TERMIUM Plus^®

Record 1,  Textual support,  English

Record number: 1, Textual support number: 1 CONT

... gyros and accelerometers have an offset, known as bias. The gyro bias for instance, shows itself after integration as an angular drift, increasing rise linearly over time(ramp)... To compensate for sensor drift, a process called augmentation is used, whereby gyro and acceleration errors are compensated by utilising other system states. For instance the angular drift error of a gyro after integration can be compensated, if true angular measurements are taken. Comparing the two shows then the gyro drift. Assuming that inertial systems are generally operated around an equilibrium position and thus linear acceleration integrates to zero over time, then attitude can be processed via gravitational acceleration, thus giving true angular measurements to compensate gyro drift.  1, record 1, English, - angular%20drift

Record 1,  Textual support,  French

Record number: 1, Textual support number: 1 CONT

[...] il est possible de réaliser des capteurs gyrométriques dont les performances sont caractérisées par une erreur de facteur d'échelle pouvant être inférieure à 10^-6, une dérive angulaire de l'ordre de quelques millièmes de degré par heure, pendant quelques heures, un domaine de mesure pouvant dépasser 360 degrés par seconde. Ces caractéristiques ont notamment autorisé la réalisation de navigateurs inertiels (sans plate-forme stabilisée) destinés aux avions civils et militaires ainsi qu'à des lanceurs spatiaux comme Ariane IV et V.  1, record 1, French, - d%C3%A9rive%20angulaire

Record 1,  Textual support,  Spanish

Record 2,  Textual support,  English

Record number: 2, Textual support number: 1 CONT

Altitude error gives incorrect distance from target and attitude error of pitch gives incorrect errors in angles of deflection and incidence...  2, record 2, English, - attitude%20error

Record 2,  Textual support,  French

Record 2,  Textual support,  Spanish

Record 3,  Textual support,  English

Record number: 3, Textual support number: 1 CONT

The Attitude and Vernier Upper Module. The Vega launch vehicle is equipped with a liquid propulsion module(AVUM), which provides roll control and pitch, yaw, and axial thrust during the final phase of flight. It shall perform the following functions :-roll control;-attitude control during coasting flight and in orbit phase;-correction of axial velocity error due to solid rocket motor performance scatter;-generation of the required velocity change for orbit circularisation(as required) ;-satellite pointing;-satellite release manoeuvres;-empty stage de-orbiting.  2, record 3, English, - attitude%20and%20Vernier%20upper%20module

Record 3,  Textual support,  French

Record number: 3, Textual support number: 1 CONT

Enfin, on attend la signature du contrat de développement du petit lanceur Vega. Il s'agit d'un lanceur composé de trois étages à propergol solide, surmonté d'un module supérieur à liquide dit AVUM (Attitude and Vernier Upper Module) - permettant le contrôle d'attitude et d'orbite, la séparation des satellites et la désorbitisation - ainsi que d'une coiffe.  2, record 3, French, - module%20sup%C3%A9rieur%20Vernier%2Fcommande%20d%27orientation

Record 3,  Textual support,  Spanish

Record 4,  Textual support,  English

Record number: 4, Textual support number: 1 DEF

An error in gyro output due to cross-coupling and acceleration encountered during vehicle turns.  3, record 4, English, - turn%20error

Record number: 4, Textual support number: 1 CONT

Principal Attitude Indicator Errors. Turn Error. During a normal coordinated turn, centrifugal force causes the gyro to precess toward the inside of the turn. This precession increases as the bank steepens; therefore, it is greatest during the actual turn. The error disappears as the aircraft rolls out at the end of a 180 degrees turn at a normal rollout rate. Therefore, when performing a steep turn, the pilot may use the attitude indicator for rolling in and out of the turn, but should use other instruments(VSI and altimeter) during the turn for specific pitch information.  4, record 4, English, - turn%20error

Record 4,  Textual support,  French

Record 4,  Textual support,  Spanish

Record 5,  Textual support,  English

Record number: 5, Textual support number: 1 CONT

The basic attitude sensor was the three-gyro inertial reference package. It contained two air-tight integrating gyro units to sense pitch and yaw, and one miniature integrating gyro unit to sense roll. The pitch and roll gyros were torqued by signals obtained by two Barnes mod IIA infrared horizon sensors. Gyrocompassing oriented the vehicle to an orbit plane yaw reference by detecting a component of the programmed pitch rate through the roll horizon sensor. The geocentric pitch rate(typically 4 deg/min, for a low-altitude orbit) was programmed as a constant torque to the pitch gyro. This pitch component, if a yaw error was present, would be sensed differentially when compared with the roll components of the two horizon-sensor heads. The differential would be seen as a function of yaw error.  2, record 5, English, - roll%20component

Record number: 5, Textual support number: 2 CONT

During heading align, the rotor of the resolver is positioned so that it transforms the N-S and E-W liquid level signals into pitch and roll components which are referenced to heading. The pitch component is amplified, demodulated and summed with amplified and demodulated feedback signals from the VG [vertical gyro] roll and pitch pickoffs and the pitch synchro. The combined signal is then modulated, amplified and converted to DC [direct current] to drive the platform pitch gimbal torque motor until the input signals are nulled.  1, record 5, English, - roll%20component

Record 5,  Textual support,  French

Record number: 5, Textual support number: 1 CONT

Durant l'alignement sur le cap, le rotor du résolver est mis en position de telle sorte qu'il transforme les signaux des niveaux à liquide N.-S. et E.-O. en composantes de tangage et de roulis en référence au cap. La composante de tangage est amplifiée, démodulée et composée avec des signaux de réaction amplifiés et démodulés venant des capteurs de roulis et de tangage du VG [gyroscope directionnel] et du synchro de tangage. Ce signal composé est alors modulé, amplifié et converti en courant continu pour entraîner le moteur couple du cardan de tangage de la plate-forme jusqu'à ce que les signaux d'entrée soient annulés.  2, record 5, French, - composante%20en%20roulis

