Attachment ExhDOrbitalDebrisV1 SES-MFS-20170825-00955

Attachment ExhDOrbitalDebrisV1

This document pretains to SES-MFS-20170825-00955 for Modification w/ Foreign Satellite (earth station) on a Satellite Earth Station filing.

IBFS_SESMFS2017082500955_1266482

Exhibit D – Orbital Debris Mitigation Statement
FCC Form 312 – Modification Application
Applicant: Kongsberg Satellite Services AS
Call Sign: E160028

EXHIBIT D – ORBITAL DEBRIS STATEMENT FOR EV7

This Exhibit D to Form 312 submitted by Kongsberg Satellite Services AS (“KSAT”) contains the
orbital debris statement for the Canadian-owned and licensed non-geostationary satellite called,
exactView-7 (“EV7” or “Satellite”), also known as Maritime Monitoring and Messaging
Microsatellite (“M3MSat”). This statement conforms to the requirements of 47 C.F.R.
§§ 25.137(d) and 25.114(d)(14).

The Satellite has no propulsion system; nonetheless the Satellite’s post-mission atmospheric
reentry will occur within 25 years in accordance with the Commission’s orbital debris
mitigation policy.

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Exhibit D – Orbital Debris Mitigation Statement
FCC Form 312 – Modification Application
Applicant: Kongsberg Satellite Services AS
Call Sign: E160028

1. Satellite Design and Orbital Parameters

No. System Description Comment

1. Satellite Bus Design Microsatellite with dimensions of 60 x 60 x 85 cm, a box-shape, and a launch
mass of 85 kg. Bus design: AIM, by Honeywell Canada (formerly COM DEV)

2. Satellite Payload Primary payload: AIS receiver. Experimental payloads: a Low Data Rate
(LDR) UHF terminal to demonstrate a satellite-based AIS data relay
capability; and a Deep-Dielectric Charging Monitor (DDCM) to measure the
static energy that has accumulated in the satellites’ electronics.

3. Satellite Orbit As of February 21, 2017, the satellite’s orbital parameters are as follows:
Apogee of 520 km and Perigee of 486 km, Mean inclination of 97.5 degrees,
Right Ascension of Ascending Node of 116 degrees, Argument of Perigee of
117 degrees, Mean Anomaly of 243.3 degrees, and an Orbital Period of 5690
seconds.

4. Power Subsystem There are 6 body-mounted solar panels, with triple-junction GaInP/GaAs/Ge
solar cells. The predicted orbital average power generation is 66 W. The
battery consists of 24 SAFT MPS 176065 (5.8 Ah) lithium-ion cells arranged in
an 8-series/3-parallel (8S3P) configuration. The battery pack has an End of
Charge Voltage of 32.8 V, and a capacity of 480 Wh. The solar panels are
connected to a set of six battery charge regulators, which provide constant
voltage or peak power tracking, and regulate the charging current into the
battery. See row 9, Mitigating Risk of Accidental Explosion, below, for additional
detail on the battery.

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Exhibit D – Orbital Debris Mitigation Statement
FCC Form 312 – Modification Application
Applicant: Kongsberg Satellite Services AS
Call Sign: E160028

5. Attitude Control The Satellite has no propulsion. Three-axis stabilized bus platform. The
attitude determination and control system suite can point at either an inertial
or nadir target to within 5 degrees. The attitude actuation suite consists of a
set of reaction wheels, and a set of magnetic torque rods with redundant coils.
The reaction wheels are organized as two redundant sets of three orthogonal
wheels each. Each wheel has a momentum capacity of 80 mNms at 1000 rad/s
angular speed, and can generate a maximum torque of 5 mNm. The torque
rods are capable of 15 Am2 each and are used for initial detumbling, and for
reaction wheel desaturation.

6. Surface Area Final Area to Mass: 0.006 m2 / kg

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Exhibit D – Orbital Debris Mitigation Statement
FCC Form 312 – Modification Application
Applicant: Kongsberg Satellite Services AS
Call Sign: E160028

2. Orbital Debris Mitigation

47 C.F.R.
No. § 25.114 Required Statements Comment

7. (d)(14)(i) Planned Release of Debris No objects will be intentionally released during the Satellite
mission. The Satellite is designed so as not release any debris.
A statement that the space station operator
There are no deployable devices or instruments (or associated
has assessed and limited the amount of
pyrotechnics). All mechanisms (such as reaction wheels) are
debris released in a planned manner during
enclosed within the body of the satellite to ensure that a
normal operations . . . .
structural failure does not result in debris being distributed
outside the spacecraft. The battery is contained within MLI
blankets and located in compact areas of the spacecraft.

