1. The MAGIC Tether Experiment 15 July 2015 University of Colorado Friday, April 02, 2004 The MAGIC Tether Experiment A Demonstration of DINO’s MAGIC Boom

2. The MAGIC Tether Experiment 15 July 2015 Colorado Space Grant Consortium & DINO 2 The MAGIC Tether Experiment Special Thanks To the KC-135 Team for All of Their Hard Work and Great Contributions –Cook, Evan –Martinez, Mike –McArthur, Grayson –Mohler, Andrew –Parker, Jeff –Seibert, Mike –Stamps, Josh –Worster, Kate

3. The MAGIC Tether Experiment 15 July 2015 Colorado Space Grant Consortium & DINO 3 Background – DINO Nadir Pointing –Gravity Gradient Stabilization Deployable Boom –Primary Satellite »25 kg –Tip Mass »5 Kg –MAGIC Tether »Mechanically-Actuated Gravity- Induced Control »Stanley Tape Measure »6m Long –Lightband »2 +/-.5 ft/sec »Full deployment after 10 sec Tip Mass Tether DINO

4. The MAGIC Tether Experiment 15 July 2015 Colorado Space Grant Consortium & DINO 4 Why do This Test Is this System Even Feasible? –Dynamics of the Semi-Rigid System are Poorly Understood –Experimental Results of Energy Dissipation Over damping will result in inadequate deployment –Poor gravity gradient stabilization »Science objectives »ADCS power Draw Under damping would shock the system –Could damage Electronics and Cameras –Could recoil, causing a collision

5. The MAGIC Tether Experiment 15 July 2015 Colorado Space Grant Consortium & DINO 5 Expected Results The MAGIC Tether team expects the following things: –Four standard springs will accelerate the relative velocity of the tip mass with respect to the primary satellite to approximately 1.7 ft/s (0.518 m/s). –The tip-off rate of the deployment to be less than 1°/s in each axis. –Given a deployment velocity of 1.7 ft/s, the optimal value of x 0 to be approximately 0.66” to critically damp the system’s motion as the tether is fully deployed. –The semi-rigid tape to be deployed in a controlled fashion without any recoil at the end of its deployment.

6. The MAGIC Tether Experiment 15 July 2015 Colorado Space Grant Consortium & DINO 6 Experiment Objectives 1.To measure the large-scale and small-scale dynamics in the deployment Linear and angular accelerations 2.To empirically measure how the energy in the system can be dissipated Spring force in the slow-down mechanism Critically damp tip mass’ motion 3.To demonstrate a successful deployment of DINO’s MAGIC Boom

7. The MAGIC Tether Experiment 15 July 2015 Colorado Space Grant Consortium & DINO 7 KC-135 Heavy Sat –14.6 kg (32.2 lbs) Light Sat –8.1 kg (17.8 lbs) Tether –Two lengths of Stanley Tape Measure (1.0 in) –4 ft (1.22 m) Sensors –6 Accelerometers –6 Rate Gyros Equipment Containment System Overview of the Experiment Safety Straps Light Sat Heavy Sat Tether

8. The MAGIC Tether Experiment 15 July 2015 Colorado Space Grant Consortium & DINO 8 Structure The structure on each of the two satellites (Heavy and Light Sat ) is composed of two 1/8” 6061Al plates connected by 4”-tall 1/4" 6061Al box walls. All sharp edges will be covered with pipe insulation Damping System Foam Padding TAZ

9. The MAGIC Tether Experiment 15 July 2015 Colorado Space Grant Consortium & DINO 9 Heavy Sat Circular inner plate Male mating adapter TAZ Deployment springs Data loggers Dummy loads Sensors and batteries Containment box Hand holds Pipe insulation The Heavy Sat will have an overall mass of approximately 14.6 kg and dimensions of 18” x 18” x 6”. Data Logger

10. The MAGIC Tether Experiment 15 July 2015 Colorado Space Grant Consortium & DINO 10 Light Sat The Heavy Sat will have an overall mass of approximately 14.6 kg and dimensions of 18” x 18” x 6”. Circular inner plate Female mating adapter Spring Adapters Data loggers Dummy loads Sensors and batteries containment box Hand holds Pipe insulation Braking System Data Logger

