ODAR rev2

0297-EX-CN-2016 Text Documents

California Polytechnic State University

2017-05-02ELS_191409

ELVL-2017-0044671
January 14, 2017




                    Orbital Debris Assessment for
                        The CubeSats on the
                      (LV) /ELaNa-19 Mission
                     per NASA-STD 8719.14A




               Ionospheric Scintillation eXplorer (ISX)

               California Polytechnic State University

                        San Luis Obispo, CA


Signature Pag




                3


                    National Aeronautics and
                    Space Administration

                    John F. Kennedy Space Center, Florida
                    Kennedy Space Center, FL 32899

                                                                                                     ELVL-2017-0044671

Reply to Attn of:   VA-H1                                                                                 January 14, 2017

                    TO:              Garrett Skrobot, LSP Mission Manager, NASA/KSC/VA-C

                    FROM:            Justin Treptow, NASA/KSC/VA-H1

                    SUBJECT:         Orbital Debris Assessment Report (ODAR) for the ELaNa-19 Mission
                                     (FCC)

                    REFERENCES:

                          A. NASA Procedural Requirements for Limiting Orbital Debris Generation, NPR
                             8715.6A, 5 February 2008
                          B. Process for Limiting Orbital Debris, NASA-STD-8719.14A, 25 May 2012
                          C. Armstrong, Jason; TriSept Corp. “ODAR info” email, Oct 20, 2016.
                          D. McKissock, Barbara, Patricia Loyselle, and Elisa Vogel. Guidelines on Lithium-
                             ion Battery Use in Space Applications. Tech. no. RP-08-75. NASA Glenn
                             Research Center Cleveland, Ohio
                          E. UL Standard for Safety for Lithium Batteries, UL 1642. UL Standard. 4th ed.
                             Northbrook, IL, Underwriters Laboratories, 2007
                          F. Kwas, Robert. Thermal Analysis of ELaNa-4 CubeSat Batteries, ELVL-2012-
                             0043254; Nov 2012
                          G. Range Safety User Requirements Manual Volume 3- Launch Vehicles,
                             Payloads, and Ground Support Systems Requirements, AFSCM 91-710 V3.
                          H. HQ OSMA Policy Memo/Email to 8719.14: CubeSat Battery Non-Passivation,
                             Suzanne Aleman to Justin Treptow, 10, March 2014


                    The intent of this report is to satisfy the orbital debris requirements listed in ref. (a) for
                    the ELaNa-19 primary mission payload. It serves as the final submittal in support of the
                    spacecraft Safety and Mission Success Review (SMSR). Sections 1 through 8 of ref. (b)
                    are addressed in this document; sections 9 through 14 fall under the requirements levied
                    on the primary mission and are not presented here.




                                                                                                                     3


The following table summarizes the compliance status of the ELaNa-19 auxiliary payload
mission flown on ELaNa XIX. The fourteen CubeSats comprising the ELaNa-19 mission
are fully compliant with all applicable requirements.


            Table 1: Orbital Debris Requirement Compliance Matrix
Requirement                Compliance Assessment    Comments
4.3-1a                     Not applicable           No planned debris release
4.3-1b                     Not applicable           No planned debris release
4.3-2                      Not applicable           No planned debris release
4.4-1                      Compliant                On board energy source
                                                    (batteries) incapable of
                                                    debris-producing failure
4.4-2                      Compliant                On board energy source
                                                    (batteries) incapable of
                                                    debris-producing failure
4.4-3                      Not applicable           No planned breakups
4.4-4                      Not applicable           No planned breakups
4.5-1                      Compliant
4.5-2                      Not applicable
4.6-1(a)                   Compliant                Worst case lifetime 6.6 yrs
4.6-1(b)                   Not applicable
4.6-1(c)                   Not applicable
4.6-2                      Not applicable
4.6-3                      Not applicable
4.6-4                      Not applicable           Passive disposal
4.6-5                      Compliant
4.7-1                      Compliant                Non-credible risk of human
                                                    casualty
4.8-1                      Compliant                ELaNa-19 includes the
                                                    CubeSail mission,
                                                    containing a 250m solar sail
                                                    / tether




                                                                                   4


Section 1: Program Management and Mission Overview

The ELaNa-19 mission is sponsored by the Human Exploration and Operations Mission
Directorate at NASA Headquarters. The Program Executive is Jason Crusan. Responsible
program/project manager and senior scientific and management personnel are as follows:

