1. 1613-4 Sept. 2008EFW INST+SOC PDR EFW AXB Jeremy McCauley Aerospace Engineer Space Sciences Laboratory, UCB jeremymc@ssl.berkeley.edu AXB Spacecraft +Z

2. 1623-4 Sept. 2008EFW INST+SOC PDR EFW AXB Overview Design Drivers Design Description –ConceptConcept –HeritageHeritage –Assembly BreakoutAssembly Breakout –ThermalThermal ETU Integration and Testing (I&T) MGSE Requirements Ongoing Developments

3. 1633-4 Sept. 2008EFW INST+SOC PDR EFW AXB Design Drivers Deploy spherical electric fields probes up to 6 meters with an E- Field sensor preamp at the end. Length adjustable (longer only) on orbit with a resolution of +/- 0.5 cm Interface to spacecraft to support deployable booms. Meet straightness requirement (< 3” radial). Provide relief for CTE mismatch between Gr/E Tube and SC body. Provide a connector for test input to the sensor accessible during all integration phases. Total Mass not to exceed 8.57 kg (Each AXB Unit to not exceed 3.64 kg; AXB Tube to not exceed 1.29 kg) Interface Operational Temperature Range: -25 to +55C (TBR) Interface Survival Temperature Range: -30 to +60C (TBR)

4. 1643-4 Sept. 2008EFW INST+SOC PDR EFW AXB Design Description: Concept Axial Boom Unit (AXB) –Sensors Extended from SC on Stacers Compact for Launch Rigid after Deploy Adjustable Length Upper Boom Unit (+Z) Lower Boom Unit (-Z)

5. 1653-4 Sept. 2008EFW INST+SOC PDR EFW AXB Design Description: Heritage Heritage Unit –Primarily AXB from THEMIS, modified for length and to fit RBSP SC Including Tube, Structure, Stacer, DAD design and springs Similar to units on POLAR and FAST –Whip from Rockets replaces THEMIS Whip Stacer –Direct Drive Unit from THEMIS SPB Added Refinements –Direct Drive Unit on a Stacer –DAD Lock Wheel Assemblies –Sphere Caging Mechanism

6. 1663-4 Sept. 2008EFW INST+SOC PDR EFW AXB Design Description: Order of Deploy Stowed Unit Unpowered Fully Restrained Step 1: Whip Deploy Frangibolt Actuated Spring Powered Step 2: Stacer Deploy Frangibolt Release Motor Driven (1.2 cm/s) Length Adjustable +Z SC Axis

7. 1673-4 Sept. 2008EFW INST+SOC PDR EFW AXB Design Description: AXB Structural Design –End Supported Tube with Aluminum End Fittings –Two (2) Identical Boom Units Stationary Deploy Assy Moving DAD Stacer Whip and Spherical Electric Fields Probe Upper Boom Unit (+Z) Lower Boom Unit (-Z) Dimensional Scale Tube Diameter 6” [15 cm] Deck Separation 43.5” [108 cm] Whip Length 13” [33 cm] Sphere Diameter 3.2” [8.0 cm]

8. 1683-4 Sept. 2008EFW INST+SOC PDR EFW AXB Design Description: Tube Structural Design –End Supported Tube: Graphite Epoxy, M55 (Layup: 0, 45, 90, 45, 0 [quasi- isotropic]) –Fixed-Fixed First Frequency: 257 Hz257 –Tube Static Stress Margin: 10 –End Fittings: Al 6061-T6 –Lower Support includes a drumhead flexure design Currently 89.1 lbf @ 52ºC dT –Static and Vibration testing as specified –Joint Epoxy: Hysol 9309NA –Bond Shear Stress Margin: 30.3 Tube End Fitting Flexure Flexure at dT=52ºC

9. 1693-4 Sept. 2008EFW INST+SOC PDR EFW AXB Design Description: Booms Boom Design –Stationary Deploy Assy –Moving DAD –Stacer –Whip and Spherical Electric Fields Probe Whip DAD Stacer Deploy Assy Stowed Configuration Deployed Configuration

10. 1703-4 Sept. 2008EFW INST+SOC PDR EFW AXB Design Description: Booms Stationary Deploy Assy –Sphere Caging Mechanism –Direct Drive Assembly –Roller Nozzle #1 Sphere Caging Mechanism Roller Nozzle #1 Direct Drive Assy Stowed Configuration Deployed Configuration

