Sounding Rocket Working Group

21 January 2014

The attached documents contain technical data within the definition of the International Traffic in Arms Regulation, and are subject to the export control laws of the U.S. Government. Transfer of this data by any means to a foreign person, whether in the U.S. or abroad, without an export license or other approval from the U.S. Department of State, is prohibited. Similarly, publication or other release into the public domain constitutes an export and is not authorized, except as approved by the cognizant U.S. government department or agency. NSRP Briefing Outline

• Programmatics - Eberspeaker/Schafer  SRPO  NSROC • Schedule Adherence - Eberspeaker • Success Criteria Guidelines - Ransone • Anomaly Status - Rosanova • Motors & Vehicle Systems - Brodell/Hesh/Hunter  Surplus  Peprgrine  Brants  Orioles  FTS  Caster • Annual Report & PI Questionnaire - Eberspeaker • Educational Activities - Eberspeaker/Koehler • Range Status - Ransone  Wallops  Pker  WSMR  Kwajalein  Norway  Australia • Technology Development - Rosanova / NSROC

2 SRPO Programmatic Eberspeaker

1. Strong Concern Regarding Program Vitality (Letter sent to NASA HQ) • The SRPO appreciates the support… 2. Establishing Kwajalein and Woomera as “Routine” Rocket Ranges • “Routine” may not be exactly the right term.

– The SRPO plans to return to Kwajalein periodically and intends to minimize cost by regulating the campaign complexity and number of flights so that intrinsic assets can be used.

– A Woomera campaign is under early stages of development and the SRPO plans to minimize costs by minimizing the need for mobile support assets.

– Status on these elements are provided in the Launch Ranges Section. 3. Success Criteria Guidelines and Examples • The development of these guidelines is ongoing. The concepts are explored in the Success Criteria Guidelines section. 4. Continued Development of Recovery Systems • Concepts to enable high energy recovery are being assessed. It is a complex issue that involves hardware development, software tool development, and operational considerations. Status of the efforts is provided in the Technology Development section.

4 Missions Flown Since Last SRWG

• Core Science • Technology & Risk Mitigation – 21.140 / Pfaff / Daytime Dynamo –None • Success – 41.090 / Pfaff / Daytime Dynamo • Education • Success – 41.106 / Koehler / RockOn – 36.239 / Korendyke / • Success – 46.005 / Koehler / RockSat – 36.290 / Woods / EVE • Success • Reimbursable – 36.294 / McCammon / –None • Success Note: in some cases – 36.296 / McCandliss / Ison success noted is based • Success on preliminary PI report – 36.261 / Clark / VESPR • Success

FY12/13 40 consecutive FY13 –19 flights successful flights 5 FY13 Completed Missions

Mission Launch Site PI Project Comments Date

1 36.255 S Nov 2 WSMR Krucker FOXSI Success - 2 36.260 G Nov 21 WSMR Cook M101 Imager Success - S-19 joint broke on landing (fall over). Mirror mount damage.

3 36.283 H Dec 13 WSMR Galeazzi DXL Success - Dual side looking doors. Brant MK1 had combustion instability

4 41.107 T Jan 29 WFF West Lithium Test Flight Success Launched within 5 minute window as required. Both releases observed.

5 49.001 E Feb 2 PFRR Rowland VISIONS Success First flight of Talos-Terrier-Oriole-Nihka. Vehicle flew within ~1 sigma.

6 41.104 TFeb 15 WSMR Rosanova Uplink Exercise Success Uplink command test + 20 Mb/s test

7 36.269 S April 9 WSMR Rabin Success First flight of Gate approach. Benign winds & no issue with gate

8 36.271 GApril 21 WSMR France Success No issue with winds or gate

9 41.100 R April Kwaj Caton Success – flew 5 sigma low 10 41.102 R April Kwaj Caton Success – Flew TBD sigma low 11 46.001 E April Kwaj Kudeki EVEX Success – Flew low 12 45.005 E April Kwaj Kudeki EVEX Success – Flew low 13 36.268 G May 10 WSMR McCandliss FORTISS #1 Success – No Gate issue. Scattered light impacted science

6 FY13 Completed Missions

Mission Launc Site PI Project Comments h Date

14 40.030 G June 4 WFF Bock Success - First telescope flown on BBXII. 11 targets observed 15 41.106 Edu June 20 WFF Koehler RockOn VI Success

16 41.090 E June 24 WFF Pfaff Daytime Dynamo 17 21.140 E June 24 WFF Pfaff Daytime Dynamo Investigating ACS gas leak on upleg and impact on science data 18 36.239 S Aug 8 WSMR Korendyke Success 19 46.005 Edu Aug 13 WFF Koehler RockSat‐X III Success

FY14 Completed Missions

Mission Launc Site PI Project Comments h Date

1 36.290 SOct 21 WSMR Woods EVE Success 2 36.294 H Nov 1 WSMR McCammon Success. No filter icing. Combustion Instability at T+30 sec. Gate approach worked well

3 36.296 G Nov 20 WSMR McCandliss FORTIS Success. Launched 1 day late due to sealing issue with experiment butterfly valve 4 36.261 G Nov 26 WSMR Clarke VESPR Success. Launched 1 day late due to sealing issue with experiment butterfly valve

7 CY14 Planning Manifest

8 CY15 Planning Manifest

9 Flight Rates

Year Core Reimbursable Total 2005 11 8 Target 19 2006 8 14 Target 22

Restoration 0 2007 18 18 2008 12 4Target + 1 Sci/Tech 17 Budget 2009 13 5Target + 3 Sci/Tech 21 2010 13 5Target + 1 Tech 19 2011 12 1 Target 13 2012 20 1 Tech 21 Upgrades 2013 17 2 Sci 19

WSMR ‐ Target missions are low complexity ‐ Sci/Tech reimbursable missions are generally medium to high complexity

10 Flight Rate

11 Mission Initiation Conferences

FY 03 04 05 06 07 08 09 10 11 12 13 MICS 20 18 31 13 14 24 18 15 21 12 18

Flights Initiated 35 30 25 20 Held

15 MICs 10 5 0 2003 2004 2005 2006 2007 2008 2009 2010 2011 2012 2013 FIscal Year

Includes core and reimbursable missions

12 Schedule Adherence Eberspeaker

21 January 2014

• SRWG Concerns / Comments  Experiment teams and NSROC should demonstrate that they are on schedule before certain milestones occur • Response: – The SRPO concurs, but this does not help prevent milestones from slipping – which then cascade to impact other milestones.

