nimbus-e press kit

8/8/2019 Nimbus-E Press Kit

1/40

p -'/!o 3Sl NATIONAL AERONAUTICS AND

SPACE ADMINISTRATIONWashington, D. C. 20546202-755-8370

FOR RELEASE: SundayDecember 10, 1972p PROJECT: NImBUS-E

RE contenSHGENERAL RELEASE ............................... 1-11SNIMBUS-E FACTS............... ................... 12-13S TH E NIMBUS SPACECRAFT ........................ 14

NIMBUS-E EXPERIMENTS.......................15-24ESMR...................................... .15-16SCMR .................................... .16-18ITPR......................................18-19NEMS............................... .. 20-21SCR...................... ............... 21-22K THIR.....................................22-24

S THE NIMBUS PROGRAM.............................25-29I DELTA LAUNCH VEHICLE . ................. ... 30-33The Flight...... ... ................ 31

Ground Equipment Contractors.. .......... .37

I T AJOR FLIGHT EVENTS ..... ... ,....:: "IMBUS-E TEAM .. ... .. .. .......... 34 39

Nimbus-E Project Officials....... ........ 34-35Spacecraft Contractors .................... 36-37Ground Eqipment Contractoi,5 .............. 37Experiment Contractors.................... 38Launch Vehicle Contractors ................ 38-39

Noma o ""'


2/40

--- --- --- -

NATIONAL AERONAUTICS AND\ SPACE ADMINSTRATION\ Washington, D. C. 20546oe phFOR RELEASE:Joseph J. McRoberts

(Phone: 202/755-3680) SundayDecember 10, 1972James F. Lynch (GSFC)(Phone: 301/982-6255)RELEASE NO: 72-234

ATMOSPHERE, OCEAN AND SURFACE MONITORING SATELLITE TO BELAUNCHED BY NASA

A satellite which will take the first verticaltemperature readings from space through clouds, monitor amysterious disappearing current off the west coast ofSouth America and thermally map the earth's surface sogeolcgists can better understand what is happening belowthe crust, will be launched soon by the NationalAeronautics and Space Administration.

Nimbus-E (Nimbus-5 in orbit), named after the Latinword for rain cloud, will be launched by the NASA noearlier than December 12 from the Western Test Range nearLompoc, Calif. A two stage Dslta rocket will place the"butterfly"-shaped observatory into a near polar, circularorbit 1,103 Km (686 statute miles) high.

-more- November 29 , 1972


3/40

-2-The 772 kilograms (1,695 pounds) applications sppce-

craft, leaviest yet in the Nimbus series, will carry sixadvanced instruments or sensors -- three improved sensorssimilar to those aboard earlier Nimbus spacecraft andthree brand new ones. These experimental sensors, designedto imprcve man's knowledge of his environment for thebenefit of all mankind, will make th e most precise measure-ments yet from space of th e oceans, atmosphere and th eearth's surface. Measurements of th e entire globe will bemade twice in every 24-hour period, once in sunlight(about local noons and once again in darkness (about mid-night).

"The ability to make vertical temperature and watervapor measurements of our planet 's atmosphere for thefirst time through clouds is truly a giant step forward inmeteorological research," said Dr. William Nordberg, ProjectScientist from NASA's Goddard Space Flight Center,Greenbelt, Md. "Many parts of the world are under cloudcover more than 50 percent of the time. But now, with th emicrowave instruments aboard Nimbus-E, we will be able topenetrate most clouds. Precise temperature readings willbe a great help to meteorologists for helping to improveweather forecast over long periods.

-more-

r


4/40

-3-"The data from the microwave instruments will also be

helpful to ships operating in the Arctic and Antarctlcregions," said Dr. Nordberg. "Thin clouds, such as cirrueand stratus which are predominate in the polar regions,are relatively transparent in the microwave portion of theelectromagnetic spectrum. We plan to map surface ice andwater with the microwave sensors aboard Nimbus-E and wemight even be able to differentiate between the old andmore recently formed ice," Dr. Nordberg said.

Sensors aboard Nimbus-E will also map the Gulf Streamoff the East Coast of the United States and the HumboldtCurPent off the West Coast of South America.

The Gulf stream meanders up to 81 km (50 miles) fromCape Hatteras, N.C., to Florida. Infrared sensors aboardNimbus-E will plot the stream's daily position fo r theNavy's Fleet Weather Service. By knowing the stream'sspecific location each day, southbound ships will try toavoid it while northbound ships will ride in the streamreceiviri a few extra "bonus" knots per hour. Sub-stantial savings can be realized by shipping interests byknowing the location of the stream on a daily, routinebasis.

-more-


5/40

-4-Changes in the Humboldt Current off the West Coast of

South America have puzzled oceanographers for years. Onemajor change now underway and causing great economicdamage is called El Nino. The change begins aroundDecember with a movement of warm equatorial watersouth. The coastal waters warm up. This causes thenutrient-bearing cooler waters of the Humboldt Current,which normally control the weather, to disappear. As aresult, the fish also disappear along with marine birdswhose droppings provide a major fertilizer export calledguano. Even crops along the coast are washed away fromthe heavy rains and flooding that accompanies El Nino.

The last severe El Nino was in 1957-58, however therehave been minor ones in 1953, '63, '66 and '69. Scientistsfear the one now believed to be slowly forming may beanother severe one.

Nimbus-E may be able to provide valuable scientificdata on causes of El Nine which would include sea surfacetemperature measurement, vertical atmospheric temperatureprofiles and cloud distribution.

