Orbital Debris Assessment

0829-EX-PL-2014 Text Documents

BlackSky Global, LLC

2014-12-10ELS_156789

BlackSky Global Pathfinder-1 & -2 Orbital
Debris Assessment Report (ODAR)
This report is presented in compliance with NASA-STD-8719.14, APPENDIX A.

Report Version: 3 , November 17, 2014

Revision history:
Version Date Author Description
1 10/29/13 Eric Lund ODAR for Pathfinder spacecraft launched into an SSO orbit
2 5/14/14 John Springmann Modifications due to new launch plan, which is deployment
from the International Space Station
3 11/17/14 John Springmann Modifications due to a new launch plan, which is secondary
deployment from SpaceX Falcon 9

Document Data is Not Restricted.
This document contains no proprietary, ITAR, or export controlled information.

DAS Software Version Used In Analysis: v2.0.2

Pathfinder-1 & -2 Orbital Debris Assessment Report (ODAR)

VERSION APPROVAL and/or FINAL APPROVAL*:

Jason Andrews, CEO

*Approval signatures indicate acceptance of the ODAR-defined risk.

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Pathfinder-1 & -2 Orbital Debris Assessment Report (ODAR)

Table Contents

Self-assessment of the ODAR using the format in Appendix A.2 of NASA-STD- 8719.14: ......... 5
Assessment Report Format:............................................................................................................. 6
ODAR Section 1: Program Management and Mission Overview ................................................... 6
ODAR Section 2: Spacecraft Description ....................................................................................... 7
ODAR Section 3: Assessment of Spacecraft Debris Released during Normal Operations ............. 8
ODAR Section 4: Assessment of Spacecraft Intentional Breakups and Potential for Explosions... 9
ODAR Section 5: Assessment of Spacecraft Potential for On-Orbit Collisions ............................ 13
ODAR Section 6: Assessment of Spacecraft Post-mission Disposal Plans and Procedures ......... 14
ODAR Section 7: Assessment of Spacecraft Reentry Hazards ..................................................... 17
ODAR Section 8: Assessment for Tether Missions....................................................................... 49

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Pathfinder-1 & -2 Orbital Debris Assessment Report (ODAR)

Self-assessment of the ODAR using the format in Appendix A.2 of NASA-STD- 8719.14:
A self-assessment is provided below in accordance with the assessment format provided in Appendix A.2 of NASA-STD-8719.14.

Orbital Debris Self-Assessment Report Evaluation: Pathfinder-1 and -2 satellites

Launch Vehicle Spacecraft

Requirement # Compliant
Not
Incomplete
Standard
Non
Compliant Not
Incomplete
Comments
Compliant or N/A Compliant
Compliant
4.3-1.a No Debris Released in LEO.
4.3-1.b No Debris Released in LEO.
4.3-2 No Debris Released in GEO.
4.4-1 Not applicable. See note 1.
4.4-2 Warm-gas propulsion tank will be deplete during
operations
4.4-3 No planned breakups.
4.4-4 No planned breakups.
4.5-1 Collision probability 0.00000
4.5-2 Damage probability < 0.0068
4.6-1(a) Natural forces cause atmospheric reentry
4.6-1(b) Not applicable.
4.6-1(c) Not applicable.
4.6-2 Spacecraft does not go to GEO.
4.6-3 Spacecraft does not go beyond LEO.
4.6-4 Requirements 4.6-1 through 4.6-3 are met
4.7-1 DAS reports human casualty probability < 1:10,000
4.8-1 No tethers used.
Notes:

1. This launch has several spacecraft manifested; the Pathfinder satellites are not the primary payload. No explosive devices are used to deploy the spacecraft.

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Pathfinder-1 & -2 Orbital Debris Assessment Report (ODAR)

releases.
Rationale/necessity for release of each object: N/A.
Time of release of each object, relative to launch time: N/A.
Release velocity of each object with respect to spacecraft: N/A.
Expected orbital parameters (apogee, perigee, and inclination) of each object after release:
N/A.
Calculated orbital lifetime of each object, including time spent in Low Earth Orbit (LEO):
N/A.

Assessment of spacecraft compliance with Requirements 4.3-1 and 4.3-2 (per DAS v2.0.2)
4.3-1, Mission Related Debris Passing Through LEO: COMPLIANT
4.3-2, Mission Related Debris Passing Near GEO: COMPLIANT

ODAR Section 4: Assessment of Spacecraft Intentional Breakups and
Potential for Explosions.
Potential causes of spacecraft breakup during deployment and mission operations:
There is no credible scenario that would result in spacecraft breakup during normal
deployment and operations.
Summary of failure modes and effects analyses of all credible failure modes which may
lead to an accidental explosion:
In-mission failure of a battery cell protection circuit could lead to a short circuit resulting
in overheating and a very remote possibility of battery cell explosion. The battery safety
systems discussed in the FMEA (see requirement 4.4-1 below) describe the combined
faults that must occur for any of seven (7) independent, mutually exclusive failure modes
to lead to explosion.
In addition to the battery protection mentioned about, the PATHFINDER battery unit
features two thermal switches which completely isolate the battery electrically if the
temperature gets too high.
Detailed plan for any designed spacecraft breakup, including explosions and intentional
collisions:
There are no planned breakups.
List of components which shall be passivated at End of Mission (EOM) including method
of passivation and amount which cannot be passivated:
The butane propulsion system shall be passivated at the end of mission by operating the
system to propellant depletion in a perigee lowering maneuver.
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Pathfinder-1 & -2 Orbital Debris Assessment Report (ODAR)

Rationale for all items which are required to be passivated, but cannot be due to their
design:
Pathfinder battery charge circuits include overcharge protection and a parallel design to
limit the risk of battery failure. However, in the unlikely event that a battery cell does
explosively rupture, the small size, mass, and potential energy, of these small batteries is
such that while the spacecraft could be expected to vent gases, most debris from the
battery rupture should be contained within the vessel due to the lack of penetration
energy.

Assessment of spacecraft compliance with Requirements 4.4-1 through 4.4-4:
Requirement 4.4-1: Limiting the risk to other space systems from accidental explosions
during deployment and mission operations while in orbit about Earth or the Moon:

For each spacecraft and launch vehicle orbital stage employed for a mission, the program
or project shall demonstrate, via failure mode and effects analyses or equivalent analyses,
that the integrated probability of explosion for all credible failure modes of each
spacecraft and launch vehicle is less than 0.001 (excluding small particle impacts)
(Requirement 56449).

Compliance statement:

Required Probability: 0.001.
Expected probability: 0.000.

Supporting Rationale and FMEA details:
Battery explosion:
Effect: All failure modes below might theoretically result in battery explosion
with the possibility of orbital debris generation. However, in the unlikely event
that a battery cell does explosively rupture, the small size, mass, and potential
energy, of the selected COTS batteries is such that while the spacecraft could be
expected to vent gases, most debris from the battery rupture should be contained
within the vessel due to the lack of penetration energy.
Probability: Extremely Low. It is believed to be a much less than 0.1%
probability that multiple independent (not common mode) faults must occur for
each failure mode to cause the ultimate effect (explosion).

Failure mode 1: Internal short circuit.

Mitigation 1: Qualification and acceptance shock, vibration, thermal cycling, and
vacuum tests followed by maximum system rate-limited charge and discharge to
prove that no internal short circuit sensitivity exists.