11. The MAGIC Tether Experiment 15 July 2015 Colorado Space Grant Consortium & DINO 11 Entire Assembly

12. The MAGIC Tether Experiment 15 July 2015 Colorado Space Grant Consortium & DINO 12 Push off Springs x 4 Based on Planetary System’s Lightband springs K = 22.5 lb/in (Per Spring) F initial = 60 lb (Total)

13. The MAGIC Tether Experiment 15 July 2015 Colorado Space Grant Consortium & DINO 13 Tether Description The semi rigid tether (SRT) –Two face-to-face Tape Measures –Commercial, off the shelf part

14. The MAGIC Tether Experiment 15 July 2015 Colorado Space Grant Consortium & DINO 14 Tether Mounting Deployment / Braking System mounted in Light Sat (Tip Mass) Boom mounted to Heavy Sat (Main Satellite) with a tether attachment system (TAZ), designed to maintain the rigid natural shape of the tether, while providing a secure attachment.

15. The MAGIC Tether Experiment 15 July 2015 Colorado Space Grant Consortium & DINO 15 Deployment System

16. The MAGIC Tether Experiment 15 July 2015 Colorado Space Grant Consortium & DINO 16 Damping System 42 Teeth per Rotation 366 Teeth per Full Deployment 3.1 J Total Energy.0085 J / Tooth Two 2.5 inch spools Geared to counter rotate Ratchet and Pawl Pawl Spring Loaded Adjustable Initial Compression

17. The MAGIC Tether Experiment 15 July 2015 Colorado Space Grant Consortium & DINO 17 Damping System

18. The MAGIC Tether Experiment 15 July 2015 Colorado Space Grant Consortium & DINO 18 Mechanical Dial In Flight Spring Adjustment.55in -.75in Linear Transducer

19. The MAGIC Tether Experiment 15 July 2015 Colorado Space Grant Consortium & DINO 19 Release System Deployment initiation –Mechanical System –Hand held actuating lever Bicycle brake –Release cable –Switch Incorporated into handle Initiates data collection

20. The MAGIC Tether Experiment 15 July 2015 Colorado Space Grant Consortium & DINO 20 Testing DAY 1 Set Spring to maximum compression,.75in (Over Damped) Position Test Equipment Deploy Reset Decompress spring.05in Repeat until.55in compression is reached (Under Damped) DAY 2 Set Spring to maximum compression in range of interest Position Test Equipment Deploy Reset Decompress spring desired amount Repeat until minimum compression in range of interest is reached

21. The MAGIC Tether Experiment 15 July 2015 Colorado Space Grant Consortium & DINO 21 Data Collection There will be four sources of data in the MAGIC Tether Experiment: –Qualitative observations by the flyers and by the digital video camera –Quantitative measurements of acceleration by the six single-axis accelerometers –Quantitative measurements of angular velocities by the six single-axis gyroscopes –Quantitative measurements of braking spring compression by the linear transducer

22. The MAGIC Tether Experiment 15 July 2015 Colorado Space Grant Consortium & DINO 22 Safety Restraint Straps –Four cinch straps to hold satellite to base plate during Takeoff/landing –Two Velcro straps for satellite securing during flight –Velcro connection between Heavy Sat and base plate during flight Safety straps –10’ straps connected from the base plate to each satellite –6’ strap connecting each satellite –Braided steel rated to 1000 lbs. Safety pin –Prevent accidental deployment Padding on all metal edges Four handholds per satellite Safety straps attached to all tools Fuses installed on electrical lines

23. The MAGIC Tether Experiment 15 July 2015 Colorado Space Grant Consortium & DINO 23 Results Trends will be extrapolated and scaled to DINO’s full Deployment length and weight. What will happen to the satellite if the damping system does not perform precisely as planned? What are the risks to the Satellite? Does the Tether “explode” violently? Is the deployment controllable? Does the damping occur as expected? Real world experience Will result in a safer, more reliable system for DINO

24. The MAGIC Tether Experiment 15 July 2015 Colorado Space Grant Consortium & DINO 24 Appendix

25. The MAGIC Tether Experiment 15 July 2015 FEA for KC-135 Experiment Grayson McArthur

26. The MAGIC Tether Experiment 15 July 2015 Colorado Space Grant Consortium & DINO 26 G-Load Specs Takeoff/landing - Forward 9 g’s - Aft 3 g’s - Down 6 g’s - Lateral 2 g’s - Up 2 g’s 3 g’s in any direction - Randomly picked 3 configurations to simulate the structure being dropped

