spacegrant.colorado.edu€¦ · Web viewThis experiment will also allow our team to discover the functionality of a monocular lens as a telescope in near space. Moreover, we aim

Colorado Space Grant Consortium

GATEWAY TO SPACE FALL 2006

DESIGN DOCUMENT

Team Hubble Jr.

Written by: Holly Zaepfel, Rachel Small, Kyle Norman, Ryan Del Gizzi, Chris Everhart, Evan Levy

October 9, 2006Revision A

Gateway to Space ASEN/ASTR 2500 Spring 2006

TABLE OF CONTENTS

1.0 Mission Overview...............................................................................................................32.0 Design.................................................................................................................................43.0 Management.....................................................................................................................104.0 Budget...............................................................................................................................125.0 Test Plan and Results………………………………………………………………...….13

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1.0 Mission Overview

Primary Mission: The primary mission of Team Hubble Jr. is to use a photometer to measure the

intensity (frequency in wavelength) of surrounding light as the atmosphere gets thinner, thereby demonstrating that the intensity of light present varies with altitude. We also hope to recover data pertaining to temperature and humidity from our HOBO data logger as to see the relationship between these factors and the levels of the atmosphere.

Secondary Mission: To successfully integrate a small field telescope with a video camera, therefore

providing our team with video footage from which we can obtain close-up, clear pictures of the horizon. This experiment will also allow our team to discover the functionality of a monocular lens as a telescope in near space. Moreover, we aim to acquire still images of the horizon with a film camera.

We are designing our balloon satellite to operate primarily as a light analysis device and secondly as a near-space telescope and image capture platform. Additionally, we will capture both external and internal temperature readings. Our primary experiment will use a TSL230 Photometer that converts detected light frequencies into voltage values that can be recorded onto the BASIC Stamp 2 memory for later extraction and plotting. This will offer data about the atmosphere remaining around the satellite as altitude changes by measuring the level of light scattered by air molecules and upper atmospheric dust particles. For our flight we will have the detected input light diffused through an opaque ping pong ball. We chose the TSL230 Photometer because of its versatility, low cost, and stable operation in varying temperatures.

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2.0 Design

The outer shell will be constructed from foam board in the shape of a cube. Hot glue and aluminum tape will be used to securely hold the edges of the cube together. The inside of the cube will be lined with insulation for two purposes. The first reason is to insulate to satellite from the extreme cold of the upper atmosphere and keep the electronics inside the satellite warm enough to function properly. The second reason will be to help protect the sensitive electronics during the most violent conditions of the satellites flight, balloon burst and landing. Batteries will be carefully placed after everything else has been integrated in the satellite in order to balance the center of mass as close to the flight string as possible. Each subsystem will operate independently of each other to prevent the “Christmas light” effect and a complete mission failure. All components will be mounted either on perimeter walls or on separate pieces of foam board running perpendicular to the base and ceiling of the satellite. We will interface the flight string with the satellite via small diameter PVC tubing running through the center of the satellite. The PVC tubing will be held in place with threaded fasteners on the outside of the satellite with fender washers to help displace the forces from the flight string to the entire surface of the foam board.

Our primary experiment will be a light to frequency photometer that will measure the amount of sunlight exposed to it as the atmosphere becomes thinner. We will be using a TSL230 photometer manufactured by Texas Instruments. We expect that the thin atmosphere at 100,000 feet will reflect less sunlight than at ground level and therefore we should capture longer frequency data as the flight progresses upward. This data will be collected by a BASIC Stamp 2 Microcontroller that is programmed to convert the voltage frequencies received into numerical “messages” that can be plotted with respect to time.

The telescope system will be composed of two primary pieces of hardware. The first will be the telescope itself, which given the total weight limit of our satellite, we will use a light-weight field monocular similar to what hunters and golfers use. The monocular specified has a 12X zoom capability and a field of view of 241 ft at 1000 yards. This will be coupled with the second component; a children’s miniature camcorder for video capture that has a 4X digital zoom capability. The total zoom will be 16X. This means that the captured view will be 16 times the size of what would be viewed by a human eye. The video camera has a resolution of 320 X 240 at 1.3 Mega Pixels. Our video recording medium will be a removable 2 GB SD Memory card to allow for continuous recording for as long as the camera’s battery will allow. We will need to test the limits of recording through our required testing procedures.

