Attachment Exhibit 43

This document pretains to SAT-MOD-20101122-00243 for Modification on a Satellite Space Stations filing.

IBFS_SATMOD2010112200243_853570

EXHIBIT 43 DG Consents Sub, Inc. Modification Application FCC Form 312 November 2010 Description of Modification of License Application In this Modification of License Application, DG Consents Sub, Inc. (“DigitalGlobe”) proposes to modify the orbit characteristics of the longest-operating satellite in its three-satellite non-geostationary satellite orbit (“non-GSO”) Earth Exploration-Satellite Service (“EESS”) system. Specifically, DigitalGlobe proposes to increase the orbital altitude of its QuickBird satellite to 496 kilometers from its present altitude of 450 kilometers. No changes are proposed in this Modification Application to either the WorldView 60 or the WorldView 110 satellites in DigitalGlobe’s non-GSO EESS system. QuickBird, authorized in 1997 as QuickBird-2 and launched in 2001,1 has been the cornerstone of DigitalGlobe’s constellation for nearly a decade. With the addition of the two WorldView satellites in recent years, DigitalGlobe is able to produce a substantially greater volume of remote sensing data in a shorter time frame than was possible with QuickBird alone. Still, QuickBird remains a vital and integral part of the DigitalGlobe constellation. DigitalGlobe has determined that with a 46 kilometer increase in the orbital altitude of the near-circular QuickBird satellite, the mission life of the spacecraft can be extended by more than one year. The proposed increase in orbit altitude will cause no increase in the interference envelope for QuickBird. Indeed, as the current power levels from the spacecraft will be maintained but from a higher altitude, there will be a reduction in power flux density levels on the Earth’s surface from levels that already meet the international limits established for the 8025-8400 MHz band. All other parameters of the authorized, in-orbit satellite are unchanged. The Commission has determined in previous cases involving non-GSO satellites in other services that increases in orbit altitudes (and associated changes in such related parameters as inclination angles) are not considered to be major unless they increase the potential for interference.2 Those same principles apply to the change in orbital configuration of the QuickBird satellite that DigitalGlobe proposes in this Application. DigitalGlobe also notes that observations the Commission previously made with respect to a pre-launch orbit altitude change for the QuickBird satellite remain true today. In May 2001, 1 See EarthWatch Incorporated, 12 FCC Rcd 21647 (Int’l Bur. 1997) (“EarthWatch”). QuickBird-2 eventually became known simply as QuickBird following the loss of the authorized QuickBird-1 satellite in a launch failure. 2 See, e.g., Orbital Communications Corp., 13 FCC Rcd 10828, (¶¶ 23-24) (Int’l. Bur. 1998); Teledesic Corp., 14 FCC Rcd 2261 (¶ 13) (Int’l. Bur. 1999) (changes in orbital configuration, including number of satellites, number of planes, orbit altitude and inclination angle, not considered major without increase in interference to other systems or increase in difficulty in sharing). 291698: v2

EarthWatch Incorporated (the former name of DigitalGlobe’s parent corporation) sought to lower the authorized orbit altitude of QuickBird from 600 kilometers to its current 450 kilometer range. In assessing this proposed reduction, the Commission noted that “spacecraft design decisions should be left to each space station licensee, because the licensee is in a better position to determine how to tailor its system to meet the particular needs of its customer base.”3 It went on to state that where an orbit altitude change is technically efficient, permits additional entrants, and is otherwise in the public interest, the Commission will approve the change.4 DigitalGlobe’s current proposal readily meets this three-pronged standard. First, the altitude change is technically efficient. The increase in altitude will extend the operational life of the QuickBird satellite. Moreover, the power flux density values for the downlink bands remain within the regulatory limits established in No. 21.16 of the International Telecommunication Union’s Radio Regulations. The altitude increase in this case (as opposed to the decrease proposed in 2001) will, in fact, mean a reduction in power flux density at the Earth’s surface.5 Second, nothing in this proposal has any impact on additional EESS entry into the 8025- 8400 MHz band. To the extent that the altitude change may make QuickBird’s network more susceptible to interference, DigitalGlobe commits not to claim any greater protection from harmful interference than it is entitled to claim with the satellite at an orbital altitude of 450 kilometers. Finally, the grant of this Modification Application will permit DigitalGlobe to extend the operational life of the QuickBird satellite by up to fifteen months. The data generated by DigitalGlobe’s three-satellite system will continue to advance myriad public and national interests such as meteorology, national security, and improved understanding of our environment and climate. Moreover, competition in the market for commercial remote sensing data will continue to be robust. A Schedule S submission containing the appropriate information for the QuickBird satellite at its proposed increased orbit is included with this Modification Application. All other parameters of the authorized, in-orbit satellite are unchanged.6 3 EarthWatch Incorporated, 16 FCC Rcd 15985, 15986 (Int’l Bur. 2001) (“EarthWatch Modification”). 4 EarthWatch Modification, .16 FCC Rcd at 15987. 5 DigitalGlobe includes an updated interference analysis in Attachment B to this exhibit. The analysis is very similar to the one included in Attachment 1 to the March 2001 EarthWatch Incorporated Modification Application that led to the establishment of QuickBird’s orbital altitude at the 450-470 km range, but shows slightly lower power flux-density values. See Modification of Authorization for EarthWatch Incorporated, File No. SAT-MOD- 20010322-00028. 6 Technical and Schedule S information is provided for QuickBird only, and not for the DigitalGlobe non-GSO EESS system as a whole. Previous technical submissions for the WorldView satellites are unaffected by the instant orbit modification proposal for QuickBird. See, e.g., Application of DG Consents Sub, Inc. for Modification of License to Revise Orbital Paramters of WorldView-60 and Add WorldView-110 to the DigitalGlobe Constellation, File No. SAT-MOD-20070730-00107 (“DigitalGlobe 2007 Modification Application”), Stamp Grant, October 4, 2007 (“DigitalGlobe 2007 Modification Stamp Grant”). 2