27. The MAGIC Tether Experiment 15 July 2015 Colorado Space Grant Consortium & DINO 27 FEA Setup Program used for analysis → CosmosWorks Takeoff/landing - Load acts through the center of gravity - Outer face of the outer panel on the light side restrained as immovable/no translation to simulate attachment to base plate - Global size of nodes set at 0.44469 in. with a tolerance of 0.02223 in. - Yield strength of Al 6061 used as max. load = 145 MPa or 21030.51 psi - Factor of safety set at 2 based on the yield strength

28. The MAGIC Tether Experiment 15 July 2015 Colorado Space Grant Consortium & DINO 28 FEA Setup Con. 3 g’s in any direction - Load acts through the center of gravity - Global size of nodes set at 0.44469 in. with a tolerance of 0.02223 in. - Yield strength of Al 6061 used as max. load = 145 MPa or 21030.51 psi - Factor of safety set at 2 based on the yield strength ► Thin edge faces of outer plates set as immovable/no translation to simulate the structure being dropped on those two edges

29. The MAGIC Tether Experiment 15 July 2015 Colorado Space Grant Consortium & DINO 29 Results Stress: Von Mises (VON) - Measured in pounds per square inch - VON = (0.5[(P1-P2) 2 +(P1-P3) 2 +(P2-P3) 2 ]) 1/2 - P1,P2,P3 are principle stresses - Measures stress intensity required for a material to start yielding Strain: Equivalent Strain (ESTRN) Displacement: Resultant (URES) - Measured in inches - Adds displacement vectors in X,Y,Z direction to get a resultant vector Design Check - FOS < 2 area shows as red - FOS > 2 area shows as blue

30. The MAGIC Tether Experiment 15 July 2015 Colorado Space Grant Consortium & DINO 30 Stress

31. The MAGIC Tether Experiment 15 July 2015 Colorado Space Grant Consortium & DINO 31 Strain

32. The MAGIC Tether Experiment 15 July 2015 Colorado Space Grant Consortium & DINO 32 Displacement

33. The MAGIC Tether Experiment 15 July 2015 Colorado Space Grant Consortium & DINO 33 Design Check

34. The MAGIC Tether Experiment 15 July 2015 Colorado Space Grant Consortium & DINO 34 Conclusions The structure will be able to withstand all the prescribed loads as indicated in NASA document AOD 33897 Experiment Design Requirements and Guidelines NASA 931 KC135A Structure will survive a 3 g impact such as being dropped by the flight crew during transition from 0 g to 2 g

35. The MAGIC Tether Experiment 15 July 2015 Colorado Space Grant Consortium & DINO 35 Issues and Concerns Mesh resolution was limited due to computer memory and time limitations Boundary conditions being appropriate for load case

36. The MAGIC Tether Experiment 15 July 2015 Onboard Support Equipment Equipment Containment System (ECS)

37. The MAGIC Tether Experiment 15 July 2015 Colorado Space Grant Consortium & DINO 37 Entire Assembly

38. The MAGIC Tether Experiment 15 July 2015 Colorado Space Grant Consortium & DINO 38 Base Plate.125-.25in Al 6061 sheet Note, Current design requires heavy hand construction… It will not fit within the CNC 4 Aircraft mounting location 7 handhold, accommodating up to 4 handlers Experiment restraint harness Safety cable attachment

39. The MAGIC Tether Experiment 15 July 2015 Colorado Space Grant Consortium & DINO 39 Tool Box Store bought Plastic and steel construction Round plastic edges Lockable

40. The MAGIC Tether Experiment 15 July 2015 Colorado Space Grant Consortium & DINO 40 Stand Off Al 6061 Industrial strength Velcro Non permanent attachment Only for stability, not critical for LD/TO

41. The MAGIC Tether Experiment 15 July 2015 Mechanisms Michael Martinez

42. The MAGIC Tether Experiment 15 July 2015 Colorado Space Grant Consortium & DINO 42 Mechanisms Contents: –Tether Description –Deployment System –Braking System

43. The MAGIC Tether Experiment 15 July 2015 Colorado Space Grant Consortium & DINO 43 Tether Description The semi rigid tether (SRT) is constructed of 2 COTS spring metal "tape measures", four feet length by 1 in wide, curved along their width. To be configured ‘face to face’, provides greater stability.