 Slips should be implemented “without blame” • Concern: Do not implement automatic “go to the end of the line” approach • Response: – The SRPO understands that “go to the end of the line” can be a problematic solution. As usual, the SRPO will attempt to find a logical launch slot for delayed missions, but teams must understand that optimum dates may not be available. – Slips must be identified as early as possible to allow efficient integration of the project schedule into the overall program workflow  Financial penalties will be counterproductive • Concern: Delays are often due to technical issues and lean budgets and withholding funding would tend to aggravate the situation. • Response: – The SRPO capitulates on this aspect. However, science teams should not hold any expectation that funding augmentations will be available to cover mission slips and impact on funding can not be ruled out in extreme cases.

20 Schedule Adherence

• SRWG Concerns / Comments  Schedule Credibility Review will be counterproductive • Concern: Sounds “formal” and could be time consuming and costly. Suggest implementing less formal “Benchmark Reviews” prior to CDR, Integration, and Launch Operations • Response: – More “reviews” won’t solve the problem. – The program needs to anticipate schedule issues as early as possible so resources can be applied to them before the impact snowballs (i.e. gets us into a situation where overtime is needed during integration when maximum resources are involved, or when field operations are underway). – The SCR was intended to be a “oops, we blew it - where do we go from here” assessment (i.e. is there any real hope of meeting launch date, is science so critical that we need to invest resources to meet schedule, will a delay require more funding, etc.). HQ would be involved since science criticality, R&A budget, and impact on other missions may be involved.

21 Schedule Adherence

• SRWG Concerns / Comments  Missions are proposed as “success oriented” projects and no funding is available for “slack”. Exhaustive schedule planning (similar to a satellite program) does not appear feasible. • Response: – Exhaustive schedule planning is not envisioned. – The SRPO feels that achievable delivery schedules (both on science and NSROC side) can be developed which provide some definable schedule contingency. Consumption of this contingency will serve as a gauge of the status of the project.

Jan Feb Mar Apr May Jun Jul Aug Sep Oct Nov Dec

MIC DR T&E MRR Field Ops

Instument A (New design) ‐ Design ‐ Fabrication (schedule uncertainty item) ‐ Pre Integration Vacuum Test

Instument B (semi‐Clone of existing ) ‐ Design Modifications ‐ Fabrication ‐ Pre integration Deployment Test

Attitude Control ‐ Analysis ‐ Integration Prep ‐ Experiment A Handshake Tests (@ WFF) ‐ Prelim Airbearing ‐ Final Airbearing 22

TM ‐ Design (schedule uncertainty item) ‐ Mechanical Fabrication ‐ Electrical Wiring ‐ Bench Tests Schedule Adherence Implementation

• Mission Managers are now collecting more detailed PI milestones and coordinating milestones/activities  The effort has resulted in planned delays of premature activities such as Design Reviews, allowing for more efficient work effort.

• NSROC overtime is down 30%  Due in part to better schedule control and reduction in wasted effort  Provides better work/life balance  More efficient use of time provides folks with the opportunity to play a little catch-up

• We still have a way to go  Non-functioning instruments still arriving at Wallops . Has resulted in undesirable violation of testing protocols and/or long integration periods  The 2014 Manifest was at 21 flights, it has shrunk to 14 due to slips – we need to keep the flight rate up…  The SRPO acknowledges that the program can cause slips (i.e. looming FTS ordnance availability…)

23 Success Criteria Guidelines Ransone

21 January 2014

• SRPO is developing “standards” for Minimum and Comprehensive Success Criteria  Reported at last SRWG but effort keeps getting pushed back due to other priorities • Goal is to define acceptable criteria to ensure consistency across missions • Also, to aid PI’s in designing missions and developing criteria for both minimum and comprehensive success • This is a work in progress and will be scrubbed in the next several months  We may need a couple members of the SRWG to participate in review and/or development of these standards • What is presented here is open to discussion and presented only to stimulate thought and discussion

25 Success Criteria Guidelines

• Success criteria should be set based on what the PI needs to publish results  Too often we get stuck on the min/max capabilities we can provide  This is understandable being we need a metric but don’t loose sight of the ultimate goal • Negotiating success criteria must be done with the SRPO  This starts at the MIC and must be maintained throughout the lifecycle  We work as a team with NSROC but ultimately SRPO is responsible • We want all experimenters to realize that setting a really “tough” success criteria does not mean we try harder to reach that goal  We always strive for comprehensive success but have to deal with the limitations of our systems and our budgets

26 Success Criteria Guidelines

• One overarching “criterion” set by the SRPO that should be stated (even if it is obvious)…….

• We will not launch a mission unless we have reasonable probability of meeting comprehensive success  Discussions on this happen more than one might think when instruments are not functional or are marginal once on the launch rail  This should be a consideration when developing these standards  In some instances we may elect to launch anyway but this requires significant discussion with SRPO, PI, NSROC team, and HQ

27 Success Criteria Guidelines

• Apogee Criteria  Some missions require a “time above” threshold; others require a minimum apogee  Minimum success has historically been set at 2 sigma (~98%) •ACS Pointing  Varies by system, application, and to some extent payload design  System specifications and/or best observed performance factor into this criteria • Attitude Knowledge  Varies by system design, which sensors we employ, and in some cases operational constraints (e.g. time of day)  It may also be a function of our ability to resolve attitude and/or PI post mission processing • Recovery  Minimum success shall not require recovery • Under very unique circumstances this may be accepted…perhaps retrieval of recorded data  Comprehensive success can include recovery

28 Success Criteria Guidelines

• Telemetry Coverage  Many times experimenters require XX% of error free data during the defined “science period”  Many factors can affect our ability to collect this data • Bit rate, performance of the mission, G/T of range assets, number of links vs. range assets, antenna patterns, etc. • “Error free” is also an ambiguous statement  In general, this has to be defined with the specific mission and unique set of circumstances in mind • Number of functional instruments  Again this is a unique criteria that is mission specific  Experimenters should not expect that 100% of instruments will function as designed to have a minimally successful mission  This is primarily a PI determined criteria that should be based on past history, unique mission requirements, and system and operational limitations

29 Success Criteria Guidelines

• Test and Evaluation of Science Instruments  Much of the SRP past success given our approach to Q/A (and our budgets) is based on “fly as you test” philosophy and a robust test program • Many design weaknesses/flaws are discovered during T&E and fixed  As with most SR provided systems, all science instruments are expected to successfully go through T&E unless specific exemption is granted • Especially relevant for instruments required to meet minimum success • Post T&E Modification of Science Instruments  For science instruments required for minimum success there should be NO post T&E modification of the experiment • Post T&E “calibration” is sometimes required but it does need to be looked at carefully to ensure we do not increase risk of failure • Need to ensure any modifications will not risk other instruments or systems

30 Success Criteria Guidelines

• Piggy Back Experiments  Piggy back experiments are a good way to test new design concepts for future flights • SRPO encourages this practice when practical  Cannot be part of success criteria unless part of the PI’s proposal  Need to be designed and operated such that they do not add undue risk to instruments needed to meet mission success • HV instruments are a good example for consideration……can a HV arc take down the TM system or other instruments??

