Attachment SES-STA-20190604-007

SES-STA-20190604-007

DECISION submitted by FCC

Grant

0000-00-00

This document pretains to SES-STA-20190604-00724 for Special Temporal Authority on a Satellite Earth Station filing.

IBFS_SESSTA2019060400724_1845907

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    2. Contact

                 Name:         Joseph A. Godles                       Phone Number:                       202—429—4900
                 Company:      Goldberg, Godles, Wiener &             Fax Number:
                               Wright LLP
                 Street:       1025 Connecticut Aye, NW               E—Mail:                             jgodlesg2w2.com
                               Ste 1000
                 City:         Washington                             State:                               DC
                 Country:      USA                                    Zipcode:                            20036      —




                 Attention:                                           Relationship:                        Legal Counsel


    (If your application is related to an application filed with the Commission, enter either the file number or the 13 Submission ID of the related
    application. Please enter only one.)
     3. Reference file Number or Submission ID
        4a. Is a fee submitted with this application?
         If Yes, complete and attach FCC Form 159.        If No, indicate reason for fee exemption (see 47 C.F.R.Section 1.1114).
    •
         Governmental Entity            Noncommercial educational licensee

    o Other(please explain):
    4b. Fee Classification    CGX   —   Fixed Satellite Transmit/Receive Earth Station
    5. Type Request

                                                             Change Station Location                         Other
    o Use Prior to Grant
    6. Requested Use Prior Date




2


    7. City                                                                     8. Latitude
                                                                                (dd mm ss.s h)    0   0   0.0   N
    9. State                                                                    10. Longitude
                                                                                (dd mm ss.s h)    0   0   0.0   W
    1 1. Please supply any need attachments.
    Attachment 1: Attachment 1                        Attachment 2: Attachment 2                          Attachment 3: Attachment 3 ODAR


    12. Description.   (If the complete description does not appear in this box, please go to the end of the form to view it in its entirety.)
         Telesat Canada seeks STA for up to 30 days for earth stations to test, validate,                                               and
         demonstrate communications with Telesat’s LEO 1 satellite.  See Attachment 1




    13. By checking Yes, the undersigned certifies that neither applicant nor any other party to the application is               Yes            No
    subject to a denial of Federal benefits that includes FCC benefits pursuant to Section 530] of the Anti—Drug Act
    of 1988,21 U.S.C. Section 862, because of a conviction for possession or distribution of a controlled substance.
    See 47 CFR 1.2002(b) for the meaning of &quot;party to the application&quot; for these purposes.


    14. Name of Person Signing                                                  15. Title of Person Signing
       El isabeth Neasmith                                                         Director, Spectrum Management & Development
               WILLFUL FALSE STATEMENTS MADE ON THIS FORM ARE PUNISHABLE BY FINE AND / OR IMPRISONMENT
                      (U.S. Code, Title 1$, Section 1001), AND/OR REVOCATION Of ANY STATION AUTHORIZATION
                       (U.S. Code, Title 47, Section 312(a)(1)), AND/OR FORFEITURE (U.S. Code, Title 47, Section 503).




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                                                          —   File

                                                              Call Sian             Grant Dates   ——\C \
                                                              (or other identifier)       —




                                                                    CN       ‘Ie Dates
 Applicant:  Telesat Canada           GRANTED From:’ ‘7                              To:%c-i
 File No.:   SES-STA201 90604-00724 International Bureau
 Call Sign:  N/A
 Special Temporary Authority
                                                         Approved: (Lc
                                                                             -
Telesat Canada (“Telesat”) is granted requesting a special temporary authority, for 30 days,
beginning August 7, 2019 to operate two Intellian Modle Vi 5OKa, 1.50 meter earth stations, one
                                                   ,

located in Pompano Beach, FL and the other located in Melbourne, FL to conduct loop-back tests
with Telesat’s non-geostationary orbit (“NGSO”) satellite, LEO 1 in the 1000 km x 1000 km, 99.5°
inclined NGSO orbit in the 28.6-29.1 GHz (Earth-to-space) and 18.8-19.3 GHz (space-to-Earth)
frequency bands under the following conditions:

1.   Operations will not exceed the operational power levels and parameters.

2.    All operations under this grant of special temporary authority shall be on an unprotected
 and non-harmful interference basis. Telesat shall not cause harmful interference to and shall not
 claim protection from interference caused to it by, any other lawfully operating radio
 communication system.