-more-*k


6/40

-5-Nimbuts-E also carries an earth resqurXes #E4perimbent,

technically tamed Surface Copomstion Mapping RaLdoafterlt (SCMR). This versatile experiment will provide new

Information in the fields of geology, hyrtology, tAgronomy,Soceanography and rmteorology. The tnatruwnt vwil maourethe temperature of the earth' or4st tw1o0 daily (about

( noon and midnight). The data from thiU experiment isSespecially attractive to geologists because by obervingJ the change in ten~ratur throughout the day, one can inrer

) what is happening below the earth'ls srfoce.Six highly advanced miteorolo6cal1 and earth resources

experiments a. aboard the imbuse- apaIperwa t. They a#rt{ Electrically Scanning Msawave RadiometUr (3MR)I Infrared Toeperature Profile Radiometer (IcPt)

Nimbus-- Microwave Spectrometer (~Mfl)I Surface Composition Miaping Radiometer (Sw,)

Selective Chopper Radtioter (3CR)Temperature Humidity Infrared fRdiometer (THIR)This is the first flight for the SSnRt, N=, , XTPR and

SCMR aboard a Nimbus spaeocraft. The SC Rnw TlIR areimproved versions of instruments which have flown onearlier Nimbus missionsr

i

atM .n a a u a moab


7/40

-6-For the first time from space two of the instruments

(ESMLR and NEMS) will utilize the spectrum's microwaveregion for remote sensing. Some clouds, such as cirrusand stratus, are relatively transparent in the r-.crowaveregion, but opaque in the infrared. Thus, the two sensorsare expected to greatly increase the observatory'scapabilities during many cloudy days.

The ESMR will globally map the thermal radiationemitted by the earth's surface and by the atmosphere. Themeasured absolute intensity of this radiation and, inparticular, the mapped radiation patterns reflect a numberof important physical properties of the surface andmeteorological conditions in the atmosphere. Over water,temperatures measured by the satellite will vary widelydepending primarily on the thickness and liquid watercontent of the overlying clouds. Heavy rain clouds, whichmay be indistinguishable in the visible or infrared fromcirrus or stratus clouds containing little liquid water,will be easily identified and tracked at this wavelength.

The ITPR will measure the earth's terrestrial andatmosphere radiation in seven spectral bands. One of thebands will be used to determine earth surface temperaturesin the absence of clouds or cloud top temperatures.

-more-

*^-------_________- -.. -. .- ^ .. .


8/40

-7-The NEMS will demionatrate the capabitltius of ma rro-

wave senaors for measurt g trupof!pheri" ttmprfture pro-files, water vapor abundance and water tontntent or tl*.udereven In the presence of mAny cloud typ~.tt whiv, bloc;k rinrfared sensors. Although infztred sRensora readily probecloud-free regions, large sections of the globe arefrequently blanketed by tirrus or oth@r cloudi, Microwavesensors have moet of the advantages of infrstd sensors,but are much less oensitive to clouds. Thus, they havethe potential of providing temperatur profile infoYrmaton,water vapor abundance and cloud water .'ontent on a globalscale under most meteorologioal conditions.

The SCR obs~rves global temperature atructute of theatmosphere at altitudee from cloud tops up to 50 kilometers(31 statute milesa) The radioniter allows temperature tobe taken along a strip 11 kilometerP (7 statute miles)long in the direction of flight by 113 kilomiters (70statute milea) wide, The SCR was provided by the UnitedKingdom through a cooperative project between NASA and theBritish Science Rozearch Council.

-more-

I


9/40

r

-8-

The SC0n measures differenee-n in the t.hetrml ~i t:;1'onicharacteristics of the earth's surface. By ?..na'rin,these difference in thermal temuiaton of igneou;is ock, forexample, it will be possible to ldentify their types :ucthas dunite, basalt, nyonite or grante. The SICM wil3monitor infrared radiation from the earth in threespectral bands. From measurements of shese thermalemissions, sclentists expect to deduce the nature ofsurface composition, thermal maps of earth aurtace, andtemperature gradient maps,

The combination of all three instruments, the ITPR,SCR and NENS, for vertical soundint of the atmosphere is apowerful new approach in meteorological research from$pace.

The THIR experitnt is prima.rsly a service system toprovide cloud and water-vapor data to experimenters. TheTHIR will measure infrared radiation from the earth in twospectral bands and from these measurements provide thefollowing during both day and night portions of the orbit:

Cloud-cover pictures;Three-dimensional mappings of cloud cover;Temperature mapping clouds, land, and ocean

surfaces;-more-


10/40

cli~rn-vs cloud conitent and cotaidnaton; and

The fti~iokn obJeetIves or MNmbua-Z t~m,:* Develop advainced paselve radiometr'Ic and

setrometric sensorti for daily global surveillance of theear~thlkn atmospheret to p~rovlde a data baiis for longrangewea~ther foecaiting specifically to com~pare vertioalsol~nding techniques leading to the Global AtmfosphericResearch Program.

# Develop and A-valuate new active and passivesensors for sounding the earth's atmosphere and mappingsurface characteristics and to extend imagin~g Int~o un-explored spectral regions, with higher spatial resolution.

* Develop advanced space technology and groundtechniques for mneteorological and other earth-observationalspacecraft.

* Participate in global observation programs~(World Weather Watch) by expanding daily global weather

-v observation capability.* Provide a supplemental souree of operation~al

meteorological data.

-more-


11/40

Sensor data obtained will be usea to support thedevelopment of improved inumerlcal methods for weather fore--az.t.ing and deter, .rn atmospheric behavior. The data isexpe",ted to al.nfltacantly advance the internationaleMather Informaticn excharne of the World MeteorologicalOrganzatron and the Global Atmospheric Research Program.Techniques to communceate these data rapidly and reliablywill be developed concurrently.

The Nimbus satellite program was initiated by UASA in1959 to develop an observatory system capable of metingthe resea'ch and development needs of the nation'satmospheric and earth sciences program.

The first vehicle was launched in 1964. In the inter-vening years the project has matured to become the nation'sprincipal satellite program for remote-sensing research.Each observatory has grown significantly in sophistication,complexity, weight, capability and in perfornmace.

Nimbus-E is the sixth spacecraft in a series of sevenapproved in the program. All of the satellitea, with thexception of Nimbus-B, have met or exceeded their missionobjectives. Nimbus-B never achieved orbit because of alaunch vehicle failure. Nimbus-F, is scheduled forlaunching in 1974.


12/40

The Nimbus program is minaged by rJASAla Office ofApplications, Wauhiington, DC. NASA's Goddard Space FlightCenter., Gi,%eenbelt, sdis respons-lb~c f'or both the space-Craft and the launch vehicle.

Lautich operations will be cnorducted for NA4SA by theU.S. Air Force 6595th Aerospace Test Wing under thetechnloal 3uperv3.slon of~ NASA's Unmanned LanhOperations,Konn~tody Space Center.. Western Test Range OperationsDi vi!son.

ftnerad Electric Co., Spece Systems OrganIzation,Valley Porga, Pa., is the MM-buo pr~ixte contractor.