31 AIB Updates Rosanova

21 January 2014

Failures AIB lead Status None

Anomalies AIB Status Lead 49.001 Premature Deployable Door Release NSROC AIB complete. Root cause: Flawed analytical approach to predicting aerodynamic loads on large deployable door.

41.100, 41.102, 45.005, 46.001 Vehicle NASA AIB complete. Root cause: Inaccurate drag models. Underperformance 36.268 Shutter Door Plate Shatter on Impact NSROC AIB complete. Root cause: Inadequate material properties verification and traceability.

21.140 ACS Gas Leak in Flight NSROC AIB complete. Root cause: Faulty valve design.

49.002 Air Spring Test Safety Barrier Breach NASA AIB complete. Root cause: Insufficient assessment of risk Close Call posed by high energy air spring that was outside the experience heritage of the Program

46.001 TMA Leak Close Call NASA AIB complete. Root cause: Bellows valve material susceptibility to corrosion in marine environment

40.030 LN2 Dewar Line Rupture Close Call NASA AIB complete. Root cause: Insufficient awareness and training to recognize hazards of cryogenic system and thus require safety review and oversight. 33 Effect on PI’s from Recent Close-Call Anomalies

• Cryogenic systems – Training: NSROC, NASA personnel will have to complete cryogenic system training – Experiment Teams will be required to provide training certification for their personnel – Documentation: Cryogenic system drawings and operating procedures will have to be reviewed and approved by WFF Safety – Analysis: Experiment Team to supply specifications on system components for WFF-Safety to perform analysis for compliance with NASA cryogenic standards – Hardware inspection: WFF Safety or delegated organization to perform inspection prior to first use or after any subsequent design changes. Also will include inspection of vendor-supplied cryogenic subsystems and components such as dewars, tanks, etc. – OSS required for initial execution of operating procedures Continued…

34 Effect on PI’s from Recent Close-Call Anomalies Continued

• Chemical Release systems – Selection of design materials: Minimize susceptibility to corrosion – Safety-related design features: Neutralize hazards, such as remote actuation of pressure chamber relief. – Back-out/Contingency procedures and PPE for launch pad fires, spills, etc. – Operational requirements changes: Some Experiment Team members may be defined as essential personnel after scrubbed launch attempt, to remain available until all operations are concluded.

35 Motors and Vehicle Systems Brodell/Hesh/Hunter

21 January 2014

37 Surplus Motors Brodell

• Surplus DOD booster inventory is healthy  Talos • Indian Head has re-certified SOPs for Talos refurbishment • Two motors re-furbished and ready for flight – Support manifest through end of CY14 • Six motors received from Hawthorne inventory in November 2013 • Three motors being shipped to Indian Head for refurbishment this CY  Taurus • Working plan to replace with the MK70 as the second stage in 3-4 stage applications – MK70 has flown four times as second stage – Tailcan-fin hardware ordered for MK70 second stage application • Static fired 25 of 50 Taurus motors in disposal effort  Terrier MK70 • Significant inventory stored at Hawthorne • Plan to have 24 shipped to WFF this CY to refresh local inventory  Terrier MK12 • Large surplus assets identified at McAlester – Transferred 12 motors to WFF that were received in December 2013 • Utilizing linen phenolic spacer when short grains are identified during refurbishment

39 Surplus Motors (cont.)

 Improved Malemute • Received 35 propulsion units with 45 exit cones in 2012 • Transferred 10 motors to from McAlester that were received in December 2013  Eliminated Nike inventory • Traded with China Lake for Talos assets  In discussion with Navy about surplus Lynx (MK104) motors  Improved Orions • Conducting inspection/test program to qualify older motors for program use – Inspection and static firing of four motors – Post firing inspections look promising – In process of inspecting/preparing one of the older 50,000 series motors to donate to the Navy for a single stage technology flight at WSMR » Motor will be recovered for post flight inspections

40 McAlester X-ray Capability

• BB x-ray capability at McAlester has been established  Utilize digital computer controlled equipment  Digital has 2X the clarity of the film  High resolution computer support equipment has been acquired  Automated digital process offers excellent cost savings, ~8X less expensive  McAlester has been very responsive to schedule needs • Working initial plans to enable X-ray inspection of Nihka motors • McAlester NIPR has been broadened to include storage, shipping, and logistical support  Period of performance extended to five years from initiation 41 NASA IG Explosive Audit

• Inspector General (IG) led audit to review NASA’s Explosive Safety Program  Audit conducted summer 2012  Findings released March 2013 with 28 WFF specific findings • A WFF Explosive Safety Officer (ESO) position has been established in the WFF safety office  In process of re-certifying site plans and limit capacities for all explosive storage buildings on Wallops Island and Mainland  Enhancing inventory system  Mandatory inspection of all incoming explosives  Re-organizing inventory for storage efficiency and ease of access  Safety Office approval required before receipt of explosive materials  Reducing unnecessary explosive materials • Elimination materials with no scheduled usage  New GPR for GSFC Explosive Safety Program is under review • Developing plans to eliminate 1.1 explosives (Taurus motors)  MK70 to replace Taurus

 Spin motors?? 42 New Taurion Vehicle Configuration

• New low performing vehicle configuration • All surplus vehicle hardware • Customer apogee requirement of 8K ft at Mach .8 • No existing motor meets flight needs  Improved Orion impulse is best fit for this application • Considering mass of the test article and the Orion impulse, weight and drag was required to get to flight conditions • Taurus case is very heavy and high drag with large diameter • 25 Taurus cases and hardware laying around on Wallops Island • Utilize expended Taurus case post static firing Surplus Taurus  First NASA use of the tactical fins Hardware  Taurus-Orion lug configuration * We get you where you need to go… cheaply

Thrust Tube Orion Motor Taurus Case

43 Peregrine Development Effort

Brodell

• Develop an alternative sustainer motor for the Sounding Rocket Program • Mitigate programmatic risk associated with the current SRPO sustainer motor  Several sustainer issues existed at the time of Peregrine kick-off • Create NASA owned design to facilitate easier design evolution • Grow in house propulsion knowledge through hands on involvement and partnership with industry • Establish multiple vendors to mitigate supply risk • Help foster competitive market

45 Peregrine Fabrication Approach

• The fabrication effort has been separated into three contracts in order to realize the lowest cost

• Igniter to be machined in house and be cast by Army at Redstone Igniter

Complete Assembly

Metal Case Flow formed + Three Insulation contracts Aft Closure managed Exit Cone by NSROC (AAE) +

Propellant

46 Peregrine Scope

• Fabricate six motor cases • Conduct one hydro burst test • Cast one “inert” pour • Cast four “live” motors Inert  Two cast operations at two motors per cast  One static fire and three flight tests

