Exhibits A through C

1140-EX-ST-2018 Text Documents

Swarm Technologies, Inc.

2018-07-06ELS_212398

Swarm Technologies
STA File Number: 1140-EX-ST-2018
Exhibit A

will occur approximately four times per day. Each transmission will require
approximately two seconds.

Grant of the STA poses no concerns for interference. Space-to-ground
transmissions under the proposed STA will be de minimis in nature and involve only the
two ground stations identified above. Moreover, Orbcomm, the sole incumbent operator,
previously approved Swarm’s dismissed 0.25U STA request, File Number 0305-EX-CN-
2017, and SpaceBEE satellites will not transmit co-channel with Orbcomm operations.
Swarm appreciates that STA operations must occur on a sufferance-only, non-
interference basis. Swarm will immediately mute transmissions in the unlikely event of
interference.

5.0 – Orbital Parameters

All four SpaceBEE satellites currently orbit at approximately 500 km with 97.5
degrees of inclination. Due to launch vehicle operator adjustments these parameters
deviate slightly from those submitted in File Number 0305-EX-CN-2017, which
contemplated a 580 km altitude with 97.7 degrees of inclination.

Detailed information on the orbital parameters of the SpaceBEE satellites are
provided below and in Exhibit B.

SPACEBEE-1 SPACEBEE-2 SPACEBEE-3 SPACEBEE-4

NORAD ID 43142 43141 43140 43139

International Code 2018-004AH 2018-004AG 2018-004AF 2018-004AE

Perigee 494.8 km 495.0 km 495.1 km 495.6 km

Apogee 509.9 km 510.1 km 510.3 km 510.8 km

Inclination 97.5 ° 97.5 ° 97.5 ° 97.5 °

.

2

EXHIBIT B
ORBITAL DEBRIS ASSESSMENT REPORT
STA File Number: 1140-EX-ST-2018

Operations
The operational phase of the satellite begins following the successful
deployment of the Swarm satellites from the launch vehicle, and successful
checkout. The operational phase continues until the end of the market study.

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 within 5 years following deployment from
the launch vehicle, as detailed in Appendix B: Swarm BEEs 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 Sectio
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 1.2714 kg (all four satellites), (individually: 0.2835, 0.2977, 0.3131, 0.3771
kg)

Dry Mass at Launch 1.2714 kg (all four satellites)

Form Factor 1/4U satellites, Qty 4 stacked into form-factor of a 1U CubeSat

COG < 0.170 cm in vertical direction from geometric center

Envelope (stowed) 100mm x 100mm x 113.5mm (all four satellites)

Envelope (deployed) 100mm x 100mm x 113.5mm (all four satellites)
Deployed dipole antenna tip to tip is 892 mm

Propulsion Systems None

Fluid Systems None

AOCS Passive stabilization about two axis, 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 BEE 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 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 10 cm 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 BEEs 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 1/4U 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 (m2/kg)

Operational, Nominal ● Satellite maintains +Z axis nadir 0.01411 (max)
● Satellite maintains position 0.01061 (min)
around Z axis as planned for
mission operations

ADCS Nonfunctional ● Satellite tumbles randomly 0.01411 (max)
0.01061 (min)

Table 2 shows the simulated orbital dwell time for a Swarm BEE 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 using DAS 2.1.2 software to be less than 10 years.

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

Case Apogee Altitude Perigee Altitude Orbital Lifetime
(km) (km) (years)

Launch

Orbit (Launch Jan.
11, 2018, 9:30 LTDN)

Satellite Area-to-Mass
(m2/kg)

SPACEBEE-1 0.01411 509.9 494.8 4.490

SPACEBEE-2 0.01344 510.1 495.0 4.556

SPACEBEE-3 0.01278 510.3 495.1 4.621

SPACEBEE-4 0.01061 510.8 495.6 4.901

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 (cm)

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 32 Box 100 x 100 x 27
Structure

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

Summary of objects expected to survive an uncontrolled reentry (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
[update: All four SPACEBEE satellite have been trackable by the Space Surveillance Network (SSN) by
normal means. No gaps in tracking have occurred, and the satellites are currently being tracked, and the
TLE orbital data is being posted publicly to the SSN database.]

