Orbital Debris Assessment Report

0171-EX-ML-2015 Text Documents

Spire Global, Inc.

2015-08-24ELS_166339

Revision History

Revision Description of Revisions Release Date
1 (baseline version) 02/10/2015
Updated launch information based on new info from launch providers:
● PSLV expected launch date moved from Q3 2015 to Q4 2015
Added newly-booked launches:
● “TBD” launch updated to “Q4 2015 Atlas-V / Cyngnus” launch
2 ● added Q1 2016 Soyuz launch 04/22/2015

● updated quantity of satellites on Q1 2016 Falcon-9 launch to 10

New DAS log with updated launch information.
Updated orbital decay information by including tensile strength decay of
3 05/23/2015
filaments

Summarized List of Compliance Status to Orbital Debris
Requirements
For convenience, below is a summarized list of the compliance status to orbital debris requirements. Detailed
explanations for each of these compliance statements are available in ODAR Sections 1 through 8.

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

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

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 N/A
about Earth or the Moon:

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

4.4-4, Limiting the short-term risk to other space systems from planned breakups: COMPLIANT

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

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

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

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

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

4.6-4, Reliability of postmission disposal operations: N/A

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

ODAR Section 1: Program Management and Mission Overview
Program / Project Peter Platzer
Manager

Mission Description The purpose of the LEMUR-2 nanosatellite fleet is to provide high-revisit maritime
domain monitoring data, as part of a market trial to test marked demand in this area. The
mission consists of a set of 17 3U Cubesats satellites launched in four separate launch
vehicles launches into various orbital planes, to increase average revisit time globally.
The LEMUR-2 fleet is a continuation of the market trial currently underway with the single
prototype LEMUR-1 satellite.

Foreign None
Government
Involvement

Project Milestones: The project milestones for the LEMUR-2 constellations align with the successive launch
of vehicles into orbit. The table blow contains launch segment information for each
Proposed Launch launch of the constellation.
Date:

Proposed Launch Proposed
Vehicles: Number Launch
Launch Date
Vehicle of Vehicle Launch Site Altitude Inclination
(no earlier
Proposed Launch Satellites Operator
than)
Sites:

Launch Vehicle Antrix / Sriharikota,
Operator: PSLV Q4 2015 4 650 km 6 deg
ISRO India

Orbital Cape
Atlas V Q4 2015 4 500 km 51.6 deg
Sciences Canaveral, FL

Roscosmo Baikonur,
Soyuz Q4 2015 2 600 km 97.8 deg
s Kazakhstan

January JAMSS / Tanegashima,
HII-A 7 575 km 31 deg
2016 JAXA Japan

Falcon- Vandenberg, 450 x
Q1 2016 10 Space-X 97.1 deg
9 CA, US 720 km

Roscosmo Baikonur,
Soyuz Q1 2016 4 600 km 98 deg
s Kazakhstan

Mission Duration: The operational lifetime of each satellite is estimated to be up to 2 years following
deployment from the launch vehicle. The orbital lifetime for the constellation is nominally
expected to be between 5-8 years, depending on the vehicle’s orbit, as described in
Section 6.

ODAR Section 2: Spacecraft Description
Physical Description:
Property Value

Total Mass at Launch 4.5kg

Dry Mass at Launch 4.5kg

Form Factor 3U CubeSat

COG <3cm radius from geometric center

Envelope (stowed) 100mm x 100mm x 340.5mm (excluding dynamic envelope)

Envelope (deployed) 1m x 1m x 300mm

Propulsion Systems None

Fluid Systems None

AOCS Stabilization/pointing with 3x orthogonal reaction wheels, desaturation
+ coarse pointing with magnetorquers, GPS navigation

Range Safety / None
Pyrotechnic Devices

Electrical Generation Triple-junction GaAs solar panels

Electrical Storage Rechargable lithium-polymer battery pack

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 2.0.2 log demonstrating the compliance to the above requirements is available in Appendix A – “DAS 2.0.2
Log”.

