Exhibit D, DebrisPln

SUPPLEMENT submitted by Kongsberg Satellite Services AS

KSAT AS supplemental filing of orbital debris plan

2016-08-30

This document pretains to SES-LIC-20160218-00154 for License on a Satellite Earth Station filing.

IBFS_SESLIC2016021800154_1147967

Supplement, August 30, 2016 Exhibit D - Orbital Debris Mitigation Statement IBFS File No. SES-REG-20160218-00154 FCC Form 312 Kongsberg Satellite Services AS ORBITAL DEBRIS PLAN Below is an orbital debris plan for the exactEarth “EV1” satellite (“Satellite”) submitted in support of the Kongsberg Satellite Services (“KSAT”) non-common carrier earth station application of February 18, 2016 (IBFS File No. SES-REG-20160218-00154). The statement is prepared by KSAT in conjunction with its customer, exactEarth, the satellite owner and operator, in accordance with requirements of 47 C.F.R. §§ 25.137(d); 25.114(d)(14). The Satellite was launched in 2012. It uses an off-the-shelf platform from Surrey Satellite Technology Ltd. (SSTL-100), designed to prevent the release of debris during the mission and having the robustness to withstand the impact of small debris. The SSTL-100 platform contains a low-power propulsion system intended to be used for minor orbital corrections and the avoidance of orbital debris. The Satellite is part of the exactEarth AIS satellite constellation.1 While the orbital perigees of the satellites in the exactEarth constellation are generally below 625 km (an altitude suitable for AIS signal collection), the Satellite was launched in a ride share arrangement to a significantly higher orbit. Unique among the satellites operated by exactEarth, all of which will reenter within 25 years post-mission, the Satellite will not. From this higher orbit, reentry within that time frame would be possible only with a substantially larger propulsion system; such a system could not be accommodated on the SSTL-100 platform. exactEarth’s current policy, consistent with space industry standards and best practices, calls for 25-year post-mission reentry of its satellites. Taking advantage of the increased options for launches of secondary payloads, exactEarth plans to add two satellites to its constellation this year, both of which will reenter within 25 years post-mission. As a satellite operator, exactEarth recognizes the importance of debris mitigation and the collective responsibility of all space actors to take measures to minimize the threat of debris to other operational spacecraft and to ensure that the usable orbits remain accessible for future missions. 1 Most of the satellites in the exactEarth constellation were authorized by the Commission’s Office of Engineering and Technology as “AprizeSats,” all with approved orbital debris plans. See letter from D. Lorenzini, AprizeSat, to A. Serafini, FCC, OET (Sept. 9, 2010) (supplementing their experimental license application, FCC File No. 0084-EX-ML-2010, with debris plans for AprizeSats 3-6); letter from D. Lorenzini, AprizeSat, to A. Serafini, FCC, OET (June 12, 2012) (supplementing their experimental license application, FCC File No. 0023-EX-ML-2012, with debris plans for AprizeSats 7-10). 1|Page

