ODAR Rev6

0108-EX-CM-2018 Text Documents

California Polytechnic State University

2018-05-25ELS_210235

Rev 6 5/24/2018 Orbital Debris Assessment for the IRVINE01 CubeSat per NASA-STD 8719.14A 1

IRVINEO1 Orbital Debris Assessment Report (ODAR) Signature Page lPuelo Brent Freeze, Technical lead, IRVINEO1 CubeSat 7 \7/ n/.\ Jennifer Blackie, Co n}umcatlons team leader Woodbridge High School Alicia Johnstone, Ground Station Manager, Cal Poly SLO

IRVINE01 Orbital Debris Assessment Report (ODAR) REFERENCES: A. NASA Procedural Requirements for Limiting Orbital Debris Generation, NPR 8715.6A, 5 February 2008 B. Process for Limiting Orbital Debris, NASA-STD-8719.14A, 25 May 2012 C. McKissock, Barbara, Patricia Loyselle, and Elisa Vogel. Guidelines on Lithium-ion Battery Use in Space Applications. Tech. no. RP-08-75. NASA Glenn Research Center Cleveland, Ohio D. UL Standard for Safety for Lithium Batteries, UL 1642. UL Standard. 4th ed. Northbrook, IL, Underwriters Laboratories, 2007 E. Kwas, Robert. Thermal Analysis of ELaNa-4 CubeSat Batteries, ELVL-2012-0043254; Nov 2012 F. Range Safety User Requirements Manual Volume 3- Launch Vehicles, Payloads, and Ground Support Systems Requirements, AFSCM 91-710 V3. G. UL Standard for Safety for Household and Commercial Batteries, UL 2054. UL Standard. 2nd ed. Northbrook, IL, Underwriters Laboratories, 2005 H. HQ OSMA Policy Memo/Email to 8719.14: CubeSat Battery Non-Passivation, Suzanne Aleman to Justin Treptow, 10, July 2014 3

IRVINE01 Orbital Debris Assessment Report (ODAR) Table 1: Orbital Debris Requirement Compliance Matrix Requirement Compliance Assessment Comments 4.3-1a Not applicable No planned debris release 4.3-1b Not applicable No planned debris release 4.3-2 Not applicable No planned debris release 4.4-1 Compliant On board energy source (batteries) incapable of debris- producing failure 4.4-2 Compliant On board energy source (batteries) incapable of debris- producing failure 4.4-3 Not applicable No planned breakups 4.4-4 Not applicable No planned breakups 4.5-1 Compliant 4.5-2 Compliant 4.6-1(a) Compliant Worst case lifetime 4.07 years 4.6-1(b) Not applicable 4.6-1(c) Not applicable 4.6-2 Not applicable 4.6-3 Not applicable 4.6-4 Not applicable Passive disposal 4.6-5 Compliant 4.7-1 Compliant Non-credible risk of human casualty 4.8-1 Compliant No planned tether release under IRVINE01 mission 4

IRVINE01 Orbital Debris Assessment Report (ODAR) ODAR Table of Contents Section 1 (Program Management and Mission Overview)..............................................................6 Section 2 (Spacecraft Description)..................................................................................................8 Section 3 (Assessment of Spacecraft Debris Released during Normal Operations).....................10 Section 4 (Assessment of Spacecraft Intentional Breakups and Potential for Explosions)...........11 Section 5 (Assessment of Spacecraft Potential for On-Orbit Collisions): ....................................12 Section 6 (Assessment of Spacecraft Post-mission Disposal Plans and Procedures)....................13 Section 7 (Assessment of Spacecraft Reentry Hazards)................................................................15 Section 8 (Assessment for Tether Missions).................................................................................19 5

