San Marco-B Press Kit

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FOR RELEASE: IMMSDIATEU RELEASE NO: 67-93 April 17, 1967PROJECT: SAN MARCO-B

(To be launched no earlierE than April 22, 1967)CONTENTS

GENERAL RELEASE---------------------------------- 1-4SCIENTIFIC PURPOSE ------------------------------ 5EXPERIMENTS -------------------------------------- 5-6LAUNCH PLATFORM---------------------------------- 7SPACECRAFT------------ --------------------------- 8-11Instrumentation:Air Density Experiment Electronics ----------- 9-10Ionospheric Experiment Electronics ------------ 10Programmer and Safety Timer------------------- 10Power Supply---------------------------------- 11Telemetry Systom----------------------------- 11Command System-------------------------------- 11Antenna System------------------------------- 11COMMAND AND DATA ACQUISITION- -------------------- 12TRACKING- ---------------------------------------- 12KCOUT LAUNCH VEHICIZ----------------------------- 12-13SAN MARCO PERSONNEL--.-------------------------. 13MEMORANDUM OF UNDERSTANDING-------------mm--.... 14-16

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ENAAiNAL AERONAUTICS AND SPACE ADMINISTRATIO)N ELS WINW SWAHN10 (OMlFOR RELEASE: IMMEDIATEApril 17, 1967RELEASE NO: 67-93

SEA PLATFORMIS LAUNCH PA DFOR SAN MARCO

An Italian satellite, the first of any nation to belaunched into orbit from a platform at sea, is scheduled forlaunching from Formosa Bay off the coast of Kenya, Africa,no earlier than April 22.

The satellite, San Marco-B, has been designed and pre-pared by the Italian Commission for Space Research (CRS).CRS has also been responsible for the entire launch complex.The launch vehicle itself will be a four-stage solid propellantScout rocket furnished by the United States.

San Marco-B, like San Marco I which was launched by anItalian crew from the National Aeronautics and Space Adminis-tration's Wallops Station, Va., In December 1964, is acooperative CRS-NASA project under an agreement concludedMay 31, 1962 (text attached).

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Primary objective of the project is to obtain continuousequatorial air density measurements at satellite heightby monitoring the drag forces on a spacecraft. These measure.-ments are of particular scientific interest because twocurrently-used techniques give contradictory results. Asecond experiment will investigate ionospheric characteristicscausing interference with long-range radio transmissions.

The launching platform which looks much like an off-shore oil drilling platform, is also called San Marco. Itis stationed three miles off the coast of Kenya about 2*degrees south of the equator. A smaller platform, the SantaRita, located about 500 yards from the San Marco platform,contains the control end operations center, range equipmentand test rooms. The two platforms are connected by submarinecontrol and power cables.

The 285--pound satellite will be launched into an orbitinclined about 2t- degrees to the equator, with a perigee ofabout 135 miles (214 kilometers), an apogee of about 420miles (677 kilometers) and a period of 94 minutes.

The measurement of air drag forces is accomplished bya payload configuration consisting fundamentally of twoconcentric structures--a heavy spherical structure containedin a much lighter spherical outer shell. The two spheres arelinked by non-rigid connections.

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-3-When the satellite moves toward the inner part of Its

orbit, the light outer shell encounters the thin upperatmosphere and is retarded by this drag to a slight degree.The heavy inner core, however, continues traveling unaffectedexcept for the forces transmitted by the flexible connections.The result Is that the distances change between the outershell and the "floating" inner core.

Equivalent position changes take place in three flexiblearms that connect the core and the shell. The precise degreeof movement, reflecting atmospheric drag--the air density--is measured by strain gauges and transmitted to groundstations by radio.

The second experiment, with instruments attached to theinner core, will investigate ionospheric Irregularities andelectron content.

Both experiments will operate at maximum advantage as aresult of the equatorial orbit, which eliminates any effectsof latitude differences on the experiment. Selection of anequatorial orbit also makes possible reception of data fromthe area of coincidences of the geographic equator and themagnetic equator.