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Pathfinder-1 & -2 Orbital Debris Assessment Report (ODAR)

Combined faults required for realized failure: Environmental testing AND
functional charge/discharge tests must both be ineffective in discovery of the
failure mode.

Failure Mode 2: Internal thermal rise due to high load discharge rate.

Mitigation 2: Cells were tested in lab for high load discharge rates in a variety of
flight-like configurations to determine like likelihood and impact of an out-of-
control thermal rise in the cell. Cells were also tested in a hot environment to test
the upper limit of the cells capability. No failures were seen.

Combined faults required for realized failure: Spacecraft thermal design must be
incorrect AND external over-current detection and disconnect function must fail
to enable this failure mode.

Failure Mode 3: Excessive discharge rate or short circuit due to external device
failure or terminal contact with conductors not at battery voltage levels (due to
abrasion or inadequate proximity separation).

Mitigation 3: This failure mode is negated by a) qualification-tested short circuit
protection on each external circuit, b) design of battery packs and insulators such
that no contact with nearby board traces is possible without being caused by some
other mechanical failure, c) obviation of such other mechanical failures by proto-
qualification and acceptance environmental tests (shock, vibration, thermal
cycling, and thermal-vacuum tests).

Combined faults required for realized failure: An external load must fail/short-
circuit AND external over-current detection and disconnect function failure must
all occur to enable this failure mode.

Failure Mode 4: Inoperable vents.

Mitigation 4: Battery vents are not inhibited by the battery holder design or the
spacecraft.

Combined effects required for realized failure: The final assembler fails to install
proper venting.

Failure Mode 5: Crushing.

Mitigation 5: This mode is negated by spacecraft design. There are no moving
parts in the proximity of the batteries.

Combined faults required for realized failure: A catastrophic failure must occur
in an external system AND the failure must cause a collision sufficient to crush
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Pathfinder-1 & -2 Orbital Debris Assessment Report (ODAR)

the batteries leading to an internal short circuit AND the satellite must be in a
naturally sustained orbit at the time the crushing occurs.

Failure Mode 6: Low level current leakage or short-circuit through battery pack
case or due to moisture-based degradation of insulators.

Mitigation 6: These modes are negated by a) battery holder/case design made of
non-conductive plastic, and b) operation in vacuum such that no moisture can
affect insulators.

Combined faults required for realized failure: Abrasion or piercing failure of
circuit board coating or wire insulators AND dislocation of battery packs AND
failure of battery terminal insulators AND failure to detect such failure modes in
environmental tests must occur to result in this failure mode.

Failure Mode 7: Excess temperatures due to orbital environment and high
discharge combined.

Mitigation 7: The spacecraft thermal design will negate this possibility. Thermal
rise has been analyzed in combination with space environment temperatures
showing that batteries do not exceed normal allowable operating temperatures
which are well below temperatures of concern for explosions.

Combined faults required for realized failure: Thermal analysis AND thermal
design AND mission simulations in thermal-vacuum chamber testing AND over-
current monitoring and control must all fail for this failure mode to occur.

Requirement 4.4-2: Design for passivation after completion of mission operations while
in orbit about Earth or the Moon:

Design of all spacecraft and launch vehicle orbital stages shall include the ability to
deplete all onboard sources of stored energy and disconnect all energy generation
sources when they are no longer required for mission operations or postmission disposal
or control to a level which cannot cause an explosion or deflagration large enough to
release orbital debris or break up the spacecraft (Requirement 56450).

Compliance statement:
Pathfinder battery charge circuits include overcharge protection and a parallel
design to limit the risk of battery failure. However, in the unlikely event that a
battery cell does explosively rupture, the small size, mass, and potential energy,
of these small batteries is such that while the spacecraft could be expected to vent
gases, most debris from the battery rupture should be contained within the vessel
due to the lack of penetration energy.

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Pathfinder-1 & -2 Orbital Debris Assessment Report (ODAR)

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

Compliance statement:
This requirement is not applicable. There are no planned breakups.

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

Compliance statement:
This requirement is not applicable. There are no planned breakups.

ODAR Section 5: Assessment of Spacecraft Potential for On-Orbit
Collisions
Assessment of spacecraft compliance with Requirements 4.5-1 and 4.5-2 (per DAS v2.0.2,
and calculation methods provided in NASA-STD-8719.14, section 4.5.4):
Requirement 4.5-1: Limiting debris generated by collisions with large objects when
operating in Earth orbit:
For each spacecraft and launch vehicle orbital stage in or passing through LEO, the
program or project shall demonstrate that, during the orbital lifetime of each spacecraft
and orbital stage, the probability of accidental collision with space objects larger than 10
cm in diameter is less than 0.001 (Requirement 56506).

Large Object Impact and Debris Generation Probability:
Collision Probability: 0.00000; COMPLIANT.

Requirement 4.5-2: Limiting debris generated by collisions with small objects when
operating in Earth or lunar orbit:
For each spacecraft, the program or project shall demonstrate that, during the mission of
the spacecraft, the probability of accidental collision with orbital debris and meteoroids
sufficient to prevent compliance with the applicable postmission disposal requirements is
less than 0.01 (Requirement 56507).

Small Object Impact and Debris Generation Probability:
Collision Probability: 0.006136; COMPLIANT.

Identification of all systems or components required to accomplish any postmission
disposal operation, including passivation and maneuvering:
No satellite operations are required for post-mission disposal. In the case that the
spacecraft was non-functional after deployment into its initial orbit of 450 x 720 km, its
orbit would completely decay within 15.25 years (according to DAS software and
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Pathfinder-1 & -2 Orbital Debris Assessment Report (ODAR)

assumptions of Section 6.3). From the planned operational orbit of 450 x 500 km, time-
to-disposal is reduced to 4.4 years. Both of these deorbit times were calculated using the
worst-case cross-sectional area of the spacecraft (minimum drag configuration).

ODAR Section 6: Assessment of Spacecraft Post-mission Disposal Plans
and Procedures
6.1 Description of spacecraft disposal option selected: The satellite will deorbit naturally by
atmospheric re-entry. At the end of the Pathfinders’ operational lives (i.e. at EOM) the attitude
control system will stop counteracting the aerodynamic disturbance torques and will rotate the
satellite into the maximum drag configuration. This will result in PAthfinder gradually assuming a
dynamically stable configuration. For atmospheric drag / re-entry calculations in DAS, the minimum
plausible cross-section drag area of 41 x 47.5 cm was assumed (smallest spacecraft side facing the velocity
direction). This is conservative because it represents the minimum cross section possible with the satellite
in any orientation, ignores protuberances, and ignores gravity gradient, ignores solar pressure torques, and
ignores the high-drag orientation set at EOM.

6.2 Plan for any spacecraft maneuvers required to accomplish postmission disposal:
The stable drag/gravity gradient configuration enables aerodynamic reentry. To accelerate the orbital
decay we plan to orient the satellite in this maximum drag configuration at the end of operations.