As has been determined with respect to prior modifications of the instant system license in the years following the Commission’s adoption of the first-come/first-served and modified processing round procedures, this Modification Application is to be considered under the first- come/first-served procedure adopted in the Commission’s Space Station Licensing Reform proceeding.7 The rationale underlying these earlier determinations – in particular, the fact that DigitalGlobe’s EESS system, unlike some other types of non-geostationary satellite orbit systems, can share the frequency bands with other EESS systems – remains fully applicable to the QuickBird satellite’s proposed operations in a slightly higher orbit.8 DigitalGlobe urges the Commission to follow the precedent it established for non-GSO EESS modification applications in the DigitalGlobe Order, and treat DigitalGlobe’s instant Modification Application under the first-come/first-served processing procedure.9 Finally, DigitalGlobe urges expedited favorable consideration of this Modification Application. The changes proposed to the orbit of the QuickBird satellite are needed to preserve and extend the spacecraft’s useful life and its important imaging mission (which has national ramifications that extent beyond DigitalGlobe’s proprietary interest). DigitalGlobe engineers will need to act within the next few months if the company is to attain and maximize these benefits. 4. Additional/General Considerations: A. Form 312, Schedule S As required by the Commission’s rules and policies, DigitalGlobe has completed, to the best of its ability and the limitations of the Commission’s software, the FCC Form 312, Schedule S submission that reflects the updated orbital characteristics of the QuickBird satellite that are proposed in this Modification Application. As the original application for the QuickBird spacecraft preceded the introduction of Form 312, Schedule S, this is the initial submission of this material for QuickBird. 7 See DigitalGlobe, Inc., 20 FCC Rcd. 15696 (¶ 1) (Int’l Bur. 2005) (“DigitalGlobe Order”) (citing Amendment of the Commission’s Space Station Licensing Rules and Policies, 18 FCC Rcd 10760 (2003)). The same determination was implicitly made in the DigitalGlobe 2007 Modification Stamp Grant. 8 To the extent that the Commission may deem it necessary for DigitalGlobe to request the same waiver of the modified processing round requirement of Sections 25.156 and 25.157, 47 C.F.R. §§ 25.156 and 25.157, in order to secure this mode of processing, DigitalGlobe hereby requests such waivers and incorporates by reference its supporting documentation from the 2004 Modification Application in File No. SAT-MOD-20040728-00151. In support of these requests, DigitalGlobe notes that the original public interest considerations – including no harmful interference being caused to other EESS systems currently operating in the band – continue to apply, and there is no inconsistency at all with the public policy goals of the processing procedure. See DigitalGlobe 2004 Modification of License Application, File No. SAT-MOD-20040728-00151, at Narrative, Section V; DigitalGlobe 2007 Modification Application at Narrative, Section 2. 9 DigitalGlobe Order, 20 FCC Rcd at 15699 (¶ 8) (citing Space Imaging, LLC, 20 FCC Rcd 11964 (Int’l Bur. 2005)). 3

Now, as has been the case with previous DigitalGlobe modification applications, limitations in the Commission’s required software prevent DigitalGlobe from including in the Schedule S certain caveats about the data provided.10 In order to comply as closely as possible with the Commission’s requirement, DigitalGlobe has produced in Attachment A hereto a manually-completed printout of the Schedule S portion of the application that includes technical data intended for inclusion on FCC 312 Schedule S by DigitalGlobe that could not be electronically input into the FCC Schedule S database format. DigitalGlobe requests that the Commission to resolve the software incompatibility issue outlined in the previous paragraph and Note 10 by relying on data in the Attachment A where there is an inconsistency or incompleteness with or to data in the electronic Schedule S submission that accompanies this Modification Application. DigitalGlobe notes that it a successfully used a similar approach to address the same incompatibility issue in both DigitalGlobe’s July 2004 Modification Application and the DigitalGlobe 2007 Modification Application.11 Any material discrepancies between the data in the electronic version of Schedule S and the version included in the print out in Attachment A hereto should therefore be resolved in favor of the print version in Attachment A. DigitalGlobe provides additional information regarding the modified orbital characteristics of the QuickBird satellite in Attachment B. This information will allow the Commission to repeat its favorable findings in the DigitalGlobe Order regarding sharing with government users systems, meteorological-satellite service uplinks, and other EESS systems, fixed service systems, fixed-satellite service (Earth-to-space).12 From an interference standpoint, the increased-altitude QuickBird satellite described here is not changed in any material way from the system that the National Telecommunications and Information Administration approved when it considered the original QuickBird applications in the late 1990s and early 2000s. B. Orbital Debris Mitigation In the DigitalGlobe Order, the Bureau determined that DigitalGlobe’s July 2004 Modification Application to add new non-geostationary-orbit satellites to the constellation that already included QuickBird was subject to the default service rule provisions in Section 25.217 of the Commission's Rules, 47 C.F.R. § 25.217.13 With regard to orbital debris mitigation, the 10 Certain data fields in Microsoft Access Database file would not accept DigitalGlobe’s data, which, in turn, caused errors in the database. For example, the response to Item S7.h (edge gain for DigitalGlobe’s “CMD” beam) should be -16 dBi, as shown in Attachment A. The -10 dBi entry in the electronic version is incorrect, and cannot be manipulated to the correct value. To rectify these situations, DigitalGlobe was forced to input generic information into the electronic database file in order to maintain the integrity of the system. The charts in Attachment A contain all of the sections from Schedule S with the correct data that DigitalGlobe was not fully able to provide in the electronic Schedule S. 11 See DigitalGlobe 2004 Modification of License Application, File No. SAT-MOD-20040728-00151, at Narrative, Attachment A; DigitalGlobe 2007 Modification Application, at Narrative. 12 See DigitalGlobe Order, 20 FCC Rcd at 15703-04 & n. 58 (¶¶ 21-25). 13 See DigitalGlobe Order, 20 FCC Rcd at 15701. 4