11. 1713-4 Sept. 2008EFW INST+SOC PDR EFW AXB Design Description: Booms Sphere Caging Mechanism –Protect Spherical Electric Field Probe –Release Whip on Orbit Frangibolt Actuator (Next Slide) Top Opens Cam Releases Arm DAD Plunger with Kickoff Spring Starts Whip –AC Test Contact for Ground Operations –Torque Margin: 40.9 Spring to Friction Drag –Green Tag Enable Plug/ Ground Test Plug Stowed Configuration Deployed Configuration DAD Plungers AC Test Contact Enable Plug Frangibolt

12. 1723-4 Sept. 2008EFW INST+SOC PDR EFW AXB Design Description: Frangibolt Frangibolt –500 lb Retention Force For Launch Loads Only –Resettable –25 W @ 28 Vdc –Actuation Time: < 10 s

13. 1733-4 Sept. 2008EFW INST+SOC PDR EFW AXB Design Description: Booms Direct Drive Assembly –Stacer Frangibolt Release –Harness Spool: Max Capacity 9.2 meters 0.085” diameter cable –Motor Drive Mechanism: SPB motor (1000:1 gear ratio) –Sense Switches: Frangibolt Release, End of Travel and Turn Counter –Slip Ring –Length Resolution: 0.78 cm/click BOT, 0.53 cm/click EOT, 2.4 clicks/s –Torque Margin: 7.6 (Motor Torque to Torque to Retract Stacer) Frangibolt Sense SwitchesSpool Harness Motor Slip Ring

14. 1743-4 Sept. 2008EFW INST+SOC PDR EFW AXB Design Description: Booms Roller Nozzle #1 –Centering of the Stacer –Resist SC Forces Rollers Rocker Arms

15. 1753-4 Sept. 2008EFW INST+SOC PDR EFW AXB Design Description: Booms Moving DAD –Deployment Assist Device (DAD) with Kickoff Springs –Lock Wheel Assemblies Increase Unseat Force from 6 lbs to 15 lbs axial from 1.6 to 4.5 lbs radial –Roller Nozzle #2 –Force Margin: 2.1 DAD Springs to Friction Stowed Configuration Deployed Configuration DAD Springs Lock Wheel Assy Roller Nozzle #2

16. 1763-4 Sept. 2008EFW INST+SOC PDR EFW AXB Design Description: Booms Stacer –Helical Spring –Deployed Acts as a Rigid Tube Spin Adjusted Resonance: 26.5 RPM –Force Margin: > 33 Stacer Force to Friction MAIN STACER PROPERTIES [in][mm] STRIP THICKNESS0.0040.10 STRIP WIDTH5.000127.00 TIP DIAMETER0.70017.78 BASE DIAMETER1.12828.65 EQUIVALENT DIAMETER 1.00525.54 Deployed Configuration Stacer

17. 1773-4 Sept. 2008EFW INST+SOC PDR EFW AXB Design Description: Booms Whip and Spherical Electric Fields ProbeWhip and Spherical Electric Fields Probe –Hinge Torque Margin: 3.63.6 Hinge Spring to Friction DAG 213 Coated –Whip Tube FOS (Bending on Deploy): 2.0 DAG 213 Coated –Sphere Probe and Preamp Assy DAG 213 Coated Cannot Clean –All Three Isolated for Potential Control –Fundamental Frequency: 23.0 RPM (> 4x SC Spin Rate  Rigid) Stowed Configuration Deployed Configuration Sphere Internal View Whip Sphere Hinge Preamp

18. 1783-4 Sept. 2008EFW INST+SOC PDR EFW AXB Design Description: Thermal (TBC) Thermally Coupled to the SC Spherical Electric Fields Probe, Whip and Hinge: –Coated with DAG 213 Stacer: –Mill Finish Elgiloy Moving DAD: –Alodine (Gold) –Taped with Germanium Black Kapton –Electroless Nickel Plating with Teflon Impregnate Stationary Deploy Assy: –Alodine (Gold) –Electroless Nickel Plating with Teflon Impregnate End Supported Tube –M55 Graphite Epoxy Aluminum End Fittings –Alodine (Gold)

19. 1793-4 Sept. 2008EFW INST+SOC PDR EFW AXB Design Description: I&T

20. 1803-4 Sept. 2008EFW INST+SOC PDR EFW AXB Design Description: I&T ETU Flow: DDD Testing –Connectors need testing for Deep Dielectric Discharge (DDD) –Not reasonable on a part by part basis –Harness will be tested in unit, prior to Preamp installation Sphere Whip Hinge Whip Harness