6.3 Calculation of area-to-mass ratio after postmission disposal, if the controlled reentry option is
not selected:
Spacecraft Mass: 41.82 km
Cross-sectional Area: 0.1947 m2
Area to mass ratio: 0.0047 m2/kg
6.4 Assessment of spacecraft compliance with Requirements 4.6-1 through 4.6-5 (per DAS
v 2.0.2 and NASA-STD-8719.14 section):
Requirement 4.6-1: Disposal for space structures passing through LEO:
A spacecraft or orbital stage with a perigee altitude below 2000 km shall be disposed of by one
of three methods:
(Requirement 56557)
a. Atmospheric reentry option:
 Leave the space structure in an orbit in which natural forces will lead to atmospheric
reentry within 25 years after the completion of mission but no more than 30 years after
launch; or
 Maneuver the space structure into a controlled de-orbit trajectory as soon as practical
after completion of mission.
b. Storage orbit option: Maneuver the space structure into an orbit with perigee altitude greater
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Pathfinder-1 & -2 Orbital Debris Assessment Report (ODAR)

EOM Orbit 450 x 500 km
Total Lifetime 7.4 years
Post-ops Life 4.4 years

Requirement 4.6-2. Disposal for space structures near GEO.
Analysis: Not applicable.

Requirement 4.6-3. Disposal for space structures between LEO and GEO.
Analysis: Not applicable.

Requirement 4.6-4. Reliability of Postmission Disposal Operations
Analysis: The minimum drag configuration is the aerodynamically stable state, meaning
that even under massive subsystem failure we would eventually assume this orientation.
This minimum drag configuration was assumed for atmospheric re-entry analysis.

Page 16

$Pathfinder-1 & -2 Orbital Debris Assessment Report (ODAR) ODAR Section 7: Assessment of Spacecraft Reentry Hazards Assessment of spacecraft compliance with Requirement 4.7-1: Requirement 4.7-1: Limit the risk of human casualty: The potential for human casualty is assumed for any object with an impacting kinetic energy in excess of 15 joules: a) For uncontrolled reentry, the risk of human casualty from surviving debris shall not exceed 0.0001 (1:10,000) (Requirement 56626). Summary Analysis Results: DAS v2.0.2 reports that PATHFINDER is compliant with the requirement. According to DAS calculations, there is a low probability that some1 spacecraft components (primary mirror, a machined disk of Invar, and machined blocks of aluminum) may reach the ground (see DAS input data below for input parameters). However, the DAS software does not currently allow explicit modeling of a the specific geometries for these components, so these numbers are expected to be larger than anticipated due to conservatism in the inputs provided to DAS. Total human casualty probability is reported by the DAS software as 1:31,500 for each Pathfinder satellite. This is expected to represent the absolute maximum casualty risk, as calculated with DAS's limited modeling capability. Analysis (per DAS v2.0.2): 11 19 2014; 10:25:39AM DAS Application Started 11 19 2014; 10:25:39AM Opened Project U:\Orbital Debris assessment\ 11 19 2014; 10:25:44AM Opened Project U:\Orbital Debris assessment\ 11 19 2014; 10:25:48AM Processing Requirement 4.3-1: Return Status : Not Run ===================== No Project Data Available ===================== =============== End of Requirement 4.3-1 =============== 11 19 2014; 10:25:55AM Processing Requirement 4.3-2: Return Status : Passed ===================== No Project Data Available ===================== =============== End of Requirement 4.3-2 =============== 11 19 2014; 10:25:57AM Requirement 4.4-3: Compliant =============== End of Requirement 4.4-3 =============== 11 19 2014; 10:26:00AM Processing Requirement 4.5-1: Return Status : Passed ============== 1 Other components that were modeled (i.e. wire harnesses, PM struts, shim, etc.) are not likely to survive reentry due to the inability to accurately model these with sufficient fidelity within the limitations imposed by DAS. Even with these components accounted for, PATHFINDER is still compliant with this requirement. Page 17$

Pathfinder-1 & -2 Orbital Debris Assessment Report (ODAR)

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

**INPUT**

Space Structure Name = SCOUTv1.001
Space Structure Type = Payload
Perigee Altitude = 450.000000 (km)
Apogee Altitude = 500.000000 (km)
Inclination = 97.400000 (deg)
RAAN = 0.000000 (deg)
Argument of Perigee = 0.000000 (deg)
Mean Anomaly = 0.000000 (deg)
Final Area-To-Mass Ratio = 0.004700 (m^2/kg)
Start Year = 2015.750000 (yr)
Initial Mass = 45.620000 (kg)
Final Mass = 41.820000 (kg)
Duration = 3.000000 (yr)
Station-Kept = True
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

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

=============== End of Requirement 4.5-1 ===============
11 19 2014; 10:27:34AM Requirement 4.5-2: Compliant

==================================================
Spacecraft = SCOUTv1.001
Critical Surface = CORTEX+X
==================================================

**INPUT**

Apogee Altitude = 500.000000 (km)
Perigee Altitude = 450.000000 (km)
Orbital Inclination = 97.400000 (deg)
RAAN = 0.000000 (deg)
Argument of Perigee = 0.000000 (deg)
Mean Anomaly = 0.000000 (deg)
Final Area-To-Mass = 0.004700 (m^2/kg)
Initial Mass = 41.820000 (kg)
Final Mass = 41.820000 (kg)

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Pathfinder-1 & -2 Orbital Debris Assessment Report (ODAR)

Station Kept = Yes
Start Year = 2015.750000 (yr)
Duration = 3.000000 (yr)
Orientation = Random Tumbling
CS Areal Density = 0.885000 (g/cm^2)
CS Surface Area = 0.020000 (m^2)
Vector = (0.000000 (u), 0.000000 (v), 0.000000 (w))
CS Pressurized = No
Outer Wall 1 Density: 0.433000 (g/cm^2) Separation: 0.400000 (cm)

**OUTPUT**

Probabilty of Penitration = 0.001586
Returned Error Message: Normal Processing
Date Range Error Message: Normal Date Range

==================================================
Spacecraft = SCOUTv1.001
Critical Surface = CORTEX+Y
==================================================

**INPUT**

Apogee Altitude = 500.000000 (km)
Perigee Altitude = 450.000000 (km)
Orbital Inclination = 97.400000 (deg)
RAAN = 0.000000 (deg)
Argument of Perigee = 0.000000 (deg)
Mean Anomaly = 0.000000 (deg)
Final Area-To-Mass = 0.004700 (m^2/kg)
Initial Mass = 41.820000 (kg)
Final Mass = 41.820000 (kg)
Station Kept = Yes
Start Year = 2015.750000 (yr)
Duration = 3.000000 (yr)
Orientation = Random Tumbling
CS Areal Density = 0.885000 (g/cm^2)
CS Surface Area = 0.020000 (m^2)
Vector = (0.000000 (u), 0.000000 (v), 0.000000 (w))
CS Pressurized = No
Outer Wall 1 Density: 0.433000 (g/cm^2) Separation: 1.800000 (cm)

**OUTPUT**

Probabilty of Penitration = 0.000089
Returned Error Message: Normal Processing
Date Range Error Message: Normal Date Range

==================================================
Spacecraft = SCOUTv1.001
Critical Surface = Battery+X
==================================================

**INPUT**

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Pathfinder-1 & -2 Orbital Debris Assessment Report (ODAR)