Bureau noted that Section 25.217(d) contains standards for end-of-life spacecraft disposal, designed to mitigate orbital debris.14 DigitalGlobe had requested a waiver of this regulation in its July 2004 filing.15 In assessing DigitalGlobe's July 2004 Modification Application, which proposed three additional non-geostationary orbit EESS satellites (one of which was to operate in an orbit in the same range as QuickBird), the Bureau concluded that "DigitalGlobe has demonstrated good cause for a waiver of the Commission's orbital debris disclosure requirements."16 The Bureau noted that: [i]n adopting the orbital debris disclosure requirements, the Commission specifically found that there was no additional benefit to reviewing the post-mission disposal plans of commercial remote sensing satellite applicants when such plans are already subject to effective regulatory review by NOAA. Thus, the Commission concluded that, to the extent that a remote sensing satellite applicant has submitted its post-mission disposal plans to NOAA for review and approval, the Commission would not require submission of such information. The Commission further stated, however, that with respect to elements of debris mitigation other than post-mission disposal for which NOAA has not received information necessary for review and approval, it would require remote sensing satellite applicants to submit such information as part of an application for a Commission license, and would review any such aspects of a remote sensing applicant's debris mitigation plans that are outside the scope of NOAA review. 17 The Bureau went on to recognize that DigitalGlobe had already submitted a post-mission disposal plan for the new satellites to NOAA as part of NOAA's licensing process. It thereby concluded that: Thus, DigitalGlobe is not required to provide a full disclosure plan to the Commission. Moreover, based on our review of the supplemental Orbital Debris Mitigation Statement provided in DigitalGlobe's 14 Id. Section 25.217(d) requires applicants, inter alia, to submit a narrative statement describing the debris mitigation design and operational strategies that they will use. 47 C.F.R. § 25.217(d). 15 See DigitalGlobe 2004 Modification Application, File No. SAT-MOD-20040728-00151, at Narrative, Section IV.D. 16 DigitalGlobe Order, 20 FCC Rcd at 15705. 17 Id. (footnotes omitted) (citing Mitigation of Orbital Debris, 19 FCC Rcd 11567, 11609 (¶¶ 102-104). 5

application, we find that DigitalGlobe need not further supplement its NOAA post-mission disclosure plans at this time.18 When DigitalGlobe modified its system in 2007 to add a third satellite and modify orbital parameters for its authorized but as of then unlaunched second satellite, DigitalGlobe made the same demonstration about the orbital debris mitigation plan for the new satellites.19 DigitalGlobe requested a waiver of Section 25.217(d) of the Commission’s Rules and provided information of a type the Commission had previously determined in connection with the 2004 DigitalGlobe Modification to be sufficiently detailed to satisfy the provisions of Section 25.114(d)(14).20 The Commission took no issue with these showings and made no special provision for orbital debris mitigation in its 2007 Stamp Grant. DigitalGlobe urges the Commission to treat the orbital debris mitigation element of the QuickBird orbit change proposed here in the same way it handled the orbital debris aspects of the addition of the WorldView satellites pursuant to the 2004 and 2007 modification applications. In other words, the Commission should either determine that the post-mission disposal arrangements through the NOAA process, as supplemented with demonstrations below, are sufficient to satisfy the combined requirements of Sections 25.114(d)(14) and 25.217(d), or it should determine that a waiver of the application information submission requirements of these two regulations is appropriate. In additional support of this request, DigitalGlobe offers the following showings on the orbital debris mitigation elements in Section 25.114(d)(14) of the Commission’s Rules:21 18 Id. (¶ 28). The orbital debris mitigation showing in DigitalGlobe's July 2004 Modification Application included information on the elements of debris mitigation other than post-mission disposal. DigitalGlobe provided statements about the assessment and limitation of the amount of debris released in a planned manner during normal operations (including the probability that an operating spacecraft in the DigitalGlobe remote sensing NGSO system will become a source of debris through collisions with man-made objects or meteors); details of the steps DigitalGlobe has taken to assess and limit the probability of accidental explosions during and after completion of mission operations; and an estimation that the system design and spacecraft mission profiles of the WorldView 60 and 110 satellites will limit the probability of collision with known large objects during the constellation’s orbital lifetime. See DigitalGlobe 2004 Modification Application, File No. SAT-MOD-20040728-00151, at Narrative, Section IV.D. 19 DigitalGlobe 2007 Modification Application, at Narrative. 20 DigitalGlobe recognizes that when the Bureau granted its 2004 Modification Application in the DigitalGlobe Order, the orbital debris mitigation requirements of Section 25.114(d)(14) of the Commission's Rules, 47 C.F.R. § 25.114(d)(14), had not yet become effective. This rule, which like Section 25.217(d) calls for the submission of a description of the design and operational strategies that will be used to mitigate orbital debris, requests more specific information than is called for in Section 25.217(d). The Commission's Second Report and Order in Mitigation of Orbital Debris noted that for elements of debris mitigation other than post-mission disposal that are covered by the Commission's new rules, the Commission would still require its submission as part of the Commission's space station licensing process, but only if the information was not necessary for review and approval by NOAA. Mitigation of Orbital Debris, 19 FCC Rcd at 11609 (¶ 104). 21 DigitalGlobe notes that the Bureau determined in the DigitalGlobe Order that the orbital debris mitigation submission in the 2004 Modification Application was sufficiently detailed to satisfy the provisions of Section 25.114(d)(14). Accordingly, the Commission concluded in the DigitalGlobe Order that DigitalGlobe did not need to further supplement its NOAA post-mission disclosure plans. The showing here on the elements of the orbital 6