3.    In the event of any harmful interference under this grant of special temporary authority,
Telesat must cease operations immediately upon notification of such interference, and must
inform the Commission, in writing, immediately of such an event.

4    LEO 1 satellite operations in the 18.8-19.3 GHz (space-to-Earth) frequency band shall
comply to the following conditions:

       a).    LEO 1 satellite shall only turn on and downlink in the 18.8-19.3 GHz frequency
band while in view of the ground stations at Pompano Beach, FL and Melbourne, FL and;

        b).   LEO 1 satellite transmit antenna gain in the 18.8-i 9.3 GHz frequency band is 25.5
dBi and the total maximum EIRP for the downlink in the 18.8-1 9.3 GHz frequency band is 36
dBW.

5.      Telsat Canada is required to provide the Air Force (Email: Jmmy.Nguyen@us.af.mil) with
the stop buzzer P00 for operations in the 18.8-1 9.3 GHz (space-to-Earth) frequency band.

6.    All operators of satellites will be provided with an emergency phone number where the
licensee can be reached in the event that harmful interference occurs, Currently the 24x7 contact
information for Telesat’s LEO 1 mission is Ph.: (321 -733-9015) in Melbourne, FL. -Request to
speak to William Mudge and Ph.: (213-465-5829) in Pompano Beach, FL. -Request to speak to
Jio Castro.

7.    Any action taken or expense incurred as a result of operations pursuant to this
special temporary authority is solely at Telesat’s risk.

8.  Grant of this authorization is without prejudice to any determination that the Commission
may make regarding pending or future Telesat applications


This action is issued pursuant to Section 0.261 of the Commission’s rules on delegated authority,
47 C.F.R. §0.261, and is effective immediately.


Telesat Canada                                                                                      Attachment 1


                       REQUEST FOR SPECIAL TEMPORARY AUTHORITY


          Telesat Canada (“Telesat”), pursuant to Section 25.120 of the Commission’s rules,
hereby requests Special Temporary Authority (“STA”) to operate two earth stations one located        -




in Pompano Beach, Florida and the other located in Melbourne, Florida to conduct loop-back
                                                                                      -




tests with Telesat’s non-geostationary orbit (“NGSO”) low earth orbit satellite, LEO 1. Telesat
seeks an STA for the 30-day period beginning on August 6, 2019. The technical specifications
for these operations are set forth in Attachment 2a and 2b hereto, which provides the information
that would be appear in Schedule B of FCC form 312, if regular authority were being sought.
          LEO 1 was launched in January 2018 and is currently in its final mission orbit of 99.5°
(circular) at an altitude of 1000 km. Telesat will operate LEO 1 pursuant to the requested STA
in accordance with the technical parameters that were specified in Telesat’s Petition for
Declaratory Ruling to Grant Access to the U.S. Market for Telesat’s NGSO Constellation
(“PDW”), including Schedule S thereto, which was granted by the Commission by Order and
Declaratory Ruling, released November 3, 2017.1 STA operations will be limited to two of the
bands covered by the PDR, i.e., 28.6-29.1 GHz (Earth-to-space) and 18.8-19.3 GHz (space-to-
Earth), which the Commission’s Ka-band plan allocates on a primary basis to NGSO operations.
         In accordance with Section 25.120, the earth stations will operate on a non-interference
basis. The communications to be made under the STA will be used to test, validate, and
demonstrate certain design features of LEO-i, including antenna tracking, RF performance, and
end-to-end network performance. These operations will set the stage for providing highly
innovative broadband services in the United States. Grant of Telesat’ s STA request, therefore, is
in the public interest.
         Telesat is submitting, as Attachment 3 to this STA request, a detailed orbital debris
assessment report prepared by NXTRAC for LEO 1, confirming compliance with U.S.
government orbit lifetime and orbital debris mitigation regulations.2 A radiation hazard study for
each earth station is provided in Attachment 2a and 2b hereto.


  FCC 17-147. Telesat’s PDR and the associated grant are hereby incorporated by reference.
2
  In addition, Telesat’s orbital debris plan for LEO I has been reviewed by the Canadian licensing authority for the
satellite, Innovation, Science and Economic Development Canada, for compliance with the guidelines issued by the
Inter-Agency Space Debris Coordination Committee and Telesat is required, by condition of license, to comply with
these guidelines.




