EP1588942A1 - Throttle lever for controlling the operation of at least one engine of an aircraft - Google Patents

Throttle lever for controlling the operation of at least one engine of an aircraft Download PDF

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Publication number
EP1588942A1
EP1588942A1 EP05290676A EP05290676A EP1588942A1 EP 1588942 A1 EP1588942 A1 EP 1588942A1 EP 05290676 A EP05290676 A EP 05290676A EP 05290676 A EP05290676 A EP 05290676A EP 1588942 A1 EP1588942 A1 EP 1588942A1
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EP
European Patent Office
Prior art keywords
guide track
track
control lever
lever
regime
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Granted
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EP05290676A
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German (de)
French (fr)
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EP1588942B1 (en
Inventor
Dany Marjanski
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Airbus Operations SAS
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Airbus Operations SAS
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Publication of EP1588942A1 publication Critical patent/EP1588942A1/en
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    • G—PHYSICS
    • G05—CONTROLLING; REGULATING
    • G05G—CONTROL DEVICES OR SYSTEMS INSOFAR AS CHARACTERISED BY MECHANICAL FEATURES ONLY
    • G05G1/00—Controlling members, e.g. knobs or handles; Assemblies or arrangements thereof; Indicating position of controlling members
    • G05G1/04—Controlling members for hand actuation by pivoting movement, e.g. levers
    • G—PHYSICS
    • G05—CONTROLLING; REGULATING
    • G05G—CONTROL DEVICES OR SYSTEMS INSOFAR AS CHARACTERISED BY MECHANICAL FEATURES ONLY
    • G05G5/00—Means for preventing, limiting or returning the movements of parts of a control mechanism, e.g. locking controlling member
    • G05G5/02—Means preventing undesired movements of a controlling member which can be moved in two or more separate steps or ways, e.g. restricting to a stepwise movement or to a particular sequence of movements
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T74/00—Machine element or mechanism
    • Y10T74/20—Control lever and linkage systems
    • Y10T74/20396—Hand operated

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  • Physics & Mathematics (AREA)
  • General Physics & Mathematics (AREA)
  • Engineering & Computer Science (AREA)
  • Automation & Control Theory (AREA)
  • Control Of Throttle Valves Provided In The Intake System Or In The Exhaust System (AREA)
  • Control Of Vehicle Engines Or Engines For Specific Uses (AREA)
  • Mechanical Control Devices (AREA)
  • Output Control And Ontrol Of Special Type Engine (AREA)

Abstract

The throttle has a guiding path (5) and a guiding path (6) that permits a control lever (2) to take one of different positions, where each position controls a particular drive speed of an aircraft engine. The path (6) has several detents (7) susceptible to receive guiding units (3). An auxiliary guiding path (8) allows the lever to be displaced continuously to control the engine speed in a continuous manner. The guiding path (5) permits the lever (2) to be displaced in a continuous manner to control continuously the speed by inversion of thrust. An independent claim is also included for an aircraft with a throttle.

Description

La présente invention concerne une manette de gaz pour commander le régime d'au moins un moteur d'un aéronef.The present invention relates to a throttle lever for controlling the speed of at least one engine of an aircraft.

Bien que non exclusivement, la présente invention s'applique plus particulièrement à une manette de gaz pour commander un turbopropulseur, c'est-à-dire un moteur comportant une turbine à gaz entraínant une ou plusieurs hélices par l'intermédiaire d'un réducteur.Although not exclusively, the present invention applies more particularly to a throttle lever for controlling a turboprop, that is to say an engine comprising a gas turbine driving a or several propellers via a reducer.

