Exhibit B ODAR

0158-EX-CN-2019 Text Documents

Swarm Technologies, Inc.

2019-03-08

            Exhibit B – Orbital Debris Assessment Report (“ODAR”)



SWARM Orbital Debris Assessment Report
SWARM TECHNOLOGIES MISSION PROFILE
PREPARED BY: SWARM TECHNOLOGIES INC
REVISION ​1​, May 21, 2018




ODAR Signature Approval
Program/ Project      Sara Spangelo
Manager

Signature


Date                  May 21, 2018




ODAR Section 1: Program Management and Mission Overview
Program/ Project      Sara Spangelo
Manager

Mission Description   This mission is a technology demo for two-way communications satellites, and
                      data relay.

Foreign Government    None
Involvement

Project Milestones    The project milestones for the Swarm satellites align with the launch
                      of the vehicles into orbit, including a delivery of the spacecraft one month prior
                      to launch of the SpaceX SSO-A mission.

Proposed Launch       September 1, 2018
Date:

Proposed Launch       Electron
Vehicles              Number of Satellites: 3
                      Altitude: 575 km
                      SSO
                      Period: 95 min

Proposed Launch       Vandenberg Air Force Base, CA, United States
Sites


 Launch Vehicle         SpaceX
 Operator:

 Mission Duration:      The operational lifetime of the hardware and electronics for each satellite is
                        designed to be up to​ 10 ​years following deployment from the launch vehicle.
                        The orbital lifetime for the satellites is expected to be between 5.​3 to 9.3 year​s,
                        depending on the vehicle’s orbit and solar influence of the Earth’s atmosphere,
                        as described in Section 6.



 Launch /               Launch
 Deployment Profile:    The Swarm satellites will be injected directly into the target orbits outlined in the
                        table above.

                        Checkout
                        For up to 1 month following deployment into orbit, the Swarm satellites will
                        remain in checkout phase. During this phase, ground operators will verify
                        correct operation of the satellite and its payloads, and prepare it for the
                        operational phase.

                        Operations
                        The operational phase of the satellite begins following the successful
                        deployment of the Swarm satellites from the launch vehicle and successful
                        checkout.

                        Post-mission Disposal
                        Following the end of the operational phase, the satellites will remain on orbit in a
                        non-transmitting mode​ while the ​orbit of the satellite passively decays until the
                        satellite reenters the atmosphere and disintegrates. The satellite is nominally
                        expected to reenter the atmosphere 5.3 y​ears following deployment from the
                        launch vehicle, as detailed in Appendix B: Swarm Satellites Orbit Lifetime.


 Selection of Orbit:    The selection of the chosen orbit was made due to available launch
                        opportunities.

 Potential Physical     As the satellite does not have any propulsion systems, its orbit will naturally
 Interference with      decay following deployment from the launch vehicle.
 Other Orbiting
 Object:                                     ​ n 5, the probability of physical interference between the
                        As detailed in Sect​io
                        satellites and other space objects is sufficiently unlikely that the satellite
                        complies with Requirement 4.5.




ODAR Section 2: Spacecraft Description
Physical Description:
 Property                    Value

 Total Mass at Launch        1.9801 kg (all three satellites), [0.3971 kg, 0.660 kg, 0.923kg] (individual


                             satellite masses)

Dry Mass at Launch           1.9801 kg (all three satellites), [0.3971 kg, 0.660 kg, 0.923kg] (individual
                             satellite masses)

Form Factor                  1U satellites, Qty 3

COG                          <X1,Y1,Z1> = <0, ​4.3​, 8  ​ .3​>, <X2,Y2,Z2> = <0, ​2.3​, ​18.5​>, <X3,Y3,Z3> =
                             <0, ​1.6​, 4
                                        ​ .8​> [mm] relative to geometric center (all three satellites)

Envelope (stowed)            100mm x 100mm x 113.5mm (each of the three satellites)

Envelope (deployed)          100mm x 100mm x 113.5mm (each of the three satellites)
                             Deployed dipole antenna tip to tip is 892 mm

Propulsion Systems           None

Fluid Systems                None

AOCS                         Stabilization, GPS navigation

Range Safety/                None
Pyrotechnic Devices

Electrical Generation        Solar cells

Electrical Storage           Rechargeable lithium-ion battery. Qty 1: 18650B Panasonic cell.

