This presentation address the issues and how to involve students in the process of develping, building and certifying flight hardware for ISS and development of Mars missions

Alena, R.

Bowes, A.

Cianciolo, A

Dono Perez, A.

Dutta, S.

Glass, C.

Guarneros Luna, A.

Murbach, M.

Papadopoulos, P.

Powell, R.

Priscal, C.

Stone, T.

Tanner, A.

Wheless, J.

NASA Technical Reports Server

Administratively Controlled Information 
The TechEdSat-N and ETC Series
 
(and Subsequent Experiments)
https://ntrs.nasa.gov/search.jsp?R=20190028939 2019-09-26T19:43:45+00:00Z
Flight Experiments of Recent Years
 (2009-2015)
Intimidator-5
July 29, 2010
PhoneSat 2.4
ORS-3 Minotaur 1
Nov 20, 2013
(still in orbit)
PhoneSat 1a, 1b, 
2.0
Antares A-ONE
Apr 21, 2013SpaceLoft-6Apr 5, 2012
Balloon
June 9, 2011
PhoneSat Team
PhoneSat 2.5
CRS-3 Falcon 9
Apr 18, 2014
EDSN
Super Strypi
Oct 29, 2015
Nodes
Orb-4 Atlas V
Dec 3, 2015
SOAREX-8
Terrier/Black Brant
July 7, 2015
Flight Experiments of Recent Years 
 (2008-2017):  
9 Flights
SOAREX-6
(2008) 
TES-1
Oct 4, 2012
SOAREX-7
(2009)
SOAREX/TechEdSat-N Team
…here before
TES-3
Aug 3, 2013
(6 wk de-orbit)
TES-2
PhoneSat
Iridium-test
Aug 21, 2013
TES-4
Mar 3, 2015
(4 wk de-orbit)
SOAREX-8
(2015)
SOAREX-9
(March 7, 2016)
TES-5
Mar 6, 2017
(currently in orbit)
Relevant Flight Experiments
Atromos: Cubesat Mission to the Surface 
of Mars
•  Mission Attributes
•  Self-stabilizing re-entry probe (TDRV-
Tube Deployed Re-Entry Vehicle)
•  EDL Technique for small probes
•  Nuclear option for mission longevity
ISS Sample Return 
SPQR-Small Payload Quick Return
•  3 stage concept
•  On-demand sample return
JSSOD and ISS
3/13/2008
•  We were 1st!
•  Nominal Success 
Criteria
•  Demonstrated ISS 
Safety Design for jettison 
from ISS
•  Demonstrated 2-tier 
RAD-Tolerant 
Architecture (ÅAC 
Microtec)
•  COM Experiment
(UHF, Iridium, 
OrbComm)
•  Launch Date on HTV3 
August 14, 2012
•  Jettison on October 4, 
2012 
•  ~7 month duration
•  Building, tested and 
certify with in 9 
monthsTechEdSat 1
Before and after Jettison from ISS
TechEdSat 3&4 
•  We were 1st 3U Jettisoned from ISS
•  Nominal Success Criteria
•  First Exo-Brake Demonstration 
•  Advanced Manufacturing 
•  Comm Experiment II
•  Two Tier Architecture
•  Launch August 20, 2013 on HTV4
•  Jettison on November 23rd, 2014
•  Re-entry on January 6, 2014
100 
150 
200 
250 
300 
350 
400 
450 
0 20 40 60 
A
lti
tu
de
 (k
m
) 
Satellite Day 
TES-3/TES-4 Flight Test 
Data 
TES-3p 
TES-4 
•  1st  NASA NanoSatellite 3U 
Jettisoned from the NRCSD 
(July 2014)
•  Exo-Brake Demonstration
•  β=8kg/m^2 
•  Advanced Manufacturing 
•  COM Experiment III + GPS
•  Two-tier Architecture
How To Include University/Intern Involvement
Caveat-
-Once pulled into the NASA ‘firewall’ (due to EAR/ITAR considerations), the hardware/
software becomes ‘NASA’ (controllability, etc.)
- Spectrum authorization (critical!) is such that NASA is the single operator, and 
authorization occurs through the NTIA process.
Method 1.  Interns work at NASA
-Through NASA internship program, direct-hire, or summer sponsorship through NASA 
grants.
The young professionals/ interns become part of the revolving TES-N team
Tiered approach keeps the more experienced helping to train next generation
Works best if projects < 1-2 years (scale of Master degree)
-Challenge – ’paperwork’ must be distributed (nobody likes to work on this to 
exclusion
Method 2.  Universities work with NASA through an SAA (Space Act Agreement)   [Piggy-
backing]
- University contributes an Experiment/Sub-system/Sensor (ESS) through defined 
interfaces
- EDUs are first developed, then the FU (Flight Unit) is delivered and becomes part of 
the TES-N
Guidance is provided on permitted materials, flight wire, solder, conformal 
coating, etc.
- The ESS is controlled by NASA (and the frequency part of NTIA if applicable) but may 
have a separate Success Criteria 
Management/Execution
Nano-Sats 
How it’s MANAGED/controlled/integrated/built/flown   (Briefly)
 
