Fall
08
Team: O
2 n Cloud 9
th
Fall 10

Mission Statement
The BalloonSat “Cloud 9“ will rise to an altitude near 30km in order to complete our mission. Our mission is to use this satellite to take 3D images of the clouds and measure the levels of oxygen in the atmosphere. We will use the pictures of the clouds and compare them to an oxygen sensor we have on board in order to indentify the effects of the density of oxygen on the formation of clouds.
Mission Objectives
1.
Construct a BalloonSat by 10/21/2010 that will reach altitudes of 30km
2.
We will measure the amount of elemental oxygen in the air using an oxygen sensor
3.
Take 3D images of surrounding clouds to compare the amount of oxygen to the type, thickness, and altitude of the clouds
Mission Overview
Through scientific discovery we have an explanation for how clouds are formed and what they are made of. We know the environment needed for clouds to form and what types of clouds produce certain weather. What we want to study is the level of pure oxygen that is needed for clouds to form and with our oxygen sensor we will be able to read how much elemental oxygen there is in the air. We can test and see if the level of pure oxygen in the atmosphere changes as we approach clouds and the various effects of oxygen levels on the formation of clouds, such as the effects of too much pure oxygen may have on the formation of a cloud. The other part of our experiment is to use 3D imaging in order to get a better idea of size and magnitude of the clouds. These images are going to be integrated into the other data so that we can correlate the amount of oxygen to the type, thickness, and altitude of cloud. The whole point of this experiment is just to explore the effects of oxygen on the formation of clouds and the various levels of oxygen and water needed for clouds to form.
Technical Overview
Structural – The structure of our BalloonSat “Cloud 9” is going to be in the shape of a rectangular prism. The structure will be about 30cm long, 10cm tall and 10cm deep. The reasoning behind the 30cm length will be explained in the optical section. The prism will be made out of foam core with aluminum tape and hot glue to hold the edges.
One side of our prism will be at an angle so as to allow our cameras to get a view of the top of the clouds. In order for our satellite to reach the target altitude we will be attaching it to a weather balloon by a nylon flight cord through an internal PVC pipe. We must also use insulation inside of our satellite because of the extreme cold temperatures reached throughout the flight. For this we will use a one-centimeter thick insulation glued on the interior of the structure and a heater. (The heater will be explained in the electrical part of the technical overview)
Optical – Part of our experiment is to take 3D images of clouds throughout the flight. We will be using two digital cameras in order to create an effect much like the eyes of a human to give us depth to pictures. The two cameras will be placed on opposite ends of our structure with 19cm in between lenses to give us the ability to have two
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different angles of the same object. We will be mounting them directly to the side of the structure and the lens will reach to the edge of the box so that only the lens will be flush with the side. The cameras will have an unobstructed view of the outside for a better quality image and we have decided against putting any form of window in between the lens and the outside. The effect of having an open-air design is that we have to protect our lenses from condensation. In order to stop water from condensing on our lenses we have to use an anti-fog agent.
Electrical – The heater that we will make in class requires three nine-volt batteries and these will be mounted on the inside of our structure. The heater will be placed in the structure so that the electrical components do not get colder than 263.15 K.
This subsystem is independent of all of the others and is only wired to a switch that is on the outside of our structure so that we can power it on and off.
The next subsystem we have to have power for is our HOBO data logger. This subsystem has an internal power source that will last for hours, but in order to make sure that it does not run out of battery mid-flight we will program it to delay the start of data collection until the launch. This system logs the data of outside temperature, inside temperature, inside relative humidity, and in our experiment will also log the oxygen level.
The oxygen sensor will be hooked up to a 4-20mA connection. The power of this system comes from two nine-volt batteries that will be mounted inside our structure.
The next subsystem is our cameras. These cameras will be wired together to one power switch so that they begin taking pictures at exactly the same time. The cameras have their own internal battery power and internal memory.
Hardware we need and where we plan to get it

Oxygen Sensor donated by In-Situ Inc.