IRVINE01 Orbital Debris Assessment Report (ODAR) ODAR Section 1: Program Management and Mission Overview Project Manager: Tinh Tran Foreign Government or Space Agency Participation: The Ecuadorian Space Agency (EXA) will provide many of the necessary parts for the CubeSat, including the batteries and the solar panels. Rocket Lab USA will control the launch vehicle, which will be launched from Mahia Peninsula, New Zealand. Schedule of Upcoming Mission Milestones: Mission kickoff date: March 1, 2016 Design review date: April 29, 2016 Delivery date: May 15, 2018 Tentative Launch Date: June 15, 2018 Mission Overview: IRVINE01 will be dispensed from a Rocket Lab 1U CubeSat dispenser into an estimated orbit of 500 km Apogee and 500 km Perigee with an inclination of 85 degrees. The mission is expected to remain in orbit for a maximum of up to 4.07 years. During this time, our payload will take pictures of celestial objects, such as the Moon and Venus, as well as collect other data using our sun sensors, GPS, and other necessary equipment. ODAR Summary: No debris released in normal operations; no credible scenario for breakups; the collision probability with other objects is compliant with NASA standards; and the estimated nominal decay lifetime due to atmospheric drag is under 25 years following operations. 6

IRVINE01 Orbital Debris Assessment Report (ODAR) Launch Vehicle and Launch Site: Electron Launch Vehicle, Mahia Peninsula, New Zealand Proposed Launch Date: June 15, 2018 Mission Duration: Normal mission operations will take place until contact is lost, or some other mission detrimental factor causes a failure of essential systems. The natural decay time of the CubeSat is under 4.07 years. Launch and deployment profile, including all parking, transfer, and operational orbits with apogee, perigee, and inclination: The launch vehicle will be dispensing various payloads into a nearly circular 500 km 85 degree inclination orbit. IRVINE01 will decay from an orbit defined as follows: Perigee: 500 km Apogee: 500 km Orbital Inclination: 85 degrees 7

IRVINE01 Orbital Debris Assessment Report (ODAR) ODAR Section 2: Spacecraft Description Mission description: Irvine01’s main mission is to take pictures of the moon and planets send them to the ground station, where they will be used for educational purposes. The primary instrument is a 3 MP camera. In addition, magnetorquers will be used for attitude control, and solar panels will be used for power. Physical description of the spacecraft: IRVINE01 conforms to the 1U CubeSat specification, with a launch mass of 0.983 kg. Basic physical dimensions are 100mm x 100mm x 106mm, with two solar panels with 170mm x 85mm x 2mm extended dimensions. The IRVINE01 solar panel structure is comprised of two 100mm x 100mm plates that are extended. The solar arrays are spring-loaded and burn-wire deployed. Power storage is provided by Lithium-Ion cells. The batteries will be recharged by solar cells mounted on the body of the satellite and on the two deployable solar panels. IRVINE01 attitude is approximately determined using the magnetic 8

IRVINE01 Orbital Debris Assessment Report (ODAR) field vector, measured by onboard magnetometers. The IRVINE01’s attitude will be controlled by a 3-axis magnetorquer controller. Total satellite mass at launch, including all propellants and fluids: 0.983 kg. Dry mass of satellites at launch, excluding solid rocket motor propellants: 0.983 kg Description of all propulsion systems (cold gas, monopropellant, bipropellant, electric, nuclear): None, but there is a zero-propellant mass-model of an electric thruster attached to balance the mass distribution of the spacecraft for the magnetorquers. Identification, including mass and pressure, of all fluids (liquids and gases) planned to be on board and a description of the fluid loading plan or strategies, excluding fluids in sealed heat pipes: None Fluids in Pressurized Batteries: None 9

IRVINE01 Orbital Debris Assessment Report (ODAR) ODAR Section 3: Assessment of Spacecraft Debris Released during Normal Operations Identification of any object (>1 mm) expected to be released from the spacecraft any time after launch, including object dimensions, mass, and material: There are no intentional 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 v2.0.1) 4.3-1, Mission Related Debris Passing Through LEO: NOT APPLICABLE 4.3-2, Mission Related Debris Passing Near GEO: NOT APPLICABLE 10

IRVINE01 Orbital Debris Assessment Report (ODAR) ODAR Section 4: Assessment of Spacecraft Intentional Breakups and Potential for Explosion There are NO plans for designed spacecraft breakups, explosions, or intentional collisions on the IRVINE01 mission. The probability of battery explosion is very low, and, due to the very small mass of the satellite and its short orbital lifetime, the effect of an explosion on the far-term LEO environment is negligible (ref (H)). The CubeSats batteries still meet Req. 56450 (4.4-2) by virtue of the HQ OSMA policy regarding CubeSat battery disconnect stating; “CubeSats as a satellite class need not disconnect their batteries if flown in LEO with orbital lifetimes less than 25 years.” (ref. (H)). Assessment of spacecraft compliance with Requirements 4.4-1 through 4.4-4 shows that with a maximum possible lifetime of 4.07 years the IRVINE01 CubeSat is compliant. 11