Apogee Altitude = 500.000000 (km)
Perigee Altitude = 450.000000 (km)
Orbital Inclination = 97.400000 (deg)
RAAN = 0.000000 (deg)
Argument of Perigee = 0.000000 (deg)
Mean Anomaly = 0.000000 (deg)
Final Area-To-Mass = 0.004700 (m^2/kg)
Initial Mass = 41.820000 (kg)
Final Mass = 41.820000 (kg)
Station Kept = Yes
Start Year = 2015.750000 (yr)
Duration = 3.000000 (yr)
Orientation = Random Tumbling
CS Areal Density = 0.658000 (g/cm^2)
CS Surface Area = 0.012000 (m^2)
Vector = (0.000000 (u), 0.000000 (v), 0.000000 (w))
CS Pressurized = No
Outer Wall 1 Density: 0.433000 (g/cm^2) Separation: 1.600000 (cm)

**OUTPUT**

Probabilty of Penitration = 0.000099
Returned Error Message: Normal Processing
Date Range Error Message: Normal Date Range

==================================================
Spacecraft = SCOUTv1.001
Critical Surface = Battery-Y
==================================================

**INPUT**

Apogee Altitude = 500.000000 (km)
Perigee Altitude = 450.000000 (km)
Orbital Inclination = 97.400000 (deg)
RAAN = 0.000000 (deg)
Argument of Perigee = 0.000000 (deg)
Mean Anomaly = 0.000000 (deg)
Final Area-To-Mass = 0.004700 (m^2/kg)
Initial Mass = 41.820000 (kg)
Final Mass = 41.820000 (kg)
Station Kept = Yes
Start Year = 2015.750000 (yr)
Duration = 3.000000 (yr)
Orientation = Random Tumbling
CS Areal Density = 0.658000 (g/cm^2)
CS Surface Area = 0.007000 (m^2)
Vector = (0.000000 (u), 0.000000 (v), 0.000000 (w))
CS Pressurized = No
Outer Wall 1 Density: 0.100000 (g/cm^2) Separation: 3.100000 (cm)

**OUTPUT**

Probabilty of Penitration = 0.000132
Returned Error Message: Normal Processing

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Pathfinder-1 & -2 Orbital Debris Assessment Report (ODAR)

Date Range Error Message: Normal Date Range

==================================================
Spacecraft = SCOUTv1.001
Critical Surface = Tank+Y
==================================================

**INPUT**

Apogee Altitude = 500.000000 (km)
Perigee Altitude = 450.000000 (km)
Orbital Inclination = 97.400000 (deg)
RAAN = 0.000000 (deg)
Argument of Perigee = 0.000000 (deg)
Mean Anomaly = 0.000000 (deg)
Final Area-To-Mass = 0.004700 (m^2/kg)
Initial Mass = 41.820000 (kg)
Final Mass = 41.820000 (kg)
Station Kept = Yes
Start Year = 2015.750000 (yr)
Duration = 3.000000 (yr)
Orientation = Random Tumbling
CS Areal Density = 1.080000 (g/cm^2)
CS Surface Area = 0.038720 (m^2)
Vector = (0.000000 (u), 0.000000 (v), 0.000000 (w))
CS Pressurized = Yes
Outer Wall 1 Density: 0.433000 (g/cm^2) Separation: 7.300000 (cm)

**OUTPUT**

Probabilty of Penitration = 0.000262
Returned Error Message: Normal Processing
Date Range Error Message: Normal Date Range

==================================================
Spacecraft = SCOUTv1.001
Critical Surface = Tank-Y
==================================================

**INPUT**

Apogee Altitude = 500.000000 (km)
Perigee Altitude = 450.000000 (km)
Orbital Inclination = 97.400000 (deg)
RAAN = 0.000000 (deg)
Argument of Perigee = 0.000000 (deg)
Mean Anomaly = 0.000000 (deg)
Final Area-To-Mass = 0.004700 (m^2/kg)
Initial Mass = 41.820000 (kg)
Final Mass = 41.820000 (kg)
Station Kept = Yes
Start Year = 2015.750000 (yr)
Duration = 3.000000 (yr)
Orientation = Random Tumbling
CS Areal Density = 1.080000 (g/cm^2)

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Pathfinder-1 & -2 Orbital Debris Assessment Report (ODAR)

CS Surface Area = 0.038720 (m^2)
Vector = (0.000000 (u), 0.000000 (v), 0.000000 (w))
CS Pressurized = Yes
Outer Wall 1 Density: 0.433000 (g/cm^2) Separation: 7.300000 (cm)

**OUTPUT**

Probabilty of Penitration = 0.000262
Returned Error Message: Normal Processing
Date Range Error Message: Normal Date Range

==================================================
Spacecraft = SCOUTv1.001
Critical Surface = Tank+X_sect1
==================================================

**INPUT**

Apogee Altitude = 500.000000 (km)
Perigee Altitude = 450.000000 (km)
Orbital Inclination = 97.400000 (deg)
RAAN = 0.000000 (deg)
Argument of Perigee = 0.000000 (deg)
Mean Anomaly = 0.000000 (deg)
Final Area-To-Mass = 0.004700 (m^2/kg)
Initial Mass = 41.820000 (kg)
Final Mass = 41.820000 (kg)
Station Kept = Yes
Start Year = 2015.750000 (yr)
Duration = 3.000000 (yr)
Orientation = Random Tumbling
CS Areal Density = 1.080000 (g/cm^2)
CS Surface Area = 0.004090 (m^2)
Vector = (0.000000 (u), 0.000000 (v), 0.000000 (w))
CS Pressurized = Yes
Outer Wall 1 Density: 0.433000 (g/cm^2) Separation: 0.470000 (cm)

**OUTPUT**

Probabilty of Penitration = 0.000992
Returned Error Message: Normal Processing
Date Range Error Message: Normal Date Range

==================================================
Spacecraft = SCOUTv1.001
Critical Surface = Tank+X_sect2
==================================================

**INPUT**

Apogee Altitude = 500.000000 (km)
Perigee Altitude = 450.000000 (km)
Orbital Inclination = 97.400000 (deg)
RAAN = 0.000000 (deg)
Argument of Perigee = 0.000000 (deg)

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Pathfinder-1 & -2 Orbital Debris Assessment Report (ODAR)

Mean Anomaly = 0.000000 (deg)
Final Area-To-Mass = 0.004700 (m^2/kg)
Initial Mass = 41.820000 (kg)
Final Mass = 41.820000 (kg)
Station Kept = Yes
Start Year = 2015.750000 (yr)
Duration = 3.000000 (yr)
Orientation = Random Tumbling
CS Areal Density = 1.080000 (g/cm^2)
CS Surface Area = 0.008180 (m^2)
Vector = (0.000000 (u), 0.000000 (v), 0.000000 (w))
CS Pressurized = Yes
Outer Wall 1 Density: 0.433000 (g/cm^2) Separation: 0.850000 (cm)

**OUTPUT**

Probabilty of Penitration = 0.000645
Returned Error Message: Normal Processing
Date Range Error Message: Normal Date Range

==================================================
Spacecraft = SCOUTv1.001
Critical Surface = Tank+X_sect3
==================================================

