Team Wolverine

Tethered Satellite Dynamics at Separation Investigation

Topic An investigation into the effects of variable tip-

off rates on a tethered satellite pair’s dynamics upon separation

Institution University of Michigan Student Space Systems Fabrication Laboratory Space Research Building 2455 Hayward St. Ann Arbor, MI 48109

Faculty Advisors Professor Pete Washabaugh Associate Professor of Aerospace Engineering pete@umich.edu (734) 763-1328

Professor Brian Gilchrist Professor of Electrical Engineering and Space Science gilchrst@umich.edu (734) 763-6230

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Team Members Dhawan, Shubhika- (shubhika@umich.edu) Junior/Electrical Engineering

Gupta, Naveen- (gnaveen@umich.edu) Ph.D. candidate/Mechanical Engineering

Lawal, Adebimpe- (adebimpe@umich.edu) Junior/Mechanical Engineering

Lessack, Suzanne- (slessack@umich.edu) Freshman/Aerospace Engineering/Flight Crew

Saeed, Nauman- (nauman@umich.edu) Senior/Industrial and Operational Engineering/Flight Crew

Sandoval, Steve- (sdsandov@umich.edu) Senior/Aerospace Engineering/Flight Crew

Smetana, Ashley- (alsmet@umich.edu) Junior/Aerospace Engineering/Flight Crew Team Contact: (724) 355-7569

Vaiyapuri, Prakash- (prvaiyap@umich.edu) Junior/Aerospace Engineering

Wind, Rebecca- (rjwind@umich.edu) Freshman/Aerospace Engineering Woelk, William- (bwoelk@umich.edu) Freshman/Aerospace Engineering/Alternate Flyer

Faculty Advisor Signature:

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Table of Contents

0.1 Flight Week Preference ................................................................................................ 5 0.2 Advisor/Mentor Request............................................................................................... 5 1.0 Technical Description ................................................................................................... 5

1.1 Abstract ..................................................................................................................... 5 1.2 Background............................................................................................................... 5 1.3 Test Objectives.......................................................................................................... 7 1.4 Need for Microgravity .............................................................................................. 7 1.5 Hypothesis statement ................................................................................................ 8 1.6 Test Description ........................................................................................................ 8

1.6.1 Equipment .......................................................................................................... 8 1.6.2 Procedure ......................................................................................................... 12 1.6.3 Justification for follow up flight ...................................................................... 17

1.7 References............................................................................................................... 17 2.0 Experimental Safety Evaluation ................................................................................. 18

2.1 Safety Evaluation Table.......................................................................................... 18 2.2 Integrated Hazard Analysis Evaluation .................................................................. 20

3.0 Outreach Plan.............................................................................................................. 23 3.1 Objectives ............................................................................................................... 23 3.2 Website ................................................................................................................... 23 3.3 Audience ................................................................................................................. 23 3.4 Community Outreach.............................................................................................. 23 3.5 Press Plan ................................................................................................................ 24 3.6 Contacts/letters agreeing to work with us............................................................... 24

4.0 Administrative Requirements ..................................................................................... 24 4.1 Institution’s letter of endorsement .......................................................................... 24 4.2 Statement of supervising faculty............................................................................. 24 4.3 Funding/Budget Statement...................................................................................... 25 4.4 Flyer Eligibility....................................................................................................... 25

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List of Figures

Figure 1: TSATT structural model ..................................................................................... 6 Figure 2: Separation mechanisms for the LightBand system5 ............................................ 7 Figure 3: Latching mechanisms on satellite pair ................................................................ 9 Figure 4: Latch configuration on satellites ....................................................................... 10 Figure 5: Idea used to centrally control latches using remote actuated motor.................. 10 Figure 6: Tether deployer diagram ................................................................................... 11 Figure 7: Optical tracking cameras to be mounted to floor of C-9 to optimally cover area the satellites will move through ........................................................................................ 12 Figure 8: Orientations of test set ups ................................................................................ 14 Figure 9: a) The two TSATT satellites are connected inside the camera field of view, b) Initial rotation imparted, c) Separation of end masses and motion observed, d) Perform setup steps and start experiment over ............................................................................... 16

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0.1 Flight Week Preference Flight Group 4: July 6-15, 2005 Flight Group 5: July 20-29, 2005 Flight Group 6: August 10-19, 2005

Our first flight week preference is flight group 4. This flight week is not during our scheduled class period, and therefore would be easy to accommodate schedule wise. Flight week 5 is our second choice, for the same reason as listed above. Flight group 6 is our last choice because it is very late in the summer, and close to the time we are going back to school.

