GATEWAY TO SPACE SPRING 2006 DESIGN DOCUMENT

Transcription

1 Colorado Space Grant Consortium GATEWAY TO SPACE SPRING 2006 DESIGN DOCUMENT Team AFROS (Aerospace FReshmen Observing Science) Written by: Colin Miller, John Stark, Matt Zelenok, David Ferguson & Jesse Sultanik April 18, 2006 Revision C Team AFROS Page 1 of 21

2 Revision Log Revision Description Date A Conceptual Design Review 3/02/06 B Preliminary Design Review 3/23/06 C Critical Design Review 4/18/06 D Analysis and Final Report 5/02/06 Team AFROS Page 2 of 21

3 Table of Contents 1.0 Mission Overview Design Management Budget Test Plan and Results Expected Results Launch and Recovery.21 Team AFROS Page 3 of 21

4 1.0 Mission Overview External radiation exposure is defined as high energy particles hitting the body and causing cell damage from some outside source. It has been proven that the sun is a major supplier of harmful radiation that increases in intensity as altitude increases within our atmosphere. Our mission is to discover the rate at which amounts of harmful radiation increase as a function of altitude. A plane flight from New York to LA will deliver a 1.3 millirem dose to it s the frequent passenger that flies at least three two way trips per week. On the other hand, a chest x-ray will deliver 10 millirems of harmful x-ray radiation, and 25 millirems is the annual exposure limit set by the EPA for nuclear power plant workers. In relation to these amounts, we are attempting to determine information about the actual severity of harmful radiation in the upper atmosphere as it pertains to commercial aviation and possibly future aviation at higher altitudes. In addition, we will be taking multiple pictures at different angles, acquiring actual ascent and descent rates from EOSS, and measuring temperature data throughout the flight. 2.0 Design 2.1 Hardware BASIC Stamp This piece of equipment is the brain of the electronics integration. Easily programmable in basic programming language, the unit can be used to give commands, receive commands, and store data, which can be extracted through a serial port interface in the basic stamp. Most kits come with the essential hardware for the construction of the stamp and PC interface (serial port). Currently the BASIC stamp 2 is the best on the market, without the expensive interface and hassle of difficult programming languages that the BASIC stamp 1 consists of. The BASIC stamp 2 compared to the BASIC stamp 1 has a faster processing speed, larger memory capacity, and better sensitivity to input; proving version two the best choice for our project. Model: BASIC Stamp 2 OEM Module (Kit Form) o PBASIC language The basic stamp 2 requires a hybrid of basic programming language to exploit all of the operable functions The basic stamp 2 has enough programming memory for lines of PBASIC code in the EEPROM{programming memory, which is nonvolatile (programming data is not lost after loss of power)} Team AFROS Page 4 of 21

5 Basic Stamp PBASIC code 2:25 AM 4/18/2006 ' {$STAMP BS2} 'necessary to run the bs2 program ' {$PBASIC 2.5} ServoControl PIN 8 it VAR Nib temp VAR Byte 'sets pin 8 on the stamp set of 15 to 'output servo commands 'variable declarations 'BASIC Stamp 2 Servo Control Servo: FOR it = 0 TO 3 ' 4 iterations, that is rotate a total of four times FOR temp = 0 TO 200 PULSOUT ServoControl, 1070 'Up PAUSE 20 FOR temp = 0 TO 200 PULSOUT ServoControl, 640 PAUSE 20 FOR temp = 0 TO 200 PULSOUT ServoControl, 230 PAUSE 20 FOR temp = 0 TO 200 PULSOUT ServoControl, 640 PAUSE 20 'Center 'Down 'Center Team AFROS Page 5 of 21