8. (d)(14)(i) Collisions with Small Debris and Loss of Control The Satellite has an outer structure (honeycomb panels) which
will minimize the effects of a strike from another orbital object.
A statement that the space station operator
The spacecraft also has redundant systems to reduce the risk that
. . . has assessed and limited the probability
small debris or a meteoroid strike would cause a loss of control.
of the space station becoming a source of
The bus is fully redundant, provided by two independent
debris by collisions with small debris or
strings, with each containing a full complement of the systems
meteoroids that could cause loss of control
required to operate the spacecraft (the magnetorquers, which

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Exhibit D – Orbital Debris Mitigation Statement
FCC Form 312 – Modification Application
Applicant: Kongsberg Satellite Services AS
Call Sign: E160028

and prevent post-mission disposal have redundant coils/electronics, are not fully independent). As
a result, the bus is single-failure tolerant. S-Band antennas (used
for TT&C) are mounted on two opposing faces to ensure
successful communication without attitude control. All six faces
of the satellite have solar panels, to ensure power can be
generated at all attitudes.
Even if control of the Satellite were lost, it would still deorbit as
planned within 25 years, as described in row 11, Orbital
Maintenance and Evolution, below.

9. (d)(14)(ii) Mitigating Risk of Accidental Explosion Breakup due to accidental explosion during or after the mission
is unlikely either because the sources of energy that can lead to
A statement that the space station operator
explosions are not present or because measures have been taken
has assessed and limited the probability of
to mitigate potential failure modes that can lead to break up, as
accidental explosions during and after
explained below:
completion of mission operations.
Propulsion System and Pressure Vessels – The spacecraft contains
 This statement must include a
no propulsion system and, therefore, does not contain any
demonstration that debris generation
propellants, fluids or high pressure vessels that require venting
will not result from the conversion of
or safing.
energy sources on board the
spacecraft into energy that fragments Battery Failure – Batteries may create debris if they leak or burst
the spacecraft. Energy sources due to overcharging, overheating, or shorting. The Satellite’s
include chemical, pressure, and battery consists of 24 SAFT MPS 176065 (5.8 Ah) lithium-ion cells
kinetic energy. arranged in an 8-series/3-parallel (8S3P) configuration. The
 This demonstration should address battery pack has a nominal full voltage of 32.8 V, and a capacity
whether stored energy will be of 480 Wh. While the battery’s charging circuits are not severed
removed at the spacecraft's end of at the end of the mission, the risk of debris generation is

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Exhibit D – Orbital Debris Mitigation Statement
FCC Form 312 – Modification Application
Applicant: Kongsberg Satellite Services AS
Call Sign: E160028

life, by depleting residual fuel and effectively mitigated by the measures described below.
leaving all fuel line valves open,
venting any pressurized system, To prevent the creation of orbital debris, the battery is shielded
leaving all batteries in a permanent within the Satellite and contains many of the safety features
discharge state, and removing any highlighted in NASA’s Guidelines on Lithium-ion Battery Use in
remaining source of stored energy, Space Applications, NASA/TM-2009-215751. First, the battery is
or through other equivalent shielded within the Satellite structure by MLI blankets, such that
procedures specifically disclosed in the rupturing of cells will not break the spacecraft’s outer shell.
the application;
Second, the battery contains self-protection features to reduce
the risk of cells leaking or rupturing, including circuit breakers
to prevent overcharging and shutdown separators and burst
discs, which function automatically without intervention from
the ground. Each battery cell has a circuit breaker that will open
the cell circuit should it be overcharged. In addition, each cell is
equipped with a mechanical vent that will preclude the cell from
bursting due to overpressure. The battery’s shutdown
separators are designed to prevent short circuits and to ensure
cell safety in the case of excess temperature. Due to the cell
design, the probability of a short is very low, but if one of the
cells were to short this would lead to the opening of the cell
circuit breaker to prevent further damage.

Catastrophic Reaction Wheel Failure – Reaction wheels are enclosed
within a mechanical structure which will contain all debris. At
the end of the mission, power to the reaction wheels will be
terminated by command, allowing them to spin-down.

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Exhibit D – Orbital Debris Mitigation Statement
FCC Form 312 – Modification Application
Applicant: Kongsberg Satellite Services AS
Call Sign: E160028

The nominal rotational speed of the wheels is well below the
maximum rotational speed (typically 200 rad/s) so as to not
create undue stress that would increase the likelihood of
fragmentation.
Pyrotechnics or Self-destruct Systems – The spacecraft does not
employ pyrotechnics or self-destruct systems.