1. Spacecraft Hardware Design DigitalGlobe confirms that the QuickBird satellite will not undergo any planned release of debris during its remaining period of operation. When the QuickBird satellite was contracted for and constructed in the late 1990s, DigitalGlobe’s predecessor in interest, in conjunction with the spacecraft manufacturer, assessed and limited the probability of the satellite becoming a source of debris by collisions with small debris or meteoroids of less than one centimeter in diameter that could cause loss of control and prevent post-mission disposal. DigitalGlobe took steps to limit the effects of such collisions through shielding, the placement of components, and the use of redundant systems. The QuickBird satellite is extremely rugged with regard to meteoroids smaller than 1 cm, by virtue of its redundancy, shielding, separation of components and physical characteristics. This ruggedness is confirmed by the nearly ten years of continuous operation in low-Earth orbit. The satellite is designed to have no single points of failure. 2. Minimizing Accidental Explosions In conjunction with the satellite’s manufacturer, DigitalGlobe has assessed and limited the probability of accidental explosions during and after completion of mission operations. The assessment was based on possible failure modes that could result in explosions, and operational procedures were adopted to limit the probability they will occur. In particular, the satellite manufacturer has taken steps to ensure that debris generation will not result from the conversion of energy sources on board the satellite into energy that fragments the satellite. All sources of stored energy onboard the DigitalGlobe spacecraft will have been depleted or when no longer required for mission operations or post-mission disposal. 3. Safe Flight Profiles DigitalGlobe has estimated that its system design and spacecraft mission profiles will limit the probability of collision with known large objects during the constellation’s orbital lifetime. This was the case with the currently-authorized orbit, and remains the case with the proposed slightly higher orbit. Digital Globe’s disclosure of the parameters (including the inclination of orbital planes, orbital period, apogee, perigee the argument of perigee, and right ascension of the ascending nodes) used by the QuickBird satellite may assist third parties in identifying potential problems that may be the result of proposed operations, and lends itself to coordination between DigitalGlobe and other operators located in similar orbits. debris mitigation requirements in Section 25.114(d)(14) other than post-mission disposal are at least as detailed and informative as the showings in DigitalGlobe’s 2004 Modification Application and 2007 Modification Application. 7

4. Post-Mission Disposal As part of DigitalGlobe’s authorization to operate a remote sensing satellite system under the Land Remote Sensing Policy Act, 15 U.S.C. §5601 et seq., DigitalGlobe filed a plan for post- mission disposal of QuickBird with NOAA. DigitalGlobe’s orbital debris mitigation and post- mission disposal plans for QuickBird in its current orbit were approved by NOAA. DigitalGlobe has provided the information pertaining to post-mission disposal of QuickBird in relation to the new orbit parameters to NOAA, and expects that favorable action by NOAA under the applicable NOAA regulations will be taken by the end of 2010. The key fact is that DigitalGlobe's post-mission disposal plans for QuickBird were initially approved by NOAA prior to commencement of QuickBird operation in the early 2000s. These plans remain fully applicable, and are not impacted in any way by the minor adjustments DigitalGlobe proposes to make to the QuickBird orbital configuration. Importantly, as QuickBird is in orbit, and its materials composition cannot be changed, the key factor here is that the slight orbit increase DigitalGlobe is proposing does not increase the satellite’s susceptibility to collisions or fragmentation events or hamper execution of post-mission disposal in any material way. 5. Accuracy with which Orbital Parameters will be Maintained As a final matter, DigitalGlobe provides the Commission with the information called for in Section 25.114(d)(14)(iii) of the Commission’s Rules, and “discloses the accuracy – if any – with which orbital parameters of [its] non-geostationary satellite orbit space stations will be maintained, including apogee, perigee, inclination, and the right ascension of the ascending node(s).” 47 C.F.R. § 25.114(d)(14)(iii). See Table 1 below. To the extent that Section 25.114(d)(14)(iii) also calls for indication of the anticipated evolution over time of the satellites’ orbits, DigitalGlobe informs the Commission here that the evolution over time of the QuickBird satellite’s orbit is anticipated to remain within the ranges given in Table 1 as a result of corrective measures (e.g., satellite thruster/maneuvering burns) to be taken by DigitalGlobe during the satellite’s remaining lifetime. Table 1: Anticipated Ranges of Accuracy to Which QuickBird Orbital Parameters Are Maintained: QuickBird Orbital Parameters Inclination Angle (deg.) +/- 0.1 Apogee (km) +/- 1.5 Perigee (km) +/- 1.5 Right Ascension of the +/- 5.84 Ascending Node (deg) 8