6 location VAR Word counts VAR Byte i VAR Byte value VAR Byte 'variable declarations for the stamp to Geiger counter interface main: standard main declaration not a subclass FOR location = 0 TO 2000 ' EPPROM STORAGE location counts = 0 FOR i =0 TO 199 'reset counts 'reads the status from the geiger counter 200 times PULSIN 15, 1, value 'reads a pulse from the geiger counter through pin 15 'on the set of 15 pins IF value =0 THEN calc ' if the pulse is existent then add a count counts = counts +1 calc: 'The IF/THEN will skip to here if true 'ensuring that a count is not added ' goes up to the FOR loop of 200 iterations WRITE location, counts 'writes the value after the 200 samples are taken DEBUG CR, DEC? counts, DEC? location 'tells us if the stamp and geiger counter 'are communicating properly ' moves up to the next location 'OVERALL the Geiger counter outputs pulses 'the "status" of the Geiger counter is read 200 times 'if there is a pulse existent then it adds to the counts variable 'this variable is stored into the EPPROM location selected by another loop 'because this value is stored every 26 seconds according to testing this 'allows for conversion into counts per min and eventually rads Team AFROS Page 6 of 21

7 'BASIC Stamp 2 Servo Control 'after some data collection the servo will fire back up and take pictures 'near the balloon burst 'no data needs to be collected from the Geiger counter on the way down Servo2: FOR it = 0 TO 3 ' 4 iterations FOR temp = 0 TO 200 PULSOUT ServoControl, 1070 'Up PAUSE 20 FOR temp = 0 TO 200 PULSOUT ServoControl, 640 PAUSE 20 FOR temp = 0 TO 200 PULSOUT ServoControl, 230 PAUSE 20 FOR temp = 0 TO 200 PULSOUT ServoControl, 640 PAUSE 20 'Center 'Down 'Center END the program is done here it will not repeat 'ALL code above is the sole input of DAVID A. FERGUSON AND COLIN MILLER 'ANYBODY who copies our code and is caught will be upheld by 'the full extent of the CU honor code Geiger Counter The Geiger counter ordered through imagesco.com will serve as the experimental interface on the balloon sat for project HAIRS. The model we will be using (GCK-05) detects radiation in the following ranges: ALPHA- greater than 3.0MeV BETA- greater than 50 KeV GAMMA- greater than 7 KeV. Team AFROS Page 7 of 21

8 The digital output jack provides a TTL logic high pulse each time a radioactive particle is detected. This output can easily be interfaced with the BASIC stamp 2, which understands and records this TTL logic high pulse in the I/O pins. The energy of ionizing radiation is measured in electron volts (ev). One electron volt is an extremely small amount of energy. Commonly used multiple units are the kilo electron (kev) and mega electron volt (MeV). Based off these parameters our Geiger counter will only measure beta and alpha particles if the energy on these particles is relatively high. The Geiger counter is pre-calibrated because beta and alpha particles need substantial energy to cause damage. HOBO The Hobo data logger will serve the primary purpose of temperature recording of the inside and outside of the box, but it will also record relative humidity throughout the duration of the flight. These readings can be done every few milliseconds or every few seconds for variant lengths of time based on the internal memory of the HOBO data logger. These hobos are easy to interface with a PC upon recovery via the HOBO software and a serial cable that will connect the HOBO to the PC. The HOBO is small and roughly the size of a large matchbook or smaller than the average flip-style cell phone. Optics Pictures will be taken on a forty exposure roll of film through 3 acrylic windows (straight out, straight down, and straight up). Because of the camera s rotation with the servo equipment, a clear sheet of acrylic material must be used to provide insulation instead of cutting holes in the box. The servo will be programmed to rotate with the BASIC stamp PBASIC language and one of the output pins. This rotation of the camera will take place independent of the snapshots. The snapshots will be controlled with the timing chip constructed in class. A set interval of two minutes will be calibrated into the timing chip such that snapshots occur over the majority of the flight. Camera rotation with the servo subsystem will continue during the burst and descent. The two minute interval with 40 exposure film will result in pictures covering 80 minutes of the flight. Servo The servo is a small mechanical device that can be used to control devices such as pitch and roll controls on model airplanes and RC car control. The device consists of a motor and shaft capable of rotating 210 degrees. Most servos are incapable of a complete revolution because of a mechanical stop in the gears. The servo has a power draw proportional to how loaded it is and also how far it must travel. So if a servo must travel a short distance it moves slow, or a long distance, like a complete 180, it will move much faster and draw a large amount of power. This property of servo motors is called proportional control. A servo is commanded to rotate by pulses of power. Usually a 1.5 millisecond pulse will cause a ninety degree rotation. This location on the servo is often referred to as the neutral position, with ninety possible degrees of rotation in either direction. It is possible to write a program in PBASIC along with the timing set in the optic system timing circuit to arrange for a picture to be taken at 0 degrees, 90 degrees, and 180 degrees. Further testing will yield an optimum angle of rotation, which could be potentially less than a full ninety degree rotation of the servo. Team AFROS Page 8 of 21