TES-6 
JSC Nano-Sat Drive-up Window!
10
…It looks easy!!! 
 (Ok – what does it really take..)TES-6 launches on Nov11 (OA-8)
TES-N Document Tree
TechEdSat Project ARC 
•  Project Plan
•  7120.5 class-sub D
•  7150.2B class-sub D SW
•  Configuration Control
•  Requirements
•  SEMP
•  Ground Ops/Safety
•  Flight Ops
•  Test Plan (13 subsystem, 9 flight)
•  Procedures, Logs, and Reports (31)
•  TM Summary
•  ODAR
•  NTIA
•  FCC Submittal; Approval
•  SBD Letter of Awareness (Iridium)
•  ICD
•  CDR
•  FRR
ISS Safety (JSC)
•  Standard/Reference Safety Document
•  ICD Verification
•  PSRP Documentation
•  622 Re-flight Documentation (1)
•  906 Certification of Flight (1)
•  SDP (1)
•  HR/UHR (Hazard Reports)
•  Standard Hazards (16)
•  Sharp edges, Shatterable Materials, 
Off-gassing, Flammable Materials, 
Touch Temperature
•  Unique Hazards (2)
•  Battery, Structural Failures, 
Deployment Failure, EMI
Delivery Launch COFR
COC 
(Certificate of 
Compliance)
Total Docs:  
64
Total Docs: 
21
TES-N Documentation Control 
TES-N Documentation Control
MCS/Hardware
Traceability	of	Product
Documentation	of	
Requirements	by	QA	
after	Review	of	
Engineering	Drawings	
or	Requirements
QA	inspections	of	
Product
ITAR	Control	
Librarian
Design
Drawings
Pictures
Presentations
Procedures	and	Logs
Procurements
MINX
Final	Drawings
Approved	Procedures	
and	Logs
Executed	Procedures	
with	Logs
Presentations
SVN
Software
CAD	modeling
TES-6 Procedure Map
TES-6 Review Cycle/Schedule
Dec-May 2017/18 PSRP p3 TES7 (Review of TES6) *Originally TES7 was launching before TES6! 
March  21, 2017 Review of TES-7,8
June 29, 2017 Review of TES-5 Flight and Anomaly
Sept 15, 2017 Review of Flight Readiness/Progress on Anomaly Resolution
Sept 22, 2017 ISS Hazard/Safety Closure
Sept 25, 2017 ACE Pre-Shipment Review
Sept 27, 2017 NanoRacks Hand-over    ** IF other customer didn’t show up.. (99.99% 
certain would)
Oct 7, 2017 NanoRacks hand-over to  JSC
Nov 11, 2017 Flight of OA-8
Week of Nov 14, 2017 Jettison of TES-6
*Note – this IS the proverbial ‘stand-by’ ticket.  The ‘new’ SPIRE nano-sat would have to miss the deadlines. 
Nov 10, 2017Hand-over to NR for SPX-14
Feb X, 2018 Jettison of TES7
*Conferences/Papers:  Calpoly/ IPPW/ Smallsat/ IAC
TES-6 Environmental Testing 
 Vibration at >Protoflight  9.47Grms   PASSED
 Press/De-Press  PASSED TVAC  PASSED
Mass measurement  (PASSED)
Long SW tests 10hr /  (DONE;  command tests in progress)
Exo-Brake inflation tube 
tests (tube leakage)  
Done
Static Loads at >Protoflight 10.35G at 3mins  PASSED
TES6/CUBIT-1 Antenna Attachment 
Issue 
9/27/2017
Conversation with Ala Shuhatovich/
JSC
 
”Not a structural failure” – but an 
anomaly
emergency case”  send PSRP 
Safety Engineer
the result of the suggested solution 
(below)
Notes:
-Survived Proto-flight levels of test 
(9.47G rms)
-More DP100 was added after the crack 
was noted
-Crack may have originated during 
installation of CUBIT-1
Solution:
-Cover further with Kapton tape (except 
for hole for photocell)
-Submit ‘anomaly’ (NOT structural failure) 
to PSRP
-Ala will inspect once more prior to 
installation
-CUBIT-1 shall be removed if there is any 
question (DARPA understands this is a 
’best-effort’ activity
Loctite    [control: Loctite 243; long cure cycle; protoflight 
vibration/accel;  post-inspection]   CLOSED
TES-6 Anomalies 
9 PRACAs
TES-6 Battery Voltage  
 (Final Functional Test/Iridium)
Time in PST, 1:30am to 11am, 11/27/17
TechEdSat 6,7,8, 9TechEdSAt-6 [3U]2nd Modulated Exo-Brake Flight Test
Exo-Brake Tensioner
New OPS/Schedule
CUBIT-1
Possible OA-8 Oct1, 2017
 