M4cDonnell Doug!la Astronautics Company, Huntingtonfteach, CaiV., iaprn aont'ract-or f'or the Delta 1 L

Kore than 5tJ major subsystem contractors arer'eaponslble forz various components In the s~pacecraft,

It launch v'ehice$e or ground receiving equipment. Inaddition, there are more than 1,,000 subcontrac0tors r.ndvendors working on the program.

(Eln OF GENERAL RELEASE: BACKaR0UND INYORMT~ION FOLLOWS)

-riore


13/40

_I I

-12-Nht!BSPlE=ACT~S

Launch Tnftoriition:Vehicle Two stage, DeltaPad Western Test Range, Calif.,SL'C-2 WestAzitmath 194 degrees TrueDate No earlier than December 12, 1972Window Opens shortly beiore 2:4'. to 3:15a.m. EST, December 12 and closesabout 30 minutes later

Orbital Slements:Of1it Circular, 1,110 km (690 statutemi les)Period 107 minutesInclination Nearly polar, sun-synchronous,80 degrees retrograde to theEquator

Spacecraft; Butterfly-shaped, 3 m (10 ft.)tall, 3intl Vt.) wide, with a2 m ft diameter sensory rir-for housing experiments andelectronics weighing 717 kilograms(1,580 pounds)

Spacecraft lifetime: One yearStabilization: Earth-oriented and three axesstabilized to within one degreeExperiments:

Electrically Thermal image of the earth andScanning Microwave oceans unouacured by clouds(E-SMR)

-more-


14/40

- _ _ _

-13-Surface Composition Identification of surfaceMapping Radiometer minerals(SCMR)Infrared Temperature Vertical temperature profile ofProfile Radiometer atmosphere (C02 )(ITPR)Nimbus-E Microwave Vertical temperature profileSpectrometer (NEMS) using 02; water and water vapor

Selective Chopper Vertical temperature profile andRadiometer (SCR) distribution of atmospheric gasesTemperature Humidity Cloud cover and water vaporInfrared (THIR) mapping

Tracking:Orbit 22 stations of NASA's world-wideSpaceflight Tracking and DataNetworkData Acquisition Rosman, North Carolina; Fairbanks,Facilities Alaska; Goldstone, California;Madrid, Spain; and Honeysuckle,Australia

Spacecraft Management: Goddard Space Flight Center,Greenbelt, Md., for NASA's Officeof Applications, Washington, DCLaunch Vehicle Mangement: Goddard Space Flight Center forMASA's Office of Space Science,Washington, DCLaunch Operations: U.S. Air Force 6595th AerospaceTest Wing, Western Test Range,Lompoc, Calif., supervision ofNASA's Kennedy Space CenterUnmanned Launch OperationsPrime Spacecraft General Electric CompanyContractor: Space DivisionValley Forge, PAPrime Launch Vehicle McDonnell Douglas Astronautics Co.Contractor: Huntington Beach, Calif.

-more-


15/40

-]4-STHEIMBUS SPACECRAFt'The structural assembly consists of four major con-figurational elements: the attitude control segment, solararray paddles, a truss structure providing tripod connec-t ion, and a sensory ring or torus structure composed of 18rectangular module bays plus 3 internal bays. The space-craft accommodates up to 222 kilograms (489 pounds) of pay-load with a packaging volume of 1.05 cubic meters (37 cubicfeet) interfacing with the sensory ring. A total earth-viewing area of 1.4 square meters (15 square feet) isavailsole to mount sensors and antennas with a requirementto view the earth. The configurational elements supportedby the spacecraft structure can be summarized as follows:The Attitude Control Subsystem (ACS) is th e upperstructure that provides unobstructed, exposed mounting for

the solar-paddle sun sensors, horizon scanners, and gasnozzles. The electronics mechanical drives and pneumaticsare mounted in a housing for protection against spaceenvironment;The solar array paddles attach to th e shaft projectingfrom the Attitude Control Subsystem housing. In the launchconfiguration, the solar array is folded along itslongitudinal axes to fit within the sensory ring envelopeand is secured to the truss structure by a latch mechanism.The spacecraft is mounted on an adal er structure which isbelted to th e launch vehicle extrude., ring;A truss structure provides a tripod connection betweenthe ACS and sensory ring and allows the alignment requiredbetween the ACS and the senesia. The truss also supportsthe auxiliary load panel; a-d tThe sensory ring .s a doughnut-shaped structure com-posed of 18 rectangular module bays, 33 centimeters (13inches) in depth. The bays house the electronic equipmentand battery modules. The lower surface of the torus pro-vides mounting space for payload and antennas. A box beam

structure, mounted within the center of the torus, providessupport for the larger sensor experiments and tape recorders.

-more-


16/40

-15-NIMBUS-E EXPERIMENTS

Six highly advanced meteorological and earth resourcesexperiments are aboard the Nimbus-E spacecraft. They are:SElectrically Scanning Microwave Radiometer (ESMR)

SInfrared Temperature Profile Radiometer (ITPR)Nimbus-E Microwave Spectrometer (NEMS)

- Surface Composition Mapping Radiometer (SCMR)E Selective Cihoper Radiometer (SCR)i Temperature Humidity Infrared Radiometer (THIR)

Electrically Scanning Microwave Radiometer (ESMR)This experiment will globally map the thermal radia-tion emitted from the earth's surface and atmosphere at awavelength of approx:mrately 1.55 centimeters (19.35GHz).The emissivity of most terrestrial objects in the IR regionis close to unity. However, in the microwave region, theemissivity of these objects varies greatly depending onthe nature of the emitting surface. This property can beused advantageously either by itself or in conjunctionwith an IR scanner. As an example, thin clouds such ascirrus and stratus are relatively transparent in the micro-wave region and in the polar regions, where these cloudspredominate, it will be possible to map surface objectssuch as the ice and water, since their emissivity variesgreatly. It may also be possible to differentiate betweenthe old and more recently formed ice.Clouds with high water content will be easilyidentified with this microwave instrument. Thus, areas ofprecipitation, intense frontal and convective activity,severe storms, and other similar meteorological featurescan be mapped and the data used to annotate the more con-ventional IR or visible cloud cover maps. Over land, theamount of vegetation covering the ground or the watercontent in the soil can be measured.