9 2.2 Structure The structure of our balloon satellite will be designed to carry all components and protect them upon landing and balloon burst. All side walls and mounts will be made of foam core and there will be a layer of insulation material between the side walls and the internal components. The design must be light enough to allow for necessary equipment to be carried. A key design feature will be the square acrylic Plexiglas windows that will be mounted on the top, bottom, and front of the satellite. Internally, the structure will feature a central pass through the box with metal tubing to allow for the attachment of the cord. 2.3 Sensing Sensing systems design will incorporate a BASIC stamp to command elements of the satellite and record data as well. We will utilize a HOBO data logger to accurately analyze temperature (internal/external) and relative humidity. The camera system will consist of a timing circuit controlling the camera as well as a servo to control camera rotation. Servo positioning will be controlled by the BASIC stamp unit. Rotation will be controlled with pulses from the BASIC stamp and will be set to pause at +90 degrees (straight up), 0 degrees (neutral), and -90 degrees (straight down). There will be a separate battery pack to keep the servo functions separate from other necessary systems such as heating and the BASIC stamp. All pictures will be taken through acrylic windows mounted into the sidewalls of the balloon satellite. Ascent and decent rates will be determined via EOSS data, which will be obtained after launch and recovery. 2.4 Heating & Environmental Factors The heating system for the craft has been built of conductive ceramic composites. The three ceramic composite pieces run off of three 9 volt batteries, and will produce enough heat to keep the craft above 0 degrees Celsius for 3-4 hours. 2.5 Geiger Counter (Experiment) Air density is directly related to the flux, a concentration of particles over an area during a certain amount of time. As the primary particle, usually a proton from the sun, hits the atmosphere, it goes through a number of collisions that makes it release energy. As it drives deeper, it loses the amount of energy needed to produce secondary particles (alpha, beta, gamma, meuons, and pions), most of which are beta particles or high-energy electrons. These particles can also make collisions with air molecules and form additional secondary particles but soon run out of energy as well. This causes a huge shower of particles on an infinitesimal scale. Our goal is to show how atmospheric radiation and altitude are related. 2.6 Coronal Discharge Mitigation There is a danger of coronal discharge on project HAIRS because of high voltage in the Geiger tube kit. The Geiger tube consists of high voltage components and low voltage components. While in operation, the Geiger Muller tube along with some other components will have a voltage potential across it. While this is not a problem at low altitude because of the Team AFROS Page 9 of 21

