Attachment Amendment Technical

This document pretains to SAT-AMD-20171025-00144 for Amended Filing on a Satellite Space Stations filing.

IBFS_SATAMD2017102500144_1296096

EXHIBIT​ ​A Planet​ ​Labs​ ​Inc. Amendment DESCRIPTION​ ​OF​ ​THE​ ​AMENDMENT Planet​ ​Labs​ ​Inc.​ ​(Planet)​ ​respectfully​ ​requests​ ​to​ ​amend​ ​its​ ​previously​ ​submitted request​ ​to​ ​modify​ ​the​ ​authorization​ ​(Modification)​ ​for​ ​the​ ​Planet​ ​Earth​ ​Exploration 1 Satellite​ ​Service​ ​(EESS)​ ​system​ ​(FCC​ ​Call​ ​Sign​ ​S2912,​ ​a.k.a.​ ​“Flock”). ​ ​ ​Specifically, Planet​ ​requests​ ​authority​ ​to: ● Modify​ ​up​ ​to​ ​three​ ​(3)​ ​of​ ​its​ ​authorized​ ​satellites​ ​of​ ​the​ ​Flock​ ​constellation​ ​to remove​ ​the​ ​imaging​ ​camera​ ​system​ ​and​ ​replace​ ​it​ ​with​ ​a​ ​nano​ ​propulsion​ ​system to​ ​be​ ​used​ ​as​ ​a​ ​technology​ ​demonstration​ ​and​ ​evaluate​ ​its​ ​potential​ ​for​ ​use​ ​on future​ ​Planet​ ​satellites​ ​(each​ ​such​ ​satellite​ ​a​ ​“Dove​ ​Turbo”​ ​satellite).​ ​The​ ​primary purpose​ ​of​ ​the​ ​propulsion​ ​system​ ​is​ ​to​ ​demonstrate​ ​orbit​ ​maintenance​ ​and constellation​ ​phasing.​ ​Further​ ​test​ ​objectives​ ​are​ ​later​ ​described​ ​in​ ​this​ ​Narrative. Planet​ ​currently​ ​has​ ​planned​ ​only​ ​one​ ​satellite​ ​demonstration​ ​but​ ​requests additional​ ​authority​ ​in​ ​the​ ​event​ ​the​ ​first​ ​satellite​ ​fails​ ​on-orbit,​ ​fails​ ​to​ ​reach​ ​orbit, or​ ​additional​ ​demonstrations​ ​or​ ​testing​ ​become​ ​necessary​ ​(Backup​ ​Dove​ ​Turbo satellites).2 A. Overview Planet​ ​operates​ ​a​ ​constellation​ ​of​ ​commercial​ ​non-geostationary​ ​orbit​ ​(NGSO) remote-sensing​ ​satellites​ ​and​ ​is​ ​authorized​ ​to​ ​operate​ ​up​ ​to​ ​200​ ​satellites​ ​at​ ​any​ ​one time.​ ​The​ ​original​ ​Dove/Flock​ ​satellite​ ​design​ ​does​ ​not​ ​include​ ​propulsion,​ ​and​ ​Planet has​ ​historically​ ​relied​ ​on​ ​passive​ ​maneuvering​ ​techniques​ ​(e.g.​ ​differential​ ​drag)​ ​for in-orbit​ ​operations​ ​of​ ​its​ ​Flock.​ ​ ​In​ ​addition​ ​to​ ​the​ ​requested​ ​modifications​ ​in​ ​the​ ​filing referenced​ ​above,​ ​Planet​ ​requests​ ​authorization​ ​to​ ​use​ ​up​ ​to​ ​three​ ​satellites​ ​for​ ​a technology​ ​demonstration​ ​of​ ​a​ ​nano​ ​propulsion​ ​system.​ ​ ​The​ ​Dove​ ​Tech​ ​Demo satellites​ ​equipped​ ​with​ ​propulsion​ ​are​ ​known​ ​as​ ​Dove​ ​Turbo​ ​satellites,​ ​each​ ​of​ ​which will​ ​have​ ​its​ ​remote​ ​sensing​ ​camera​ ​system​ ​removed​ ​and​ ​replaced​ ​with​ ​a​ ​propulsion system.​ ​The​ ​purpose​ ​of​ ​the​ ​propulsion​ ​system​ ​is​ ​to​ ​demonstrate​ ​active​ ​orbit 1 ​ ​See​ ​Modification​ ​Application,​ ​File​ ​No.,​ ​IBFS​ ​File​ ​No.​ ​SAT-MOD-20170713-00103​ ​(filed​ ​July​ ​13,​ ​2017) (“Modification”). 2 ​ ​Planet​ ​respectfully​ ​requests​ ​expedited​ ​consideration​ ​of​ ​this​ ​amended​ ​modification​ ​application.​ ​ ​The expected​ ​launch​ ​date​ ​for​ ​the​ ​Dove​ ​Turbo​ ​satellite​ ​is​ ​December​ ​20,​ ​2017. 1

