ETTC'2003 - SEE

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L/S/C /X/Ku /Ka band Spacelink System – The solution for compact and high-tech ground station Tuner 1 Tuner 2 Tuner 3 SPACELINK SYSTEM Digital functions Demod 1 Combiner Demod 3 Demod 2 Tracking BER 2 channels CONTROLLER - GUI interface CCSDS, DVB Frame sync Frame sync Frame sync Storage Control On-board Test Modulator with PRBS Generator To reach the best performances, we choose the last component generation and the results are excellent since the degradation is less than 0,5 dB over the full range : 20 –450 Mbps. Results Pleiades constellation (8-PSK modulation – 155 Mbps) Systems Midi Pyrénées 2/4 Up to 225 mbps Up to 225 mbps Up to 225 mbps Control center Antenna
Spacelink System – The solution for compact and high-tech ground station SPOT 5 (QPSK modulation – 50 Mbps) These results can be optimized by customers !!!. Indeed , users can programs their own filters for a better adaptation with on-board modulator. That means SPACELINK SYSTEM can be compliant with all satellites as it accepts: - synchronous modulations : QPSK / BPSK/ 8 PSK / SQPSK - asynchronous modulations : AQPSK / UQPSK Users have to focus on the fact that SPACELINK SYSTEM accept suitable configurations. Your SPACELINK SYSTEM is fully configurable to reach your needs such as : - LOW DATA RATE MULTIMISSION MODEM : 1 kbps to 20 Mbps Low bit rate telemetry receiver with acquisition capabilities - HIGH DATA RATE MULTIMISSION MODEM : 10 Mbps to 450 Mbps - 3-CHANNELS TRACKING SYSTEM With RF down-converter ( from L to Ka band) - RECORDING UNIT : UP TO 150 GO - TTC/ RANGING and test configurations - REMOTE SENSING / TELEMETRY / TELECOM COMPLETE GROUND STATION Systems Midi Pyrénées 3/4
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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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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
Page 224 and 225: establishing different socket conne
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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
Page 244 and 245: BACK ETCC'2003 European Test and Te
Page 246 and 247: ETCC'2003 European Test and Telemet
Page 252 and 253: SESSION 6 : SYSTEMES DE TELEMESURE
Page 254 and 255: f f p IF = R b = 4R b ∆f = 0. 7R
Page 256 and 257: 2.3 ADC Fig.5 (a) y (t) and its spe
Page 258 and 259: 2.5 FM demodulation Fig.9 I ‘(nT1
Page 260 and 261: References 1. Gardner FM. A BPSK/QP
Page 264 and 265: Spacelink System - The solution for
Page 266 and 267: SPOT Σ ∆ X band feed Data LNA Tr
Page 268 and 269: défilant. Le cahier des charges d
Page 270 and 271: TOURELLE HEXAPODE La tourelle hexap
Page 272 and 273: Ci après, tableau des spécificati
Page 274 and 275: BACK CRISTAUX PHOTONIQUES ET METAMA
Page 276 and 277: BACK Systems, Design & Tests Direct
Page 278 and 279: 1. INTRODUCTION Cette communication
Page 280 and 281: Figure 2-1 Vue générale de la Bas
Page 282 and 283: 3. ETALONNAGE DE LA BASE 3.1 PRINCI
Page 284 and 285: Par définition, le taux de polaris
Page 286 and 287: This document is the property of EA
Page 288 and 289: amplitude (dB) 10 0 -10 -20 -30 -40
Page 290 and 291: amplitude (dB) 10 0 -10 -20 -30 -40
Page 292 and 293: V1=K1.GVV.E.{[cos()-.sin()] + 1_vra
Page 294 and 295: Quelques calculs d’incertitude so
Page 296 and 297: - 21 - Amplitude polarisation verti
Page 298 and 299: - 23 - Amplitude composante vertica
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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.
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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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