Supplement, August 30, 2016 Exhibit D - Orbital Debris Mitigation Statement IBFS File No. SES-REG-20160218-00154 FCC Form 312 Kongsberg Satellite Services AS KSAT applauds the Commission’s Satellite Division for its policy foresight and efforts to mitigate debris, and respectfully requests lenient treatment of this isolated case. Despite the Satellite operator’s current policy of compliance with the 25-year reentry guideline, the Satellite’s low-power propulsion system is unable to compensate for the high perigee at end of mission. No action short of physical retrieval of the Satellite, which is not an available commercial option, could change the orbit of the Satellite so as to conform to the 25-year reentry guideline. KSAT also requests a waiver of Section 25.283(c) of the Commission’s rules,2 to the extent applicable, concerning discharge of batteries at end of mission. Good cause exists for this treatment as the underlying purpose of the Commission’s policy—to mitigate debris—is effectively achieved here even though the battery’s charging circuits are not severed at the end of the mission. As explained below, the battery contains many of the safety features highlighted in NASA’s Guidelines on Lithium-ion Battery Use in Space Applications, NASA/TM-2009- 215751. The Satellite uses a Lithium-ion battery. The Li-ion cells used in the battery are Sony 18650 Hard Carbon commercial cylindrical cells. The battery is shielded within the Satellite structure and is designed to prevent breakups; it contains self-protection circuits to avoid over charging (that could result in an explosion). The battery is located in an area where an explosion or rupture would not break the spacecraft’s outer shell. The battery is protected from overcharge by dump resistors in the power system that shunt the charging current when a voltage clamps above an upper level. Once the battery returns to nominal voltage, the clamp is taken off and the dump resistors become inactive again. The cells within the battery are also individually protected against overcharge (for example, if a cell in a string becomes mismatched as it ages). In such case, the pressure increase in the cell will activate a Current Interrupt Device that will permanently open circuit the cell (and hence string) in the battery. 2 Several precedents exist for waiver of strict compliance with Section 25.283(c). See, e.g., Dish Operating L.L.C. License Modification Application Grant, IBFS File No. SES-MFS-20080926-01242, Condition 487 (Jan. 30, 2009) (granting a waiver of sec. 25.283(c) for Ciel-2 in part because of “the limited probability that [residual stored energy sources] would result in . . . an explosion or deflagration large enough to release orbital debris”); Panasonic Avionics Corp. License Modification Application Grant, IBFS File No. SES-MFS-20130930-00845, Condition 90168 (Sept. 24, 2014) (granting a waiver of sec. 25.283(c) for Apstar 7, a Thales Alenia Space Spacebus-4000C2 model spacecraft that was launched on March 31, 2012, which was unable to deplete all residual stored energy). 2|Page

Supplement, August 30, 2016 Exhibit D - Orbital Debris Mitigation Statement IBFS File No. SES-REG-20160218-00154 FCC Form 312 Kongsberg Satellite Services AS The Sony cell also has a Positive Temperature Coefficient (PTC) switch which will heat up when a large current (charge or discharge) occurs in the cell, and limit the current by increasing the resistance. In the case of over pressure caused by excessive temperature (due to external heat for example), there is an external disc that will puncture and vent the cell safely. 3|Page

Supplement, August 30, 2016 Exhibit D - Orbital Debris Mitigation Statement IBFS File No. SES-REG-20160218-00154 FCC Form 312 Kongsberg Satellite Services AS ATTACHMENT ORBITAL DEBRIS STATEMENT FOR THE EXACTEARTH EV1 SATELLITE 1. Basic Satellite Design and Orbital Parameters No. System Description Comment 1. Satellite Bus Design Microsatellite with dimensions of 60 x 60 x 80 cm, a box-shape, and a launch mass of 98 kg. The Satellite uses the off-the-shelf SSTL-100 platform/bus from Surrey Satellite Technology Ltd. (SSTL), adapted for the Satellite mission with by COM DEV designed AIS receiver payload. 2. Satellite Payload Payload: AIS receiver. 3. Satellite Orbit Apogee of 830.7 km; perigee of 805.9 km; inclination of 98.955 degrees. Launch Date: July 22, 2012. 4. Propulsion System The spacecraft has a low power propulsion system – the “SSTL Low Power Resistojet” – for minor orbital corrections. It is rated for thrust only up to 100 mN. The fuel is butane and is stored within pressurized tanks in a liquid/vapor mixture. 5. Power Subsystem Solar Arrays: Body mounted solar arrays with single junction GaAs cells, total area 1.08 m2. One deployable solar array with triple Junction GaAs cells, total area 0.36m2. Approximately 65 4|Page

Supplement, August 30, 2016 Exhibit D - Orbital Debris Mitigation Statement IBFS File No. SES-REG-20160218-00154 FCC Form 312 Kongsberg Satellite Services AS W orbital average DC power at BOL. Battery: Li-ion cells providing 15 Ah capacity. Main Bus Voltage Range: 28V-33V range 6. Attitude Control Three-axis stabilized nadir pointing bus platform, using reaction wheels and magnetic torque rods. Command and data handling: Dual-redundant Controller Area Network (CAN) bus 2. Orbital Debris Mitigation 47 C.F.R. No. § 25.114 Required Statements Comment 1. (d)(14)(i) Planned Release of Debris No objects will be intentionally released during the mission. The spacecraft is designed such that it does not release any debris. A statement that the space station operator There are no deployable devices other than solar panels and no has assessed and limited the amount of debris will result from their deployment. The solar panel debris released in a planned manner during deployment is achieved using a Frangibolt system (non- normal operations . . . . explosive actuator) with an enclosure around the assembly to capture of any loose pieces. All mechanisms, such as reaction wheels and torque rods, are enclosed and the batteries are contained within the stack assembly. 5|Page