10. (d)(14)(iii) Collision with Large Debris or Other Objects The potential for collision with other spacecraft was taken into
account when selecting the orbit for the Satellite.
A statement that the space station operator
has assessed and limited the probability of An analysis of the Satellite’s orbital parameters has been
the space station becoming a source of performed using NASA’s Debris Assessment Software, version
debris by collisions with large debris or 2.0.2. DAS was used to simulate the probability of the Satellite
other operational space stations. . . . colliding with an orbiting object larger than 10 cm in diameter;
the collision probability value was 0.000004. The log of the DAS
 Where a space station will be
analysis is appended in section 3.1 below. See section 3.1,
launched into a low-Earth orbit that
Probability of Collision with Large Objects (below).
is identical, or very similar, to an
orbit used by other space stations, exactEarth will rely on the accurate and timely information from
the statement must include an JSpOC to enable all operators to maintain situational awareness
analysis of the potential risk of and to expediently respond to any possible conjunctions.
collision and a description of what
measures the space station operator
plans to take to avoid in-orbit
collisions.
 If the space station operator is
relying on coordination with another
system, the statement must indicate

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Exhibit D – Orbital Debris Mitigation Statement
FCC Form 312 – Modification Application
Applicant: Kongsberg Satellite Services AS
Call Sign: E160028

what steps have been taken to
contact, and ascertain the likelihood
of successful coordination of
physical operations with, the other
system. . . .

11. (d)(14)(iii) Orbital Maintenance and Evolution Because the Satellite does not have a propulsion system, it does
not have the ability to maintain its orbit with accuracy. The
The statement must disclose the accuracy—
spacecraft’s orbit will decay naturally from its present orbit of
if any—with which orbital parameters of
520 x 486 km (as of February 21, 2017) (see additional orbital
non-geostationary satellite orbit space
details in row 3, above). The Satellite has a mission/design life of
stations will be maintained, including
5 years. It has a final area-to-mass ratio of approximately 0.006
apogee, perigee, inclination, and the right
m2/kg.
ascension of the ascending node(s).
Using NASA’s Debris Assessment Software, v 2.0.2, the Satellite
 In the event that a system is not able
has a calculated orbit lifetime of approximately 6.8 years
to maintain orbital tolerances, i.e., it
remaining and will reenter the Earth’s atmosphere in the year
lacks a propulsion system for orbital
2024. See the details of the DAS analysis and the simulated
maintenance, that fact should be
evolution of the orbit in section 3.2, Orbit Evolution, below.
included in the debris mitigation
disclosure. Such systems must also
indicate the anticipated evolution
over time of the orbit of the
proposed satellite or satellites . . . .

12. (d)(14)(iv) Post-Mission Disposal Plan The Satellite contains no propulsion system and thus has no
means of performing a deliberate post-mission reentry
A statement detailing the post-mission
maneuver. The disposal plan is to let the Satellite’s orbit decay
disposal plans for the space station at end of
naturally until it reenters the atmosphere and disintegrates.

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Exhibit D – Orbital Debris Mitigation Statement
FCC Form 312 – Modification Application
Applicant: Kongsberg Satellite Services AS
Call Sign: E160028

life, including the quantity of fuel—if any— Based on estimates using NASA’s DAS, reentry will occur
that will be reserved for post-mission approximately 8 years from launch, which occurred in June 2016.
disposal maneuvers. . . . See row 11. At the end of mission, all intentional transmissions
from the Satellite and power to its reaction wheels are set to
terminate. See section 3.3, Post-Mission Disposal (below).

13. (d)(14)(iv) Casualty Risk Assessment for Atmospheric Because the post-mission disposal plan for the Satellite involves
Reentry atmospheric reentry, a casualty risk assessment has been
performed using the NASA Debris Assessment Software,
The statement must also include a casualty
Version 2.0.2. The DAS analysis indicates that EV7 is compliant
risk assessment if planned post-mission
with NASA Requirement 4.7-1. See the results of the DAS
disposal involves atmospheric re-entry of
analysis in section 3.4, Casualty Risk Analysis (below).
the space station. In general, an assessment
should include an estimate as to whether
portions of the spacecraft will survive re-
entry and reach the surface of the Earth, as
well as an estimate of the resulting
probability of human casualty. . . .