Record number: 5, Textual support number: 2 CONT

Il s'agit de la rotation galiléenne mais [...] la rotation à annuler quand on souhaite obtenir un pointage Terre parfait est la rotation relative au repère orbital de composantes en roulis, tangage et lacet.  1, record 5, French, - composante%20en%20roulis

Record 5,  Textual support,  Spanish

Record 6,  Textual support,  English

Record number: 6, Textual support number: 1 CONT

The basic attitude sensor was the three-gyro inertial reference package. It contained two air-tight integrating gyro units to sense pitch and yaw, and one miniature integrating gyro unit to sense roll. The pitch and roll gyros were torqued by signals obtained by two Barnes mod IIA infrared horizon sensors. Gyrocompassing oriented the vehicle to an orbit plane yaw reference by detecting a component of the programmed pitch rate through the roll horizon sensor. The geocentric pitch rate(typically 4 deg/min, for a low-altitude orbit) was programmed as a constant torque to the pitch gyro. This pitch component, if a yaw error was present, would be sensed differentially when compared with the roll components of the two horizon-sensor heads. The differential would be seen as a function of yaw error.  2, record 6, English, - pitch%20component

Record number: 6, Textual support number: 2 CONT

During heading align, the rotor of the resolver is positioned so that it transforms the N-S and E-W liquid level signals into pitch and roll components which are referenced to heading. The pitch component is amplified, demodulated and summed with amplified and demodulated feedback signals from the VG [vertical gyro] roll and pitch pickoffs and the pitch synchro. The combined signal is then modulated, amplified and converted to DC [direct current] to drive the platform pitch gimbal torque motor until the input signals are nulled.  3, record 6, English, - pitch%20component

Record 6,  Textual support,  French

Record number: 6, Textual support number: 1 CONT

Durant l'alignement sur le cap, le rotor du résolver est mis en position de telle sorte qu'il transforme les signaux des niveaux à liquide N.-S. et E.-O. en composantes de tangage et de roulis en référence au cap. La composante de tangage est amplifiée, démodulée et composée avec des signaux de réaction amplifiés et démodulés venant des capteurs de roulis et de tangage du VG [gyroscope directionnel] et du synchro de tangage. Ce signal composé est alors modulé, amplifié et converti en courant continu pour entraîner le moteur couple du cardan de tangage de la plate-forme jusqu'à ce que les signaux d'entrée soient annulés.  2, record 6, French, - composante%20en%20tangage

Record number: 6, Textual support number: 2 CONT

[...] il s'agit de la rotation galiléenne mais [...] la rotation à annuler quand on souhaite obtenir un pointage Terre parfait est la rotation relative au repère orbital de composantes en roulis, tangage et lacet.  1, record 6, French, - composante%20en%20tangage

Record 6,  Textual support,  Spanish

Record 7,  Textual support,  English

Record number: 7, Textual support number: 1 DEF

That portion of the guidance signal error which causes control surface, wheel and column motion and could affect aircraft attitude angle during coupled flight, but does not cause aircraft displacement from the desired course and/or glide path.  1, record 7, English, - control%20motion%20noise

Record number: 7, Textual support number: 1 OBS

control motion noise; CMN: term, abbreviation and definition officially approved by the International Civil Aviation Organization (ICAO).  2, record 7, English, - control%20motion%20noise

Record 7,  Textual support,  French

Record number: 7, Textual support number: 1 DEF

Partie de l'erreur de signal de guidage qui provoque des déplacements des gouvernes et commandes d'assiette latérale et longitudinale et qui est susceptible d'influer sur l'assiette de l'aéronef en vol couplé, mais qui n'écarte pas l'aéronef de l'alignement de piste et/ou de l'alignement de descente souhaités.  1, record 7, French, - bruit%20sur%20les%20commandes

Record number: 7, Textual support number: 1 OBS

bruit sur les commandes; CMN : terme, abréviation et définition uniformisés par l'Organisation de l'aviation civile internationale (OACI).  2, record 7, French, - bruit%20sur%20les%20commandes

Record 7,  Textual support,  Spanish

Record number: 7, Textual support number: 1 DEF

Aquella parte del error de la señal de guía que origina movimiento en los timones y mandos y pudiera afectar al ángulo de actitud de la aeronave durante el vuelo acoplado, pero que no hace que la aeronave se desvíe del rumbo y/o de la trayectoria de planeo deseados.  1, record 7, Spanish, - ruido%20de%20mandos

Record number: 7, Textual support number: 1 OBS

ruido de mandos; CMN : término, abreviatura y definición aceptados oficialmente por la Organización de Aviación Civil Internacional (OACI).  2, record 7, Spanish, - ruido%20de%20mandos

Record 8,  Textual support,  English

Record number: 8, Textual support number: 1 OBS

When the roll attitude error signal is greater than 2 degrees, the signal is applied directly to the slow-in rate limiter.  1, record 8, English, - slow%2Din%20rate%20limiter

Record 8,  Textual support,  French

Record number: 8, Textual support number: 1 OBS

Limiteur adoucisseur (...) Il est utilisé pour limiter l'amplitude des signaux de roulis à une valeur déterminée.  1, record 8, French, - limiteur%20adoucisseur

Record number: 8, Textual support number: 2 OBS

Le code de source complet est MECAR-SE-210F,1972,22-14-0,3  2, record 8, French, - limiteur%20adoucisseur

Record 8,  Textual support,  Spanish