ANDESITE: Walsh Brian, Principle Investigator

CeREs: Summerlin Errol, Principle Investigator

CHOMPTT: Conklin John, Principle Investigator

CubeSail: Carroll     David, Principle Investigator

DaVinci: Finman Lorna, Principle Investigator

ISX: Bellardo John, Principle Investigator, California Polytechnic State University (Cal Poly)

NMTSat: Jorgensen Anders, Principle Investigator

RSat: Kang Jin, Principle Investigator

Shields-1: Thomsen Laurence, Principle Investigator

STF-1: Grubb Matthew, Principle Investigator

TOMSat EAGLESCOUT: Hattersley Bonnie, Principle Investigator

TOMSat R3: Hattersley Bonnie, Principle Investigator

GEOStare: de Vries Wim, Principle Investigator

SHFT-1: Lux Jim, Principle Investigator




                                                                                       5


                 Program Milestone Schedule
                         Task                                 Date
                    CubeSat Selection                CSLI award February 2016
            CubeSat Mission Readiness review:           February 28th 2017
               CubeSat delivery to TriSept                  May 8th 2017
               CubeSat integration with LV                 May 18th 2017
                      Launch date                          June 23rd 2017

                        Figure 1: Program Milestone Schedule


The ELaNa-19 mission will be launched as the Primary payload on the VCLS
RocketLabs ELaNa XIX mission on an Electron launch vehicle from CCAFS, FL. The
ELaNa-19 compliment, will deploy 14 pico-satellites (or CubeSats). The CubeSat slotted
position is identified in Table 2: ELaNa-19 CubeSats. The ELaNa-19 manifest includes:
ANDESITE, CeREs, CHOMPTT , CubeSail, DaVinci, ISX, NMTSat, RSat, Shields-1,
STF-1, TOMSat EAGLESCOUT, TOMSat R3, GEOStare, and SHFT-1. The current
launch date is in June 23, 2017. The 14 CubeSats are to be ejected from the Electron
shortly after the launch, placing the CubeSats in an orbit approximately 500 X 500 km at
inclination of 85 deg (ref. (h)).

Each CubeSat ranges in sizes from a 10 cm x 10cm x 30 cm to 10 cm x 20 cm x 30 cm,
with masses from about 1.81 kg to ~9.19 kg total. The CubeSats have been designed and
universities and government agencies and each have their own mission goals.




                                                                                      6


Section 2: Spacecraft Description

There are 14 CubeSats flying on the ELaNa-19 Mission. Table 2: ELaNa-19 CubeSats
outlines their generic attributes.

                            Table 2: ELaNa-19 CubeSats

CubeSat                                              CubeSat           CubeSat Masses
                        CubeSat size
Quantity                                              Names                 (kg)
   1           6U (24 cm x 36.3 cm x 11 cm)         ANDESITE                9.19
   1            3U (10 cm x 10 cm x 34 cm)            CeREs                 4.56
   1            3U (10 cm x 10 cm x 34 cm)          CHOMPTT                 1.56
   1            3U (10 cm x 10 cm x 31 cm)           CubeSail               3.74
   1         3U (11.7 cm x 11.3 cm x 34.05 cm)        DaVinci               2.60
   1         3U (11.2 cm x 11.1 cm x 34.05 cm)          ISX                 3.70
   1            3U (10 cm x 10 cm x 34 cm)           NMTSat                 1.58
   1         3U (11.3 cm x 11.3 cm x 34.05 cm)          Rsat                4.15
   1         3U (10.6 cm x 10.6 cm x 34.05 cm)       Shields-1              6.94
   1         3U (11.5 cm x 11.5 cm x 34.05 cm)         STF-1                1.81
                                                     TOMSat
    1        3U (10.3 cm x 10.3 cm x 34.05 cm)                              4.09
                                                   EAGLESCOUT
    1        3U (10.3 cm x 10.3 cm x 34.05 cm)      TOMSat R3               4.09
    1        3U (11.2 cm x 11.1 cm x 34.05 cm)       GEOStare               7.15
    1         3U (11.3 cm x 11.2 cm x 36.6 cm)        SHFT-1                5.10

The following subsections contain descriptions of these 14 CubeSats.




