 Payload The payload will accomplish two objectives: to establish a rapidly deployed, low cost web server network and to accomplish the requirements of the NASA Science Mission Directorate (SMD). The purpose of the payload is to deploy a long range data network from a rocket. The motivation behind this payload idea is in situations of internet outage such as disasters or government shut down (a la the Arab Spring). When deployed, the server network would enable communication between multiple servers or ground stations over 2 miles apart by using additional servers as network hops. This network will provide a means for peer-to-peer data sharing as well as remote storage of data and information. For the USLI competition, the UNH Rocket Cats will deploy at least two web servers to demonstrate the feasibility of such a plan. In a situation of true network outage, a larger network could be deployed over a greater range to reach more parties. This network would allow users to share status reports, transmit images and access information loaded on the devices prior to flight. For this network to have significant advantage over satellite communication, it must be quick to deploy, low cost, durable and easily accessed by multiple parties. For the server hardware, a Raspberry Pi computing device will be used. This device is chosen for its small form factor, low cost and 26 general purpose input/output (GPIO) ports. A 4GB SD card will be used for onboard data storage. The communication will be carried out using the ZigBee networking protocol. This protocol is chosen due to the available of supporting hardware such as the XBee Pro modules. This protocol supports mesh and point to point networks and is designed to provide low power and long range communication. The team will collect quality of service information on this network for post flight analysis. In addition to the web server tasks, one server will be designated as an SMD payload. This payload will also contain the sensors necessary to measure pressure, temperature, relative humidity, solar irradiance, ultraviolet radiation and GPS position. Measurements will be made every 5 seconds during descent and 11

15 every 60 seconds after landing. In order to accomplish the image gathering requirements, a video camera will be used to record the entire flight. Using the onboard processing capabilities, this video will be image processed in real time to extract properly oriented frames which will be saved and transmitted. The data gathered by the SMD payload will be saved onboard and also made accessible in a familiar web interface at the ground station using the deployable server network. The combination of the SMD and the web server project will allow the team to fully demonstrate the capabilities and expandability of such a network to accomplish nodal communication and gather scientific data. 4.5 Requirements Vehicle In order to achieve mission success the vehicle must deliver the payload to 5,280 ft (AGL). The rocket must be recovered in a state that it is able to be flown again on the same day. The vehicle must be able to be launch ready within 2 hours from when the FAA waiver opens and be able to remain in this state for at least 1 hours without any loss of functionality Recovery The recovery system of the rocket must deploy a drogue parachute at apogee and also deploy a main parachute at a lower altitude to slow the rocket to a safe kinetic energy (75 ft-lbf). The recovery system must also deploy the payload sections when the RSO gives permission. The recovery system must be designed so that all independent sections land within 2,500 ft. of the launch pad, assuming a 15 mph wind. The recovery system will use commercially available altimeters and low-current electric matches. Using GPS, the recovery system must transmit the location of each independent component to the ground station Payload The success of the deployable server network will rely on the satisfaction of the following criteria: 1. All network elements are activated and communication is enabled. 2. Read/write is enabled for all network elements. 3. The network will function during ascent, descent and for 1 hr after landing. 4. All data to satisfy the SMD will be collected and transmitted to the ground station. This information will also be stored, in duplicate, on the second payload server. 4.6 Technical Challenges The major technical challenge currently foreseen will be the development of a system to deploy the two independent payload elements at RSO permission. These independent devices must deploy from the rocket at an arbitrary altitude after receiving a signal from the ground station. In order to accomplish this task without affecting the dual deployment recovery system a number of different designs have been considered. The design currently being considered is one in which the payload elements remain tethered to the recovery harness and are then detached at the RSO signal. In order to obtain the best performance, a number of different deployment methods will be developed and tested on the ground and in test flights. The current goal of onboard video processing of SMD data will also pose a major technical challenge. While a more simple method for obtaining images may be possible, the team has chosen this method because it 12

16 is a novel approach to the challenge and utilizes the processing power of the Raspberry Pi. To accomplish this task the team will combine previous image processing experience with newly learned knowledge about video parsing. Large amounts of on the ground and in air testing will be used to verify this method. As a first year team, the most general challenge will be the inexperience of team members in the realm of rocketry. To gain more experience each team member will build a level 1 rocket for a certification attempt during the opening weeks of the school year. This project will teach team members more about rocketry and build excitement about the project. In addition, the team leader attended the Advanced Rocketry Workshop to help learn more about the USLI competition and high power rocketry. 5 Educational Engagement In order to encourage educational interest in STEM projects at the middle school level, the UNH Rocket cats will work with local middle schools to provide educational engagement activities. The team will utilize the online NASA educators resources to help create a lesson and engagement plan. The current outreach plan will be to build a small wind tunnel using large cardboard tube, ceiling fan and a scale. The wind tunnel will be used to demonstrate the principles of drag by measuring the drag force of different objects. The students will then build their own rocket prototypes using small cardboard tube and choosing their own length, nosecone and fins. During the activity, the students will develop a hypothesis for the lowest drag rocket. This will be tested and the students will record their data. A questionnaire and feedback form will be filled out by the students so that further outreach may be improved upon. A number of local middle schools have expressed great interest in engaging in such an activity with the team. For further engagement, the team will utilize the ties gained through the strong UNH heritage of local and regional outreach projects. 13