285099.00005/104109405.1


Telesat Canada                                                                                         Attachment 1


         As indicated above, operations will be limited to the portions of the Ka-band in which
NGSO operations have primary status. Accordingly, EPFD limits are inapplicable. Telesat will
coordinate its STA operations with the U.S. federal government under footnote US3 343 of the
United States Table of Frequency Allocations.4 Telesat will share ephemeris data in accordance
with Section 25.146(e) of the Commission’s rules. With regard to matters of physical
coordination, there are no operators using similar orbits.
         Accordingly, for good cause as shown herein, Telesat requests that the Commission grant
Telesat’s STA request.




  Telesat has been having discussions with the Commission as to the applicability of US334 and is coordinating with
the federal government out of an abundance of caution.
“Telesat notes that it answered question El 8 in the Schedule B that is provided in Attachment 2a and 2b as “No”
(i.e., that frequency coordination is not required) based on its understanding that the question relates to non-federal
government coordination requirements, if any.


285099.00005/104109405.1


Telesat Canada
Attachment 3




            PREPARED FOR TELESAT IN SUPPORT OF THE
            LEO I SATELLITE

            ANALYSIS BY NXTRAC

            11 APRIL2019


                      DOCUMENT DATA IS NOT RESTRICTED

                 THIS DOCUMENT CONTAINS NO PROPRIETARY, ITAR
                      OR EXPORT CONTROLLED INFORMATION


                                                                                 NTRAC


Revision History
 Revision     Description of Revisions                                          Release Date
              Initial Release Initial ODAR Report Format per NASA NASA-STD
                            ---



                                                                                 10/02/201 8
              8719.14 Revision A with Change I dated 8 Nov2011
   1.1        Updates to incorporate analysis results                            3/08/2019




NXTRAC Mission Analysts
         Dr. Darren D. Garber
         Jacqueline J. Eanes




ODAR Analysis Tools
         NASA Debris Assessment Software (DAS) v2.1.1
         NASA General Mission Analysis Tool (GMAT) R2018a




NXTRAC                   800 S. PCH Suite 8-247 Redondo Beach CA 90277       310-713-7301

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                                                                                              MXTRA C


Introduction
This document provides a detailed orbital debris assessment
report (ODAR) for the operations and disposal of the Telesat
LEO 1 satellite. This ODAR provides an overview of current and
planned LEO I operations and demonstrates compliance with
all US Government orbit lifetime and orbital debris mitigation
regulations.


Telesat’s LEO I satellite was launched on 12 Jan 2018, as
NORAD catalog identifier 43113, and is depicted in Figure 1.
As of this report, the LEO I satellite has maneuvered to its final
mission orbit; a 1000 km altitude circular orbit inclined at 99.5
                                                                        Figure 1: Telesat LEO 1
degrees. Telesat’s LEO 1 satellite has a planned 3-year mission
lifetime at which point the health of the satellite may be
assessed for mission extension activities. If a viable mission extension is not possible, a sequence
of planned disposal maneuvers will be performed over 3 to 6 months to allow atmospheric drag
to ultimately remove the vehicle from orbit.
For this analysis, a 165.5 kg small satellite with an initial area to mass ratio of 0.00513 m2/kg, was
placed in a 1000 km altitude 99.5 degree inclined orbit for three years. Over the three year
operational period the orbit evolves to 975 x 1025 km and will then be maneuvered to a final
elliptical disposal orbit of 425 x 975 km. Its final mass at end of life is expected to be 127.9 kg with
a corresponding increased area to mass ratio of 0.006646 m2/kg. From this final orbit and
configuration, the decay and collision potential for LEO I were assessed with the precision NASA
GMAT trajectory engine and the standard NASA DAS 2.1.1 toolset.
Analysis of the LEO 1 mission operations and deorbit plan meets or exceeds all disposal and
flight safety requirements with a decay timeline less than the 25 year maximum and a minimal
collision probability (9e-5).