IRVINE01 Orbital Debris Assessment Report (ODAR) 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 v2.1.1, 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: (DAS 2.1.1) IRVINE01; Collision Probability: 0.00000; COMPLIANT. The above analysis results are a product of the DAS 2.1.1 software. We then assume hard spheres of diameter 1 m for IRVINE01 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 post-mission disposal requirements is less than 0.01 (Requirement 56507). Small Object Impact and Debris Generation Probability: IRVINE01; COMPLIANT. Identification of all systems or components required to accomplish any post-mission disposal operation, including passivation and maneuvering: No post-mission disposal procedures are necessary, since the satellite’s orbit will naturally decay within 4.07 years. 12

IRVINE01 Orbital Debris Assessment Report (ODAR) ODAR Section 6: Assessment of Spacecraft Post-mission Disposal Plans and Procedure 6.1: Description of Spacecraft Disposal Option Selected: IRVINE01 will de-orbit naturally by atmospheric re-entry within 4.07 years. All components will burn up during re-entry. 6.2: Plan for Any Spacecraft Maneuvers Required to Accomplish Post-Mission Disposal: No maneuvers are required. 6.3: Calculation of Area-to-Mass Ratio After Post-Mission Disposal, if the Controlled Re- entry Option is Not Selected: Spacecraft Mass: 0.983 kg Cross-Sectional Area: 141 cm2 6.4: Assessment of Spacecraft Compliance with Requirements 4.6-1 Through 4.6-5 (per DAS v. 2.1.1 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 Re-Entry 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 by no more than 30 years after launch. ○ 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 than 2000 km and apogee less than GEO - 500 km. c. Direct Retrieval: ○ Retrieve the space structure and remove it from orbit within 10 years after completion of mission. Analysis: The IRVINE01 satellite re-entry is COMPLIANT using method “I”. 13

IRVINE01 Orbital Debris Assessment Report (ODAR) 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 Post-Mission Disposal Operations: Analysis: The maximum drag configuration is the aerodynamically stable state, meaning that even under massive subsystem failure we would eventually assume this orientation. 14

IRVINE01 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 v2.1.1 reports that IRVINE01 is compliant with the requirement. There will be no risk of human casualty during reentry because it will completely burn up in the atmosphere. 15

IRVINE01 Orbital Debris Assessment Report (ODAR) Requirements 4.7-1b, and 4.7-1c below are non-applicable requirements because IRVINE01 does not use controlled reentry. 4.7-1, b) NOT APPLICABLE. For controlled re-entry, 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 land masses, 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 re-entries, the product of the probability of failure of the re-entry burn (from Requirement 4.6-4.b) and the risk of human casualty assuming uncontrolled re-entry shall not exceed 0.0001 (1:10,000) (Requirement 56628)) ODAR Section 8: Assessment for Tether Missions Not applicable. There are no tethers in the IRVINE01 mission. 16

IRVINE01 Orbital Debris Assessment Report (ODAR) DAS Log File 05 24 2018; 16:12:15PM Activity Log Started 05 24 2018; 16:12:15PM New Project Files Created 05 24 2018; 16:14:58PM Mission Editor Changes Applied 05 24 2018; 16:15:00PM Project Data Saved To File 05 24 2018; 16:19:04PM Processing Requirement 4.5-1: Return Status : Passed ============== Run Data ============== **INPUT** Space Structure Name = IRVINE01 Space Structure Type = Payload Perigee Altitude = 500.000000 (km) Apogee Altitude = 500.000000 (km) Inclination = 85.000000 (deg) RAAN = 0.000000 (deg) Argument of Perigee = 0.000000 (deg) Mean Anomaly = 0.000000 (deg) Final Area-To-Mass Ratio = 0.014300 (m^2/kg) Start Year = 2018.455000 (yr) Initial Mass = 0.983000 (kg) Final Mass = 0.983000 (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 17