ATTACHMENT A ANNOTATED FCC FORM 312, SCHEDULE S 9

FCC 312 FEDERAL COMMUNICATIONS COMMISSION Page 1: General, Schedule S SATELLITE SPACE STATION AUTHORIZATIONS Frequency Bands, and GSO Orbit (Technical and Operational Description) S1. GENERALINFORMATION Complete for all satellite applications. a. Space Station or Satellite Network Name: e Estimated Date of Placement into Service: T. Will he space suation(s) oparate on a Common Camer basis? USASAT 30A (§2129) Quickbird: Jan 2002 vES K no b. Construction Commencement Date: 1. Estimated Lifetime of Satellite(s): j. Number of ransponders offered on a Common Camer basis: Quickbird: Tuly 1997 12 Years 0 : Constraction Completion Date: 2: Toul Number of Transponders: T Total Common Camer Transponder Bandwidth: Quickbird: May 2001 0 0 MHz T. Esimated Lanch Date: h Total Transponder Bandwidth(No: Transponders x Bandwidiy: T. Orbit Type: Mark all boxes that apply Quickbird: Dec 2001 0 vile Gso [ ncso 2. OPERATING FREQUENCY BANDS Identify the frequency ranfge and transmit/receive mode f&: :fll frequency bands inwhich this station will operate. Also indicate the nature 0 s) for each n Lower CHo) E + CHz) a. Numeric id c Numeric d Unit . T/R Mode F. Nature of Service(s): List all that apply to this band 8025 M 8345 M T Earth exploration satellite service $3, ORBITAL INFORMATION FOR GEOSTATIONARY SATELLITES ONLY: . Nommal Orbiat Longitude (Derees IW: b. Reason for orbital Tocation sclection: [Longitudinal Tolerance or W Station—Keeping . Inclination Excursion or Range of orbital are in which adequate service NS Station—Keeping can be provided (Optional): Degrees c. Toward West Degrees ‘Tolerance: [ Westernmost: d. Toward East Degrees Degrees g. Eastermmost i: Reason for service are selection (Optional): Rev 4d, June 19, 2003, 5:45 pm ECC 312, Schedule S — Page 1 June, 2003

FEDERAL COMMUNICATIONS COMMISSION Page 2: NGSO Orbits SATELLITE SPACE STATION AUTHORIZATIONS FCC Form 312 — Schedule S: (Technical and Operational Description) $4, ORBITAL INFORMATION FOR NON—GEOSTATIONARY SATELLITES ONLY S4a, Total Numberof Satellites in Network or System: _1 $4c. Celestial Reference Body (Earth, Sun, Moon, etc.): Earth S$4b. Total Number ofOrbital Planes in Network or System: _1 $4d. Orbit Epoch Date: _1 Oct 2010; 12:00:00 UTCG For each Orbital P Provide: ; 5 D Orl? h ~ (r“s f Inclination es ‘;‘; s 5 0 Right Ascension Argument (Degrees) mal No, of Sitel~ Angle ftal Perio erigce of the Ascending of Perigee (m) Begin (.ALL:};.: (e) Other Plane No. lites in Plane c (Seconds) Chm) Node (Deg.) 3 (QB) 9739 5664. a 4 344.8 360 S5, INITIALSATELLITE PHASE ANGLEFor each satellite in each orbital ide the initial Je. c c 0 c G Orbital 8. Satellite Hnitial Shese Angle (a) Orbital | ® Satellie Tnitial Shase Antle (a) Orbital | ® Satellie Initial Shise Angle ) Orbital | ®. Satellite Inidht Thuse Augle Plane No. Number Plane No. Number 5 Plane No. Number Plane No. Number 3 (OB) 0 cas pm Rev 4d, June 19, 2003, 5:45 ECC 312, ScheduleJune, S — Page 20032

FEDERAL COMMUNICATIONS COMMISSION Page 3: Service Areas SATELLITE SPACE STATION AUTHORIZATIONS FCC Form 312 — Schedule S: (Technical and Operational Description) S6. SERVICE AREA CHARACTERISTICS For each service area (a) (b)Type of (©) (d) Service Area Deseription. Provide list of geographic s Service Associated Te Service meggn fls Area Nime m 3—Itr_ codes), stellites areas (state postal codes or FTU Area ID qhach or Bpres (GXTFilo) or Figure No. of Service Area Diagram. cas pm Rev 4d, June 19, 2003, 5:45 ECC 312, Schedule S — Page 3 June, 2003