NXTRAC                    800 S. PCH Suite 8-247 Redondo Beach CA 90277                 310-713-7301

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                                                                                          NATRA C




Summarized List of Compliance Status to Orbital Debris
Requirements



 4.3-1, Mission-Related Debris Passing Through LEO:                                 COMPLIANT


 4.3-2, Mission-Related Debris Passing Near GEO                                     COMPLIANT

 4.4-3, Limiting the long-term risk to other space systems from planned breakups:   COMPLIANT

 4.5-1 Probability of Collision with Large Objects:                                 COMPLIANT

 4.5-2, Probability of Damage from Small Objects:                                   COMPLIANT

 4.6-1, Disposal for space structures passing through LEO:                          COMPLIANT

 4.6-2, Disposal for space structures passing through GEO:                          NIA

 4.6-3, Disposal for space structures between LEO and GEO:                          N!A

 4.7-1, Casualty Risk for Reentry Debris                                            COMPLIANT

 4.8-1, Collision Hazards of Space Tethers                                          NIA




NXTRAC                    800 S. PCH Suite 8-247 Redondo Beach CA 90277             310-713-7301

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                                                                                                      NXTM C


1.0 Program Management & Mission Overview
 Program / Project Manager: Christian Vince

 Mission Description:
 LEO 1 was launched into lower orbit on January 12, 2018 and maneuvered into its final orbit of 1000 km altitude
 circular orbit inclined at 99.5 degrees over a period of several weeks. The satellite has a planned 3-year mission
 lifetime, during which it will be used for testing and demonstration. At the end of mission life, a sequence of
 maneuvers will be performed over 3 to 6 months to allow atmospheric draft to ultimately remove the vehicle from
 orbit through reentry.


 Foreign Government Involvement: Canada

 Project Milestones: Final mission orbit achieved   —   disposal operations begins NET 5 April 2021

 Launch Date: 12 Jan 2018

 Launch Vehicle: LEO 1 PSLV

 Launch Site: LEO 1 India

 Launch Vehicle Operator: LEO 1 India

 Mission Duration: 3 YEARS

 Mission Start: 5 April 2018

 Launch / Deployment Profile:

 Launch

 Checkout

 Raise   —   2 months

 Operations

 Post-mission Disposal: Maneuver to 425 x 975 km orbit, then NATURAL ORBITAL DECAY


 Selection of Orbit: Operations 1000 x 1000 km 99.5 degree, disposal 425 x 975 km

 Potential Physical Interference with other Orbiting Object: 9e-5




NXTRAC                      800 S. PCH Suite 8-247 Redondo Beach CA 90277                    310-713-7301

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                                                                                              MXTRA C


2.0 Spacecraft Description
Physical Description:

                             PARAMETER                                                          VALUE

 Total Mass at Launch                        165.5 kg

 Dry Mass at Launch                          127.9 kg

 Form Factor                                 Small Satellite

 Center of Mass                              0.28 x 0.2$ x 0.55 m

 Envelope (stowed)                           0.642 x 0.642 x 1.003 m

 Envelope (deployed)                         0642 x 0.642 x 1.003 m

 Propulsion Systems                          Hydrazine

 Fluid Systems                               NONE

 AOCS                                        3-axis controlled ADCS unit consisting of sun-vector
                                             sensors, earth-horizon sensors, magnetometer,
                                             magnetorquers, and reaction wheels

 Range Safety I Pyrotechnic Devices          NONE

 Electrical Generation                       SOLAR POWER

 Electrical Storage                          LITHIUM ION BATTERY

 Radioactive Materials                       NONE

1. Can spacecraft propellant and pressurant tanks be emptied at end of mission?
        YES

2. Can the spacecraft battery be disconnected from the charging circuit at end of mission?
        YES

3. If the answer to either of questions I and/or 2 is negative, what alternatives are available (bus
        modification or different bus) and at what additional, if any, cost?
        N/A

4. Have all mission-related debris generation been eliminated to the greatest extent possible?
        YES



MXTRA C                  800 S. PCH Suite 8-247 Redondo Beach CA 90277                  310-713-7301

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                                                                                             NXTRAC


5. For spacecraft operating in low Earth orbit (less than 2000 km), will the spacecraft reenter the
       atmosphere within 25 years after end of mission (and no more than 30 years after
       launch) or will the spacecraft be moved to a disposal orbit above 2000 km?
       YES LEO I will reenter the atmosphere within 25 years after end of mission
               -




6. For spacecraft operating in GEO, will the spacecraft be moved to a compliant disposal orbit,
       i.e., one which will remain at least 200 km (—125 mi) above/below GEO for at least 100
       years?
       NIA

7. Will all launch vehicle orbital stages and mission-related debris be left in low Earth orbits with
       orbital lifetimes of less than 25 years or left in compliant disposal orbits above 2,000 km
       (—1,240 mi)?
       MIA  rn
       iiri :s,p:




8. If an uncontrolled atmospheric reentry is anticipated after EOM, does the spacecraft bus or
       the payload contain any objects which might survive reentry, e.g., tanks, structural
       components, or other items made of high melting temperature materials such as
       titanium, beryllium, or stainless steel?
       YES but the small titanium tank poses less than 1:71200 hazard to human life
              -




9. If a disposal maneuver is planned for a mission not utilizing a controlled reentry, will the
       spacecraft propulsion system have a designed reliability of at least 0.9 at EOM?
       YES

10.    Does the spacecraft have any critical components, other than sensors and solar cells,
       which are exposed to the environment without MMCD protection?
       NO




NXTRAC                   800 S. PCH Suite 8-247 Redondo Beach CA 90277                 310-713-7301

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                                                                                          NXTRAC


3.0 Assessment of Debris During Normal Operations
Description:

LEO I has been designed so that during its normal operation it will release no debris. The
materials on the outside are tolerant of radiation and thermal cycling/mechanical fatigue to ensure
no release of extraneous material. All critical components (e.g., computers and control devices)
are built within the structure and shielded from external influences to ensure the spacecraft
remains in full control from the ground.


Objects larger than 1mm expected to be released during orbit:               NONE

Rationale for release of each object:                                       NIA
Time of release of each object:                                             N/A
Release velocity of each object:                                            N/A
Expected orbital parameters of each object:                                 NIA
Calculated orbital lifetime of each object:                                 NIA




 Assessment of spacecraft compliance with Requirements 4.3-1 & 4.3-2:

 4.3-1, Mission-Related Debris Passing Through LEO:                                COMPLIANT


 4.3-2, Mission-Related Debris Passing Near GEO:                                   COMPLIANT




NXTR4C                   800 S. PCH Suite 8-247 Redondo Beach CA 90277              310-713-7301

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                                                                                           NXTRAC




4.0 Assessment of Spacecraft Intentional Breakups and
   Potential for Explosions
Description:

LEO 1 has been designed with redundancy considerations so that individual unit faults will not
cause the loss of control of the spacecraft.

Telesat has also taken specific precautions to pre-empt accidental explosions in orbit. All pressure
vessels (pressurized propellant tanks, heat pipes, Lithium ion batteries etc.) on board have the
appropriate structural margins to failure as per the MIL-Spec requirements used in the industry.
All batteries and fuel tanks are monitored for pressure or temperature variations. The batteries
are operated utilizing a redundant automatic recharging scheme. Doing so ensures that charging
terminates normally without building up additional heat and pressure. Alarms in the Satellite
Control Centre will inform controllers of any anomalous variations. Additionally, long-term
trending analysis will be performed to monitor for any unexpected trends. On board fault
protection will ensure the isolation of any affected units and their replacement with the back-up
hardware/systems. As this process would occur within the spacecraft, it would also afford
protection from command link failures (on the ground).
Potential causes for spacecraft breakup:
There are only two plausible causes for breakup of the satellites:
   • Failure of batteries
   • Mechanical failure of the reaction wheels
Summary of failure modes and effects analysis of all credible failure modes which may
lead to an accidental explosion:
The battery pack complies with all controls / process requirements identified in NASA JSC-20793
Section 5.4.3 to mitigate the chance of any accidental venting / explosion caused from
overcharging, over-discharging, internal shorts, and external shorts.
The reaction wheels are contained within a sealed compartment to preclude release of debris
from operating at a high angular rate or part failure. Additional risk mitigation strategies include
limiting the maximum rate the wheels operate.
Detailed Plan for any designed spacecraft breakup, including explosions and intentional
collisions:
There is no planned breakup of the satellite on-orbit.
List of components passivated at EOM:
At the end of mission, the wheels will be despun and the batteries will be set to only discharge.
Rationale for all items required to be passivated that cannot be due to design: N/A


NXTRAC                   800 S. PCH Suite 8-247 Redondo Beach CA 90277               310-713-7301

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                                                                                           NXTRAC




 Assessment of spacecraft compliance with Requirements 4.4-1 through 4.4-4:

 4.4-1 Limiting the risk to other space systems from accidental explosions during      COMPLIANT
 deployment and mission operations while in orbit about Earth or the Moon

 4.4-2, Design for passivation after completion of mission operations while in orbit   COMPLIANT
 about Earth or the Moon

 4.4-3, Limiting the long-term risk to other space systems from planned breakups:      COMPLIANT
 There are no planned breakups of any of the satellite.

