1. Space Debris Critical Design Review
Fall 2008 Rev A/B
Space Debris Critical Design Review
Cole Bostrom
Corey Godwin
Jonathon Kirchmaier
Emily Logan
Sean Murphy
Seanna Renworth
October 14, 2008

2. Mission Overview
Mission Statement: While ascending to an altitude of approximately thirty kilometers on November 15, 2008, the BalloonSat “Space Debris” shall capture images at five different angles with the timed deployment of a mirror cluster that shall consist of four mirrors attached to the end of a mechanical platform. During this process the internal temperature of the Balloon Sat shall remain above zero degrees Celsius and the internal and external temperatures shall be monitored by a HOBO inside the BalloonSat.

3. Mission Overview
The team hopes to discover if it is more effective to extend a platform consisting of mirrors outside of a satellite to gain pictures of the stars at multiple angles instead of arranging the mirrors inside the BalloonSat.
The BalloonSat shall take images at many angles of the stars. The team shall then identify the stars in the pictures based off of the position of the BalloonSat. If the team can successfully deploy a mechanical platform to gain pictures of the stars then the team shall be able to identify more stars than would have been possible without a mechanical platform.

4. Requirements Flow Down
Mission Objectives
Objective Requirements
System Requirements
To construct a BalloonSat that can ascend to an altitude of approximately 30 kilometers by November 15, 2008
The BalloonSat shall be fully tested and ready to launch on November 15, The BalloonSat shall be made of foam core, and weigh no more than 1000 grams. It shall be a rectangular prism.
The foam core shall be cut in the shape of a rectangular prism, and shall be secured with hot glue and aluminum tape. There shall be minimal edges that require glue and tape; the rest shall result from cutting and folding the foam core. The items inside of the BalloonSat shall not cause the overall weight of the foam core structure and the items to be over 1000 grams. The BalloonSat structure and all systems shall be tested for full functionality and ready to fly one week before launch.
To acquire pictures from five angles with a high enough quality that star formations can be identified
The BalloonSat shall capture images of the surroundings for a period of time during the flight using a Canon camera that shall be focused on four mirrors angled up, down, and to either side. The camera shall also have a view straight out from the BalloonSat. There shall be a filter between the camera and the mirrors to prevent ambient light from distorting the images.
The camera shall be turned on before launch, and shall be programmed to take pictures on an interval throughout the entire flight. These images shall be stored in a memory card and downloaded after the BalloonSat is retrieved.
To make a cluster of mirrors that can be extended outside the BalloonSat during flight
The mirrors shall be extended outside the BalloonSat itself 30 minutes in to the flight by a system of gears, a motor, and a motor controller. The mirrors shall be retracted 75 minutes after extension.
The mirrors are secured directly to the outer wall. The outer door of the platform shall be connected to and extended by two rails that are moved by plastic gears. The gears shall be turned by a motor. The motor shall be connected to a motor controller, which is connected to a carrier board and basic stamp. The basic stamp shall be programmed to deploy and retract the platform at the indicated times.

5. Requirements Flow Down
Mission Objectives
Objective Requirements
System Requirements
To keep the internal temperature of the BalloonSat above zero degrees Celsius
A heater that consists of three resistors shall be used to keep the internal temperature above zero degrees Celsius. The heater shall be turned on with a switch before launch and shall remain on throughout the flight. The entire inner surface of the BalloonSat shall be insulated.
The heater shall be made of three resistors connected in parallel. The resistors shall be connected to batteries and a switch that shall be positioned on the outside of the box for easier access. The insulation shall be cut to the proper size so that it can line the inner surfaces of the BalloonSat.
To measure the internal and external temperature of the BalloonSat
A HOBO Data Logger shall be used to measure internal and external temperature for the entire flight.
The HOBO has a sensor on it that will measure internal temperature, and a temperature probe that is connected to the HOBO shall protrude at least 2.5 centimeters from the BalloonSat to measure the external temperature. Both temperatures shall be recorded for the entire flight. The HOBO shall be programmed with a delayed start so that it begins measuring temperature when the BalloonSat is launched. The data shall be stored on the HOBO and shall be downloaded onto a computer after the BalloonSat has been retrieved.