FEDERAL COMMUNICATIONS COMMISSION Page 4: Antenna Beams SATELLITE SPACE STATION AUTHORIZATIONS FCC Form 312 — Schedule S: (Technical and Operational Description) 87. SPACE STATION ANTENNA BEAM CHARACTERISTICS For each antenna beam e ) (» (b) Antenna Gain Pointing Min. — Cross—| sock ization 0 Service tu nput (DBfTective c (m) Max. (n) System s (0) G/T at Beam n TR P T Brror Hrror Polar Iso— L Output EiRP ce Max.G a Mode "(grio as ) ) lation (dB) Area ID (%sasis Powe&P‘(‘W) (dBw) sitan () Pl.a(xdfi;ll‘(") (‘V/ alue Je | NE Size ST3 T _ |6 14 0* 15 N 8.1 0.8 49 ST4 T 24.7 1237 0** _|15 N 333 2.65 29.0 CMD R 0* 0* N —26.0 —94.9** 3 — 7 — — Rev 4d, June 19, 2003, 5:45 pm Notes: Antenna is spacecraft body—mounted. and not pointed at earth station FCC312, Schedule 8 — Page 4 y sy ** Beam is circularly symmetric. por *** Commandreceiver is not a transponder. June, 2003

FEDERAL COMMUNICATIONS COMMISSION SATELLITE SPACE STATION AUTHORIZATIONS Page 5: Beam Diagrams FCC Form 312 — Schedule S: (Technical and Operational Description) 8. Blli%é\M D[/},‘GRAMS For eixsch beam pattern r()vid? the referenceto.the eraphic i numerical data: Iso lux density levels in cach beam U lrcsut?rom the emission \%l{“’ the c?filux densi i6 (s) ©Co—or @Gso (0 (0 Max. Power Flux idBW/m2 Reference Bandwidth® Ream ‘tk GHote |ReFOrbilal] NG§O AntermaGain GSQ Antenna Gain At Angle of Amival sbove horizontal(for emission with highest PFD) D Reference olar de Longitude Contour Description Contour Data Bandwidth® Ip Mode |(°C" or "X" . Ew) 7‘Table / Exhibio (GXT File) £ ( 10 @15 20 0925 (@kilz or IMHz sea as appropriate to ts pm Rev 4d, June 19, 2003, 5:45 ‘ ECC 312, ScheduleJune, 8 — Page 20035

FEDERAL COMMUNICATIONS COMMISSION Page 6: Channels and SATELLITE SPACE STATION AUTHORIZATIONS Transponders FCC Form 312 — Schedule S: (Technical and Operational Description) 59. SPACE STATION CHANNELS For cach channel $10. SPACE STATION TRANSPONDERS** For each (a) (b) (© KO (0 ... 00. (a) ... ® As ed Cont : TT&C i T d ( d C Channel mangiign DR rrequency Pelmsaten CommChainel ‘Transponder "@&dar"" cnBhey vigs Chginet Beam No. Cilte) Mode (MHz) (HLV.LR) (PorC) ID (aB) No. 1D No. iD ST3 4000 T 8030.0 € ST4 320000 7 8185.0 C 250 R 2085.6875 T ransponder between outpuof z ancnna and anenna. **Also complete this table for hall—links such as TT&C and processing. In such cases, Rev 4d, June 19, 2003, 5:45 pm provide the receive or transmit information, as appropriate. FCC 312, Schedule S — Page 6 June, 2003

FEDERAL COMMUNICATIONS COMMISSION Page 7: Digital Modulation SATELLITE SPACE STATION AUTHORIZATIONS FCC Form 312 — Schedule S: (Technical and Operational Description) S11. DIGITAL MODULATION PARAMETERS For each digital emission o 8 (h @ . saiihes @ wmties oc cBia meaten M§MID Mod. Noh Designator Bandiidn Ciz) Noo Phases Skie ) C Hopsdion smessone U Rate Gain (dB ST3 4M 4000 1 262 0.5 0 22.05 27.0 ST4 320MGTD 320000 2 256000 0.80 0 20.7 27.0 CMD 250KXFD 250 receive Rev 4d, June 19, 2003, 5:45 pm poustzAdietiesnel’;‘g)g7

FEDERAL COMMUNICATIONS COMMISSION Page 8: Analog Modulation SATELLITE SPACE STATION AUTHORIZATIONS FCC Form 312 — Schedule S: (Technical and Operational Description) $12, ANALOG MODULATION PARAMETERS For each emission ide: NONE i8 io © © 0 T j) Video (k) Video (Video & Analog Emission Agod foe miges per $ NSE wogh Modutatca Mod. ID Designator Cctte) (:eeyt?elow)| Camer " PAL, etc. (dB) Index *Indicate whethersignal is (a) FDM/FM, (b) CSSB/AM, (c) SCPC/FM, or (d) TV/FM. FCC 312, Schedule S — Page 8 Rev 4d, June 19, 2003, 5:45 pm ‘ June, 2003

FEDERAL COMMUNICATIONS COMMISSION Page 9: Typical Emissions SATELLITE SPACE STATION AUTHORIZATIONS FCC Form 312 — Schedule S: (Technical and Operational Description) $13. TYPICAL EMISSIONS For each planned of emission ; Modulation ID (©) (© (§) Noise () Energ ransmit St) ransmit ‘ y Transponder ID Range Carriers Carrier udget Dispersal AssocSin . ; Mix, Power Flux Density s @Sun ud AhS O Asdce per Spacing Reference. Bandwidth® Max.Antenna Msm FamssT (able S11) (TableS12) | kH2) (Table No.) (ciz) Gain (dBi) ; Max Min. m) Max. (@dBWinz wi * For those emissions using cnergy dispersall\,&mvide the bandwidth of the energy dispersal. Otherwise, leaveblank. **Use a Reference Bandwidth of4 kHz or 1 z as appropriate to the FCC Rules that apply to the subject frequency band (§ 25.208). pecarr. SCMU‘CJE,,’:;%&? Rev 4d, June 19, 2003, 5:45 pm