**INPUT**

Apogee Altitude = 500.000000 (km)
Perigee Altitude = 450.000000 (km)
Orbital Inclination = 97.400000 (deg)
RAAN = 0.000000 (deg)
Argument of Perigee = 0.000000 (deg)
Mean Anomaly = 0.000000 (deg)
Final Area-To-Mass = 0.004700 (m^2/kg)
Initial Mass = 41.820000 (kg)
Final Mass = 41.820000 (kg)
Station Kept = Yes
Start Year = 2015.750000 (yr)
Duration = 3.000000 (yr)
Orientation = Random Tumbling
CS Areal Density = 1.080000 (g/cm^2)
CS Surface Area = 0.008180 (m^2)
Vector = (0.000000 (u), 0.000000 (v), 0.000000 (w))
CS Pressurized = Yes
Outer Wall 1 Density: 0.433000 (g/cm^2) Separation: 1.970000 (cm)

**OUTPUT**

Probabilty of Penitration = 0.000113
Returned Error Message: Normal Processing
Date Range Error Message: Normal Date Range

==================================================
Spacecraft = SCOUTv1.001
Critical Surface = Tank+X_sect4

Page 23

Pathfinder-1 & -2 Orbital Debris Assessment Report (ODAR)

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

**INPUT**

Apogee Altitude = 500.000000 (km)
Perigee Altitude = 450.000000 (km)
Orbital Inclination = 97.400000 (deg)
RAAN = 0.000000 (deg)
Argument of Perigee = 0.000000 (deg)
Mean Anomaly = 0.000000 (deg)
Final Area-To-Mass = 0.004700 (m^2/kg)
Initial Mass = 41.820000 (kg)
Final Mass = 41.820000 (kg)
Station Kept = Yes
Start Year = 2015.750000 (yr)
Duration = 3.000000 (yr)
Orientation = Random Tumbling
CS Areal Density = 1.080000 (g/cm^2)
CS Surface Area = 0.008180 (m^2)
Vector = (0.000000 (u), 0.000000 (v), 0.000000 (w))
CS Pressurized = Yes
Outer Wall 1 Density: 0.433000 (g/cm^2) Separation: 3.710000 (cm)

**OUTPUT**

Probabilty of Penitration = 0.000057
Returned Error Message: Normal Processing
Date Range Error Message: Normal Date Range

==================================================
Spacecraft = SCOUTv1.001
Critical Surface = Tank+X_sect5
==================================================

**INPUT**

Apogee Altitude = 500.000000 (km)
Perigee Altitude = 450.000000 (km)
Orbital Inclination = 97.400000 (deg)
RAAN = 0.000000 (deg)
Argument of Perigee = 0.000000 (deg)
Mean Anomaly = 0.000000 (deg)
Final Area-To-Mass = 0.004700 (m^2/kg)
Initial Mass = 41.820000 (kg)
Final Mass = 41.820000 (kg)
Station Kept = Yes
Start Year = 2015.750000 (yr)
Duration = 3.000000 (yr)
Orientation = Random Tumbling
CS Areal Density = 1.080000 (g/cm^2)
CS Surface Area = 0.008180 (m^2)
Vector = (0.000000 (u), 0.000000 (v), 0.000000 (w))
CS Pressurized = Yes
Outer Wall 1 Density: 0.433000 (g/cm^2) Separation: 5.890000 (cm)

Page 24

Pathfinder-1 & -2 Orbital Debris Assessment Report (ODAR)

**OUTPUT**

Probabilty of Penitration = 0.000055
Returned Error Message: Normal Processing
Date Range Error Message: Normal Date Range

==================================================
Spacecraft = SCOUTv1.001
Critical Surface = Tank-X_sect1
==================================================

**INPUT**

Apogee Altitude = 500.000000 (km)
Perigee Altitude = 450.000000 (km)
Orbital Inclination = 97.400000 (deg)
RAAN = 0.000000 (deg)
Argument of Perigee = 0.000000 (deg)
Mean Anomaly = 0.000000 (deg)
Final Area-To-Mass = 0.004700 (m^2/kg)
Initial Mass = 41.820000 (kg)
Final Mass = 41.820000 (kg)
Station Kept = Yes
Start Year = 2015.750000 (yr)
Duration = 3.000000 (yr)
Orientation = Random Tumbling
CS Areal Density = 1.080000 (g/cm^2)
CS Surface Area = 0.004090 (m^2)
Vector = (0.000000 (u), 0.000000 (v), 0.000000 (w))
CS Pressurized = Yes
Outer Wall 1 Density: 0.433000 (g/cm^2) Separation: 0.470000 (cm)

**OUTPUT**

Probabilty of Penitration = 0.000992
Returned Error Message: Normal Processing
Date Range Error Message: Normal Date Range

==================================================
Spacecraft = SCOUTv1.001
Critical Surface = Tank-X_sect2
==================================================

**INPUT**

Apogee Altitude = 500.000000 (km)
Perigee Altitude = 450.000000 (km)
Orbital Inclination = 97.400000 (deg)
RAAN = 0.000000 (deg)
Argument of Perigee = 0.000000 (deg)
Mean Anomaly = 0.000000 (deg)
Final Area-To-Mass = 0.004700 (m^2/kg)
Initial Mass = 41.820000 (kg)
Final Mass = 41.820000 (kg)
Station Kept = Yes

Page 25

Pathfinder-1 & -2 Orbital Debris Assessment Report (ODAR)

Start Year = 2015.750000 (yr)
Duration = 3.000000 (yr)
Orientation = Random Tumbling
CS Areal Density = 1.080000 (g/cm^2)
CS Surface Area = 0.008180 (m^2)
Vector = (0.000000 (u), 0.000000 (v), 0.000000 (w))
CS Pressurized = Yes
Outer Wall 1 Density: 0.433000 (g/cm^2) Separation: 0.850000 (cm)

**OUTPUT**

Probabilty of Penitration = 0.000645
Returned Error Message: Normal Processing
Date Range Error Message: Normal Date Range

==================================================
Spacecraft = SCOUTv1.001
Critical Surface = Tank-X_sect3
==================================================

**INPUT**

Apogee Altitude = 500.000000 (km)
Perigee Altitude = 450.000000 (km)
Orbital Inclination = 97.400000 (deg)
RAAN = 0.000000 (deg)
Argument of Perigee = 0.000000 (deg)
Mean Anomaly = 0.000000 (deg)
Final Area-To-Mass = 0.004700 (m^2/kg)
Initial Mass = 41.820000 (kg)
Final Mass = 41.820000 (kg)
Station Kept = Yes
Start Year = 2015.750000 (yr)
Duration = 3.000000 (yr)
Orientation = Random Tumbling
CS Areal Density = 1.080000 (g/cm^2)
CS Surface Area = 0.008180 (m^2)
Vector = (0.000000 (u), 0.000000 (v), 0.000000 (w))
CS Pressurized = Yes
Outer Wall 1 Density: 0.433000 (g/cm^2) Separation: 1.970000 (cm)

**OUTPUT**

Probabilty of Penitration = 0.000113
Returned Error Message: Normal Processing
Date Range Error Message: Normal Date Range

==================================================
Spacecraft = SCOUTv1.001
Critical Surface = Tank-X_sect4
==================================================

**INPUT**

Apogee Altitude = 500.000000 (km)

Page 26

Pathfinder-1 & -2 Orbital Debris Assessment Report (ODAR)