Supplement, August 30, 2016 Exhibit D - Orbital Debris Mitigation Statement IBFS File No. SES-REG-20160218-00154 FCC Form 312 Kongsberg Satellite Services AS 2. (d)(14)(i) Collisions with Small Debris and Loss of Control The spacecraft has an outer structure of honeycomb panels which will mitigate the impact of a strike from another object. A statement that the space station operator The propulsion system is used to avoid space debris when a . . . has assessed and limited the probability notification of a close encounter is received. The satellite bus is of the space station becoming a source of designed so that there are no credible single point failures. All debris by collisions with small debris or units either have full hot, cold or functional redundancy or meteoroids that could cause loss of control where this is not possible or practical to do so, graceful and prevent post-mission disposal degradation (such as loss of single string on the battery/solar cells). 3. (d)(14)(ii) Mitigating Risk of Accidental Explosion Breakup due to accidental explosion during or after the mission is unlikely because of the measures taken to mitigate potential A statement that the space station operator failure modes that can lead to break up, as explained below: has assessed and limited the probability of accidental explosions during and after Propulsion System and Pressure Vessels – The Satellite has a low completion of mission operations. power propulsion system (the “SSTL Low Power Resistojet”) for minor orbital corrections. The fuel is butane and is stored within  This statement must include a pressurized tanks in a liquid/vapor mixture. The pressure of the demonstration that debris generation mixture is 4 bar and baffles are employed to reduce slosh within will not result from the conversion of the tank. The tank has been designed so that it leaks before energy sources on board the bursting to avoid a break-up of the spacecraft. (The burst to spacecraft into energy that fragments working pressure ratio is 25:1.) At the end of the mission, a the spacecraft. Energy sources command set will be created to provide a depletion burn. include chemical, pressure, and kinetic energy. Battery Failure – The batteries are shielded within the Satellite structure and are designed to prevent breakups; they contain  This demonstration should address self-protection circuits to avoid over charging (that would result whether stored energy will be in an explosion). The batteries are located in areas where removed at the spacecraft's end of 6|Page

Supplement, August 30, 2016 Exhibit D - Orbital Debris Mitigation Statement IBFS File No. SES-REG-20160218-00154 FCC Form 312 Kongsberg Satellite Services AS life, by depleting residual fuel and explosions or ruptures would not break the spacecraft outer leaving all fuel line valves open, shell. While the batteries’ charging circuits are not severed at the venting any pressurized system, end of the mission, the risk of debris generation is effectively leaving all batteries in a permanent mitigated by the measures described above. discharge state, and removing any The Li-ion cells used in the battery are Sony 18650 Hard Carbon remaining source of stored energy, commercial cylindrical cells. Both the battery and its individual or through other equivalent cells are protected from overcharge by dump resistors in the procedures specifically disclosed in power system, which shunt the charging current when a voltage the application; clamps above an upper level. Moreover, in the case of over pressure caused by excessive temperature (due to external heat for example) there is an external disc that will puncture and vent the cell safely. See pages 2-3 for more detail. Catastrophic Reaction Wheel Failure – Reaction wheels are enclosed within a mechanical structure designed to contain debris. At the end of the mission, power to the reaction wheels will be terminated by command, allowing them to spin down. Pyrotechnics or Self-destruct Systems – The spacecraft does not employ pyrotechnics or self-destruct systems. 4. (d)(14)(iii) Collision with Large Debris or Other Objects An analysis of the Satellite’s orbital parameters has been performed using NASA’s Debris Assessment Software, version A statement that the space station operator 2.0.2 to simulate the probability of the Satellite colliding with an has assessed and limited the probability of orbiting object larger than 10 cm in diameter; the collision the space station becoming a source of probability value was 0.000045, a passing result. See section 3.1, debris by collisions with large debris or Probability of Collision with Large Objects (below), containing other operational space stations. . . . the log of the DAS analysis. To work around limitations in 7|Page