10 insulating air it becomes of some concern at the altitudes at which we will be flying. The problem comes from the fact that electronics at low altitude depend on the natural insulation provided by the air to prevent static and coronal discharge. However, at high altitude this natural resistance decreases, so a relatively low voltage has the potential to discharge. A coronal discharge occurs when a high voltage source causes the surrounding gas to become ionized end become a highly conductive plasma. This effect can disrupt circuits and any other electrical device nearby. Our solution to this problem will be an application of a clear acrylic conformal coating to the surface of the tube and all other high voltage components of the Geiger counter kit. This will add extra insulation and will help to mitigate any unwanted electrical phenomenon. The application of this coating will be as easy as applying it to the tube with a brush and allowing it to dry or cure. Most conformal coatings are rated for a certain voltage per millimeter before they fail. Additional protection can be given by isolating the Geiger subsystem with a cardboard box, but a healthy application of conformal coating is all that is needed. 2.7 Subsystem and overall system requirements Overall System Requirements Satellite structure shall be made of foam core and remain structurally sound after impact o Foam core seams shall be sealed with aluminum tape o Testing shows reliability of design upon impact of ~20m/s All subsystems shall remain functional from lift off to landing o Through testing and determination of appropriate battery power and life span. o All high voltage sources shall be properly insulated, using acrylic conformal coatings, to prevent against coronal discharge and arching Satellite shall be attached to the balloon tether o Attachment will be by passing the tether through the center of the satellite and tying it off at either end using non-abrasive bushings. o Tether will be enclosed by a non-abrasive, non-conductive tube. Temperature inside the satellite shall not drop below zero degrees Celsius for the entire flight o Through the use of ceramic resistive heaters powered by three 9 volt batteries and foam insulation. Interior and exterior temperature shall be measured and recorded o A HOBO H and temperature probe shall be used Internal humidity levels shall be recorded. o A HOBO H will be used for measurement and recording Altitude and assent/decent rates shall be obtained from the EOSS data Project shall not exceed 775 grams Images collected shall include the horizon, the balloon, and the earth o By rotating our camera through 180 degrees using servos, a timing circuit and three clear plexi-glass windows cut in the top bottom and side of the housing. o Servo timing and position will be controlled through the use of a basic stamp and timing unit o Servo will be powered by a NiCad battery Team AFROS Page 10 of 21

11 There shall be an American flag and Team AFROS contact information on the satellite. Total cost shall be below $300 Subsystems Geiger equipment Shall be kept above 0 degrees Celsius for the duration of flight Shall interface with the basic stamp Shall be rigged to collect data to allow for recording of data within the memory parameters of the basic stamp Shall survive shaking and stress experienced in flight and during burst Shall be protected from coronal discharge with conformal coating Heating Shall be powered by three 9v batteries in series Shall heat the craft to a temperature above 0 degrees Celsius for the duration of flight Optics Shall be kept above 0 degrees Celsius for the duration of flight Shall take a picture every 120 seconds. Shall be interfaced with the stamp and properly secured for still photography Internal Control System Shall be kept above 0 degrees Celsius for the duration of flight Shall interface with the basic stamp s programming Shall operate cooperatively with the timing of the camera Shall power the servo a maximum of 120 movements and with a 4.8V, 250 milliamp NiCd battery pack The servo shall finish in a fixed position (with the camera pointing out a window) on the 120 th movement Basic Stamp Shall be kept above 0 degrees Celsius for the duration of flight Shall operate on a 5.6V power source for the duration of flight, 4 hrs Shall record TTL pulses from Geiger subsystem at regular intervals Shall command the servo subsystem movement 120 subsequent times Team AFROS Page 11 of 21

12 2.8 Illustrations Team AFROS Page 12 of 21

13 Functional Block Diagram 2.9 Final parts list EOSS Camera SERVO ad SERVO battery HOBO data logger Geiger counter Heater 4 9V batteries Basic Stamp Mounting bracket for Camera servo integraton Three acrylic windows Team AFROS Page 13 of 21