Radioactive Materials        None




ODAR Section 3: Assessment of Debris Released During Normal
Operations
Objects larger than 1mm expected to be released during orbit:                 None

Rationale for release of each object:                                         N/A

Time of release of each object:                                               N/A

Release velocity of each object:                                              N/A

Expected orbital parameters of each object:                                   N/A

Calculated orbital lifetime of each object:                                   N/A




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


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

 4.3-2, Mission-Related Debris Passing Near GEO:                                       COMPLIANT
A DAS 2.1.2 log demonstrating the compliance to the above requirements is available in Appendix A –
“DAS 2.1.2 Log”.




ODAR Section 4: Assessment of Spacecraft Intentional Breakups
and Potential for Explosions
Potential causes for spacecraft breakup (there is only one plausible causes for breakup of the satellites):
    ● Energy released from onboard Lithium-ion battery from the unlikely event of overcharging or
        shorts

Summary of failure modes and effects analysis of all credible failure modes which may lead to an
accidental explosion:
The battery aboard the satellite is a 12.5 Whr Lithium-Ion battery, which represents the only credible
failure mode during which stored energy is released. The main failure modes associated with Lithium Ion
batteries result from overcharging, over-discharging, internal shorts, and external shorts.

The battery onboard Swarm satellites complies with all controls / process requirements identified in
JSC-20793 Section 5.4.3 to mitigate chance of any accidental venting / explosion caused by the above
failure modes.

Detailed Plan for any designed spacecraft breakup, including explosions and intentional
collisions:
There is no planned breakup of the satellites on-orbit.

List of components passivated at EOM:
At end of mission, all radio transmissions and beacons will be disabled. Spacecraft transmissions are only
initiated by ground command and self terminate. All RF transmissions from the satellite can be disabled
via command from the ground.

Rationale for all items required to be passivated that cannot be due to design:
N/A


 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 satellites.

 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.




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

Probability for Collision with Objects >10cm:
The probability of a collision of any of the satellites with an orbiting object larger than 10cm in diameter
was sufficiently small that the simulation performed using DAS 2.1.2 software returned a probability value
of 0.


 Assessment of spacecraft compliance with Requirement 4.5-1 and 4.5-2:

 4.5-1, Probability of Collision with Large Objects:                                     COMPLIANT

 4.5-2, Probability of Damage from Small Objects:                                        COMPLIANT
A DAS 2.1.2 log demonstrating the compliance to the above requirements is available in Appendix A –
“DAS 2.1.2 Log”.




ODAR Section 6: Assessment of Spacecraft Post-mission
Disposal Plans and Procedures
Description of Disposal Option Selected:
Following its deployment, the satellite’s orbit will naturally decay until it reenters the atmosphere. Table 1
describes the mission scenarios for which lifetime analysis of Swarm satellites was considered, and the
effective area-to-mass ratio of the satellite in each scenario. The ratio was calculated using the external
dimensions of the satellite and deployed arrays. The satellites will be deployed from the P-POD with a
spring and will separate from one another with ​separation springs in the feet.

Drag area from deployed antennas (2x ​446mm whip antennas) was neglected; as such, the effective
area-to-mass calculated below is a conservative case.

              Table 1 - Area-to-Mass Ratio of Swarm Satellites in Various Mission Scenarios
 Scenario                   Description                                 Effective Area-to-Mass (m​2​/kg)

 Operational, Nominal           ●   Satellite maintains +Z axis nadir                      0.025183​* (max)
                                ●   Satellite maintains position                            0.010838*​ (min)
                                    around Z axis as planned for


                                    mission operations                     *Assumes 100% maximum area

 ADCS Nonfunctional             ●   Satellite tumbles randomly                                 0.025183​* (max)
                                                                                                0.010838*​ (min)

                                                                           * Assumes 100% maximum area


Table 2 shows the simulated orbital dwell time for a Swarm satellite for the range of possible orbits, in
each of the identified mission scenarios. In all mission scenarios and orbits, the dwell time of the
satellite was simulated us​ing DAS 2.1.2 software to be less than 10 years.