                                                                                   7


ISX (Ionospheric Scintillation eXplorer) – Cal Poly, SLO – 3U
California Polytechnic State University




                             Figure 11: ISX Expanded View
Overview
The Ionospheric Scintillation eXplorer (ISX) is a satellite developed by undergraduate
and graduate students as part of Cal Poly's PolySat research group in collaboration with SRI.
The satellite is sponsored by NSF. ISX will measure the scintillation of disrupts in
ionospheric plasma tubules using DTV signals. ISX will study the multi-frequency radio
wave propagation properties of intermediate-to-large scale ionospheric structures of
Equatorial Spread F that cause rapid phase and amplitude fluctuation of transionospheric
signals.

CONOPS
Upon deployment from the PPOD, ISX will power on. Approximately 15 minutes later,
the antenna will deploy. 115 minutes after antenna deployment, the beacon will be
activated and the satellite will be available to acquire with the ground station. Acquisition
and verification of the correct orientation and rates of the satellite will take place one
week into the mission. The payload will then start taking data for one year.

Materials
The structure is made of 6061-T6 Aluminum. The antenna is made of NiTi. The antenna
route is made of Delrin. It contains standard commercial off the shelf (COTS) materials,
electrical components, PCBs, and solar cells.

Hazards
There are no pressure vessels, hazardous or exotic materials.

                                                                                           18


Batteries
The electrical power storage system consists of nine 3.7V 2600mAh Lithium-Ion
18650 batteries, model LR1865SK, with over-charge/current protection circuitry. There
are three strings in parallel, with each string consisting of three batteries in series. UL
Listing information is as follows BBCV2.MH48285.




                                                                                          19


Section 3: Assessment of Spacecraft Debris Released during Normal
Operations

The assessment of spacecraft debris requires the identification of any object (>1 mm)
expected to be released from the spacecraft any time after launch, including object
dimensions, mass, and material.

The section 3 requires rationale/necessity for release of each object, time of release of
each object, relative to launch time, release velocity of each object with respect to
spacecraft, expected orbital parameters (apogee, perigee, and inclination) of each object
after release, calculated orbital lifetime of each object, including time spent in Low Earth
Orbit (LEO), and an assessment of spacecraft compliance with Requirements 4.3-1 and
4.3-2.

No releases are planned on the ELaNa-19 CubeSat mission therefore this section is not
applicable.




                                                                                          32


Section 4: Assessment of Spacecraft Intentional Breakups and Potential for
Explosions.

There are NO plans for designed spacecraft breakups, explosions, or intentional
collisions on the ELaNa-19 mission.

The probability of battery explosion is very low, and, due to the very small mass of the
satellites and their short orbital lifetimes the effect of an explosion on the far-term LEO
environment is negligible (ref (h)).

The CubeSats batteries still meet Req. 56450 (4.4-2) by virtue of the HQ OSMA policy
regarding CubeSat battery disconnect stating;

       “CubeSats as a satellite class need not disconnect their batteries if flown in LEO
       with orbital lifetimes less than 25 years.” (ref. (h))

ELaNa-19 manifest one, 6U CubeSats which are not included in the 3U or smaller
mentioned in ref. (h). However, this CubeSat has protective circuitry in their designs and
COTS components.

ANDESITE’s EPS and battery system has over-current poly switch protection, over-
current bus protection, and battery under-voltage protection built into the EPS system.
The ANDESITE CubeSat use UL listed battery cells.

Limitations in space and mass prevent the inclusion of the necessary resources to
disconnect the battery or the solar arrays at EOM. However, the low charges and small
battery cells on the CubeSat’s power system prevents a catastrophic failure, so that
passivation at EOM is not necessary to prevent an explosion or deflagration large enough
to release orbital debris.

Assessment of spacecraft compliance with Requirements 4.4-1 through 4.4-4 shows that
with a maximum cubesat lifetime of 6.6 years maximum the ELaNa-19 CubeSat is
compliant.




                                                                                            33


Section 5: Assessment of Spacecraft Potential for On-Orbit Collisions

 Calculation of spacecraft probability of collision with space objects larger than 10 cm in
diameter during the orbital lifetime of the spacecraft takes into account both the mean
cross sectional area and orbital lifetime.

The largest mean cross sectional area (CSA) among the fourteen CubeSats is that of the
CubeSail CubeSat with solar sail / tether deployed (250m X 0.08m solar sail):




                         Figure 21: CubeSail Deployed Config

                               +./0'1& ,/&'
                                                = 3   5 6 +2 5 8
            %&'( *+, =             2                        2
               Equation 1: Mean Cross Sectional Area for Convex Objects
                          %&'( *+, = ,
                                           9': + ,; + ,;
                                                  3
              Equation 2: Mean Cross Sectional Area for Complex Objects
All CubeSats evaluated for this ODAR are stowed in a convex configuration, indicating
there are no elements of the CubeSats obscuring another element of the same CubeSats
from view. Thus, mean CSA for all stowed CubeSats was calculated using Equation 1.
This configuration renders the longest orbital life times for all CubeSats.