EXHIBIT​ ​A Planet​ ​Labs​ ​Inc. Amendment maintenance​ ​maneuvers,​ ​constellation​ ​phasing,​ ​collision​ ​avoidance​ ​techniques,​ ​and potentially​ ​accelerated​ ​deorbit​ ​at​ ​end​ ​of​ ​life;​ ​the​ ​propulsion​ ​operations​ ​will​ ​not​​ ​exceed the​ ​maximum​ ​operational​ ​altitude​ ​authorized​ ​for​ ​the​ ​Flock​ ​satellites,​ ​and​ ​all​ ​propulsion maneuvers​ ​will​ ​be​ ​duly​ ​coordinated​ ​with​ ​JSpOC,​ ​the​ ​Space​ ​Data​ ​Association​ ​(SDA), and​ ​any​ ​other​ ​satellite​ ​operators​ ​in​ ​neighboring​ ​orbital​ ​regimes​ ​that​ ​may​ ​be​ ​affected. The​ ​satellite’s​ ​physical,​ ​electrical,​ ​avionics,​ ​and​ ​communications​ ​systems​ ​will​ ​remain unchanged​ ​from​ ​the​ ​flight-proven​ ​Dove​ ​design. Each​ ​such​ ​Dove​ ​Turbo​ ​satellite​ ​will​ ​be​ ​considered​ ​one​ ​of​ ​the​ ​200​ ​authorized Flock​ ​satellites​ ​and​ ​does​ ​not​ ​change​ ​the​ ​orbital​ ​debris​ ​risk​ ​or​ ​the​ ​compatibility​ ​of communications​ ​with​ ​other​ ​systems.​ ​ ​More​ ​specifically,​ ​each​ ​such​ ​satellite​ ​will​ ​be​ ​in​ ​an orbit​ ​as​ ​currently​ ​authorized​ ​for​ ​the​ ​Flock​ ​with​ ​the​ ​same​ ​physical​ ​properties​ ​as​ ​regular Doves​ ​and​ ​thereby​ ​no​ ​change​ ​to​ ​orbital​ ​debris​ ​and​ ​collision​ ​risk​ ​from​ ​regular​ ​Flock satellites. All​ ​of​ ​the​ ​communications​ ​systems​ ​will​ ​be​ ​on-board​ ​and​ ​capable​ ​of​ ​operating, and​ ​used​ ​for​ ​communications​ ​for​ ​the​ ​same​ ​purposes​ ​as​ ​regular​ ​Flock​ ​satellites​ ​currently authorized​ ​and​ ​operating.​ ​ ​The​ ​UHF​ ​channels​ ​will​ ​be​ ​used​ ​for​ ​regular​ ​Space​ ​Operations and​ ​anomaly​ ​resolution.​ ​The​ ​S-band​ ​channel​ ​will​ ​be​ ​used​ ​for​ ​regular​ ​Space​ ​Operation tasking​ ​including​ ​for​ ​the​ ​propulsion​ ​system​ ​control.​ ​ ​The​ ​X-band​ ​channel​ ​will​ ​be​ ​used​ ​for the​ ​downlink​ ​of​ ​propulsion​ ​system​ ​performance​ ​data.​ ​ ​It​ ​is​ ​expected​ ​however​ ​the​ ​use​ ​of the​ ​S-band​ ​and​ ​X-band​ ​channels​ ​will​ ​be​ ​far​ ​less​ ​frequent​ ​than​ ​for​ ​regular​ ​Doves​ ​given that​ ​there​ ​is​ ​no​ ​regular​ ​image​ ​scheduling​ ​and​ ​data​ ​downlink.​ ​ ​All​ ​communication transmissions​ ​will​ ​be​ ​consistent​ ​with​ ​the​ ​authorized​ ​parameters​ ​for​ ​the​ ​Flock​ ​system. B. General​ ​Description​ ​of​ ​Overall​ ​Facilities,​ ​Operations,​ ​and​ ​Services The​ ​Dove​ ​Turbo​ ​satellite​ ​will​ ​share​ ​the​ ​same​ ​mission​ ​operations​ ​and​ ​control points​ ​as​ ​the​ ​regular​ ​Flock​ ​satellite​ ​system​ ​as​ ​described​ ​in​ ​the​ ​Modification​ ​application. The​ ​satellite​ ​will​ ​also​ ​share​ ​the​ ​same​ ​orbital​ ​characteristics​ ​authorized​ ​for​ ​the​ ​Flock constellation. The​ ​services​ ​of​ ​the​ ​satellite​ ​will​ ​be​ ​for​ ​demonstration​ ​of​ ​propulsion​ ​technology that​ ​may​ ​be​ ​used​ ​on​ ​future​ ​Planet​ ​satellites​ ​to​ ​further​ ​improve​ ​on-orbit​ ​operations, 2