14 3.0 Management 3.1 Current Schedule(last update 4-16) 2/14 RFP due (Accomplished) 2/16 Conceptual Design Review due (Accomplished) 2/20 Order parts (Geiger counter, etc ) (Accomplished) 3/02 Design document revision A due (Accomplished) 2/27-3/07 Work on internal temperature system, and all its aspects. Also work on skeletal structure of the Balloon Sat and begin camera integration DROP TEST over the weekend. (Accomplished) 3/11-3/18 Assemble Geiger Counter system with stamp: Testing if possible. (in progress) 3/15-3/24 Camera and servo integration and testing Have all components built(in progress) 3/23 Critical Design Review due Design Document revision B due (Accomplished) 3/27-4/02 Spring Break! 4/02-4/07 (Teem meetings every day during this period) Project integration of all subsystems and fix flaws: 4/07 COLD TEST #1 and #2 (Accomplished) 4/06-4/12 Extreme testing phase: Whip test, stamp (Team meetings held every day during this integration test, servo operation test. Work period) on Rev C (Accomplished) 4/15 Phone call made to HKP Systems Team lead requesting 60 grams from their allotted mass due to Project HAIRS overweight nature 4/15 Camera mounting and final testing of camera system 4/17 Revision C completion and team meeting /17 HKP SYSTEMS CALL RECEIVED at 2048 informing us of back out on initial mass agreement made friday 4/18 Team meeting giving the project final polish 4/18 Design Document rev. C (Accomplished) 4/19 EVERYTHING NEEDS TO BE DONE Team AFROS Page 14 of 21

15 4/20 Launch Readiness review (TBC) 4/21 Balloon Sat due by 1330 DLC 270A (TBC) 4/22 LAUNCH (TBC) 5/02 Analysis and Final Report (TBC) TBC stands for: to be completed 3.2 Division of Labor David Ferguson Team Lead, Electronics, and Soldering Duties include organization of team meetings and operations, team member assignments, team relations, electronics and circuitry, BASIC stamp programming, and design document/presentations. Colin Miller Optics Design and Servo Integration Duties include Basic stamp programming, servo mounting, camera timing and Acrylic windows (design, construction, and testing), design document/presentations. Matthew Zelenok Soldering and Budget Duties include budget management (Mass and Money), soldering and assembly of circuit components (Geiger counter and BASIC stamp), heating/cold test/environmental design, and design document/presentations. Jesse Sultanik Testing and Assembly Duties include design of testing plan and procedures, general assembly of project, and design document/presentations. John Stark Structure, Foam Core, and Mechanical design Duties include foam core design and construction, structural design and mechanical features, and design document/presentations. 3.3 Organizational chart David Ferguson: Team leader, Systems Engineer Colin Miller Remote Sensing and Servo Integration Matt Zelenok Budget and Environmental Control John Stark Structures Jesse Sultanik Construction and Testing Team AFROS Page 15 of 21

16 3.4 Team information Member Duties Qualifications Contact info David Ferguson Electronics Integration (Team leader) - In charge of electronics and computer interfacing. Organizes and delegates tasks to keep team on schedule. Matt Zelenok John Stark Colin Miller Jesse Sultanik Environmental Design - In charge of system integrity that may be compromised by environmental factors. Has the biggest time crunch with heating subsystem (required to complete cold test). Also in charge of budget. Structures - In charge of shell and mechanical design of satellite. Responsible for eliminating design flaws. Will coordinate whip and drop tests. Remote Sensing - In charge of servo/camera subsystem. Reports to structures and electronics with subsystem parameters. Fabrication/Construction Lead - Head of construction and assembly. Also heads final testing of satellite. Limited experience in many programming languages including: Java, HTML, C++. Great leadership skills. Experience with electronics and soldering, as well as construction and wiring Extensive experience in mechanical design. Technical experience with machining, carpentry and wiring. Construction and technical design experience. David.a.Ferguson@colorado.edu Cell- (719) Matthew.Zelenok@colorado.edu Cell- (719) jpbstark@comcast.net Cell- (303) Colin.Miller@colorado.edu Cell- (970) Jesse.Sultanik@colorado.edu Cell- (914) Team AFROS Page 16 of 21

