Department of Computer Science and Engineering The University of Texas at Arlington. Team: Team MASS. Project: Rocket Recovery System

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1 Department of Computer Science and Engineering The University of Texas at Arlington Team: Team MASS Project: Team Members: Clinton Spivey Heera Main David Salvagnini Olalekan Ajayi Last Updated: Tuesday, November 13, :30 PM

2 Table of Contents Table of Contents... ii Document Revision History... vi List of Figures... vii List of Tables... viii 1. Product Concept Purpose and Use Features and Functions External Inputs and Outputs Product Interfaces Customer Requirements Rocket lands where launched regardless of wind conditions Reusability Intelligent Rotating Base Station - Standby Mode Intelligent Rotating Base Station - Preparation Mode Intelligent Rotating Base Station - Launch Mode Intelligent Rotating Base Station - Rocket Stability Section Low Powered IRBS - Rotation IRBS - Pad pitch RRS - Abort countdown IRBS - Wind speed detection Packaging Requirements October 9, 2012 ii Team MASS

3 4.1 Hardware Software User Manual Performance Requirements Setup Intelligent Rotating Base Station Size Battery Life Outdoor Use IRBS Modes - Time RRM - Microcontroller instructions per cycle Safety Requirements Rocket Certification Rocket Materials Rocket Motors Ignition System Misfires Launch Safety Launcher Rocket Size Flight Safety Launch Site Launcher Location Recovery System Recovery Safety Launch Angle Payloads October 9, 2012 iii Team MASS

4 6.16 Stability No Exposed Wiring Clearly Display Mode Instructions to Switch Modes Automatic Abort Maintenance and Support Requirements Documentation Items excluded Support Launch Procedure Legal Requirements Rocket Engine Power Rocket Engine Propellant Rocket Weight Rocket Materials Rocket Federal Aviation Administration Acceptance Criteria Verify that the SD-12 rocket lands within a 50 foot radius of the IRBS Verify that the SD-12 rocket turns into the wind at time t and angle theta as determined by the IRBS controller Verify that the IRBS rotates to face the wind Verify that the IRBS pitches the pad up to 30 degrees Verify that the countdown sequence can be aborted at any time via remote button press Use Cases The user sets up The user enables Standby Mode The user enables Preparation Mode October 9, 2012 iv Team MASS

5 10.4 The user enables Launch Mode The user launches the rocket Feasibility Assessment Scope Analysis Research Technical Analysis Cost Analysis Resource Analysis Schedule Analysis Future Items Maintenance and Support Requirements: 7.2 Item Included Maintenance and Support Requirements: 7.3 Support Reusability of Rocket Recovery Module October 9, 2012 v Team MASS

6 Document Revision History Revision Number Revision Date Description Rationale /9/12 Rough Draft Peer Review First version of SRS /9/12 Rough Draft Peer Review Added Feasibility Analysis /9/12 Rough Draft Peer Review Made minor format edits /10/12 Rough Draft- Peer Review Format edits /30/12 Rough Draft- Peer Review Made minor edits and added new table /04/12 Gate Review - Peer Review Final changes and revisions /11/12 Final Draft Made final changes /13/12 Final Corrections Final changes per class/instructor recommendations October 9, 2012 vi Team MASS

7 List of Figures Figure Figure The LCD screen... 5 Figure Intelligent Rotating Base Station - Standby Mode... 5 Figure Intelligent Rotating Base Station - Preparation Mode Activation... 5 Figure Intelligent Rotating Base Station - Wind Information... 6 Figure Intelligent Rotating Base Station - Wind Warning... 6 Figure Intelligent Rotating Base Station - Launch Platform Information... 6 Figure Intelligent Rotating Base Station - Launch Mode Activation... 7 Figure Intelligent Rotating Base Station - Launch Countdown... 7 Figure Use Case # Figure Use Case # Figure Use Case # Figure Use Case # Figure Use Case # October 9, 2012 vii Team MASS

8 List of Tables Table External Inputs... 4 Table External Outputs... 4 Table Minimum Personnel Distance Table Table Rocket Motor Coding Table Table Intelligent Rotating Base Station: Cost Analysis Table Rocket Recovery Module and Rocket: Cost Analysis Table SD-12 Launch Cost Estimate Table Total Cost Table Function Point Estimate Table Effort Estimate Table CoCoMo Nominal, Embedded October 9, 2012 viii Team MASS