Supplement, August 30, 2016 Exhibit D - Orbital Debris Mitigation Statement IBFS File No. SES-REG-20160218-00154 FCC Form 312 Kongsberg Satellite Services AS  Where a space station will be NASA’s Debris Assessment Software, which can cause erroneous launched into a low-Earth orbit that results when the satellite will not reenter before the year 2050, a is identical, or very similar, to an fictional post-mission disposal maneuver lowering the Satellite orbit used by other space stations, perigee to altitude of 450 km was assumed in order to generate a the statement must include an result for this item. analysis of the potential risk of 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 what steps have been taken to contact, and ascertain the likelihood of successful coordination of physical operations with, the other system. . . . 5. (d)(14)(iii) Orbital Maintenance and Evolution The Satellite has a design life of 5 years. The Satellite will maintain orbital tolerances during its mission life using its low- The statement must disclose the accuracy— power propulsion system. Post-mission, from a perigee of if any—with which orbital parameters of approximately 800 km with an inclination of 98.955 degrees, the non-geostationary satellite orbit space satellite will perform a depletion burn with any remaining stations will be maintained, including propellant, after which the orbit will decay naturally. The apogee, perigee, inclination, and the right Satellite’s RAM area and solar radiation pressure area exceed 60 ascension of the ascending node(s). 8|Page

Supplement, August 30, 2016 Exhibit D - Orbital Debris Mitigation Statement IBFS File No. SES-REG-20160218-00154 FCC Form 312 Kongsberg Satellite Services AS  In the event that a system is not able cm x 60 cm with the deployed solar panel. Given its high orbit to maintain orbital tolerances, i.e., it and very limited propulsion system, the Satellite will not be able lacks a propulsion system for orbital to reenter within 25 years post-mission. The off-the-shelf SSTL- maintenance, that fact should be 100 satellite platform could not accommodate a propulsion included in the debris mitigation system capable of lowering the Satellite’s orbit to effect reentry disclosure. Such systems must also within that time frame from such a high orbit. See section 3.2, indicate the anticipated evolution Orbit Evolution (below), for a plot of the orbital evolution within over time of the orbit of the the time frame NASA’s Debris Assessment Software, version proposed satellite or satellites . . . . 2.0.2, is able to calculate. 6. (d)(14)(iv) Post-Mission Disposal Plan The post-mission disposal plan is to allow the orbit to decay naturally after a propulsion system depletion burn. A command A statement detailing the post-mission set will be uploaded to instruct the Satellite to perform the disposal plans for the space station at end of depletion burn with any remaining propellant in order to lower life, including the quantity of fuel—if any— the perigee. The Satellite has insufficient energy to perform a re- that will be reserved for post-mission entry maneuver. The Satellite’s time to deorbit post-mission will disposal maneuvers . . . . exceed 25 years. See section 3.3, Post-Mission Disposal (below), using NASA’s Debris Assessment Software, version 2.0.2. 7. (d)(14)(iv) Casualty Risk Assessment for Atmospheric We simulated the Satellite’s uncontrolled atmospheric reentry Reentry and the risk of human casualty resulting from reentry debris using NASA’s Debris Assessment Software, version 2.0.2, testing The statement must also include a casualty compliance with NASA-STD 8719.14 Revision A, Requirement risk assessment if planned post-mission 4.7-1 (“For uncontrolled reentry, the risk of human casualty from disposal involves atmospheric re-entry of surviving debris shall not exceed 0.0001 (1:10,000) . . . .”). the space station. In general, an assessment should include an estimate as to whether The Satellite complies with Requirement 4.7-1: The DAS analysis 9|Page

Supplement, August 30, 2016 Exhibit D - Orbital Debris Mitigation Statement IBFS File No. SES-REG-20160218-00154 FCC Form 312 Kongsberg Satellite Services AS portions of the spacecraft will survive re- has estimated that the risk of human casualty presented by EV1’s entry and reach the surface of the Earth, as reentry is 1:64200, a passing result by a substantial margin. See well as an estimate of the resulting the component list table and the DAS log of the casualty risk probability of human casualty . . . . analysis in section 3.4, Casualty Risk Analysis (below). 10 | P a g e