ODAR Section 4: Assessment of Spacecraft Intentional
Breakups and Potential for Explosions
Potential causes for spacecraft breakup:

There are only two plausible causes for breakup of the satellites:
● energy released from onboard batteries, and
● mechanical failure of the reaction wheels
Summary of failure modes and effects analysis of all credible failure modes which may lead to an
accidental explosion:

The batteries aboard the satellites are two 42Wh Lithium-Polymer batteries, and represent the only credible
failure mode during which stored energy is released. The main failure modes associated with Lithium Polymer
batteries result from overcharging, overdischarging, internal shorts, and external shorts.
The battery pack onboard LEMUR-2 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.
The only failure mode of the reaction wheel assemblies that could lead to creation of debris would be breakup of
the wheels themselves due to mechanical failure while operating at a high angular rate. Risk mitigation strategies
for breakups due to the reaction wheels include limiting the maximum rotational speed of the wheels, and
containing them within a sealed compartment.
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 the end of mission, the only components that will require passivation are the reaction wheels. At the end of the
mission, the reaction wheels will be de-spun to passivate.
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 2.0.2 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 2.0.2 log demonstrating the compliance to the above requirements is available in Appendix A – “DAS 2.0.2
Log”.

ODAR Section 6: Assessment of Spacecraft Postmission
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 LEMUR-2 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.
Drag area from deployed antennas (2x 0.5m whip antennas, 3x 0.3m whip antennas) was neglected; as such, the
effective area-to-mass calculated below is a conservative case.

Table 1 - Area-to-Mass Ratio of LEMUR-2 Satellites in Various Mission Scenarios

Scenario Description Effective Area-
to-Mass (m2/kg)
1
Satellite ▪ Solar arrays deploy only after 5 years 0.0000 (yrs 1-5)
Nonfunctional ▪ Satellite tumbles randomly 0.0169 (yrs 5+)

Solar panel ▪ Solar panels fail to deploy
failure ▪ Satellite maintains +Z axis nadir 0.0130
▪ Position around Z axis as planned for mission operations

Operational, ▪ Solar panels deploy
nominal ▪ Satellite maintains +Z axis nadir 0.0208
▪ Position around Z axis as planned for mission operations

ADCS ▪ Solar arrays deploy
0.0169
Nonfunctional ▪ Satellite tumbles randomly

1
For the analysis, it was conservatively assumed that the satellite does not lose any altitude during the first 5 years (ie, an
area of 0).

Table 2 shows the simulated orbital dwell time for a LEMUR-2 satellite in each of the planned orbits of the
constellation, in each of the identified mission scenarios. In all mission scenarios and orbits, the dwell time of the
satellite was simulated using DAS 2.0.2 software to be less than 20 years.

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

Orbital Lifetime (Years)

Q1 2016 Q1 2016 Q4 2015 Q1 2016
Q4 2015 Q4 2015
HII-A Falcon-9 Atlas V Soyuz
Soyuz PSLV
Effective (7 (10 (4 satellites) (4 satellites)
Area-to- (2 satellites) (4 satellites)
Description satellites) satellites)
Mass
(m2/kg)
575km x 650km x 500km x 600km x
600km x 750km x
575km, 31 650km, 6 500km, 51.6 600km SSO
600km SSO 450km, SSO
deg deg deg

Satellite 19.8 17.0 11.6 23.8
2
7.2 19.8
0.0074
Nonfunctional

Solar panels 11.1 8.8 8.0 23.2 6.1 11.1
0.0130
failure

ADCS 9.0 8.0 7.4 18.8 5.7 9.0
0.0169
Nonfunctional

Operational, 8.3 7.5 6.9 17.3 5.2 8.3
0.0208
Nominal

Identification of Systems Required for Postmission Disposal: None
Plan for Spacecraft Maneuvers required for Postmission 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

2
No decay in first 5 years, after that deployment of antenna and solar panel due to decay of nylon filament with an
effective area/mass of 0.0169 m2/kg

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 postmission 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 Shape Size (mm)
(g)

Solar Panels (long) Glass, GaAs, FR4 6 150 Flat 100 x 300
PCB Plate

GPS Antenna (large) Aluminum 1 450 Box 300 x 80 x
8

GPS Antenna (small) Aluminum 1 50 Box 50 x 50 x
17

Subsystem PCBs FR4 PCB 12 80 Flat 90 x 90
Plate

Primary Structure Aluminum 1 560 Box 100 x 100
x 300

Optical Camera Aluminum, FR4 1 350 Cylinder 30 x 100
PCB, Glass

Reaction wheel assembly Aluminum, copper, 1 600 Box 100 x 100
+ enclosure FR4 PCB x 56