17 6 Project Plan 6.1 Time line Figure 5: Proposed time line for UNH Rocket Cats team to accomplish the objectives of the USLI competition. 6.2 Budget Plan The overall anticipated budget is given in the following table. In order to account for inevitable increases in project costs, a round number of $9,000 is chosen for planning purposes. A more complete cost breakdown is given in the following subsections. Item Cost Structures $1150 Propulsion $470 Payload $1115 Misc. $350 Travel $5000 Outreach $300 Total $

18 6.2.1 Vehicle Components Part Quantity Unit Price($) Cost($) Full Scale Vehicle G10 Fiberglass Tubing Nose Cone Motor Tube Motor Retainer Motor Case Fins Rail Buttons Assorted Hardware, etc Full Scale Total 625 Subscale Vehicle Fiber Tubing Nose Cone Motor Tube Motor Retainer Motor Case Fins Rail Buttons Assorted Hardware Subscale Total 350 Recovery Components Adept22 Altimeter Electric Matches Drogue Chute Main Chute Shock Cord Recovery Total 175 Motors Subscale Motor Full Scale Motor Motors Total

19 6.2.2 Payload Part Quantity Unit Price($) Cost($) Payload Raspberry Pi XBee Pro 60mW Sandisk 4GB SD Card Venus GPS Receiver Power Supply Hardware/case Recovery System Payload Total 525 SMD Components Video Camera Sensors SMD Total 450 Ground Support XBee Pro 60mW XBee USB Interface Antenna Ground Support Total Funding Plan In order to fund the project, the team will look to a number of local business and organizations. The team has already raised over $4,000 in funding for the project. At the university, the team will look to the following organizations for funding support: UNH Mechanical Engineering, Physics, Electrical Engineering and Computer Science Departments UNH Student Activity Fee Committee UNH Parents Association UNH Student Organizations/Clubs New Hampshire Space Grant Consortium In addition to on campus funding resources the team will contact local business for sponsorship. In order to solicit support, the team will create a marketing outreach sheets for team members. In order to create incentive for sponsors the team will display company logos on team media and provide mention in press releases. The team will provide plaques to sponsors for their support. 6.4 Programmatic Challenges Without the work of teams from prior years, the team will have the challenge of making completely new connections to local businesses and organizations. The team will develop and practice meeting strategies. While this is a first year USLI team, UNH has entered in other NASA events. The UNH Rocket Cats will utilize some of the connections and lessons learned from these teams to assist in easing this challenge. 16

20 Being that this is a first time USLI team, there will be a lot to learn about the competition itself. The team leader attended the Advanced Rocketry Workshop. This workshop helped to understand the proposal, report and flight aspects of the competition. The information learned will be shared with the rest of the team members. Given the breadth of the project goals, this project will involve a number of different departments. Many students from these departments will use the project as their senior capstone. In order to ensure success of a cross department capstone instructors for the departments involved have agreed to collaborate. 6.5 Sustainability The UNH Rocket Cats intend to not only compete in the USLI competition but create a framework for future USLI teams. This will be accomplished by making sure to create clear and organized documentation of all parts of the competition process. This documentation will be passed on as hard copies and soft copies located online. The organization will allow future teams to focus on improving on previous designs and not logistical or organizational issues. The team will encourage the involvement of underclassmen students in the engineering program. Students from PHYS 605, who are predominately juniors, may assist in this project as the final project for their class. We will use the same model as other long running UNH engineering teams to provide continuity for Rocket Cats and sustain interest. 7 Appendix 7.1 Safety Agreement As a member of the UNH Rocket Cats USLI team I agree, by signing this document, that I will abide by the safety rules set forth by the team, the NAR, NASA and federal, local and state governments. These rules have been created to ensure that engagement in this project is a safe experience. In my engagement I will abide by all University, local, state and federal laws and regulations. This includes all laws not just those specific to high power rocketry. I have read and understand the NAR High Power Rocket Safety Code and agree to abide by it throughout the project and at launch events. I understand that in all situations the Range Safety Officer has final say over launch proceedings. I understand that my awareness is necessary to ensuring a safe working environment for all team personnel. I will immediately mention any safety concerns to the safety officer or next available team personnel. I will abide by the following safety regulations: 1. Range safety inspections of each rocket before it is flown. Each team shall comply with the determination of the safety inspection 2. The range safety officer has the final say on all rocket safety issues. Therefore, the Range Safety officer has the right to deny the launch of any rocket for safety reasons. 3. Any team that does not comply with the safety requirements will not be allowed to launch their rocket. Signed Date 17