44. The MAGIC Tether Experiment 15 July 2015 Colorado Space Grant Consortium & DINO 44 Deployment System

45. The MAGIC Tether Experiment 15 July 2015 Colorado Space Grant Consortium & DINO 45 Deployment System (cont) The MAGIC Tether deployment system consists of two 2.5 inch spools, geared to counter rotate and unwind the spring metal boom in a controlled manner.

46. The MAGIC Tether Experiment 15 July 2015 Colorado Space Grant Consortium & DINO 46 Deployment System (cont) Deployment / Braking System –The stowed SRT will be wound on the two spools such that when deployed the two tape measures will be face to face, forming a rigid structure. –Tape to spool connection recessed to reduce stress at connection

47. The MAGIC Tether Experiment 15 July 2015 Colorado Space Grant Consortium & DINO 47 Braking System Velocity control is provided by a 48 tooth, 2.0 inch ratchet and pawl system, with the ratchet shafted to the geared spool, and the pawl spring loaded to provide a loading / braking force against the ratchet. Initial k for spring ~ 0.245 N/mm

48. The MAGIC Tether Experiment 15 July 2015 Colorado Space Grant Consortium & DINO 48 Release System Deployment initiation –Mechanical System –Hand held actuating lever Bicycle brake –Release cable –Switch Incorporated into handle Initiates data collection

49. The MAGIC Tether Experiment 15 July 2015 Colorado Space Grant Consortium & DINO 49 Tether Reset Device Tether reset device Two options –Manual crank –Electric drill Flexible extension used to reach the drive shaft easily Attached to the toolbox by a steel cable tether

50. The MAGIC Tether Experiment 15 July 2015 Colorado Space Grant Consortium & DINO 50 Tether Mounting Deployment / Braking System mounted in Light Sat (Tip Mass) Boom mounted to Heavy Sat (Main Satellite) with a tether attachment system (TAZ), designed to maintain the rigid natural shape of the tether, while providing a secure attachment.

51. The MAGIC Tether Experiment 15 July 2015 Sensors Kate Worster Michael Seibert

52. The MAGIC Tether Experiment 15 July 2015 Colorado Space Grant Consortium & DINO 52 Sensors: Objectives The Sensors Subsystem is designed to measure the large-scale and small-scale dynamics of the experiment during its deployment, including linear and angular accelerations imparted by the tether Sensors and Data Acquisition –Onboard storage of science and engineering data –Provide data for post-flight analysis

53. The MAGIC Tether Experiment 15 July 2015 Colorado Space Grant Consortium & DINO 53 Sensors & Data Acquisition System Functional Diagram Data Signal Power lines Data Logger HVY_AZHVY_AYHVY_AZ HVY_G3 HVY_G2HVY_G1 KS 9V15V Heavy Side KS Kill Switch

54. The MAGIC Tether Experiment 15 July 2015 Colorado Space Grant Consortium & DINO 54 Sensors & Data Acquisition System Functional Diagram Data Signal Power lines Data Logger LHT_AZLHT_AYLHT_AZ LHT_G3 LHT_G2 LHT_G1 KS 9V15V LHT_T_D Light Side

55. The MAGIC Tether Experiment 15 July 2015 Colorado Space Grant Consortium & DINO 55 Functional Requirements RequirementsAccelerometerRate Gyro Linear Transducer Data Logger Laptop Measure acceleration Measure twist & rotation Measure spring compression Data acquisition & analysis

56. The MAGIC Tether Experiment 15 July 2015 Colorado Space Grant Consortium & DINO 56 Gyro Specifications-ADXRS150EB Surface-mount package of 7mm x 7mm x 3mm and mass of 0.5 grams. Each rate gyro has a resolution of 0.05  /s/  Hz and a dynamic range of  150  /s. Input voltage of 5.00v DC from onboard power supply and a quiescent supply current between 6.0-8.0 mA.

