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kw.\*:("MOTEUR FUSEE")

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THRUSTER CHARACTERIZATION USING A THRUST BALANCE = CARACTERISATION D'UN PROPULSEUR UTILISANT L'EQUILIBRAGE DE LA POUSSEEBAILEY AG.1972; REV. SCI. INSTRUM.; U.S.A.; DA. 1972; VOL. 43; NO 12; PP. 1773-1774; BIBL. 1 REF.Serial Issue

PERFORMANCE OF A MODIFIED DOWNSTREAM-CATHODE MPD THRUSTERBURKHART JA.1973; J. SPACECR. ROCK.; U.S.A.; DA. 1973; VOL. 10; NO 1; PP. 86-88; BIBL. 3 REF.Serial Issue

A PROPULSION SYSTEM FOR ORBIT-TO-ORBIT SHUTTLEWELLS WW; LAMONT EA.1971; S.A.E. TRANS.; U.S.A.; DA. 1971; VOL. 80; NO PART 4; PP. 2586-2597Serial Issue

FORTSCHRITTLICHE HYDRAZIN-LAGE- UND BAHNKORREKTUR. ANTRIEBSSYSTEME UND IHRE ANWENDUNG IN EUROPA = PROGRES DE L'HYDRAZINE, CORRECTION D'ORBITE ET DE POSITION. LES SYSTEMES DE PROPULSION ET LEUR UTILISATION EN EUROPESCHMITZ HD; WOIDNECK H.sdIN: 5. JAHRESTAG. DTSCH. GES. LUFT RAUMFAHRT; BERLIN; 1972; S.L.; DA. S.D.; PP. 1-26Conference Paper

FULL CONTROL OF SOLID PROPELLANT ROCKETS BY SECONDARY INJECTION = CONTROLE COMPLET DE FUSEES A PROPERGOLS SOLIDES PAR INJECTION SECONDAIREZEIERMAN I; MANHEIMER TIMNAT Y.1973; J. SPACECR. ROCK.; U.S.A.; DA. 1973; VOL. 10; NO 3; PP. 161-162; BIBL. BIBL. (2 REF.Serial Issue

BUOYANCY EFFECT ON FUEL CONTAINMENT IN A GAS-CORE NUCLEAR ROCKET = EFFET DE FLOTTABILITE SUR L'EMMAGASINAGE DU COMBUSTIBLE DANS UNE FUSEE NUCLEAIRE A COEUR GAZEUXPUTRE HA.1972; J. SPACECR. ROCK.; U.S.A.; DA. 1972; VOL. 9; NO 12; PP. 932-934; BIBL. 4 REF.Serial Issue

SCHWIERIGKEITEN BEIM BAROMETRISCHEN AUSSCHLEUSEN VON FLUESSIGKEITEN AUS DEM VAKUUM MITTELS FALLROHREN = DIFFICULTES RENCONTREES AU COURS DE L'EVACUATION BAROMETRIQUE DE LIQUIDES D'UNE ENCEINTE SOUS VIDE A L'AIDE DE TUBES DE GRAVITELAMBRECHT H.1973; DTSCHE LUFT-U. RAUMFAHRT, MITT.; DTSCH.; DA. 1973; NO 10; PP. 1-27; BIBL. 3 REF.Serial Issue

DISHED ACCELERATION GRIDS ON A 30-CM ION THRUSTERRAWLIN VK; BANKS BA; BYERS DC et al.1973; J. SPACECR. ROCK.; U.S.A.; DA. 1973; VOL. 10; NO 1; PP. 29-35; BIBL. 16 REF.Serial Issue

ION THRUSTER THERMAL CHARACTERISTICS AND PERFORMANCEWEN L; CROTTY JD; PAWLIK EV et al.1973; J. SPACECR. ROCK.; U.S.A.; DA. 1973; VOL. 10; NO 1; PP. 35-41; BIBL. 12 REF.Serial Issue

MANOEUVRE OPTIMALE D'ATTERRISSAGE SUR UNE PLANETE PAR UN MOTEUR A POUSSEE LIMITEE AVEC ANGLE D'ENTREE DONNE DANS L'ATMOSPHERE PLANETAIREKLIMKO AS.1973; VEST. LENINGRAD. UNIV.; S.S.S.R.; DA. 1973; NO 1; PP. 94-105; ABS. ANGL.; BIBL. 5 REF.Serial Issue

EINE GRAPHISCHE BESTIMMUNG DER ENTHALPIE IM HALSQUERSCHNITT EINES RAKETENTRIEBWERKES UND DEREN BEDEUTUNG FUER DIE LEISTUNGSBERECHNUNG = DETERMINATION GRAPHIQUE DE L'ENTHALPIE DANS LE COL DE LA TUYERE D'UN MOTEUR FUSEE ET SON IMPORTANCE POUR LE CALCUL DE LA PUISSANCEBUCHNER E.1973; ASTRONAUTIK; DTSCH.; DA. 1973; VOL. 10; NO 1; PP. 141-142; ABS. ANGL.; BIBL. 4 REF.Serial Issue