EXHIBIT​ ​A Planet​ ​Labs​ ​Inc. Amendment conjunction​ ​avoidance,​ ​and​ ​responsible​ ​utilization​ ​of​ ​Low​ ​Earth​ ​Orbit. C. Technical​ ​Description Other​ ​than​ ​replacing​ ​the​ ​imaging​ ​camera​ ​with​ ​a​ ​propulsion​ ​system,​ ​the​ ​satellite​ ​is technically​ ​identical​ ​to​ ​the​ ​other​ ​Flock​ ​satellites.​ ​ ​It​ ​shares​ ​the​ ​same​ ​design​ ​and manufacture​ ​of​ ​the​ ​structural,​ ​power,​ ​avionics,​ ​and​ ​communications​ ​aspects​ ​of​ ​the Flock​ ​satellites​ ​and​ ​shares​ ​the​ ​same​ ​associated​ ​earth​ ​stations​ ​for​ ​the​ ​uplink​ ​and downlink​ ​of​ ​space​ ​operations​ ​data​ ​and​ ​propulsion​ ​system​ ​performance​ ​data.​ ​ ​There​ ​are no​ ​changes​ ​to​ ​the​ ​frequencies​ ​and​ ​concept​ ​of​ ​operations​ ​for​ ​each​ ​of​ ​the​ ​bands​ ​as proposed​ ​in​ ​the​ ​Modification. The nano propulsion system is known as Indium Field Emission Electric Propulsion. This propulsion system consists of a 250-gram cylinder of indium, associated heaters, ion generator mechanism, and beam neutralizer mechanism. Thrust is generated by the acceleration of ions via an applied electric field between an emitter crown and extractor electrode. The expected thrust is 350 micro-Newtons (uN), and there is a total of 5000 Newton-second total impulse capability for up to 1415 m/s velocity​ ​change​ ​for​ ​the​ ​5​ ​kg​ ​Dove​ ​Turbo​ ​satellite. The​ ​test​ ​objectives​ ​of​ ​the​ ​technology​ ​demonstration​ ​will​ ​inform​ ​Planet​ ​of​ ​several use​ ​cases​ ​for​ ​the​ ​propulsion​ ​system​ ​including​ ​the​ ​following: ● Validate​ ​the​ ​efficacy​ ​of​ ​an​ ​electric​ ​propulsion​ ​system​ ​for​ ​the​ ​phasing​ ​and maintenance​ ​of​ ​the​ ​orbit​ ​including​ ​altitude​ ​adjustments​ ​(typical​ ​of​ ​orbit maintenance​ ​maneuvers,​ ​i.e​ ​approximately​ ​1​ ​km). ● With​ ​efficacy​ ​data,​ ​estimate​ ​the​ ​ability​ ​for​ ​collision​ ​avoidance​ ​maneuvers using​ ​the​ ​propulsion​ ​system. ● At​ ​the​ ​end​ ​of​ ​the​ ​Dove​ ​Turbo​ ​mission​ ​and​ ​if​ ​feasible,​ ​demonstrate​ ​a​ ​rapid de-orbit​ ​capability​ ​for​ ​end-of-mission​ ​disposal​ ​(potentially​ ​reducing​ ​orbital lifetime​ ​to​ ​less​ ​than​ ​1​ ​year). D. Orbital​ ​Debris​ ​Mitigation The​ ​propulsion​ ​system​ ​does​ ​not​ ​change​ ​the​ ​potential​ ​for​ ​collisions​ ​or​ ​risk​ ​of 3