6. Design

7. Design Switch Camera Camera Power HOBO logger
Camera Memory
Switch
Camera
Camera Power
HOBO logger
Temperature-internal and external
Humidity
HB-25 (9V battery)
Carrier Board
Platform Deployment Motor
Basic Stamp
Heater Power
(9V Batteries)
Heater 1

8. Mass and Money Budgets Item Cost (dollars) Foam core Provided
Insulation
Adhesive (hot glue, aluminum tape)
Heating System (1)
Canon A570IS Digital Camera (1)
HOBO H data logger (1)
Central tube for flight string (1)
Anti-abrasion bushings (2)
Batteries (9V and 12V)
Light Filter
Mirrors (4)
No cost
Gearbox (1)
$18.45
Plastic Gears (1 package)
$4.95
HB-25 Motor Controller (1)
$49.99
Carrier Board (1)
$19.99
Connector Cable (1)
$1.99
Basic Stamp (1)
$58.02
12 in. Plastic Hexagonal Bar (1)
$17.88
Spare Parts
Factored previously
Cost paid by GTS
$153.39
Cost paid by Space Debris
Total Cost
$171.27
Component
Weight (grams)
Foam Core (712.5 cm2)
125 g
Structure Adhesive
20 g
Mirrors (4)
50 g
Camera
220 g
HOBO
34 g
Heater (1)
23.1 g
Insulation (342.3 cm2)
Eyebolts (2)
5 g
Anti abrasion bushings (2)
Tube
10 g
Gearbox and gears
43.6
HB-25
76.6 g
Carrier Board and Basic Stamp
47.9 g
Plastic for rails
51.45 g
9V batteries (3)
184.4 g
12V battery
7.3 g
Switch (2)
11.4 g
Light Filter
Total Weight g

9. Design The BalloonSat Space Debris shall require:
712.5 cm2 of foam core
342.3 cm2 of insulation
Adhesives in the form of hot glue and aluminum tape
One heating system consisting of three 4 ohm resistors and three 9 volt batteries
One carrier board and basic stamp with one 9 volt battery
Two connecting cables
One HB-25
One simple gearbox
One tube for the flight string
Two anti-abrasion bushings with a diameter between 3.6 and 5.5 millimeters
One mirror cluster consisting of four mirrors
One plastic hexagonal bar
One HOBO H data logger and external temperature sensor
One Canon A570IS Digital Camera
Two switches
The spare parts are already included in the hardware listed
Light Filter

10. Schedule Week of September 22-28: Complete design and prototype 9-22
Conceptual Design Review 9-23
Week of September 29- October 5:
Acquire Authority to Proceed and order all hardware by 10-2
Begin building payload and payload systems 10-3
Week of October 6-12:
Structure tests begin 10-8
Drop test and stair test with simulated mass in balloonsat
Week of October 13-19:
Revise payload design, build modified structure, complete payload systems by 10-14
Critical Design Review, Review B due 10-14
Continue structure tests, begin systems testing 10-15
Whip test with simulated mass
Perform imaging tests with the platform and mirrors
After confirming full function of systems, perform whip test with platform retracted and extended 10-17
Week of October 20-26:
In-class demo of current BalloonSat 10-23
Begin cold tests and testing final design 10-24
Cold test will run for full flight time, to test the successful extension of the platform
Week of October 27- November 2:
Continue testing final design, complete all final minor modifications 10-29
Cold test final BalloonSat
LLR cards assigned 10-30
Week of November 3-9:
BalloonSat complete 11-3
In-class mission simulation test 11-4
Continue in-class mission simulation test, Review C due 8:00 a.m., LLR cards due in class 11-6
Week of November 10-16:
Pre-launch inspection and Launch Readiness Review 11-11
Final weigh in and turn in 11-14
Launch at 7:30 a.m
Week of November 17-23
Analyze data from mission in class 11-18
Begin Final Report 11-18
Begin reconstruction of BalloonSat 11-19
Week of November Fall Break
Week of December 1-6
Finish reconstruction of fully functioning BalloonSat
Final Team Presentation and report, Review D due 12-2
ITLL Design Expo 12-6

11. Test Plan
The team shall implement many types of tests in order to ensure the BalloonSat achieves all the requirements and objectives of the mission. The imaging tests shall be performed in order to verify alignment of the camera and focus with the filter. These tests shall be performed on the individual system as well as with all of the systems together so that it will be possible to test all the elements of imaging.
Drop, Whip, Dry Ice, System

12. Expected Results
The team expects to receive clear images of the stars from the perspective of five different angles
To acquire better images than would have been possible without an extendable platform.

13. Biggest Worries
Time! (Still not our friend)
Single point failure
Weight Budget