HOBO provided by Gateway to Space class

Two cameras, one donated and one from Amazon.com
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2 4Gb cards from Amazon.com
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5 nine-volt batteries provided by Gateway to Space class
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4-20mA cable from HOBO Onset Corporation
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Plastic flight tube provided by Gateway to Space class
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Foam core provided by Gateway to Space class
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Aluminum tape provided by Gateway to Space class
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Washers and bolts for flight tube and rope attachment provided by
Gateway to Space class

Heater provided by Gateway to Space class
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Insulation provided by Gateway to Space class

Switches provided by Gateway to Space class
Illustration and Special Features of our Design
The team’s design includes two similar digital cameras side by side, which will allow for stereoscopic imaging and provide some sense of depth in the images of clouds obtained. The slanted side on which the cameras are mounted will allow the cameras to point downward toward the clouds in the troposphere for a longer interval. There is an
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oxygen (O
2
) sensor that will add oxygen concentration data to the rest of the data collected. These features allow for correlations to be drawn between humidity, oxygen levels, cloud appearance, temperature, and altitude.
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How we plan to turn our design into an actual satellite
The satellite will be comprised of two separate systems, one of which will collect qualitative data and one of which will collect quantitative data. In addition, we will have a satellite support system.
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Qualitative System: Optical camera system
The satellite will contain two cameras spaced apart at 19 cm, which will have a primary goal of capturing images of the clouds at various altitudes during flight. This separation distance is optimized in order to create a focal 3D distance of 17.7 m. The cameras will be integrated into the structure by means of a wedged insert that orients the device lenses down at an angle of 24 degrees. Each camera will contain 2 internal AA batteries that will provide power to the system. The camera firmware is also equipped with an internal timing system that will control the photo-sampling rate and an internal memory card for data storage. The simultaneity of image generation from the two cameras will allow a 3D image to be viewed by placing the two printed photos into www.start3d.com, which creates transition slides and then animates this. The focal distance and sampling rate accuracy will be tested prior to launch using the website to ensure clarity of the 3D images. If the 3D picture quality is not optimized, the camera distance within the box and internal timing system will be revised accordingly. An external switch located outside of the satellite structure will activate the system proceeding launch.
Quantitative System: HOBO data-logging system
The quantitative system consists of the HOBO data logger. This unit is equipped with internal temperature, internal relative humidity, and external temperature capabilities. The HOBO data logging system also includes it’s own internal power source. In addition to these given parameters, the team is also planning to record oxygen content of the atmosphere. In-Situ Inc will donate the oxygen sensor, called an RDO Pro optical oxygen sensor. The oxygen sensor is equipped with customizable 4-20mA output capabilities that are compatible with the HOBO data-logging device. This will be wired to the HOBO’s 4-20mA cable, equipped with specialized 10K ohm resistor to adequately control current input from the oxygen sensor. The system will also be wired to a 9V battery, which will power the RDO Pro device. The RDO Pro is equipped with a specialized current output control chip (datasheet: xtr 117) that regulates the current being sent to the HOBO device. If the sensor unexpectedly produces a current above
25mA, the output regulator will essentially deactivate the entire system. With a 10K ohm resistor in the system, the maximum voltage that can be obtained by the system is 2.5V, which is the HOBO allowed specification. Thus, the HOBO data-logging device is incapable of being exposed to an overvoltage due to the RDO Pro optical oxygen sensor.
The sampling rate of the HOBO and it’s corresponding sensors will be controlled using the HOBO software, while the oxygen sensor sampling rate will be customized using the
Win-Situ 5 software, provided by In-Situ Inc. The data will be collected and recorded within the HOBO data-logging device’s internal memory for the duration of the mission, and downloaded after landing for analysis using the provided HOBO software. The team will do a full testing analysis before launch to determine the overall functionality of the device, as well as the accuracy of the sensors. The system design will be modified accordingly to account for any errors. An external switch located outside of the satellite structure will activate the system proceeding launch.
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- Satellite Support System: Heating, insulation, and condensation
To ensure performance of both the qualitative and quantitative systems, an optimized environment will be achieved using the satellites internal support system. A heater will be provided to the team, consisting of an external switch for system activation prior to launch, and three 9V batteries to power the heating device during flight. Onecentimeter foam insulation will also be provided to line the satellite structure and maximize heat efficiency. A desiccant will be donated by In-Situ Inc. and placed inside the satellite structure to absorb moisture accumulation. Revisions to the internal heating system will be made if the target temperature of 263.15 K is not achieved.
