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The dediated nature of the sumeiUUance required horn the satellite mea th;n~ the periods dnardwg which service is required are of short duraaion. T idly* a ~tellite in the b w UP^ orbitTU0) wccsesmy for SAR sprations takes only 5 minutes to traverse a "heatre meEasursw6 2QntQkm on the SidG! ad with only 2 such passes likely day, payload power demands can readily be mct from battcmies. "be advantqy of this to the platform desip is that relativdy smdl solar arrays cm then be used to collect electrical pwer and trickle-charge the batteries durisna the prolonged periods of payload inrachty. 2.4 Ssmm Dosdgm Gads The desien oals for the icnsor concept are show in $. able 1. A major diffiwlty in realising a radar desien off this sophistication is the achievement of such high resolutions and in the im lementation of a phascd array antenna ab P e to operate over isuch wide inwmmxmsi bandwidths. / Synthetic Aperture Radar '(SAR) is a sideways looking coherent irritn~gimg technique an able of produein8 rnq14k.e imagery. {AIR employs difftlmttnt principlles foi achievin rcsoludon in oQle two dimensions of the imaBery. Convewaisnal high resolutiooa radar techniques such as transwniutian~ a wideband, lowe duration pu8m caad correcolg anmatch~n? to it on reer+' bUWri! we employed in Ppnc dunension pqwmdidm 27-3 to tRK2 m?!eMiu@ 8rn& Tcbk a iflmu. .a the GpplrndWidOBls; commeun5ura8e \%;am rmlenaiiom BOP 8 dcty of me G~U8~0rn 00 a&mal$Be bm&duI$ me due 00 U$@ capabili0ies of vavefom d pew era to as mud digititseas and the dispersion Ullnl.aParegPg uhe U HeceiVg Chai!?I§. '&aPeDt impose$ $I redlo~c limit of Unless cbmps can be aopceed, a huPaher limitirolg fac~au will be the current o rating band Jlmdom defined by the Gdd AdViSQV %tdk COUlndl (wmc) which im se restriaionas of 300 MWZ at X-band (GGpB9) and WO MWZ at J-band (13.7CIHIa). Dispersion in the atmosphere md ionos here is not thought to present a majjou pm $, Bern and, if present, the effects could be removed using techniques equivalent to S~U~Q~OSUS. Ovtr31 it is felt that a resolution of Irn at baqd is feasible at a 30' gnhg angle. The synthetic aperture technique is employed in the damemion parallel to the satellite track This involves the coherent addition of many pulses to synthesize an ogertuue sufficienoly Pong to provide the desired resolution on the ground. "his synthesis is only passible if the variation in phase pasah from uhe sews& to the tar et and back is k n ~ to ~ 8 n fraction of t fl e radar wavekngoh along the synthetic aperture. This implies that very accurate knowledge of the orbital path of the satellite is required. Hobper,, for resolutions of the order.;i';@€., Im no measurement method of &@t;bkbit gives sufficient acmacy in realistic timescales. To sumournt this problem it is expected that autofocus techniques will have to be employed. These have the added benefit that they will also automatically correct for other effects which can alter the phase path length, such as atmospheric, ionospheric and gravity perturbations. 3 TACSAT SAR Sjettellite Concept
I I I I I ! I I I I I I ~ I I I I I I 0 I I I I ~ I i I I ! .; I I I I i I I I I I I I I I i I I I I I
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ADVISORY GROUP FOR AEROSPACE RESEAR
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Acccorclinp tto 11s C”liirlcr. th
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0 Im oyi.rationr rcccntc\ *Tcm+tc d
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Theme 'fieme 0 - 0 Avionics Pencl a
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-- Printed in Clawificcl puhlicatio
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1'. 2 c From tplc four pafcn. thcrc
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Talcs. Thc lcchnology emphasis wnr
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These arc three spccific fecornmen&
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when WO Rave gone from one'modsl sa
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3-4 mggd and easily operated. This
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3-6 interim capability should one o
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OI~UI'IS MISSIONS I PAYLOAD TYPE -.
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1 Int raduction The iiotcntial cxpl
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indicated hat an IR vcrsion of the
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a 0 Annex A Radar system A. I Backg
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Annex C ESM system C.1 Background A
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e communications, point to point, p
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(i-4 TACSAT Operations Phase The TA
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6-6 w J > a 3 v, [E ' 0 LL U3 I- Q
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(1-2 rcliabiliry pcrfornianccs, bot
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0 8-4 specific tools for each main
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0 0
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affichent un coot au kilo de 2 a 3
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I 1 - CONSTELLATION LAIJNCHES COST
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ls FIGURE 3 6-11
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a a
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SYmME DE NAVIGATION PAR SATELLIT'ES
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du sntcllitc fixCe. Aucunc controin
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0 0 ' ml 3200. 2800. 2400. 2000. 16
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A cct instant. ct si IC PDOP cat in
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giostationnaire (RS mlslnn contrc 5
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0 This pqxr is dividcd in lhrcc pat
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0 Grouad-air-ground communication T
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0 a .. . . .I AIR COMMAND AND CQNTR
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ENNEAAV ORDER OF BATLE ASSESSMENT D
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0 0 (CO") -COMMUNlCATlONTACSATSARE
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0 0 . 14-2 xiv)physical attack and
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14-4 There has been a minimum of jo
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Architecture TABLE -1 Number of Sat
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14-8 Table - 3 : The EHF Ground Seg
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0. 16-2 combincd analog and digital
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flgurm 2. Frequency Synlhmrlur Aduc
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L n , JA. " Flguro 5. LlghtwolgM LD
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GEOSYNCHRONOUSALTITUDEORBlT VARIABL
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I SYNCHRONIZATION TECHNIQUES FOR ME
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-U I 1 b I l l . . . . , Figure 2:
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@ & a time acquisition. Due to thc
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6 SYSIXM SYNCHRONIZATION ALGORITHM
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TACSAT payload. Sptinl and time syn
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\ I ..I , .. . . U' c L. rL 50 i !