 4.4-4, Limiting the short-term risk to other space systems from planned breakups:     COMPLIANT
 There are no planned breakups of any of the satellites.




NXTRAC                    800 S. PCH Suite 8-247 Redondo Beach CA 90277                310-713-7301

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                                                                                            NX’TRAC


5.0 Assessment of Spacecraft Potential for On-Orbit
  Collisions
Description:

Telesat has been operating geostationary satellites for many years and performs station-keeping
from the Telesat Satellite Control Centre in Ottawa, Ontario, Canada.

Telesat also has experience in operating a non-geostationary LEO satellite. Specifically, since
2007 Telesat has been operating Radarsat-2 for MacDonald, Dettwiler and Associates Ltd.
(MDA). Radarsat-2 is a LEO non-geostationary satellite at an altitude of 798 km.


In order to protect against collision with other orbiting objects, Telesat shares daily ephemeris
data with the Canadian Space Agency (CSA), the Combined Space Operations Center fCSpOC)
(formerly the Joint Space Operations Center (JSpOC)), and the Space Data Center (SDC). These
daily ephemeris updates have been tagged with both the CSpOC and the SDC as available to all
operators for their space situational analysis. The CSpOC and the CSA provide notifications to
Telesat for any object they see approaching a Telesat satellite including LEO 1, together with
assessments of whether avoidance maneuvers are required, and Telesat maneuvers its satellites
accordingly.

For the LEO satellite Radarsat-2, Telesat works with the Canadian Space Agency to use
Probability of Collision (PoC) analysis to determine the need for collision avoidance maneuvers.
This system of highly effective PoC analysis is in use for LEO I operations and will be maintained
for the entire mission and disposal phases. The PoC analysis provides a greater than 3 day
notice of requirement of action for coordination of planned avoidance maneuvers, based on the
normal accuracy of the CSpOC observations of the objects in the space catalog.

Telesat has and will continue to coordinate with other non-geostationary satellite networks, such
as it has with Iridium, to minimize the risk of collision between LEO I and any other NGSO
satellite.

To further limit the potential for collision, Telesat monitors new satellite launches to ensure that
future satellites do not present a danger to LEO 1.

 LEO 1 has a propulsion system to maintain its orbit. The propulsion system on the satellite also
enables it to make necessary maneuvers to avoid collision with any approaching object.
Avoidance of other space objects will be achieved by the satellite firing its thrusters to adjust its
position within its control box in order to avoid the other object. Coordination with other operators
will aid this process.


Probability for Collision with Objects >10cm: 9e-5


NXTRAC                   800 S. PCH Suite 8-247 Redondo Beach CA 90277                310-713-7301

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                                                                                NXTRAC




 Assessment of spacecraft compliance with Requirement 45-1 and 45-2:


 45-1, Probability of Collision with Large Objects:                       COMPLIANT


 4.5-2, Probability of Damage from Small Objects:                         COMPLIANT




NXTRAC                    800 S. PCH Suite 8-247 Redondo Beach CA 90277     310-713-7301

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                                                                                              NXTRAC




6.0 Assessment of Spacecraft Post-Mission Disposal
  Plans and Procedures
Description:

Telesat has been operating GSO satellites for more than 40 years during which multiple
generations of its satellites have been retired and duly disposed of in the appropriate (graveyard)
orbit to avoid adding debris to the GSO orbit. Telesat takes LEO orbital debris mitigation very
seriously, as it plans to be a major operator of satellites in LEO orbits. Debris control and
mitigation are stated requirements for Telesat spacecraft design specifications. Telesat has
always met the requirements of the regulatory bodies and intends to continue to fully meet debris
mitigation requirements.

At the end of life, LEO 1 will be de-orbited by re-entering the satellite into the Earth’s atmosphere
and burning.

The de-orbiting has two phases. The first phase consists of the satellite being moved from its
operational orbit to a planned lower orbit, the “Decaying Lower Orbit”. The second phase, the
passive disposal phase, the satellite will be passivated and will burn up in the Earth’s atmosphere.