21 7.2 NAR High Power Rocket 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 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. 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 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 motor s 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 than 610 meters (2000 feet). 18

22 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. 7.3 Materials Safety Data Sheets CTI Rocket Motors 19

23 MSDS ProX Rocket Motor Reload Kits Page 1/6 Version 2.02 Revision Date. 8 Feb 2010 ========================================================================= MATERIAL SAFETY DATA SHEET ========================================================================= ProX Rocket Motor Reload Kits & Fuel Grains PRODUCT / COMPANY IDENTIFICATION Product Name: Pro29, Pro38, Pro54, Pro75, and Pro98 Rocket Motor Reload Kits Synonyms: Rocket Motor Proper Shipping Name: Articles, Explosive, N.O.S. (Ammonium Perchlorate) Part Numbers: Reload kits: P29R-Y-#G-XX, P38R-Y-#G-XX, P54R-Y-#G-XX, P29R-Y-#GXL-XX, P38R-Y-#GXL-XX, P54R-Y-#GXL-XX, Propellant grains: P75AC-PG-XX, P98AC-PG-XX, P98AC-MB-PG-XX Where: Y = reload type (A = adjustable delay, C = C-slot) # = number of grains & XX = propellant type Product Use: Solid fuel motor for propelling rockets Manufacturer: Cesaroni Technology Inc. P.O. Box Stouffville Rd. Gormley, Ont. Canada L0H 1G0 Telephone Numbers: Product Information: Hour Emergency Telephone Number: (CANUTEC) COMPOSITION / INFORMATION ON INGREDIENTS Propellant Ingredient Name CAS Number Percentage Ammonium Perchlorate % Metal Powders % Synthetic Rubber % Black Powder Ignition pellet Ingredient Name CAS Number Percentage Potassium Nitrate % Charcoal... n/a 8-18 % Sulphur % Graphite trace HAZARDS IDENTIFICATION Emergency Overview: There articles contain cylinders of ammonium perchlorate composite propellant, encased in inert plastic parts. The forward closure also contains a few grams of black powder. ProX Rocket motor reload kits are classified as explosives, and may cause serious injury, including death if used improperly. All explosives are dangerous and must be handled carefully and used following approved safety procedures under the direction of competent, experienced personnel in accordance with all applicable federal, state and local laws and regulations. Avoid inhaling exhaust products.

24 MSDS ProX Rocket Motor Reload Kits Page 2/6 Version 2.02 Revision Date. 8 Feb 2010 General Appearance: Cardboard tubes contain various plastic parts. Inside the plastic tube are cylinders of composite propellant (rocket fuel). The forward closure also contains a small quantity of black powder. All parts are odourless solids. Potential Health Effects: Eye: Not a likely route of exposure. May cause eye irritation. Skin: Not a likely route of exposure. Low hazard for usual industrial/hobby handling. Ingestion: Not a likely route of exposure. Inhalation: Not a likely route of exposure. May cause respiratory tract irritation. Do not inhale exhaust products. 4.0 FIRST AID MEASURES Eyes: Skin: Immediately flush eyes with plenty of water for at least 15 minutes, occasionally lifting the upper and lower eyelids. Get medical aid. Flush skin with plenty of soap and water for at least 15 minutes while removing contaminated clothing and shoes. Get medical aid if irritation develops or persists. Ingestion: Do NOT induce vomiting. If conscious and alert, rinse mouth and drink 2-4 cupfuls of milk or water. Inhalation: Remove from exposure to fresh air immediately. If not breathing, give artificial respiration. If breathing is difficult, give oxygen. Get medical aid. Burns: Burns can be treated as per normal first aid procedures. 5.0 FIRE FIGHTING MEASURES Extinguishing Media: In case of fire, use water, dry chemical, chemical foam, or alcohol-resistant foam to contain surrounding fire. Exposure Hazards During Fire: Exposure to extreme heat may cause ignition. Combustion Products from Fire: During a fire, irritating and highly toxic gases may be generated by thermal decomposition or combustion. Fire Fighting Procedures: Keep all persons and hazardous materials away. Allow material to burn itself out. As in any fire, wear a selfcontained breathing apparatus in pressure-demand, MSHA/NIOSH (approved or equivalent), and full protective gear. Special Instructions / Notes: These articles burn rapidly and generate a significant flame for a short period of time. Black powder is a deflagrating explosive. It is very sensitive to flame and spark and can also be ignited by friction and impact. When ignited unconfined, it burns with explosive violence and will explode if ignited under even slight confinement. Do not inhale exhaust products. 6.0 ACCIDENTAL RELEASE MEASURES Safeguards (Personnel): Spills: Clean up spills immediately. Replace articles in packaging and boxes and seal securely. Sweep or scoop up using non-sparking tools. 7.0 HANDLING AND STORAGE Handling: Keep away from heat, sparks and flame. Avoid contamination. Do not get in eyes, on skin or on clothing. Do not taste or swallow. Avoid prolonged or repeated contact with skin. Follow manufacturer s instructions for use.