Our secondary imaging system will be composed of a still image film camera that will be operated by the Velleman 555 timing circuit; both are provided outside of our working budget. The timing between each still image capture will be approximately 3 minutes. This will provide 75 minute capture window as the camera will have a 25 exposure roll of film loaded.

Since most of our equipment operates on 3 volts, we may develop a master battery pack of 1.5 Volt AA batteries ganged together in sequence to provide that voltage to all items that need it. We will also need to provide a steady 9 volt power supply to the microcontroller and photometer that should be independent of the heater circuit.

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SUBSYSTEM AND OVERALL SYSTEM REQUIREMENTS

In our primary experiment, we will have to program the microcontroller to operate and collect data from the photometer. This is accomplished by using Parallax’s BASIC Stamp Editor Software (version 2.2.6) to write the source code, compile, debug, and finally upload onto the microcontroller. We are also using a Parallax “Board of Education” programming circuit board with USB connectivity to a PC to perform the programming and uploading of data. The board belongs to one of the team members and is not part of the parts list or budget. This will also serve as the means of connection to extract the captured data after the satellites land. Here is a preliminary version of our source code:

' {$STAMP BS2}' {$PBASIC 2.0}

TSL230 CON 0light VAR WordLOOP:COUNT TSL230,100,lightDEBUG HOME,DEC5 light, CRRETURNPAUSE 1000GOTO LOOP

We will need to experimentally determine how long to set the PAUSE based on the total available memory after the source code is installed. The current source code has the PAUSE set to 1000 milliseconds or 1 second between readings.

System Requirements: The Photometer system will require a constant 9 volt power supply and a toggle

switch to activate the microcontroller at the time of flight. The secondary experiment, as explained earlier, will use 3 volts to power the video

camera which will be provided by the onboard batteries ((2) 1.5 volt AA). We will need to turn the camera on and start the recording prior to flight since there will be no other control other than what is built into the camera. We can check the zoom and adjust as necessary with the view finder screen.

The still image camera system has on board battery power for the camera itself, and the timing circuit will require 12 volts from the battery pack that was included at assembly.

The weather monitoring system (HOBO) will use on board battery power. Thermal Protection System (Heater) will use on board battery power.

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PARTS

Item System QuantityFoam-Core Structure 2Length of aluminum tape Structure 1ELPH Still Camera Still Image (Primary) 1Velleman 555 Timer Circuit Still Image (Primary) 1Film for Camera Still Image (Primary) 2HOBO H08-004-02 Data Logger Weather 1Temperature sensor leads Weather 2Heater Circuit Assembly Thermal Protection 19 Volt Batteries Thermal Protection 3Unit of insulation Thermal Protection 1TSL230 Photometer Assembly Photometer 1Ping Pong Ball used as a light diffuser Photometer 1Basic Stamp 2 Microcontroller Photometer 1Winchester Model WM-1225 12X25 Monocular Telescope 1VCamNow children’s camcorder Telescope 12Gb SD Memory Card for video capture Telescope 1Master Power Switches Power System

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DRAWINGS

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FUNCTIONAL BLOCK DIAGRAM

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1 3.0 Management

ORGANIZATIONAL CHART

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Team Hubble Jr.

Holly & Rachel(Team leads)

Ryan & Kyle

Chris

Budget Scheduling

Evan

Testing manager Launch program, FFR

Injury prevention, safety

Launch day sequence

Hardware manager

Cube design/assembly

(Structure System)

Video Camera/ Telescope System

Photometer System

Organization and management

Document integration

Building and Testing

Weather (HOBO) System

Secondary Still Image System

Primary Still Image System

Power System

Thermal System


SCHEDULE

September 21st: CoDR presentation due 22nd: Team meeting, 11:30am 28th: DD Rev A assigned 29th: Team meeting, 11:30am

October 6th: Team meeting, 11:30am, begin purchasing and ordering hardware 9th: DD Rev A due 13th: Team meeting, 11:30am 17th: Begin construction of BalloonSat, CDR presentation due, DD Rev B due 20th: Team meeting, 11:30am, work on construction 22nd: Team meeting, work on construction 25th: Subsystems test 27th: Team meeting, 11:30am, Drop and Whip Tests 30th: Cooler Test

