ETTC'2003 - SEE

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hardware down and led to widely accepted and supported mediums for data transmission such as Ethernet. Moreover things change quickly in this world. Network bandwidth increases according to Moore’s law. Copper gives way to fibre, and 10Mbit LANs give way to 1Gbit SANs. Today Fibre-channel, FDDI and ATM are all transmission mediums that are finding favour in the commercial world. This leaves those of us in the flight test world hungrily eying develops in the commercial world and wondering how we can leverage their cost benefits into our programs. In this paper a COTS solution is presented that marries the two worlds. It tries to: - Let the FTI equipment do what it does well – sample synchronously - Let the commercial word do what it does well – move large amounts of data around - Perform the exchange in a rigorous and well-defined way - Maintain flexibility so that new developments in the commercial world can be quickly adapted. When FTI meets Commercial Figure 1: A typical Flight Test Instrumentation Configuration Communications jargon speaks of Bridges, Routers and Gateways. Although the definitions can be a little fuzzy, it is possible to think of them as follows:
• A bridge is a connection between two physically separate networks that forwards packets from one to another. It does no protocol changing, and has limited ability to handle errors or communication failures. • A router is a more intelligent bridge that can handle communication failures and make decisions about the best path to use to deliver a package. • A gateway is a translator between networks that may use different protocols. It can strip out the payload of a packet and re-package it in a different protocol. So in order to transfer data from, say, a CAIS network to a fibre-channel network it looks like what we need is a gateway. But in the commercial world gateways are typically intelligent devices, often implemented by a PC with several networking cards. So you might have a PC with a CAIS bus-controller PCI card, and a fibrechannel SCSI card. The PC provides the intelligence through software to strip out the CAIS payload and re-package it for storage via fibre-channel. This is a perfectly good solution in a benign environment, but what about on-board a fighter during flight test? How long does a PC and the associated software take to recover from a brown-out? So we are looking for the functionality of a gateway, but implemented in a way that is closer to a flight data acquisition unit (DAU) – with small size and rugged performance. Consider the task of moving two parameters from a CAIS bus DAU to an Ethernet packet. If we view it in terms of the classic ISO 7-layer model then we have to strip away the lower four layers up to the Transport layer, and then re-package the data (Figure 2). X Y RES CMD Application Presentation Session Transport Network Data Link Physical RAM X Y Application Presentation Session Transport Network Data Link Physical Figure 2: Moving data from CAIS to Ethernet UDP/IP Packet Preamble X Y Post-ample A principal difficulty in all this is that it takes time, and commercial protocols (such as Internet Protocol – IP) do not worry too much about determinism in the transport
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SÉANCE D'OUVERTURE / OPENING SESSI
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A l’aube de ce siècle, Airbus s
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Etape 4 : L’avion réel une fois
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C’est, sur l’exemple des essais
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parfois même sous la forme de plat
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oth the system and the manufacturin
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Such an interdependence between tes
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eference books, but it is as fundam
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BACK MANAGEMENT DES ESSAIS SYSTEME
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BACK ESSAIS D’ENSEMBLE LANCEURS C
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Elle ne doit cependant pas être me
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- le plan de mesures est conséquen
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4.2 MAQUETTE DYNAMIQUE ARIANE 5 Dan
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Les points délicats liés à l’o
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Processus Commande Architecture Int
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BACK 1 Introduction AIRBUS AIRCRAFT
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So, different test tools shall be d
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3.4 Architecture of A380 Simulators
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3.6 A380: Models In order to suppor
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GENERAL PRESENTATION OF JUZZLE GENE
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Figure 3 : Graphic User Interface o
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IMPLEMENTATION AND SIMULATION OF A
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REFERENCES [1] Space engineering, R
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Client Compliance Matrix (par rappo
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SESSION 2 : TECHNIQUES ET MOYENS D'
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POSTE INE A380 Les besoins fonction
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Les principes de l’architecture :
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Les éléments de l’architecture
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BACK Trajectographie temps réel DG
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Deux précisions temps réel sont p
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4.00 3.00 2.00 1.00 0.00 -1.00 -2.0
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CONCLUSION La phase d'essais en vol
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RÉSUMÉ: Osiris est une gamme de m
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1. INTRODUCTION Dassault Aviation e
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Exemple de modules banc d'intégrat
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éduction de durée des essais par
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5. EXEMPLE L'OSIRIS MULTIFONCTION U
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6. LA MODULARITÉ DE LA GAMME OSIRI
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• JBUILDER • ORACLE Cette modul
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• VX Wxorks reste l'OS de la part
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6.5 Exemple d'interconnexion avec d
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PRINCIPE 7.3 Exemple de réalisatio
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8. LA NOUVELLE GAMME SUR PC: VÉNUS
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• Un IHM de sélection des param
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9. CONCLUSION OSIRIS a maintenant g
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TABLE DES MATIERES 1. LE DATA-LINK
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AVIONS appartenant au réseau 25_P_
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• Les données à émettre sur le
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• 25_P_2/04 PCM émis par l'avion
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3.2 Le temps différé • En temps
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4. CONCLUSION • Toutes les IHM in
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INTRODUCTION Pour définir des proc
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- Ecarts de position en temps réel
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ANNEXE 1 CONSTITUTION CONSTITUTION
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They however incorporate some eleme
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As technology evolves, the boundary
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shown below together with the AGE c
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BACK ESSAIS SYSTEME SUR LES PROJETS
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3 qui contient le logiciel de vol.