Under the 1962 agreement, NASA is providing the launchvehicles, use of its facilities a-nd tralning 1oi* Italia.personnel.

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The Italian group is responsible for design, fabricationand testing of all payloads and experiments as well as thelaunching of the Scout. The Italian team established therange, including the mobile platforms, and, with some supportfrom NASA, tracking and data acquisition facilities necessaryto the project.

Nq exchange of funds between the two countries isinvolved. Scientific data resulting from the program will bemade available to the world scientific community.

About 75 members of the Italian San Marco project teamhave been in training at intervals for the past few years atWallops Station, Va., and other NASA facilities as well asat Ling-Temco-Vought (LTV), Dallas, Tex., the Scout primecontractor.

(END OF GENERAL RELEASE; BACGROUND INFORMATION FOLLOWS)

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-5-SCIENTIFIC PURPOSE

The scientific purpose ofr the San Marco Project is toperform a serios of experiments of common interest to NASAand the Italian Commission for Space Research. Primarypurpose of the experiments is measurement of local densityin the upper atmosphere in the equatorial region.San Marco I

San Marco I, launched Dec. 15, 1964, provided data which:1. Confirmed the usefulness and reliability of the dragbalance device for accurate determination of airdensity values.2. Demonstrated that the drag balance could be used todetermine the attitude of the satellite and to obtaina better understanding of the drag coefficient and itsvariations with time.3. Are of scientific interest when compared with other dataavailable on air density.

EXPERIMENTSThe purpose of the experiments aboard the San Marco-Bspacecraft is to investigate the Earth's atmosphere charactar-istics. The specific areas to be investigated are:-- The atmospheric density in the altitude range betweenapproximately 135 and 217 mihes (214 and 350 kilo-meters).-- The electron content between the spacecraft and ground,the local electron density irregularities, and theguided propagation phenomena (ducting) particularlyaround tht geomagnetic equator.

Air DensityThe purpose of this experiment is to perform a continuousand direct measurement of the atmospheric drag and, therefore,or the atmospheric density in a range of altitudes from perigeeto approximately 350 kilometers. The experiment will permitmeasurement of short-period variations such as the daily densityvariations and particularly those linked to magnetic storms.

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-6-The continuous measurement should assist in determining

thr molecular temperature of the atmosphere and, with someanisumptions, the mean molecular weight. The spin rate ofthe spacecraft must be minimized because of the sensitivityof the air density balance. Therefore, the spacecraft isdespun to less than 6 rpm shortly before spacecraft separation.The spacecraft spin axis has a random orientation.onoereEerent

The purpose of this experiment is to measure the totalelectron content between the spacecraft and ground, studythe ionospheric irregularities responsible fo r scintillationin the equatorial zone, and investigate the ionospheric guidedpropagation (ducting) phenomena. Because of the low-inclinationorbit of the San Marco-B, particular propagation conditionsmay arise that allow an easy evaluation of the total electronnumber by measuring the spacecraft signal vector rotationangle.The investigation of' the total electron content and its

variation with time and longitude is of particular interestbecause of the equatorial ionospheric anomalies. Irregularitiesin electron density distribution will be detected throughamplitude scintillation of the received signal and by directmeasurement of the fluctuation3 of the antenna impedancetelemetered to the ground.The ducted phenomena will occur when the spacecraft passesimmediately below layers of high electron density. The space-craft Signals, which pass between the ionized layers at a lowangle of incidence, can experience the guided propagationphenomena which permit signal transmission for great distances.

The possibility of receiving a spacecraft signal guided viaan ionospheric duct at a ground station is related to theexistence of a gate through which the signal can reach theground. The gate is primarily caused by lack of uniformity inthe ionosphere.