21. 1813-4 Sept. 2008EFW INST+SOC PDR EFW AXB Design Description: I&T ETU Flow: Deployments –Expected number of deployments on the instrument at launch: 4 Length and Fundamental Frequency Test Alignment and Runout Test Thermal Vacuum Hot Thermal Vacuum Cold Deployments at Instrument and SC Level will be by means of Frangibolt simulators only

22. 1823-4 Sept. 2008EFW INST+SOC PDR EFW AXB Design Description: I&T ETU Flow: Length and Fundamental Frequency Testing –Unit will be deployed horizontally on a g-negating track, then suspended vertically for fundamental frequency data. Gravitational component will be subtracted from frequency. –Wire EOT switch test –Motor, Frangibolt current profile

23. 1833-4 Sept. 2008EFW INST+SOC PDR EFW AXB Design Description: I&T ETU Flow: Alignment and Stiffness Testing –Requirement: 3 inches radial at Sphere –RSS Analysis of Stationary Deploy Assy and Moving DAD Tolerance Stackup: 0.20 degree (0.8 inches) –Stacer Runout is not accounted for –Hinge, Whip and Sphere Runout is TBD –Unit will be deployed horizontally on a g-negating track, then lifted to floats for g-negated runout and stiffness measurements. (POLAR)

24. 1843-4 Sept. 2008EFW INST+SOC PDR EFW AXB Design Description: I&T ETU Flow: Vibration Testing –Vibration (modal survey, sine, and random) to Qualification levels per 7417-9019 Section 5.4.5 at the Component level (IDPU, SPB, AXB) –Self-shock survival from boom deployments actuations shall be demonstrated at the component level (SPB and AXB) by at least 2 actuations (only the initial release generates a shock) –Post-vibration deployments during Thermal Vacuum testing

25. 1853-4 Sept. 2008EFW INST+SOC PDR EFW AXB Design Description: I&T ETU Flow: Thermal Vacuum Testing –6 operational cycles plus 1 survival cycle, per the requirements and limits indicated in 7417-9019 section 5.3.2 –Deployment tests will be performed at hot and cold levels –Whip and Caging Mechanism deployment testing performed at the subassembly level –Stacer deployment performed at the assembly level Unit will be deployed horizontally on a g-negating track within the Thermal Vacuum Chamber –Preamplifiers will be separately tested.

26. 1863-4 Sept. 2008EFW INST+SOC PDR EFW AXB Design Description: MGSE MGSE Required: –Whip Offload Fixture Deployment testing of hinge, whip and sphere in air and at vacuum Requires design and fabrication –Horizontal Deployment Track: Deployment testing of Stacer in air and at vacuum Requires adaptation of SWAVES Track for form factor –Runout Fixture: G-negated runout measurements of the deployed antenna Requires fabrication of float system and rotational fixtures –Vibe Fixture: Vibration Testing of Boom Unit with Whip, Sphere and Caging Assembly Requires design and fabrication –Shipping Container: I&T Travel Protection Requires adaptation of THEMIS or STEREO IMPACT Cases

27. 1873-4 Sept. 2008EFW INST+SOC PDR EFW AXB Ongoing Developments Motor Driven Deployment of a Stacer –EM Deployment Testing Successful Harnessing the Whip –EM Harness and Braid successfully built for Hinge Testing

28. 1883-4 Sept. 2008EFW INST+SOC PDR EFW AXB Design Description Back up slides –Redundancy is Key….