Supplement, August 30, 2016 Exhibit D - Orbital Debris Mitigation Statement IBFS File No. SES-REG-20160218-00154 FCC Form 312 Kongsberg Satellite Services AS 3. Inputs to and Results from NASA Debris Assessment Software, v2.0.2, for the Satellite (EV1) 3.1. Probability of Collision with Large Objects – § 25.114(d)(14)(iii) 07 18 2016; 15:00:28PM Processing Requirement 4.5-1: Return Status : Passed ============== Run Data ============== **INPUT** Space Structure Name = EV1 Space Structure Type = Payload Perigee Altitude = 805.900000 (km) Apogee Altitude = 830.700000 (km) Inclination = 98.955000 (deg) RAAN = 0.000000 (deg) Argument of Perigee = 0.000000 (deg) Mean Anomaly = 0.000000 (deg) Final Area-To-Mass Ratio = 0.004091 (m^2/kg)3 Start Year = 2012.000000 (yr) Initial Mass = 98.000000 (kg) Final Mass = 88.000000 (kg) Duration = 5.000000 (yr) Station-Kept = True Abandoned = False PMD Perigee Altitude = 450.000000 (km) PMD Apogee Altitude = 830.000000 (km) PMD Inclination = 98.955000 (deg) PMD RAAN = 0.000000 (deg) PMD Argument of Perigee = 0.000000 (deg) PMD Mean Anomaly = 0.000000 (deg) **OUTPUT** Collision Probability = 0.000045 Returned Error Message: Normal Processing Date Range Error Message: Normal Date Range Status = Pass 3 Calculated as follows: 0.6 m * 0.6 m / 88 kg = 0.0040909090909091 m2/kg. 11 | P a g e

Supplement, August 30, 2016 Exhibit D - Orbital Debris Mitigation Statement IBFS File No. SES-REG-20160218-00154 FCC Form 312 Kongsberg Satellite Services AS ============== =============== End of Requirement 4.5-1 =============== 3.2. Orbit Evolution – § 25.114(d)(14)(iii) Plot of Orbital Evolution assuming no post-mission disposal maneuver is performed (a worst case scenario): 07 13 2016; 19:15:32PM Science and Engineering - Apogee/Perigee History for a Given Orbit **INPUT** Perigee Altitude = 805.900000 (km) Apogee Altitude = 830.700000 (km) Inclination = 98.955000 (deg) RAAN = 315.039000 (deg) 12 | P a g e

Supplement, August 30, 2016 Exhibit D - Orbital Debris Mitigation Statement IBFS File No. SES-REG-20160218-00154 FCC Form 312 Kongsberg Satellite Services AS Argument of Perigee = 30.500000 (deg) Mean Anomaly = 0.000000 (deg) Area-To-Mass Ratio = 0.004091 (m^2/kg) Start Year = 2017.000000 (yr) Integration Time = 93.000000 (yr) **OUTPUT** Plot 07 13 2016; 19:17:42PM Science and Engineering - Orbit Lifetime/Dwell Time **INPUT** Start Year = 2017.000000 (yr) Perigee Altitude = 805.900000 (km) Apogee Altitude = 830.700000 (km) Inclination = 98.955000 (deg) RAAN = 315.039000 (deg) Argument of Perigee = 30.500000 (deg) Area-To-Mass Ratio = 0.004091 (m^2/kg) **OUTPUT** Orbital Lifetime from Startyr = 100.002738 (yr) Time Spent in LEO during Lifetime = 100.002738 (yr) Last year of Propagation = 2117 (yr) Returned Error Message: Object did not reenter within MAXPROPYRS 3.3. Post-Mission Disposal – Atmospheric Reentry – § 25.114(d)(14)(iv) 07 13 2016; 19:18:30PM Processing Requirement 4.6 Return Status : Failed ============== Project Data ============== **INPUT** Space Structure Name = EV1 Space Structure Type = Payload 13 | P a g e