Case tubes and forward domes

Live

47 Peregrine Test Program

All tests include full instrumentation Static Fire, MSFC, 10/9/14

Terrier‐Peregrine Test Flight, WFF, 10/16/14

Talos‐Terrier‐Peregrine Test Flight, WFF, 1/13/15

S‐19 Terrier‐Peregrine Test Flight, WSMR, 2/12/15

48 Peregrine Hardware in Progress

49 Peregrine Status

• Conducted a HQ status review on 11/22/13  Presented technical status of case, insulation, and casting contracts  FY14 “re-plan” schedule was presented and accepted • Approximate 2.5 month extension for program • Primary delay is due to case manufacturing • Cost(s) remain within budget • All case tubes have been flow formed • Forward and aft dome pre weld machining is complete • Motor cases are in the process of welding forward and aft domes to center flow formed tubes • Hardware Acceptance Review of first two cases is expected in early March 2013 • Insulation Critical Manufacturing Review (CMR) was conducted on 11/15/13 • First aft closure has been completed, received, and shipped to case vendor to support case proof tests • Propellant formulation testing is progressing without issue • All casting tooling is in manufacturing • Shipping container received at cast vendor on 11/7/13 and DOT certification is in process 50 Igniter Development

• Pyrogen design is based on the extensively tested MSFC Ullage motor igniter design • Igniters to be cast at Army Aviation and Missile Research Development and Engineering Center (AMRDEC) in Huntsville • Igniter hardware fabricated at MSFC Igniter proof test • Proof testing of igniter assembly components (chamber, closure and exhaust port) is complete with no significant issues • Pre cast igniter Critical Manufacturing Review is scheduled for next month • Open air igniter test will be conducted at MSFC by May 2014 • Assembled Igniter Hardware Acceptance Review is scheduled for July 2014

51 Igniter hardware Vehicle Hardware Status

• Hardware includes tailcans, inter-stage adapters, fins, lugs and testing/manufacturing fixtures  For all 1-4 stage configuration • All designs 100% complete • Prototype hardware in process of manufacturing  Manufacturing at 95% completion • Load and qualification testing of fins/tailcan assembly completed this month • Fin design balanced for all 1-4 stage vehicle configurations  Design developed by AETD/NSROC  Prototype delivery in December 2013  All production fins to be delivered by June 2014

52 Payload Development

• 12.077 - Design Review conducted September 2013

 Two stage Terrier MK70-Peregrine configuration, WWF launch site 12.079  No recovery WFF  Full diagnostics instrumentation to evaluate flight performance  Ames Research Center STP re-entry experiment 12.078 WSMR • 12.079 - Design Review November 2013 12.077 WFF  Three stage Talos-Terrier MK70-Peregrine configuration, WFF launch site WFF  No recovery  Inert fourth Nihka stage  Qualifies both three and four stage configurations by determining the hand-off conditions for the theoretical fourth stage ignition  Full diagnostics instrumentation to evaluate flight performance  Glen Research Center Heat transfer STP experiment • 12.078 - Design Review scheduled for March 2014  Two stage Terrier MK70-Peregrine configuration, WSMR launch site  Implementation of Peregrine S-19 Guidance and FTS systems  Payload to be recovered  Peregrine motor to be recovered o Evaluate insulation margins o Evaluate nozzle erosion characteristics of the spinning flight

 GSFC GPS Spacecube and MSFC Cubsat communication experiments 53 Peregrine Schedule

54 Black Brant Status Hesh

•SRPO has cleared all Black Brant class vehicles for flight •6 successful Black Brant missions since last SRWG meeting •5th combustion instability experienced on 36.294 McCammon in November 2013 – Similar behavior to 36.283 Galeazzi combustion instability • Black Brant performance still showing signs of improvement –The unblended AP mixing process continues to improve nozzle erosion – Performance is more consistent, even across different version motors –The new AP and process has not decreased the likelihood for combustion instability •NSROC continues to inspect flown motor hardware to study the erosion patterns and margins in the nozzle

Combustion Instability Missions – Ongoing Inspection of Pressure Curves from Recovered Hardware Chamber Pressure Recent Missions 56 Black Brant Evolution Definitions

# on Comb. # In Version Definition Flt Count Instabilities Inventory Mk1 Version 0 Baseline BB Mk1 design with US oxidizer (AP) 3 0 0 Mk1 Version 1 Switch from US oxidizer to Chinese oxidizer 24 2 2 Mk1 Nozzle throat size increase, cylindrically bored out post motor Version 2 assembly 10 0 1 Mk1 Version 3 Nozzle throat size increase, contoured pre motor assembly 3 1 1

Mk1 Chinese oxidizer not pre-blended, larger nozzle throat size contoured Version 4 pre motor assembly. 5 0 0 Motor case material change from 4335 to hybrid 4335 rings/4140 Mk2 sheet steel, Chinese oxidizer not pre-blended, larger nozzle throat Version 0 size, contoured pre motor assembly. 2 0 0

Mk2 Switch from Chinese oxidizer to US oxidizer. Second nozzle throat Version 1 size increase, cylindrically bored out post motor assembly 7 1 0 Mk3 Motor case material change to 4140 with closed die forging end rings, Version 0 nozzle throat size same as Mk2 V1, contoured pre motor assembly 2 0 0 Mk3 Version 1 Nozzle graphite material change, all other features same as Mk3 V0 5 1 7 61 total flights of BB Mk1/2/3 motors 57 Continued Stability Testing and Analysis

• Combustion Instability study with MSFC/WFF/China Lake is Frequency response ongoing from T‐burner testing  NESC/SRPO supported effort • T-Burner tests completed  Testing completed on Mk1 (Norchem, unstable motor) and Mk2 (Wecco AP)  Testing to be performed on standard Brant propellant and future BB Mk4 propellant  Quench bomb tests conducted on samples to determine particle sizes  Microscopic inspection of propellant completed Propellant Instability Growth Rate • MSFC has completed analysis using the Standard Stability Prediction (SSP) code and released a report • Continue to collect and analyze flight data and recovered motor hardware

Magnified image of T‐burner test hardware CFD results showing vortex dynamics in fin slot propellant surface

58 Black Brant Inventory, Contracts and Delivery Schedule

• Total of 11 Black Brant motors in inventory (4 BB Mk1, 7 BB Mk3)  4 BB Mk1 motors are quarantined from WSMR use due to pre-blended Chinese propellant • BB Mk1 motors will be utilized at WFF and PFRR where possible  BB Mk3 motors will be flown from WSMR until BB Mk4 is flight qualified • 2 Black Brant motor contracts:  Contract for 12 motors (option year 4 contract) • 10 motor deliveries remaining in FY14  Contract for 12 motors (option year 5 contract) • FY14 long lead and early production contract issued to Bristol – 12 Black Brant Mk4 motors will be delivered in FY15 • Long Lead Procurement Activities  WECCO Type II Ammonium Perchlorate • Bristol has purchased enough material to ensure continuous production on all option year motor contracts  4140 Steel • Bristol has received sheet steel and forgings to ensure continuous production on all option year motor contracts