25 MSDS ProX Rocket Motor Reload Kits Page 3/6 Version 2.02 Revision Date. 8 Feb 2010 Storage: Store in a cool, dry place away from sources of heat, spark or flame. Keep in shipping packaging when not in use. 8.0 EXPOSURE CONTROLS / PERSONAL PROTECTION Engineering Controls: Use adequate explosion proof ventilation to keep airborne concentrations low. All equipment and working surfaces must be grounded. Personal Protective Equipment: Eyes: Wear appropriate protective eyeglasses or chemical safety goggles as described by OSHA's eye and face protection regulations in 29 CFR or European Standard EN166. Skin: Clothing should be appropriate for handling pyrotechnic substances. Clothing: Clothing should be appropriate for handling pyrotechnic substances. Respirators: A respirator is not typically necessary. Follow the OSHA respirator regulations found in 29CFR or European Standard EN 149. Always use a NIOSH or European Standard EN 149 approved respirator when necessary. 9.0 PHYSICAL AND CHEMICAL PROPERTIES Physical State: solid Appearance: rubber cylinders inside plastic parts Odour: none Odour Threshold: Not available. ph: Not available. Vapour Pressure: Not available. Vapour Density: Not available. Viscosity: Not available. Evaporation Rate: Not available. Boiling Point: Not available. Freezing/Melting Point: Not available. Coefficient of water/oil distribution: Not available. Autoignition Temperature: 280 C Flash Point: Not available. Explosion Limits, lower (LEL): Not available. Explosion Limits, upper (UEL): Not available. Sensitivity to Mechanical Impact: unprotected black powder can be ignited by impact Sensitivity to Static Discharge: unprotected black powder can be ignited by static discharge Decomposition Temperature: > 400 C Solubility in water: black powder is soluble in water Specific Gravity/Density: black powder = Propellant = not available Molecular Formula: Not applicable Molecular Weight: Not applicable STABILITY AND REACTIVITY Chemical Stability: Stable under normal temperatures and pressures. Conditions to Avoid: Heat, static electricity, friction, impact Incompatibilities with Other Materials: Combustible or flammable materials, explosive materials Hazardous Products Of Decomposition: Oxides of nitrogen Hazardous Polymerization: Will not occur.

26 MSDS ProX Rocket Motor Reload Kits Page 4/6 Version 2.02 Revision Date. 8 Feb TOXICOLOGICAL INFORMATION Routes of Entry: Skin contact not likely Skin absorption not likely Eye contact not likely Inhalation not likely Ingestion not likely Effects of Acute Exposure to Product: No data available Effects of Chronic Exposure to Product: No data available Exposure Limits: Black Powder Pellets Ingredient Name CAS Number OSHA PEL ACGIH TLV Potassium Nitrate not established not established Charcoal n/a not established not established Sulphur not established not established Graphite mg/m 3 15 mmpct (TWA) Propellant Ingredient Name CAS Number OSHA PEL ACGIH TLV Ammonium Perchlorate not established not established metal powder varies varies Synthetic Rubber not established not established Irritancy of the Product: No data available Sensitization to the Product: No data available Carcinogenicity: Not listed by ACGIH, IARC, NIOSH, NTP, or OSHA Reproductive Toxicity: No data available Teratogenicity: No data available Mutagenicity: No data available Toxically Synergistic Products: No data available LD50: No data available 12.0 ECOLOGICAL INFORMATION Environmental Data: Ecotoxicity Data: Not determined. EcoFaTE Data: Not determined DISPOSAL CONSIDERATIONS Product As Sold: Product Packaging: Special Considerations: Pack firmly in hole in ground with nozzle pointing up. Ignite motor electrically from a safe distance and wait 5 minutes before approaching. Dispose of spent components in inert trash. Dispose of used packaging materials in inert trash. Consult local regulations about disposal of explosive materials.