Supplement, August 30, 2016 Exhibit D - Orbital Debris Mitigation Statement IBFS File No. SES-REG-20160218-00154 FCC Form 312 Kongsberg Satellite Services AS Perigee Altitude = 805.900000 (km) Apogee Altitude = 830.700000 (km) Inclination = 98.955000 (deg) RAAN = 0.000000 (deg) Argument of Perigee = 0.000000 (deg) Mean Anomaly = 0.000000 (deg) Area-To-Mass Ratio = 0.004091 (m^2/kg) Start Year = 2012.000000 (yr) Initial Mass = 98.000000 (kg) Final Mass = 88.000000 (kg) Duration = 5.000000 (yr) Station Kept = True Abandoned = True PMD Perigee Altitude = 805.900000 (km) PMD Apogee Altitude = 830.700000 (km) PMD Inclination = 98.955000 (deg) PMD RAAN = 0.000000 (deg) PMD Argument of Perigee = 0.000000 (deg) PMD Mean Anomaly = 0.000000 (deg) **OUTPUT** Suggested Perigee Altitude = 425.900000 (km) Suggested Apogee Altitude = 830.700000 (km) Returned Error Message = LEO reentry PMD exceeds lifetime limit. Released Year = 2042 (yr) Requirement = 61 Compliance Status = Fail ============== =============== End of Requirement 4.6 =============== 3.4. Casualty Risk Analysis – § 25.114(d)(14)(iv) We simulated the Satellite’s (EV1) 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. Three components may survive reentry. While one component is estimated to have an impact energy that exceeds 15 Joules, the analysis indicates a passing result for EV1. Below is a 14 | P a g e

Supplement, August 30, 2016 Exhibit D - Orbital Debris Mitigation Statement IBFS File No. SES-REG-20160218-00154 FCC Form 312 Kongsberg Satellite Services AS table listing the components used in the simulation and, following that, we have inserted the DAS log indicating compliance with Requirement 4.7-1: Component Material Object Diameter/ Length Height Name Quantity Type Shape Mass (kg) Width (m) (m) (m) EV1 1 Aluminum Box 88.000 0.600 0.800 0.600 (generic) Solar Arrays 3 Aluminum Flat Plate 3.000 0.600 0.617 (closure panels) (generic) Battery 1 Aluminum Box 4.915 0.159 0.221 0.068 (generic) Battery support 1 Aluminum Box 0.849 0.202 0.335 0.048 bracket (generic) Reaction Wheel 3 Aluminum Cylinder 0.900 0.104 0.100 (generic) Torque Rod 3 Aluminum Cylinder 0.470 0.250 0.256 (generic) Bus Electronics 9 Aluminum Box 3.000 0.322 0.322 0.033 (Micro Trays (generic) inc. PCBs) Bus Electronics 6 Aluminum Box 0.430 0.135 0.190 0.029 (Nano Trays (generic) inc. PCBs) Tie Bars 305.0 8 Titanium (6 Cylinder 0.043 0.063 0.305 Al-4 V) Tie Bars 102.0 6 Titanium (6 Cylinder 0.010 0.050 0.102 Al-4 V) Thruster 1 Aluminum Cylinder 0.240 0.021 0.650 (generic) Propellant Tank 2 Stainless Cylinder 1.400 0.11 0.325 Steel (generic) Hinge 2 Aluminum Cylinder 0.250 0.260 0.090 (generic) HDRS 1 Aluminum Cylinder 1.007 0.120 0.980 (generic) Structural 1 Aluminum Flat Plate 3.300 0.600 0.600 HDRS Panel (generic) Exterior 1 Aluminum Box 4.600 0.600 0.600 0.025 Bottom Panel (generic) Exterior Top 1 Aluminum Box 2.300 0.600 0.600 0.020 (generic) 15 | P a g e

Supplement, August 30, 2016 Exhibit D - Orbital Debris Mitigation Statement IBFS File No. SES-REG-20160218-00154 FCC Form 312 Kongsberg Satellite Services AS Component Material Object Diameter/ Length Height Name Quantity Type Shape Mass (kg) Width (m) (m) (m) Deployable 1 Aluminum Box 2.467 0.617 0.640 0.012 Panel (fully (generic) populated) 08 26 2016; 16:30:43PM *********Processing Requirement 4.7-1 Return Status : Passed ***********INPUT**** Item Number = 1 name = EV1 quantity = 1 parent = 0 materialID = 5 type = Box Aero Mass = 88.000000 Thermal Mass = 88.000000 Diameter/Width = 0.600000 Length = 0.800000 Height = 0.600000 name = Solar Arrays (closure panels) quantity = 3 parent = 1 materialID = 5 type = Flat Plate Aero Mass = 3.000000 Thermal Mass = 3.000000 Diameter/Width = 0.600000 Length = 0.617000 name = Battery quantity = 1 parent = 1 materialID = 5 type = Box Aero Mass = 4.915000 Thermal Mass = 4.915000 Diameter/Width = 0.159000 Length = 0.221000 Height = 0.068000 16 | P a g e