November 1st: Stair Test 3rd: Team meeting, 11:30am, test final design 9th: LRR Cards due, DD Rev C due 10th: Team meeting, 11:30am 11th: LAUNCH DAY!!! 17th: Team meeting, 11:30am 24th: Team meeting, 11:30am 26th: Team meeting 30th: DD Rev D due

December 4th: Final team meeting 5th: Final presentation due 9th: Design Expo 12th: Hardware turn – in and reimbursements

Time limitations: In order to ensure that enough time is allotted for testing, the construction and integration of all components and systems will need to be completed as soon as possible. By following the above schedule and making proper use of in class team time, our group should experience minimal time constraints. Due to the earlier launch date this year, the satellite construction and testing will need to be completed in a shorter time period than what is usually allowed; therefore scheduling has been adjusted accordingly.

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4.0 Budget

Team Budget

Income Amount Allowance from CSGS and EOSS $275 Total income $275

Expenses Cost PercentVCamNow Camcorder $85 34.38%Winchester 12x25 Monocular $21 8.31%Tubing, washers, etc. $5 2.02%TSL230 Photometer $5 2.01%512 SD Memory Card $40 16.12%BASIC Stamp $49 19.75%Extra batteries, wires, etc. $25 10.08%Shipping $8 3.31%Film $10 4.03% Total expenses $248 100.00%

Total Expenses $248 Difference between income and expenses $27

Mass Budget

Components Mass (g) PercentFoam-Core 40.0 5.69%Length of aluminum tape 10.0 1.42%ELPH Still Camera, Velleman 555 Timer Circuit, Battery Case 175.2 24.94%

Film for Camera 20.0 2.85%HOBO H08-004-02 Data Logger 25.6 3.64%Temperature sensor leads 3.0 0.43%Heater Circuit Assembly 25.9 3.69%Three 9 Volt Batteries 140.6 20.02%Unit of insulation 15.0 2.14%TSL230 Photometer Assembly 3.0 0.43%Ping Pong Ball used as a light diffuser 1.0 0.14%Basic Stamp 2 Microcontroller 2.5 0.36%Winchester Model WM-1225 12X25 Monocular 74.2 10.56%VCamNow children's camcorder 150.4 21.41%2Gb SD Memory Card for video capture 1.0 0.14%Master Power Switches 15.0 2.14% Total Mass 702.4 100.00%

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5.0 Test Plan and Results

We will complete the following tests that will challenge our satellite. The first of the five tests is the Drop Test. The Drop Test will consist of a team member standing fifteen feet above the ground and dropping the completely operational cube to determine if the satellite can still function after the drop. The second test is the Cooler Test. During the flight our satellite will experience cold temperatures as it ascends. The satellite will be put into a cooler with dry ice for one to two hours. The Cooler Test will determine whether or not the satellite can withstand the intense cold of near space. During testing we will make sure to monitor the batteries. If new batteries are needed, we will test them with a voltage meter. The third test to be conducted is the Subsystem Test, which will determine the functionality of our telescope, digital camera, HOBO and photometer as individual systems. The telescope will give us a closer view of the horizon during the flight. The digital camera’s sole responsibility is to take still photos of the earth. The HOBO will measure internal and external temperature as well as humidity. Lastly, the photometer will measure how the intensity of light varies with altitude. If any of these subsystems do not function properly, additional tests will be administered following the correction of the problem. The fourth test is the Whip Test. The Whip Test requires us to attach a string to our satellite, and “whip” our satellite around on the end of the string. After the test is complete we will examine the structural integrity and check subsystems to see if they are fully operational. The fifth test will be an Image Test. To test the still and video camera systems we will do a simulation around the campus with the cameras operating. After a tour of the campus, we will check the video and still image data from the cameras and repair any problems that we are faced with. The duration of the 2GB SD memory card will be assessed at this time. An additional component to this test will be to ensure that the data from the video camera can successfully be uploaded to a computer. The final test will be the Mission Simulation Test. The purpose of the Mission Simulation Test is to ensure that the satellite can function as an integrated system. Data will be analyzed, and if any one subsystem is not functional, then necessary corrections and adjustments will be made.

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Documents

spacegrant.colorado.edu€¦ · Web viewThis experiment will also allow our team to discover the functionality of a monocular lens as a telescope in near space. Moreover, we aim