Once a CubeSat has been ejected from the P-POD and deployables have been extended
Equation 2 is utilized to determine the mean CSA. Amax is identified as the view that
yields the maximum cross-sectional area. A1 and A2 are the two cross-sectional areas
orthogonal to Amax. Refer to Appendix A for component dimensions used in these
calculations

 The CubeSail (3.74 kg) orbit at deployment is 500km apogee altitude by 500 km perigee
altitude, with an inclination of 85 degrees. With an area to mass ratio of 2.684 m2/kg,
DAS yields 0.1 years for orbit lifetime for its deployed state, which in turn is used to
obtain the collision probability. Even with the variation in CubeSat design and orbital

                                                                                          34


lifetime ELaNa-19 CubeSats see an average of 0.00000 probability of collision. All
CubeSats on ELaNa-19 were calculated to have a probability of collision of 0.00000.
Table 4 below provides complete results.

There will be no post-mission disposal operation. As such the identification of all systems
and components required to accomplish post-mission disposal operation, including
passivation and maneuvering, is not applicable.




                                                                                        35


                                    Table 4: CubeSat Orbital Lifetime & Collision Probability

                                                         Stowed                                            Deployed
                                     Mean C/S    Area-to    Orbital    Probability of                 Area-to   Orbital    Probability of
                                                                                        Mean C/S
  CubeSat              Mass (kg)       Area
                                      (m^2)
                                                  Mass
                                                (m^2/kg)
                                                            Lifetime
                                                              (yrs)
                                                                         collision
                                                                          (10^X)
                                                                                        Area (m^2)
                                                                                                       Mass
                                                                                                     (m^2/kg)
                                                                                                                Lifetime
                                                                                                                  (yrs)
                                                                                                                             collision
                                                                                                                              (10^X)
     ANDESITE            9.19        0.0763     0.0083        5.8       0.00000         0.1083       0.012        5.2       0.00000
       CeREs             4.56        0.0390     0.0086        5.7       0.00000         0.0735       0.016        4.8       0.00000
     CHOMPTT             1.56        0.0390     0.0250        4.4       0.00000         0.0415       0.027        4.3       0.00000
      CubeSail           3.74        0.0362     0.0097        5.5       0.00000         10.0364      2.684        0.1       0.00000
      DaVinci            2.60        0.0459     0.0177        4.7       0.00000         0.1006       0.039         4        0.00000
        ISX              3.70        0.0442     0.0120        5.2       0.00000         0.0445       0.012        5.2       0.00000
      NMTSat             1.58        0.0417     0.0264        4.3       0.00000         0.0493       0.031        4.2       0.00000
        Rsat             4.15        0.0449     0.0108        5.3       0.00000         0.0629       0.015        4.9       0.00000
     Shields-1           6.94        0.0417     0.0060        6.6       0.00000         0.0494       0.007        6.2       0.00000
       STF-1             1.81        0.0467     0.0259        4.3       0.00000         0.0490       0.027        4.3       0.00000
     TOMSat
                         4.09        0.0406     0.0099        5.5       0.00000          0.0635      0.016        4.8       0.00000
   EAGLESCOUT
     TOMSat R3             4.09      0.0406     0.0099        5.5       0.00000          0.0635      0.016        4.8       0.00000
      GEOStare             7.15      0.0443     0.0062        6.4       0.00000          0.0880      0.012        5.2       0.00000
        SHFT-1             5.10      0.0476     0.0093        5.6       0.00000          0.1855      0.036        4.1       0.00000
Solar Flux Table Dated 11/07/2016


The probability of any ELaNa-19 spacecraft collision with debris and meteoroids greater
than 10 cm in diameter and capable of preventing post-mission disposal is less than
0.00000, for any configuration. This satisfies the 0.001 maximum probability requirement
4.5-1.

Since the CubeSats have no capability or plan for end-of-mission disposal, requirement
4.5-2 is not applicable.

Assessment of spacecraft compliance with Requirements 4.5-1 shows ELaNa-19 to be
compliant. Requirement 4.5-2 is not applicable to this mission.