In consideration of the small satellite form factor, the satellites employ a radar return enhancement
technology to ensure passive ground tracking capability by third party tracking services. Each of our
satellites is a ¼-U size, or 100 mm x 100 mm x 28 mm, and is composed of an aluminum frame, and 6
PCBs on each face. Each 100 mm x 100 mm face PCB has a built-in ground plane and solar cells, which
provide the same radar return as a 1U satellite, or a 3U satellite end-on. Each 100 mm x 28 mm face is
composed of a passive Ku-band radar reflector, specifically designed to be used to passively increase the
radar cross section of small satellites for enhanced tracking. Each 100 mm x 28 mm face has an
equivalent radar return signature of a 100 mm x 280 mm area (or 10x larger than it’s actual area), in effect
providing a radar signature equivalent of a 3U satellite, side-on. The passive radar retroreflector was
designed for the Haystack Auxiliary RADAR (HAX) operated by MIT Lincoln Labs, which has the following
capabilities:
Peak Power: 50 Kilowatts
Center frequency: 16.7 GHz (Ku Band)
Bandwidth: 2 GHz
Antenna Diameter: 12.2 meters
Antenna Gain (at 16.7 GHz): 63.6 dB
Antenna Beamwidth: 0.10 degrees
Polarization: Right Hand Circular
Pulse Length: 1.64 milliseconds
Pulse Repetition Frequency: 60 Hz

The radar retroreflectors were developed by Terry Albert at SPAWAR. Albert, Terry R CIV
SPAWARSYSCEN-PACIFIC, 56290 <terry.albert@navy.mil>

The HAX Radar, which is part of the NORAD system, operated by the Joint Space Operations Center (JSpOC),
he radar reflectors will improve the RADAR return from the smallsat, and thereby
will track our satellites. T
improve the ability to detect and track it. HAX can track the satellite any time the smallsat flies over it, and
JSpOC calculates the TLEs from the RADAR returns. Any other radar unit in the Ku-band (14.7 GHz to 18.7
GHz) would similarly be able to track our satellites, and would see a signature that is the equivalent to a
3U satellite.

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
Below is the log of the DAS 2.1.2 simulation performed to demonstrate compliance to the above requirements.

04 20 2017; 15:03:17PM Activity Log Started
04 20 2017; 15:03:17PM New Project Files Created
04 20 2017; 15:04:46PM Mission Editor Changes Applied
04 20 2017; 15:04:50PM Project Data Saved To File

04 21 2017; 22:16:49PM Science and Engineering - Orbit Lifetime/Dwell Time

**INPUT**

Start Year = 2017.000000 (yr)
Perigee Altitude = 600.000000 (km)
Apogee Altitude = 600.000000 (km)
Inclination = 97.792400 (deg)
RAAN = 316.647000 (deg)
Argument of Perigee = 0.000000 (deg)
Area-To-Mass Ratio = 0.035000 (m^2/kg)

**OUTPUT**

Orbital Lifetime from Startyr = 6.269678 (yr)
Time Spent in LEO during Lifetime = 6.269678 (yr)
Last year of Propagation = 2023 (yr)
Returned Error Message: Object reentered
04 21 2017; 22:17:01PM Science and Engineering - Orbit Lifetime/Dwell Time

**INPUT**

Start Year = 2017.000000 (yr)
Perigee Altitude = 600.000000 (km)
Apogee Altitude = 600.000000 (km)
Inclination = 97.792400 (deg)
RAAN = 316.647000 (deg)
Argument of Perigee = 0.000000 (deg)
Area-To-Mass Ratio = 0.015400 (m^2/kg)

**OUTPUT**

Orbital Lifetime from Startyr = 9.872690 (yr)
Time Spent in LEO during Lifetime = 9.872690 (yr)
Last year of Propagation = 2026 (yr)
Returned Error Message: Object reentered
04 21 2017; 22:23:05PM Science and Engineering - Orbit Lifetime/Dwell Time

**INPUT**

Start Year = 2017.000000 (yr)
Perigee Altitude = 600.000000 (km)
Apogee Altitude = 600.000000 (km)
Inclination = 97.792400 (deg)
RAAN = 316.647000 (deg)
Argument of Perigee = 0.000000 (deg)
Area-To-Mass Ratio = 0.015400 (m^2/kg)