29. 1893-4 Sept. 2008EFW INST+SOC PDR EFW AXB Design Description IDReq. Title Priorit y Requirement Body or Section Heading 3 Functional Requirements 3.1 Functional, performance and general design requirements EFW-1Instrument Design life shall be designed for a total lifetime duration of 2 years plus 60 days. EFW-200Instrument Calibrationshall be calibrated prior to launch, and be designed to accommodate additional in-flight calibration EFW-6Instrument Orbit Inclination Operability shall be capable of operating in an orbit with an inclination of 10° ± 0.25°. EFW-7Instrument Orbit Perigee Operability shall be capable of operating in an orbit where perigee altitude is between 500 km and 675 km (TBR). EFW-8Instrument Orbit Apogee Operability shall be capable of operating in an orbit where apogee altitude is between 30,050 km and 31,250 km (TBR). EFW-201 Instrument Accommodation of Observatory Sun Off-Point Angle (Component) shall shall be capable of collecting required science measurements under the condition where the off-pointing angle between the spin axis of each observatory and the Sun-Earth line during nominal operations does not exceed 25 degrees North or South of the ecliptic plane, or 25 degrees East or West relative to the Earth orbit plane, where "north" and "south" are with respect to an ecliptic coordinate system. EFW-202 Instrument Accommodation of Observatory Sun Off-Point Angle (Composite) shall be capable of collecting required science measurements under the condition where the total off-pointing angle between the spin axis of each observatory and the Sun-Earth line during nominal operations is greater than 15 degrees, and does not exceed 27 degrees. EFW-9 Instrument Accommodation of Observatory Operational Spin Rate Range shall be capable of operating nominally within an observatory spin rate range of no less than 4 rpm and no more than 6 rpm. EFW-10 Instrument Accommodation of Observatory Selected Operational Spin Rate shall be capable of collecting required science measurements at a specific, optimal spin rate selected for both observatories that is within the specified allowable range

30. 1903-4 Sept. 2008EFW INST+SOC PDR EFW AXB Design Description IDReq. Title Priorit y Requirement Body or Section Heading 3 Functional Requirements 3.1 Functional, performance and general design requirements EFW-11 Instrument Accommodation of Observatory Selected Spin Rate Stability shall be capable of collecting required science measurements at an observatory spin rate that is maintained to within +/- 0.25 rpm of the in-flight selected value, except during maneuvers. EFW-203 Instrument Accommodation of Unattended Mission Operations shall be capable of accommodating an observatory spin rate during commissioning period activities within a range between 3 RPM (TBR) and 15 RPM (TBR). EFW-12 Instrument Accommodation of Unattended Mission Operations shall be designed to accommodate periods of unattended mission operations (unstaffed MOC) during the operational phase of the mission of up to TBD hours EFW-21EFW Instrument Complement shall consist of four orthogonally oriented, boom-mounted spin-plane boom- mounted sensors, an Electronics Box, and two axial boom mounted sensors with harness as defined in the Spacecraft to EFW ICD. EFW-22 Functionally Identical EFW Instrument Suites shall be functionally identical. EFW-23EFW - Spacecraft ICD Compliance shall comply with the EFW-to-Spacecraft interface control documents (ICDs). EFW-24EFW Instrument Availability shall be designed to be available for the collection of its required measurements at least 99% of the time during the operational phase of the mission EFW-209 EFW Spin Axis Measurement Sensitivity Validity shall meet Spin Axis measurement sensitivity requirements outside time periods defined as follows: the interval where the aft axial boom is shadowed by the spacecraft or solar panels, and 25 seconds after the end of such periods.

31. 1913-4 Sept. 2008EFW INST+SOC PDR EFW AXB Design Description IDReq. Title Priorit y Requirement Body or Section Heading 3 Functional Requirements 3.1 Functional, performance and general design requirements EFW-51 Measure Spin Axis DC Electric Field (Survey) shall measure axial electric field components (survey), as follows: -- frequency range: DC to 15Hz; -- magnitude range: 2 mV/m - 500 mV/m; -- cadence: 32 vectors/second; -- sensitivity: 4 mV/m or 20% for R > 3.5 Re, 6 mV/m or 20% for 3.5 Re > R > 2.5 Re, 12 mV/m or 20% for R < 2.5 Re. EFW-52Measure Spin Axis DC Electric Field (Burst) shall measure axial electric field components (burst), as follows: -- frequency range: DC to 256 Hz; -- magnitude range: 0.4 - 500 mV/m; -- cadence: 512 samples per second; -- sensitivity: 1 mV/m or 10% @ 50 Hz (TBR). Required Components to Achieve Above EFW-54EFW Axial E-Field Booms shall be capable of deploying 6 meters with an E-Field sensor preamp at the end capable of measuring E-Fields to 400 kHz EFW-54aEFW Axial E-Field Booms shall Deploy the AXB sensors within +/- 1 degree of the AXB deployment system axis EFW-56EFW Harnessing shall connect the SPB, AXB, IDPU, EMFISIS/MAG and EMFISIS/SCM units together as detailed in the ICDs EFW-61EFW Power Control shall contain circuitry to open SPB and AXB doors and deploy sensors