59 Bristol Technical Updates

• New Graphite Throat Insert  R7340 graphite has performed similarly to heritage ATJ graphite  5 flights completed with new graphite nozzle • 3 of the 4 motors recovered with new graphite nozzle have had throat ejected on impact

a) ATJ, Pre‐blended Norchem, 3.9” throat b) ATJ, Unblended Norchem, 4.3” throat

c) ATJ, Unblended WECCO, 4.3” throat d) R7340, Unblended WECCO, 4.3” throat

60 Bristol Technical Updates

• Black Brant Mk4 Development  Working toward a configuration that is as close as possible to the standard Black Brant motor with updated materials and using industry “rules of thumb” to minimize the risk of combustion instability  Propellant formulation began in February 2013 and Bristol has completed 13 sub-scale tests to date, varying many propellant parameters to determine the best path forward for a final formulation  Varied % solids loading, decreased aluminum content, using smaller particle sizes of AP, and a bi-modal AP blend • Resulted in a burn rate that is within specification, but higher than the historical standard Black Brant burn rate  To mitigate the higher expected chamber pressure (due to the higher burn rate) the nozzle must be redesigned to have a larger throat diameter than the standard Black Brant motor and have more material margin  Current schedule shows completion of the first article test motor in the September-December 2014 timeframe

61 Black Brant Summary

• A fifth combustion instability occurred in November 2013  Cannot predict or prevent combustion instability and resulting vibration levels  Implementation of “Gate” rule has worked well and has allowed WSMR launches to continue  Potential for high vibration levels pose a risk to mission success • Migration to unblended US ammonium perchlorate in the propellant has produced better consistency in pressure curves and reduced nozzle erosion • New graphite in nozzle has been qualified and flown  Similar erosion performance as heritage ATJ graphite • Bristol’s motor production schedule has improved resulting in a growing motor inventory to support 2014 missions • Working toward a Black Brant MK4 configuration that will operate near the standard Brant pressure with the same or larger throat diameter, and follow industry “rules of thumb” to reduce the risk of combustion instability  Intended to eliminate combustion instability and move away from “gate” rule • SRPO and NSROC are continuing to work with China Lake, MSFC, and propulsion experts across the country to review flight data, test the Black Brant propellant, and analyze the motor

62 Oriole Rocket Motors Hesh

• Oriole motors have been procured to augment supply of sustainer motors • Six Orioles received to support program needs • Supported four science missions to date  45.004 / Larsen March 2012 at WFF  12.075 / Test flight September 2012 at WFF  49.001 / Rowland February 2013 at PFRR  45.005 / Kudeki April 2013 at Kwajalein • Two flights remaining  49.002 / Swenson January 2014 at PFRR  49.003 / LaBelle November 2014 at Andoya • Four stage vehicle performance improvement with MK70 and Oriole in stack • Higher mission cost with this motor • Residual post burn Oriole thrust causing some mission implementation issues • Cannot support all missions due to stability criteria concern • No additional assets on order at this time • Kratos planning test flight of guided Oriole using TVC from WSMR

64 Flight Termination Status Adam Hunter

21 January 2014

• Implementation of new electro/mechanical safe and arm device complete.  Flown on 5 successful missions. • FTS Ordnance  NSROC has two orders of Ordnance on order, both have seen failures during Lot Acceptance Testing and caused delays in delivery.  Delivery Issues • NSROC FTS Controller (FTSC)  Acceptance testing completed, Qualification testing procedures and documentation is in the approval process. FTS Battery Cell  Qualification completion date early summer 2014 Matching Board • WSMR 3-Event CDI  First flight on 36.290 was successful. • Battery Cell Matching  Completed the design of hardware and software to capacity match FTS battery cells. • This has streamlined the acceptance testing of the FTS hardware.

39.290 Woods CDI 66 FTS Paddle Update

• Thermal Cycle Failure  During qualification testing the paddle material and epoxy had two separate failures. • The paddle material outgassed at high temperatures and caused surface ruptures. • The epoxy holding the Linear Shape Charge to the paddles failed at high temperature.  The failures occurred at +156°C, well above the previous lot testing of +71°C. • Solution/Path Forward  Thermal Protective System be adhered to the paddle • Reduces the test temperature requirements to +71°C, the same specification as the previous lot. • Orbital- LSG is performing thermal analysis to determine the Thermal Protective System thickness.  Not enough epoxy was in contact with the Linear Shape Charge. • To correct this, a step will be added to the manufacturing process to backfill the channel where the Linear Shape Charge is held.  Vendor is updating the schedule with the potential for a mid-summer delivery.

67 Conical Shape Charge Update

• Two flight ready CSC’s are available. • A failure occurred on the last unit tested during functional testing of the most recent lot of CSC’s • Failed Lot Investigation  The environments seen by this CSC were out of the norm for the lot, and the lot was exposed to higher levels than previously tested to.  WSMR Missile Flight Safety is considering a Delta Lot Acceptance Test at NSROC levels. • The test plan would yield 13 flight units and is scheduled to be complete by early summer Conical Shape Charge  NSROC is working with the Vendor to perform additional root cause failure testing.

68 FTS Inventory and Order Status

• Funding constraints continue to be problematic for acquiring larger orders of FTS hardware which results in a “just in time” delivery for many components  Results in higher risk for not being able to support missions if vendors deliver late • Antennas  Adequate inventory to support mission manifest  New order placed in December 2013 • Receivers  Adequate inventory to support mission manifest. • Batteries  Capacity matching has been performed on the remaining cells in the qualified lot.  Manufacturing and acceptance testing continues to meet the mission manifest.  A new lot of batteries is in the budget for FY14, this will be ordered and qualified as time and resources permit. • Electronics Box  Flight Termination Logic Unit – Orbital LSG • Current orders of FTLUs can support 11 flights through January 2015.  Flight Termination System Controller – NSROC development • 4 units built and acceptance tested for qualification effort. • Qualification completion is set for Summer 2014.