**OUTPUT**

Orbital Lifetime from Startyr = 9.872690 (yr)
Time Spent in LEO during Lifetime = 9.872690 (yr)
Last year of Propagation = 2026 (yr)
Returned Error Message: Object reentered
04 21 2017; 22:23:21PM Science and Engineering - Orbit Lifetime/Dwell Time

**INPUT**

Start Year = 2017.000000 (yr)
Perigee Altitude = 600.000000 (km)
Apogee Altitude = 600.000000 (km)
Inclination = 97.792400 (deg)
RAAN = 316.647000 (deg)
Argument of Perigee = 0.000000 (deg)
Area-To-Mass Ratio = 0.035000 (m^2/kg)

**OUTPUT**

Orbital Lifetime from Startyr = 6.269678 (yr)
Time Spent in LEO during Lifetime = 6.269678 (yr)
Last year of Propagation = 2023 (yr)
Returned Error Message: Object reentered
04 21 2017; 22:23:48PM Science and Engineering - Orbit Lifetime/Dwell Time

**INPUT**

Start Year = 2017.000000 (yr)
Perigee Altitude = 580.000000 (km)
Apogee Altitude = 580.000000 (km)
Inclination = 97.700000 (deg)
RAAN = 316.647000 (deg)
Argument of Perigee = 0.000000 (deg)
Area-To-Mass Ratio = 0.035000 (m^2/kg)

**OUTPUT**

Orbital Lifetime from Startyr = 5.798768 (yr)
Time Spent in LEO during Lifetime = 5.798768 (yr)
Last year of Propagation = 2022 (yr)

Returned Error Message: Object reentered
04 21 2017; 22:24:08PM Science and Engineering - Orbit Lifetime/Dwell Time

**INPUT**

Start Year = 2017.000000 (yr)
Perigee Altitude = 580.000000 (km)
Apogee Altitude = 580.000000 (km)
Inclination = 97.700000 (deg)
RAAN = 316.647000 (deg)
Argument of Perigee = 0.000000 (deg)
Area-To-Mass Ratio = 0.015400 (m^2/kg)

**OUTPUT**

Orbital Lifetime from Startyr = 7.676934 (yr)
Time Spent in LEO during Lifetime = 7.676934 (yr)
Last year of Propagation = 2024 (yr)
Returned Error Message: Object reentered
04 21 2017; 22:24:41PM Science and Engineering - Orbit Lifetime/Dwell Time

**INPUT**

Start Year = 2017.000000 (yr)
Perigee Altitude = 500.000000 (km)
Apogee Altitude = 500.000000 (km)
Inclination = 97.400000 (deg)
RAAN = 316.647000 (deg)
Argument of Perigee = 0.000000 (deg)
Area-To-Mass Ratio = 0.015400 (m^2/kg)

**OUTPUT**

Orbital Lifetime from Startyr = 5.229295 (yr)
Time Spent in LEO during Lifetime = 5.229295 (yr)
Last year of Propagation = 2022 (yr)
Returned Error Message: Object reentered
04 21 2017; 22:24:54PM Science and Engineering - Orbit Lifetime/Dwell Time

**INPUT**

Start Year = 2017.000000 (yr)
Perigee Altitude = 500.000000 (km)
Apogee Altitude = 500.000000 (km)
Inclination = 97.400000 (deg)
RAAN = 316.647000 (deg)
Argument of Perigee = 0.000000 (deg)
Area-To-Mass Ratio = 0.035000 (m^2/kg)

**OUTPUT**

Orbital Lifetime from Startyr = 4.380561 (yr)
Time Spent in LEO during Lifetime = 4.380561 (yr)
Last year of Propagation = 2021 (yr)
Returned Error Message: Object reentered

04 24 2017; 14:19:28PM Processing Requirement 4.3-1: Return Status : Passed

==============
Project Data
==============
Objects Passing Through LEO = True
Number of Objects = 1