         Table 2 – Orbit Dwell Time for Swarm Satellite in Each Planned Orbit and Mission Scenario


                                                         Orbital Lifetime (years)

 Case                                                            Nominal

 Launch                                                  September 2018 SSO-A
                                                               (3 Satellites)

 Orbit                                                    575 km x 575 km SSO

 Scenario                  Effective
                           Area-to-Mass
                           (m​2​/kg)

 Operational, Nominal        0.010838​ (min)                                        9.248460

                             0.025183​ (max)                                        5.311431

 ADCS Nonfunctional          0.010838​ (min)                                        9.248460

                             0.025183​ (max)                                        5.311431


Identification of Systems Required for Post-mission Disposal:​ None

Plan for Spacecraft Maneuvers required for Post-mission Disposal:​ N/A

Calculation of final Area-to-Mass Ratio if Atmospheric Reentry Not Selected:​ N/A


 Assessment of Spacecraft Compliance with Requirements 4.6-1 through
 4.6-4:

 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:                            N/A

 4.6-4, Reliability of post-mission disposal operations:                              COMPLIANT




ODAR Section 7: Assessment of Spacecraft Reentry Hazards
Detailed description of spacecraft components by size, mass, material, shape, and original
location on the space vehicle:
A system-level mass breakdown and primary materials list included in the generic satellite bus is available
in the table below:



 Subsystem         Materials                Quantity       Mass (grams)   Shape       Size (mm)

 Solar Panels         Copper, Glass             2                1           Box         79 x 50 x 0.3

 Main Board                 FR4                 2               48           Box         98 x 98 x 1.6
 PCB

 Primary                  Al 6061               1              128           Box       100 x 100 x 100
 Structure

 Battery                   Li-Ion               1              48.5        Cylinder      18 (r) x 67 (l)


Summary of objects expected to survive an uncontrolled ree​ntry (using DAS 2.1.2 software):​ ​None
Calculation of probability of human casualty for expected reentry year and inclination:​ 0%



 Assessment of spacecraft compliance with Requirement 4.7-1:

 4.7-1, Casualty Risk from Reentry Debris:                                            COMPLIANT


A DAS 2.1.2 log demonstrating the compliance to Requirement 4.7-1 is available in Appendix A – “DAS
2.1.2 Log”.




ODAR Section 7A: Assessment of Spacecraft Hazardous
Materials
Summary of Hazardous Materials Contained on Spacecraft: ​None


ODAR Section 8: Assessment for Tether Missions
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 post-mission disposal: ​N/A
Probability of tether colliding with large space objects:​ N/A
Probability of tether being severed during mission or after post-mission disposal:​ N/A
Maximum orbital lifetime of a severed tether fragment:​ N/A


 Assessment of compliance with Requirement 4.8-1:

 4.8-1, Collision Hazards of Space Tethers:                                          N/A




ODAR Section 9: Orbital Tracking Methodology
Each of the satellites is a standard 1U CubeSat in size (10 cm x 10 cm x 10 cm), and can be tracked by
normal means with the Space Surveillance network.

Further, each of our satellites has an onboard GPS receiver, and the GPS location of each of our
satellites is transmitted every time that the satellite is interrogated from the ground. We will have the
ability to silence all RF transmission of the satellite by command from the ground. Our GPS data, and
computed TLEs, will be provided to JSpOC, and any other entity that wishes to receive the live telemetry.
The GPS device will provide telemetry for the hardware lifetime of the satellite, which exceeds the
anticipated orbital lifetime of the satellite.


Appendix A: DAS 2.1.2 Log
05 12 2018; 21:12:24PM Activity Log Started
05 12 2018; 21:14:56PM Mission Editor Changes Applied
05 12 2018; 21:19:21PM Processing Requirement 4.3-1: Return Status : Passed

==============
Project Data
==============
         Objects Passing Through LEO = True
         Number of Objects = 4

**INPUT**
       Quantity = 1
       Final Area-To-Mass Ratio = 0.025183 (m^2/kg)
       Perigee Altitude = 575.000000 (km)
       Apogee Altitude = 575.000000 (km)
       Inclination = 97.000000 (deg)
       RAAN = -1.000000 (deg)