FEDERAL COMMUNICATIONS COMMISSION Page 10: TT&C SATELLITE SPACE STATION AUTHORIZATIONS FCC Form 312 — Schedule S: (Technical and Operational Description) $14. Is the space station(s) controlled and monitored remotely? If YES, provide the location and telephone numberof the TT&C control point(s). [m BeS C no Remote Control (TT&C) Location(s): STda. Street Address S1db. Ciy $He.Comy STHd. Sate / Country S1deZip Code STdL. Telephone Number S1dg. Call Sign of Control Station (if appropriate) S14a. Street Address S1db. City SHe. Comty SI4d. Sute / Country SideZip Code STIT. Telephone Number S14g. Call Sign of Control Station i appropare) §14a. Street Address S14b. Ciy S$He. Comy ST4d. Sate / Country S1deZip Code STdL. Telephone Number STdg. Call Sign of Control Station (if appropriate) $14a. Street Address S1zb. Ciy SHe. Comty SI4d. Sute / Country SideZip Code ST4T. Telephone Number S14g. Call Sign of Control Station (if appropriate) §14a. Street Address S1zb. City S1de. County S14d. Siate / Country Side. Zip Code STIT. Telephone Number 14. Call Sign of Control Sation (if appropnate) §14a. Street Address S14b. Ciy SHie.Comy ST4d. Sate / Country S1deZip Code STdL. Telephone Number STdg. Call Sign of Control Station (if appropriate) Rev 4d, June 19, 2003, 5:45 pm ECC312, bchcdulizlsr"ef’;‘gl&lo

FEDERAL COMMUNICATIONS COMMISSION Page 11: Characteristics & SATELLITE SPACE STATION AUTHORIZATIONS Certifications FCC Form 312 — Schedule S: (Technical and Operational Description) S15. SPACECRAFT PHYSICAL CHARACTERISTICS _QB—2 ST3a. Mass of spaceeralt without fuel (kB) 952.5 Spacecraft Dimensions Probability of S'uyvival S13b. Mass of fuel & disposables at launch (kg) (meters) to End of Life 76.0 (0.0 — 1.0) Si5c: Mass of spacecraft and fucl at faunch (Gg) STST Longth m STsL Payload 1028.5 1.6 0.7981 S13d. Mass of fucl, in orbit,at beginning of life (kg) Si5e. Width (m) S15j. Bus 76.0 L.3 0.9397 S15e. Deployed Area of Solar Amay (square merers) SiSh. Height (m S1SkToul 7.7 29 0.7500 $16. SPACECRAFT ELECTRICAL CHARACTERISTICS $ f Electrical Power (Watts) Electrical Power (Watts) paceoratt At Beginning of Life At End of Life Subsystem — — ; ; At Equinox At Solstice At Equinox At Solstice Payload (Watts) ®79 © 79 ® 79 P 79 Bus (Watts) __|© 4gg ©® ass ® qss ©@ 4ss Total (Waus) |© 567 ® 567 ( 567 © 567 Solar Array ® o7 ® m ® 721 © 721 (Watts) Depth of Battery] & ® © i. ® Discharge (%) 15 % 15 % 15 % 15 % $17. CERTIFICATIONS a. Are the power flux density limits of § 25.208 met? OA ves D No L NA b. Are the appropriate service area coverage requirements of § 25.143(b)(ii) and (iii), or § 25.145(c)(1) and (2) met? D YES D No |Z| N/A c. Are the frequency tolerances of § 25.202(e) and the out—of—band emission limits of § 25.202(f)(1), (2), and (3) met? IZI YES D No D N/A In addition to the information required in this Form, the space station applicantis required to provide all the information specified in Section 25.114 of the Commission‘s rules, 47 C.F.R. § 25.114. Rev 4d, June 19, 2003, 5:45 pm ECC312, bchcdulclsnref’;‘glgzl 1

ATTACHMENT B Summary Information Related to DigitalGlobe Non-GSO EESS Remote Sensing Satellite System 291698: v2

Mission Data Downlink Analysis 320 MHz DATA RATE DOWNLINK ANALYSIS Fo = 8.185 GHz DOWNLINK PARAMETERS: Frequency 8.185 GHz Orbit height in km 481 km Local elevation above hor. 5 degrees Data rate 320 Mbps Bandwidth 160 MHz Spacecraft ant. EIRP at max scan 59.0 dBm Slant range 2027.92 km Ground ant. G/T 30.8 dB/K BER 1.00E—09 Required Eb/No (without coding) 12.7 dB Hardware imp. BER loss —2.0 dB LINK CALCULATION: TOTAL POWER TO GROUND: Satellite EIRP 59.0 dBm Path loss ~176.8 dB Total loss (rain, polarization, etc.) —2.2 dB RECEIVER SENSITIVITY: Required Eb/No 12.7 dB Available Eb/No 23.3 dB DOWNLINK MARGIN 8.6 dB ANTENNA SIZES: Spacecraft Antenna Seqment Spacecraft dish diameter 9.8 inches Approx. HPBW 10.4 degrees Gain of spacecraft antenna 24.7 dBic Loss between HPA out and ant. output —3.6 dB Transmitter Po 6.0 watts EIRP of satellite system 59.0 dBm Ground Antenna Seqment Ground antenna G/T 30.8 dB/K System noise temperature 188.2 K (referenced at aperture) Directivity gain ground antenna 54.0 dBic Ground dish diameter 7.3 meters Approx. HPBW 0.4 degrees