**INPUT**
Quantity = 4
Final Area-To-Mass Ratio = 0.035000 (m^2/kg)
Perigee Altitude = 580.000000 (km)
Apogee Altitude = 580.000000 (km)
Inclination = 97.600000 (deg)
RAAN = -1.000000 (deg)
Argument of Perigee = -1.000000 (deg)
Mean Anomaly = -1.000000 (deg)
Released Year = 2017.000000 (yr)

**OUTPUT**
Perigee Altitude = -6378.136000 (km)
Apogee Altitude = -6378.136000 (km)
Inclination = 0.000000 (deg)
Lifetime = 5.807192 (yr)
Object Reentered within 25 years of Release = True
Object-Time = 23.162218 (obj-yrs)
Total Object-Time = 23.162218 (obj-yrs)
Status = Pass
Returned Error Message - Normal Processing

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

=============== End of Requirement 4.3-1 ===============

04 24 2017; 11:28:14AM Processing Requirement 4.3-2: Return Status : Passed

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

=============== End of Requirement 4.3-2 ===============
04 24 2017; 11:28:22AM Requirement 4.4-3: Compliant

=============== End of Requirement 4.4-3 ===============
04 24 2017; 11:28:23AM Requirement 4.4-3: Compliant

=============== End of Requirement 4.4-3 ===============
04 24 2017; 11:40:35AM Processing Requirement 4.5-1: Return Status : Passed

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

**INPUT**

Space Structure Name = SwarmBEE
Space Structure Type = Payload
Perigee Altitude = 580.000000 (km)
Apogee Altitude = 580.000000 (km)
Inclination = 97.600000 (deg)
RAAN = 0.000000 (deg)
Argument of Perigee = 0.000000 (deg)
Mean Anomaly = 0.000000 (deg)
Final Area-To-Mass Ratio = 0.035000 (m^2/kg)
Start Year = 2017.000000 (yr)
Initial Mass = 0.183100 (kg)
Final Mass = 0.183100 (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 = 0.000000
Returned Error Message: Normal Processing
Date Range Error Message: Normal Date Range
Status = Pass

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

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

04 21 2017; 15:50:26PM Requirement 4.5-2: Compliant

04 21 2017; 15:53:04PM Processing Requirement 4.6 Return Status : Passed

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

**INPUT**

Space Structure Name = SwarmBEE
Space Structure Type = Payload

Perigee Altitude = 580.000000 (km)
Apogee Altitude = 580.000000 (km)
Inclination = 97.600000 (deg)
RAAN = 0.000000 (deg)
Argument of Perigee = 0.000000 (deg)
Mean Anomaly = 0.000000 (deg)
Area-To-Mass Ratio = 0.004150 (m^2/kg)
Start Year = 2017.000000 (yr)
Initial Mass = 0.156400 (kg)
Final Mass = 0.156400 (kg)
Duration = 5.000000 (yr)
Station Kept = False
Abandoned = True
PMD Perigee Altitude = 576.060384 (km)
PMD Apogee Altitude = 576.060384 (km)
PMD Inclination = 97.748927 (deg)
PMD RAAN = 344.718056 (deg)
PMD Argument of Perigee = 8.342328 (deg)
PMD Mean Anomaly = 0.000000 (deg)

**OUTPUT**

Suggested Perigee Altitude = 576.060384 (km)
Suggested Apogee Altitude = 576.060384 (km)
Returned Error Message = Passes LEO reentry orbit criteria.

Released Year = 2045 (yr)
Requirement = 61
Compliance Status = Pass

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

=============== End of Requirement 4.6 ===============
04 25 2017; 12:32:07PM *********Processing Requirement 4.7-1
Return Status : Passed

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

name = SwarmBEE
quantity = 1
parent = 0
materialID = 5
type = Box
Aero Mass = 0.183100
Thermal Mass = 0.183100
Diameter/Width = 0.100000
Length = 0.100000
Height = 0.028300

name = Solar Panels
quantity = 2
parent = 1
materialID = 24
type = Box
Aero Mass = 0.001000
Thermal Mass = 0.001000
Diameter/Width = 0.050000
Length = 0.079000
Height = 0.000300

name = Subsystem PCB
quantity = 2
parent = 1
materialID = 5
type = Box
Aero Mass = 0.041300
Thermal Mass = 0.041300
Diameter/Width = 0.098000
Length = 0.098000
Height = 0.001600

name = Primary Structure
quantity = 1
parent = 1
materialID = 8
type = Box
Aero Mass = 0.032000
Thermal Mass = 0.032000
Diameter/Width = 0.100000
Length = 0.100000
Height = 0.002700