0.2 Advisor/Mentor Request We request that, if possible, we be put in contact with a mentor that is familiar with either tethers, motion capture systems, or both.

1.0 Technical Description

1.1 Abstract The Tethered SATellite Testbed (TSATT) project sponsored by the Air Force is based on a tethered satellite pair. This system will separate in space, remaining connected via a deployable tether. The behavior of this tether and the two satellite end masses upon deployment is unknown. Through a C-9 microgravity project, the team hopes to gain an understanding of tether dynamics in a weightless environment. A 1:4 scale of TSATT will be used with a tether length of approximately 1.5 meters. Various initial orientations and rotations will be induced, and the resulting motions recorded and evaluated. The motions experienced on the C-9 will be representative of the possible conditions experienced by the tethered satellite pair once released into space. Data collected from this experiment will be used to validate computer models and refine predictions of tether and end mass motion. The models acquired from testing in microgravity can be applied to any tethered satellite mission being launched.

1.2 Background The goal of the TSATT project is to investigate new rendezvous sensor technology being developed by the NASA Jet Propulsion Laboratory (JPL). TSATT provides the means by which JPL’s Autonomous Formation Flying sensor would be flight tested. The satellite pair will be launched on an expendable launch vehicle and separated from it via a LightBand system, which consists of redundant spring plungers, hinged leaves, and separation springs (Figure 1). The spring plungers will unlatch and rotate the leaves, giving them an initial spin. The separation springs will then push the halves apart and disengage the satellite pair from the launch vehicle.

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Due to the motion of the launch vehicle and the forces from the LightBand, TSATT may encounter variable tip-off rates at the time of separation from the launch vehicle. This rotation may generate unexpected tether motion. Prior investigations in tether dynamics focused on shuttle-borne tethered satellite motion1 and the effects of the dynamics between the shuttle and satellite2. As part of the OEDIPUS-C mission, ground based testing was done but under fully deployed conditions3. Unlike previous experiments, which required a space launch in order to investigate the dynamics of their systems3, testing in a microgravity environment on Earth will allow us to simulate the dynamics that the satellites will see in space and identify potential problems with the configuration design and operation of TSATT.

Figure 1: TSATT structural model Computer modeling of tethered systems has come a long way from the days when NASA first began investigating tether simulations4. Our team intends to use a motion capture system that generates a file of the objects’ motion in real time. This data would be compared with predictive models that are already used to simulate satellite/tether motion on orbit. These models will also be used to simulate the conditions attempted during the C-9 experiment. Besides providing a real-life validation of the simulation code, the experiment would highlight possible deviation from ideal behavior that could then be accounted for in an improved tether dynamics model. In the future, this model would be used to predict the orbital motion of TSATT with greater accuracy. In addition, possible dangerous orbital modes of the tether could be highlighted and prevented during the spacecraft’s development.

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Figure 2: Separation mechanisms for the LightBand system5

1.3 Test Objectives The main objective of the proposed experiment is to investigate tether dynamics of a tethered satellite pair during the separation period. Due to a varying tip-off rotation upon release from the rocket, a variety of initial conditions would be tested to maximize the amount of information that can be gained by this microgravity environment. The team is also currently working on a dynamics model. This model would be verified by conducting the microgravity experiment and comparing the test results to our predictions. The dynamics model will be updated with the test data and be applied to TSATT and future tether satellite projects. Along with verifying the dynamics model and investigating the tether dynamics of the system at separation, we also hope to test the end mass separation system TSATT will be using, as well as identify any additional variables that may contribute to unwanted motion in the tethered satellite system.

1.4 Need for Microgravity Testing the motion of a tethered satellite system and the tether dynamics it will experience requires the system be in a gravitational environment similar to space. By conducting this hands-on experiment in the microgravity environment, provided by the Reduced Gravity Office on the C-9, the team will be able to observe tether dynamics and update a model to predict motion in space of tethered satellite systems. In a gravity environment, the tether dynamics of the system cannot be properly modeled due to the effect of gravity felt by the tether. The tether is not free to move unconstrained with six degrees of freedom, and therefore it would not simulate the actual motion TSATT will experience. Only in a “weightless” environment will we be able to fully observe the motion of the tethered system and therefore obtain an accurate model of the tethered satellite. This model will not only be beneficial to the TSATT mission but also to any future tethered satellite mission.