57. The MAGIC Tether Experiment 15 July 2015 Colorado Space Grant Consortium & DINO 57 Accel. Specifications-ADXL150 Nominal sensitivity: 38.0mV/g and a maximum sensitivity of 43.0mV/g. The functional voltage range 4.0V - 6.0V and a quiescent supply current of 1.8mA for nominal operation and 3.0mA as the maximum supply current. Resolution: 1.0mg/  Hz Dynamic range: 80dB Each can withstand 2000 g’s when un-powered and 500 g’s when powered

58. The MAGIC Tether Experiment 15 July 2015 Colorado Space Grant Consortium & DINO 58 9V Power Supply Specifications 9V ZnMn 2 battery Average voltage of 9.0 volts Average capacity of 655mAhr (0.8 volts per cell Weighs 45.6 grams (1.6oz) and has a total volume of 21.2cm 3 (1.3in 3 ).

59. The MAGIC Tether Experiment 15 July 2015 Colorado Space Grant Consortium & DINO 59 15V Power Supply Specifications 1.5V Alkaline Zinc-Manganese Dioxide (ZnMn 2 ) battery Average voltage of 1.5 volts Average capacity of 3135mAhr (0.8 volts per cell Weighs 23.0 grams (0.8 oz) and has a total volume of 8.1cm 3 (0.5in 3 ).

60. The MAGIC Tether Experiment 15 July 2015 Colorado Space Grant Consortium & DINO 60 COTS Parts Status PartAvailabilityStatus ADXL150In stock on Analog Devices website Not yet ordered ADXRS150In stock on Analog Devices website Not yet ordered InhibitsAvailable at CSGC and JB Saunders Have some, others will be purchasing next week Sensor housing, 18 gauge wire, prototype board Available at JB SaundersPurchasing next week

61. The MAGIC Tether Experiment 15 July 2015 Colorado Space Grant Consortium & DINO 61 Data Collection Omnidata Polycorder and Data Fielder loggers 415K on board storage 25Hz sampling rate Start/Stop trigger capability 10 analog input channels 0V-5V, 0V-10V & 0V-15V input ranges

62. The MAGIC Tether Experiment 15 July 2015 Colorado Space Grant Consortium & DINO 62 Data Collection Heavy Sat –6 Inputs 3 Accelerometers 3 Rate Gyroscopes Light Sat –7 Inputs 3 Accelerometers 3 Rate Gyros 1 Linear Transducer

63. The MAGIC Tether Experiment 15 July 2015 Colorado Space Grant Consortium & DINO 63 Data Collection Configuration –Omnidata DF200 GUI –RS-232 –Variables Sampling Rate Saving Rate Channel Input Voltage Range Data Retrieval –Omnidata DF200 GUI –RS-232 –Data Retrieval Options Histogram Spreadsheet

64. The MAGIC Tether Experiment 15 July 2015 Colorado Space Grant Consortium & DINO 64 Ground Support Equipment Requirements Laptop –RS232 Capability Serial Port USB to Serial adapter Spring Set Screw Calibration –Calipers Initial state displacement measurement

65. The MAGIC Tether Experiment 15 July 2015 Procedures Jeff Parker

66. The MAGIC Tether Experiment 15 July 2015 Colorado Space Grant Consortium & DINO 66 In-Flight Procedures Preparations for the First Parabola These procedures must be followed to set the experiment up for the first parabola: 1.Flyer B: verify that the digital video camera is on and working normally. 2.Flyer A: verify that the sensors’ wiring harness is connected to the first data logger on each satellite. 3.Flyer A: turn on power to both satellites by switching the kill switch into the on position. Flyer B: verify that power has been turned on. An LED will indicate normal power for each battery system onboard. Flyer B: replace any battery packs that require replacing. 4.Flyer A: configure each of the two data loggers using a brief set of instructions attached clearly to the equipment containment toolbox. Flyer B: verify every instruction as they are entered. 5.Flyer B: verify the setting of the slow-down mechanism. 6.Flyer B: remove the four cinch straps from the experiment and stow them in the equipment containment toolbox. Flyer A: assist as necessary. This leaves two Velcro straps still attached to the experiment system. 7.Flyers A and B: visually inspect the experiment to make sure that everything is in working order, including the Velcro straps, the safety straps, the deployment system, the safety deployment pin, and the slow-down mechanism.