STAR TRACKING THROUGH THE EXHAUST BEAM OF MERCURY BOMBARDMENT THRUSTERS = POURSUITE D'ETOILES AU TRAVERS DU FAISCEAU DE SORTIE DE PROPULSEURS A BOMBARDEMENT DE MERCUREMILDER NL; SOVEY JS.1973; J. SPACECR. ROCK.; U.S.A.; DA. 1973; VOL. 10; NO 1; PP. 47-51; BIBL. 18 REF.Serial Issue

ADVANCED PINTLE-CONTROLLED MOTOR WITH THRUST VECTOR CONTROLSAYLES DC; LEVINSKY CT.1971; S.A.E. TRANS.; U.S.A.; DA. 1971; VOL. 80; NO PART 4; PP. 2557-2564Serial Issue

DYNAMIC RESPONSES OF SOLID ROCKETS DURING RAPID PRESSURE CHANGE = REPONSES DYNAMIQUES DE FUSEES A PROPERGOLS SOLIDES DURANT DES VARIATIONS RAPIDES DE PRESSIONTURK SL; BATTISTA RA; KUO KK et al.1973; J. SPACECR. ROCK.; U.S.A.; DA. 1973; VOL. 10; NO 2; PP. 137-142; BIBL. 14 REF.Serial Issue

THE ELECTRICAL PROPULSION OF SPACE VEHICULESBRIGHT AW; MAKIN B.1973; CONTEMPOR. PHYS.; G.B.; DA. 1973; VOL. 14; NO 1; PP. 25-38; BIBL. 4 REF.Serial Issue

THE SIMULATION OF HIGH PRESSURE HYDROGEN/OXYGEN ROCKET ENGINES = LA SIMULATION DES MOTEURS DE FUSEE A HYDROGENE/OXYGENE A HAUTE PRESSIONHOPKINS H; KONOPKA W; LENG J et al.sdIN: AIAA 7TH AERODYN. TEST. CONF. PALO ALTO, CALIF., 1972; NEW YORK; AM. INST. AERONAUT. ASTRONAUT.; DA. S.D.; NO 993; PP. 1-10; BIBL. 13 REF.Conference Paper

DEVELOPMENT OF THE ALGOL III SOLID ROCKET MOTOR FOR SCOUTFELIX BR; MCBRIDE NM.1971; S.A.E. TRANS.; U.S.A.; DA. 1971; VOL. 80; NO PART 4; PP. 2565-2575; BIBL. 5 REF.Serial Issue

VISCOUS EFFECTS ON BIOWASTE RESISTOJET NOZZLE PERFORMANCEKALLIS JM; GOODMAN M; HALBACH CR et al.1972; J. SPACECR. ROCK.; U.S.A.; DA. 1972; VOL. 9; NO 11; PP. 869-875; BIBL. 7 REF.Serial Issue

FRENCH RESEARCH ON CESIUM CONTACT ION SOURCESLE GRIVES E; LABBE J.1973; J. SPACECR. ROCK.; U.S.A.; DA. 1973; VOL. 10; NO 2; PP. 113-118; BIBL. 8 REF.Serial Issue

A FACILITY FOR LONG-TERM ION THRUSTER SYSTEM TESTINGMCKINNEY HF; SUTTON RA.1973; J. SPACECR. ROCK.; U.S.A.; DA. 1973; VOL. 10; NO 1; PP. 42-46; BIBL. 5 REF.Serial Issue

CONVECTIVE HEATING ON DELTA-WING SPACE-SHUTTLE BOOSTERS INCLUDING INTERFERENCE EFFECTSDOUGHTY RO; ERICKSON RC; BROCK OR et al.1972; J. SPACECR. ROCK.; U.S.A.; DA. 1972; VOL. 9; NO 12; PP. 876-882; BIBL. 16 REF.Serial Issue

COMPONENT DEVELOPMENT FOR A 10-CM MERCURY ION THRUSTERPYE JW.1973; J. SPACECR. ROCK.; U.S.A.; DA. 1973; VOL. 10; NO 2; PP. 106-112; BIBL. 19 REF.Serial Issue

ENTWICKLUNG VON BETANKUNGSANLAGEN UND CHECKOUT-SYSTEMEN FUER DIE SATELLITENPROJEKTE TD-1A UND AEROS = MISE AU POINT DES INSTALLATIONS DE REMPLISSAGE ET DES SYSTEMES DE CONTROLE POUR LES PROJETS DE SATELLITE TD-1A ET AEROSSCHNEIDER E.1973; RAUMFAHRTFORSCHUNG; DTSCH.; DA. 1973; VOL. 17; NO 1; PP. 23-28; ABS. ANGLSerial Issue

DIRECT THRUST MEASUREMENTS AND BEAM DIAGNOSTICS ON AN 18-CM KAUFMAN ION THRUSTERJUNGE HJ; SPRENGEL UW.1973; J. SPACECR. ROCK.; U.S.A.; DA. 1973; VOL. 10; NO 2; PP. 101-105; BIBL. 6 REF.Serial Issue

LE LANCEUR DIAMANT B-P4ROUSSEL JG.1973; AERONAUT. ET ASTRONAUT.; FR.; DA. 1973; NO 39; PP. 5-20; ABS. ANGL. ALLEMSerial Issue

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