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1.5 Hypothesis statement We hypothesize that in microgravity conditions the motion of the tethered satellite system will not be significantly different from orbital simulations of the system in space. We hope to numerically corroborate the predicted dynamics model we will generate. Any deviations from the expected behavior of the two satellites at separation will be useful in further refinements of this model which predicts behavior of tethered satellites in orbit.

1.6 Test Description

1.6.1 Equipment Tethered Satellite System- Two homogeneous end masses will be designed to represent TSATT. A 1:4 scale will be used when building the C-9 version of TSATT. This means approximate dimensions of the end masses will be 11.43 centimeters in diameter and 10.16 centimeters long. Since the team is mainly interested in the motion of the end masses and tether at separation, we do not need to scale the tether according to the rest of the system, as far as length is concerned. The tether deployer will contain approximately 3 meters of tether. A pin system will hold the two end masses together until a specified time, at which time the pins will be released, via remote control, and the springs mounted between the two satellites will impart a small force to separate the halves. This motion will be accompanied by an induced spinning. A passive reeling device will be employed to release the tether from a tether deployer system located within each end mass. Markers will be placed both on the tether and the end masses in order to track the movement of the system.

Imparting Spin- The two masses will be spun manually. This will allow our team to introduce random rotational modes and a limited amount of the translational motion. These randomly introduced motions can be measured by the tracking system. There could be various unpredictable rotational and translational modes of velocities present in TSATT after it has been released from the launch vehicle. Hence, we can impart the desired rotational mode for the study of tether dynamics and manual rotation renders us with a versatile choice of the orientations of the spins and tip off rates that can be imparted to the masses. Once microgravity is reached, a team member will impart a predetermined spin on the satellite system. To ensure that the manual spin does not impart undesirably large translational velocity so that the satellite pair remains within the motion tracking cameras’ field of view, various simulation spins will be performed on an air table (available in physics labs on campus) prior to flight.

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Separation Mechanism- Separation will be triggered with the help of a remote. Once the system is stabilized and has been given desired spin, the team can trigger the separation. The two masses will be hooked together with a pin mechanism (also called ‘spring plunger mechanism’). The mechanism will unlatch itself (thus releasing the two masses independent) with the help of release remote actuated motors. The separation velocity will be controlled by the spring plunger mechanism (these springs are initially in compressed state when the two masses are latched together). Once the pins are unlatched the springs will push the two masses apart. The latches will be pivoted on the pins in order to fit in the pin slots present on the other half of the mass. Figures 3 shows the 3D view of the kind of latching mechanism that will be provided. Figure 4 shows the cross-sectional view of one of the latching mechanisms and the positioning of the spring below the spring plunger mechanism. Figure 5 depicts the idea that will be used to centrally control the 4 latches (simultaneously) with the help of a single remotely actuated motor. Note that the figures below show the rectangular guides, but the shape can be chosen optimally based on the manufacturability.

Figure 3: Latching mechanisms on satellite pair

Guides (in blue) Rotating Latches

Slots for guides (in blue)

Slots for Latches

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Figure 4: Latch configuration on satellites

Figure 5: Idea used to centrally control latches using remote actuated motor

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Tether Deployment Mechanism- After the masses have been separated, they remain connected by the tether. The tether deployment mechanism will be similar to two pulleys mounted on the two masses with the tether rolled on the pulleys (as shown in figure 6). The kick-off force from the springs will result in unreeling of the tether from the pulleys. The later portion of the tether will have a passive damping mechanism so as to dampen out the kinetic energy of the system by the time the tether is completely unfolded. Passive damping will be something similar to the gluey kind of the behavior (something like insulation tape) of tether while it is being unreeled (this will be only towards the end of unreeling of tether). Thus based on some preliminary calculation (Conservation of Energy calculations) the length of tether that needs to be provided with passive damping can be determined. After the simulation study has been completed during flight the pulley can be rotated in the opposite direction with the help of lever (provided on the surface of the two masses ref. fig 6). With the help of suitable gear train based on the kind of time constraints the pulley can be made to rotate (by hands) fast enough to reel back the tether within the time that will be available between the two parabola flights.