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Exhibit D – Orbital Debris Mitigation Statement
FCC Form 312 – Modification Application
Applicant: Kongsberg Satellite Services AS
Call Sign: E160028

3. Inputs to and Results from NASA Debris Assessment Software, v2.0.2

3.1. Probability of Collision with Large Objects – § 25.114(d)(14)(iii)

04 19 2017; 16:23:39PM Processing Requirement 4.5-1: Return Status : Passed

==============
Run Data
==============

**INPUT**

Space Structure Name = EV7
Space Structure Type = Payload
Perigee Altitude = 486.000000 (km)
Apogee Altitude = 520.000000 (km)
Inclination = 97.500000 (deg)
RAAN = 0.000000 (deg)
Argument of Perigee = 0.000000 (deg)
Mean Anomaly = 0.000000 (deg)
Final Area-To-Mass Ratio = 0.006000 (m^2/kg)
Start Year = 2017.142000 (yr)
Initial Mass = 85.000000 (kg)
Final Mass = 85.000000 (kg)
Duration = 5.000000 (yr)
Station-Kept = False
Abandoned = True
PMD Perigee Altitude = -1.000000 (km)
PMD Apogee Altitude = -1.000000 (km)
PMD Inclination = 0.000000 (deg)
PMD RAAN = 0.000000 (deg)
PMD Argument of Perigee = 0.000000 (deg)
PMD Mean Anomaly = 0.000000 (deg)

**OUTPUT**

Collision Probability = 0.000004
Returned Error Message: Normal Processing
Date Range Error Message: Normal Date Range
Status = Pass

==============

=============== End of Requirement 4.5-1 ===============

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Exhibit D – Orbital Debris Mitigation Statement
FCC Form 312 – Modification Application
Applicant: Kongsberg Satellite Services AS
Call Sign: E160028

04 19 2017; 16:24:13PM Science and Engineering - Orbit Lifetime/Dwell Time

**INPUT**

Start Year = 2017.142000 (yr)
Perigee Altitude = 486.000000 (km)
Apogee Altitude = 520.000000 (km)
Inclination = 97.500000 (deg)
RAAN = 116.000000 (deg)
Argument of Perigee = 117.000000 (deg)
Area-To-Mass Ratio = 0.006000 (m^2/kg)

**OUTPUT**

Orbital Lifetime from Startyr = 6.899384 (yr)
Time Spent in LEO during Lifetime = 6.899384 (yr)
Last year of Propagation = 2024 (yr)
Returned Error Message: Object reentered

3.3. Post-Mission Disposal – Atmospheric Reentry – § 25.114(d)(14)(iv)

04 19 2017; 16:24:20PM Processing Requirement 4.6 Return Status : Passed

==============
Project Data
==============

**INPUT**

Space Structure Name = EV7
Space Structure Type = Payload

Perigee Altitude = 486.000000 (km)
Apogee Altitude = 520.000000 (km)
Inclination = 97.500000 (deg)
RAAN = 0.000000 (deg)
Argument of Perigee = 0.000000 (deg)
Mean Anomaly = 0.000000 (deg)
Area-To-Mass Ratio = 0.006000 (m^2/kg)
Start Year = 2017.142000 (yr)
Initial Mass = 85.000000 (kg)
Final Mass = 85.000000 (kg)
Duration = 5.000000 (yr)

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Exhibit D – Orbital Debris Mitigation Statement
FCC Form 312 – Modification Application
Applicant: Kongsberg Satellite Services AS
Call Sign: E160028

Station Kept = False
Abandoned = True
PMD Perigee Altitude = 456.137079 (km)
PMD Apogee Altitude = 499.639981 (km)
PMD Inclination = 97.692652 (deg)
PMD RAAN = 42.701580 (deg)
PMD Argument of Perigee = 90.031435 (deg)
PMD Mean Anomaly = 0.000000 (deg)

**OUTPUT**

Suggested Perigee Altitude = 456.137079 (km)
Suggested Apogee Altitude = 499.639981 (km)
Returned Error Message = Passes LEO reentry orbit criteria.