        First Phase De-Orbit: Decaying Lower Orbit

In the first phase, the satellite will be moved from its operational orbit to a planned lower orbit, the
‘Decaying Lower Orbit”.
The Decaying Lower Orbit for LEO I is a highly elliptical orbit of approximately 975 x 425 km.
This orbit minimizes the time in the disposal orbit and the debris generation potential, for the fuel
onboard. If more propellant is on board than is conservatively estimated, then the perigee will be
lowered to its maximum extent to further decrease the duration of the passive disposal.

The propellant needed to achieve the minimum de-orbit altitude is based on the change in velocity
(delta-V) required. Telesat will carefully track propellant usage over the life of the LEO I satellite
to ensure the satellite de-orbit is planned at a time that ensures this reserve of fuel is available,
along with additional fuel margin to allow for uncertainties in propellant accounting, orbital
determination and maneuver execution. Propellant tracking is accomplished using a bookkeeping
method in accordance with industry standard. Using this method, the ground control station tracks
the number of jet seconds utilized for station keeping, momentum control and other attitude
control events. The amount of fuel used is determined from the number of jet seconds. This
process, which is calibrated using data collected from thruster tests conducted on the ground, has
been found to be accurate to within a few months of life on the satellite. In addition to bookkeeping
updated based on orbital performance, Telesat will use in orbit thermal testing analysis and
trending, as a cross check. Telesat is familiar with and has experience with all of the above cited
methods.



NXTRAC                    800 S. ?CH Suite 8-247 Redondo Beach CA 90277                  310-713-7301

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                                                                                             NXTRAC

       Second Phase De-Orbit: Passive Disposal

In the second phase, the passive disposal phase, all stored energy sources onboard the satellite
will be removed by venting the remaining propellant and any remaining pressurant. All propulsion
lines and latch valves will be vented and left open. All battery chargers will be turned off and
batteries will be left in a permanent discharge state. All momentum storage devices will be
switched off. These steps will ensure that no buildup of energy can occur and eliminate the risk
of explosion after the satellite has stopped operating.

Once the satellite is moved to this lower orbit, and passivated to a safe state, it will be left in the
Decaying Lower Orbit which, within 25 years, will result in the re-entry of the satellite into the
Earth’s atmosphere and burning of the satellite.


Calculated for LEO 1, using the Decaying Lower Orbit of approximately 975 x 425 km, to deorbit
its satellites, the NASA DAS program for the probability of collision with an object of greater than
10cm, with a mission duration of about 3 years plus approximately a 15 year passive disposal,
the collision risk, is 0.00008.

At the time of entry into disposal phase, Telesat will custom design disposal orbit parameters that
minimize probability of collision with the International Space Station (ISS), other operational
satellites and constellations. To pre-predict the requited parameters in advance is challenging,
but Telesat is experienced in eccentricity and inclination collocation and probability of collision
avoidance strategies. At this eccentricity, even a passive disposal strategy, with properly chosen
argument of perigee and orbital parameters, will create significant separation.




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                                                                                            NXTRA C



Following its maneuver to a lower perigee of 425 km, the satellites orbit will naturally decay until
it reenters the atmosphere. Determining orbital decay timelines is challenging due to the complex
interplay of the satellite’s initial orbital parameters (e.g. altitude, eccentricity and inclination),
spacecraft mass, area, attitude profile (e.g. nadir facing, tumbling, gravity gradient) and
atmospheric density as a function of solar and geomagnetic activity. Predicting the environment
decades in the future results in a wide range of decay timelines depending on the level of activity
assumed. To account for this atmospheric variability, 5000 Monte Carlo trials were performed to
quantify the decay timeline distribution for LEO 1 as depicted in Figure 2. The simulation varied
solar activity and atmospheric density per the DAS 2.1.1 current solar flux table. The 95th
percentile for the decay timeline distribution is 8.25 years with 20 years representing the gggth
percentile as shown in Figure 3 and 10 sigma from the mean. In Figure 4, a detailed 6.7 year (1
sigma) decay profile is depicted for the LEO I satellite. As can be seen in Figure 2, the LEO 1
satellite will deorbit well within 25 years once achieving its final 425 by 975 km disposal orbit.