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

Thermal Mass = 0.048500
Diameter/Width = 0.039000
Length = 0.067000

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

name = SwarmBEE
Demise Altitude = 77.988602
Debris Casualty Area = 0.000000
Impact Kinetic Energy = 0.000000

*************************************
name = Solar Panels
Demise Altitude = 77.964577
Debris Casualty Area = 0.000000
Impact Kinetic Energy = 0.000000

*************************************
name = Subsystem PCB
Demise Altitude = 75.182190
Debris Casualty Area = 0.000000
Impact Kinetic Energy = 0.000000

*************************************
name = Primary Structure
Demise Altitude = 76.035942
Debris Casualty Area = 0.000000
Impact Kinetic Energy = 0.000000

*************************************
name = Battery Pack
Demise Altitude = 73.450478
Debris Casualty Area = 0.000000
Impact Kinetic Energy = 0.000000

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

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

name = SwarmBEE2
quantity = 4
parent = 0
materialID = 5
type = Box
Aero Mass = 0.183100
Thermal Mass = 0.183100
Diameter/Width = 0.100000
Length = 0.100000

Height = 0.028300

name = S
quantity = 4
parent = 1
materialID = 5
type = Box
Aero Mass = 0.183100
Thermal Mass = 0.183100
Diameter/Width = 0.100000
Length = 0.100000
Height = 0.028300

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

name = SwarmBEE2
Demise Altitude = 77.988602
Debris Casualty Area = 0.000000
Impact Kinetic Energy = 0.000000

*************************************
name = S
Demise Altitude = 69.932800
Debris Casualty Area = 0.000000
Impact Kinetic Energy = 0.000000

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

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

EXHIBIT C
NTIA SPACE RECORD DATA FORM
STA File Number: 1140-EX-ST-2018

NTIA Space record data form

NTIA requires the following data for space related experiments using government shared spectrum. For
each transmit frequency, please provide the data for both ends of the transmit-receive link. Use Part A
to describe the satellite to ground information. Part B is for all ground to space transmit links.

Part A: Space to Earth Downlink Data

Satellite Transmitter Data

Transmit Frequency:
137.950 MHz
Satellite Name:
SPACEBEE-1, SPACEBEE-2, SPACEBEE-3, SPACEBEE-4
Data Field Data Answer Description/Comments
Polarization (XAP) XAP = V POLARIZATIONS INCLUDE :
H = HORIZONTAL,
V = VERTICAL,
S = HORIZONTAL AND VERTICAL,
L = LEFT HAND CIRCULAR,
R = RIGHT HAND CIRCULAR,
T = RIGHT AND LEFT HAND CIRCULAR,
J = LINEAR POLARIZATION
Orientation (XAZ) XAZ = EC NB= NARROWBEAM
EC = EARTH COVERAGE
Antenna ANTENNA GAIN = 2.14 dBi (NTIA format (XAD), EXAMPLE, XAD01 16G030B)

Dimension (XAD) BEAMWIDTH = Toroidal
HPBW = 90 x 360 degrees.
XAD = XAD01 02G090B
Type of satellite Type = Nongeostationary Choose either:
Geostationary or
(State = SP) State = SP Nongeostationary
(City = geo or City = non
non)