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5 • essais en station « in vivo
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Avis, options et recommandations (5
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BACK Automatic Validation of Flight
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− The second level provides all d
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The operational flexibility of SINU
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• Test duration is reduced : for
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mimics from CCS ones. The objective
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1. Introduction ...................
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2. Présentation Le segment sol Ste
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AUS Station STA TM/TC Station STS T
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• La Commission de Revue d’Essa
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Certains essais particuliers liés
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Page 146 and 147: TTC’2003 Stentor 10/06/2003 QUALI
Page 148 and 149: TTC’2003 Le Programme Stentor 10/
Page 150 and 151: TTC’2003 Satellite GEO TM/TC/Rang
Page 152 and 153: TTC’2003 •Equipes CNES : Qualif
Page 154 and 155: TTC’2003 •L’organisation mise
Page 156 and 157: TTC’2003 Interfaces Externes :
Page 158 and 159: TTC’2003 Les Contraintes de Déve
Page 160 and 161: TTC’2003 Contient ontient la la m
Page 162 and 163: TTC’2003 10/06/2003 Qualification
Page 164 and 165: TTC’2003 10/06/2003 Qualification
Page 166 and 167: BACK Résumé : Outil de traitement
Page 168 and 169: 1 Principes généraux de l’outil
Page 170 and 171: 1.2.3 Valise de piste L’outil peu
Page 172 and 173: 2 Capacités fonctionnelles 2.1 Arc
Page 174 and 175: Vue f(t) 2.3.1 Vues y=f(t) Ces vues
Page 176 and 177: Maquette aéronef Alarmes Bar-graph
Page 178 and 179: 2.3.3 Représentation trajectograph
Page 180 and 181: 2.3.5 Vidéo Par ailleurs, si le ma
Page 182 and 183: 3 Concept de structure d’accueil
Page 184 and 185: 4 Exemples d’utilisation 4.1.1 HB
Page 186 and 187: SESSION 3 : Capteurs et dispositifs
Page 188 and 189: BACK THE NEXT GENERATION AIRBORNE D
Page 190 and 191: 3. DC SPECIFICATIONS - SEEING THE W
Page 192 and 193: For the purposes of this paper it i
Page 196 and 197: mechanism. In a system where a late
Page 198 and 199: 0 X Y X' Y' 0 X Y Sampling Cycle X
Page 200 and 201: - Perform the exchange in a rigorou
Page 202 and 203: GLOSSARY AFDX Avionics Full DupleX
Page 204 and 205: The complete message is recorded by
Page 206 and 207: The L3 switches allow forwarding da
Page 208 and 209: Furthermore, the configuration of t
Page 210 and 211: BACK LOGICIEL JAVA D’ACQUISITION
Page 212 and 213: ISA ISA Interface utilisateur Objet
Page 214 and 215: CONCLUSION La première version de
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Page 218 and 219: ( +, & + < 0 9& - & = (( + 1 - + +,
Page 220 and 221: BACK Telemetry Recording Workstatio
Page 222 and 223: Figure 1: Real-time pen tip display
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Page 228 and 229: SESSION 5 : TELEMESURE (SPECTRE - M
Page 230 and 231: Currently various avenues are explo
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Page 234 and 235: The index multiplier block will be
Page 236 and 237: The current implementation consists
Page 238 and 239: Spécificité de la télémesure AI
Page 240 and 241: Technique COFDM : La modulation COF
Page 242 and 243: La réception s’effectue par une
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BACK ETCC'2003 European Test and Te
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ETCC'2003 European Test and Telemet
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SESSION 6 : SYSTEMES DE TELEMESURE
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f f p IF = R b = 4R b ∆f = 0. 7R
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2.3 ADC Fig.5 (a) y (t) and its spe
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2.5 FM demodulation Fig.9 I ‘(nT1
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References 1. Gardner FM. A BPSK/QP
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L/S/C /X/Ku /Ka band Spacelink Syst
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Spacelink System - The solution for
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SPOT Σ ∆ X band feed Data LNA Tr
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défilant. Le cahier des charges d
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TOURELLE HEXAPODE La tourelle hexap
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Ci après, tableau des spécificati
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BACK CRISTAUX PHOTONIQUES ET METAMA
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BACK Systems, Design & Tests Direct
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1. INTRODUCTION Cette communication
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Figure 2-1 Vue générale de la Bas
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3. ETALONNAGE DE LA BASE 3.1 PRINCI
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Par définition, le taux de polaris
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This document is the property of EA
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amplitude (dB) 10 0 -10 -20 -30 -40
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amplitude (dB) 10 0 -10 -20 -30 -40
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V1=K1.GVV.E.{[cos()-.sin()] + 1_vra
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Quelques calculs d’incertitude so
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- 21 - Amplitude polarisation verti
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- 23 - Amplitude composante vertica
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- 25 - Amplitude composante vertica
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3.4 SYNTHESE DES RESULTATS CONCERNA
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4.2 DEFINITION DE L'ANTENNE DE MISE
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4.4 DEFINITION DE L'ANTENNE DE REFE
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5.1.2 Diagrammes de rayonnement 5.1
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5.2 ANTENNE DE REFERENCE BANDE P 5.
