ETTC'2003 - SEE

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GLOSSARY AFDX Avionics Full DupleX ARP Address Resolution Protocol ATM Asynchronous Transfer Mode CDP CISCO Discovery Protocol COTS Component Of The Shelf FANS Future Air Navigation System FTI Flight Test Installation FTP File Transfer protocol ICMP Internet Control Message Protocol IENA Test Installation for New Aircrafts IGMP Internet Group Management Protocol IO Input / Output IP Internet Protocol LAN Local Area Network PCM Pulse Code Modulation QoS Quality Of service SABRE FTI Data Base for A380 SNMP Simple Network Management Protocol STP Spanning Tree Protocol TCP Transmission Control Protocol TFTP Trivial File Transfer protocol UDP User Datagram Protocol WB Wide Band
CLASSICAL FLIGHT TEST INSTALLATIONS Over 20 years of Flight Tests have led to complex architectures for Flight Test Installations, mainly built by adding bricks to existing chains. When technology raised some barriers, the safe and easy way has often been to create new acquisition & recording chains. This has been the case with the duplication of the basic FTI (only Basic FTI is shown in Fig. 1) to perform FANS Flight Tests, or with the Wide Band specific chain for analog measurements up to 20 kHz. « CRASH » PARAMETERS ANALOG MEASUREMENTS DC to 20 Khz MEASUREMENTS DC to 100Hz buses discretes FTI n° 1 FTI n° 2 CONDITIONING UNIT PARAMETERS ’S COPY CONDITIONING UNITS PARAMETERS ’S COPY DIGITAL ACQUISITION UNITS PCM1 DIGITAL ACQUISITION UNITS PCM2 DIGITAL ACQUISITION UNITS PCM3 DIGITAL ACQUISITION UNITS PCM4 DIGITAL ACQUISITION UNITS PCM4 PCM2 PCM3 DIGITAL ACQUISITION UNIT CENTRAL CONTROL UNIT SWITCHING UNITS PCM1 PCM4 4 PCM COCKPIT VOICE DIGITAL RECORDER 1 PCM1 PCM2 PCM3 PCM4 DIGITAL RECORDER 2 CRASH RECORDER SIGNAL PROCESSING UNIT 2 DIGITAL RECORDER MADAM CENTRAL UNIT Figure 1 – A340-500/600 Basic FTI Architecture Various other acquisition chains have seen the light for very specific needs (audio, video, small FTIs…) and are also totally independent one from the others. The real limitation of these architectures, apart of the limited throughput, lies on the noninterconnectivity of the various equipments. Since data format is not homogeneous, and systems IO are only Half Duplex and mostly point-to-point connections, it was not possible to merge or exchange data between FTI systems on classical architecture. In classical FTI architecture, acquisition systems provide an output link coming from Telemetry world (Pulse Code Modulation), which principle is a cyclic transmission of all the aircraft parameters at a cadence around 800 kbit/s. MADAM DISPLAY MADAM KEYBOARD MADAM PRINTER One PCM is usually built with the following characteristics : 12 bits per Word 128 Words per Minor Cycle 256 Minor Cycles per Major Cycle 2 Major Cycles per second ANALOG RECORDER 1 ANALOG RECORDER 2 ANALOG RECORDER 3 SLOW PCM6 PCM 5 SYNCHRO CUB PROCESSOR UNIT 1 CUB DISPLAY UNIT 1 CUB 1 KEYBOARD TO TELEMETRY GROUND STATION ANTENNAS TELEMETRY TRANSMITTER FLIGHT CONDITION PROCESSOR UNIT FLIGHT CONDITION DISPLAY UNIT DGPS RAW DATA and PCM5 RECORDER The standard bit rate of PCM messages used on AIRBUS FTIs is then 786,432 kbit/s. LD CUB PROCESSOR UNIT 2 CUB DISPLAY UNIT 2 CUB 2 KEYBOARD FLIGHT TEST ENGINEER STATION GPS RECEIVER GPS CLOCK GPS TIME TIME BASE GENERATOR GPS ANTENNA PLOTTING PROCESSOR UNIT TRAJECTOGRAPHY GPS DIFFERENTIEL UNIT GMT IRIG-B TO EQUIPEMENTS GRAPHIC RECORDERS HARD COPIERS
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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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Id Nom flux EXP37 Plan de vol Annex
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TTC’2003 Stentor 10/06/2003 QUALI
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TTC’2003 Le Programme Stentor 10/
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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
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Page 208 and 209: Furthermore, the configuration of t
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Page 212 and 213: ISA ISA Interface utilisateur Objet
Page 214 and 215: CONCLUSION La première version de
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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
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Page 240 and 241: Technique COFDM : La modulation COF
Page 242 and 243: La réception s’effectue par une
Page 244 and 245: BACK ETCC'2003 European Test and Te
Page 246 and 247: 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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