Supplement, August 30, 2016 Exhibit D - Orbital Debris Mitigation Statement IBFS File No. SES-REG-20160218-00154 FCC Form 312 Kongsberg Satellite Services AS name = Battery suport bracket quantity = 1 parent = 1 materialID = 5 type = Box Aero Mass = 0.849000 Thermal Mass = 0.849000 Diameter/Width = 0.202000 Length = 0.335000 Height = 0.048000 name = Reaction Wheel quantity = 3 parent = 1 materialID = 5 type = Cylinder Aero Mass = 0.900000 Thermal Mass = 0.900000 Diameter/Width = 0.104000 Length = 0.100000 name = Torque Rod quantity = 3 parent = 1 materialID = 5 type = Cylinder Aero Mass = 0.470000 Thermal Mass = 0.470000 Diameter/Width = 0.250000 Length = 0.256000 name = Bus Electronics (Micro Trays inc. PCBs) quantity = 9 parent = 1 materialID = 5 type = Box Aero Mass = 3.000000 Thermal Mass = 3.000000 Diameter/Width = 0.322000 Length = 0.322000 Height = 0.033000 name = Bus Electronics (Nano Trays inc. PCBs) quantity = 6 17 | P a g e

Supplement, August 30, 2016 Exhibit D - Orbital Debris Mitigation Statement IBFS File No. SES-REG-20160218-00154 FCC Form 312 Kongsberg Satellite Services AS parent = 1 materialID = 5 type = Box Aero Mass = 0.430000 Thermal Mass = 0.430000 Diameter/Width = 0.135000 Length = 0.190000 Height = 0.029000 name = Tie Bars 305.0 quantity = 8 parent = 1 materialID = 65 type = Cylinder Aero Mass = 0.043000 Thermal Mass = 0.043000 Diameter/Width = 0.063000 Length = 0.305000 name = Tie Bars 102.0 quantity = 6 parent = 1 materialID = 65 type = Cylinder Aero Mass = 0.010000 Thermal Mass = 0.010000 Diameter/Width = 0.050000 Length = 0.102000 name = Thruster quantity = 1 parent = 1 materialID = 5 type = Cylinder Aero Mass = 0.240000 Thermal Mass = 0.240000 Diameter/Width = 0.021000 Length = 0.650000 name = Propellant Tank quantity = 2 parent = 1 materialID = 54 type = Cylinder 18 | P a g e

Supplement, August 30, 2016 Exhibit D - Orbital Debris Mitigation Statement IBFS File No. SES-REG-20160218-00154 FCC Form 312 Kongsberg Satellite Services AS Aero Mass = 1.400000 Thermal Mass = 1.400000 Diameter/Width = 0.110000 Length = 0.325000 name = Hinge quantity = 2 parent = 1 materialID = 5 type = Cylinder Aero Mass = 0.250000 Thermal Mass = 0.250000 Diameter/Width = 0.260000 Length = 0.090000 name = HDRS quantity = 1 parent = 1 materialID = 5 type = Cylinder Aero Mass = 1.007000 Thermal Mass = 1.007000 Diameter/Width = 0.120000 Length = 0.980000 name = Structural HDRS Panel quantity = 1 parent = 1 materialID = 5 type = Flat Plate Aero Mass = 3.300000 Thermal Mass = 3.300000 Diameter/Width = 0.600000 Length = 0.600000 name = Exterior Bottom Panel quantity = 1 parent = 1 materialID = 5 type = Box Aero Mass = 4.600000 Thermal Mass = 4.600000 Diameter/Width = 0.600000 Length = 0.600000 19 | P a g e