32. 1923-4 Sept. 2008EFW INST+SOC PDR EFW AXB Design Description IDReq. Title Priorit y Requirement Body or Section Heading 3 Functional Requirements 3.2 Power allocations and related requirements EFW-65EFW Main Power Max Voltage shall tolerate without damage a maximum input voltage of 40V indefinitely as defined in the ICD EFW-66EFW Main Power Turn Off shall tolerate without damage having power removed without notice as defined in the ICD EFW-68EFW AXB Deployment Power shall not exceed 4.0 Amps from the EFW AXB Deployment Service EFW-69EFW Survival Heaters shall accommodate survival heaters up to 1/2 nominal power at 22V bus voltage, or approximately 113 Ohms. 3.3 Performance budget sub-allocations with respect to system budgets EFW-72EFW AXB Whip Release Powershallnot exceed 2.0 Amps at 28V EFW-73EFW AXB Stacer Release Powershallnot exceed 2.0 Amps at 28V EFW-74EFW AXB Motor Powershallnot exceed 0.2 Amps at 28V (1.5A startup) 3.4 Operational requirements EFW-77EFW AXB Operational Temp Rangeshallperform as designed from -25 to +55C (TBR) EFW-80EFW AXB Survival Temp Rangeshallsurvive without damage from -30 to +60C (TBR) 3.6 Interfaces to the spacecraft bus EFW-90EFW AXB ICD Complianceshall comply with the requirements and constraints imposed by all relevant instrument-to-spacecraft interface control documents (ICDs). 3.8 System test Interfaces EFW-92AXB Signal Test Inputshall provide a connector for test input to the sensor accessible when the top and bottom of the spacecraft are accessible.

33. 1933-4 Sept. 2008EFW INST+SOC PDR EFW AXB Design Description IDReq. Title Priorit y Requirement Body or Section Heading 3 Functional Requirements 3.10 Fault detection and correction considerations/requirements EFW-100EFW AXB Deployment Enableshall not deploy AXB booms or fire AXB actuators without the AXB and Main power ON. 3.11 Redundancy description EFW-101EFW Boom Pair Redundancyshallbe capable of powering each E field axis separately. EFW-102EFW Safing by subsystemshall separately current-limit each axis and the front end electronics required for EMPHASIS EFI signal, and the remainder of the EFW electronics 3.12 Mass allocation EFW-103EFW Total Massshall The EFW shall not exceed the total allocated mass budget of 31.17kg (or as allocated in RBSP System Mass Budget). EFW-106EFW AXB Massshallnot exceed 3.64 kg EFW-107EFW AXB Tube Massshallnot exceed 1.29 kg EFW-108EFW Harness Massshallnot exceed 2.50 kg (TBR) 3.15 Contamination control requirements EFW-132 Instrument Compliance with Contamination Control Plan shall comply with the requirements and constraints imposed by the RBSP Observatory Contamination Control Plan, APL document no. 7417-9007 EFW-133 Instrument Compliance with EM Environment Control Plan shall comply with the requirements and constraints imposed by the RBSP Electromagnetic Environment Control Plan, APL document no. 7417-9018. EFW-135EFW ESC Controlshall comply with the UCB Electrostatic Cleanliness (ESC) Plan

34. 1943-4 Sept. 2008EFW INST+SOC PDR EFW AXB Design Description IDReq. Title Priorit y Requirement Body or Section Heading 3 Functional Requirements 3.15 Contamination control requirements EFW-136 Instrument Compliance with Environmental Design and Test Requirements Document shall comply with the requirements and constraints imposed by the RBSP Environmental Design and Test Requirements Document, APL document no. 7417-9019. EFW-137EFW Quality Assuranceshall comply with the RBSP Performance Assurance Implementation Plan, as modified by the Compliance Matrix EFW-210 Instrument Compliance with Space Asset Protection shall shall comply with requirements imposed by [document ref. TBD], RBSP Space Asset Protection Plan EFW-211 Instrument Compliance with Safety Program Plan shall comply with requirements imposed by [APL document ref. TBD], RBSP System Safety Program Plan EFW-212Observatory Naming Convention shall use an observatory naming convention, as follows: -- Observatory A is the top observatory in the stacked configuration for launch; -- Observatory B is the bottom observatory in the stacked configuration for launch.