For Geostationary Longitude = IF ANY SATELLITES ARE GEOSTATIONARY, REPORT
ITS LATITUDE AS 000000N (XLA AND/OR RLA) AND
REPORT ITS LONGITUDE (XLG AND/OR RLG).
For INCLINATION ANGLE____97.5_______, IF ANY SATELLITES ARE NONGEOSTATIONARY,
REPORT ITS INCLINATION ANGLE, APOGEE
Nongeostationary APOGEE IN KILOMETERS____500_____, IN KILOMETERS, PERIGEE IN KILOMETERS,
(Orbital Data) PERIGEE IN KILOMETERS_____500____, ORBITAL PERIOD IN HOURS AND FRACTIONS OF
HOURS IN DECIMAL, THE NUMBER OF SATELLITES
ORBITAL PERIOD IN HOURS __1__AND
IN THE SYSTEM, THEN T01, EXAMPLE,
FRACTIONS OF HOURS IN REM04
DECIMAL___0.577___, *ORB,98.0IN00510AP00510PE001.58H01NRT01,
AND FOR SPACE-TO-SPACE
THE NUMBER OF SATELLITES IN THE COMMUNICATIONS WITH ANOTHER
SYSTEM_____4______, NONGEOSTATIONARY SATELLITE ADD AN
ADDITIONAL
*ORB FOR IT ENDING IN R01, EXAMPLE, REM05
ORB = *ORB,72.9IN03209AP00655PE013.46H01NRR01
ORB,097.7IN00580AP00580PE0001.6H04
NNRT01

1

Earth Station Data (Receiver) #1
State (RSC) RSC = CA
City Name (RAL) RAL = Los Altos
Latitude Lat = 37 21 53 N
(DDMMSS)
Longitude Lon = 122 06 39 W
(DDDMMSS)
Antenna RAP = V POLARIZATIONS INCLUDE :
H = HORIZONTAL,
Polarization (RAP) V = VERTICAL,
S = HORIZONTAL AND VERTICAL,
L = LEFT HAND CIRCULAR,
R = RIGHT HAND CIRCULAR,
T = RIGHT AND LEFT HAND CIRCULAR,
J = LINEAR POLARIZATION
Antenna Azimuth RAZ = 0-360 THE EARTH STATION RECEIVER ANTENNA
AZIMUTH (RAZ), THE MINIMUM ANGLE OF
(RAZ) V00 to V90 ELEVATION, V00 TO V90, EXAMPLE, RAZ01 V00
(Azimuth = 0 to 360, Elevation 0 to 90)
Antenna ANTENNA GAIN______2.00________, EXAMPLE ASSUMING NONGEOSTATIONARY,
RAD01 16G030B000-360A00357H006
Dimensions (RAD) BEAMWIDTH_____180________,
AZIMUTHAL RANGE__0 to 360______,
THE SITE ELEVATION ABOVE MEAN SEA
LEVEL IN METERS ___113_______
THE ANTENNA HEIGHT ABOVE TERRAIN
IN METERS ____3__________

RAD = RAD01 02G038B
FCC notes:
1. Use S-Note S945.
2. REM AGN, Cubesat, (insert name)

Earth Station Data (Receiver) #2
State (RSC) RSC = GA
City Name (RAL) RAL = Buford
Latitude Lat = 34 05 05 N
(DDMMSS)
Longitude Lon = 083 56 51 W
(DDDMMSS)
Antenna RAP = V POLARIZATIONS INCLUDE :
H = HORIZONTAL,
Polarization (RAP) V = VERTICAL,
S = HORIZONTAL AND VERTICAL,
L = LEFT HAND CIRCULAR,
R = RIGHT HAND CIRCULAR,
T = RIGHT AND LEFT HAND CIRCULAR,
J = LINEAR POLARIZATION
Antenna Azimuth RAZ = 0-360 THE EARTH STATION RECEIVER ANTENNA
AZIMUTH (RAZ), THE MINIMUM ANGLE OF
(RAZ) V00 to V90 ELEVATION, V00 TO V90, EXAMPLE, RAZ01 V00

2

(Azimuth = 0 to 360, Elevation 0 to 90)
Antenna ANTENNA GAIN______2.00________, EXAMPLE ASSUMING NONGEOSTATIONARY,
RAD01 16G030B000-360A00357H006
Dimensions (RAD) BEAMWIDTH_____180________,
AZIMUTHAL RANGE__0 to 360______,
THE SITE ELEVATION ABOVE MEAN SEA
LEVEL IN METERS ___366_______
THE ANTENNA HEIGHT ABOVE TERRAIN
IN METERS ____3__________

RAD = RAD01 02G038B
FCC notes:
1. Use S-Note S945.
2. REM AGN, Cubesat, (insert name)

3

Part B: Ground Stations, Earth to Space link data:

Earth Station Transmitter Data #1

Transmit Frequency: 137.950 MHz
State (XSC) XSC = CA
City Name (XAL) XAL = Los Altos
Latitude Lat = 37 21 53 N
(DDMMSS)
Longitude Lon = 122 06 39 W
(DDDMMSS)
Antenna XAP = V POLARIZATIONS INCLUDE :
H = HORIZONTAL,
Polarization (XAP) V = VERTICAL,
S = HORIZONTAL AND VERTICAL,
L = LEFT HAND CIRCULAR,
R = RIGHT HAND CIRCULAR,
T = RIGHT AND LEFT HAND CIRCULAR,
J = LINEAR POLARIZATION
Antenna Azimuth XAZ = 0-360 THE EARTH STATION Transmitter ANTENNA
AZIMUTH (XAZ), THE MINIMUM ANGLE OF
(XAZ) V00 to V90 ELEVATION, V00 TO V90, EXAMPLE, XAZ01 V00
(Azimuth = 0 to 360, Elevation 0 to 90)
Antenna ANTENNA GAIN______2.00________, EXAMPLE ASSUMING NONGEOSTATIONARY,
XAD01 16G030B000-360A00357H006
Dimensions (RAD) BEAMWIDTH_____180________,
AZIMUTHAL RANGE__0 to 360______,
THE SITE ELEVATION ABOVE MEAN SEA
LEVEL IN METERS ___113_______
THE ANTENNA HEIGHT ABOVE TERRAIN
IN METERS ____3__________

RAD = RAD01 02G038B
Satellite Receive Specifications

Polarization (RAP) RAP = V POLARIZATIONS INCLUDE :
H = HORIZONTAL,
V = VERTICAL,
S = HORIZONTAL AND VERTICAL,
L = LEFT HAND CIRCULAR,
R = RIGHT HAND CIRCULAR,
T = RIGHT AND LEFT HAND CIRCULAR,
J = LINEAR POLARIZATION
Azimuth (RAZ) RAZ = EC STATION RECEIVER ANTENNA AZIMUTH (XAZ),
THE MINIMUM ANGLE OF
ELEVATION, V00 TO V90, EXAMPLE, RAZ01 V00

Dimension (XAD) ANTENNA GAIN = 2.14 dBi (NTIA format (RAD), EXAMPLE, RAD01 16G030B)

BEAMWIDTH = Toroidal
HPBW = 90 x 360 degrees.
XAD = XAD01 02G090B
Type of satellite Type = Nongeostationary Choose either:
Geostationary or
(State = SP) State = SP Nongeostationary

4

City = G/No City = non
For Geostationary Longitude = IF ANY SATELLITES ARE GEOSTATIONARY, REPORT
ITS LATITUDE AS 000000N (XLA AND/OR RLA) AND
REPORT ITS LONGITUDE (XLG AND/OR RLG).
For INCLINATION ANGLE____97.5_______, IF ANY SATELLITES ARE NONGEOSTATIONARY,
REPORT ITS INCLINATION ANGLE, APOGEE
Nongeostationary APOGEE IN KILOMETERS____500_____, IN KILOMETERS, PERIGEE IN KILOMETERS,
(Orbital Data) PERIGEE IN KILOMETERS_____500____, ORBITAL PERIOD IN HOURS AND FRACTIONS OF
HOURS IN DECIMAL, THE NUMBER OF SATELLITES
ORBITAL PERIOD IN HOURS __1__AND
IN THE SYSTEM, THEN T01, EXAMPLE,
FRACTIONS OF HOURS IN REM04
DECIMAL___0.577___, *ORB,98.0IN00510AP00510PE001.58H01NRT01,
AND FOR SPACE-TO-SPACE
THE NUMBER OF SATELLITES IN THE COMMUNICATIONS WITH ANOTHER
SYSTEM_____4______, NONGEOSTATIONARY SATELLITE ADD AN
ADDITIONAL
*ORB FOR IT ENDING IN R01, EXAMPLE, REM05
ORB = *ORB,72.9IN03209AP00655PE013.46H01NRR01
ORB,097.7IN00580AP00580PE0001.6H04
NNRR01