EXHIBIT​ ​A Planet​ ​Labs​ ​Inc. Amendment generating​ ​orbital​ ​debris.​ ​ ​Attached​ ​as​ ​Exhibit​ ​B​ ​is​ ​a​ ​revised​ ​version​ ​of​ ​the​ ​Orbital Debris​ ​Assessment​ ​Report​ ​(ODAR)​ ​specific​ ​to​ ​the​ ​Dove​ ​Turbo​ ​satellite.​ ​ ​The​ ​ODAR shows​ ​there​ ​is​ ​no​ ​change​ ​in​ ​the​ ​risk​ ​for​ ​orbital​ ​debris​ ​generation​ ​and​ ​collisions​ ​with other​ ​spacecraft​ ​since​ ​the​ ​physical​ ​characteristics​ ​of​ ​the​ ​satellite​ ​are​ ​the​ ​same​ ​as regular​ ​Flock​ ​satellites.​ ​The​ ​propulsion​ ​system​ ​does​ ​not​ ​contain​ ​any​ ​stored​ ​energy​ ​and therefore​ ​no​ ​risk​ ​for​ ​accidental​ ​explosions.​ ​ ​All​ ​energy​ ​is​ ​provided​ ​by​ ​the​ ​batteries​ ​and solar​ ​arrays,​ ​which​ ​is​ ​the​ ​same​ ​as​ ​regular​ ​Flock​ ​satellites.​ ​ ​The​ ​risk​ ​for​ ​human​ ​casualty from​ ​material​ ​reaching​ ​the​ ​Earth’s​ ​surface​ ​during​ ​re-entry​ ​is​ ​zero​ ​(0)​ ​since​ ​there​ ​are​ ​no high​ ​melting​ ​point​ ​or​ ​large​ ​mass​ ​materials​ ​capable​ ​of​ ​surviving​ ​re-entry,​ ​including​ ​the indium​ ​cylinder​ ​within​ ​the​ ​propulsion​ ​system. Planet​ ​has​ ​considered​ ​the​ ​possible​ ​failure​ ​modes​ ​of​ ​the​ ​propulsion​ ​system operations​ ​and​ ​mitigation​ ​to​ ​prevent​ ​failures​ ​from​ ​increasing​ ​the​ ​risk​ ​towards​ ​collisions and​ ​orbital​ ​debris​ ​generation.​ ​ ​In​ ​particular,​ ​Planet​ ​has​ ​in-house​ ​expertise​ ​from​ ​the Skysat​ ​satellite​ ​mission​ ​(Call​ ​Sign​ ​S2862)​ ​currently​ ​operational​ ​with​ ​a​ ​propulsion system​ ​and​ ​that​ ​person​ ​will​ ​guide​ ​the​ ​process​ ​for​ ​control​ ​and​ ​operation​ ​of​ ​the​ ​Dove Turbo​ ​propulsion​ ​system​ ​to​ ​fully​ ​characterize​ ​and​ ​monitor​ ​the​ ​resulting​ ​effects​ ​to​ ​the orbit. The​ ​propulsion​ ​system​ ​is​ ​controlled​ ​by​ ​a​ ​software​ ​defined​ ​state-machine​ ​with multiple​ ​gates​ ​before​ ​thrusters​ ​are​ ​enabled.​ ​ ​Although​ ​not​ ​a​ ​credible​ ​failure​ ​case,​ ​in​ ​the theoretical​ ​worst-case​ ​scenario​ ​wherein​ ​the​ ​propulsion​ ​system​ ​does​ ​not​ ​turn​ ​off,​ ​the batteries​ ​will​ ​deplete​ ​within​ ​three​ ​hours​ ​thereby​ ​limiting​ ​the​ ​duration​ ​of​ ​a​ ​continuous thrust​ ​event. E. Additional/General​ ​Considerations Other​ ​than​ ​as​ ​stated​ ​in​ ​this​ ​amendment​ ​application,​ ​there​ ​are​ ​no​ ​other​ ​requested changes​ ​to​ ​the​ ​modification​ ​application. 4

EXHIBIT​ ​A Planet​ ​Labs​ ​Inc. Amendment TECHNICAL​ ​CERTIFICATE I,​ ​Craig​ ​Scheffler,​ ​hereby​ ​certify,​ ​under​ ​penalty​ ​of​ ​perjury,​ ​that​ ​I​ ​am​ ​the technically​ ​qualified​ ​person​ ​responsible​ ​for​ ​the​ ​preparation​ ​of​ ​the​ ​engineering information​ ​contained​ ​in​ ​the​ ​technical​ ​portions​ ​of​ ​the​ ​foregoing​ ​application​ ​and​ ​the related​ ​attachments,​ ​that​ ​I​ ​am​ ​familiar​ ​with​ ​Part​ ​25​ ​of​ ​the​ ​Commission’s​ ​rules,​ ​and​ ​that the​ ​technical​ ​information​ ​is​ ​complete​ ​and​ ​accurate​ ​to​ ​the​ ​best​ ​of​ ​my​ ​knowledge​ ​and belief. Craig​ ​Scheffler Spectrum​ ​Manager Planet​ ​Labs​ ​Inc. 5


Document Created: 2019-04-10 22:18:30
Document Modified: 2019-04-10 22:18:30
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