       Argument of Perigee = -1.000000 (deg)
       Mean Anomaly = -1.000000 (deg)
       Released Year = 2018.000000 (yr)

**OUTPUT**
      Perigee Altitude = -6378.136000 (km)
      Apogee Altitude = -6378.136000 (km)
      Inclination = 0.000000 (deg)
      Lifetime = 5.293493 (yr)
      Object Reentered within 25 years of Release = True
      Object-Time = 5.256674 (obj-yrs)
      Total Object-Time = 26.940452 (obj-yrs)
      Status = Pass
       Returned Error Message - Normal Processing

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

**INPUT**
       Quantity = 1
       Final Area-To-Mass Ratio = 0.015154 (m^2/kg)
       Perigee Altitude = 575.000000 (km)
       Apogee Altitude = 575.000000 (km)
       Inclination = 97.000000 (deg)
       RAAN = -1.000000 (deg)
       Argument of Perigee = -1.000000 (deg)
       Mean Anomaly = -1.000000 (deg)
       Released Year = 2018.000000 (yr)

**OUTPUT**
      Perigee Altitude = -6378.136000 (km)
      Apogee Altitude = -6378.136000 (km)
      Inclination = 0.000000 (deg)
      Lifetime = 6.565915 (yr)
      Object Reentered within 25 years of Release = True
      Object-Time = 6.529774 (obj-yrs)
      Total Object-Time = 26.940452 (obj-yrs)
      Status = Pass
       Returned Error Message - Normal Processing

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

**INPUT**
       Quantity = 1
       Final Area-To-Mass Ratio = 0.010838 (m^2/kg)
       Perigee Altitude = 575.000000 (km)
       Apogee Altitude = 575.000000 (km)
       Inclination = 97.000000 (deg)
       RAAN = -1.000000 (deg)
       Argument of Perigee = -1.000000 (deg)
       Mean Anomaly = -1.000000 (deg)


       Released Year = 2018.000000 (yr)

**OUTPUT**
      Perigee Altitude = -6378.136000 (km)
      Apogee Altitude = -6378.136000 (km)
      Inclination = 0.000000 (deg)
      Lifetime = 9.318151 (yr)
      Object Reentered within 25 years of Release = True
      Object-Time = 9.281314 (obj-yrs)
      Total Object-Time = 26.940452 (obj-yrs)
      Status = Pass
       Returned Error Message - Normal Processing

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

**INPUT**
       Quantity = 1
       Final Area-To-Mass Ratio = 0.018921 (m^2/kg)
       Perigee Altitude = 575.000000 (km)
       Apogee Altitude = 575.000000 (km)
       Inclination = 97.000000 (deg)
       RAAN = -1.000000 (deg)
       Argument of Perigee = -1.000000 (deg)
       Mean Anomaly = -1.000000 (deg)
       Released Year = 2018.000000 (yr)

**OUTPUT**
      Perigee Altitude = -6378.136000 (km)
      Apogee Altitude = -6378.136000 (km)
      Inclination = 0.000000 (deg)
      Lifetime = 5.899658 (yr)
      Object Reentered within 25 years of Release = True
      Object-Time = 5.872690 (obj-yrs)
      Total Object-Time = 26.940452 (obj-yrs)
      Status = Pass
       Returned Error Message - Normal Processing

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

=============== End of Requirement 4.3-1 ===============
05 12 2018; 21:19:24PM Processing Requirement 4.3-2: Return Status : Passed

=====================
No Project Data Available
=====================

=============== End of Requirement 4.3-2 ===============
05 12 2018; 21:19:26PM Requirement 4.4-3: Compliant

=============== End of Requirement 4.4-3 ===============


05 12 2018; 21:59:43PM Processing Requirement 4.5-1:   Return Status : Passed

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

**INPUT**

       Space Structure Name = spaceBEE-9
       Space Structure Type = Payload
       Perigee Altitude = 575.000000 (km)
       Apogee Altitude = 575.000000 (km)
       Inclination = 97.000000 (deg)
       RAAN = 0.000000 (deg)
       Argument of Perigee = 0.000000 (deg)
       Mean Anomaly = 0.000000 (deg)
       Final Area-To-Mass Ratio = 0.025183 (m^2/kg)
       Start Year = 2018.000000 (yr)
       Initial Mass = 0.397100 (kg)
       Final Mass = 0.397100 (kg)
       Duration = 10.000000 (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 = 0.000000
       Returned Error Message: Normal Processing
       Date Range Error Message: Normal Date Range
       Status = Pass