Perigee Altitude = 450.000000 (km)
Orbital Inclination = 97.400000 (deg)
RAAN = 0.000000 (deg)
Argument of Perigee = 0.000000 (deg)
Mean Anomaly = 0.000000 (deg)
Final Area-To-Mass = 0.004700 (m^2/kg)
Initial Mass = 41.820000 (kg)
Final Mass = 41.820000 (kg)
Station Kept = Yes
Start Year = 2015.750000 (yr)
Duration = 3.000000 (yr)
Orientation = Random Tumbling
CS Areal Density = 1.080000 (g/cm^2)
CS Surface Area = 0.008180 (m^2)
Vector = (0.000000 (u), 0.000000 (v), 0.000000 (w))
CS Pressurized = Yes
Outer Wall 1 Density: 0.433000 (g/cm^2) Separation: 3.710000 (cm)

**OUTPUT**

Probabilty of Penitration = 0.000057
Returned Error Message: Normal Processing
Date Range Error Message: Normal Date Range

==================================================
Spacecraft = SCOUTv1.001
Critical Surface = Tank-X_sect5
==================================================

**INPUT**

Apogee Altitude = 500.000000 (km)
Perigee Altitude = 450.000000 (km)
Orbital Inclination = 97.400000 (deg)
RAAN = 0.000000 (deg)
Argument of Perigee = 0.000000 (deg)
Mean Anomaly = 0.000000 (deg)
Final Area-To-Mass = 0.004700 (m^2/kg)
Initial Mass = 41.820000 (kg)
Final Mass = 41.820000 (kg)
Station Kept = Yes
Start Year = 2015.750000 (yr)
Duration = 3.000000 (yr)
Orientation = Random Tumbling
CS Areal Density = 1.080000 (g/cm^2)
CS Surface Area = 0.008180 (m^2)
Vector = (0.000000 (u), 0.000000 (v), 0.000000 (w))
CS Pressurized = Yes
Outer Wall 1 Density: 0.433000 (g/cm^2) Separation: 5.890000 (cm)

**OUTPUT**

Probabilty of Penitration = 0.000055
Returned Error Message: Normal Processing
Date Range Error Message: Normal Date Range

Page 27

Pathfinder-1 & -2 Orbital Debris Assessment Report (ODAR)

11 19 2014; 10:28:11AM Processing Requirement 4.6 Return Status : Passed

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

**INPUT**

Space Structure Name = SCOUTv1.001
Space Structure Type = Payload

Perigee Altitude = 450.000000 (km)
Apogee Altitude = 500.000000 (km)
Inclination = 97.400000 (deg)
RAAN = 0.000000 (deg)
Argument of Perigee = 0.000000 (deg)
Mean Anomaly = 0.000000 (deg)
Area-To-Mass Ratio = 0.004700 (m^2/kg)
Start Year = 2015.750000 (yr)
Initial Mass = 45.620000 (kg)
Final Mass = 41.820000 (kg)
Duration = 3.000000 (yr)
Station Kept = True
Abandoned = True
PMD Perigee Altitude = 450.000000 (km)
PMD Apogee Altitude = 500.000000 (km)
PMD Inclination = 97.400000 (deg)
PMD RAAN = 0.000000 (deg)
PMD Argument of Perigee = 0.000000 (deg)
PMD Mean Anomaly = 0.000000 (deg)

**OUTPUT**

Suggested Perigee Altitude = 450.000000 (km)
Suggested Apogee Altitude = 500.000000 (km)
Returned Error Message = Passes LEO reentry orbit criteria.

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

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

=============== End of Requirement 4.6 ===============
11 19 2014; 10:29:04AM *********Processing Requirement 4.7-1
Return Status : Passed

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

name = SCOUTv1.001
quantity = 1
parent = 0

Page 28

Pathfinder-1 & -2 Orbital Debris Assessment Report (ODAR)

materialID = 5
type = Box
Aero Mass = 41.820000
Thermal Mass = 41.820000
Diameter/Width = 0.400000
Length = 0.850000
Height = 0.400000

name = Shell
quantity = 1
parent = 1
materialID = 27
type = Cylinder
Aero Mass = 0.300800
Thermal Mass = 0.300800
Diameter/Width = 0.280000
Length = 0.390000

name = SM baffle
quantity = 1
parent = 1
materialID = 8
type = Cylinder
Aero Mass = 0.058100
Thermal Mass = 0.058100
Diameter/Width = 0.074000
Length = 0.046000

name = SM cover
quantity = 1
parent = 1
materialID = 8
type = Cylinder
Aero Mass = 0.064300
Thermal Mass = 0.064300
Diameter/Width = 0.070000
Length = 0.023000

name = PM
quantity = 1
parent = 1
materialID = -1
type = Flat Plate
Aero Mass = 1.036500
Thermal Mass = 1.036500
Diameter/Width = 0.223300
Length = 0.223300

name = PM baffle
quantity = 1
parent = 1
materialID = 8
type = Cylinder
Aero Mass = 0.234800
Thermal Mass = 0.234800

Page 29

Pathfinder-1 & -2 Orbital Debris Assessment Report (ODAR)

Diameter/Width = 0.116000
Length = 0.186500

name = SM spider
quantity = 1
parent = 1
materialID = 72
type = Flat Plate
Aero Mass = 0.432300
Thermal Mass = 0.432300
Diameter/Width = 0.100000
Length = 0.100000

name = Shutter Housing
quantity = 1
parent = 1
materialID = 72
type = Box
Aero Mass = 0.784600
Thermal Mass = 0.784600
Diameter/Width = 0.100000
Length = 0.100000
Height = 0.024200

name = AMS upper plate
quantity = 1
parent = 1
materialID = 27
type = Flat Plate
Aero Mass = 0.103000
Thermal Mass = 0.103000
Diameter/Width = 0.270000
Length = 0.270000

name = AMS core structure
quantity = 1
parent = 1
materialID = 7
type = Flat Plate
Aero Mass = 0.090400
Thermal Mass = 0.090400
Diameter/Width = 0.270000
Length = 0.270000

name = AMS lower plate
quantity = 1
parent = 1
materialID = 27
type = Flat Plate
Aero Mass = 0.102900
Thermal Mass = 0.102900
Diameter/Width = 0.270000
Length = 0.270000

name = Lens Tube Shim

Page 30

Pathfinder-1 & -2 Orbital Debris Assessment Report (ODAR)

quantity = 1
parent = 1
materialID = 54
type = Flat Plate
Aero Mass = 0.023200
Thermal Mass = 0.023200
Diameter/Width = 0.020000
Length = 0.200000

name = PM Baffle AMS Lock Ring
quantity = 1
parent = 1
materialID = 8
type = Flat Plate
Aero Mass = 0.015600
Thermal Mass = 0.015600
Diameter/Width = 0.020000
Length = 0.200000

name = Main PM Mount Flexure
quantity = 3
parent = 1
materialID = 9
type = Flat Plate
Aero Mass = 0.089300
Thermal Mass = 0.089300
Diameter/Width = 0.101000
Length = 0.138000

name = PM struts
quantity = 3
parent = 1
materialID = 72
type = Box
Aero Mass = 0.032900
Thermal Mass = 0.032900
Diameter/Width = 0.030000
Length = 0.030000
Height = 0.010000

name = Camera
quantity = 1
parent = 1
materialID = 5
type = Box
Aero Mass = 0.328000
Thermal Mass = 0.328000
Diameter/Width = 0.060000
Length = 0.060000
Height = 0.045000