69 Castor Rocket Motors Eberspeaker/Krause

• Three Castor motors were obtained by Wallops  This is more of a Wallops capability rather than an SRPO initiative  Supplies are limited (maybe the only 3 we can get) • They were obtained with the hope to support some yet-to-be- determined reimbursable mission(s) in the future • The cost of a castor-based launch vehicle is generally prohibitive and not entirely consistent with the nature of the SR program  Taking the motor to a flight condition will not be a trivial investment

71 Castor IVB Opportunity

• The Missile Defense Agency Is Providing NASA With Three (3) Castor IVB Guided Rocket Motors  Orbital Sciences and the European Space Agency Have A Successful Track Record With The Castor IVB  Five Conical Shape Charges Provided With These Motors Offset Transfer Cost and Avoided eight (8) month WSMR ‘shut down’ • Single Stage Castor IVB and Castor IVB with Upper Stage Provides Unique Capability For The Appropriate Application • Orbital Is Providing NASA With A Trade Study On The Best Implementation Approach And Associated Budgetary Pricing  Orbital LSG  Swedish Space Corporation  Wallops Integrated Approach

72 Castor IVB Rocket Motors

• 3 each Castor IVB Rocket Motors will be provided to the NSRP  2009 lineage  Solid propellant motor from ATK  Gimbaled Thrust Vector Control • 2-axis control

• Successful heritage  37 motors built since 1991  29 motors flown in Sounding Rocket configuration, ballistic trajectories

• Scheduled for arrival in 2014

73 Castor IVB Launch Vehicle

• Performance Capability for Single Stage  MAXUS flights with 25”ø payload Payload Weight (lbm) Altitude (km) Time above 100 km (sec) 1,763 (800 kg) 700 765 (12m 45 sec)  Target Configurations include 38”ø, 40”ø, 52”ø payload • Typically flew max range trajectories • Current Status  Compiling trade study for program implementation • Flight Proven Providers – MAXUS – Swedish Space Corp (8 flights) – Target Launch Vehicle configuration - Orbital’s Launch System Group(18 flights) • Cost, Schedule, Flight Hardware, and Operational Technique • Additional capability also available  Add 2nd stage - M57A1

Payload Weight (lbm) Altitude (km) Time above 100 km 500 2,200 1,686 sec (>28 min) 2,000 1,000 970 sec (>16 min) 74 2013 Annual Report

The SRPO has published its 2013 Annual Report. Berit Bland has done yet another fine job in putting the document together.

Available in hard copy and on line…

75 Questionnaire

The SRPO needs to compile information concerning the number of graduate students involved with sounding rocket missions, instruments that migrated from sounding rockets to satellites, and scientific papers based on sounding rocket missions.

This data is vital in being able to demonstrate the value of the program to the nation.

The SRPO has sent out an email request to all current and past PI’s.

76 Education Eberspeaker / Koehler

• RockOn  Scheduled for June 19, 2014  Wallops Launch • RockSat X  Scheduled for August 12, 2014  Wallops  Colorado Space Grant investing addition of “piggy-back” canister with middle school “cubes” • Expand impact of the flight opportunity w/ not cost impact • Tie into a corporate educational initiative

78 Launch Ranges Ransone

• Wallops Island  Navy Targets program just launched 3 Terrier Orion’s in 1 minute off the island • 4 rockets were staged with only 3 launched (1 was a planned backup) • Their program may grow dramatically leading to increased launch capability on the island  Plans to move the 50K Launcher have matured and it is now certain it will be moved (without SRPO having to pay for it) • Recall this is VERY close to the Antares launch pad • This will give us 2 large permanent launchers on the island that are available routinely without schedule conflict issues • We have two more semi-permanent launchers (MRL and SuperHAD)

80 Launch Ranges Update

• Poker Flats Research Range  Team is in the field now supporting the Samara mission • Black Brant IX…..only vehicle to be launched this season  Swenson mission slipped a year due to technical difficulties but range was ready to support • Required 6 TM antennas to provide adequate TM coverage (redundancy) • Included completion of the new Redstone #2 Antenna  Plans underway to replace the MRL launcher taken to Kwaj • Another MRL has been located and will likely be installed this summer • This will restore the launcher capability of past years – total of 5  Environmental Impact Statement is COMPLETE!!!!! • Record of Decision signed by AA of SMD in late December • Expected path forward selected to continue operating as we have for many years with a more active and robust recover program – Summer launches not covered…..not eliminated but we are not encouraging it at this time due to fire and other environmental related issues • This recovery program is seen as a model for responsible operation in this sensitive region  Kathe’s replacement was hired – Bob Valdez has taken over many of the Ops Manager functions since she was promoted to Range Manager  No other issues to report……we continue to manage our funds wisely to keep the range open and functional 81 Launch Ranges Update

• White Sands Missile Range  Everything going good with new facilities now in operation  Rick Evavold is now the site lead and is doing a superb job keeping the facilities O&M as a top priority • WSTF is taking a more active role helping maintain our facility  Wireless internet recently installed in the VAB…….. • Best improvement in years!!!!!  New ViTS system being installed in conference room that can be tied in with SRPO conference room at Wallops  Cryo and Pressure operations receiving a lot of attention at WSMR (and Wallops as well) • We have not been fully compliant with existing and emerging safety requirements for some time…….expect request for more information  Discussions underway to move Navy 50K launcher to LC-36 • MRL is too small for most of our missions and is rarely used

82 Launch Ranges Update

• Kwajalein  Keeping much of our range infrastructure in “mothballs” on Roi  Goal is to keep as much there as feasible to reduce cost and make it more easily to do “routine” missions  Three launchers are there – one Army and two NASA  Payload Assembly “Tent” is still there and is standing • Effort to transfer/sell to RTS fell through • We may have it taken down and stored to extend the life •Norway  Working on preparing the range for upcoming LaBelle and Conde missions • One Oriole 12 and one Black Brant 12  Joint Implementation Plan was drafted by John Brinton before he retired and is almost ready for legal review; procurement package to follow  Range is planning to provide one 7m class TM antenna; Tromso or Svalbard will provide redundant TM coverage  Launcher crew scheduled for April/May launcher maintenance trip

83 Launch Ranges Update

• Australia  Campaign had to slip to Fall (Sept/Oct) 2016 • Driven by time required for new gov’t to gov’t agreement  After much searching and false starts, it was determined there were NO existing agreements under which we could conduct a SR campaign  New legislative requirements (Aust.) in place since our last campaign that address “commercial” use of space and liability/investigation  Agreement is in work with lead at NASA HQ Office of International and Interagency Relations • Kickoff telecom with Australian counterparts held prior to Holidays  De-scoped campaign “plans” to exclude high altitude vehicles • Zero tolerance for asbestos import is one factor – Talos has it • BBXI class vehicle dispersion is “off-range” and would further complicate agreement process • Will re-visit on future campaigns but not at this time

84 Technology Development Rosanova

21 January 2014

• DR conducted for 46.007 Sub-TEC 6, to be flown April 2014, WFF – NSROC will provide details for individual experiments to be flown. – Summary: • Refined Rocket-Propelled Sub-Payload systems • Refined strain gauge monitoring system • New High Data rate telemetry and recording components • New low cost inertial attitude solution (eventually for control on missions with loose pointing requirements) •New timer •New GPS • New command uplink hardware • New vacuum monitor • New high temperature wrap-around antenna • New HD camera • New gyro