Released Year = 2024 (yr)
Requirement = 61
Compliance Status = Pass

==============

=============== End of Requirement 4.6 ===============

3.4. Casualty Risk Analysis – § 25.114(d)(14)(iv)

The DAS analysis indicates that EV7 is compliant with the FCC’s guidelines. We simulated the
Satellite’s uncontrolled atmospheric reentry and the resulting risk of human casualty from
reentry debris using DAS 2.0.2, testing compliance with Requirement 4.7-1 of NASA-STD
8719.14, where “potential for human casualty is assumed for any object with an impacting
kinetic energy in excess of 15 joules.” The DAS simulation indicates that eleven of the Satellite’s
components may survive reentry – the eleven titanium support plates – with impact energy of
approximately 2 joules, which is below the 15 joule threshold. Below is a table listing all of the
components used in the simulation and, following that, we have inserted the DAS log
indicating compliance with Requirement 4.7-1:

Component Quantit Material Mass Diameter/ Length
Name y Type (kg) Object Shape Width (m) (m) Height (m)
EV7 1 Aluminum 85 Box 0.600 0.850 0.600
(generic)

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Exhibit D – Orbital Debris Mitigation Statement
FCC Form 312 – Modification Application
Applicant: Kongsberg Satellite Services AS
Call Sign: E160028

Component Quantit Material Mass Diameter/ Length
Name y Type (kg) Object Shape Width (m) (m) Height (m)
Structure + 2 Aluminum 4.00 Flat Plate 0.600 0.850 N/A
Solar Arrays (generic)
- Zenith/-Y
Structure + 1 Aluminum 2.547 Flat Plate 0.600 0.600 N/A
Solar Arrays (generic)
- Anti-PAF
Structure + 1 Aluminum 3.26 Flat Plate 0.600 0.850 N/A
Solar Arrays (generic)
- +Y
Structure + 1 Aluminum 1.129 Flat Plate 0.600 0.850 N/A
Solar Arrays (generic)
- Nadir
Structure + 1 Aluminum 10.26 Box 0.440 0.530 0.054
Solar Arrays (generic)
- PAF
Corner posts 2 Aluminum 2.085 Box 0.104 0.560 0.104
(generic)
Payload 1 Aluminum 2.578 Flat Plate 0.496 0.570 0.020
connector (generic)
plate
Battery 1 Aluminum 4.486 Box 0.170 0.225 0.090
(generic)
Rate sensor 1 Aluminum 1.08 Box 0.126 0.126 0.055
assy (generic)
Reaction 2 Aluminum 1.338 Box 0.139 0.170 0.082
Wheel (generic)
Torque Rod 3 Aluminum 1.096 Cylinder 0.056 0.236 N/A
(generic)
AIS antenna 1 Aluminum 4.831 Box 0.354 0.354 0.065
(generic)
Antenna 6 Aluminum 0.127 Box 0.069 0.207 0.019
support (generic)
Receiver 2 Aluminum 2.238 Box 0.215 0.230 0.081
assy (generic)
C-band 1 Aluminum 3.80 Box 0.181 0.232 0.109
transmitter (generic)
LDR 1 Aluminum 1.41 Box 0.244 0.257 0.048
transponder (generic)
Data 2 Aluminum 3.657 Box 0.184 0.316 0.103
recorder (generic)
ADCS/CDSU 1 Aluminum 0.99 Box 0.138 0.400 0.028
(generic)

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Exhibit D – Orbital Debris Mitigation Statement
FCC Form 312 – Modification Application
Applicant: Kongsberg Satellite Services AS
Call Sign: E160028

Component Quantit Material Mass Diameter/ Length
Name y Type (kg) Object Shape Width (m) (m) Height (m)
S-band 2 Aluminum 0.815 Box 0.128 0.144 0.049
transponder (generic)
Power 1 Aluminum 2.868 Box 0.220 0.220 0.118
module/OBC (generic)
Communicat 1 Aluminum 1.269 Box 0.192 0.215 0.087
ions module (generic)
Support 11 Titanium 0.019 Box 0.050 0.050 0.020
plates (generic)
Launch 1 Aluminum 1.20 Box 0.440 0.440 0.088
separation (generic)
ring
Sun sensor 2 Aluminum 0.16 Box 0.715 0.850 0.113
(generic)
Sun sensor 1 Aluminum 0.263 Box 0.810 0.848 0.612
CIM (generic)
GPS 1 Aluminum 0.52 Box 0.1737 0.402 0.095
(generic)
LNA 1 Aluminum 0.45 Box 0.0938 0.1057 0.0627
Assembly (generic)
C band base 1 Aluminum 0.89 Box 0.154 0.1652 0.1487
plate (generic)

04 19 2017; 16:24:50PM *********Processing Requirement 4.7-1
Return Status : Passed