Battery pack Li-Polymer 2 470 Box 80 x 60 x
40

Summary of objects expected to survive an uncontrolled reentry (using DAS 2.0.2 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 2.0.2 log demonstrating the compliance to Requirement 4.7-1 is available in Appendix A – “DAS 2.0.2
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 postmission disposal: N/A
Probability of tether colliding with large space objects: N/A
Probability of tether being severed during mission or after postmission disposal: N/A

Maximum orbital lifetime of a severed tether fragment: N/A

Assessment of compliance with Requirement 4.8-1:

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

$Appendix A: DAS 2.0.2 Log Below is the log of the DAS 2.0.2 simulation performed to demonstrate compliance to the above requirements. 04 22 2015; 22:49:55PM DAS Application Started 04 22 2015; 22:49:57PM Opened Project C:\Program Files (x86)\NASA\DAS 2.0\project\ 04 22 2015; 22:50:57PM Opened Project C:\Users\nanosatisfi\Downloads\ODAR-2015-04-22\ODAR\ 04 22 2015; 22:51:47PM Science and Engineering - Orbit Lifetime/Dwell Time **INPUT** Start Year = 2015.500000 (yr) Perigee Altitude = 500.000000 (km) Apogee Altitude = 500.000000 (km) Inclination = 51.600000 (deg) RAAN = 0.000000 (deg) Argument of Perigee = 0.000000 (deg) Area-To-Mass Ratio = 0.007400 (m^2/kg) **OUTPUT** Orbital Lifetime from Startyr = 7.178645 (yr) Time Spent in LEO during Lifetime = 7.178645 (yr) Last year of Propagation = 2022 (yr) Returned Error Message: Object reentered 04 22 2015; 22:52:41PM Science and Engineering - Orbit Lifetime/Dwell Time **INPUT** Start Year = 2015.500000 (yr) Perigee Altitude = 500.000000 (km) Apogee Altitude = 500.000000 (km) Inclination = 51.600000 (deg) RAAN = 0.000000 (deg) Argument of Perigee = 0.000000 (deg) Area-To-Mass Ratio = 0.013000 (m^2/kg) **OUTPUT** Orbital Lifetime from Startyr = 6.121834 (yr) Time Spent in LEO during Lifetime = 6.121834 (yr) Last year of Propagation = 2021 (yr) Returned Error Message: Object reentered$

04 22 2015; 22:52:51PM Science and Engineering - Orbit Lifetime/Dwell
Time

**INPUT**

Start Year = 2015.500000 (yr)
Perigee Altitude = 500.000000 (km)
Apogee Altitude = 500.000000 (km)
Inclination = 51.600000 (deg)
RAAN = 0.000000 (deg)
Argument of Perigee = 0.000000 (deg)
Area-To-Mass Ratio = 0.016900 (m^2/kg)

**OUTPUT**

Orbital Lifetime from Startyr = 5.700205 (yr)
Time Spent in LEO during Lifetime = 5.700205 (yr)
Last year of Propagation = 2021 (yr)
Returned Error Message: Object reentered
04 22 2015; 22:53:02PM Science and Engineering - Orbit Lifetime/Dwell
Time

**INPUT**

Start Year = 2015.500000 (yr)
Perigee Altitude = 500.000000 (km)
Apogee Altitude = 500.000000 (km)
Inclination = 51.600000 (deg)
RAAN = 0.000000 (deg)
Argument of Perigee = 0.000000 (deg)
Area-To-Mass Ratio = 0.020800 (m^2/kg)

**OUTPUT**

Orbital Lifetime from Startyr = 5.212868 (yr)
Time Spent in LEO during Lifetime = 5.212868 (yr)
Last year of Propagation = 2020 (yr)
Returned Error Message: Object reentered
04 22 2015; 22:53:24PM Science and Engineering - Orbit Lifetime/Dwell
Time