name = MLI
quantity = 1
parent = 1
materialID = 44

Page 31

Pathfinder-1 & -2 Orbital Debris Assessment Report (ODAR)

type = Cylinder
Aero Mass = 0.293300
Thermal Mass = 0.293300
Diameter/Width = 0.300000
Length = 0.450000

name = Propulsion Deck Base Plate
quantity = 1
parent = 1
materialID = 8
type = Flat Plate
Aero Mass = 2.987600
Thermal Mass = 2.987600
Diameter/Width = 0.400000
Length = 0.400000

name = Avionics Deck Base Plate
quantity = 1
parent = 1
materialID = 8
type = Flat Plate
Aero Mass = 2.283700
Thermal Mass = 2.283700
Diameter/Width = 0.400000
Length = 0.400000

name = Optical Bench Base Plate
quantity = 1
parent = 1
materialID = 8
type = Flat Plate
Aero Mass = 1.459100
Thermal Mass = 1.459100
Diameter/Width = 0.400000
Length = 0.400000

name = Antenna Deck Base Plate
quantity = 1
parent = 1
materialID = 8
type = Flat Plate
Aero Mass = 0.812200
Thermal Mass = 0.812200
Diameter/Width = 0.400000
Length = 0.400000

name = Antenna Deck Extension
quantity = 1
parent = 1
materialID = 8
type = Flat Plate
Aero Mass = 0.052700
Thermal Mass = 0.052700
Diameter/Width = 0.029000
Length = 0.400000

Page 32

Pathfinder-1 & -2 Orbital Debris Assessment Report (ODAR)

Thermal Mass = 0.031200
Diameter/Width = 0.024000
Length = 0.032000

name = Pin Piller Bracket
quantity = 1
parent = 1
materialID = 8
type = Box
Aero Mass = 0.037800
Thermal Mass = 0.037800
Diameter/Width = 0.022500
Length = 0.100000
Height = 0.015000

name = Fasteners
quantity = 1600
parent = 1
materialID = 54
type = Cylinder
Aero Mass = 0.001250
Thermal Mass = 0.001250
Diameter/Width = 0.006000
Length = 0.020000

name = Cortex
quantity = 1
parent = 1
materialID = 8
type = Box
Aero Mass = 2.867500
Thermal Mass = 2.867500
Diameter/Width = 0.151000
Length = 0.161000
Height = 0.106000

name = Reaction Wheels
quantity = 3
parent = 1
materialID = 54
type = Cylinder
Aero Mass = 0.228400
Thermal Mass = 0.228400
Diameter/Width = 0.063000
Length = 0.025400

name = Reaction Wheel Bracket
quantity = 1
parent = 1
materialID = 8
type = Box
Aero Mass = 0.204800
Thermal Mass = 0.204800
Diameter/Width = 0.075000
Length = 0.090000

Page 35

Pathfinder-1 & -2 Orbital Debris Assessment Report (ODAR)

name = GPS Antenna Assembly
quantity = 1
parent = 1
materialID = 8
type = Box
Aero Mass = 0.043400
Thermal Mass = 0.043400
Diameter/Width = 0.030000
Length = 0.030000
Height = 0.025400

name = Solar Panel 1
quantity = 6
parent = 1
materialID = 50
type = Flat Plate
Aero Mass = 0.319100
Thermal Mass = 0.319100
Diameter/Width = 0.180000
Length = 0.340000

name = Battery
quantity = 1
parent = 1
materialID = 8
type = Box
Aero Mass = 2.196200
Thermal Mass = 2.196200
Diameter/Width = 0.108000
Length = 0.178000
Height = 0.065000

name = Harnesses
quantity = 1
parent = 1
materialID = 19
type = Cylinder
Aero Mass = 1.524900
Thermal Mass = 1.524900
Diameter/Width = 0.005100
Length = 8.500000

name = Tank
quantity = 2
parent = 1
materialID = 8
type = Cylinder
Aero Mass = 1.322900
Thermal Mass = 1.322900
Diameter/Width = 0.156000
Length = 0.238000

name = HEX
quantity = 1

Page 37

Pathfinder-1 & -2 Orbital Debris Assessment Report (ODAR)

parent = 1
materialID = 5
type = Box
Aero Mass = 0.186400
Thermal Mass = 0.186400
Diameter/Width = 0.054000
Length = 0.114000
Height = 0.023000

name = Propulsion Manifold Assembly
quantity = 1
parent = 1
materialID = 8
type = Box
Aero Mass = 0.296700
Thermal Mass = 0.296700
Diameter/Width = 0.065000
Length = 0.075000
Height = 0.030000

name = Tubing Run 1
quantity = 4
parent = 1
materialID = 54
type = Cylinder
Aero Mass = 0.015500
Thermal Mass = 0.015500
Diameter/Width = 0.002000
Length = 0.800000

name = Tube Fitting
quantity = 8
parent = 1
materialID = 54
type = Sphere
Aero Mass = 0.034600
Thermal Mass = 0.034600
Diameter/Width = 0.100000

name = SM spider fitting
quantity = 9
parent = 1
materialID = 5
type = Cylinder
Aero Mass = 0.052000
Thermal Mass = 0.052000
Diameter/Width = 0.041000
Length = 0.015000

name = HEX Insulation
quantity = 1
parent = 1
materialID = 76
type = Flat Plate
Aero Mass = 0.020900

Page 38

Pathfinder-1 & -2 Orbital Debris Assessment Report (ODAR)

Thermal Mass = 0.020900
Diameter/Width = 0.054000
Length = 0.114000

name = HEX Bracket
quantity = 1
parent = 1
materialID = 66
type = Flat Plate
Aero Mass = 0.035000
Thermal Mass = 0.035000
Diameter/Width = 0.089000
Length = 0.143000

name = UHF Antenna Assembly
quantity = 1
parent = 1
materialID = 8
type = Cylinder
Aero Mass = 0.067100
Thermal Mass = 0.067100
Diameter/Width = 0.025200
Length = 0.050000

name = MLB flyaway portion
quantity = 1
parent = 1
materialID = 9
type = Box
Aero Mass = 0.473700
Thermal Mass = 0.473700
Diameter/Width = 0.184000
Length = 0.185000
Height = 0.005000

name = Antenna Deck Angle Brackets
quantity = 8
parent = 1
materialID = 8
type = Box
Aero Mass = 0.007400
Thermal Mass = 0.007400
Diameter/Width = 0.020000
Length = 0.130000
Height = 0.001100

name = CORTEX thermal pad
quantity = 1
parent = 1
materialID = -4
type = Flat Plate
Aero Mass = 0.068400
Thermal Mass = 0.068400
Diameter/Width = 0.151000
Length = 0.161000