Section 6: Assessment of Spacecraft Postmission Disposal Plans and Procedures

All ELaNa-19 spacecraft will naturally decay from orbit within 25 years after end of the
mission, satisfying requirement 4.6-1a detailing the spacecraft disposal option.

Planning for spacecraft maneuvers to accomplish postmission disposal is not applicable.
Disposal is achieved via passive atmospheric reentry.

Calculating the area-to-mass ratio for the worst-case (smallest Area-to-Mass) post-
mission disposal among the CubeSats finds Shields-1 in its stowed configuration as the
worst case. The area-to-mass is calculated for is as follows:

                  !"#$ & ' ()"# (+,) = ()"#
                                                                        ,
                                                       34     !#.. ( + )


                        !#.. (/0)                                    /0
                               Equation 3: Area to Mass

                                                          ;
                                 0.0417:; = 0.0060 :

                                  6.94>?                 >?
Shields-1 has the smallest Area-to-Mass ratio and as a result will have the longest orbital
lifetime. The assessment of the spacecraft illustrates they are compliant with
Requirements 4.6-1 through 4.6-5.

DAS 2.0.2 Orbital Lifetime Calculations:

DAS inputs are: 500 km maximum apogee 500 km maximum perigee altitudes with an
inclination of 85 degrees at deployment no earlier than June 23rd 2017. An area to mass
ratio of 0.0060 m2/kg for the Shields-1 CubeSat was imputed. DAS 2.0.2 yields a 6.6
years orbit lifetime for Shields-1 in its stowed state.

This meets requirement 4.6-1. For the complete list of CubeSat orbital lifetimes reference
Table 4: CubeSat Orbital Lifetime & Collision Probability.

Assessment results show compliance.


Section 7: Assessment of Spacecraft Reentry Hazards

A detailed assessment of the components to be flown on ELaNa-19 was performed. The
assessment used DAS 2.0, a conservative tool used by the NASA Orbital Debris Office to
verify Requirement 4.7-1. The analysis is intended to provide a bounding analysis for
characterizing the survivability of a CubeSat’s component during re-entry. For example,
when DAS shows a component surviving reentry it is not taking into account the material
ablating away or charring due to oxidative heating. Both physical effects are experienced
upon reentry and will decrease the mass and size of the real-life components as the reenter
the atmosphere, reducing the risk they pose still further.

The following steps are used to identify and evaluate a components potential reentry risk
relative to the 4.7-1 requirement of having less than 15 J of kinetic energy and a 1:10,000
probability of a human casualty in the event the survive reentry.
             1. Low melting temperature (less than 1000 °C) components are identified as
                 materials that would
                 casualty. This        never survive
                                is confirmed throughreentry and pose
                                                     DAS analysis     noshowed
                                                                   that  risk to human
                                                                                  materials
                 with melting temperatures equal to or below that of copper (1080 °C) will
                 always demise upon reentry for any size component up to the dimensions
                 of a 1U CubeSat.

           2. The remaining high temperature materials are shown to pose negligible
              risk to human casualty through a bounding DAS analysis of the highest
              temperature
              similar        components,
              1500°C,dimensions
                        it can      and hasstainless
                               be expected           steel
                                            toa posses
                                                melting     (1500°C).
                                                         temperature
                                                       the same        If a component
                                                                      between
                                                                 negligible  risk1000  °Cisand
                                                                                            of
                                                                                  as stainless
              steel components. See Table 5 through Table 7.

       Table 5: ELaNa-19 High Melting Temperature Material Analysis (1/3)
             CubeSat     High Temp Component               Material            Demise Alt (km)   KE (J)

             ANDESITE   Node Deployment Springs         Steel AISI 304              76.4           0

             ANDESITE          Antennae                 Steel AISI 410                0            0
             ANDESITE         6-32 Screws          Stainless Steel (generic)        77.5           0

             ANDESITE         2-56 Screws          Stainless Steel (generic)        77.4           0

             ANDESITE            Hinges            Stainless Steel (generic)          0            1

              CeREs          Tungsten Tube                Tungsten                    0          150
              CeREs             Detector                    Silicon                   0            0

              CeREs         Closeout Plate 1              Tungsten                    0            8

            CHOMPTT      StenSat UHF Antennae      Stainless Steel (generic)          0            0

            CHOMPTT      Lithium UHF Antennae      Stainless Steel (generic)          0            0
            CHOMPTT     Backplane Holder - 11 mm        Steel AISI 304                0            0

            CHOMPTT     Backplane Holder - 13 mm        Steel AISI 304                0            0