**INPUT**

Start Year = 2015.500000 (yr)
Perigee Altitude = 600.000000 (km)
Apogee Altitude = 600.000000 (km)
Inclination = 98.000000 (deg)
RAAN = 0.000000 (deg)
Argument of Perigee = 0.000000 (deg)
Area-To-Mass Ratio = 0.020800 (m^2/kg)

**OUTPUT**

Orbital Lifetime from Startyr = 8.268309 (yr)
Time Spent in LEO during Lifetime = 8.268309 (yr)
Last year of Propagation = 2023 (yr)
Returned Error Message: Object reentered
04 22 2015; 22:53:38PM Science and Engineering - Orbit Lifetime/Dwell
Time

**INPUT**

Start Year = 2015.500000 (yr)
Perigee Altitude = 600.000000 (km)
Apogee Altitude = 600.000000 (km)
Inclination = 98.000000 (deg)
RAAN = 0.000000 (deg)
Argument of Perigee = 0.000000 (deg)
Area-To-Mass Ratio = 0.016900 (m^2/kg)

**OUTPUT**

Orbital Lifetime from Startyr = 8.974675 (yr)
Time Spent in LEO during Lifetime = 8.974675 (yr)
Last year of Propagation = 2024 (yr)
Returned Error Message: Object reentered
04 22 2015; 22:53:46PM Science and Engineering - Orbit Lifetime/Dwell
Time

**INPUT**

Start Year = 2015.500000 (yr)
Perigee Altitude = 600.000000 (km)
Apogee Altitude = 600.000000 (km)
Inclination = 98.000000 (deg)
RAAN = 0.000000 (deg)
Argument of Perigee = 0.000000 (deg)
Area-To-Mass Ratio = 0.013000 (m^2/kg)

**OUTPUT**

Orbital Lifetime from Startyr = 11.082820 (yr)
Time Spent in LEO during Lifetime = 11.082820 (yr)
Last year of Propagation = 2026 (yr)
Returned Error Message: Object reentered
04 22 2015; 22:53:57PM Science and Engineering - Orbit Lifetime/Dwell
Time

**INPUT**

Start Year = 2015.500000 (yr)
Perigee Altitude = 600.000000 (km)

Apogee Altitude = 600.000000 (km)
Inclination = 98.000000 (deg)
RAAN = 0.000000 (deg)
Argument of Perigee = 0.000000 (deg)
Area-To-Mass Ratio = 0.007400 (m^2/kg)

**OUTPUT**

Orbital Lifetime from Startyr = 19.805613 (yr)
Time Spent in LEO during Lifetime = 19.805613 (yr)
Last year of Propagation = 2035 (yr)
Returned Error Message: Object reentered
04 22 2015; 22:55:47PM Mission Editor Changes Applied
04 22 2015; 22:56:24PM Mission Editor Changes Applied
04 22 2015; 22:56:28PM Project Data Saved To File
04 22 2015; 22:56:48PM Processing Requirement 4.3-1: Return Status :
Not Run

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

=============== End of Requirement 4.3-1 ===============
04 22 2015; 22:56:51PM Processing Requirement 4.3-2: Return Status :
Passed

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

=============== End of Requirement 4.3-2 ===============
04 22 2015; 22:56:53PM Requirement 4.4-3: Compliant

=============== End of Requirement 4.4-3 ===============
04 22 2015; 22:57:01PM Processing Requirement 4.5-1: Return Status :
Passed

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

**INPUT**

Space Structure Name = Lemur2_PSLV
Space Structure Type = Payload
Perigee Altitude = 650.000000 (km)
Apogee Altitude = 650.000000 (km)
Inclination = 6.000000 (deg)
RAAN = 0.000000 (deg)
Argument of Perigee = 0.000000 (deg)
Mean Anomaly = 0.000000 (deg)

Final Area-To-Mass Ratio = 0.020800 (m^2/kg)
Start Year = 2015.500000 (yr)
Initial Mass = 4.500000 (kg)
Final Mass = 4.500000 (kg)
Duration = 17.300000 (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 = 0.000002
Returned Error Message: Normal Processing
Date Range Error Message: Normal Date Range
Status = Pass