Figure 6: Tether deployer diagram

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Optical Tracking- The team will be using an optical tracking system developed by Advanced Realtime Tracking GmbH. Reflective markers, of negligible mass, will be placed on both end masses and the tether. The cameras read the position of these markers and their orientation in a three dimensional frame. The cameras send the data to a computer that processes the position data in real time. From each test we run, we would obtain a file containing the motion of the satellites and tether for that specific test. This would give us many files that could easily be compared and used in predicting the motion TSATT will encounter. The cameras will need to securely mount to the airplane in order to cut down on vibration. Introducing vibration into the system reduces the accuracy of the readings. Camera placement is not defined as of yet. The team will continue to work with Advanced Realtime Tracking GmbH in order to determine the optimal positioning of cameras and reflective markers on the system.

Figure 7: Optical tracking cameras to be mounted to floor of C-9 to optimally cover area the satellites will move through

1.6.2 Procedure The end masses will be attached to each other and placed in the volume covered by the cameras. The cameras will be mounted to the floor, but the satellite system will be a free floating experiment. When reduced gravity is achieved, the cameras will begin tracking the motion of the small, reflective markers placed on the end masses and tether, and a team member will impart an initial spin to the system. The system will then be separated, and the end masses will begin to move away from each other. After the period of zero gravity is complete the system will be readied for the next test.

Preflight

The TSATT prototype will be constructed and a computer program/motion tracking will be implemented to predict motion of the satellite. To make sure that the equipment works properly and that there are no problems in the process, the prototype will be tested on an air table. This is, in a sense, a two-dimensional microgravity arrangement. Although this does not give an actual simulation of what happens in space, it will help ensure that our equipment works as expected. Tested equipment will include the separation mechanism, the tether deployer,

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and the camera system. This portion of the experiment is very important since it will give us an idea of how the prototype may react in microgravity. This pre-flight testing will help determine any adjustments that should be made to the equipment and better define the on-board testing plan of which rotations should be tested. The satellite experiment, as well as the team, will travel to Houston Ellington Field to perform the experiment. After final NASA inspections and final approvals, the experiment will be setup on board the C-9. The cameras will be mounted to the floor and arranged in such a way that it optimizes the field of view. After the setup, the take-off procedures need to be reviewed before take off. In flight Multiple orientations of the tethered satellite pair will be tested and recorded during periods of zero gravity to simulate the possible orientations the TSATT satellite will encounter during its mission. The rotational rates are approximate since the initial spin is imparted by a crew member; exact spin rates will be determined by the motion tracking system. For estimated of thirty parabolas or experiments per flight, a total of sixty have been planned with two different angular velocities. On the first day, the spin will yield an angular velocity of 0.25 rad/s spin rate. The second day will have thirty experiments with 0.30 rad/s angular velocities. These angular velocities were decided by scaling down the original TSATT system velocities. With five repetitions allotted to every spin orientations, it would provide efficient data per spin in cases where the initial spin may encounter a human error or equipment failure. The different orientations will show the effect of spin orientation on the behavior of the TSATT at deployment. There are two different spin rates to observe any significant difference in behavior with change to angular velocities.

Test Matrix Initial

Rotations Day 1 Day 2 0.25 rad/s * 5 repetitions 0.30 rad/s * 5 repetitions

0.25 rad/s * 5 repetitions 0.30 rad/s * 5 repetitions

0.25 rad/s * 5 repetitions 0.30 rad/s * 5 repetitions

x

y

z

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0.25 rad/s * 5 repetitions 0.30 rad/s * 5 repetitions

Random Tumbling 0.25 rad/s * 5 repetitions 0.30 rad/s * 5 repetitions

Spin System Axis 0.25 rad/s * 5 repetitions 0.30 rad/s * 5 repetitions

Table 1: In flight test matrix

Figure 8: Orientations of test set ups

y

z

y

x

z

Spin System Axis

y

y

x

z

z

y

z

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Sequence of Steps

Alti

tude

Time

a)

Alti

tude

Time

b)

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Figure 9: a) The two TSATT satellites are connected inside the camera field of view, b) Initial rotation imparted, c) Separation of end masses and motion observed, d) Perform setup steps and start experiment over

Alti

tude

Time

?A

ltitu

de

Time

c)

d)

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Post Flight Pack up experiment after two day experimental period and return to Michigan. The videos will be thoroughly studied and the data will be compared with and inputted into computer models to provide analysis to the TSATT development integration team. Articles will be submitted for print at local newspapers and on campus newsletters. An outreach program will be conducted and C-9 experience will be shared with the community.