-more-


17/40

-16-Investigator: Dr. Thomas WilheitGoddard Space Flight CenterProject Engineer: Dean SmithGoddard Space Flight CenterCo-Contractor: Space GeneralDivision of Aerojet GeneralAzusa, CaliforniaGE Experiment Subsystem Engineer: William FranklinObjective: Cloud type differentiation, precipitationintensity of frontal and convectiveaction, severity of storms, morphology ofice cover over water, amounts of vegeta-tion, water content of the soil.Type of Instrument: Microwave Scanning/Imaging RadiometerSpatial Resolution: 16 n. mi.29 km (18 statute miles)Orbital Average Power: 42 wattsWeight: Deployed portion 30 kilograms (67 pounds)Location: Deployed outboard of the sensor ring indirection of flightSize: Electronics and Antenna I M L x 1 M W x 1/2 M H(3 ft. L x 3 ft. w x 1/2 ft. H)

i'Surface Composition Mapping Radiometer (SCM )

The SCMR is designed to determine the nature of theearth surface composition by precise measurement of theresidual radiation (restatrahlen). Extremely high sensi-tivity is achieved by the use of a (HgCd Te) ?ercury-Cadmiun-Teluride detector cooled to 1150K by radiation tospace. It is a high-resolution scanning IR imaging radi-ometer giving resolution size of .66 km (.4 statute miles).It has three spectral channels at 0.8 to d1,, 8.3 to 9.3and 10.2 to 11.2 micrometers in the atmospheric window.


18/40

-17-The 1 micrometer channel is designed to measure re-flected solar radiation from the earth (and clouds). Theband was selected because it is a spectral region wherethe reflectivity of chlorophyl is high, thus increasingthe differentiation between vegetation (normally of lowreflectivity in the visible) and unvegetated areas. Assuch it will enhance the geological mission, as well asprovide data to other earth sciences.Thermal emission of surface objects is a function ofboth the temperature of the object and its emissi'ity,which can be a function of wavelength. In the case ofquartz for example, there is a dramatic decrease inemissivity around 9 micrometers. The effect can be usedto identify thernature of various surface compositions. Ameasurement of the radiance of highly acidic rock formation(one with a large amount of quartz) will differ from anormal rock even though the physical temperature is thesame. The magnitude of the difference in apparent (or

brightness) temperature can be as much as 12 to 150C. ThejCMR on board data handling system provides both stored(tape recorded) and real-time data read-out.Investigators: W. A. Hovis, Jr.Goddard Space Flight Center

W. R. Callahan, Fairfield UniversityR. J. P. Lyon, Stanford University

Project Engineer: H. Shaw, Goddard Space Flight CenterCo-Contractor: ITT, Pt. Wayne, IndianaGE Experiment Subsystem Engineer: Nicholas A. Koepp-BakerObjective: To determine the nature and type of rockand sand surface composition by measuringt;he reststrahlen of quartz within thesurface material.Type of Instrument: IR Scanning/Imaging RadiometerSpatial Resolution: .66 kmi (.41 statute miles)


19/40

Data Handling: Recorded on special recorder andtransmitted via S-band TransmitterOrbital Average Power: 15.7 watts (Duty cycle 10minutes per orbit)Cooling Requirements: 100oKType of Cooler: 2 Stage Space RadiatorWeight: Sensor - 23 kilograms (50 Ibs.)Data System - 9 kilograms (19 Ibs.)Location: Under Sensor RingSize: Radiometer - .6 M L x .3 M W x .5 M H(21" L x 9 Wx 17" H)Special Requirements: Special data handling system

Infrared Temperature Profile Radiometer (ITPR)The ITPR is a seven channel scanning vertical tempera-ture profile measuring instrument. It consists of sixcassegrain telescopes facing a scanning mirror which are

focused onto seven pyroelectric detectors (one telescopehas a dichroic mirror which splits the beam and focusesthe energy from different spectral regions onto two detec-tors). The spectral filters in front of the detectorsselect the required wavelengths. These various spectralchannels are used to determine the temperature of thesurface, the vertical temperature profile, and to measurewater vapor radiance.The purpose of the experiment is to test an infraredradiometer which is designed to meet the engineering andscientific demands of an operational remote temperaturesounder to provide the three dimensional temperaturestructure of the atmosphere fo r operational forecasts bythe mid-1970's.


20/40

: 1.9-The major obstacle to be overcome before satelliteobservations will provide atmospheric temperature andmoisture profiles on a global scale is interpretingobservations when thin overcast and/or broken cloudconditions exist within the field of view of the radiometer.Investigators: W. L. Smith, National Oceanic andAtmospheric Administration

D. W. Wark, National Oceanic andAtmospheric AdministrationProject Engineer: James Fischer, National Oceanicand Atmospheric AdministrationCo-Contractor: Gulton IndustriesAlbuquerque, New Mexico (System)

Beckman InstrumentsFullerton, California (Optics)

GE Experiments Subsystem Engineer: Dario E. GaloppoObjective: To measure radiance in 15 micron CarbonDioxide Band, water vapor band, andwindow region fo r vertical temperatureprofile measurements.Type of Instrument: Multichannel Scanning/ImagingRadiometerSpatial Resolution: 19 n. mi.Peak Power: Electronics - 10 wattsRadiometer - 12 wattsTotal - 2Weight: Electronics Module 7 kilograms 16 lbs.Optical Head 12 kilograms 27 Ibs,Total 19ilogras 3 I1f.Location: Under the sensory ringSize: Optics 20" L x 15" H x 12.2" W

-more-ew4


21/40

-20-Nimbus-E Microwave Spectrometer (NEMS)

The instrument has a total of five microwave radi-ometer channels. It will measure thermal radiation at fivewavelengths near the 5-mma oxygen resonances and the 1.35-cm water vapor resonance. Each frequency is affected to adifferent degree by the terrestrial surface, clouds, pre-cipitation, water vapor, and temperature profile, andtherefore by appropriately interpreting a set of simulta-neous equations most of these meteorological parameterscan be separately estimated.