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

**INPUT**

Space Structure Name = Lemur2_Soyuz
Space Structure Type = Payload
Perigee Altitude = 600.000000 (km)
Apogee Altitude = 600.000000 (km)
Inclination = 97.800000 (deg)
RAAN = 0.000000 (deg)
Argument of Perigee = 0.000000 (deg)
Mean Anomaly = 0.000000 (deg)
Final Area-To-Mass Ratio = 0.020800 (m^2/kg)
Start Year = 2015.500000 (yr)
Initial Mass = 4.500000 (kg)
Final Mass = 4.500000 (kg)
Duration = 8.300000 (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 = 0.000002
Returned Error Message: Normal Processing

Date Range Error Message: Normal Date Range
Status = Pass

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

**INPUT**

Space Structure Name = Lemur2_Falcon9
Space Structure Type = Payload
Perigee Altitude = 425.000000 (km)
Apogee Altitude = 750.000000 (km)
Inclination = 97.100000 (deg)
RAAN = 0.000000 (deg)
Argument of Perigee = 0.000000 (deg)
Mean Anomaly = 0.000000 (deg)
Final Area-To-Mass Ratio = 0.020800 (m^2/kg)
Start Year = 2015.500000 (yr)
Initial Mass = 4.500000 (kg)
Final Mass = 4.500000 (kg)
Duration = 6.900000 (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 = 0.000001
Returned Error Message: Normal Processing
Date Range Error Message: Normal Date Range
Status = Pass

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

**INPUT**

Space Structure Name = Lemur2_HIIB
Space Structure Type = Payload
Perigee Altitude = 575.000000 (km)
Apogee Altitude = 575.000000 (km)
Inclination = 31.000000 (deg)
RAAN = 0.000000 (deg)
Argument of Perigee = 0.000000 (deg)
Mean Anomaly = 0.000000 (deg)
Final Area-To-Mass Ratio = 0.020800 (m^2/kg)
Start Year = 2015.500000 (yr)
Initial Mass = 4.500000 (kg)

Final Mass = 4.500000 (kg)
Duration = 7.500000 (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 = 0.000001
Returned Error Message: Normal Processing
Date Range Error Message: Normal Date Range
Status = Pass

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

**INPUT**

Space Structure Name = Lemur2_AtlasV
Space Structure Type = Payload
Perigee Altitude = 500.000000 (km)
Apogee Altitude = 500.000000 (km)
Inclination = 51.600000 (deg)
RAAN = 0.000000 (deg)
Argument of Perigee = 0.000000 (deg)
Mean Anomaly = 0.000000 (deg)
Final Area-To-Mass Ratio = 0.020800 (m^2/kg)
Start Year = 2015.500000 (yr)
Initial Mass = 4.500000 (kg)
Final Mass = 4.500000 (kg)
Duration = 5.200000 (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 = Lemur2_Soyuz2
Space Structure Type = Payload
Perigee Altitude = 600.000000 (km)
Apogee Altitude = 600.000000 (km)
Inclination = 98.000000 (deg)
RAAN = 0.000000 (deg)
Argument of Perigee = 0.000000 (deg)
Mean Anomaly = 0.000000 (deg)
Final Area-To-Mass Ratio = 0.020800 (m^2/kg)
Start Year = 2015.500000 (yr)
Initial Mass = 4.500000 (kg)
Final Mass = 4.500000 (kg)
Duration = 8.300000 (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 = 0.000002
Returned Error Message: Normal Processing
Date Range Error Message: Normal Date Range
Status = Pass

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

=============== End of Requirement 4.5-1 ===============
04 22 2015; 22:57:09PM Requirement 4.5-2: Compliant
04 22 2015; 22:57:12PM Processing Requirement 4.6 Return Status :
Passed

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

**INPUT**

Space Structure Name = Lemur2_PSLV
Space Structure Type = Payload

Perigee Altitude = 650.000000 (km)
Apogee Altitude = 650.000000 (km)

Inclination = 6.000000 (deg)
RAAN = 0.000000 (deg)
Argument of Perigee = 0.000000 (deg)
Mean Anomaly = 0.000000 (deg)
Area-To-Mass Ratio = 0.020800 (m^2/kg)
Start Year = 2015.500000 (yr)
Initial Mass = 4.500000 (kg)
Final Mass = 4.500000 (kg)
Duration = 17.300000 (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 = 650.000000 (km)
Suggested Apogee Altitude = 650.000000 (km)
Returned Error Message = Reentry during mission (no PMD req.).