1.6.3 Justification for follow up flight This is not a follow up flight.

1.7 References

1. Banerjee, A K; Kane, T R. “Journal of the Astronautical Sciences.” American Institute of Aeronautics and Astronautics 30 (1982): 347-365. 2. Misra, A K; Modi, V J. “Dynamics and control of tether connected two-body systems- A brief review.” International Astronautical Federation 25 (1982): 54. 3. Modi, V J; Pradhan S; Chu M; Tyc G; Misra A K. “Experimental investigation of the dynamics of spinning tethered bodies.” Acta Astronautica 9 (1996): 487-495. 4. Rupp, Charles C. “Early tether dynamics flight experiments.” Proceedings of the Second International Conference, Italy, 4-8 October 1987. 1988. 39-42. 5. Lightband: An Advanced Separation System for Payload Separation and Staging. July, 2004. Planetary Systems Corporation. October 17, 2005. <http://www.planetarysystemscorp.com/documents/2000523RevCBrochure.pdf>.

6. Lang, David D. “General 3-D animation techniques for tether dynamics.” American Institute of Aeronautics and Astronautics, Inc (1989): 194-199. 7. Liu, Tom; Richards, Bill. “Saturday Aerospace Workshops.” Michigan Space Grant Consortium. November, 2005.

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2.0 Experimental Safety Evaluation

2.1 Safety Evaluation Table Personal Protective Equipment • Safety Glasses

Personal Training Required Flight Manifest Lessack, Suzanne- Flyer, no prior experience

Saeed, Nauman-Flyer, no prior experience Sandoval, Steve-Flyer, no prior experience Smetana, Ashley-Flyer, no prior experience Woelk, William- Alternate Flyer, no prior experience

Experiment Description & Background

The TSATT project is independently performed in cooperation with the U.S. Air Force, NASA Jet Propulsion Laboratory (JPL), and Tethers Unlimited Inc. (TUI). The Student Space System Fabrication Laboratory (S3FL) at the University of Michigan is designing the tethered TSATT satellite. Two end masses will be connected by a one kilometer long tether that will deploy and retract as part of the mission. The variation of the initial tip-off rotation induced at separation from the rocket poses concerns to the TSATT team due to unknown tether dynamic possibilities. By testing a scaled down model of TSATT in a microgravity environment, with different initial rotations, the team will be able to better define its mission and design and be prepared in the event of a variance in the type of tip-off rotation experienced.

Equipment Description The two components of the TSATT will be manually put to spin in different configurations at zero g after which the tether will be deployed and the two end masses will separate. The goal of this team is to observe the patterns or behaviors exhibited by the spinning and the tether deployment in zero g. For further details please refer to the procedures for pictorial descriptions.

Structural Design The design will be modeled after TSATT. The structure will be made of light weight aluminum end masses, joined by a tether, and containing a tether deploying device. The system will also have a device that connects the two end masses (light-band type mechanism).

Electrical System All the cameras will need electrical connections. The separation device will use power supplied through batteries. A passive tether release mechanism will be used so power will not need to be supplied.

Pressure/Vacuum System

No pressure/vacuum system will be used in this experiment.

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Laser System No lasers will be used in this experiment. Crew Assistance Requirements

We require assistance in electrical supply connection on board the C-9.

Institutional Review Board (IRB)

This experiment does not involved human test subjects, animal test subjects, and/or biological substances.

Hazard Analysis Please refer to the Integrated Hazard Analysis. Tool Requirement Use of screw drivers may be necessary during initial setup, and small wrenches and screw drivers may

be needed in case of unforeseen problems with the satellites during flight. Diagnostic checking equipments like Flukemeter may be involved during experiment.

Ground Support Requirements

Pre-flight testing and possible repairs between two flight days may require some ground support.