The three channels near 5-mm wavelength probeprimarily the temperature profile, and two channels near1-cm wavelength over oceans are sensltive to water vaporand liquid water, and over land can indicate surfacetemperature.Infrared sensors readily probe cloud-free regions of

the atmosphere, but large sections of the globe are some-times blanketed by clouds. Microwave sensors have most ofthe advantages of infrared sensors, but are much lesssensitive to clouds. Thus, they have the potential ofproviding temperature profile information, water vaporabundance, and cloud water content on a global scale undermost meteorological conditions.Investigators: Dr. D. Staelin, MITMr. Frank Barath, JPLProject Engineer: Morton FriedmanGoddard Space Flight CenterCo-Contractor: JPL, Pasadena, CaliforniaGE Experiments Subsystem Engineer: William FranklinObjective: To measure the vertical temperature profileusing the oxygen line at 5 nm., and theliquid water and water vapor radiance inthe troposphere.Type of Instrument: Multichannel Microwave RadiometerSpatial Resolution: 185 kilometers (115 statute miles)

-more-


22/40

-21-

Average Power: 33.5 watts- Weight: 32 kilograms (70 pounds) Location: In the Sensor Ring

Selective Chopper Radiometer (SCR)The SCR is a 16 channel vertical temperature profileinstrument. This instrument has four main sets of channels,A, B, C and D. The experiment utilizes interferencefilters and selected chopping, and filters acting asdichroic beam splitters and four channels utilizing carbondioxide absorption cells. Channel A and B comprise con-ventional filter radiometer for measuring temperatureprofiles to approximately 18 kilometers (11 .m,).Channel C contains water vapor and window channelsnecessary to correct the vertical temperature profileinversion computations. It also contains two chanaels at49.5 and 133.3 microns in which the indices of refractionof ice crystals are different, resulting in a measurementof the presence of cirrus clouds.Channel D contains four wavelengths in the 2 to 4micron region; one at the wings of the 2 micron watervapor/CO2 absorption band, two in the 2.6 micron absorptionband, and one at 3.5 micron window. These channels havedifferent functions day and night. During the day the 3.5micron channel measures the reflected radiation from cloudswithout gaseous absorption while the other three channels

measure the absolute radiation temperature of the earthand its cloud cover.Investigators: Dr. S. D. Smith

4- WHeriot Watts UniversityDr. J. T. Houghton| Oxford University

Project Engineer: Jants BebrisCo-Contractor: Rutherford Laboratory, Chilton, Didcot,e Berkshire, England

Marconi Space and Defense Systems,\ Frimley, Camberly, Surrey, England 4

t i


23/40

-22-

GE Experiment Subsystem Engineer: David JonesObjective: Observe global temperature structure ofthe atmosphere at altitudes up to 50 Kmover an extended period in time; makesupporting observations of water vapor

distribution; and determine the densityor ice particles in cirrus clouds.Type or Instrument: Multichannel RadiometerSpatial Resolution: 29 Km (18 statute miles)Orbital Aver-age Power: Electronics - 7.3 wattsRadiometer 87 wattsTotalWeight: i.diometer - 13 kiograms (28 pounds)Electronics - ndilgrms10s

Total - Id o10grarnsLocation: Udder sensory ringSize: .5 M Lx .2 MaW x .3 M H(17" L x 18" Wx 12" H) - Radiometer

.2 M L x .2 M W x .2 M H(6" T-, 8" W x 6 1/2" H) - ElectronicsTmpearetuw Humidity Inlmjed Radiometer (THIR)

The THIR wadch functions as the payload support cloudcover mapper is used both independently and in conjunctionwith other experiments. It provides data on cloud cover,ground tempereture8, and water vapor distribution. Itidentifies cloud fmreo areas as well as providing cloud toptemperatures.


24/40

-23-

The THIR operates in two spectral intervals, one ofwhich is af atmospheric window (10.5 - 12.5 microns) andthe second is an absorption Band (6.5 - 7.0 microns).This latter band is centered near the strong water vaporabsorption band. Since both these channels are in thelong wave IR region, the data obtained is independent ofreflected sunlight and, hence, can be used day or night.. The window channel will give both two and three dimensionalmaps of atmospheric cloud cover. The latter can be createdby measurements of vertical temperature profiles, so thatth e measured cloud radiances can be associated withspecific alt i tudes. Cloud free areas present an oppor-tunity to make thermal maps and measure gradients ofoceans and land areas. The water vapor channel (since itis an absorption band) will receive energy not from theground, but only from a band of altitudes (which can bedescribed by its weighting function). This allowsmeasurements .of water vapor distribution, as well ascirrus cloud modification of the upwelling radiation.

Investigator: A. W. McCullochGoddard Space Flight CenterProject Engineer: Morton Friedman

Goddard Space Flight CenterSubcontractor: Santa Barbara Research CenterE. Trantow, Project ManagerGE Experiment Subsystem Engineer: Dario A. GaloppoObjective: High resolution terrestial cloud and

atmospheric water vapor radiation imagingType of Instrument: IR Scanning/Imaging RadiometerSpatial Resolution: 10 Km (6 statute miles) inwindow channel; 24 Km (15

statute miles)Peak Power: 8.0 watts

-more-


25/40

-24-Weight: Electronics - 3 kilogr~ams ( 6 pounds)Radiometer - 6klgas1poundsTotal - 9 ~ograms pouaaLocation: Below sensory ringSize: Radiometer -. 2 M x .2 4 x .4 M47" x 7"' x 15.6"

3.5

-more-


26/40

I1

-25-THE NIMBUS PROGRAM

Nimbus was originally conceived as a meteorologicalsatellite concerned primarily with providing atmospher!cdata for improved weather forecasting. With the additionof more sophisticated sensirg devices on each succeedingspacecraft, this applications/research observatory programhas grown significantly in capability and performanceuntil it now encompasses a wide range of earth sciences.