TechEdSat-7 [2U]
High Packing Density Exo-Brake
[Novel strut design – no modulation]
Beta= 1kg/m2; 450 km
CUBIT-2
2nd Virgin Orbit Flight Feb, 2018
 
TechEdSat-8 [6U]
Hot Exo-Brake
Modulated with beta=4kgm2
‘Deep Dive’
Novel COM
ISS/NRCSD July, 2018 TBD
TechEdSat-9
3U proposed on 1st VO flight
 
* All CSLI Approved (not TES-9; 
proposed as ballast!)
IRAD Proposal:  ARCxSAT 
Proposed as ARC smallsat multi-platform development tool;  EDL entry system flight tests could include ADEPT, 
HIAD, TDRV – and other concepts… AT EARTH ORBIT ENTRY VELOCITY
C.  Partial EDU plus EDL experiment in ARCxSAT mult-use cavity 
(12x12x26in). 
D.  GEO-POD Mars concept based on ARCxSAT/ISS Dimensions 
(deployed at >GEO with SSL launcher.  Part of 
Propsed easibility study.
B.  ARCXSAT deployed from the ISS with Exo-Brake, EDL
And satlet/swarm experiments deployed.
A.  ARCXSAT  design layout with ISS Cyclops/Kaber Compatibility.  
Critical interface through micro-conical Is shown on right.
Bigger Platform Possibilities
SOAREX-N
Sub-Orbital 
 Experiments 
 
Next-Up!
SOAREX 8 Mission
2:42 launch
10:48 EXO-Brake Deployment
SOAREX 8 results of all experiments  
 
OAREX-8 – Summary 
10 
2.2 SOAREX8 – Results! 
Element Status Comment Applied To 
Future Project 
S-Rocket Deck 
      Battery/PWR (Milwaukee!!) 
                                      [first time!] 
Worked! 
      Yes 
 
Simplifies on-pad Ops/ 
Interface 
Sub-orbitals 
      C-band Worked! Independent Tracking Ubiquitous 
Module 1                     [first time!] 
      T5 core 
       Irid-1 
       WSM Coord1 
Worked! 
     Yes 
     Yes 
     Yes 
Robust TechEdSat5/P5 
[ COM paradigm for nano-
sats] 
Module 2                     [first time!] 
       P5 Core 
       ISM-Band 
       Camera 
      WSM Coord2 
Worked! 
      Yes 
      Yes 
      Yes 
      Yes 
Robust 
Dual Irid and Coord 
TechEdSat5/P5 
 
[1 Mbs solution- Future 
NanoSats!] 
 
Module 3                    [first time!] 
      X-band NanoSat 
      AIM/Thompson CAM 
       
Delayed 
      No 
      No 
Late delivery; EDU Worked on 
bench! 
NEN failed to track!! 
TechEdSat6/P6 
SOAREX-9 
[10-50 Mbs solution] 
Future NanoSats/
Interplanetary COM 
NoseCone System     [first time!] 
      MRMSS 
      WSM3 
Worked! 
      Yes 
      Yes 
New design; future piggy-back 
flights 
(first time) 
SOAREX-9 
Exo-Brake Deployment 
                                      [first time!] 
Worked! 42ft2 pneumatic-aided erection  SPQR 
Planetary Probes 
S8 Box  
Deployment 
Partial! Partial ejection from ejector after 
apogee; stiction! 
SPQR 
Planetary Probes 
SOAREX-9 Flight Payload
SOAREX 9 Mission
Flight Mission
WSM Experiment
Evolution of unique Wireless Sensor Module
Far left:  Original SOAREX-1 data acquisition module
Second from left:  SOAREX-9 WSM 1.0 trial version
Third from left:  currently developed system for SOAREX9 and TES-5
Fourth from left:  Marc’s key chain…
WSM 2.0  
Experimen
t on TES-5 
Summary
TES-N and SOAREX-M flight projects have included interns/universities since the beginning.
At present, there are 3 ’platforms’ used for university collaboration/interaction
Balloon to 30km
Sub-orbital (SOAREX) to 300km
Orbital (TES-N) to 400km
Team management stems from a ’steady core’ with young professional/intern in two tiers.
The two proposed Tiers
NASA core projects/internships
SAA (contributing an Experiment/Sub-system/Sensor set to a concise ICD)
Creating a ’flow’ of flight opportunities (TES-6 delivered; TES-7,8,9 in development)
Hyperspectrals!!
Longer view/incremental approach suggested
TechEdSat has an antecedent in 1995 SMARTSAT Scanning Interferometer study; ARC/Stanford
CHALLENGES are POWER and COM/DATA Transfer!!!
(We have x-band, TDRS transmitters, ETC  !!)
Interplanetary Nanosat


TechEdSat-N and ETC Series

TechEdSat-N and ETC Series

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