9 1. Product Concept This section describes the which includes its purpose, audience, and uses as a consumer product. 1.1 Purpose and Use The (RRS) prevents the loss of a launched model rocket by compensating for the speed and direction of wind. The will guide the rocket back to its launched location with the aid of an embedded parachute. The (RRS) has three components: The Intelligent Rotating Base Station (IRBS), The SD-12 Rocket, and the Rocket Recovery Module (RRM). These three systems working together will accomplish the goal of landing the rocket near the launch site. 1.2 Intended Audience The audiences for this project is any model rocket hobbyist from the beginner who doesn t know how to compensate for wind, to the advanced rocket builder who does not want to lose their prized model rocket. Figure 1.1- October 9, Team MASS

10 Figure October 9, Team MASS

11 2. 2. Product Description and Functional Overview Herein is provided a general description of the. The description is composed of its primary functions, key inputs/outputs, and intended use. 2.1 Features and Functions The s central purpose is to launch a low powered model rocket and land it near the area where it was launched from. The (RRS) has three components; The Intelligent Rotating Base Station (IRBS), The SD-12 Rocket, and the Rocket Recovery Module (RRM). The Intelligent Rotating Base Station is a launch pad that gathers information about the wind speed and direction using an attached anemometer. The IRBS will then compensate for the wind by rotating and tilting the launch pad in the appropriate direction. The IRBS will pass the wind data to the SD-12 Rocket equipped with the Rocket Recovery Module before launch. After the launch of the SD-12 rocket, the RRM will make real time calculations, using the IRBS data, to direct the rocket to a specified location. After the engine burn phase, a parachute will be deployed, and the SD-12 will float back to the coordinates where it was launched. The system will have an LCD screen and buttons attached to the IRBS for the user to use. The will have 3 modes. These modes include; Standby Mode, Preparation Mode, and Launch Mode. The Standby mode will allow the user to attach the SD-12 rocket to the IRBS and make necessary adjustments. In this mode no data is being collected or used. The Preparation Mode will start to collect wind data and from the attached anemometer and make the adjustments to the IRBS. The Launch Mode will have the IRBS stop making adjustments and start transmitting the aggregated wind data to the RRM. Once the SD-12 rocket receives all the information the rocket is ready to launch. Key limitations of the include that the rocket is unable to gather wind information after it is launched. The system will also be designed and developed for the SD-12 rocket; transferring the system to a different rocket will not be supported at this time. 2.2 External Inputs and Outputs Inputs Name Description Usage Intelligent Rotating Base Station -- Gathers a steady stream of wind speed and Allows the Intelligent Rotating Base Station compensate for the wind by rotating and tilting the launch pad. This data is also passed October 9, Team MASS

12 anemometer direction data. to the RRM. Physical buttons attached to the LCD. Gathers input from the user. This allows the user to navigate the GUI and make selections. Rocket Recovery Module. Wind speed and direction data. The Rocket Recovery Module will receive the wind speed and direction data from the IRBS. Outputs Table External Inputs Name Description Usage Intelligent Rotating Base Station -- LCD Wind speed and direction data. User can see wind speed and wind direction on an LCD screen. Intelligent Rotating Base Station -- LCD Launch Platform direction and angle. User can see launch platform direction and angle on an LCD screen. Intelligent Rotating Base Station --Servos Wind speed and direction data. The wind speed and directions data will be used to move the servos to the desired location. SD-12 Rocket with Rocket Recovery Module equipped Wind speed and direction data. The wind speed and directions data will be used to move the rocket control surfaces. Intelligent Rotating Base Station Wind speed and direction data. The winds speed and direction data will be sent to the Rocket Recovery Module. Table External Outputs 2.3 Product Interfaces The user of the will interact with the system through an LCD screen and physical buttons. The user will not have a lot of interaction with the system; therefore, the graphical user interface will not be very robust. October 9, Team MASS

13 Figure The LCD screen Figure Intelligent Rotating Base Station - Standby Mode Figure Intelligent Rotating Base Station - Preparation Mode Activation October 9, Team MASS

14 Figure Intelligent Rotating Base Station - Wind Information Figure Intelligent Rotating Base Station - Wind Warning Figure Intelligent Rotating Base Station - Launch Platform Information October 9, Team MASS

15 Figure Intelligent Rotating Base Station - Launch Mode Activation Figure Intelligent Rotating Base Station - Launch Countdown October 9, Team MASS