Data produced by the sensing instruments on Nimbus 1through Nimbus 4 are now being studied and applied in thefollowing fields:* Oceanography (geography of the oceans and

related phenomena);* Hydrology (S3tudy of water, especially on surface

-f the land, in the soil and underlying rocks, and in th eatmosphere);* Geology (the science that treats the history ofthe earth and its life, especially as recorded in therocks);* Geomorphology (study of the form of the earth,the general configuration of its surface, distribution ofland and water, the evolution of land forms);* Geography (description of land, sea and air, anddistribution of life, including man and his industries);

and,* Cartography (art or business o' drawing ormaking charts or maps).Nimbus-E will add another field to the list, agri-culture, because the Electrical Scanning Microwave Radi-ometer (ESMR) will provide data on moisture and vegetationpatterns over various land surfaces.

-more-


27/40

-26-

Nimbus-1The first satellite in the series was launched intoorbit aboard a Thor/Agena B from th e Western Test Range inth e early morning of August 28, 1964. In spite of a shortAgena second burn, resulting in an eccentric orbit with a932 km (579 s.m.) apogee and 422 km (262 s.m.) perigeeinstead of th e 1,110 km (690 s.m.) circular orbit,Nimbus-1 became fully operational shortly after orbitinsertion.Nimbus-1 worked f r about one month before it stoppedoperating due to a failure of th e solar array drive systemwhich is a major part of th e satellite's power system.During its lifetime, it proved that a weather satellitecould maintain three-axis stability and earth orientation.It provided man with th e first high resolution televisionand infrared weather photos from a satellite.Nimbus-1 carried three experiments -- th e Automatic

Picture Transmission (APT) camera, The Advanced VidiconCamera Subsystem (AVCS) and th e High Resolution InfraredRadiometer (HRIR). The AP T camera system was warmlywelcomed by meteorologists world-wide because for th e firsttime weather pictures could be received at small, inexpen-sive, portable stations as th e satellite passed overhead.The first Nimbus spacecraft took Hurricane Cleo'sportrait during its first day in orbit and subsequentlytracked many other hurricanes and Pacific typhoons. Inaddition, th e pictures enabled cartographers to correctinaccuracies on relief maps and supplied better definit ionof the formation of th e Antarctic ice front.

Nimbus-2Nimbus-2 was launched into a near perfect orbit by aTAT/Agena B on May 15, i966. It carried th e same instru-ments as Nimbus-1, plus a Medium Resolution InfraredRadiometer 'MRIR). The spa-ecraft design liFe was 6months (about 2,500 orbits). The mission was finallyterminated in Orbit 13,029 on January 17, 1969, afteralmost 33 months of operation.

-more-

Pc>* " mm~ mwm ~f~ | | " ft I * a 1 ~ ^~ ~ t ~ T ' iri nM i T nr ~i --^ i -i ~ -* --* * - - -* --. - .. _ .. ._._ -. . ._ _- . . ^ ^SWC-S W


28/40

/

-27-

By th e time Nimbus 2 was launched, th e number of APTstations had grown from 65 to over 300. situated in some43 countries. The system was modified so that HRIR(infrared) nictures could also be received by th e APTstations. Analysis methods and computer programs wereimproved, eliminating the need for cloud-free data.Temperature patterns could be obtained of lakes andocean currents (o f vital interest to shipping and fishingindustries) and thermal pollution could also be identified.The MRIR experiment aboard Nimbus-2 measured electro-magnetic radiation emitted and reflected from the earth infive wavelength intervals from visible to infrared (in-visible to th e human eye). The data permitted detailed

study of th e effect of water vapor, carbon dioxide, andozone on the earthis heat balance.Nimbus-3

Nimbus-3 was successfully launched April 14, 1969.The spacecraft carried seven meteorological experiments,plus a two-unit nuclear isotopic system for generatingelectrical power, the SNAP-19 (Systems for NuclearPlxxiliary Power), developed by th e Atomic Energy Commission.The Nimbus-3 meteorological experiments were:* Infrared Interferometer Spectrometer (IRIS)* Satell i te Infrared Spectrometer (SIRS)* Interrogation Recording and Location System (IRLS)* High Resolution Infrared Radiometer (HRIR)* Medium Resolution Infrared Radiometer (MRIR)* Monitor of Ultraviolet Solar Energy (MUSE)* Image Disector Camera System (IDCS)The vertical temperature measurements of the atmospheremade by Nimbus-3 were acclaimed by weathermen as one of th emo?3 significant events in th e history of meteorology. The

instrument which rwade this possible was th e SIRS (SIRS wasdeveloped by the Environmental Science Service Administra-tion)..-more -


29/40

-28-The SIRS measured, simultaneously, infrared spectralradiances in narrow intervals of the carbon dioxideabsorption band, from which temperature profiles of theearth's atmosphere can be developed.The first temperature profile was constructed from

SIRS data on April 14, 1969, and provided excellentcorrelation with radiosonde measurements (weatherballoons) from Kingston, Jamaica. Subsequent correlatio.lwith data taken over the United States and the PacificOcean was also excellent.Prior to Nimbus-3, data over the oceans had beenscanty, so that only 20 percent of the world had detailedweather information. SIRS data made it possible to obtaintemperature data over the entire earth with an accuracy of2 degrees F above 7,000 meters (20,000 feet) and 4 degreesbelow 7,000 meters (20,000 feet).The quality of the SIRS data is attributed to thedesign features of the instrument and to the very stableenvironment of Nimbus-3.The IRIS experiment aboard Nimbus-3 provided World-wide atmospheric information, including ozone distribution,on a scale not previously possible. Ozone measurementscan be immensely valuable for weather prediction in thevast tropical region and southern hemisphere where con-ventional meteorological network-gathered upper air data issparse. Temperature, humidity, and ozone profiles weredeveloped which correlated excellently with radiosonde andground-based spectrometer data.

Nimbus-4Nimbue-4 was launched April 8, 1970. Six of the nineexperiments are still capable of providing data. Theexperiments are:* Infrared Interferometer Spectrometer.(IRIS)* Satellite Infrared Spectrometer (SIRS) - operable* Interrogation Recording & Location System(IRLS) - operable

-more-


30/40

-29-

1* Monitor of Ultraviolet Solar Energy (MUSE) -operable* Image Dissector Camera System (IDCS) - operable

Sae Backscatter Ultraviolet Spectrometer (BUV) -.operable1* Filter Wedge Spectrometer (FWS)

0 Selective Chopper Radiometer (SCR) - operable* Temperature Humidity Infrared Radiometer (THIR)

' Three new experiments (BUV, FWS and SCR) were carriedby Nimbus-4 as well as three significantly improved; versions of sensors (IRIS, SIRS and IRLS) which had flownon earlier Nimbus missions. In addition, there are three* experiments (THIR, IDCS and MUSE) similar to those aboardNimbus-3.