                                HISTOGRAM OF DECAY TIMELINES FOR LEO1
                                         5000 MONTE CARLO TRIALS
      1200




                                                        AVERAGE 4.99 YEARS
                                                        MEDIAN 4.62 YEARS
                                                        Sm DEV 1.65 YEARS




  F

      6


  D




        0



                                               DECAY TIMELINE (YEARS)


Figure 2: Histogram of Monte Carlo Trials for LEO 1 Decay Timeline (5000 trials)




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                           PERCENTAGE OF TRIALS LESSTHAN 25 YEARS IN DURATION
      100%

      95%

      90%

      85%

      80%

      75%

      70%

      65%

  b 60%
  z
      55%
  U
      50%
      45%
  U

      40%

      35%

      30%

      25%

      20%

      15%

      10%

       5%

       0%
             C    N   It         C   1.   C   C   C    4   It   It   It    It   C   —   C   C   ‘   0   ‘4   I   N   It   N       N       N
                                                                                                                              N       N


                                                  DECAY TIMELINE (YEARS)


Figure 3: Monte Carlo Trials of Decay Timeline by Percentile (5000 trials)




NXTRAC                     800 S. PCH Suite 8-247 Redondo Beach CA 90277                                         310-713-7301

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    1200




    1000




     900




     400




     200




       0


                                        YEARS SINCE START OF DISPOSAL ORBIT


                                             PERIGEE      APOGEE


Figure 4: Nominal Orbital Decay Profile for Telesat LEO 1 Satellite


Identification of Systems Required for Postmission Disposal:
GNC, Communications and Propulsion
Plan for Spacecraft Maneuvers required for Post-Mission Disposal:
Lower perigee from 975 x 425km over 3 6 months with coordination with CSpOC and other
mission management entities. Nominally 100 km per month with a minimum change in perigee
altitude of 50 km and a maximum change in perigee altitude of 200 km.
Calculation of final Area-to-Mass Ratio if Atmospheric Reentry Not Selected: NIA




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 Assessment of Spacecraft Compliance with Requirements 4.6-1 through 4.64:

 4.6-1, Disposal for space structures passing through LEO                            COMPLIANT
      All of the satellites will reenter the atmosphere within 25 years of mission
      completion and 30 years of launch.

 4.6-2, Disposal for space structures passing through GEO:                           N/A

 4.6-3, Disposal for space structures between LEO and GEO:                           NIA

 4.6-4, Reliability of postmission disposal operations:                              NIA




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                                                                                        NTRAC




7.0 Assessment of Spacecraft Reentry Hazards
Description:

LEO 1 has been designed to ensure the probability of survival of spacecraft components through
the re-entry into the Earth’s atmosphere is extremely limited. The design is consistent with
requirement 4.7.-i of NASA-SID 8719.14- Process for Limiting Orbit Debris and has been
assessed using NASA DAS (Debris Assessment Software) to ensure that the human casualty risk
resulting from the de-orbiting of the satellites is less than 1 in 10,000, in accordance with the
applicable guidelines.


Detailed description of spacecraft components by size, mass, material, shape, and
original location on the space vehicle:


 Subsystem                    Materials                  Quantity    Mass (g)     Size (mm)

 Propulsion                   Titanium Fuel Tank         1           5640         506



Summary of objects expected to survive an uncontrolled reentry (using DAS 2.1.1
software):
 None


Calculation of probability of human casualty for expected reentry year and inclination:
1:71200


 Assessment of spacecraft compliance with Requirement 4.7-1:

 4.7-1, Casualty Risk from Reentry Debris:                           COMPLIANT



7.1        Assessment of Spacecraft Hazardous Materials
Summary of Hazardous Materials Contained on Spacecraft:
 None



8.0 Assessment for Tether Missions
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Type of tether:
N/A

Description of tether system:
N/A
Determination of minimum size of object that will cause the tether to be severed:
N/A
Tether mission plan, including duration and postmission disposal:
N/A
Probability of tether colliding with large space objects:
N/A
Probability of tether being severed during mission or after postmission disposal:
N/A
Maximum orbital lifetime of a severed tether fragment:
N/A



 Assessment of compliance with Requirement 4.8-1:

 48-1, Cotlision Hazards of Space Tethers:              N/A




NXTRAC                   800 S. PCH Suite 8-247 Redondo Beach CA 90277       310-713-7301

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Figure 6: DAS 2.1.1 Conservative Decay Profile




NXTRAC                       800 S. PCH Suite 8-247 Redondo Beach CA 90277                           310-713-7301

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Document Created: 2019-08-28 14:47:46
Document Modified: 2019-08-28 14:47:46

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