16 3. Customer Requirements This section describes the basic functionalities, usability, and appearance of the product as required by the customer. These following requirements were put together by Team MASS. 3.1 Rocket lands where launched regardless of wind conditions Description: The system will launch a model rocket and land it within a 50 foot radius from the area where it was launched Source: Team MASS Constraints: N/A Standards: None Priority: Critical Simple User Interface Description: The system will be easy for user to use. This will require less input from the customer thereby make the operation simple Source: Team MASS Constraints: None Standards: None Priority: Medium Reusability Description: The system will be made of non-breakable components. The customer will be able to use the system again by changing the engine and putting it back together Source: Team MASS Constraints: None Standards: None Priority: High - 2 October 9, Team MASS

17 3.4 Intelligent Rotating Base Station - Standby Mode Description: The base station will have a standby mode. The standby mode will be the mode used during setup and preparation prior to entering the preparation mode Source: Team MASS Constraints: None Standards: None Priority: Critical Intelligent Rotating Base Station - Preparation Mode Description: The preparation mode will be the active state of the base station in which environment variables are read, calculations made, and proper positioning conducted to prepare for the launch stage Source: Team MASS Constraints: None Standards: None Priority: Critical Intelligent Rotating Base Station - Launch Mode Description: The launch stage will last 30 seconds. In this stage there will be no more wind data collection and the aggregated wind data will be sent to the Rocket Recovery Module inside the SD-12 Rocket. The base station will be in its final launch position Source: Team MASS Constraints: None Standards: None Priority: Critical Intelligent Rotating Base Station - Rocket Stability Section Description: To ensure stability of the rocket while on the base station during high winds. This section of the base station contains the rods that the SD-12 Rockets lugs ride along to guide it during the first few feet of the launch. There will be a second rod that runs perpendicular to the first and the rocket will have two sets of lugs that will ride along the two rods. October 9, Team MASS

18 3.7.2 Source: Team MASS Constraints: None Standards: None Priority: Critical Low Powered Description: The system will use common everyday 9 volt batteries Source: Team MASS Constraints: If the microprocessor and servos require more than 9 volts : Standards: None 3.8.5: Priority: Medium IRBS - Rotation Description: Based on the anemometer the IRBS will rotate to orient itself and the SD-12 rocket into the wind Source: Team MASS Constraints: Servos, actuators, and electric motors will need to be powerful enough to move the weight Standards: None Priority: Critical IRBS - Pad pitch Description: Based on the anemometer the IRBS will pitch the pad at an angle into the wind depending on its strength Source: Team MASS Constraints: Servos and actuators will need to be powerful enough to move the weight Standards: None Priority: Critical - 1 October 9, Team MASS

19 3.11 RRS - Abort countdown Description: The IRBS will have an abort button that will abort the launch countdown and revert back to the IRBS to its standby mode Source: Team MASS Constraints: None Standards: None Priority: Critical IRBS - Wind speed detection Description: The anemometer mounted on the IRBS will be used to feed wind speed data to the IRBS microcontroller. This will be used to compute the time and angle that the SD-12 Rocket will take on ascent Source: Team MASS Constraints: None Standards: None Priority: Critical - 1 October 9, Team MASS

20 4. Packaging Requirements Below are the packaging requirements for. This includes hardware, software, and user manual. 4.1 Hardware Description: The packaging will include the Intelligent Rotating Base Station and the SD-12 Rocket. The Rocket will be equipped with a Rocket Recovery Module. The anemometer will be included in the package, and the user will have to attach it to the Intelligent Rotating Base Station. The user will have to buy engines, batteries, and wadding separately. The user will also have to do minor assembling Source: Team MASS Constraints: None Standards: None Priority: High Software Description: The software will be embedded in the Rocket Recovery Module and Intelligent Rotating Base Station Source: Team MASS Constraints: The microprocessor will have to have adequate memory to hold the software Standards: None Priority: Critical User Manual Description: A user manual will be included for user s assistance Source: Team MASS October 9, Team MASS

21 4.3.3 Constraints: None Standards: None Priority: High - 2 October 9, Team MASS

22 5. Performance Requirements The quality of any product is determined by its performance. Herein we outline the performance requirements in detail to ensure that the project is of the utmost quality. 5.1 Setup Description: Setup of the entire system will not take more than 20 minutes. Setup time includes the time that it takes from arrival to the launch site to actual recovery of the SD-12 Rocket Source: Team MASS Constraints: None Standards: None Priority: Low Intelligent Rotating Base Station Size Description: The IRBS should not have a larger footprint than the standard launch pad. The only exception to this would be the external anemometer that is attached to the Base Station Source: Team MASS Constraints: The footprint must be smaller than 1 cubic meter Standards: None Priority: Low Battery Life Description: The battery life should last for at least one launch cycle Source: Team MASS Constraints: The size and type of battery used will affect the battery life. October 9, Team MASS