67. The MAGIC Tether Experiment 15 July 2015 Colorado Space Grant Consortium & DINO 67 In-Flight Procedures Free-Fall minus three minutes 8.Flyer A: remove the safety deployment pin and Velcro it to the side of Heavy Sat (it also has a short tether attached to it to restrain it from possibly floating away). 9.Flyer B: check the temperature of the cabin using the thermometer attached to the toolbox. 10.Flyer B: record all settings and activities in the logbook. The ambient temperature, air currents, and other environmental factors should be noted. Free-Fall minus one minute 11.Flyer A: release one of the two remaining Velcro hold-down straps. If the experiment behaves in an unexpected manner, immediately replace the straps and inspect the deployment system. This may sacrifice the parabola, but it could avoid releasing an uncontrolled deployment. 12.Flyer B: prepare the active data logger on each satellite. This requires about eight key-strokes that will be easily visible near the data logger on the system. 13.Flyer A: release the last hold-down Velcro strap (the satellite system still has Velcro attached to its base to keep it still on the base plate). 14.Flyers A and B: situate yourselves such that your feet are restrained by the foot- restraints and you are on opposite sides of the flight system. Make sure that Flyer A will be near Heavy Sat and Flyer B will be near Light Sat upon deployment completion.

68. The MAGIC Tether Experiment 15 July 2015 Colorado Space Grant Consortium & DINO 68 In-Flight Procedures Free-Fall 15.Flyers A and B: make sure you are stable in the foot-restraints and prepared for the experiment. 16.Flyers A and B: lift the experiment off of the base plate and maneuver into the correct position over the base plate. During the deployment, the Light Sat will move approximately 2.5 feet and the Heavy Sat will move approximately 1.5 feet. Hence it is important to deploy the system in the proper location in space such that the full deployment occurs within the specified experiment volume. This position is marked on the base plate. 17.Flyer A: hold and stabilize the satellite system from the side such that the deployment action will occur sideways and that Flyer A will be near Heavy Sat and Flyer B will be near Light Sat upon deployment completion. 18.Flyer A: take hold of the deployment trigger. 19.Once all personnel are clear from any interference with the MAGIC Tether’s deployment (keeping in mind that both the primary and tip mass systems will move upon deployment), then Flyer A: carefully release the system and trigger the deployment. Keep hold of the deployment trigger, both as a safety and because letting it go might induce added dynamics into the system. 20.The separation springs activate and the deployment proceeds. 21.The tether is reeled out from the Light Sat; accelerometers and rate gyros on both bodies measure the linear and rotational accelerations experienced by both systems; the data are recorded on the data loggers. 22.The slow-down mechanism removes energy from the moving system from the moment of deployment until the system comes to a stop.

69. The MAGIC Tether Experiment 15 July 2015 Colorado Space Grant Consortium & DINO 69 In-Flight Procedures 23.The Light Sat either comes to a halt with respect to the Heavy Sat or it recoils after the tether stretches taut. Flyer B records the resulting dynamics in the logbook. Flyer B then records the distance that the tether deployed by observing the tic marks on the tether. 24.The maximum separation velocity between the two bodies is 1.7 ft/s, slow enough to grapple if need be. Therefore, if any recoil action exists that appears to threaten a collision between the two satellites, then Flyer A: carefully grapple the two satellites prior to impact. If, however unlikely, the system recoils at an unexpectedly high velocity, then Flyer A: remain in a safe position and wait until the system settles down before retrieving the hardware. 25.If not otherwise retrieved, Flyer A: take hold of the Heavy Sat. 26.Flyer B: take hold of the Light Sat. 27.Flyer A: place the Heavy Sat onto the Velcro swath on the base plate to secure it before the end of the free-fall. End of Free-Fall 28.Flyer B: keep hold of the Light Sat while the aircraft’s accelerations increase. 29.Flyer A: use the tether-reset device to recoil the tether onto the spools. 30.Flyer B: mate the Light Sat onto the Heavy Sat, compressing the separation springs. The deployment device will not allow the springs to release until triggered, so there is no danger of accidental deployment during this phase.