            CHOMPTT     Reaction Wheel Assembly    Stainless Steel (generic)        68.6           0




                                                                                                          38


Table 6: ELaNa-19 High Melting Temperature Material Analysis (2/3)
  CubeSat          High Temp Component                     Material            Demise Alt (km)   KE (J)

  CHOMPTT                 Batteries                Stainless Steel (generic)         69            0

  CHOMPTT       Battery Holder Plates 2a&2b             Steel AISI 304                0           25

  CHOMPTT               Lithium Radio              Stainless Steel (generic)          0            6

  CHOMPTT            Retoreflector Array           Stainless Steel (generic)          0            4

  CubeSail            New Component                Stainless Steel (generic)          0            1

  CubeSail               Fasteners*                Stainless Steel (generic)        77.9           0
  CubeSail              SRU Nut Plate              Stainless Steel (generic)        74.4           0

  CubeSail                 Motor                        Steel AISI 304               70            0

  CubeSail                Drive Pin                     Steel AISI 304              77.1           0

  CubeSail     Reaction Wheel Daughter Board       Stainless Steel (generic)          0           14
    ISX              Historesis Material           Stainless Steel (generic)         77            0

    ISX            Screw - Representative          Stainless Steel (generic)        76.9           0

    ISX                Structural Rods             Stainless Steel (generic)        77.4           0

    ISX                  ISIS screws               Stainless Steel (generic)        77.1           0

    ISX                  ISIS washers              Stainless Steel (generic)          0            0

    ISX          GAMMA Antenna washers             Stainless Steel (generic)          0            0

    ISX           GAMMA Antenna screws             Stainless Steel (generic)        76.2           0

    ISX            GAMMA Antenna nuts              Stainless Steel (generic)          0            0

    ISX               solar panel screw            Stainless Steel (generic)        76.6           0

    ISX                solar panel nut             Stainless Steel (generic)          0            0

    ISX                Solar panel clip            Stainless Steel (generic)          0            0

    ISX                15mm spacers                Stainless Steel (generic)         75            0

    ISX                25mm spacers                Stainless Steel (generic)        73.5           0

    Rsat                   Motors                  Stainless Steel (generic)        73.3           0

    Rsat                    ADCS                   Stainless Steel (generic)          0            3

    Rsat                  Fasteners                Stainless Steel (generic)        77.6           0
  Shields-1                Shield0                   Titanium (6 Al-4 V)              0           16
  Shields-1                Shield1                        Tantalum                    0           69
  Shields-1                Shield2                   Titanium (6 Al-4 V)              0           14
  Shields-1                Shield3                        Tantalum                    0           27
  Shields-1                Shield4                   Titanium (6 Al-4 V)              0            0
  Shields-1                Shield5                        Tantalum                    0            0
  Shields-1                Shield6                   Titanium (6 Al-4 V)              0            0
  Shields-1                Shield7                   Titanium (6 Al-4 V)              0            0
  Shields-1                Shield8                   Titanium (6 Al-4 V)              0            0

  Shields-1   Charge Dissipation Film electrodes        Steel AISI 304              73.8           0

  Shields-1     Charge Dissipation Film spring     Stainless Steel (generic)        76.1           0

  Shields-1            RTDs (Est Dims)             Stainless Steel (generic)        77.5           0
  Shields-1              Fasterners2               Stainless Steel (generic)        77.7           0
  Shields-1              Fasteners3                Stainless Steel (generic)        77.7           0




                                                                                                          39


      Table 7: ELaNa-19 Summary of Surviving High Temperature Material
                             Components (3/3)
         CubeSat           High Temp Component                   Material            Demise Alt (km)   KE (J)

         Shields-1              Fasteners4               Stainless Steel (generic)          0            0

         Shields-1           Solar Panel Screws               Steel AISI 410              77.6           0

         Shields-1          Solar Panel Washers               Steel AISI 410                0            0

         Shields-1        Remove Before Flight Pin       Stainless Steel (generic)        73.7           0

         Shields-1              Sep Switch               Stainless Steel (generic)        73.7           0

         Shields-1   ADCS Components (Hysteresis Rods)   Stainless Steel (generic)        77.5           0

          STF-1                 Ferrite Bead             Stainless Steel (generic)        77.3           0

          STF-1                 Geiger Tube              Stainless Steel (generic)         67            0

          STF-1                 Fasteners5               Stainless Steel (generic)        77.9           0

         TOMSat               Reaction Wheels            Stainless Steel (generic)        63.9           0