23 5.3.4 Standards: None Priority: Critical Outdoor Use Description: The will function outside in normal conditions Source: Team MASS Constraints: Inclement weather and wind greater than 20 mph Standards: None Priority: Critical IRBS Modes - Time Description: The Intelligent Rocket Base Station will have 3 modes with the following time constraints for each: standby, no time constraint. Preparation: 2 minutes minimum, 3 maximum. Launch: strictly 30 seconds Source: Team MASS Constraints: User aborts launch Standards: None Priority: High RRM - Microcontroller instructions per cycle Description: The processing power of the microcontroller will be fast enough to make stability correction that ensure smooth flight through the end of the burn Source: Team MASS Constraints: Cost and availability Standards: None Priority: High - 2 October 9, Team MASS

24 6. Safety Requirements In dealing with a model rocket certain safety concerns should be considered and adhered to. Herein we outline safety requirements in detail to ensure a completely safe environment for the team, spectators, the environment, and air traffic. 6.1 Rocket Certification Description: Only fly rockets or rocket motors that are within the scope of the group s user certification and required licensing Source: National Association of Rocketry Model Rocket Safety Code Constraints: None Standards: None Priority: Critical Rocket Materials Description: The rocket will be limited in construction to lightweight materials such as paper, wood, rubber, plastic, or fiberglass Source: National Association of Rocketry Model Rocket Safety Code Constraints: None Standards: None Priority: Critical Rocket Motors Description: The rocket 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. The group will not allow smoking, open flames, nor heat sources within 25 feet of these motors Source: National Association of Rocketry Model Rocket Safety Code Constraints: None October 9, Team MASS

25 6.3.4 Standards: None Priority: Critical Ignition System Description: The group will launch the rockets with an electrical launch system and electrical motor igniters. The launch system will have a safety interlock in series with the launch switch, and will use a launch switch that returns to the "off" position when released Source: National Association of Rocketry Model Rocket Safety Code Constraints: None Standards: None Priority: Critical Misfires Description: If the rocket does not launch when intended, a group member 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 Source: National Association of Rocketry Model Rocket Safety Code Constraints: None Standards: None Priority: Critical Launch Safety Description: The group will use a countdown before launch, and will ensure that everyone is paying attention and is a safe distance of at least 15 feet away when the group launch rockets with D motors or smaller, and 30 feet when we launch larger rockets. When conducting a simultaneous launch of more than ten rockets the group will observe a safe distance of 1.5 times the maximum expected altitude of any launched rocket Source: National Association of Rocketry Model Rocket Safety Code Constraints: None Standards: None Priority: Critical - 1 October 9, Team MASS

26 6.7 Launcher Description: The group will launch the rocket from a stable launch device that provides rigid guidance until the model rocket has reached a speed adequate to ensure a safe flight path. To prevent accidental eye injury, group members will always place the launcher so the end of the rod is above eye level or group members will cap the end of the rod when approaching it. Group members will cap or disassemble the launch rod when not in use and will never store it in an upright position. The launcher will have a jet deflector device to prevent the motor exhaust from hitting the ground directly. The group will always clear the area around my launch device of brown grass, dry weeds, or other easy-to-burn materials Source: National Association of Rocketry Model Rocket Safety Code Constraints: The group is creating our own launch pad will be untested Standards: None Priority: Critical Rocket Size Description: The rocket will weigh no more than 1,500 grams (53 ounces) at lift-off and its rocket motors will produce no more than 320 Newton-seconds (71.9 pound-seconds) of total impulse. The rocket will weigh no more than the motor manufacturer's recommended maximum lift-off weight for the motors used, or the group will use motors recommended by the manufacturer for my model rocket Source: National Association of Rocketry Model Rocket Safety Code Constraints: The group is adding many parts as the control system of the rocket. Lightweight materials should be used on all parts Standards: None Priority: Critical Flight Safety Description: The group will not launch the 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 the rocket. The group will not launch the rockets if wind speeds exceed 20 miles per hour. The group will comply with Federal Aviation Administration airspace regulations when flying, and will ensure that the rocket will not exceed any applicable altitude limit in effect at that launch site Source: National Association of Rocketry Model Rocket Safety Code October 9, Team MASS

