ETTC'2003 - SEE

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The complete message is recorded by 4 PCM channels Mass Data Recorders, or decoded for on board analysis. The same information is physically duplicated to go from one acquisition system toward several end-users. The acquisition, processing and storage performances requested by A380 Flight Tests having blown up, AIRBUS had to set up a more global architecture, to unify data format and to jump from cyclic low speed data exchange to up-to-date technologies. SWITCHED IENA IENA ARCHITECTURE The IENA architecture (Installation d’Essais pour les Nouveaux Avions – Flight Test Installation for New Aircraft) is based on 4 levels of data handling : L1 (Level 1) : Sensor level There is performed the data conversion from a physical input (pressure, temperature, force…) into a measurable electrical parameter, tension or current. Some L1 system may integrate a part of L2 functions : filtering, AD conversion… L2 (Level 2) : Acquisition level L2 systems deal with the analog, numerical and discrete acquisition ; they perform the following tasks : - for analog inputs : sensor piloting, analog filtering, data sampling and AD conversion, limited mathematical functions… - for numerical inputs : label sorting, filtering - for all : time stamping with respect to the global synchronisation, data shaping in IENA PACKETS, sorting of packets towards the destinations (groups of L4) L3 (Level 3) : Concentration level L3 is the IENA-specific level, there are gathered data flows coming from all the L2 towards the L4 systems. There is no data modification through L3, the only actions performed are commutation and duplication of the incoming frames. These functions are realised by standard Ethernet switches. L4 (Level 4) : Recording and Analysis level L4 systems are on board end-users for aircraft parameters : - Mass data storage for on-ground post analysis - On-board analysis computers, performing pre-treatment and display for Flight Test Engineers - Telemetry The Flight Test Data Base SABRE –in which the configuration of every system is traced– manages all the IENA systems. SABRE describes the long way of every aircraft parameter from the very beginning of its life (physical phenomenon) to its storage in IENA PACKETS.
MEASUREMENTS L1 Acquisition L2 Acquisition L2 Acquisition L2 Electrical Network L2 ETHERNET LAN Switch L3 Switch L3 Switch L3 Interface L4 CUB L4 Partial recorder Mass Data recorder L4 Configuration loading & control Mass Data Recorder L4 CUB L4 Video Accident Recorder Telemetry Partial recorder Figure 2 - A380 FTI Generic Architecture Time Base Generator As it can be seen on Figure 2, the L3 constitute the real centre of FTI communication : interconnection between L2 and L4 is ensured through a switched Ethernet LAN. L2 L4 Computer L3 Switch L4 Storage Acquired Parameters Computed parameters Ethernet Multicast IP / UDP IENA packets Figure 3 - A380 FTI LAN (Acquisition Mode) Accident FTI Wide Band FTI BASIC Trajectography Flight test Engineer Station ADIS Water Ballast «Crash» Parameters BASIC FTI WIDE BAND FTI CRASH FTI
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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
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TTC’2003 •Equipes CNES : Qualif
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Page 158 and 159: TTC’2003 Les Contraintes de Déve
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Page 162 and 163: TTC’2003 10/06/2003 Qualification
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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
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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 202 and 203: GLOSSARY AFDX Avionics Full DupleX
Page 206 and 207: The L3 switches allow forwarding da
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
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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
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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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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