ETTC'2003 - SEE

More documents

Recommendations

Info

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
Page 1 and 2:
SÉANCE D'OUVERTURE / OPENING SESSI
Page 3 and 4:
A l’aube de ce siècle, Airbus s
Page 5 and 6:
Etape 4 : L’avion réel une fois
Page 7 and 8:
C’est, sur l’exemple des essais
Page 9 and 10:
parfois même sous la forme de plat
Page 11 and 12:
oth the system and the manufacturin
Page 13 and 14:
Such an interdependence between tes
Page 15 and 16:
eference books, but it is as fundam
Page 17 and 18:
BACK MANAGEMENT DES ESSAIS SYSTEME
Page 19 and 20:
BACK ESSAIS D’ENSEMBLE LANCEURS C
Page 21 and 22:
Elle ne doit cependant pas être me
Page 23 and 24:
- le plan de mesures est conséquen
Page 25 and 26:
4.2 MAQUETTE DYNAMIQUE ARIANE 5 Dan
Page 27 and 28:
Les points délicats liés à l’o
Page 29 and 30:
Processus Commande Architecture Int
Page 31 and 32:
BACK 1 Introduction AIRBUS AIRCRAFT
Page 33 and 34:
So, different test tools shall be d
Page 35 and 36:
3.4 Architecture of A380 Simulators
Page 37 and 38:
3.6 A380: Models In order to suppor
Page 39 and 40:
GENERAL PRESENTATION OF JUZZLE GENE
Page 41 and 42:
Figure 3 : Graphic User Interface o
Page 43 and 44:
IMPLEMENTATION AND SIMULATION OF A
Page 45 and 46:
REFERENCES [1] Space engineering, R
Page 47 and 48:
Client Compliance Matrix (par rappo
Page 49 and 50:
SESSION 2 : TECHNIQUES ET MOYENS D'
Page 51 and 52:
POSTE INE A380 Les besoins fonction
Page 53 and 54:
Les principes de l’architecture :
Page 55 and 56:
Les éléments de l’architecture
Page 57 and 58:
BACK Trajectographie temps réel DG
Page 59 and 60:
Deux précisions temps réel sont p
Page 61 and 62:
4.00 3.00 2.00 1.00 0.00 -1.00 -2.0
Page 63 and 64:
CONCLUSION La phase d'essais en vol
Page 65 and 66:
RÉSUMÉ: Osiris est une gamme de m
Page 67 and 68:
1. INTRODUCTION Dassault Aviation e
Page 69 and 70:
Exemple de modules banc d'intégrat
Page 71 and 72:
éduction de durée des essais par
Page 73 and 74:
5. EXEMPLE L'OSIRIS MULTIFONCTION U
Page 75 and 76:
6. LA MODULARITÉ DE LA GAMME OSIRI
Page 77 and 78:
• JBUILDER • ORACLE Cette modul
Page 79 and 80:
• VX Wxorks reste l'OS de la part
Page 81 and 82:
6.5 Exemple d'interconnexion avec d
Page 83 and 84:
PRINCIPE 7.3 Exemple de réalisatio
Page 85 and 86:
8. LA NOUVELLE GAMME SUR PC: VÉNUS
Page 87 and 88:
• Un IHM de sélection des param
Page 89 and 90:
9. CONCLUSION OSIRIS a maintenant g
Page 91 and 92:
TABLE DES MATIERES 1. LE DATA-LINK
Page 93 and 94:
AVIONS appartenant au réseau 25_P_
Page 95 and 96:
• Les données à émettre sur le
Page 97 and 98:
• 25_P_2/04 PCM émis par l'avion
Page 99 and 100:
3.2 Le temps différé • En temps
Page 101 and 102:
4. CONCLUSION • Toutes les IHM in
Page 103 and 104:
INTRODUCTION Pour définir des proc
Page 105 and 106:
- Ecarts de position en temps réel
Page 107:
ANNEXE 1 CONSTITUTION CONSTITUTION
Page 110 and 111:
They however incorporate some eleme
Page 112 and 113:
As technology evolves, the boundary
Page 114 and 115:
shown below together with the AGE c
Page 116 and 117:
BACK ESSAIS SYSTEME SUR LES PROJETS
Page 118 and 119:
3 qui contient le logiciel de vol.
Page 120 and 121:
5 • essais en station « in vivo
Page 122 and 123:
Avis, options et recommandations (5
Page 124 and 125:
BACK Automatic Validation of Flight
Page 126 and 127:
− The second level provides all d
Page 128 and 129:
The operational flexibility of SINU
Page 130 and 131:
• Test duration is reduced : for
Page 132 and 133:
mimics from CCS ones. The objective
Page 134 and 135:
1. Introduction ...................
Page 136 and 137:
2. Présentation Le segment sol Ste
Page 138 and 139:
AUS Station STA TM/TC Station STS T
Page 140 and 141:
• La Commission de Revue d’Essa
Page 142 and 143:
Certains essais particuliers liés
Page 144 and 145:
Id Nom flux EXP37 Plan de vol Annex
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 194 and 195: hardware down and led to widely acc