27 6.9.3 Constraints: The group must make sure that the wind detector functions properly before launching Standards: None Priority: Critical Launch Site Description: The group will launch the rocket outdoors in a cleared area, free of tall trees, power lines, buildings, and dry brush and grass. The launch area will be at least as large as that recommended in the accompanying table Source: National Association of Rocketry Model Rocket Safety Code Constraints: None Standards: None Priority: Critical Launcher Location Description: The 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 (Fig. 6.1) from any boundary of the launch site Source: National Association of Rocketry Model Rocket Safety Code Constraints: None Standards: None Priority: Critical Recovery System Description: The group will use a recovery system such as a parachute in the rocket so that all parts of the rocket return safely and undamaged and can be flown again, and the group will use only flame-resistant or fireproof recovery system wadding in the rocket Source: National Association of Rocketry Model Rocket Safety Code Constraints: The project will require that we build our own parachute release since a secondary charge from the engine cannot be used because of the payload. This system will need to be tested before using. October 9, Team MASS

28 Standards: None Priority: Critical Recovery Safety Description: The group will not attempt to recover the 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 Source: National Association of Rocketry Model Rocket Safety Code Constraints: None Standards: None Priority: Critical Launch Angle Description: The launch device will be pointed within 30 degrees of vertical. The group will never use model rocket motors to propel any device horizontally Source: National Association of Rocketry Model Rocket Safety Code Constraints: The group is going to build a launch pad that point into the wind automatically. We must make sure that the base is not pointed more than 30 degrees of vertical Standards: None Priority: Critical Payloads Description: The rocket will never a payload that is intended to be flammable, explosive, or harmful Source: National Association of Rocketry Model Rocket Safety Code Constraints: None Standards: None Priority: Critical Stability Description: Calculations will be made to prove stability prior to first flight. October 9, Team MASS

29 Source: National Association of Rocketry Model Rocket Safety Code Constraints: Limited knowledge in aerospace engineering and high level mathematics Standards: None Priority: Critical No Exposed Wiring Description: All wiring and electronic components will be contained and insulated to prevent shock to users and/or targets Source: Team MASS Constraints: None Standards: None Priority: Critical Clearly Display Mode Description: The system will contain an LED that will illuminate when it is in Standby Mode, Preparation Mode, or Launch Mode. The LED should be positioned so that it can be seen from where the operator is launching the rocket Source: Team MASS Constraints: None Standards: None Priority: High Instructions to Switch Modes Description: The instructions that are included with the will describe how to safely use it and how to switch modes Source: Team MASS Constraints: None Standards: None Priority: High 2 October 9, Team MASS

30 6.20 Automatic Abort Description: The shall have an automatic abort that will detect abnormal launch conditions that the user cannot. These launch conditions include, but are not limited to winds over 20 mile per hour, launch pad tilt over 30 degrees, and loss of data connection Source: Team MASS Constraints: None Standards: None Priority: High 2 LAUNCH SITE DIMENSIONS Installed Total Impulse (N-sec) Equivalent Motor Type /4A, 1/2A A B C D E 1, F 1, G 1, Two G's 1,500 Table Minimum Personnel Distance Table Minimum Site Dimensions (ft.) October 9, Team MASS

31 7. Maintenance and Support Requirements The RRS will be designed with the user in mind and as such will be easy and fun to maintain. Herein we outline the maintenance and support requirements in detail to ensure the project is user friendly and consistent in operation. 7.1 Documentation Description: The RRS will come with a setup manual that outlines in detail the setup and launch procedures. This manual will include safety guidelines to follow to ensure that the user is safe throughout the entire operation Source: Team MASS Constraints: N/A Standards: N/A Priority: High Items excluded Description: There are many items that are required to operate the RRS that would not be included in a commercially available kit. Those items are enumerated below: Rocket Engines Fireproof wadding 2, 9 v batteries Source: Team MASS Constraints: N/A Standards: N/A Priority: High Support Description: Customer support will be limited to the duration of the project Source: Team MASS October 9, Team MASS

32 7.3.3 Constraints: N/A Standards: N/A Priority: Low Launch Procedure Description: A launch procedure, with outlined checks at each mode of the IRBS, will be provided to ensure a successful launch Source: Team MASS Constraints: N/A Standards: N/A Priority: High 2 October 9, Team MASS

33 8. Legal Requirements In dealing with a model rocket certain legal issues should be considered and adhered to. Herein we outline the legal requirements in detail to ensure the project meets all aspects of local, state, and federal law. 8.1 Rocket Engine Power Description: The rocket must not use motor with more than 160 Newton-seconds of total impulse (an "H" motor or larger) or multiple motors that all together exceed 320 Newtonseconds. It must also not use a motor with more than 80 Newtons average thrust. (see rocket motor coding table) Source: National Fire Protection Association (NFPA) Code Constraints: None Standards: None Priority: Critical Rocket Engine Propellant 8.2. Description: The rocket engine must not exceed 125 grams of propellant Source: National Fire Protection Association (NFPA) Code Constraints: None Standards: None Priority: Critical Rocket Weight Description: The rocket must not weigh more than 1,500 grams including motor(s) Source: National Fire Protection Association (NFPA) Code Constraints: The group is adding many parts as the control system of the rocket. October 9, Team MASS