Page 39

Pathfinder-1 & -2 Orbital Debris Assessment Report (ODAR)

parent = 1
materialID = 5
type = Box
Aero Mass = 0.089200
Thermal Mass = 0.089200
Diameter/Width = 0.070000
Length = 0.080000
Height = 0.017000

name = X-band radio
quantity = 1
parent = 1
materialID = 5
type = Box
Aero Mass = 1.100000
Thermal Mass = 1.100000
Diameter/Width = 0.100000
Length = 0.170000
Height = 0.040000

name = X-band thermal pad
quantity = 1
parent = 1
materialID = 27
type = Flat Plate
Aero Mass = 0.009100
Thermal Mass = 0.009100
Diameter/Width = 0.100000
Length = 0.170000

name = X-band antenna
quantity = 1
parent = 1
materialID = 8
type = Box
Aero Mass = 0.253000
Thermal Mass = 0.253000
Diameter/Width = 0.130000
Length = 0.180000
Height = 0.020000

name = X-band antenna bracket
quantity = 1
parent = 1
materialID = 8
type = Flat Plate
Aero Mass = 0.096500
Thermal Mass = 0.096500
Diameter/Width = 0.115000
Length = 0.190000

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

name = SCOUTv1.001

Page 41

Pathfinder-1 & -2 Orbital Debris Assessment Report (ODAR)

Demise Altitude = 77.994308
Debris Casualty Area = 0.000000
Impact Kinetic Energy = 0.000000

*************************************
name = Shell
Demise Altitude = 77.852847
Debris Casualty Area = 0.000000
Impact Kinetic Energy = 0.000000

*************************************
name = SM baffle
Demise Altitude = 76.695441
Debris Casualty Area = 0.000000
Impact Kinetic Energy = 0.000000

*************************************
name = SM cover
Demise Altitude = 75.898074
Debris Casualty Area = 0.000000
Impact Kinetic Energy = 0.000000

*************************************
name = PM
Demise Altitude = 0.000000
Debris Casualty Area = 0.677823
Impact Kinetic Energy = 352.276215

*************************************
name = PM baffle
Demise Altitude = 76.591527
Debris Casualty Area = 0.000000
Impact Kinetic Energy = 0.000000

*************************************
name = SM spider
Demise Altitude = 0.000000
Debris Casualty Area = 0.490000
Impact Kinetic Energy = 306.363739

*************************************
name = Shutter Housing
Demise Altitude = 0.000000
Debris Casualty Area = 0.460774
Impact Kinetic Energy = 943.253662

*************************************
name = AMS upper plate
Demise Altitude = 77.900097
Debris Casualty Area = 0.000000
Impact Kinetic Energy = 0.000000

*************************************
name = AMS core structure
Demise Altitude = 77.552058

Page 42

Pathfinder-1 & -2 Orbital Debris Assessment Report (ODAR)

Debris Casualty Area = 0.000000
Impact Kinetic Energy = 0.000000

*************************************
name = AMS lower plate
Demise Altitude = 77.900097
Debris Casualty Area = 0.000000
Impact Kinetic Energy = 0.000000

*************************************
name = Lens Tube Shim
Demise Altitude = 0.000000
Debris Casualty Area = 0.439895
Impact Kinetic Energy = 2.196004

*************************************
name = PM Baffle AMS Lock Ring
Demise Altitude = 77.442222
Debris Casualty Area = 0.000000
Impact Kinetic Energy = 0.000000

*************************************
name = Main PM Mount Flexure
Demise Altitude = 76.783808
Debris Casualty Area = 0.000000
Impact Kinetic Energy = 0.000000

*************************************
name = PM struts
Demise Altitude = 0.000000
Debris Casualty Area = 1.169982
Impact Kinetic Energy = 16.326183

*************************************
name = Camera
Demise Altitude = 70.819613
Debris Casualty Area = 0.000000
Impact Kinetic Energy = 0.000000

*************************************
name = MLI
Demise Altitude = 77.886566
Debris Casualty Area = 0.000000
Impact Kinetic Energy = 0.000000

*************************************
name = Propulsion Deck Base Plate
Demise Altitude = 68.448769
Debris Casualty Area = 0.000000
Impact Kinetic Energy = 0.000000

*************************************
name = Avionics Deck Base Plate
Demise Altitude = 70.740699
Debris Casualty Area = 0.000000

Page 43

Pathfinder-1 & -2 Orbital Debris Assessment Report (ODAR)

name = Harnesses
Demise Altitude = 76.717301
Debris Casualty Area = 0.000000
Impact Kinetic Energy = 0.000000

*************************************
name = Tank
Demise Altitude = 72.991449
Debris Casualty Area = 0.000000
Impact Kinetic Energy = 0.000000

*************************************
name = HEX
Demise Altitude = 74.602339
Debris Casualty Area = 0.000000
Impact Kinetic Energy = 0.000000

*************************************
name = Propulsion Manifold Assembly
Demise Altitude = 72.103917
Debris Casualty Area = 0.000000
Impact Kinetic Energy = 0.000000

*************************************
name = Tubing Run 1
Demise Altitude = 77.353394
Debris Casualty Area = 0.000000
Impact Kinetic Energy = 0.000000

*************************************
name = Tube Fitting
Demise Altitude = 0.000000
Debris Casualty Area = 3.793610
Impact Kinetic Energy = 2.745913

*************************************
name = SM spider fitting
Demise Altitude = 73.930183
Debris Casualty Area = 0.000000
Impact Kinetic Energy = 0.000000

*************************************
name = HEX Insulation
Demise Altitude = 77.892566
Debris Casualty Area = 0.000000
Impact Kinetic Energy = 0.000000

*************************************
name = HEX Bracket
Demise Altitude = 0.000000
Debris Casualty Area = 0.508104
Impact Kinetic Energy = 1.570259

*************************************
name = UHF Antenna Assembly

Page 47

Pathfinder-1 & -2 Orbital Debris Assessment Report (ODAR)

Debris Casualty Area = 0.000000
Impact Kinetic Energy = 0.000000

*************************************
name = X-band radio
Demise Altitude = 69.227277
Debris Casualty Area = 0.000000
Impact Kinetic Energy = 0.000000

*************************************
name = X-band thermal pad
Demise Altitude = 77.974035
Debris Casualty Area = 0.000000
Impact Kinetic Energy = 0.000000

*************************************
name = X-band antenna
Demise Altitude = 75.897246
Debris Casualty Area = 0.000000
Impact Kinetic Energy = 0.000000

*************************************
name = X-band antenna bracket
Demise Altitude = 77.030441
Debris Casualty Area = 0.000000
Impact Kinetic Energy = 0.000000

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

=============== End of Requirement 4.7-1 ===============
11 19 2014; 10:32:42AM Project Data Saved To File

Requirements 4.7-1b, and 4.7-1c below are non-applicable requirements because
Pathfinder does not use controlled reentry.

4.7-1, b) NOT APPLICABLE. For controlled reentry, the selected trajectory shall
ensure that no surviving debris impact with a kinetic energy greater than 15 joules is
closer than 370 km from foreign landmasses, or is within 50 km from the continental
U.S., territories of the U.S., and the permanent ice pack of Antarctica (Requirement
56627).
4.7-1 c) NOT APPLICABLE. For controlled reentries, the product of the probability of
failure of the reentry burn (from Requirement 4.6-4.b) and the risk of human casualty
assuming uncontrolled reentry shall not exceed 0.0001 (1:10,000) (Requirement 56628).

ODAR Section 8: Assessment for Tether Missions
Not applicable. There are no tethers on the Pathfinder satellites.

Page 49

Pathfinder-1 & -2 Orbital Debris Assessment Report (ODAR)

END of ODAR for Pathfinder-1 and Pathfinder-2

Page 50

Document Created: 2014-12-10 10:36:49
Document Modified: 2014-12-10 10:36:49