Data Retrieval
Satellite data retrieval will be presented in both a qualitative and quantitative form. All data will be collected for the entire ascent and decent of the flight. For the qualitative analysis, the two installed cameras will take simultaneous images of the clouds during flight. The camera images will be stored in the internal memory card for the duration of the flight. After recovery, the images from both cameras will be printed and matched with the simultaneous image from the opposite camera. The fixed sampling rate during flight will allow the cameras to take images simultaneously, and at various altitudes along the flight path. The two matching images will be placed into a website, which creates transition slides and animates them. This 3D representation will give the team a qualitative analysis of the cloud density at various altitudes above the Earth. The quantitative data analysis will consist of numerical measurements using the various sensors attached to the HOBO data-logging device. Four sensors will be connected to the
HOBO including internal and external temperature, internal and external humidity, and oxygen concentration. All data collected by the sensors will be logged within the
HOBO’s internal memory system. After recovery, the data will be downloaded from the
HOBO’s internal memory to a computer using the HOBO software. The two temperature sensors will report data in the units of Celsius, and the humidity sensors in units of density.
The oxygen sensor however, will report the concentration of oxygen in units of voltage, due to the 4-20mA connection. The oxygen data will be converted from voltage to partial pressure of oxygen by application of Ohm’s Law V=IR. Using the known value of resistance R (10k ohm) and the measured voltage, the current can be found for each sample logged. The minimum and maximum current levels will be assigned a partial pressure of oxygen value using the Win-Situ software provided by In-Situ Inc. Thus, every current level on the scale from 4-20mA will correspond to a specific value of oxygen partial pressure, which will be computed using a simple algebraic ratio. Internal humidity readings will be evaluated to determine the efficiency of the moisture absorption system, and internal and external temperature readings will be compared to determine the heater efficiency.
How we will keep people from getting hurt
We will take a number of safety precautions during all construction times and tests. During construction, if we are using power tools we will wear safety goggles and make sure that all blades are kept away from hands. We will also be using exact-o knifes in our construction, so we will always make sure to cut away from ourselves and others so the knife doesn’t slip and injure someone. We will be implementing several different tests that have fairly standard safety precautions. One safety precaution that is essential is a warning system that the test is about to begin. The tester will ask if the other team
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members are ready, and upon confirmation the tester will loudly announce the name of the test and a countdown so all that are in earshot know the test is taking place and know to stand clear of the test site. A safe distance for most tests we will be performing is about a 5m radius. This safety radius however should be increased to about 10m for the drop test, noting that the wind might carry the test satellite or pieces could come off and injure someone. Other team members not performing the test will also watch for people passing by and make sure that they know that a test is taking place and to stay away from the test site. Another way to keep the team and others safe is to perform tests in a non-populated area. Basically the key to being safe during testing and construction is to not do anything foolish and use common sense, but having these safety procedures laid out ahead of time will also help ensure team and passerby safety.
Functional Block Diagram
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Testing of our design
There are several tests that must be done on our BalloonSat to ready it for flight.
Here we will give a description of each and how the data they give us will help ready our satellite for flight. During all of the tests that involve the structure strength we will simulate the mass by placing rocks or other weights inside.
The Drop Test :
One stage of this test is dropping our structure down a flight of stairs to simulate the impact on the structure as it hits the ground when it lands. This stage will tell us if our structure can withstand an impact that makes the structure roll across the ground. The second stage of this test is dropping it off a second story ledge to simulate the impact of the landing.
The Whip Test :
In this test we will attach a flight string to our satellite and swing it around in circles. This test will tell us two things, one if our flight string interface is strong enough to endure the forces that will be exerted on it from the fall back to the ground. It will also tell us if our structure can withstand the forces acting upon it when if falls, or if it will rip apart.