Released Year = 2032 (yr)
Requirement = 61
Compliance Status = Pass

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

**INPUT**

Space Structure Name = Lemur2_Soyuz
Space Structure Type = Payload

Perigee Altitude = 600.000000 (km)
Apogee Altitude = 600.000000 (km)
Inclination = 97.800000 (deg)
RAAN = 0.000000 (deg)
Argument of Perigee = 0.000000 (deg)
Mean Anomaly = 0.000000 (deg)
Area-To-Mass Ratio = 0.020800 (m^2/kg)
Start Year = 2015.500000 (yr)
Initial Mass = 4.500000 (kg)
Final Mass = 4.500000 (kg)
Duration = 8.300000 (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 = 600.000000 (km)
Suggested Apogee Altitude = 600.000000 (km)
Returned Error Message = Reentry during mission (no PMD req.).

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

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

**INPUT**

Space Structure Name = Lemur2_Falcon9
Space Structure Type = Payload

Perigee Altitude = 425.000000 (km)
Apogee Altitude = 750.000000 (km)
Inclination = 97.100000 (deg)
RAAN = 0.000000 (deg)
Argument of Perigee = 0.000000 (deg)
Mean Anomaly = 0.000000 (deg)
Area-To-Mass Ratio = 0.020800 (m^2/kg)
Start Year = 2015.500000 (yr)
Initial Mass = 4.500000 (kg)
Final Mass = 4.500000 (kg)
Duration = 6.900000 (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 = 425.000000 (km)
Suggested Apogee Altitude = 750.000000 (km)
Returned Error Message = Reentry during mission (no PMD req.).

Released Year = 2021 (yr)
Requirement = 61
Compliance Status = Pass

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

**INPUT**

Space Structure Name = Lemur2_HIIB
Space Structure Type = Payload

Perigee Altitude = 575.000000 (km)
Apogee Altitude = 575.000000 (km)
Inclination = 31.000000 (deg)
RAAN = 0.000000 (deg)
Argument of Perigee = 0.000000 (deg)
Mean Anomaly = 0.000000 (deg)
Area-To-Mass Ratio = 0.020800 (m^2/kg)
Start Year = 2015.500000 (yr)
Initial Mass = 4.500000 (kg)
Final Mass = 4.500000 (kg)
Duration = 7.500000 (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 = 2022 (yr)
Requirement = 61
Compliance Status = Pass

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

**INPUT**

Space Structure Name = Lemur2_AtlasV
Space Structure Type = Payload

Perigee Altitude = 500.000000 (km)
Apogee Altitude = 500.000000 (km)
Inclination = 51.600000 (deg)
RAAN = 0.000000 (deg)
Argument of Perigee = 0.000000 (deg)
Mean Anomaly = 0.000000 (deg)
Area-To-Mass Ratio = 0.020800 (m^2/kg)

Start Year = 2015.500000 (yr)
Initial Mass = 4.500000 (kg)
Final Mass = 4.500000 (kg)
Duration = 5.200000 (yr)
Station Kept = False
Abandoned = True
PMD Perigee Altitude = 248.048791 (km)
PMD Apogee Altitude = 256.789865 (km)
PMD Inclination = 51.571325 (deg)
PMD RAAN = 7.848664 (deg)
PMD Argument of Perigee = 74.605471 (deg)
PMD Mean Anomaly = 0.000000 (deg)

**OUTPUT**

Suggested Perigee Altitude = 248.048791 (km)
Suggested Apogee Altitude = 256.789865 (km)
Returned Error Message = Passes LEO reentry orbit criteria.