QuickBird Wideband Power Flux Density as a function of Ground Elevation Angle 413500 14000 A——i——i——i——i——i—AA—AA—AAA————t———A4 14500 Power Flux Density [degrees] 15000 15500 160.00 16500 417000 uy + + + + + y + 0.00 10.00 2000 3000 40.00 50.00 60.00 70.00 80.00 90.00 =—Carmier Modulation AR—PFD Limitat Earth‘s Surface

Narrowband Downlink Link Analysis TELEMETRY DOWNLINK RT, PBK /NADIR EarthWatch FREQUENCY 8.03 GHz POWER 5 WATTS WAVELENGTH 0.04 METERS ALTITUDE 481.0 KM 5 DEG SLANT RANGE 2027.9 KM REAL TIME DATA ON 1.7, PCM/PSK/PM DATA RATE 16.384 KBPS PLAY BACK DATA PCM/PM DATA RATE 262.144 KBPS MARGIN 4B R/T MOD INDEX 11 CARRIER 29.4 PBK MOD INDEX 12 RT 19.5 PBK 156 ANTENNA: NADIR PARAMETER UnNITS VALUE 7 TOTAL TRANSNMIT POWER dBm 37.0 2 PASsIVE Loss dB —8.1 3 S/C ANTENNA GAIN >+/— 90 DEG dBic 0.0 4 FREE SPACE DISPERSION Loss dB 176.7 5 ATMOSPHERIC Loss dB 1.5 6 GROUND STATION G/T (spec) dB/K 315 7 TOTAL RECEIVED POWERT dBm/K 417.8 8 BOLTZMANN CONSTANT dBm/Hz—K ~198.6 9 TOTAL RECEIVED POWERKT dB—Hz 80.8 CARRIER CHANNEL 10 CARRIER/TOTAL PoOWER dB ~TLZ 11 CARRIER POWER/KT (min) dB—Hz 69.2 12 CARRIER LOOP BW (300 Hz) dB—Hz 24.8 13 CARRIER/NOISE dB 44.4 14 REQUIRED CARRIERNOISE dB 15.0 15 CARRIER MARGIN dB 29.4 DATA CHANNEL (PENMIPM) (playback 76 DATATOTAL POWER (Mi=1.2) dB 4.4 17 DATA POWER/KT dB—Hz 76.5 18 INFORMATION RATE 262 Keps dB—Hz 54.2 19 AVAILABLE S/N dB 228 20 REQUIRED Eb/No 10E—5 BER dB 11.9 21 CODING GAIN dB 5.2 22 AVAILABLE SIGNAL MARGIN dB 156 DATA CHANNEL (PCNUPSERPM) (real time) 23 DATATOTAL POWER (MI=1.1) dB T23 24 DATA POWERIKT dB—Hz 685 25 INFORMATION RATE 16 KBPS dB—Hz 421 26 AVAILABLE S/N dB 26.3 27 REQUIRED Eb/No 10E—5 BER dB 120 28 CODING GAIN dB 5.2 29 AVAILABLE SIGNAL MARGIN dB 19.5

25

S—band Command Uplink Link Analysis COMMAND UPLINK OMNI ANTENNA NOMINAL EarthWatch FREQUENCY 2.0856875 GHz UPLINK 45.0 dBw EIRP WAVELENGTH 0.14 METERS ALTITUDE 481.0 KM 5 DEG SLANT RANGE 2027.9 KM COMMAND DATA ON TONES DATA RATE KBPS CMD MOD INDEX 1.0 MARGIN dB CARRIER 8.0 CMD 3.0 ANTENNA: OMNI NOMINAL +/— 75 DEG PARAMETER UNIT VALUE UPLINK EIRP dBw 45.0 FREE SPACE DISPERSION LOSS dB ~165.0 POINTING LOSS dB —0.5 ATMOSPHERIC LOSS 42 mm/hr dB —0.4 S/C ANTENNA GAIN < +/— 75 DEG dBi ~16.0 POLARIZATION LOSS dB —3.0 S/C LINE LOSS dB ~1.1 TOTAL S/C RECEIVED POWER dBm —111.0 CARRIER PERFORMANCE NET RECEIVED POWER cBm 111.0 MIN CARRIER ACQUIS POWER dBm —119.0 MARGIN CARRIER ACQUISITION dB 8.0 COMMAND CHANNEL PERFORMANCE (M=1.0) NET RECEIVED POWER dBm —111.0 MINIMUMCMD CHANNEL POWER dBm —114.0 COMMAND DESIGN MARGIN dB 3.0

TECHNICAL CERTIFICATE I, Michael Martinez, 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 amendment 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. Michael Martinez Michael Martinez Director of Space Operations DigitalGlobe, Inc. Dated: November 19, 2010 27


Document Created: 2010-11-22 11:38:30
Document Modified: 2010-11-22 11:38:30
© 2024 FCC.report
This site is not affiliated with or endorsed by the FCC