IRVINE01 Orbital Debris Assessment Report (ODAR) Returned Error Message: Normal Processing Date Range Error Message: Normal Date Range Status = Pass ============== =============== End of Requirement 4.5-1 =============== 05 24 2018; 16:21:35PM Requirement 4.5-2: Compliant 05 24 2018; 16:27:37PM Processing Requirement 4.6 Return Status : Passed ============== Project Data ============== **INPUT** Space Structure Name = IRVINE01 Space Structure Type = Payload Perigee Altitude = 500.000000 (km) Apogee Altitude = 500.000000 (km) Inclination = 85.000000 (deg) RAAN = 0.000000 (deg) Argument of Perigee = 0.000000 (deg) Mean Anomaly = 0.000000 (deg) Area-To-Mass Ratio = 0.014300 (m^2/kg) Start Year = 2018.455000 (yr) Initial Mass = 0.983000 (kg) Final Mass = 0.983000 (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) 18

IRVINE01 Orbital Debris Assessment Report (ODAR) **OUTPUT** Suggested Perigee Altitude = 500.000000 (km) Suggested Apogee Altitude = 500.000000 (km) Returned Error Message = Reentry during mission (no PMD req.). Released Year = 2022 (yr) Requirement = 61 Compliance Status = Pass ============== =============== End of Requirement 4.6 =============== 05 24 2018; 16:28:14PM Processing Requirement 4.3-1: Return Status : Not Run ===================== No Project Data Available ===================== =============== End of Requirement 4.3-1 =============== 05 24 2018; 16:28:18PM Processing Requirement 4.3-2: Return Status : Passed ===================== No Project Data Available ===================== =============== End of Requirement 4.3-2 =============== 05 24 2018; 16:28:22PM Requirement 4.4-3: Compliant =============== End of Requirement 4.4-3 =============== 05 24 2018; 16:29:22PM Science and Engineering - Orbit Lifetime/Dwell Time **INPUT** Start Year = 2018.455000 (yr) Perigee Altitude = 500.000000 (km) Apogee Altitude = 500.000000 (km) Inclination = 85.000000 (deg) RAAN = 0.000000 (deg) 19

IRVINE01 Orbital Debris Assessment Report (ODAR) Argument of Perigee = 0.000000 (deg) Area-To-Mass Ratio = 0.014300 (m^2/kg) **OUTPUT** Orbital Lifetime from Startyr = 4.068446 (yr) Time Spent in LEO during Lifetime = 4.068446 (yr) Last year of Propagation = 2022 (yr) Returned Error Message: Object reentered 05 24 2018; 16:35:42PM Project Data Saved To File 05 24 2018; 16:35:45PM Activity Log Started 05 24 2018; 16:35:45PM Opened Project C:\Local\NASA\DAS2.1.1\IRVINE01\ 05 24 2018; 16:37:29PM Mission Editor Changes Applied 05 24 2018; 16:37:43PM Processing Requirement 4.3-1: Return Status : Not Run ===================== No Project Data Available ===================== =============== End of Requirement 4.3-1 =============== 05 24 2018; 16:37:49PM Processing Requirement 4.3-2: Return Status : Passed ===================== No Project Data Available ===================== =============== End of Requirement 4.3-2 =============== 05 24 2018; 16:37:53PM Requirement 4.4-3: Compliant =============== End of Requirement 4.4-3 =============== 05 24 2018; 16:41:56PM Processing Requirement 4.5-1: Return Status : Passed ============== Run Data ============== **INPUT** Space Structure Name = IRVINE01 20

IRVINE01 Orbital Debris Assessment Report (ODAR) Space Structure Type = Payload Perigee Altitude = 500.000000 (km) Apogee Altitude = 500.000000 (km) Inclination = 85.000000 (deg) RAAN = 0.000000 (deg) Argument of Perigee = 0.000000 (deg) Mean Anomaly = 0.000000 (deg) Final Area-To-Mass Ratio = 0.014300 (m^2/kg) Start Year = 2018.455000 (yr) Initial Mass = 0.983000 (kg) Final Mass = 0.983000 (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 =============== 05 24 2018; 16:42:09PM Requirement 4.5-2: Compliant 05 24 2018; 16:42:10PM Processing Requirement 4.6 Return Status : Passed ============== Project Data ============== **INPUT** 21