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LAUNCH PLATFORMLaunching of' San Marco-B will take place from a mobile baseconsisting of two floating platforms which are fixed to the seabottom by movable legs. Use of this type of launch platform,never previously employed, has the following advantages:1. Makes possible launchings by a country whosegeographic location does not permit launchings

from within its own borders,2. Permits launchings from a wide variety of locations.The San Marco rocket launching platform was originallypart of a U.S. mobile facility. It has 20 steel legs firmlyembedded in the sandy seabed at latitude 20 - 56' - 40" South,longitude 400 - 12 ' - 47" East--ideal for equatorial spacelaunchings. The 120-foot shed which houses the Scout vehicleprior to launch Is air conditioned for environmental control.A large pit on the launch platform, open to the sea, will absorbthe rocket exhaust of' the Scout first-stage motor.The Santa Rita platform, a modified oil drilling platformbuilt by the Italian firm Nuovo Pignone, contains the nervecenter of the project, the control room, and houses the trackingand instrumentation required to launch and track the Scout.There are 23 cables linking the San Marco launch complexwith its sister platform. Some idea of' the complexity of theoperation can be gained from the fact there are more than 3,000connections of various kinds linking the two platforms.Independent generators at the two locations produce electricity

at two voltages to r;meet the requirements of the scientificequipment and the housing and other facilities.

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I9'-'JCH, 136- TO 150 -MHzTELEA.CTRY AND CONVMJAND?.1ONOPOLE ANTENNA (4)

VIGO - s>CH 20 MHz IONOSPHEREEXPERIM.1ENT MONOPOLE ANTENNA. (2 )

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SPACECRA!'TThe Sari Marco is a 26-inch-diameter sphere with four 19-inch monopole antennas for telemetry and command and two re-tractable 100-inch monopole antennas for the Ionospheric ex-periment. Six solar cells, mounted on the spacecraft shell,provide a rough indication o1' the satellite attitude.The structure of the spacecraft forms an integral part ofthe air density experiment. The experiment configuration con-sists of a light external shell connected through the elasticelements of the air denbity measuring balance to the heavierinternal atruc'ure of' the spacecraft. The internal structureconsists of' a cylindrical center post and a central drAm. Thelongitudinal stre3sses aro supported primarily by the centerpost. A system or diagonal struts connects the periphery ofthe drum tv the poles of the cylinder to increase the space-craft rigidity.The power supply, consisting of four battery packages, iestored inside the drum. The spacecraft electronic instrumenta-tion is mounted on the upper and lower sides of the drum. Theair density balance is housed in the center of the cylindricalpost, in a pooition ot' symmetry with respect to the inner andouter structures. The spacecraft main body Io connected to thelaunch vehicle during the launch phase by means of an adapterring Joined to the cylindrical post by eight short ribs. Themain body of the spacecraft is constructed of aluminum alloys.The outer shell of the spacecraft and the arms which con-nect the shell to the air denaity balance constitute the movablestructure of' the spacecraft. The shell is a thin-walled sphererormed from spun aluminum. The tubular arms are connected atthe poles of the shell and go through the center post to thebalance element. A series of windows is provided on the shellfor the umbilical and continuity plugs, the antennas, and theeight columns of the adapter ring.A pneumatic caging system protects the air density balancemechanism fromi excessive loads during launch. The system con-nects the outer shell directly to the inner structure, therebyby-passing the balance mechanism.In addition, the elements of the balance are separatelycaged by actuators operated by the pneumatic system. At launchthe pneumatic system is under pressure. The pressure is re-leased at spacecraft separation, thereby uncag.ng the balancemechanism.

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InstrumentationThe spacecraft electronic instrumentation has been dividedinto the following seven main systems:, Air density experiment electronics (drag balance). Ionospheric experiment electronics* Programmer and safety timer. Poter supply* Telemetry system, Command system* Antenna system