Hazardous Materials No hazardous materials involved in this experiment Procedures Pre-flight:

The TSATT prototype will be constructed and a computer program will be developed to predict motion of satellite. A 3-D modeling program implementation could be an option for relaying information as a computerized model. Pre-flight testing on an air table will be performed before departing to Houston. During the allotted flight time, the prototype as well as the team will travel to Houston Ellington Field to perform experiment. After final NASA inspections and approvals, the setup will be placed on board the C-9. The cameras will be mounted accordingly, and final procedures will be reviewed before take off. In-Flight: The two TSATT components will be attached and manually rotated with different orientation spins at zero g. The tether will deploy and the two end masses will separate using a mechanical system that is triggered via remote control. The final step helps the team determine the likely TSATT behavior during spin and tether deployment. Post-Flight: Pack up experiment after two day experimental period and return to Michigan. The videos will be thoroughly studied and the data will be input into computer models to provide analysis to the TSATT development integration team. Articles will be submitted for print at local newspapers and on campus newsletters. An outreach program will be conducted, and C-9 experience will be shared with the community.

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2.2 Integrated Hazard Analysis Evaluation

Integrated Hazard Analysis

Date: 10/04/2005 Hazard Analysis of C-9 TSATT System Facility: C-9 Aircraft and Ellington Field, Houston Prepared by: University of Michigan C-9 Team Organization: University of Michigan Student Space Systems Fabrication Lab

Risk Assessment Code (RAC) Probability Estimate Severity Class A B C D I 1 1 2 3 II 1 2 3 3 III 2 3 4 4 IV 3 3 4 4

Risk Assessment Code RAC 1 = Unacceptable. Correct as soon as possible RAC 2 = Undesirable RAC 3 = Some what acceptable with Controls RAC 4 = Acceptable with Controls Severity Class I = Catastrophic-Death, several serious injuries or illnesses II = Critical-Serious injury or illness, may cause lost work day III = Marginal-Several minor injuries IV = Negligible- Minor injury or damage Probability Codes A – Frequent B – Probable

Approved by: ________________________ NASA Microgravity Office

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C – Occasional D – Remote –Unlikely to Occur Hazard Condition Cause Effect Disposition

before Controls

Controls Verification Disposition after Controls

Facility/C-9 Emergency Fire Personal injury, experiment and property damage

I/B/1 Emergency Notification Procedure. Back-up facility and power generators and lighting

Visitor Orientation I/D/3

General Personal Injury Slipping and tripping. Include other personal injuries.

Personal Injury III/B/3 All test equipments will be positioned out of the walking areas.

Follow NASA safety procedures and checklists.

III/D/4

Electric Shock Internal failure and exposure to electromagnets

Personal injury I/A/1 Equipment grounded. Pre-test small batteries. No exposed terminals. Fuse and breakers prevent high current from source.

Team will verify compatible voltage flow and make sure no terminals are exposed and wires are fixed and not moving.

I/D/3

Share Edges or Pinch Points

Do not remove or identify sharp edges

Personal Injury III/A/2 Sharp edges eliminated by design. Visual inspection before flight

Any non-removable sharp edges will be identified or marked prior to experiment.

III/D/4

Electrostatic Discharge (ESD)

ESD prevention surface, ground, and component handling

Personal, equipment damage

III/A/2 Equipment grounded.

ESD Mats. Test area is controlled

III/D/4

Incompatible Interface Inappropriate power supply to spring deployment mechanism or remote control.

Equipment Damage

II/C/3 Pre-test voltage to remote control and receiver from batteries

Inspection of interface, verify voltage supply are compatible

II/D/3

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Computer Safety/Software Safety

Not having anti-virus. Damage to computer data

II/B/2 Latest Anti-virus installed

Verify that latest antivirus controls are in place

II/C/3

Weight-Item Dropped Improper team operation

Equipment damage II/A/1 Follow lifting and carrying procedures

As per S3FL C-9 procedures and guidelines

II/C/3

Critical Equipment Expensive in terms of time and money

Equipment damage II/C/3 C-9 team members will handle equipment

Handled by the team members.

II/D/3

Operating Temperature N/A N/A N/A N/A N/A N/A Surface Temperature N/A N/A N/A N/A N/A N/A Leaks/Explosions N/A N/A N/A N/A N/A N/A Shatter-able Materials N/A N/A N/A N/A N/A N/A Toxic Chemicals N/A N/A N/A N/A N/A N/A Batteries Leak Personal Injury and

equipment damage IV/C/4 Small battery used and

enclosed in the system to avoid personal contact and equipment damage. Easily replaceable.