***********INPUT****
Item Number = 1

name = EV7
quantity = 1
parent = 0
materialID = 5
type = Box
Aero Mass = 85.000000
Thermal Mass = 85.000000
Diameter/Width = 0.600000
Length = 0.850000
Height = 0.600000

name = Structure + Solar Arrays - Zenith/-Y
quantity = 2

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Exhibit D – Orbital Debris Mitigation Statement
FCC Form 312 – Modification Application
Applicant: Kongsberg Satellite Services AS
Call Sign: E160028

parent = 1
materialID = 5
type = Flat Plate
Aero Mass = 4.000000
Thermal Mass = 4.000000
Diameter/Width = 0.600000
Length = 0.850000

name = Structure + Solar Arrays - Anti-PAF
quantity = 1
parent = 1
materialID = 5
type = Flat Plate
Aero Mass = 2.547000
Thermal Mass = 2.547000
Diameter/Width = 0.600000
Length = 0.600000

name = Structure + Solar Arrays - +Y
quantity = 1
parent = 1
materialID = 5
type = Flat Plate
Aero Mass = 3.260000
Thermal Mass = 3.260000
Diameter/Width = 0.600000
Length = 0.850000

name = Structure + Solar Arrays - Nadir
quantity = 1
parent = 1
materialID = 5
type = Flat Plate
Aero Mass = 1.129000
Thermal Mass = 1.129000
Diameter/Width = 0.600000
Length = 0.850000

name = Structure + Solar Arrays - PAF
quantity = 1
parent = 1
materialID = 5
type = Box
Aero Mass = 10.260000

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Exhibit D – Orbital Debris Mitigation Statement
FCC Form 312 – Modification Application
Applicant: Kongsberg Satellite Services AS
Call Sign: E160028

Thermal Mass = 10.260000
Diameter/Width = 0.440000
Length = 0.530000
Height = 0.054000

name = Corner posts
quantity = 2
parent = 1
materialID = 5
type = Box
Aero Mass = 2.085000
Thermal Mass = 2.085000
Diameter/Width = 0.104000
Length = 0.560000
Height = 0.104000

name = Payload connector plate
quantity = 1
parent = 1
materialID = 5
type = Box
Aero Mass = 2.578000
Thermal Mass = 2.578000
Diameter/Width = 0.496000
Length = 0.570000
Height = 0.020000

name = Battery
quantity = 1
parent = 1
materialID = 5
type = Box
Aero Mass = 4.486000
Thermal Mass = 4.486000
Diameter/Width = 0.170000
Length = 0.225000
Height = 0.090000

name = Rate sensor assy
quantity = 1
parent = 1
materialID = 5
type = Box
Aero Mass = 1.080000

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Exhibit D – Orbital Debris Mitigation Statement
FCC Form 312 – Modification Application
Applicant: Kongsberg Satellite Services AS
Call Sign: E160028

Thermal Mass = 1.080000
Diameter/Width = 0.126000
Length = 0.126000
Height = 0.055000

name = Reaction Wheel
quantity = 2
parent = 1
materialID = 5
type = Box
Aero Mass = 1.338000
Thermal Mass = 1.338000
Diameter/Width = 0.139000
Length = 0.170000
Height = 0.082000

name = Torque Rod
quantity = 3
parent = 1
materialID = 5
type = Cylinder
Aero Mass = 1.096000
Thermal Mass = 1.096000
Diameter/Width = 0.056000
Length = 0.236000

name = AIS antenna
quantity = 1
parent = 1
materialID = 5
type = Box
Aero Mass = 4.831000
Thermal Mass = 4.831000
Diameter/Width = 0.354000
Length = 0.354000
Height = 0.065000

name = Antenna support
quantity = 6
parent = 1
materialID = 5
type = Box
Aero Mass = 0.127000
Thermal Mass = 0.127000

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Exhibit D – Orbital Debris Mitigation Statement
FCC Form 312 – Modification Application
Applicant: Kongsberg Satellite Services AS
Call Sign: E160028

Diameter/Width = 0.069000
Length = 0.207000
Height = 0.019000

name = Receiver assy
quantity = 2
parent = 1
materialID = 5
type = Box
Aero Mass = 2.238000
Thermal Mass = 2.238000
Diameter/Width = 0.215000
Length = 0.230000
Height = 0.081000

name = C-band transmitter
quantity = 1
parent = 1
materialID = 5
type = Box
Aero Mass = 3.800000
Thermal Mass = 3.800000
Diameter/Width = 0.181000
Length = 0.232000
Height = 0.109000

name = LDR transponder
quantity = 1
parent = 1
materialID = 5
type = Box
Aero Mass = 1.410000
Thermal Mass = 1.410000
Diameter/Width = 0.244000
Length = 0.257000
Height = 0.048000

name = Data recorder
quantity = 2
parent = 1
materialID = 5
type = Box
Aero Mass = 3.657000
Thermal Mass = 3.657000