Air Denalt~y Experiment ElectronicsThe air density experiment performs a continuous measure-ment of the forces (aerodynamic pressure) acting on the externalsurface of the spacecraft. The main instrumentation of the ex-periment is the air density balance, an elastic system that con-nects the external shell to the inner structure of the spacecraft.Three orthogonal elastic elements connected in series are used toseparate the three components of the total force along the prin-cipal axes of the spacecraft. The displacements of the elasticsystem are amplified and demodulated to obtain dc signals pro-portional to the force components.The sensitivity of the balance system can be changed from2.5 gram full-scale to 1 gram full-scale by ground command. Inthe 2.5-gram full-scale mode, an automatic change of gain of theamplifier (1 to 10 ratio) is provided to obtain an extension ofthe measured forces up to 25 grams. Zero shirt of the balance(within + 80% of full-scale) can be corrected by ground command.The zero shift correction circuit consists of three do-motor-driven potentiometers, ono for each axis. Correction sig-nals obtained from the potentiometers are added to the outputsof the balance to compensate for shifts in the balance outputs.Commands are provided to produce clockwise or counterclockwiserotation of the motors. The length of the second execute toneof these commands can control the magnitude of the shiftcorrection.

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An in-flight callbra-.on szgna1 Is included with the airdensity experiment. The signaL consists of' three levels of -second duration each and is stvperimposed every 32 seconds oneach of the three force channels.ionoopheric Experimerit ElectronicR

The ionospheric experiment consists of' an I1W transmitteroperating at 20.005 MHz. The transmitter carrier in frequency-shirt-keyed (FSK) for recognition of the radiated signal. Thetransmitter Leeds two monopoles of an extensible dipole antennathrough a matching network. The antenna, normally retracted, isextended when the ionospheric experiment is turned on by groundcomand. The niormal characteristics of the transmitter are:

Frequency 20.005 MHzOutput powov V00 mwk'SK fre4uency shil't -100 Hz to 20.0049 MH zAmplitude modulation 0.1 db

Programmer wid Safety _TierThe programmer, which is activated by ground command, Isused to control the air density experiment and/or telemetrytransmitter. When the proper command is received, the pro-grammer performs the following actions:

Turns on the air density experiment (using the dragbalance electronics) and the telemetry transmitter.

Starts an eight-minute ttming cycle.At the end of the eight-mlnute timing cycle, turns offthe air density experiment and telemetry transmitter.

Normally the air density experiment and telemetry trans-mitter will be turned of V by ground command before the programmercompletes its eight-minute timing cycle.The San Marco-B has been equipped with a safety timer so

that data can still be retrieved even though the command sys-tem fails. The safety timer will automatically take controlof experiment selection, if no air density experiment commandsare received during a six-day period.-more-


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Power SupplyThe source of power for the San Marco spacecraft is agroup of mercury batteries. The individual batteries, MalloryRM-42R, 14-ampere-hour capacity, are connected in series togive the rated voltages and then in parallel to give the totalrated current. The batteries are arranged in four separatepackages that provide these outputs:+28 volts -20 volts416 volts - 6 voltsDiodes are connected in series with the battery packagesto avoid back-current.

Telemetry SystemThe PA.M/FM/PM telemetry system consists of four continuouschannels (four low-level VCO s) or 14 data and one subcommu-tated channel (a high-level VCO) of PAM data. Three or thelow-level VCO's are used to monitor the air density experiment.The fourth low-level VCO is used to monitor the variation ofantenna impedance when the ionospheric experiment is on, andto monitor the spacecraft shell temperature when the experi-ment is off. The PAM pulse train obtained from the PAM com-mutator (used for housekeeping and experiment data) modulatesthe high-level VCO. The VCO outputs modulate a PM telemetrytransmitter. Two telemetry transmitters (136.74 MHz) are pro-vided, one for redundancy. The desired transmitter is selectedby ground command.

Command SystemAn audio tone command system is used aboard the San Marcospacecraft. A command frame consists of an address tone andtwo execute tones. The address tone is transmitted f"irst toarm the tone decoder for a four second period during which thetw o execute tones are sent. The command tones are OSFC-standardexcept that the width of the second execute tone can be variedbetween 0.15 and 1.7 second for the air-density-balance shiftcorrection. Variable width tones will be transmitted only bythe Mobile Italian Telemetry System (NITS).

Antenna SystemsThe 136- to 150-MHz antenna system (used by the tw o tele-metry transmitters on 136.74 MHz and the command receiver on149.52 MHz) consists of four monopole antennas (19 inches long)mounted on the equatorial plane of the spacecraft in a turnstileconfiguration. A coaxial hybrid multiplexer network, with fourterminals, Is used between the antenna and the transmitter andreceiver circuits.