70. The MAGIC Tether Experiment 15 July 2015 Colorado Space Grant Consortium & DINO 70 In-Flight Procedures 31.Flyer A: strap the system down using the two Velcro hold-down straps. 32.Flyer B: command the two active data loggers to stop recording data. 33.Flyer B: adjust the knob on the slow-down mechanism to set the slow-down spring to the next desired value of x 0. Flyer A: verify the set value. 34.Flyer B: record all dynamics, activities, and new settings in the logbook. The ambient temperature, air currents, and other environmental factors should be noted. 35.Flyers A and B: while waiting for the next free-fall, visually inspect the system for signs of fatigue, failures, or damage. If power sensors indicate a battery pack low on power, replace the battery pack at this time. If a data logger is nearing memory capacity, then switch the power and data cables from the active data logger to the spare data logger. Follow the startup procedure listed in line 4. 36.Return to step 11 and repeat. End of Flight 37.Flyer A: place the deployment safety pin into the deployment system. 38.Flyer A: secure all four additional cinch straps on the system. 39.Flyer B: shut the data loggers down following the simple procedures listed on the side of the structure. 40.Flyer B: flip the kill switch on each satellite, turning off power to each system. 41.Flyer A and B: verify that all straps are in place and secure. 42.Flyer A and B: verify that all components are stowed and secure.

71. The MAGIC Tether Experiment 15 July 2015 Colorado Space Grant Consortium & DINO 71 Emergency Procedures In the event of an emergency, the following procedures will be followed. These procedures will be posted directly on the experiment, detailing exactly how to shut the system down quickly. 1.If either satellite is not strapped to the base plate, follow the appropriate procedures here: Flyer A: take hold of the Heavy Sat Flyer B: take hold of the Light Sat Flyer A: place the Heavy Sat on the base plate Flyer B: mate the Light Sat on the Heavy Sat Flyer A: strap the system down using the two Velcro straps 2.Switch the master kill switch on each satellite to shut off all power on each satellite. 3.Shut off the power to the data loggers.

72. The MAGIC Tether Experiment 15 July 2015 Colorado Space Grant Consortium & DINO 72 Safety Restraint Straps –Four cinch straps to hold satellite to base plate during Takeoff/landing –Two Velcro straps for satellite securing during flight –Velcro connection between Heavy Sat and base plate during flight Safety straps –20’ straps connected from the base plate to each satellite –6’ strap connecting each satellite –Braided steel rated to 1000 lbs. Safety pin –Prevent accidental deployment Padding on all metal edges Four handholds per satellite Safety straps attached to all tools Fuses installed on electrical lines

73. The MAGIC Tether Experiment 15 July 2015 Data Analysis Jeff Parker

74. The MAGIC Tether Experiment 15 July 2015 Colorado Space Grant Consortium & DINO 74 Data Types There will be four sources of data in the MAGIC Tether Experiment: –Qualitative observations by the flyers and by the digital video camera –Quantitative measurements of acceleration by the six single-axis accelerometers –Quantitative measurements of angular velocities by the six single-axis gyroscopes –Quantitative measurements of braking spring compression by the linear transducer

75. The MAGIC Tether Experiment 15 July 2015 Colorado Space Grant Consortium & DINO 75 Data Reduction Accelerometers and rate gyros have biases and scale factors –Calibrated by temperature measurements and specific calibration measurements Analog measurements between 0 – 5 Volts Expected Dynamics: –Large acceleration spike at beginning of deployment –Diminishing decelerations until end of tether or all energy is dissipated –Possible dynamics due to tether’s deployment –Possible recoil dynamics due to excessive energy

76. The MAGIC Tether Experiment 15 July 2015 Colorado Space Grant Consortium & DINO 76 Expected Results The MAGIC Tether team expects the following things: –Four standard springs will accelerate the relative velocity of the tip mass with respect to the primary satellite to approximately 1.7 ft/s (0.518 m/s). –The tip-off rate of the deployment to be less than 1°/s in each axis. –Given a deployment velocity of 1.7 ft/s, the optimal value of x 0 to be approximately 0.66” to critically damp the system’s motion as the tether is fully deployed. –The semi-rigid tape to be deployed in a controlled fashion without any recoil at the end of its deployment.