35. 1953-4 Sept. 2008EFW INST+SOC PDR EFW AXB Design Requirements Mechanical Design Requirements –From 7417-9019 RBSP Environmental Specification, Rev. H –Quasi Static Limit Load: 25 g (5 kg to 25 kg) –Factors of Safety: See Chart –Provide a fundamental frequency of greater than 50 Hz (Stowed). Factor of Safety (FOS) Type STATICSTATIC SINESINE R / A A C N O D U O S M T I C Metallic Yield1.3 1.6 Metallic Ultimate1.4 1.8 Stability Ultimate1.4 1.8 Composite Ultimate1.5 1.9 Bonded Inserts/Joints Ultimate 1.5 1.9

36. 1963-4 Sept. 2008EFW INST+SOC PDR EFW AXB Design Description: Materials Materials and Properties Assumed –Metals, Yield Stress: Brass 360, 49 kpsi Aluminum, 2024-T8, 58 kpsi Aluminum, 2117-T4, 24 kpsi Aluminum, 5052-H32, 28 kpsi Aluminum, 6061-T6, 40 kpsi Beryllium Copper, #25 (C17200), 160 kpsi Bronze C544, 35 kpsi Copper (Oxygen-free, C10100), N/A Elgiloy, Spring Temper Steel, SS, 18-8, 70 kpsi Steel, SS, 300 Series, 30 kpsi Steel, SS, 400 Series, N/A Tantalum per ASTM-B365-98, 65 kpsi (Ultimate) Titanium, 6Al-4V, 120 kpsi

37. 1973-4 Sept. 2008EFW INST+SOC PDR EFW AXB Design Description: Materials Materials and Properties Assumed –Composites: Graphite Epoxy - Fiberite Hy-E 1034C or eq (M55) –Plastics: Acrylic (Medium-high impact), 6kpsi Black Delrin, 11 kpsi (Ultimate) White Delrin, 11 kpsi (Ultimate) Vespel SP3, 8 kpsi (Ultimate) PEEK, 16 kpsi

38. 1983-4 Sept. 2008EFW INST+SOC PDR EFW AXB Design Description: Materials Materials and Properties Assumed –Adhesives: Hysol 9309NA, 4 kpsi (Tensile shear Strength) Hysol 1C Hysol 0151 3M EA1838 3M EA 2216 –Tapes: Kapton Tape (acrylic adhesive) –Lubricants: Braycote 601 –or— Braycote 601 EF DAG 154 Paint

39. 1993-4 Sept. 2008EFW INST+SOC PDR EFW AXB Design Description: Materials Coatings Used –Alodine per MIL-C-5541 CL 3 (Gold) –Black Anodize per MIL-A-8625 Type II, Class 2 –Hard Black Anodize per MIL-A-8625 Type III, Class 2 –Electroless Nickel Plating with Teflon Impregnate –Silver Plate per QQ-S-365 Type I, Grade A –Vapor Deposited Nickel –Braycote 601 –or— Braycote 601 EF –DAG154 Paint –DAG213 Paint

40. 2003-4 Sept. 2008EFW INST+SOC PDR EFW AXB Design Description: Stress Margins Critical PartStress Margin Stacer Frangibolt14 Mounting Flexure0.6 Mounting Flange2.7 Mounting Tube10 Tube Bond (Top)30 Whip Tube128 Whip Hinge Pin34

41. 2013-4 Sept. 2008EFW INST+SOC PDR EFW AXB Design Description: Tube Structural Design –End Supported Tube: Graphite Epoxy, M55 (Layup: 0, 45, 90, 45, 0 [quasi-isotropic]) –Fixed-Fixed First Frequency: 257 Hz 257

42. 2023-4 Sept. 2008EFW INST+SOC PDR EFW AXB Design Description: Boomss

43. 2033-4 Sept. 2008EFW INST+SOC PDR EFW AXB Design Description: Booms Whip and Spherical Electric Fields Probe –Hinge Torque Margin: 3.63.6 Hinge Spring to Friction DAG 213 Coated –Whip Tube FOS (Bending on Deploy): 2.0 DAG 213 Coated –Sphere Probe and Preamp Assy DAG 213 Coated Cannot Clean –All Three Isolated for Potential Control –Fundamental Frequency: 23.0 RPM (> 4x SC Spin Rate  Rigid) Stowed Configuration Deployed Configuration Whip Sphere Hinge Preamp

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