As per design IV/D/4

Radioactive Substances/Materials

N/A N/A N/A N/A N/A N/A

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3.0 Outreach Plan

3.1 Objectives Our outreach objective is to make the public aware of new space research being conducted by students on campus. The research our team is doing will contribute to future space missions that benefit many organizations. We will use this fact to inspire others on campus, in the community, and younger students to join the engineering and science community and join cutting edge research teams.

3.2 Website A website will be designed by the team. Our site will be linked to the Student Space Systems Fabrication Laboratory website as a “Current Project” listing.

3.3 Audience We will be addressing elementary and middle school students, Boy Scout troops, minority students, as well as the campus and local community.

3.4 Community Outreach In the spring of 2006, workshops will be held for middle school age students from the Lansing, Michigan area in cooperation with the Michigan Space Grant Consortium. These students come to the University of Michigan for three consecutive Saturdays. During these workshops, students learn about a wide variety of aerospace topics, including the aerodynamics of flight, rockets, and wind tunnels. Our team will help run these workshops and spend time discussing our project and the benefits of being able to simulate zero-g on Earth6. Power point presentations will be given, along with showing video of previous microgravity flights. We will demonstrate the deployment of our system using an air table, and we will rely on student interaction to demonstrate how our motion capture system works.

Also in the spring of 2006 we will be working with Peckham Industries, in Lansing, to increase the opportunities for the children of the employees, who are largely of a minority background. Every year they sponsor a rocket launch for the children. We will help run this event and give a presentation of our microgravity project along with the demonstrations mentioned above.

On campus we conduct recruiting events in the College of Engineering and the College of Literature, Science, and Arts. This consists of a booth with a poster presentation detailing our project and a mass meeting. Contacts are being made within the University of Michigan chapters of Sigma Gamma Tau and American Institute of Aeronautics and Astronautics (AIAA) in order to present our research to these societies on campus.

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The Michigan Space Grant Consortium is sponsoring a conference on October 22, 2005 at the University of Michigan in which we will present our proposed project. Another conference attended by students from our lab is the SmallSat Conference where they present the work being conducted in the lab over the past year. Our microgravity project is tied directly to our main project, TSATT, and would therefore be discussed at this national conference.

3.5 Press Plan We will be submitting a summary of our experience to the local paper that is distributed on campus and throughout the community. Articles will also be submitted to the department newsletters and circulated throughout the University. Departments that would be interested in our article include Aerospace, Electrical Engineering and Computer Science (EECS), and Atmospheric, Oceanic, and Space Sciences (AOSS). Announcement of the project will also be placed on the University of Michigan College of Engineering website.

3.6 Contacts/letters agreeing to work with us Please see attached letters.

4.0 Administrative Requirements

4.1 Institution’s letter of endorsement Please see attached letter

4.2 Statement of supervising faculty Please see attached letter.

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4.3 Funding/Budget Statement Equipment Unit Cost($) Units Contingency Total Cost($)Video Cameras* $ 1,000.00 2 15% $ 2,300.00 Separation Mechanism $ 250.00 1 15% $ 287.50 End masses $ 50.00 2 15% $ 115.00 Tether Deployer $ 100.00 1 15% $ 115.00 Tether $ 30.00 1 15% $ 34.50 Total $ 2,852.00 Transportation and Accommodations Air Travel $ 320.00 4 15% $ 1,472.00 Hotel $ 80.00 4 15% $ 368.00 Rental Car $ 580.00 1 15% $ 667.00 Shipping $ 50.00 2 15% $ 115.00 Total $ 2,622.00 Post-Flight Presentation Supplies $ 40.00 1 15% $ 46.00 Total $ 5,520.00 Table 2: Proposed Cost budget

*Note: Camera system may be rented for a month at 10% of the actual cost of the cameras.

Possible funding sources include TSATT through S3FL, MSGC, the University of Michigan College of Engineering, Women in Science and Engineering (WISE) program, and Minority Engineering Program Office.

4.4 Flyer Eligibility All flyers are US citizens and Undergraduates enrolled at the University of Michigan. All flyers are over the age of 18 and not participating in any other reduced gravity project.