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COMMAND AND DATA ACQUISITIONThe Mobile Italian Telemetry Station (MITS) will have pri-mary responsibility for commanding the San Marco-B and for ac-quiring telemetry data from the spacecraft, In addition, twoUniversity College or Nairobi stations (located at Dar es Salaam,Tanzania and Asmara, Ethiopia) and an Italian station in Nairobiwill be responsible for acquiring ionospheric experiment data.QUITOEo NASA's station at Quito, Ecuador, will be respon-sible for commanding the spacecraft and acquiring ionosphericand air density experiment data. LIMAPU, the NASA station atLima, Peru, will be responsible for acquiring ionospheric ex-periment data and will act as back-up to QUITOE for commandingthe spacecraft.

TRACKINGDuring the launch and early-orbit phases, tracking datawill be obtained by the following participating stations and

trackJng organizations:. Llma, Peru (LIMAPU). Quito, Ecuador (QUITOE). Mobile Italian Telemetry Station (NITS). Santa Rita Station (SRS). North American Air Defense Command (NORAD). Smithsonian Astrophysical Observatory (SAO)During the normal phase of operation, tracking data willbe obtained by the Satellite Tracking and Data Acquisition Net-work (STADAN). QUITOE will provide primary tracking support.LIMAPU will provide a limited amount or additional trackingsupport.

SCOUT LAUNCH VEHICLEScout is a multi-stage launch vehicle using four solidpropellant rocket motors capable of carrying payloads of vary-ing sizes on orbital, space probe or reentry missions. Scoutis 72 feet long and weighs 20 tons at llftoff.It was developed by NASA's Langley Research Center,Hampton, Va.

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FEET72 ,

SAN MARCO-8FOURTH STAGE SPACECRAFT

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The four motors are interlocked with transition sectionswhich contain guidance, control, ignition, instrumentation sys-tems, separation mechanisms, and spin motcrs. Guidance is pro-vided by a gyro system and control is achieved by a combinationof aerodynamic surfaces, Jet vanes #nd hydrogen peroxide jets.Scout is capable of placing approximately 310 pounds intoa 300-mile circular orbit or of carrying a 100-pound scientificprobe some 10,000 miles away from Earth.Scout stages include the following motors:First Stage: Algol IIB - 100,900 pounds thrust, burningtime 80 seconds.Second Stage: Castor II - 60,760 pounds thrust, burningtime 40 seconds.Third Stage: Antares II (ABL X-2t,9) - 20,940 poundsthrust, burning time 35 seconds.Fourth Stage: Altair FW4-S - 5,750 pounds thrust, burningtime 31.5 seconds.

SAN MARCO PERSONNELThe project was conceived by Professor Luigi Broglio,chairman of the Italian Commissioa for Space Research and direc-tor of the San Marco Project. The payload was developed by Pro-fessor Broglic and his group at the Aerosp. e Research Center inRome.Professor Broglio will direct the Italian Spacc Commissionteam during the operation. Professor Michele Sirinian is LaunchCrew Director and Dr. 0. Ravelli is Chief Spacecraft Engineer.Overall direction of NASA's participation is under >Office of Space Science and Applications in cooperation h theOffice of International Affairs.Langley Research Center, Hampton, Va., is responsible fortechnical direction of the NASA portion of the program and par-ticipated in training of the Italian launch crew.Wallops Station trained Italian range support and operationpersonnel.Goddard Space kFlight Center, Greenbelt, Md., will assist

in worldwide tracking and data acquisition.NASA Program Manager is Dr. Russel K. Sherburne, OSSA,Launch Vehicles and Propulsion Programs. Tne Project Manager,at Langley Research Center, is Roland D. English. Louis P. Tostiis Langley Operations Director and Anthony Caporale is GoddardProject Engineer. -more-


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MEMORANDUM OF UNDERSTANDING 3ENE I TIMITALIAN SPACE CCt4ISSION OF THE NATIONAL COUNCIL OF RESUACE