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Exhibit D – Orbital Debris Mitigation Statement
FCC Form 312 – Modification Application
Applicant: Kongsberg Satellite Services AS
Call Sign: E160028

Diameter/Width = 0.184000
Length = 0.316000
Height = 0.103000

name = ADCS/CDSU
quantity = 1
parent = 1
materialID = 5
type = Box
Aero Mass = 0.990000
Thermal Mass = 0.990000
Diameter/Width = 0.138000
Length = 0.400000
Height = 0.028000

name = S-band transponder
quantity = 2
parent = 1
materialID = 5
type = Box
Aero Mass = 0.815000
Thermal Mass = 0.815000
Diameter/Width = 0.128000
Length = 0.144000
Height = 0.049000

name = Power module/OBC
quantity = 1
parent = 1
materialID = 5
type = Box
Aero Mass = 2.868000
Thermal Mass = 2.868000
Diameter/Width = 0.220000
Length = 0.220000
Height = 0.118000

name = Communications module
quantity = 1
parent = 1
materialID = 5
type = Box
Aero Mass = 1.269000
Thermal Mass = 1.269000

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Exhibit D – Orbital Debris Mitigation Statement
FCC Form 312 – Modification Application
Applicant: Kongsberg Satellite Services AS
Call Sign: E160028

Diameter/Width = 0.192000
Length = 0.215000
Height = 0.087000

name = Support plates
quantity = 11
parent = 1
materialID = 66
type = Box
Aero Mass = 0.019000
Thermal Mass = 0.019000
Diameter/Width = 0.050000
Length = 0.050000
Height = 0.020000

name = Launch separation ring
quantity = 1
parent = 1
materialID = 5
type = Box
Aero Mass = 1.200000
Thermal Mass = 1.200000
Diameter/Width = 0.440000
Length = 0.440000
Height = 0.088000

name = Sun sensor
quantity = 2
parent = 1
materialID = 5
type = Box
Aero Mass = 0.160000
Thermal Mass = 0.160000
Diameter/Width = 0.715000
Length = 0.850000
Height = 0.113000

name = Sun sensor CIM
quantity = 1
parent = 1
materialID = 5
type = Box
Aero Mass = 0.263000
Thermal Mass = 0.263000

21 | P a g e

Exhibit D – Orbital Debris Mitigation Statement
FCC Form 312 – Modification Application
Applicant: Kongsberg Satellite Services AS
Call Sign: E160028

Diameter/Width = 0.810000
Length = 0.848000
Height = 0.612000

name = GPS
quantity = 1
parent = 1
materialID = 5
type = Box
Aero Mass = 0.520000
Thermal Mass = 0.520000
Diameter/Width = 0.173700
Length = 0.402000
Height = 0.095000

name = LNA Assembly
quantity = 1
parent = 1
materialID = 5
type = Box
Aero Mass = 0.450000
Thermal Mass = 0.450000
Diameter/Width = 0.093800
Length = 0.105700
Height = 0.062700

name = C band base plate
quantity = 1
parent = 1
materialID = 5
type = Box
Aero Mass = 0.890000
Thermal Mass = 0.890000
Diameter/Width = 0.154000
Length = 0.165200
Height = 0.148700

**************OUTPUT****
Item Number = 1

name = EV7
Demise Altitude = 77.993785
Debris Casualty Area = 0.000000
Impact Kinetic Energy = 0.000000

22 | P a g e

Exhibit D – Orbital Debris Mitigation Statement
FCC Form 312 – Modification Application
Applicant: Kongsberg Satellite Services AS
Call Sign: E160028

*************************************
name = Structure + Solar Arrays - Zenith/-Y
Demise Altitude = 71.358714
Debris Casualty Area = 0.000000
Impact Kinetic Energy = 0.000000

*************************************
name = Structure + Solar Arrays - Anti-PAF
Demise Altitude = 72.080785
Debris Casualty Area = 0.000000
Impact Kinetic Energy = 0.000000

*************************************
name = Structure + Solar Arrays - +Y
Demise Altitude = 72.707386
Debris Casualty Area = 0.000000
Impact Kinetic Energy = 0.000000

*************************************
name = Structure + Solar Arrays - Nadir
Demise Altitude = 76.349761
Debris Casualty Area = 0.000000
Impact Kinetic Energy = 0.000000