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It is IqmmtQlive of the ,wc.sa Cmst
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I' !'.
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v / I ,p ,
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f I
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3. IAUWCUU SVSTEM SELECTION CRUQTXO
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19-41 5.8.1.8 A/Im faniity of whicl
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CURRLHT PRowcTKm N DEVELOPMENT " P
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.clrc;lih w m iua thc orhilot planc
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19-10 OcazO midm ~ r nof mp htb~rm
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19-12 0 'I% whicles must PW: lnunch
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8.3 Uniad KingdodWussia Inrtn'm HOT
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1P.16 'II-tcx chen@ngcnvimnmcntal c
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SPACECRAIT AND I.AIJNCII SIISlT.MS
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c Firvn 4. Horimld vrhiclr andpaylo
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H 8p~nwmd by DARPA ud will dcliwr8
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'ThcTauNt prylodckcoicwl inlnlactt
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20-10 (hcntercoaunnndma have ben di
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RESUME Puisque ks futun lanceun per
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. 232 CdcJ du IIIOIWYHI?~ Mmoeuvm m
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En rcvnnchc, m ce qui concemc la pe
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Lea masses d'ergoh pour les trois o
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- Figure 13 - Les orbiteo intermedi
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SVMMARy - rution inonly I5 monh. Qu
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I f igun 5-1 QulrUfar spcun@ syslrm
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?- I
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* Snull ground conlrol VMS 1s.a.a F
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.. 1. INTRODUCTION Attitude- and Or
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m, = f*U*d Whcn liquid bipropellant
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sensors, gyros) intorporated in the
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th: burn-our (or dry) mm and subsys
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23-10 between the modulator output
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23-12 . pcnsatc for thc imbact of l
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23-14 e I w 11 n IS n n a 41 U 9s M
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23-16 / Fig. 4.3.1: ICDS principle
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23-18 Communication Weat her - Oper
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23-20 r - .-_ -- - -. --_.._ I U i
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23-22 I .a * .o.s 8.2 am3 c 0.012 a
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PRW mrms lottrfrsa : UDir Bnterfscc
Page 351 and 352: 24.2 CJ6Qh ion pl'b;pPelaion tho ap
Page 353 and 354: 48 iao 4.b 11 8.2 19.3 26.5 88.6 C
Page 355 and 356: I I ! I i ~ I I I I I I I ! I I I I
Page 357 and 358: [ Z ] C. Purrotta, M.Bieconi, A. Bi
Page 359 and 360: I 23-2 2. ):SADLISG TF.CIISOLOGY PR
Page 362: 124.1 PhwdAwmy Mimv.~tnhbkL.u#eApn(
Page 366: Lulrhd durimilr NASA md Navy p*bd o
Page 370 and 371: 2s-a The paylord concept is distinc
Page 374: 2s-10 \ I i I f
Page 378: ~Y!!?w!L Tho fnasibllity of install
Page 382: c_- XZiiK matelT. mloy ka>r*can h.i
Page 386 and 387: , i'or a typical 708 operating duty
Page 388: Tho ]Lo~ton boU& Of the Dfb-UFfliTf
Page 392 and 393: I I 0 I I I I I , For tn ainglo pla
Page 394 and 395: NovorthdanfS high frograonq CIQBfi~
Page 396: 008e~Ensrr witfa ~ bde~ec~ion s of
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Page 404: 274 from soia may. For this mission
Page 408 and 409: =mitrioa~ ~ ~ h i frown ~ ~ e allei
Page 410 and 411: e The SAW must possess a raa)is$wet
Page 412: I I I ! 27-9 Different data rate: c
Page 416 and 417: In resent ears, industry made gr0fp
Page 418: I I I I I I , I .: I I I 27- 12 7.0
Page 422: 27-14 , I I
Page 426: , ._ .'< . , '\ '
Page 432: LOW.oIlN ANTENNA b ClsLEWRIP 4 SOWR
Page 436: NOI-1-0' MZ-1-90 NO 3- I I 57 NO1-1
Page 440: Cost Efl'ectivc TacSats for Militar
Page 444: ' Figure 3. Usa Driven Dwign Future
Page 448: L Figure 6. Tu&oprrpliom Rovi Usus
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Vlrtbl~ D~tect~n b Rows of 18um qua
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I I I . . / 0 - 0 0 0 0 0 0 0 0 0 0
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covering a variety of scenes, asses
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AbsltmsU 'E'AC.WT MEmOROWflCU PAYLO
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I I I I Trtarasiaiaand Pnogramme (M
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several chys. If S~CDPO term foreca
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e: l , / I Discussion Question: You
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7 t!lETTl?3T iDOCWMEWAmOT'd PAGE AG
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