17 4.0 Budget 4.1 Mass Budget Quantity Article Mass (Each) Mass Total 1 Geiger Counter HOBO Data Logger Basic Stamp Camera Heating Element N/A Foam Core/ Structure Acrylic Window N/A Wires and Switches N/A Aluminum Tape/Insulation v Battery Futaba Servo Futaba Servo Battery Total Mass Monetary Budget Quantity Part Price Cost Acquisition 1 Geiger Counter $ $ Mail Order* 1 HOBO Data Logger Supplied $0.00 Supplied (Class) 1 Heating Element Supplied $0.00 Supplied (Class) 1 Foam Core Supplied $0.00 Supplied (Class) 1 Timing chip Supplied $0.00 Supplied (Class) 1 Basic Stamp kit(2 OEM style) $35.00 $35.38 Mail Order* 1 Acrylic Donated $0.00 McGuckin s 1lb Dry Ice $24.00 $24.00 Safeway N/A Film and development $7.00 $7.00 Safeway 3 9V Battery Supplied $0.00 Supplied (Class) 3 9V Battery $6.00 $6.00 Wal Mart 6 23A Battery Supplied $18.00 Supplied (Class) 1 Camera Supplied $0.00 Supplied (Class) N/A Wiring and Switches Supplied $0.00 Supplied (Class) 1 Futaba Servo $16.96 $16.96 Mail Order* 1 Futaba Servo Battery $20.00 $20.00 Mail Order* N/A Insulation Supplied $0.00 Supplied (Class) 1 Exacto Knife $2.69 $2.69 Ace Hardware 1 Silicone Rubber Cement $4.85 $4.85 Ace Hardware 1 Carpenter Square $6.47 $6.47 Ace Hardware 1 Aluminum Tape $4.25 $4.25 Ace Hardware 1 Exacto Blades $2.51 $2.51 Ace Hardware Total Cost: $ Team AFROS Page 17 of 21

18 5.0 Test Plan and Results Drop Test Satisfies the weight of the satellite with simulated mass Impacts at the speed of a general balloon landing. o Box must not experience heavy damage. o Box must remain intact. Results Survived physically. Impacted at 10mph more than the landing estimate of 30mph. *Reinforcement of the corners recommended. *Balance of the payload important. *Securing of payload to prevent crush damage important. Cold Test #1 A and B Tested with dry ice in a external cooler and a sealed(heater only). Satisfies heating subsystem requirements only. Heater shall operate for the duration of the cold test. Expected Results Box will remain above 0 degrees Celsius for the duration of the cold test from the given system. If box passes (remains at the temperature requirement) for the duration of the test we will move on to a cold test with all other equipment able to operate at 0 degrees Celsius or higher. Actual Results Stayed warm for 1.5hrs only The first test used a single battery, and the second used three batteries Problem located in the method of testing. The satellite box was in direct contact with the dry ice. This shows that even in direct contact with the dry ice that a 3 battery heater will work for some time. However, if the box was exhibiting conductive cooling at the altitude of flight the heater and insulation would have to be much more powerful. OVERALL: semi-success C1 is the hobo inside the box C3 is the temp outside (the probe was moved to distinguish it at 1900hrs) Team AFROS Page 18 of 21

19 Mission failure at hrs after test initialization however we believe failure was due to the box location directly on the dry ice. Cold Test #2 Tested with dry ice in an external cooler and a sealed (heater and parts). Satisfies all subsystem requirements. Heater shall operate for the duration of the cold test. Expected Results Box will remain above 0 degrees Celsius for the duration of the cold test from the given system. This will show that the equipment can operate in the cold environment given. Actual Results Showed operation of all of our equipment throughout the entire flight OVERALL: Success Whip test Box will be constructed with the string passing through its center. Whip test will be performed to ensure no structural failure or cutting of the cord occurs Expected results The box will remain intact during the whip test. The string will not be cut or fall off during the whip test. Actual Results The box and components remained strong and attached during whip tests OVERALL: Success Subsystem Testing Tested to show all systems function properly. o Camera subsystem rotates properly and takes pictures at the correct intervals. o Stamp interfaces with servo system and Geiger counter subsystem. o All equipment operates as expected. Expected Results All equipment functions to our desired parameters, or it is fixed so it can do so. Generate the sample length the stamp must take to record Geiger counter data. Actual Results Using the pulsout command in pbasic, the servo rotates to three angles and pauses there to take a picture. The pulsin command reads a length of pulse the Geiger counter outputs when radioactive particles are detected. This is then stored into the current selected EPPROM location of the stamp in accordance with a time frame reference. This allows the number of readings to be stored and then compared to a time reference. This yields a count per min type variable, which can then be linked to rads and rem with a few simple arithmetic conversions. OVERALL: Success Team AFROS Page 19 of 21