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 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
Page 216 and 217: ; ( ( + & 2+5. . & & , & . + & +2(
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
Page 226 and 227: 73 64 63 61 60 48 45 40 35 Level (d
Page 228 and 229: SESSION 5 : TELEMESURE (SPECTRE - M
Page 230 and 231: Currently various avenues are explo
Page 232 and 233: Binary X Binary to RNS and RNS to B
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 262 and 263:
L/S/C /X/Ku /Ka band Spacelink Syst
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
Page 300 and 301:
- 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
Page 318 and 319:
Gain (dBi) 15 10 5 0 -5 -10 -15 -20
Page 320 and 321:
BACK INTRODUCTION MESURE DE CHAMP P
Page 322 and 323:
MESURE DE CHAMP PAR SYSTEME PORTABL
Page 324 and 325:
MESURE DE CHAMP PAR SYSTEME PORTABL
Page 326 and 327:
Abstract Helicopters are relatively
Page 328 and 329:
Au sol, la station réceptionne le
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 352 and 353:
UNIT Unit EMC documents : - groundi
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
Page 390 and 391:
Page 392 and 393:
Page 394 and 395:
In order to optimize the phase nois
Page 396 and 397:
Photo-oscillator active device Opti
Page 398 and 399:
the inverse of N×N correlation mat
Page 400 and 401:
quasi-synchronous multiuser detecto
Page 402 and 403:
Multiuser Interference Canceler ”
Page 404 and 405:
the inverse of N×N correlation mat
Page 406 and 407:
quasi-synchronous multiuser detecto
Page 408 and 409:
Multiuser Interference Canceler ”
Page 410 and 411:
All these sub-systems can be easily
Page 412 and 413:
3.5 ACPR RACK Gateway and satellite
Page 414 and 415:
4.2 COMPONENT DEGRADATION MEASUREME
Page 416 and 417:
Indeed, when the objective of the t
Page 418 and 419:
All the five points can be achieved
Page 420 and 421:
M r Mmax (0 dB, -180°) b = 0 a ωc
Page 422 and 423:
2 - Test devices at ENSICA Souffler
Page 424 and 425:
Soufflerie à Densité Variable (SD
Page 426 and 427:
Capacité : - pour la charge axiale
Page 428 and 429:
Machine d’essai de fatigue en fle
Page 430 and 431:
torsion. - asservissement de chaque
Page 432 and 433:
KEY 1 WORD IENA PACKET format An IE
Page 434 and 435:
TD: “0” means that the paramete
Page 436 and 437:
PARAMETER DESCRIPTION This array de
Page 438 and 439:
BACK UTILISATION de CAMERAS NUMERIQ
Page 440 and 441:
TABLE DES MATIÈRES 1. INTRODUCTION
Page 442 and 443:
2. CONTEXTE DES ESSAIS Le but des e
Page 444 and 445:
3. LES BESOINS ET LES CONTRAINTES 3
Page 446 and 447:
4. CHOIX DE LA CAMERA 4.1 Démarche
Page 448 and 449:
5.1.4 Adaptations Les deux principa
Page 450 and 451:
Tir d'un missile AIR/AIR éjecté T
Page 452 and 453:
6. CONCLUSION Cette évaluation mon
Page 454 and 455:
Capteur Intelligent IEEE 1451.4 Pri
Page 456 and 457:
pC/g Piezo Accelerometer mV/g Piezo
Page 458 and 459:
BACK F. Mailly et Al. ETTC 2003 MIC
Page 460 and 461:
4.2. Sensitivity according to the h
Page 462 and 463:
BACK STUDY OF 3∆t PASSIVE LOCATIN
Page 464 and 465:
∆t 1 ∆t ∆t 2 = t = t M N −1
Page 466 and 467:
For the speed of the reentry vehicl
Page 468 and 469:
BACK TITLE In orbit satellite Gain
Page 470 and 471:
dBm dBm Results obtain with the con
Page 472 and 473:
3. NEW METHOD DEVELOPPED FOR IOT SA
Page 474 and 475:
The following figures present the g
Page 476 and 477:
3.2 Analysis of the contribution Th
Page 478 and 479:
ETSC Annual Activities Gerhard Maye
Page 480 and 481:
BACK Abstract European Telemetry St
Page 482 and 483:
The file structure is also adopted
Page 484 and 485:
BACK The statistical Evaluation Of
Page 486 and 487:
BACK Abstract Vendor Independent Da
show all

ETTC'2003 - SEE

You also want an ePaper? Increase the reach of your titles

Delete template?

Save as template?