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

**INPUT**

       Space Structure Name = spaceBEE-10
       Space Structure Type = Payload
       Perigee Altitude = 575.000000 (km)
       Apogee Altitude = 575.000000 (km)
       Inclination = 97.000000 (deg)
       RAAN = 0.000000 (deg)
       Argument of Perigee = 0.000000 (deg)
       Mean Anomaly = 0.000000 (deg)
       Final Area-To-Mass Ratio = 0.015154 (m^2/kg)


       Start Year = 2018.000000 (yr)
       Initial Mass = 0.660000 (kg)
       Final Mass = 0.660000 (kg)
       Duration = 10.000000 (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 = 0.000000
       Returned Error Message: Normal Processing
       Date Range Error Message: Normal Date Range
       Status = Pass

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

**INPUT**

       Space Structure Name = spaceBEE-11
       Space Structure Type = Payload
       Perigee Altitude = 575.000000 (km)
       Apogee Altitude = 575.000000 (km)
       Inclination = 97.000000 (deg)
       RAAN = 0.000000 (deg)
       Argument of Perigee = 0.000000 (deg)
       Mean Anomaly = 0.000000 (deg)
       Final Area-To-Mass Ratio = 0.010838 (m^2/kg)
       Start Year = 2018.000000 (yr)
       Initial Mass = 0.923000 (kg)
       Final Mass = 0.923000 (kg)
       Duration = 10.000000 (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 = 0.000000
       Returned Error Message: Normal Processing


       Date Range Error Message: Normal Date Range
       Status = Pass

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

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

05 12 2018; 22:01:29PM Requirement 4.5-2: Compliant
05 12 2018; 22:01:30PM Processing Requirement 4.6      Return Status : Passed

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

**INPUT**

       Space Structure Name = spaceBEE-9
       Space Structure Type = Payload

       Perigee Altitude = 575.000000 (km)
       Apogee Altitude = 575.000000 (km)
       Inclination = 97.000000 (deg)
       RAAN = 0.000000 (deg)
       Argument of Perigee = 0.000000 (deg)
       Mean Anomaly = 0.000000 (deg)
       Area-To-Mass Ratio = 0.025183 (m^2/kg)
       Start Year = 2018.000000 (yr)
       Initial Mass = 0.397100 (kg)
       Final Mass = 0.397100 (kg)
       Duration = 10.000000 (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**

       Suggested Perigee Altitude = 575.000000 (km)
       Suggested Apogee Altitude = 575.000000 (km)
       Returned Error Message = Reentry during mission (no PMD req.).

       Released Year = 2023 (yr)
       Requirement = 61
       Compliance Status = Pass

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


**INPUT**

       Space Structure Name = spaceBEE-10
       Space Structure Type = Payload

       Perigee Altitude = 575.000000 (km)
       Apogee Altitude = 575.000000 (km)
       Inclination = 97.000000 (deg)
       RAAN = 0.000000 (deg)
       Argument of Perigee = 0.000000 (deg)
       Mean Anomaly = 0.000000 (deg)
       Area-To-Mass Ratio = 0.015154 (m^2/kg)
       Start Year = 2018.000000 (yr)
       Initial Mass = 0.660000 (kg)
       Final Mass = 0.660000 (kg)
       Duration = 10.000000 (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**

       Suggested Perigee Altitude = 575.000000 (km)
       Suggested Apogee Altitude = 575.000000 (km)
       Returned Error Message = Reentry during mission (no PMD req.).

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

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

**INPUT**

       Space Structure Name = spaceBEE-11
       Space Structure Type = Payload

       Perigee Altitude = 575.000000 (km)
       Apogee Altitude = 575.000000 (km)
       Inclination = 97.000000 (deg)
       RAAN = 0.000000 (deg)
       Argument of Perigee = 0.000000 (deg)
       Mean Anomaly = 0.000000 (deg)
       Area-To-Mass Ratio = 0.010838 (m^2/kg)


        Start Year = 2018.000000 (yr)
        Initial Mass = 0.923000 (kg)
        Final Mass = 0.923000 (kg)
        Duration = 10.000000 (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**

        Suggested Perigee Altitude = 575.000000 (km)
        Suggested Apogee Altitude = 575.000000 (km)
        Returned Error Message = Reentry during mission (no PMD req.).