Earth Station Transmitter Data #2

Transmit Frequency: 137.950 MHz
State (XSC) XSC = GA
City Name (XAL) XAL = Buford
Latitude Lat = 34 05 05 N
(DDMMSS)
Longitude Lon = 083 56 51 W
(DDDMMSS)
Antenna XAP = V POLARIZATIONS INCLUDE :
H = HORIZONTAL,
Polarization (XAP) V = VERTICAL,
S = HORIZONTAL AND VERTICAL,
L = LEFT HAND CIRCULAR,
R = RIGHT HAND CIRCULAR,
T = RIGHT AND LEFT HAND CIRCULAR,
J = LINEAR POLARIZATION
Antenna Azimuth XAZ = 0-360 THE EARTH STATION Transmitter ANTENNA
AZIMUTH (XAZ), THE MINIMUM ANGLE OF
(XAZ) V00 to V90 ELEVATION, V00 TO V90, EXAMPLE, XAZ01 V00
(Azimuth = 0 to 360, Elevation 0 to 90)
Antenna ANTENNA GAIN______2.00________, EXAMPLE ASSUMING NONGEOSTATIONARY,
XAD01 16G030B000-360A00357H006
Dimensions (RAD) BEAMWIDTH_____35________,
AZIMUTHAL RANGE__0 to 360______,
THE SITE ELEVATION ABOVE MEAN SEA
LEVEL IN METERS ___366_______
THE ANTENNA HEIGHT ABOVE TERRAIN
IN METERS ____3__________

RAD = RAD01 02G038B
Satellite Receive Specifications

5

Polarization (RAP) RAP = V POLARIZATIONS INCLUDE :
H = HORIZONTAL,
V = VERTICAL,
S = HORIZONTAL AND VERTICAL,
L = LEFT HAND CIRCULAR,
R = RIGHT HAND CIRCULAR,
T = RIGHT AND LEFT HAND CIRCULAR,
J = LINEAR POLARIZATION
Azimuth (RAZ) RAZ = EC STATION RECEIVER ANTENNA AZIMUTH (XAZ),
THE MINIMUM ANGLE OF
ELEVATION, V00 TO V90, EXAMPLE, RAZ01 V00

Dimension (XAD) ANTENNA GAIN = 2.14 dBi (NTIA format (RAD), EXAMPLE, RAD01 16G030B)

BEAMWIDTH = Toroidal
HPBW = 90 x 360 degrees.
XAD = XAD01 02G090B
Type of satellite Type = Nongeostationary Choose either:
Geostationary or
(State = SP) State = SP Nongeostationary
City = G/No City = non
For Geostationary Longitude = IF ANY SATELLITES ARE GEOSTATIONARY, REPORT
ITS LATITUDE AS 000000N (XLA AND/OR RLA) AND
REPORT ITS LONGITUDE (XLG AND/OR RLG).
For INCLINATION ANGLE____97.5_______, IF ANY SATELLITES ARE NONGEOSTATIONARY,
REPORT ITS INCLINATION ANGLE, APOGEE
Nongeostationary APOGEE IN KILOMETERS____500_____, IN KILOMETERS, PERIGEE IN KILOMETERS,
(Orbital Data) PERIGEE IN KILOMETERS_____500____, ORBITAL PERIOD IN HOURS AND FRACTIONS OF
HOURS IN DECIMAL, THE NUMBER OF SATELLITES
ORBITAL PERIOD IN HOURS __1__AND
IN THE SYSTEM, THEN T01, EXAMPLE,
FRACTIONS OF HOURS IN REM04
DECIMAL___0.577___, *ORB,98.0IN00510AP00510PE001.58H01NRT01,
AND FOR SPACE-TO-SPACE
THE NUMBER OF SATELLITES IN THE COMMUNICATIONS WITH ANOTHER
SYSTEM_____4______, NONGEOSTATIONARY SATELLITE ADD AN
ADDITIONAL
*ORB FOR IT ENDING IN R01, EXAMPLE, REM05
ORB = *ORB,72.9IN03209AP00655PE013.46H01NRR01
ORB,097.7IN00580AP00580PE0001.6H04
NNRR01

6

Document Created: 2018-07-06 15:01:12
Document Modified: 2018-07-06 15:01:12

© 2024 FCC.report
This site is not affiliated with or endorsed by the FCC