Supplement, August 30, 2016 Exhibit D - Orbital Debris Mitigation Statement IBFS File No. SES-REG-20160218-00154 FCC Form 312 Kongsberg Satellite Services AS Height = 0.025000 name = Exterior Top quantity = 1 parent = 1 materialID = 5 type = Box Aero Mass = 2.300000 Thermal Mass = 2.300000 Diameter/Width = 0.600000 Length = 0.600000 Height = 0.020000 name = Deployable Panel (fully populated) quantity = 1 parent = 1 materialID = 5 type = Box Aero Mass = 2.467000 Thermal Mass = 2.467000 Diameter/Width = 0.617000 Length = 0.640000 Height = 0.012000 **************OUTPUT**** Item Number = 1 name = EV1 Demise Altitude = 77.997933 Debris Casualty Area = 0.000000 Impact Kinetic Energy = 0.000000 ************************************* name = Solar Arrays (closure panels) Demise Altitude = 71.378480 Debris Casualty Area = 0.000000 Impact Kinetic Energy = 0.000000 ************************************* name = Battery Demise Altitude = 58.961182 Debris Casualty Area = 0.000000 Impact Kinetic Energy = 0.000000 20 | P a g e

Supplement, August 30, 2016 Exhibit D - Orbital Debris Mitigation Statement IBFS File No. SES-REG-20160218-00154 FCC Form 312 Kongsberg Satellite Services AS ************************************* name = Battery suport bracket Demise Altitude = 75.081019 Debris Casualty Area = 0.000000 Impact Kinetic Energy = 0.000000 ************************************* name = Reaction Wheel Demise Altitude = 69.767761 Debris Casualty Area = 0.000000 Impact Kinetic Energy = 0.000000 ************************************* name = Torque Rod Demise Altitude = 76.775980 Debris Casualty Area = 0.000000 Impact Kinetic Energy = 0.000000 ************************************* name = Bus Electronics (Micro Trays inc. PCBs) Demise Altitude = 67.551261 Debris Casualty Area = 0.000000 Impact Kinetic Energy = 0.000000 ************************************* name = Bus Electronics (Nano Trays inc. PCBs) Demise Altitude = 74.917410 Debris Casualty Area = 0.000000 Impact Kinetic Energy = 0.000000 ************************************* name = Tie Bars 305.0 Demise Altitude = 0.000000 Debris Casualty Area = 4.364455 Impact Kinetic Energy = 1.026582 ************************************* name = Tie Bars 102.0 Demise Altitude = 0.000000 Debris Casualty Area = 2.704783 Impact Kinetic Energy = 0.197254 ************************************* name = Thruster 21 | P a g e

Supplement, August 30, 2016 Exhibit D - Orbital Debris Mitigation Statement IBFS File No. SES-REG-20160218-00154 FCC Form 312 Kongsberg Satellite Services AS Demise Altitude = 76.567402 Debris Casualty Area = 0.000000 Impact Kinetic Energy = 0.000000 ************************************* name = Propellant Tank Demise Altitude = 0.000000 Debris Casualty Area = 1.245284 Impact Kinetic Energy = 569.692993 ************************************* name = Hinge Demise Altitude = 76.930355 Debris Casualty Area = 0.000000 Impact Kinetic Energy = 0.000000 ************************************* name = HDRS Demise Altitude = 76.578011 Debris Casualty Area = 0.000000 Impact Kinetic Energy = 0.000000 ************************************* name = Structural HDRS Panel Demise Altitude = 70.396956 Debris Casualty Area = 0.000000 Impact Kinetic Energy = 0.000000 ************************************* name = Exterior Bottom Panel Demise Altitude = 67.733402 Debris Casualty Area = 0.000000 Impact Kinetic Energy = 0.000000 ************************************* name = Exterior Top Demise Altitude = 73.198636 Debris Casualty Area = 0.000000 Impact Kinetic Energy = 0.000000 ************************************* name = Deployable Panel (fully populated) Demise Altitude = 72.984472 Debris Casualty Area = 0.000000 22 | P a g e

Supplement, August 30, 2016 Exhibit D - Orbital Debris Mitigation Statement IBFS File No. SES-REG-20160218-00154 FCC Form 312 Kongsberg Satellite Services AS Impact Kinetic Energy = 0.000000 ************************************* =============== End of Requirement 4.7-1 =============== 23 | P a g e


Document Created: 2016-08-30 17:00:48
Document Modified: 2016-08-30 17:00:48
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