         TOMSat              Single Torque Rod           Stainless Steel (generic)        74.8           0

         TOMSat                    18267                   Titanium (generic)               0            2
         TOMSat                    18265                   Titanium (generic)               0            1

         TOMSat                    18264                   Titanium (generic)               0            1

         TOMSat                    18268                   Titanium (generic)               0            0

         TOMSat                    18266                   Titanium (generic)               0            2
         TOMSat                    18263                   Titanium (generic)               0            0

         TOMSat                    18270                   Titanium (generic)               0            0

         TOMSat                    Laser                   Aluminum 6061-T6               72.8           0

         GEOstare            Batteries-GEOStae           Stainless Steel (generic)          0            1
         GEOstare             Telescope baffle             Titanium (generic)               0           22

         GEOstare                Telescope               Stainless Steel (generic)        65.4           0

         GEOstare               Fasteners7                     Steel A-286                 78            0

          SHFT-1             Internal Fasteners          Stainless Steel (generic)         77            0

          SHFT-1             External Fasteners          Stainless Steel (generic)         77            0


The majority of high temperature components demise upon reentry. And all CubeSats
comply with the 1:10,000 probability of Human Casualty Requirement 4.7-1. A
breakdown of the determined probabilities follows on Table 8.




                                                                                                                40


                Table 8: Requirement 4.7-1 Compliance by CubeSat

                                CubeSat         Risk      Risk < 1:10,000

                               ANDESITE         1:0          Compliant

                                 CeREs       1:210,600       Compliant

                               CHOMPTT       1:93,400        Compliant

                                CubeSail        1:0          Compliant

                                DaVinci         1:0          Compliant

                                  ISX           1:0          Compliant

                                NMTsat          1:0          Compliant

                                  Rsat          1:0          Compliant

                               Shields-1     1:32,400        Compliant

                                 STF-1          1:0          Compliant

                                TOMSat          1:0          Compliant

                               GEOstare      1:200,000       Compliant

                                SHFT-1          1:0          Compliant
                       *Requirement 4.7-1 Probability of Human Casualty > 1:10,000


If a component survives to the ground but has less than 15 Joules of kinetic energy it is
not included in the Debris Casualty Area that inputs into the Probability of Human
Casualty calculation. Which is why CubeSats that have surviving components like
ANDESITE, CubeSail, DaVinci, ISX, NMTsat Rsat, STF-1 TOMSat EAGLESCOUT,
TOMSat R3, and SHFT-1 have a 1:0 probability as none of their components have more
than 15J of energy. The breakdown of CubeSat’s with greater than 15J of energy
components is as follows: CeREs has 1, CHOMPTT has1, Shields-1 has 3, and GEOStare
has 1.

All CubeSats launching under the ELaNa-19 mission are shown to be in compliance with
Requirement 4.7-1 of NASA-STD-8719.14A.

See the Appendix for a complete accounting of the survivability of all CubeSat
components.




                                                                                      41


Section 8: Assessment for Tether Missions

In the ELaNa-19 mission, CubeSail’s deployable sail made of a mylar film qualifies as a
momentum tether although a ribbon would be a more accurate description of its
dimensions (0.0004 cm x 7.9cm x 25,317 cm).

The tether mission plan can be referenced in the CubeSail specific mission plan located in
Section 2.

Following the Methods to Assess Compliance for Tethered Systems (section 4.8.4), the
DAS analysis determined the CubeSail design to be COMPLIANT with both
Requirement 4.5-1 and 4.5-2 dealing with meeting the requirements limiting the
generation or orbital debris from on-orbit collisions. The probability of collision on orbit
for the un-deployed system, fully deployed system, and ½ the system in the event of a
tether severing event was calculated to be << 0.001.

CubeSail is also compliant with Requirements 4.6-1 to 4.6-4 (Postmission Disposal),
given the low 500km x 500km, this orbit will have CubeSail passively deorbit in 5.5
years if the system does not deploy, <<0.1 years if the system does deploy, and <<0.1
year if the tether breaks into two equal parts as calculated via DAS 2.0.2. All three
scenarios are compliant with the Requirement 4.6-1 to 4.6-4.




                       Figure 22: Tether Assessment of CubeSail


ELaNa-19 CubeSat, CubeSail satisfies Section 8’s requirement 4.8-1.




                                                                                           42


Section 9-14

ODAR sections 9 through 14 for the launch vehicle are not covered here.

If you have any questions, please contact the undersigned at 321-867-2958.