        Released Year = 2027 (yr)
        Requirement = 61
        Compliance Status = Pass

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

=============== End of Requirement 4.6 ===============
05 12 2018; 22:03:37PM *********Processing Requirement 4.7-1
        Return Status : Passed

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

name = spaceBEE-9
quantity = 1
parent = 0
materialID = 5
type = Box
Aero Mass = 0.397100
Thermal Mass = 0.397100
Diameter/Width = 0.100000
Length = 0.100000
Height = 0.100000

name = Battery Pack
quantity = 1
parent = 1
materialID = 5
type = Cylinder
Aero Mass = 0.380760
Thermal Mass = 0.048500


Diameter/Width = 0.039000
Length = 0.670000

name = Primary Structure
quantity = 1
parent = 2
materialID = 5
type = Box
Aero Mass = 0.332260
Thermal Mass = 0.320000
Diameter/Width = 0.100000
Length = 0.100000
Height = 0.100000

name = Subsystem PCB
quantity = 2
parent = 3
materialID = 76
type = Box
Aero Mass = 0.006130
Thermal Mass = 0.005130
Diameter/Width = 0.980000
Length = 0.980000
Height = 0.001600

name = Solar Panels
quantity = 2
parent = 4
materialID = 23
type = Box
Aero Mass = 0.001000
Thermal Mass = 0.001000
Diameter/Width = 0.050000
Length = 0.079000
Height = 0.000300

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

name = spaceBEE-9
Demise Altitude = 77.998184
Debris Casualty Area = 0.000000
Impact Kinetic Energy = 0.000000

*************************************
name = Battery Pack
Demise Altitude = 77.483612
Debris Casualty Area = 0.000000
Impact Kinetic Energy = 0.000000


*************************************
name = Primary Structure
Demise Altitude = 69.740013
Debris Casualty Area = 0.000000
Impact Kinetic Energy = 0.000000

*************************************
name = Subsystem PCB
Demise Altitude = 69.740013
Debris Casualty Area = 0.000000
Impact Kinetic Energy = 0.000000

*************************************
name = Solar Panels
Demise Altitude = 69.639374
Debris Casualty Area = 0.000000
Impact Kinetic Energy = 0.000000

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

***********INPUT****
 Item Number = 2

name = spaceBEE-10
quantity = 1
parent = 0
materialID = 5
type = Box
Aero Mass = 0.660000
Thermal Mass = 0.660000
Diameter/Width = 0.100000
Length = 0.100000
Height = 0.100000

name = s
quantity = 1
parent = 1
materialID = 5
type = Box
Aero Mass = 0.660000
Thermal Mass = 0.660000
Diameter/Width = 0.100000
Length = 0.100000
Height = 0.100000

**************OUTPUT****
Item Number = 2

name = spaceBEE-10
Demise Altitude = 77.997765


Debris Casualty Area = 0.000000
Impact Kinetic Energy = 0.000000

*************************************
name = s
Demise Altitude = 68.818443
Debris Casualty Area = 0.000000
Impact Kinetic Energy = 0.000000

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

***********INPUT****
 Item Number = 3

name = spaceBEE-11
quantity = 1
parent = 0
materialID = 5
type = Box
Aero Mass = 0.923000
Thermal Mass = 0.923000
Diameter/Width = 0.100000
Length = 0.100000
Height = 0.100000

name = s
quantity = 1
parent = 1
materialID = 5
type = Box
Aero Mass = 0.923000
Thermal Mass = 0.923000
Diameter/Width = 0.100000
Length = 0.100000
Height = 0.100000

**************OUTPUT****
Item Number = 3

name = spaceBEE-11
Demise Altitude = 77.998993
Debris Casualty Area = 0.000000
Impact Kinetic Energy = 0.000000

*************************************
name = s
Demise Altitude = 67.556015
Debris Casualty Area = 0.000000
Impact Kinetic Energy = 0.000000