-morei

-moree-


31/40

-30-

THE DELTA LAUNCH VEHICLEThe general characteristics of the Delta for theNimbus-E mission are:Total Height: 33 m (105 ft.)Total Weight: About 113,400 kg (250,000 Ibs.)Maximum Body Diameter: 2.44 m (8 ft.)(Not including solids)The Delta first stage is a modified Thor boosterincorporating nine strap-on solid fuel rocket motors. Thebooster is powered by an engine using liquid oxygen andRJ-1 Kerosene. The main engine is gimbal mounted to pro-vide pitch and yaw control from lift-off to main enginecut-off (MECO). Two liquid propellant vernier enginesprovide roll control throughout the first stage operation,and pitch and yaw control from MECO to first stage separa-tion.The second stage is powered by a liquid-fuel pressure-fed engine which is also gimbal mounted to provide pitchand yaw control through second stage burn out. The secondstage propellants are Nitrogen Tetroxide (N,0 ) for theoxidizer and Aerozine 50 for the fuel. A nitrogen gassystem ucing eight fixed nozzles provides roll controlduring powered and coast flight as well as pitch and yawcontrol after second stage cutoff.The all inertial guidance system, consisting of anInertial Measurement Unit (adapted from the Apollo LunarModule) and digital guidance computer (adapted from theCentaur launch vehicle program), control the *%icle andsequence of operations from lift-off to spacecraft separa-tion. The sensor package provides vehicle attitude andacceleration information to the guidance computer. Theguidance computer generates vehicle steering commands toeach stage to correct trajectory deviations by comparingcomputed position and velocity against prestored values.This system will permit more accurate orbits and will bemore flexible than the radio command guidance system usedby the earlier Delta rocket.

-more- 5fr ;"~


32/40

S-31-The Delta program is managed for NASA's Office offSpace Science by the Goddard Space Flight Center. LaunchSservices are provided by the U.S. Air Force 6595th Aero-Sspace Test Wing under supervision of NASA's Kennedy SpaceCenter, Unmanned Launch Operations. The Delta prime con-tractor is McDonnell Douglas Astronautics Company,

SHuntington Beach, California.The Flight

The Thor main engine and six of the solid motors areignited at lift-off, and the remaining three solids areignited later at altitude. Between T plus 100 and 105seconds the vehicle is yawed approximately ie degree to4 achieve the desired inclination of the transfer orbit.The Nimbus-E flight plans calls for the second stageto undergo two burns. The first burn will place the

vehicle into an elliptical transfer orbit with a perigee(closest point to Earth) of 185 km (115 statute miles, andan apogee (farthest point from Earth) of about 1,110 km(690 statute miles).The orbiting second stage will be restarted (about 57minutes after lift-off) over the Indian Ocean nearTananarive to circularize the Nimbus-E orbit. This secondburn will last fo r 12 seconds and place the spacecraftinto a final circular orbit at an altitude of 1,110 km (690statute miles).About 3 1/2 minutes after the second stage shuts downfo r the second time, the Nimbus-E separation sequence willbegin. Gas jets aboard Delta will turn it, and Nimbus, toan attitude of 80 degrees of the local verticle of theEarth. A spring system will then separate Nimbus-E fromthe Delta. The Nimbus-E attitude and control subsystemwill then be activated so the spacecraft becomes Earthoriented and stabilized in all three axes.At about 15 minutes after spacecraft separation (andagain 15 minutes later at T plus 77 minutes and T plus 93minutes respectively) the Delta second stage will beignited for the third and fourth times in a special testrelated to the restart capability of the new second stage.The fourth and final burn will place the Delta second stageinto a perigee of 1,085 km (674 statute miles) and anapogee of 1,360 km (845 statute miles).

4 -n1Ois-


33/40

MAJOR DELTA 93/NIMBUS-E FLIGHT EVENTSTime Altitude Velocity (Kilometers Per Hour)

Solid Motors Burn-(six solids) T plus 39 sec. 6 km (4 s.m.) 1530 km/HR (951 mph)Solid Motors T plus 39 sec. 6 km (4 s.m.) 1530 km/HK (951 mph)Solid Motor(three solids) T plus I min. 18 sec. 21 km (13 s.m.) 3285 km/HR (2041 mph)Motor Separationnine solids) T plus 1 min. 25 sec. 27 km (16 s.m.) 3495 km/HR (2172 mph)

Engine Cut Off- T plus 3 min. 40 sec. 99 km (61 s.m.) 17,515 km/HR (10,883 mph)Engine Cut Off- T plus 3 min. 46 sec. 104 km (65 s.m.) 17,525 km/HR (10,890 mph)

1, Stage II T plus 3 min. 48 sec. 106 km (66 s.m.) 17,515 km/HR (10,883 mph)II Ignition T plus 3 min. 52 sec. 109 km (68 s.m.) 17,490 km/HR (10,868 mph)

Fairing T plus 4 min. 25 sec. 130 km (81 s.m.) 18,C30 km/HR (11,241 mph)Second Engine Cu t Off

T plus 9 min. 4 sec. 185 km (115 s.m.) 29,305 km/HR (18,208 mph)Second Stage T plus 57 min. 5 ses. 1110 km (690 s.m.) 25,810 km/HR (16,037 mph)

SECO T plus 57 min. 17 sec. 1110 km (690 s.m.) 26,680 km/HR (16,579 mph)Separation T plus 60 min. 38 sec. 1110 km (690 s.m.) 26,680 km/HR (16,579 mph)


34/40

-33-KSC -1-TR

NASA launch operations from th e Western Test Rangeare conducted by Kennedy Space Center Unmanned LaunchOperations Directorate. Most of th e KSC contingent are onpermanent assignment at Vandenberg AFB, although a smallsupplemental group from KSC in Florida assists during thefinal preparations and launch countdown.