AND THEUNITED STATES NATIONAL AERONAUTICS AND SPACE ADWINIBTRATION

1. The Italian Space Commission of the National Council of Psearch(The Commission) and the United States National Aeronautics and SpaceAdministration (NASA) affinn a mutual desire to conduct a serieu ofexperiments which it is hoped wiLl culminate in the launch'ng of ascientific satellite into an equatorial orbit. The objective is toperform measurements of atmospheric and ionospheric characteristics Ina region of the earth's atmosphere not previously explored and to make theresulting scientific data freely available. This experimental program isplanned to consist of three phases:

(a) First phase -- An appropriate sounding rocket will be utilizedto provide a flight test of the principal elements of the scientific payload.This launching will take place from the Wallops Island Station and/or froman Italian platform of the San Marco type located near the equator.

(b) Secord phase -- A prototype of the ultimate satellite payloadwill be placed in orbit by means of a Scout booster launched fro% th e WallopsIsland Station.(c) Third phase -- A scientific 3atellite, bearing experiments

as described above, will be placed in an equatorial orbit by meano of aL'out booster launched from a platform of the San Mhrco type, located Inequatorial waters.

2. The cooperating agencies shall proceed from each phase to the nAtupon mutual agreement that technical feasibility has been demonstrated and,in particular, that environmental requirements for the third phase of theprogram have been satisfied.3. The Comnission shall, in general, assume responsibility for the'

following:(a) Sutpport of Italian personnel for any training required Inlaunching, tracking, data reduction an d analysis, and other elements of theprogram, as mutually agreed.(b) Design, fabrication, and testing of all payloads, includingsatellite engineering.

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(c) Such studies and action as are reiuired to &scure amatually acceptable environment for transport, handling, and launchingof the Scout in the third phase of the program.(d) The availability, equipping, maintenance, and operationof the "San Marco" towable platforms.(e) The establishment of a suitable launch complex for thethird phase of the program, including range safety provisions, as mutual.ly agreed.Ct) Launching of the satellite in the third phase of the pro-gram(g) Data analysis in all phases of the program.(h) Tracking and lata acquisition facilities required in PhaseIII that are particular to Projoct San Marco and which are not availablefrom NASA.(i) Support, logistics, and all other costs peculAAr to rot*ectSan Marco.

4. The ITASA shall be responsible, in general, for the following:(a) Provision of an appropriate sounding rocket and backup,as mutually agreed, for the first phase of the program.(b) The provision of Scout boosters vith backups for the secondand third phases of the program.(c) Such training of Italian personnel as ray be feasible, adas may be accommodated wvthout significant incremental expense.(d) Technical consultation, as appropriate.(e) Such additional ground testing of the payloads as may berequired(f) The provision of data to facilltate effective designrfabrication, and testing of the payloads.(g) Tracking and data acquisition in he first and secon phasesof the program as con be accomplished by existing YASA sounding rocket and

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(h) Provision of tracking and data acquisition services ofthe "uto, Ecuador, Mini~&ck Station in phase three of the program,wd such additional communications support at other locations as my befeasible on a non-interference basis, subject to the concurrence, asappropriate, of any foreign governments involved. Special. equipment orpmrrsonnel needed in his connection will be the responsibility of TheCcmission.No exchange of funds is contemplated between the two cooperating

6. lach agency agrees to designate a single project annger whoshall be responsible for coordinating the agreed functions and rspouste.billties of each agency with the other. Together they will establish ajoint working group with appropriate membership. Details for implementa.tios shall be resolved on a mutual basis within this working group.7. The scheduling of each of the three phases of the program shallbe as mutually agreed.8. All launches vhich are a part of this program will be in suchareas as may be agreed between the two agencies which shall consult theirgovernments, as appropriate.9. This Memorandum of Understanding shall be subject to the tics.currence of the Italian'Foreign Office and the U.S. Departent of State,expressed through an exchange of notes.

FOR THE CGMYSION: rOR XABA:

4 rofessor Luigi 3roglio Dr. H. L.Geneva - May 31, 1962

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San Marco-B Press Kit

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