ETTC'2003 - SEE

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3.2 A/C 0 General architecture: A/C 0 is only a concept, test facility A/C 0 doesn’t really exist. Its application consists in capability of coupling together several already existing test facilities. Each of them can be considered as sub parts of A/C0. The A/C0 perimeter is adaptable and variable with regards to the required test representativity. The concerned sub parts are: • Integration simulator • Iron bird: Integration Bench dedicated for Flight Control system, Hydraulic system, Electrical system • System Integration Bench as Communication and navigation SIB, Engine SIB, Anti Ice SIB Due to the complexity of the systems, the numerous tests to be performed and the limited time dedicated for tests, these means can be used independently to allow a more important test capacity and a quicker progress of the development work. The coupling between several means is realised only when it’s necessary to cover the objectives of tests. Another way to apply this concept is the implementation on the integration simulators of representative system models, designed, manufactured and validated by the aircraft system responsible itself. 3.3 Design directives: The A/C0 is a representative physical integration assembly of the A/C systems meeting the following specifications: • Basic systems must be present (a maximum of calculators shall be present). • Aircraft real time simulation (flight loop, aerodynamics, engines, systems or parts of systems, which cannot be real) must be representative. • For some specific tests (at system and not at aircraft level), real systems may be disconnected. In this case, they must be simulated. • A cockpit which is equipped with all real equipment (avionics, seats, controls...) must be installed, visibility diagrams must comply with. • The equipment must be physically installed at same location as on aircraft (avionics bay). • Wiring and systems connectors must be the same as on the aircraft (except for test connectors); lengths must be comply with. • Test representativity may be improved by a visual system and a cabin motion system. • Each designer must supply its own simulation necessary to adequately replicate the system for the test facility. • The same Flight Test Installation as for Flight Test A/C is installed and it contributes to its validation before A/C1 first flight . So, to improve test efficiency, the working method for test exploitation is the same for ground tests and flight tests.
3.4 Architecture of A380 Simulators: EFCS SIB SIB COUPLINGS (NAV / COM / ENG / AICU / CMV) OPTIONAL REAL SYSTEMS (ADIRS / CPIOM A / B / F / G) IRON BIRD control surfaces simulation control surfaces simulation control surfaces simulation SIMULATOR S81 electronic bay There are 3 integration simulators named S81, S82 and S83, they are identical: • S81 only has the capacity of coupling with Iron Bird • S82 only has the capacity to be set on cabin motion system • Each of them has the capability to integrate A/C real and/or simulated systems according to test needs • one mobile visual system could be connected to each of them • A control surface simulation means is available for each simulator and is connected when there is no coupling with Iron Bird. • Each of them has SIB coupling capacities: NAV/COM, ENGINE, AICU, CMV • Real systems optional use is possible (ADIRS / CPIOM A, B, F, G) • FTI ( Flight Test Installation) is shared between the 3 simulators Simulators is constituted of: • Equipped cockpit: cabin , equipment, seats … • Simulated natural aircraft flight loop: aerodynamic, engine comportment, … • Simulated environment: atmosphere, Navaids, visual, … • Avionics bay with calculators: Warning and visualisation, Flight management, Flight control, … • Simulation computers and hardware Interfaces which assume the communication between the simulated world and the real equipement. • Exploitation tools for printing, recording … A400M cockpit simulation host computer Exploitation tools SIMULATOR S82 electronic bay cockpit simulation host computer Exploitation tools SIMULATOR S83 electronic bay cockpit simulation host computer Exploitation tools cockpit FTI cockpit cabin motion system moveable visual system
Page 1 and 2: SÉANCE D'OUVERTURE / OPENING SESSI
Page 3 and 4: A l’aube de ce siècle, Airbus s
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Page 31 and 32: BACK 1 Introduction AIRBUS AIRCRAFT
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Page 39 and 40: GENERAL PRESENTATION OF JUZZLE GENE
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Page 45 and 46: REFERENCES [1] Space engineering, R
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Page 51 and 52: POSTE INE A380 Les besoins fonction
Page 53 and 54: Les principes de l’architecture :
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Page 57 and 58: BACK Trajectographie temps réel DG
Page 59 and 60: Deux précisions temps réel sont p
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Page 63 and 64: CONCLUSION La phase d'essais en vol
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Page 77 and 78: • JBUILDER • ORACLE Cette modul
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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
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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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