The Nimbus space vehicle has been undergoing checkoutand launch preparations since the first stage of th e Deltabooster arrived in mid-October. The booster was erectedat launch complex SLC-2W on th e 19th of October and thenine auxiliary solid motors were attached to th e boosteron th e 25th and 26th of October.The Delta second stage was hoisted atop the firststage on October 30. Tests were conducted of the launchvehicle electrical, mechanical, propulsion, and guidance

systems before th e spacecraft was mated to th e launchvehicle. After spacecraft mate, a simulated flight wasconducted, the last overall test of the vehicle.

'i

-more-


35/40

-34-NIr4BUS-E PROJECT OFFICIALS

NASA Headquarters, Washington,-lCMr. Leonard Jaffe Deputy Associate Administrator

Office of Applications(Acting) Director, EirthObservations ProgramMr. Bruton B. Schardt Nimbus Program ManagerMr. Joseph B. Mahon Director, Launch Vehicles andPropulsion ProgramMr. I. T. Gillam, IV Delta Program Manager

Goddard pace Flight Center, Greenbelt, MDDr. John F. Clark DirectorMr. Robert N. Lindley Director of ProjectsMr. Harry Press Associate Director for EarthObservation SatellitesMr. Stanley Weiland Project ManagerDr. William Nordberg Project ScientistMr. William R. Schindler Delta Project Manager

Mr. George D. Hogan Observatory ManagerMr, Wilber B. Huston Mission DirectorMr. Ralph B. Shapiro Operations ManagerMr. John W. ]*ind-strom,. Jr. Marzger, Nimbu.s Data UtilizationCenterMr. Richard Ormsby Manager, Nimbus TechnicalControl Center


36/40

-35-Mr. E. Michael Chewriing Network Support ManagerMr. William F. Mack Mission Support Manager

Kennedy Space Center, FLMr. John J. Reilon Director,. Unmanned LaunchOperations

fMr. Wilmer Thacker (a--ar, Delta Operations

Mr. Eugene Langenteld Spacecraft CoordinatorGeneral Electric Companxy, Valley Forge, PAMr. I. S. Hass General Manager,. Earth

Observatoryr "rramsMr. L. T Seaman Manager, Observatory Systems8

tMr.oseph Bele~b Deputy Manager., Nimbus Program* McDonnell-DouglasAstronautics CoMany, Hu~ntinlgton Beaoh,. CA

Mr. E. W. Bonnett Delta Projoit Manager


37/40

-36-NIMBUS -E EXPERK MEERS

Dr. Thomas T. Wilheit Electrically Scanning MicrowaveGoddard Space Flight Center Radiometer (ESMR)Dr. Warren A. Hovis, Jr. Surface Composition MappingGoddard Space Flight Center Radiometer (SCMR)W. R. CallahanFairfield UniversityR. J. P. LyonStanford UniversityW. L. Smith &1 . W. Wark Infrared Temperature ProfileNational Oceanic and Radiometer (ITPR)Atmospheric AdministrationDr. David H. Staelin, MIT Nimnbus-9 KIcrowave SpectrometerFrank Barath, JPLS. D. Smith Selective Chopper Radiometerferiot Watts University (SCR)J. T. Houghtonoxford UniversityAndrew W. McCulloch Temperature Humidity InfraredGoddard Space Flight Center Radiometer (THIR)

-more-


38/40

-37-SPACECRAFT CONTRACTORS

Company SubsystemGeneral Electric Co. Prime Contractor

t Space Systems Organization Nimbus D Integration and Test,, Valley Po.?gc, PA Stabilization and ControlSubsystem Integration, Space-Scraft Structure and AntennasCalifornia Computer Products Command ClockSLos Angeles, CARadiation, Inc. Versatile InformationMelbourne, FL Processor, (VIP), or house-Skeeping telemetryRadio Corporation of America High Data Rate Storage System,Astro Electronics Division Command Receivers, Solar PowerPrinceton, NJ SystemSperry Gyroscope Rate Measuring PackageGreat Neck, NY

Major GroundcEuipment ContractorsCompany ResponsibilityTerratek, Inc., Operate the Nimbus DataA subsidary of Allied Utilization CenterResearch Associates, IncSSeabrook, MDContro? Data Corp. Ground Station ComputersMinneapolis, MNLeer Siegler, Inc. Computer System for Decompu-Anaheim, CA tating Versatile InformationProcessor (VIP) Telemetry DptaRCA Service Co . Operate the Nimbus DataCherry Hill, NJ Handling System at the GoddardSpace Flight Center and AlaskaIthaco, Inc. Attitude Control ComponentsIthaca, NY and Subsystems

-more-


39/40

a

-38-PRIME EXPERIMENT CONTRACTORS

Space Ge,,eral, Division of Electrically Scanniru3 Micro-Aerojet Gener. J wave Radiometer (ESY1%)Azusa, CAITT Surface Composition NappingFt. Wayne, IN Radiometer (SCMR)Gulton Indusbries (Under Infrared Temperature Prc'fileNOAA Contract) Radiometer (ITPR) -- (Svstem)Albuquer--qe, NMBeckman Instruments (ITPR) -- (Optics)Fullerton, CAJPL Nimbus-E M4icrowavePasadena, CA Spectrometer (NEMS)M A-u'erford Lab, Chilton, Selective Chopper RadiometerDideot, Berkshire, England (SCR)Marconi Space and DefenseSystems, Frimley, Camberly,Surrey, EnglandSanta Barbara Research Temperature Hlumidity InfraredCenter Radiometer (THIR)Santa Barbara, CA

MAJCMI DELTA LAUNCH VEHICLE CONTRACTORSCompar ResponsibilityMcDonnell Do'glas Prime ContractorAstronautd's Co.Huntington Beach, CG.Aer,-jet Gener.ql Corp. Second Stage propulsionSacramento, CA systemliami lt-n Standard Inertial Measuring UnitDt',i-on o.L' United Aircraft Portion of the inertialCorp. . 4Idance systemFarmington, CT

-moze-


40/40

-39-Company Responsibi lityRocketdyne, North American First stage main engine andRockwell Corporation vernier enginesCanoga Park, CATeledyne Industries. Inc. Computer fcr inertia, guidanceNorthridge, CA systornThiokol Chemical Corporati.on Solid MotorsElkton, VID

nimbus-e press kit

Documents