86 Other Developments

• NSROC to provide details on each • Summary: – High altitude decelerators – Recovery/Location aides – Radially deploying payload skin – Radially deploying (and retracting) star tracker mount – Ground station support equipment upgrades

87 Technology Roadmap: 3-year

Sub‐TEC 7: X‐Band TM, More Small Sub‐P/L Sub‐TEC 6: Ejections, others Rocket‐propelled subs Several new TM components

14Q1 14Q2 14Q3 14Q4 15Q1 15Q2 15Q3 15Q4 16Q1 16Q2 16Q3 16Q4

20Mb/s TM Radial deploy High Alt Decel., Long dist on science mission skin test flight water recovy test flight (on student mission)

Planned Flights Proposed Milestones

88 Flight Performance Brent Edwards

21 January 2014

• The following analysis does not include the 100+ pounds of required waterproof and buoyancy material estimated by ME. Additional length for recovery support systems was not included. • Although the re-entry analysis does not show any significant probability of re-entry heating damage, utilizing a BBXII vehicle, the payload is entering the atmosphere at a much higher velocity and Mach of a typical WSMR BBIX flight. • Limitations of current 1D heating software can’t accurately predict re-entry heating. • Reentry damage predictions sensitive to re-entry body static margin. • With this payload weight, a BBX vehicle does not provide as much performance gain as a BBXI. • Impact ranges increase significantly with a multistage vehicle.

40.030 Bock payload modeled (861 lbs, 760 lbs re‐entry), Re‐entry conditions at 300,000 ft

Apogee Impact Range Velocity at Mach No. *Q (psf) Vehicle (km) (km) re‐entry (fps) at re‐entry at Mach 1 BBX 413 511 8417 9.5 215 BBXI 488 415 9015 10.2 126 BBXII 580 651 10100 11.4 233 BBIX (WSMR) 300 78 6500 7.2 172 (typical)

*Re‐entry payload specific, sensitive to re‐entry static margin.

90 Flight Performance

• Implemented and evaluated the new gate criteria for 8 successful WSMR guided launches. 2 required azimuth shift to meet launch criteria. • Re-write of the WSMR launch support software for Windows 7 compatibility and multiple improvements. Has proved to be more dynamic that heritage software. This is the prime simulation software for all future WSMR launches. • Working to increase predicted heating capability with the evaluation of more dynamic programs.

91 Sounding Rocket Recovery Aid Technology Nick Cranor

21 January 2014

Payload‐ Recovery Aid Recovery Aid Challenges Year Used Successful?

Christensen‐ Caribou tracker No The RF range of the tracker was very limited. That 2002 combined with the mountainous terrain of AK and subzero temperature effects on battery life, resulted in alengthy recovery search. The payload was eventually located visually from a helicopter. Lehmacher‐ Iridium No During this flight it was discovered that the Iridium 2009 GPS receiver could not handle sounding rocket flight dynamics. Since the Iridium tracker was on from T‐0, valid GPS data was not received. Green‐2011 Iridium No To mitigate the issues seen on Lehmacher the Iridium tracker was not programmed to turn on until after chute deploy. A parachute anomaly occurred during flight, not allowing iridium to function. Bailey‐2011 Iridium Yes None. Payload located with ease. Brodell‐2011 Payload Yes None. Payload located with ease. Iridium Motor No Spotter flights were sent immediately after launch; Strobes however the motor was never located. Global Star Streamers GPS did not function. Global Star GPS 93 Recovery Aids The existing NSROC Iridium system has been successful, overcoming many of the challenges experienced in the past; however there is still room for improvement.

Immediate need: Collins Mission, PFRR Jan 2015, Recoverable  On a nominal flight the previous Iridium system could accomplish this; however if an off-nominal chute event occurred the existing Iridium System would not be able to provide GPS coordinates of the payload. Future need: Australia, Chemical Payloads, or Motor Hardware  Existing Iridium System may not be able to provide GPS coordinates of the hardware due to limitations in the Iridium Trackers GPS.

NSROC Approach for Improvement Improve upon the existing NSROC Iridium system by replacing the Iridium GPS receiver with our own TRG2 GPS receiver, thus removing the previous limitations of not being able to power on until after chute deploy.

94 Recovery Aids Phase 1 – NSROC Iridium Communications Stack (FY14) • Utilize existing off-the-shelf interface hardware to bridge the communications barrier between GPS and Iridium (was internal to Iridium tracker). This hardware is in stock and will require minimal software development • Utilize proven Iridium Antenna’s w/ Acusil thermal coating • Implement on Collins Missions

Existing Communications HWIridium Antenna w/Acusil TR‐G2 GPS Receiver

Contains: • Small form factor • NMACS Power Deck • Better at filtering iridium RF then • CACS Interface Deck current JNS100 GPS receiver • SMAC Board • Connector plate • RS422/232 buffer converter box

95 Recovery Aids Phase 1 – NSROC Iridium Communications Stack (FY14)

96 GNC / Conde Development Brian Tibbetts

21 January 2014

•1st flight of the MaNIACS  August 2013.  Demonstrated spinning and non-spinning maneuvers. • Navigation solution  Developed for LDSD.  Completed 4 flights with good results.  Viable in lieu of GPS or enhanced with GPS. • Completed flight testing on semi-autonomous attitude initialization.  Launcher azimuth is the only external input.  Developed for LDSD.  Improved accuracy.  Plan to be operational on the NIACS family soon (Sub-Tec likely). • Balance of material addresses the Ampule Deployment System.

98 Mission & Key Requirements

• Required for Conde / 52.001. • Measure neutral & ion flow fields. • Desire 50 km separation between main payload and any detonation. • Deploy 24 ampules in 6 groups of 4 ampules. • Deploy at specified attitude within ±25 km. • No single failure shall result in an ampule failing to detonate in flight.

99 Conde Deployment Simulation

100 General System Description

• GLN-MAC in NIACS:  Sets attitude for deployment  Provide trajectory data for time determination • SMAC Ampule Supervisor (SAS):  Determines detonation times  Aggregates data from ampules  Provides data to TM  Some level of communications redundancy to ACM’s • Ejectables:  Ampule with chemicals and initiator(s).  Rocket motor.  Ampule Control Module (ACM): • 2 ea per ejectable • Implements detonation time from SAS • Transmit housekeeping data back to SAS  Battery packs (2 independent sets, one set for each ACM).

101 Mechanical Arrangement

• Rifled barrel, ~10 Hz deploy • New door design to keep ejection path clear.