*************************************
name = Structure + Solar Arrays - PAF
Demise Altitude = 54.374085
Debris Casualty Area = 0.000000
Impact Kinetic Energy = 0.000000

*************************************
name = Corner posts
Demise Altitude = 73.265496
Debris Casualty Area = 0.000000
Impact Kinetic Energy = 0.000000

*************************************
name = Payload connector plate
Demise Altitude = 72.429347
Debris Casualty Area = 0.000000
Impact Kinetic Energy = 0.000000

*************************************

23 | P a g e

Exhibit D – Orbital Debris Mitigation Statement
FCC Form 312 – Modification Application
Applicant: Kongsberg Satellite Services AS
Call Sign: E160028

name = Battery
Demise Altitude = 61.887128
Debris Casualty Area = 0.000000
Impact Kinetic Energy = 0.000000

*************************************
name = Rate sensor assy
Demise Altitude = 68.901136
Debris Casualty Area = 0.000000
Impact Kinetic Energy = 0.000000

*************************************
name = Reaction Wheel
Demise Altitude = 70.727425
Debris Casualty Area = 0.000000
Impact Kinetic Energy = 0.000000

*************************************
name = Torque Rod
Demise Altitude = 69.714527
Debris Casualty Area = 0.000000
Impact Kinetic Energy = 0.000000

*************************************
name = AIS antenna
Demise Altitude = 64.088667
Debris Casualty Area = 0.000000
Impact Kinetic Energy = 0.000000

*************************************
name = Antenna support
Demise Altitude = 76.686715
Debris Casualty Area = 0.000000
Impact Kinetic Energy = 0.000000

*************************************
name = Receiver assy
Demise Altitude = 68.976542
Debris Casualty Area = 0.000000
Impact Kinetic Energy = 0.000000

*************************************
name = C-band transmitter
Demise Altitude = 65.306417

24 | P a g e

Exhibit D – Orbital Debris Mitigation Statement
FCC Form 312 – Modification Application
Applicant: Kongsberg Satellite Services AS
Call Sign: E160028

Debris Casualty Area = 0.000000
Impact Kinetic Energy = 0.000000

*************************************
name = LDR transponder
Demise Altitude = 71.911878
Debris Casualty Area = 0.000000
Impact Kinetic Energy = 0.000000

*************************************
name = Data recorder
Demise Altitude = 68.137683
Debris Casualty Area = 0.000000
Impact Kinetic Energy = 0.000000

*************************************
name = ADCS/CDSU
Demise Altitude = 73.971199
Debris Casualty Area = 0.000000
Impact Kinetic Energy = 0.000000

*************************************
name = S-band transponder
Demise Altitude = 71.476019
Debris Casualty Area = 0.000000
Impact Kinetic Energy = 0.000000

*************************************
name = Power module/OBC
Demise Altitude = 67.770167
Debris Casualty Area = 0.000000
Impact Kinetic Energy = 0.000000

*************************************
name = Communications module
Demise Altitude = 72.525675
Debris Casualty Area = 0.000000
Impact Kinetic Energy = 0.000000

*************************************
name = Support plates
Demise Altitude = 0.000000
Debris Casualty Area = 4.531446
Impact Kinetic Energy = 1.806095

25 | P a g e

Exhibit D – Orbital Debris Mitigation Statement
FCC Form 312 – Modification Application
Applicant: Kongsberg Satellite Services AS
Call Sign: E160028

*************************************
name = Launch separation ring
Demise Altitude = 75.442574
Debris Casualty Area = 0.000000
Impact Kinetic Energy = 0.000000

*************************************
name = Sun sensor
Demise Altitude = 77.829551
Debris Casualty Area = 0.000000
Impact Kinetic Energy = 0.000000

*************************************
name = Sun sensor CIM
Demise Altitude = 77.849683
Debris Casualty Area = 0.000000
Impact Kinetic Energy = 0.000000

*************************************
name = GPS
Demise Altitude = 76.696379
Debris Casualty Area = 0.000000
Impact Kinetic Energy = 0.000000

*************************************
name = LNA Assembly
Demise Altitude = 73.407691
Debris Casualty Area = 0.000000
Impact Kinetic Energy = 0.000000

*************************************
name = C band base plate
Demise Altitude = 74.200691
Debris Casualty Area = 0.000000
Impact Kinetic Energy = 0.000000

*************************************

=============== End of Requirement 4.7-1 ===============

26 | P a g e

Document Created: 2017-08-25 14:34:43
Document Modified: 2017-08-25 14:34:43

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