The Cooler Test :
In this test we will be testing our internal technology and our insulation to see if it will withstand the extreme cold of high altitude. We will place our satellite with all of our technological components inside a cooler with dry ice in it, turn on our satellite, and see if the internal temperature will stay above 263.15 K with our heater and insulation in affect. The satellite will stay in the cooler for about 30 minutes to simulate the estimated time that the satellite will be exposed to the extreme cold temperatures of high altitude.
Camera Test
In this test we will ensure that our 3D picture taking idea can work, and we will test all the software needed to make the 3D image. We will take our two cameras and put them about 19 cm apart and have them take pictures simultaneously. Our object will have to be about 17.7 meters or more away, since that is our estimate of how far away some clouds will be from our satellite in flight. Then we will take our pictures and test our software to make sure that the 3D image will come out, or if we need to adjust our camera distances to ensure a better 3D picture.
Oxygen Sensor Test
We will test our oxygen sensor by placing it in our satellite and see if it is taking readings. It will be placed in a sample of water to check for accuracy.
Full Mission Simulation :
We will also test our satellite as a whole, to make sure that all the components work together. This test will also show if all components work properly in our structure.
Item
Budget and Weight Overview
Cost Subtotal Purchase Location
Camera with 4GB card
O2 Sensor
Picture Print outs
$ 114.49
Donated
$ 5.00
$ 114.49
$ 114.49
$ 119.49
Amazon.com and shipping
In-Situ Inc
King Soopers in store photo printing .20 per picture
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Stereographic Viewer
4GB memory card
$ 41.95 $ 161.44
$ 29.99 $ 191.43
Resistor 10k Ohm 5 pack $ 0.99
4 to 20 amp cable with built in resistor
Total
$ 192.42
$ 25.00 $ 217.42
$ 217.42
Weight (g) Subtotal (g)
RadioShack
Onset
2 Cameras
HOBO
440
30
440
470
Pokescope.com plus shipping
Best Buy
Heater 100 570
Oxygen Sensor
Additional power
Foam Core
150
190
60
720
910
970
Aluminum tape
Flight tube
5>
5
975
980
Total 980
We shall keep our budget by minimizing the cost of all the supplies we require. This can be accomplished by shopping around to find the best value for the components we need.
Another step we will follow to avoid going over budget is by prioritizing, and going through an approval process for all purchases outside what is built into our budget and the management part of the team will control the purchasing power.
Organizational Flow Chart
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Lea Harris (612-730-3570) Lea.Harris@colorado.edu
- Team Leader and managing director of the teams, coordinating the team and helping in any of the building, structure, electric, or science teams.
Ian Barry (970-372-7883) Ian.Barry@colorado.edu
-Head of Structures team, designing the basic plot of the structure and the technical design of how to make our satellite fit to the double camera and multiple sensors.
Ben Woeste-(303-257-6931) Ben_woeste@yahoo.com
Head of the Optical team.
Researcher and head of the optical design team for the satellite’s 3-D picture data and constructing the plans for the space inside our box to put the cameras.
Brodie Schulze-(970-629-3832) Keegan.Schulze@colorado.EDU Head of the
Power Team. He will be controlling the research and construction of how the three sensors will be connected to batteries, the two cameras, and the thermal heater. One job will be helping the structures team to place the power components in the satellite.
Caitlyn Cooke-(530-249-2354) Caitlyn.Cooke@colorado.EDU Head of the
Electrical team that connects the Oxygen sensor to the HOBO sensors and the two cameras to the power. Caitlyn is also the main Software Head for the specialized sensor that requires special data retrieval.
Sebastian-Johannes Lorenz-(303-618-3160)
SebastianJohannes.Lorenz@colorado.edu
Head of the Thermal Crew. Designating where and how we wish to use the thermal temp controller. Designing the cold tests, and making sure each subsystem is safe while in flight.
Megan O’Sullivan- (832-656-9096) megan.a.osullivan@colorado.edu
Head of the Health/Safety and Science crew. Megan will be the safe keeper on hand, with help from Lea to control all possible injuries or stress factors. Megan is also the
Head of the Science Research to control our satellite’s main systems. This subject is the outer science research that will link all of the different crews together to construct the details of the satellite that don’t fall under the Electric, Optical,
Managing, Thermal, and Structural teams.
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Sep. 15 th 2010