• Use of async data and shared wiring within the section to reduce wiring harnesses. • Ejectables loaded into barrel; loaded barrel installed. 102 Payload Configuration

103 New / Extended Technology Areas

In addition to the shear number of sub payloads, there are a number of challenging technical areas:

Area Sim H/W S/W Testing Sub‐payload deployment approach X Navigation solution for ACS control X X In‐flight, real‐time ACS targeting X X X In‐flight event timing determination X X Miniaturized Category A pyro circuit X X Communications / Large Scale Bus Handling X X X Extended dispersion estimation X New sequence test methods X X X Large Volume of TM Housekeeping Data –Async X X X

104 Sounding Rocket Working Group Template NSROC Mechanical Engineering Philip Cathell

21 January 2014

• 6 air springs to launch 6 sub-payloads at high velocities.  Sub-payloads are Ø6.50” and 4.1” tall and weigh 7.8 pounds w/ antennae.  Sub Payloads are grasped in place and spin at 2 Hz prior to release.  Air Spring Tubes are sized for 38, 19, and 38 m/s ejection velocities.  Tubes locked w/ rotating ball bearing collar  Motion of tubes arrested with crush bumpers.  Tubes are joined and re-pressurized using ACS components

106 49.002 Swenson Air Springs

107 49.002 Swenson Air Spring

• Videos:  Collar Release Mechanism  Early Deployment Test  Horizontal Redesigned System  Outdoor Subpayload Release

108 Clamshell Deployable Skin

• Alternative Skirt Structure for long experiment structures, booms, deployables, etc. • Design refined in 2012 with SolidWorks Simulation & SolidWorks Motion Analyses. • Design reviewed, 36” prototype fabricated, assembled and tested in 2013.

109 Clamshell Deployable Skin

• Bend Test showed ample margin on design, in family with a normal skin.

Analyzed / Calculated Tip Deflection Actual Tip Deflection 0.147” 0.134” • Deployed at 2 Hz & 4 Hz. • High Speed Video Footage shows clean releases and separation from test structure.

110 Clamshell Deployable Skin

• Videos  Simulation  Realtime  High Speed w/ 2 and 4 Hz

111 Radial Deploying Star Tracker

• Deploying and Retracting Mechanism originally designed as a more optimum Side Looking Star Tracker. • System is powered and controlled via a Shutter Door control/microswitch design. • Soon to begin operational alignment testing.

• Video

112 High Speed Camera- Ground Support Equipment

• Obtained in June 2013 to remove our reliance on range’s high speed camera. • Can track moving objects for velocity & acceleration calculations. • Proving useful on 49.002 Swenson Air Spring Testing

113 Electrical and Telemetry Electrical Engineering

21 January 2014

• Improves per unit cost and manufacturing lead time • Constant dollars buys 2 UB antenna sets versus 1 set of previous vendor product • 2 month lead time • Scheduled to fly on 46.007/Rosanova

115 Strain Gauge Monitoring System (SGMS)

• Improved In-house design and manufacture • Improves accuracy and resolution • Digital design improves noise characteristics • Scheduled to fly on 46.007/Rosanova AD590KF

Strain Range 1.5% = 15000 με Temp. Range Nominal: ‐269° ‐ 290° C (‐452° ‐ 550° F) Short‐term: ‐269 ‐ 400° C (‐452° ‐ 750° F) Strain Range ±5032 με (worst case GF = 2.1) (with board) ±5284 με (nominal GF = 2)

Strain Resolution 5.2 με (with board)

116 Quasonix TIMTER Transmitter

• Constant dollars buy 10 transmitters vs. 7 of previous vendor • Improved capability and design flexibility lessens program logistics • Allows future expansion of telemetry data rate • Scheduled to fly on 46.007/Rosanova

Parameter Value Old Value

RF Power Output Variable up to 20 W (43 dBm) Fixed 2 W, 5W, 10 W

Modulations PCM/FM, Analog FM, PCM/FM, Analog FM SOQPSK‐TG Max Bit Rate Up to 46 Mbps Up to 25 Mbps

Input Type Analog, TTL, RS‐422 Analog

Center Frequency 2200.5 – 2394.5 MHz Two Bands Range 2200 – 2290, 2360 – 2395 MHz Programming RS‐232 Discrete Interface Current (+28 V –10 1.099 A 1.307 A W) 117 Quasonix RDMS Receiver

• Required for Quasonix TIMTER Transmitter Parameter Value Old Value use in SOQPSK mode RF Power Input Up to +20 dBm Up to +10 dBm • Allows future expansion of telemetry data rate Noise Figure 5 dB Max 10 dB typ. • Scheduled to be used for Modulations PCM/FM, Analog FM, PCM/FM, Analog FM 46.007/Rosanova SOQPSK‐TG Max Bit Rate Up to 46 Mbps Up to 20 Mbps

Outputs Video, Data, Clock Video only

Programming Ethernet Front Panel Controls Interface

118 Ulyssix Altair System with DEWEsoft

• Replaces existing (troublesome) TDP/GDP’s • Functions:  RF Receiver  Bit Synchronizer  Decommutator  Real-Time Ethernet Data output (TCP/IP and UDP)  Async UART Outputs  Vintage Parallel Output (moving to obsolete)  Recorder (.tad, .ch10, .d7d)  Data Extractor  Latency Tester  Bit Error Rate Tester

119 Zodiac Data Systems MDR-4 Flight Recorder

• Meets high data rate on-board recording needs(up to 600Mbps through ethernet) • Can record experiment data bypassing the telemetry stream (through ethernet) Parameter Value Units • Records PCM stream up to 30Mbps Number of Channels • Scheduled to fly on 46.007/Rosanova Ethernet Card 2 PCM Card 8 Max Single Ch. Bitrate Ethernet Card 600 Mbps PCM Card 30 Mbps Max Aggregate Bitrate Ethernet Card 640 Mbps PCM Card 100 Mbps File System .ch10 File Download Interface eSATA, USB 2.0, Ethernet System Control Interface USB, Ethernet, RS‐ 232/422, Discretes Voltage Input 11 to 36 V Current 1.5 (at +28 V) A

120 mJAGR (miniature Javad Antivibration GPS Receiver)

• Replaces the legacy JAGR design, which used the obsolete Javad JNS100. • Design uses model TR-G2 HDA (High Dynamics Application) .  Utilizes a new rugged TCXO (much lower g-sensitivity)  NSROC leveraged Orbital- LSG developed oscillator ruggedization • TR-G2 is a single frequency GPS receiver (L1 C/A code only). • Provides IRIG-B Time code signal to any Payload user. • Scheduled to fly on 46.007/Rosanova

NSROC JAGR GPS JAGR mJAGR

1.50” tall Enclosure 4.5 x 3.0 ” 2.0 x 3.0” footprint Enclosure (without mounting w/o LNA flange)

121 High Temp S-Band Antenna

AntDevCo ADC-12017 - 3 Piece High Temp. Antenna • Developed to meet high (700° F) temperature as seen on most Terrier- Improved Malemute flights) • Wideband performance, 2.2 - 2.3 GHz • 17.26” Diameter; up to 10 W power handling capability • Scheduled to fly on 46.007/Rosanova

122