ETTC'2003 - SEE

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UNIT Unit EMC documents : - grounding & bonding diagrams - frequency plan - Interface control document - EMC test plan - EMC test procedure - EMC test report EMC tests at unit level Launchers user’s handbook S/C EMC test requirements Design rules implementation Validation S/C EMC Specification EMC Control Plan 2 System requirements EMC Assessments : SYSTEM - Grounding and bonding diagrams - Conducted analysis : power bus model, crosscoupling analysis, signal interface analysis - Radiated analysis : self-compatibility and RF compatibility w.r.t launchers - ESD analysis - Harness shielding need analysis - Magnetic analysis Problems identification : - Analysis of specification waivers/deviations at unit level - Solution implementation at System level : shielding… - EMC/ESD design rules implementation Validation EMC tests at System level : Test plan, test procedure, test report
EMC CONTROL ACTIVITY The EMC control activity is shared in two main domains which are detailed in the following paragraphs : design engineering and tests. Control of design rules implementation The control of the application of the design rules is exercised at unit level by an active participation of the EMC engineer to the unit design reviews: examination of the interface circuits, mechanical construction, connector implementation, zero Volt diagrams... At system level this activity consists in participation to the mechanical design for grounding aspects, definition of shielding when necessary, harness routing and implementation, approval of the outer materials... Analyses & Modelling The analyses allow to demonstrate the good behaviour of the satellite prior to the system tests in the case of radiated mode and conducted mode analyses, in order to implement as early as possible the recovery actions, if necessary. The main analyses are : • Assessment of the satellite electromagnetic environment and the associated safety margins : In conducted mode : electrical model of the power bus in conjunction with electrical power supply engineer, cross-coupling analysis, signal interface analysis In radiated mode : launcher compatibility analysis, self-compatibility analysis (at internal and external units level) • Magnetic analysis • Definition of the satellite grounding and bonding diagrams • Analysis of the EMC waivers/deviations • Shielding need analysis • ESD (Surface charging analysis) analysis Tests At system level, the activity consists in defining the tests that are performed, and in co-ordination with AIT and Project teams, the definition of the configuration that are tested and the criteria of success for the susceptibility tests. The EMC tests are performed according to the test documentation : plan, procedure and report. 3
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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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TTC’2003 •L’organisation mise
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TTC’2003 Interfaces Externes :
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TTC’2003 Les Contraintes de Déve
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TTC’2003 Contient ontient la la m
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TTC’2003 10/06/2003 Qualification
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TTC’2003 10/06/2003 Qualification
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BACK Résumé : Outil de traitement
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1 Principes généraux de l’outil
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1.2.3 Valise de piste L’outil peu
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2 Capacités fonctionnelles 2.1 Arc
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Vue f(t) 2.3.1 Vues y=f(t) Ces vues
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Maquette aéronef Alarmes Bar-graph
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2.3.3 Représentation trajectograph
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2.3.5 Vidéo Par ailleurs, si le ma
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3 Concept de structure d’accueil
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4 Exemples d’utilisation 4.1.1 HB
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SESSION 3 : Capteurs et dispositifs
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BACK THE NEXT GENERATION AIRBORNE D
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3. DC SPECIFICATIONS - SEEING THE W
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For the purposes of this paper it i
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hardware down and led to widely acc
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mechanism. In a system where a late
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0 X Y X' Y' 0 X Y Sampling Cycle X
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- Perform the exchange in a rigorou
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GLOSSARY AFDX Avionics Full DupleX
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The complete message is recorded by
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The L3 switches allow forwarding da
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Furthermore, the configuration of t
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BACK LOGICIEL JAVA D’ACQUISITION
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ISA ISA Interface utilisateur Objet
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CONCLUSION La première version de
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; ( ( + & 2+5. . & & , & . + & +2(
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( +, & + < 0 9& - & = (( + 1 - + +,
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BACK Telemetry Recording Workstatio
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Figure 1: Real-time pen tip display
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establishing different socket conne
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73 64 63 61 60 48 45 40 35 Level (d
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SESSION 5 : TELEMESURE (SPECTRE - M
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Currently various avenues are explo
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Binary X Binary to RNS and RNS to B
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The index multiplier block will be
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The current implementation consists
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Spécificité de la télémesure AI
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Technique COFDM : La modulation COF
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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
Page 302 and 303: 3.4 SYNTHESE DES RESULTATS CONCERNA
Page 304 and 305: 4.2 DEFINITION DE L'ANTENNE DE MISE
Page 306 and 307: 4.4 DEFINITION DE L'ANTENNE DE REFE
Page 308 and 309: 5.1.2 Diagrammes de rayonnement 5.1
Page 310 and 311: 5.2 ANTENNE DE REFERENCE BANDE P 5.
Page 312 and 313: Gain (dBi) 5.2.2.2 Résultats Ils s
Page 314 and 315: Comme attendu, la coupe xOz présen
Page 316 and 317: Gain (dBi) 5.3.2 diagramme de rayon
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Page 320 and 321: BACK INTRODUCTION MESURE DE CHAMP P
Page 322 and 323: MESURE DE CHAMP PAR SYSTEME PORTABL
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Page 326 and 327: Abstract Helicopters are relatively
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Page 330 and 331: BACK Résumé Architecture d’une
Page 332 and 333: Architecture type lanceur lourd ARI
Page 334 and 335: Architecture petit lanceur L’arch
Page 336 and 337: Diagramme de l’UCTM Voies analogi
Page 338 and 339: Exemples de capteurs utilisés Type
Page 340 and 341: SESSION 8 : COMPATIBILITE ELECTROMA
Page 342 and 343: 1. CONTEXTE GENERAL Le durcissement
Page 344 and 345: Figure 1 : Actions de qualification
Page 346 and 347: 5. LES PARAMETRES D’OPTIMISATION
Page 348 and 349: 7. PERFORMANCE ET OPTIMISATION DU P
Page 350 and 351: La qualification du durcissement re
Page 354 and 355: At equipment level EMC TEST PROGRAM
Page 356 and 357: BACK ETTC 2003. Le rôle de la simu
Page 358 and 359: comprenant des objets complexes, n
Page 360 and 361: Cette approche permet, avec les mê
Page 362 and 363: Les Thèses ONERA UPS Prise en comp
Page 364 and 365: Pression Ligne bifilaire non blind
Page 366 and 367: 1.8 1,8 Tension continue V 1.6 1.4
Page 368 and 369: 270 Ω I0 IL 2,7 kΩ (b) Alimenta
Page 370 and 371: What is the budget of the statistic
Page 372 and 373: Monte Carlo approach: This is a thr
Page 374 and 375: 2 Etat de l’art des standards de
Page 376 and 377: 2.1.6 Emissions standards 61967 par
Page 378 and 379: - Limites pour l’immunité DPI (e
Page 380 and 381: PRESENTATIONS POSTER / POSTER PRESE
Page 382 and 383: BACK LA TELEMESURE SUR AIRBUS JC GH
Page 384 and 385: Dans le cycle d ’essais en vol ,
Page 386 and 387: CONCLUSION - NOS BESOINS FUTURS AIR
Page 388 and 389: LOGICIELS DE MESURE ET DE TRAITEMEN
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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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