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Gain (dBi) 5.2.2.2 Résultats Ils s
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Comme attendu, la coupe xOz présen
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Gain (dBi) 5.3.2 diagramme de rayon
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Gain (dBi) 15 10 5 0 -5 -10 -15 -20
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BACK INTRODUCTION MESURE DE CHAMP P
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MESURE DE CHAMP PAR SYSTEME PORTABL
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MESURE DE CHAMP PAR SYSTEME PORTABL
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Abstract Helicopters are relatively
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Au sol, la station réceptionne le
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BACK Résumé Architecture d’une
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Architecture type lanceur lourd ARI
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Architecture petit lanceur L’arch
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Diagramme de l’UCTM Voies analogi
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Exemples de capteurs utilisés Type
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SESSION 8 : COMPATIBILITE ELECTROMA
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1. CONTEXTE GENERAL Le durcissement
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Figure 1 : Actions de qualification
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5. LES PARAMETRES D’OPTIMISATION
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7. PERFORMANCE ET OPTIMISATION DU P
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La qualification du durcissement re
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UNIT Unit EMC documents : - groundi
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At equipment level EMC TEST PROGRAM
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BACK ETTC 2003. Le rôle de la simu
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comprenant des objets complexes, n
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Cette approche permet, avec les mê
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Les Thèses ONERA UPS Prise en comp
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Pression Ligne bifilaire non blind
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1.8 1,8 Tension continue V 1.6 1.4
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270 Ω I0 IL 2,7 kΩ (b) Alimenta
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What is the budget of the statistic
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Monte Carlo approach: This is a thr
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2 Etat de l’art des standards de
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2.1.6 Emissions standards 61967 par
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- Limites pour l’immunité DPI (e
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PRESENTATIONS POSTER / POSTER PRESE
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BACK LA TELEMESURE SUR AIRBUS JC GH
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Dans le cycle d ’essais en vol ,
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CONCLUSION - NOS BESOINS FUTURS AIR
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LOGICIELS DE MESURE ET DE TRAITEMEN
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In order to optimize the phase nois
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Photo-oscillator active device Opti
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the inverse of N×N correlation mat
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quasi-synchronous multiuser detecto
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Multiuser Interference Canceler ”
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the inverse of N×N correlation mat
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quasi-synchronous multiuser detecto
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Multiuser Interference Canceler ”
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All these sub-systems can be easily
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3.5 ACPR RACK Gateway and satellite
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4.2 COMPONENT DEGRADATION MEASUREME
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Indeed, when the objective of the t
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All the five points can be achieved
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M r Mmax (0 dB, -180°) b = 0 a ωc
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2 - Test devices at ENSICA Souffler
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Soufflerie à Densité Variable (SD
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Capacité : - pour la charge axiale
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Machine d’essai de fatigue en fle
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torsion. - asservissement de chaque
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KEY 1 WORD IENA PACKET format An IE
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TD: “0” means that the paramete
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PARAMETER DESCRIPTION This array de
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BACK UTILISATION de CAMERAS NUMERIQ
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TABLE DES MATIÈRES 1. INTRODUCTION
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2. CONTEXTE DES ESSAIS Le but des e
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3. LES BESOINS ET LES CONTRAINTES 3
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4. CHOIX DE LA CAMERA 4.1 Démarche
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5.1.4 Adaptations Les deux principa
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Tir d'un missile AIR/AIR éjecté T
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6. CONCLUSION Cette évaluation mon
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Capteur Intelligent IEEE 1451.4 Pri
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pC/g Piezo Accelerometer mV/g Piezo
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BACK F. Mailly et Al. ETTC 2003 MIC
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4.2. Sensitivity according to the h
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BACK STUDY OF 3∆t PASSIVE LOCATIN
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∆t 1 ∆t ∆t 2 = t = t M N −1
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For the speed of the reentry vehicl
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BACK TITLE In orbit satellite Gain
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dBm dBm Results obtain with the con
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3. NEW METHOD DEVELOPPED FOR IOT SA
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The following figures present the g
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3.2 Analysis of the contribution Th
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ETSC Annual Activities Gerhard Maye
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BACK Abstract European Telemetry St
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The file structure is also adopted
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BACK The statistical Evaluation Of
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BACK Abstract Vendor Independent Da
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