34 8.3.4 Standards: None Priority: Critical Rocket Materials Description: The rocket must use only lightweight, non-metal parts for the nose, body, and fins of my rocket Source: National Fire Protection Association (NFPA) Code Constraints: None Standards: None Priority: Critical Rocket Federal Aviation Administration Description: Model rockets are exempt from FAA regulation, provided they; are launched on a suborbital trajectory; when launched, must not cross into the territory of a foreign country unless an agreement is in place between the United States and the country of concern; is unmanned; and does not create a hazard to persons, property, or other aircraft Source: Code of Federal Regulations Constraints: The launch site should be far away from airports and low flying planes Standards: None Priority: Critical 1 October 9, Team MASS

35 Hobby Rocket Motor Information Classification Impulse Range Impulse Limit Category Model Rocket 1/8A Micro 1/4A Low Power 1/2A 1.25 A 2.5 B 5 C 10 D 20 E 40 Mid Power F 80 G 160 Table Rocket Motor Coding Table October 9, Team MASS

36 9. Acceptance Criteria Herein we outline the customer s criteria to help determine the success and acceptability of the project. The final product should meet the following referenced criteria as stated prior to being deemed nominal and complete. 9.1 Verify that the SD-12 rocket lands within a 50 foot radius of the IRBS Requirement(s) addressed: Requirement 3.1: The SD-12 Rocket is expected to land where it was launched within a radius of 50 feet from the IRBS. This is the main focus behind the project and a lack of this requirement being met signifies a failure to complete the project Verification Procedure: The customer will witness the launch 9.2 Verify that the SD-12 rocket turns into the wind at time t and angle theta as determined by the IRBS controller Requirement(s) addressed: Requirement 3.1: After the IRBS computes and finalizes the turn angle at some time that information will be fed to the SD-12 rocket via wire. After this data is received the rocket is launched and it must carry out the turn according the aforementioned time and angle Verification Procedure: The customer will witness the launch 9.3 Verify that the IRBS rotates to face the wind Requirement(s) addressed: Requirement 3.9: The SD-12 Rocket will make calculations assuming that its launched in an orientation such that the IRBS is facing the wind Verification Procedure: The customer will witness the IRBS rotate into the wind 9.4 Verify that the IRBS pitches the pad up to 30 degrees Requirement(s) addressed: Requirement 3.10: The SD-12 Rocket will make calculations assuming that its launched in an orientation such that the IRBS is pitched into the wind Verification Procedure: The customer will witness the IRBS pitch the pad up to 30 degrees October 9, Team MASS

37 9.5 Verify that the countdown sequence can be aborted at any time via remote button press Requirement(s) addressed: Requirement 3.11: A detailed countdown procedure will be followed to ensure a safe and successful launch experience. In the event that there is a problem and the launch must be aborted a remote button will be pressed at which time the IRBS will be set to the standby mode resulting in an aborted launch Verification Procedure: The customer will witness the IRBS abort function October 9, Team MASS

38 10. Use Cases Use cases show how an actor will interact with the. This section establishes the actor/system interactions for each of the different relevant use cases of the device. TUCBW stands for This Use Case Begins With TUCEW stands for This Use Case Ends With 10.1 The user sets up Scenario: The actor sets up all the components and makes sure they power on Actor(s): User launching the rocket TUCBW: The user gathers all the required components to the TUCEW: The user powers up the. Figure Use Case #1 October 9, Team MASS

39 10.2 The user enables Standby Mode Scenario: The actor activates the Standby Mode Actor(s): User launching the rocket TUCBW: The user powers up the TUCEW: The user sees Standby Mode Figure Use Case # The user enables Preparation Mode Scenario: The actor activates the Preparation Mode Actor(s): User launching the rocket TUCBW: The user sees the LCD screen display Enter Preparation Mode? TUCEW: The user sees the wind and Intelligent Rotating Base Station data. October 9, Team MASS

40 Figure Use Case # The user enables Launch Mode Scenario: The actor activates the Launch Mode Actor(s): User launching the rocket TUCBW: The user sees the LCD screen display Enter Launch Mode? TUCEW: The user sees the countdown time. October 9, Team MASS