20 Integration and Mission operations test The subsystems will than be assembled and integrated into constructed box. Following this all systems will be enabled and observed over a simulated mission length. Expected Results All subsystems will remain functional after integration and the activation switches will work as intended. A successful mission will be simulated. Actual Results Testing of the entire satellite-basic stamp showed a 5.0 second interval between pictures taken and a 26 second interval between pulses recorded in the basic stamp program. These intervals will allow for conversions into rads or other measurements of radiation. Overall: Success 6.0 Expected Experimental Results Radiation As altitude increases levels/severity of radiation should increase as well (due to decrease in atmospheric density) Alpha and beta particles are more potent in higher levels of the earth s atmosphere Should result in rough exponential curve as a function of altitude Relative Humidity Relative Humidity is expected to vary as altitude increases. Note: RH inside the box will be greater than surrounding atmosphere due to higher temperature inside, and the seal inside. Pictures Recover photographs of Earth, Balloon, and Horizon from various altitudes The temperature of the flight should show a bell shaped curve with temperature decreasing until the tropopause, leveling inside the tropopause, and increasing warmer in the stratosphere. The warming in the stratosphere is due to the absorption of UV light by the ozone layer. Because of this phenomenon we expect a drastic drop in temperature until the tropopause where the temperature will flatten out and then begin warming while the balloon satellite is in the stratosphere. The radiation levels measured in the atmosphere should increase exponentially because of the flux of the upper atmosphere. As the atmosphere thins and density of the atmosphere declines radiation will increase. As a high energy particle hits the upper atmosphere it decelerates and scatters into numerous particles in a shower of radiation. The ozone and other molecules protect us from this otherwise harmful source of radiation. Because of this, we expect an increasing amount of high energy gamma, beta, and alpha particles during our ascent; and a decreasing frequency of these particles in our descent. Team AFROS Page 20 of 21

21 7.0 Launch and Recovery The following is an itemized procedure preceding satellite turn in 1. Program HOBO to launch at the appropriate time 2. remove protective blue covering on satellite windows 3. mount all items in the satellite with acrylic adhesive 4. replace all four 9V batteries in the satellite power subsystem 5. replace camera battery 6. load new roll of forty exposure film into camera 7. check all soldering joints to ensure secure fastening 8. verify all electrical connections 9. Seal box and surround with aluminum tape to allow for additional structural integrety 10. Turn in The following is an itemized list of procedures to be followed on the day of launch 1. Box must be verified ready to go 2. Turn on heater switch 2min before launch 3. Turn on servo/geiger counter subsystem switch 4. Launch w/o dropping All members will be required to attend launch regardless of circumstances Attachment and release The satellite will be attached be passing the line through the box by using the provided nylon tube, and knotting the line at either end and using paper clips to secure the box to the line. This should be done be at least two people to ensure that the box is not dropped and nothing is damaged in the process. Our best handler will than hold the box and deploy it during launch. Prior to launch it is his ultimate responsibility to see that both external switches are flipped and the box is fully powered. During launch the handler will run to keep up with the rising balloon letting go of the satellite. This will make sure the box doesn t drag on the ground and suffer damage on launch. Recovery Recovery of the satellite will be only involve retrieval of the box and a quick external assessment of damage. The box will also be powered down by turning off both external switches and the box will be quickly opened to check for internal damage. All data will be off loaded and processed upon return to CU Boulder. Team AFROS Page 21 of 21