Released Year = 2020 (yr)
Requirement = 61
Compliance Status = Pass

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

**INPUT**

Space Structure Name = Lemur2_Soyuz2
Space Structure Type = Payload

Perigee Altitude = 600.000000 (km)
Apogee Altitude = 600.000000 (km)
Inclination = 98.000000 (deg)
RAAN = 0.000000 (deg)
Argument of Perigee = 0.000000 (deg)
Mean Anomaly = 0.000000 (deg)
Area-To-Mass Ratio = 0.020800 (m^2/kg)
Start Year = 2015.500000 (yr)
Initial Mass = 4.500000 (kg)
Final Mass = 4.500000 (kg)
Duration = 8.300000 (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 = 600.000000 (km)
Suggested Apogee Altitude = 600.000000 (km)
Returned Error Message = Reentry during mission (no PMD req.).

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

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

=============== End of Requirement 4.6 ===============
04 22 2015; 22:58:19PM *********Processing Requirement 4.7-1
Return Status : Passed

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

name = Lemur2_PSLV
quantity = 1
parent = 0
materialID = 5
type = Box
Aero Mass = 4.500000
Thermal Mass = 4.500000
Diameter/Width = 0.100000
Length = 0.340000
Height = 0.100000

name = Structure_tray
quantity = 2
parent = 1
materialID = 9
type = Box
Aero Mass = 0.200000
Thermal Mass = 0.200000
Diameter/Width = 0.100000
Length = 0.340000
Height = 0.005000

name = Structure_ribs
quantity = 10
parent = 1
materialID = 9
type = Box
Aero Mass = 0.010000
Thermal Mass = 0.010000
Diameter/Width = 0.012000
Length = 0.083000
Height = 0.006000

name = Structure_mountingplates
quantity = 5
parent = 1
materialID = 9
type = Flat Plate
Aero Mass = 0.100000
Thermal Mass = 0.100000
Diameter/Width = 0.080000
Length = 0.100000

name = PCB
quantity = 15
parent = 1
materialID = 23
type = Flat Plate
Aero Mass = 0.080000
Thermal Mass = 0.080000
Diameter/Width = 0.080000
Length = 0.080000

name = Lenses
quantity = 2
parent = 1
materialID = 9
type = Cylinder
Aero Mass = 0.200000
Thermal Mass = 0.200000
Diameter/Width = 0.030000
Length = 0.120000

name = Reaction Wheels
quantity = 3
parent = 1
materialID = 67
type = Cylinder
Aero Mass = 0.120000
Thermal Mass = 0.120000
Diameter/Width = 0.030000
Length = 0.020000

name = solar_panels
quantity = 6
parent = 1
materialID = 23
type = Flat Plate
Aero Mass = 0.100000
Thermal Mass = 0.100000
Diameter/Width = 0.083000
Length = 0.324000

name = solar_cells

quantity = 61
parent = 1
materialID = 24
type = Flat Plate
Aero Mass = 0.015000
Thermal Mass = 0.015000
Diameter/Width = 0.040000
Length = 0.080000

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

name = Lemur2_PSLV
Demise Altitude = 77.996621
Debris Casualty Area = 0.000000
Impact Kinetic Energy = 0.000000

*************************************
name = Structure_tray
Demise Altitude = 76.444527
Debris Casualty Area = 0.000000
Impact Kinetic Energy = 0.000000

*************************************
name = Structure_ribs
Demise Altitude = 77.121871
Debris Casualty Area = 0.000000
Impact Kinetic Energy = 0.000000

*************************************
name = Structure_mountingplates
Demise Altitude = 75.443886
Debris Casualty Area = 0.000000
Impact Kinetic Energy = 0.000000

*************************************
name = PCB
Demise Altitude = 76.127535
Debris Casualty Area = 0.000000
Impact Kinetic Energy = 0.000000

*************************************
name = Lenses
Demise Altitude = 72.843566
Debris Casualty Area = 0.000000
Impact Kinetic Energy = 0.000000

*************************************
name = Reaction Wheels
Demise Altitude = 0.000000
Debris Casualty Area = 1.169982

Impact Kinetic Energy = 202.520203

*************************************
name = solar_panels
Demise Altitude = 77.271605
Debris Casualty Area = 0.000000
Impact Kinetic Energy = 0.000000

*************************************
name = solar_cells
Demise Altitude = 77.747871
Debris Casualty Area = 0.000000
Impact Kinetic Energy = 0.000000