41 Figure Use Case # The user launches the rocket Scenario: The actor launches the rocket Actor(s): User launching the rocket TUCBW: The user hitting the launch button on the remote TUCEW: The user sees the rocket land. October 9, Team MASS

42 Figure Use Case #5 October 9, Team MASS

43 11. Feasibility Assessment We are using this metric as a tool to inform our sponsor and ourselves of the detailed practicality of the project. It is predicted that the project will be a success and hence this assessment is being produced and used as confirmation to our existing stand. This section is used to analyze the feasibility of using the following six components: Scope Analysis, Research, Technical Analysis, Cost Analysis, Resource Analysis, and Schedule Analysis Scope Analysis The scope of work for the critical priority requirements of our project is reasonable and within our capability. The team present knowledge of the design and execution for building of rocket provides the confidence that the project will be done by the stipulated two semesters assigned. Working together with our sponsor will provide solutions to some of the obstacle we might come across within the process of getting the product done; this further explains the confidence we have in the feasibility of the project. Having all the factor working together, there are several customer requirements that comprise the majority of our project. These are the requirements that will most likely take the largest amount of time to implement, and as such, we will be giving them the most attention. Those requirements are as follows: Customer Requirement 3.1: The system should be able to make the rocket lands where launched. Customer Requirement 3.2: The system will be easy for user to use. This will require less input from the customer thereby make the operation simple. Customer Requirement 3.3: The system will be made of non-breakable components. The customer will be able to use the system again by changing the engine and putting together all the components. Customer Requirement 3.6: The system will use low powered batteries which save cost Research It is very important that our team does the appropriate research on this project in order to build a working prototype. The research that the team will undertake will include areas in hardware, software, aerodynamics, statics, dynamics, propulsion, and control engineering. Many of the topics related to aerospace engineering the team is fairly weak in. The teams sponsor, The UTA Aero Mavericks, will assist in the research areas that we are not strong in. The team also has done extensive research to make sure that the project is financially feasible as well. The project should be well under the $ limit October 9, Team MASS

44 with plenty of room to spare. We were able to find this out by doing a cost analysis on the necessary parts that will be needed Technical Analysis This project will have our team utilizing hardware design and mathematical formulas with analysis. The hardware design for the different units will not likely be total construction of our team, but rather attaching and connecting different pre-existing technologies so they may properly interface. The issue with making these connections is two-fold; the technologies must be compatible, and the final combined units must work appropriately The design will consist of Intelligent Rotation Base Station (IRBS) that rotates and gathers data, Rocket Recovery Module (RRM) that enclosed the microprocessor which captures the rocket wind, and (RRS). The team will consult with the Mechanical Engineering Lab and any Senior Design team for assistance with the designing of the IRBS. Mathematical formulas and analysis believe to be important in our project because it involves creation of measurement that will be applied to measure the height projection for the rocket and the wind current Cost Analysis The RRS project is anticipated at falling far short of the $800 budget given as an original maximum cost. Since the project appeals armature rocket enthusiasts the cost is intentionally low. Conversely given that the nature of the project is in academia we have indulged in a more complex product design resulting in a slightly higher cost. The below tables outline the cost of the project in detail per component. Arduino Uno R3 1 $29.99 LCD Shield Kit w/ 16x2 Character Display 1 $19.95 Servo - Standard size, High Torque 1 $32.99 Electric Motor - High Torque 1 $14.87 Wind Meters (Anemometer) 1 $ V Battery Wire 1 $.99 Plexiglass - 24 x48 x $25.00 Two-Piece Launch Rod 1 $5.39 October 9, Team MASS

45 Electron Beam Launch Controller 1 $16.49 Metal Disc 6 Diameter 1 $2.00 TOTAL $ Table Intelligent Rotating Base Station: Cost Analysis Arduino Mini 05 1 $33.99 USB 2 Serial Converter 1 $13.00 Servo Micro 2 $8.95 BMA180 Accelerometer 1 $29.95 MPL115A1 Barometer 1 $24.95 LPY510AL Gyro 1 $19.95 Balsa Wood Sheet 3 x48 x1/8 1 $4.65 9V Battery Wire 1 $.99 BT 80 Rocket tubes 2 $8.79 BT 80 Nose Cone 1 $4.29 Custom Plastic Fins 4 $40.00 Engine mount kit 1 $8.79 BT 80 Coupler 1 $6.99 Parachute $1.99 Shock Cord 1 $4.99 October 9, Team MASS