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

***********INPUT****
 Item Number = 4

name = spaceBEE-9-debris
quantity = 1
parent = 0
materialID = 5
type = Box
Aero Mass = 0.397100
Thermal Mass = 0.397100
Diameter/Width = 0.100000
Length = 0.100000
Height = 0.100000

name = s
quantity = 1
parent = 1
materialID = 5
type = Box
Aero Mass = 0.397100
Thermal Mass = 0.397100
Diameter/Width = 0.100000
Length = 0.100000
Height = 0.100000

**************OUTPUT****
Item Number = 4

name = spaceBEE-9-debris
Demise Altitude = 77.990471
Debris Casualty Area = 0.000000
Impact Kinetic Energy = 0.000000

*************************************
name = s
Demise Altitude = 70.143852
Debris Casualty Area = 0.000000
Impact Kinetic Energy = 0.000000

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

***********INPUT****
 Item Number = 5

name = spaceBEE-10-debris
quantity = 1
parent = 0
materialID = 5


type = Box
Aero Mass = 0.660000
Thermal Mass = 0.660000
Diameter/Width = 0.100000
Length = 0.100000
Height = 0.100000

name = s
quantity = 1
parent = 1
materialID = 5
type = Box
Aero Mass = 0.660000
Thermal Mass = 0.660000
Diameter/Width = 0.100000
Length = 0.100000
Height = 0.100000

**************OUTPUT****
Item Number = 5

name = spaceBEE-10-debris
Demise Altitude = 77.997765
Debris Casualty Area = 0.000000
Impact Kinetic Energy = 0.000000

*************************************
name = s
Demise Altitude = 68.818443
Debris Casualty Area = 0.000000
Impact Kinetic Energy = 0.000000

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

***********INPUT****
 Item Number = 6

name = spaceBEE-11-debris
quantity = 1
parent = 0
materialID = 5
type = Box
Aero Mass = 0.923000
Thermal Mass = 0.923000
Diameter/Width = 0.100000
Length = 0.100000
Height = 0.100000

name = s
quantity = 1


parent = 1
materialID = 5
type = Box
Aero Mass = 0.923000
Thermal Mass = 0.923000
Diameter/Width = 0.100000
Length = 0.100000
Height = 0.100000

**************OUTPUT****
Item Number = 6

name = spaceBEE-11-debris
Demise Altitude = 77.998993
Debris Casualty Area = 0.000000
Impact Kinetic Energy = 0.000000

*************************************
name = s
Demise Altitude = 67.556015
Debris Casualty Area = 0.000000
Impact Kinetic Energy = 0.000000

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

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


Appendix B: Swarm Satellites Orbit Lifetime

05 12 2018; 22:23:45PM Science and Engineering - Orbit Lifetime/Dwell Time

**INPUT**

         Start Year = 2018.000000 (yr)
         Perigee Altitude = 575.000000 (km)
         Apogee Altitude = 575.000000 (km)
         Inclination = 0.000000 (deg)
         RAAN = 0.000000 (deg)
         Argument of Perigee = 0.000000 (deg)
         Area-To-Mass Ratio = 0.025183 (m^2/kg)

**OUTPUT**

        Orbital Lifetime from Startyr = 5.311431 (yr)
        Time Spent in LEO during Lifetime = 5.311431 (yr)
        Last year of Propagation = 2023 (yr)
        Returned Error Message: Object reentered
05 12 2018; 22:24:09PM Science and Engineering - Orbit Lifetime/Dwell Time


**INPUT**

       Start Year = 2018.000000 (yr)
       Perigee Altitude = 575.000000 (km)
       Apogee Altitude = 575.000000 (km)
       Inclination = 0.000000 (deg)
       RAAN = 0.000000 (deg)
       Argument of Perigee = 0.000000 (deg)
       Area-To-Mass Ratio = 0.010838 (m^2/kg)

**OUTPUT**

       Orbital Lifetime from Startyr = 9.248460 (yr)
       Time Spent in LEO during Lifetime = 9.248460 (yr)
       Last year of Propagation = 2027 (yr)
       Returned Error Message: Object reentered



Document Created: 2019-02-19 15:58:08
Document Modified: 2019-02-19 15:58:08

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