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

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

name = Lemur2_Soyuz
quantity = 1
parent = 0
materialID = 9
type = Box
Aero Mass = 4.500000
Thermal Mass = 4.500000
Diameter/Width = 0.100000
Length = 0.340000
Height = 0.100000

name = Lemur2_Soyuz
quantity = 1
parent = 1
materialID = 9
type = Box
Aero Mass = 4.500000
Thermal Mass = 4.500000
Diameter/Width = 0.100000
Length = 0.340000
Height = 0.100000

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

name = Lemur2_Soyuz
Demise Altitude = 77.998722
Debris Casualty Area = 0.000000
Impact Kinetic Energy = 0.000000

*************************************
name = Lemur2_Soyuz

Demise Altitude = 66.439011
Debris Casualty Area = 0.000000
Impact Kinetic Energy = 0.000000

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

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

name = Lemur2_Falcon9
quantity = 1
parent = 0
materialID = 5
type = Box
Aero Mass = 4.500000
Thermal Mass = 4.500000
Diameter/Width = 0.100000
Length = 0.340000
Height = 0.100000

name = Lemur2_Falcon9
quantity = 1
parent = 1
materialID = 5
type = Box
Aero Mass = 4.500000
Thermal Mass = 4.500000
Diameter/Width = 0.100000
Length = 0.340000
Height = 0.100000

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

name = Lemur2_Falcon9
Demise Altitude = 77.997660
Debris Casualty Area = 0.000000
Impact Kinetic Energy = 0.000000

*************************************
name = Lemur2_Falcon9
Demise Altitude = 64.797706
Debris Casualty Area = 0.000000
Impact Kinetic Energy = 0.000000

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

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

name = Lemur2_HIIB

quantity = 1
parent = 0
materialID = 9
type = Box
Aero Mass = 4.500000
Thermal Mass = 4.500000
Diameter/Width = 0.100000
Length = 0.340000
Height = 0.100000

name = Lemur2_HIIB
quantity = 1
parent = 1
materialID = 9
type = Box
Aero Mass = 4.500000
Thermal Mass = 4.500000
Diameter/Width = 0.100000
Length = 0.340000
Height = 0.100000

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

name = Lemur2_HIIB
Demise Altitude = 77.995176
Debris Casualty Area = 0.000000
Impact Kinetic Energy = 0.000000

*************************************
name = Lemur2_HIIB
Demise Altitude = 64.728616
Debris Casualty Area = 0.000000
Impact Kinetic Energy = 0.000000

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

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

name = Lemur2_AtlasV
quantity = 1
parent = 0
materialID = 9
type = Box
Aero Mass = 4.500000
Thermal Mass = 4.500000
Diameter/Width = 0.100000
Length = 0.340000
Height = 0.100000

name = Lemur2_AtlasV
quantity = 1
parent = 1
materialID = 9
type = Box
Aero Mass = 4.500000
Thermal Mass = 4.500000
Diameter/Width = 0.100000
Length = 0.340000
Height = 0.100000

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

name = Lemur2_AtlasV
Demise Altitude = 77.993738
Debris Casualty Area = 0.000000
Impact Kinetic Energy = 0.000000

*************************************
name = Lemur2_AtlasV
Demise Altitude = 65.304866
Debris Casualty Area = 0.000000
Impact Kinetic Energy = 0.000000

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

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

name = Lemur2_Soyuz2
quantity = 1
parent = 0
materialID = 9
type = Box
Aero Mass = 4.500000
Thermal Mass = 4.500000
Diameter/Width = 0.100000
Length = 0.340000
Height = 0.100000

name = Lemur2_Soyuz2
quantity = 1
parent = 1
materialID = 9
type = Box
Aero Mass = 4.500000
Thermal Mass = 4.500000
Diameter/Width = 0.100000
Length = 0.340000
Height = 0.100000

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

name = Lemur2_Soyuz2
Demise Altitude = 77.997137
Debris Casualty Area = 0.000000
Impact Kinetic Energy = 0.000000

*************************************
name = Lemur2_Soyuz2
Demise Altitude = 66.448152
Debris Casualty Area = 0.000000
Impact Kinetic Energy = 0.000000

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

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

Document Created: 2015-08-24 20:13:10
Document Modified: 2015-08-24 20:13:10