46 Launch Lugs 4 $5.49 Glue and Epoxy 1 $10.00 Paint 4 $22.20 TOTAL $ Table Rocket Recovery Module and Rocket: Cost Analysis E9-0 3 $14.99 Wadding 1 $3.99 9V Battery 2 $4.99 TOTAL $23.97 Table SD-12 Launch Cost Estimate Intelligent Rotating Base Station $ Rocket Recovery Module and Rocket $ SD-12 Launch $23.97 TOTAL $ Table Total Cost 11.5 Resource Analysis Team MASS consists of one computer engineer, one computer scientist, and two software engineer. We feel that this should be an adequate mix of team members to complete the project within the time frame allotted. We also feel that the lack of a lot of software requirements will work in our advantage. Our computer engineer and one of our software engineers has had experience working with hardware and this will help during our implementation of the actual product. The computer scientist on the team has had experience building rockets before as a hobby and will help out tremendously when it comes time to October 9, Team MASS

47 build the SD-12 Rocket. The team also has a software engineer that is very proficient at Microsoft Project and keeping track of our time we spend working on the project. The area s that our team lacks in the aerospace engineering fields, this is where our sponsor and research will come into play. We feel that with the assistants of our sponsors and our dedication to research this risk can be minimized Schedule Analysis Team MASS has used various estimation methods to determine the feasibility of the Rocket Recovery System Software Project Size and Productivity Approach Low Side (Aggressive) High Side (Conservative) Size Estimate 1000 LOC 1500 LOC Productivity 41.5 LOC/PM 37.5 LOC/PM Effort 24 PM 40 PM Duration 6 months 10 months (4 person team) We will have fewer lines of codes, but the complexity will be high Schedule Estimation Rule of Thumb: Using McConnell Equation 8-1 (p.183) Schedule in months = 3.0 * man-month 1/3 Low Side (Aggressive) High Side (Conservative) 3 * (24) 1/3 3 * (40) 1/3 Duration = ¾ months = ¼ months Function Point Estimate Only high complexity is used for function point estimate because all of our inputs, outputs, and files have high priority. Using McConnell Table 8-2 (p. 176), High Complexity Program Characteristics High Complexity Function Point Total Number of inputs 2 * 6 12 October 9, Team MASS

48 Number of outputs 4 * 7 28 Inquiries 1 * 6 6 Logical Internal Files 2 * External Interface File 2 * Total 96 Table Function Point Estimate Adjustment factor = 1 1 * 96 = 96 adjusted function points Using McConnell Table 8-7 (p. 185), System Kind of Software Best Case Average Case Worst Case months months months Table Effort Estimate CoCoMo Basic CoCoMo Estimation Coefficients, based on project type/complexity: Coefficient A b C D Organic Semi-detached Embedded Table CoCoMo Nominal, Embedded Low Side High Side (Aggressive) (Conservative) Effort - PM E = 3.6(1) 1.20 E = 3.6(1.5) 1.20 E = a(sloc) b = 3.6 PM = 5.86 PM Duration - months E = 2.5(3.6) 0.32 E = 2.5(5.86) 0.32 D = c(e) d = ¾ months = ½ months October 9, Team MASS

49 Because we have fewer lines of code, our COCOMO estimate is low Comparing Comparing all the estimation methods used above Low Side (Aggressive) High Side (Conservative) Size and Productivity 6 months 10 months Rule of Thumb 8 ¾ months 10 ¼ months Function Points/Jones s 7 months 9 months CoCoMo 3 ¾ months 4 ½ months Sanity Test (Weiss & Wysocki, 1992) E = (O + 4M + P) / 6, where O = optimistic, M = Nominal, P = Pessimistic Therefore, our E = (3 ¾ + 4(7) + 10 ¼) / 6 = 7 months October 9, Team MASS

50 12. Future Items In this last section, we will replicate all requirements that are listed as priority 5. This is repetitive, but necessary as a summary statement of features/functions that were considered/discussed and documented herein, but will NOT be addressed in the prototype version of the product due to constraints of budget, time, skills, technology, feasibility analysis etc Maintenance and Support Requirements: 7.2 Item Included Requirement Description: There are many items that are required to operate the RRS that would not be included in a commercially available kit Constraint: Budget 12.2 Maintenance and Support Requirements: 7.3 Support Requirement Description: Customer support will be limited to the duration of the project Constraint: None 12.3 Reusability of Rocket Recovery Module Requirement Description: The Rocket Recovery Module should be able to operate on any rocket Constraint: Limited time for the project October 9, Team MASS