IRVINE01 Orbital Debris Assessment Report (ODAR) Space Structure Name = IRVINE01 Space Structure Type = Payload Perigee Altitude = 500.000000 (km) Apogee Altitude = 500.000000 (km) Inclination = 85.000000 (deg) RAAN = 0.000000 (deg) Argument of Perigee = 0.000000 (deg) Mean Anomaly = 0.000000 (deg) Area-To-Mass Ratio = 0.014300 (m^2/kg) Start Year = 2018.455000 (yr) Initial Mass = 0.983000 (kg) Final Mass = 0.983000 (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** Suggested Perigee Altitude = 500.000000 (km) Suggested Apogee Altitude = 500.000000 (km) Returned Error Message = Reentry during mission (no PMD req.). Released Year = 2022 (yr) Requirement = 61 Compliance Status = Pass ============== =============== End of Requirement 4.6 =============== 05 24 2018; 16:45:16PM Project Data Saved To File 05 24 2018; 17:21:26PM Activity Log Started 22

IRVINE01 Orbital Debris Assessment Report (ODAR) 05 24 2018; 17:21:26PM Opened Project C:\Local\NASA\DAS2.1.1\IRVINE01\ 05 24 2018; 17:25:50PM Processing Requirement 4.6 Return Status : Passed ============== Project Data ============== **INPUT** Space Structure Name = IRVINE01 Space Structure Type = Payload Perigee Altitude = 500.000000 (km) Apogee Altitude = 500.000000 (km) Inclination = 85.000000 (deg) RAAN = 0.000000 (deg) Argument of Perigee = 0.000000 (deg) Mean Anomaly = 0.000000 (deg) Area-To-Mass Ratio = 0.014300 (m^2/kg) Start Year = 2018.455000 (yr) Initial Mass = 0.983000 (kg) Final Mass = 0.983000 (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** Suggested Perigee Altitude = 500.000000 (km) Suggested Apogee Altitude = 500.000000 (km) Returned Error Message = Reentry during mission (no PMD req.). Released Year = 2022 (yr) 23

IRVINE01 Orbital Debris Assessment Report (ODAR) Requirement = 61 Compliance Status = Pass ============== =============== End of Requirement 4.6 =============== 05 24 2018; 17:28:00PM *********Processing Requirement 4.7-1 Return Status : Passed ***********INPUT**** Item Number = 1 name = IRVINE01 quantity = 1 parent = 0 materialID = 5 type = Box Aero Mass = 0.983000 Thermal Mass = 0.983000 Diameter/Width = 0.100000 Length = 0.100000 Height = 0.100000 name = #4 SS Screw Min Material quantity = 100 parent = 1 materialID = 54 type = Cylinder Aero Mass = 0.000525 Thermal Mass = 0.000525 Diameter/Width = 0.002794 Length = 0.011120 name = #4 SS Screw Max Material quantity = 100 parent = 1 materialID = 54 type = Cylinder Aero Mass = 0.001453 24

IRVINE01 Orbital Debris Assessment Report (ODAR) Thermal Mass = 0.001453 Diameter/Width = 0.004648 Length = 0.011120 **************OUTPUT**** Item Number = 1 name = IRVINE01 Demise Altitude = 77.992966 Debris Casualty Area = 0.000000 Impact Kinetic Energy = 0.000000 ************************************* name = #4 SS Screw Min Material Demise Altitude = 76.503357 Debris Casualty Area = 0.000000 Impact Kinetic Energy = 0.000000 ************************************* name = #4 SS Screw Max Material Demise Altitude = 75.440552 Debris Casualty Area = 0.000000 Impact Kinetic Energy = 0.000000 ************************************* =============== End of Requirement 4.7-1 =============== 25


Document Created: 2018-05-24 22:36:54
Document Modified: 2018-05-24 22:36:54
© 2024 FCC.report
This site is not affiliated with or endorsed by the FCC