/original signed by/

Justin Treptow
Flight Design Analyst
NASA/KSC/VA-H1

cc:   VA-H/Mr. Carney
       VA-H1/Mr. Beaver
       VA-H1/Mr. Haddox
       VA-G2/Mr. Atkinson
       VA-G2/Mr. Marin
       SA-D2/Mr. Frattin
       SA-D2/Mr. Hale
       SA-D2/Mr. Henry
       Analex-3/Mr. Davis
       Analex-22/Ms. Ramos




                                                                             43


                        Appendix Index:

Appendix A.   ELaNa-19 Component List by CubeSat: ANDESITE
Appendix B.   ELaNa-19 Component List by CubeSat: CeREs
Appendix C.   ELaNa-19 Component List by CubeSat: CHOMPTT
Appendix D.   ELaNa-19 Component List by CubeSat: CubeSail
Appendix E.   ELaNa-19 Component List by CubeSat: DaVinci
Appendix F.   ELaNa-19 Component List by CubeSat: ISX
Appendix G.   ELaNa-19 Component List by CubeSat: NMTSat
Appendix H.   ELaNa-19 Component List by CubeSat: RSat
Appendix I.   ELaNa-19 Component List by CubeSat: Shields-1
Appendix J.   ELaNa-19 Component List by CubeSat: STF-1
Appendix K.   ELaNa-19 Component List by CubeSat: TOMSat EAGLESCOUT
Appendix L.   ELaNa-19 Component List by CubeSat: TOMSat R3:
Appendix M.   ELaNa-19 Component List by CubeSat: GEOStare:
Appendix N.   ELaNa-19 Component List by CubeSat: SHFT-1




                                                                  44


      Appendix F.         ELaNa-19 Component List by CubeSat: ISX (1/2)
                                                                                                                          Diameter/
            Row                                                                                              Individual               Length   Height   High   Melting
CUBESAT                           Name                    Qty             Material               Body Type                 Width                                         Survivability
           Number                                                                                             Mass (g)                 (mm)    (mm)     Temp   Temp
                                                                                                                            (mm)

ISX          1               ISX 3U CubeSat                1               Various                  Box        3699.3       100        100     340.5     No       -        Demise

ISX          2              CubeSat Structure              1           Aluminum 6061                Box         456         100        100     340.5     No       -        Demise

ISX          3                   +Z Panel                  1                 PCB                    Box          30         100        100      2.5      No       -        Demise

ISX          4                   -Z Panel                  1                 PCB                    Box          30         100        100      2.5      No       -        Demise

ISX          5            Radio Daughter Board             1                 PCB                    Box          15          36         83      2.5      No       -        Demise

ISX          6             GPS Daughter Board              1                 PCB                    Box          15          39         83      2.5      No       -        Demise

ISX          7                  GPS Patch                  1               Ceramic                  Box         11.4        25.1       25.1     5.2      No       -        Demise

ISX          8                C-Band Patch                 1               Ceramic                  Box         2.1          12         12      4.3      No       -        Demise

ISX          9               Antenna Routes                3                Delrin                  Box          5           65         65      3.4      No       -        Demise

ISX          10                  Antenna                   6             Nitonol Wire               Box          2          0.31       165      0.51     No       -        Demise

ISX          11               System Board                 1                 PCB                    Box          60         100         83       3       No       -        Demise

ISX          12     Payload Interface and Battery Board    1                 PCB                    Box          50          83         83       3       No       -        Demise

ISX          13                 Side Panel                 4                 PCB                    Box         120          83        320      2.5      No       -        Demise

ISX          14                 Solar Cell                20                Eglass                  Box         2.3          70         40      0.5      No       -        Demise

ISX          15          Solar Angle Sensor Board          5                 PCB                    Box          5           20         30      2.5      No       -        Demise

ISX          16        Solar Angle Sensor Apperture        5              Aluminum                  Box          3           19         21       5       No       -        Demise

ISX          17               Battery Bracket              1           Aluminum 6061                Box         168          76         82       67      No       -        Demise

ISX          18                 Heat Shrink                2    RNF-100 Polyolefin Heat Shrink     Tube          2          63.5       25.4     0.5      No       -        Demise

ISX          19                  Batteries                 9              Lithion Ion             Cylinder       45         18.4       65.1     N/A      No       -        Demise

ISX          20                Dummy Cell                  1                Delrin                Cylinder       10          19         66      N/A      No       -        Demise




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Document Modified: 2017-04-19 13:53:33

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