On sait qu'une manette de gaz comporte généralement :

  • un levier de commande qui est susceptible d'être basculé de part et d'autre d'une position prédéterminée respectivement vers l'avant et vers l'arrière, sous une action manuelle d'un pilote de l'aéronef, et qui comporte un moyen de guidage solidaire dudit levier de commande et susceptible de coopérer avec au moins une première et une seconde pistes de guidage qui limitent les déplacements dudit moyen de guidage et ainsi dudit levier de commande ;
  • ladite première piste de guidage qui permet au levier de commande d'être déplacé de façon continue à partir de ladite position prédéterminée vers l'arrière, pour commander de façon continue le régime en inversion de poussée ; et
  • ladite seconde piste de guidage, pour le déplacement vers l'avant du levier de commande, qui comporte une pluralité de crans susceptibles de recevoir ledit moyen de guidage de manière à permettre au levier de commande de prendre l'une d'une pluralité de positions différentes, chacune desdites positions commandant un régime particulier d'avancement dudit moteur.
It is known that a throttle generally comprises:
  • a control lever which can be tilted on either side of a predetermined position respectively forward and rearward, under manual action of a pilot of the aircraft, and which comprises a guide means secured to said control lever and capable of cooperating with at least a first and a second guide tracks which limit the movements of said guide means and thus said control lever;
  • said first guide track which allows the control lever to be continuously moved from said predetermined rearward position to continuously control the thrust reversal regime; and
  • said second guide track, for the forward movement of the control lever, which has a plurality of notches capable of receiving said guide means so as to allow the control lever to take one of a plurality of positions different, each of said positions controlling a particular speed of advancement of said engine.

La présence desdits crans permet une gestion maítrisée de certains régimes moteur particuliers, tels que le régime de décollage / remise des gaz par exemple.The presence of said notches allows a controlled management of certain particular engine speeds, such as the take-off / gas for example.

Une telle manette de gaz n'est toutefois pas bien adaptée à certains types de vol ou phases de vol, notamment des phases de vol militaires telles que le ravitaillement en vol par exemple, pour lesquels la commande du régime nécessite une très grande sensibilité. Le régime d'avancement du ou des moteurs doit en effet, dans de telles situations, pouvoir être modifié de façon très souple, sans interruption, et être adapté progressivement. Une telle sensibilité ne peut pas être obtenue avec la manette de gaz du type précité, en raison de la présence desdits crans qui empêchent un déplacement sans interruption du levier de commande.Such a throttle is however not well adapted to certain flight types or phases of flight, including military flight phases such as in-flight refueling, for which Diet control requires a very high sensitivity. The system of government of the engine (s) must indeed, in such situations, can be modified flexibly, without interruption, and adapted gradually. Such sensitivity can not be achieved with the throttle of the aforementioned type, because of the presence of said notches which prevent uninterrupted movement of the control lever.

De plus, en raison de cet inconvénient, on a tendance à limiter le plus possible le nombre de crans, et donc le nombre de régimes particuliers susceptibles d'être gérés ainsi individuellement.Moreover, because of this disadvantage, there is a tendency to limit the more possible the number of notches, and therefore the number of special diets likely to be managed individually.

La présente invention concerne une manette de gaz permettant de remédier à ces inconvénients.The present invention relates to a throttle lever for remedy these disadvantages.

A cet effet, selon l'invention, ladite manette de gaz du type comportant :

  • un levier de commande qui est susceptible d'être basculé de part et d'autre d'une position prédéterminée respectivement vers l'avant et vers l'arrière, sous une action manuelle d'un pilote de l'aéronef, et qui comporte un moyen de guidage solidaire dudit levier de commande et susceptible de coopérer avec au moins une première et une seconde pistes de guidage qui limitent les déplacements dudit moyen de guidage et ainsi dudit levier de commande ;
  • ladite première piste de guidage qui permet au levier de commande d'être déplacé de façon continue à partir de ladite position prédéterminée vers l'arrière, pour commander de façon continue le régime en inversion de poussée ; et
  • ladite seconde piste de guidage, pour le déplacement vers l'avant du levier de commande, qui comporte une pluralité de crans susceptibles de recevoir ledit moyen de guidage de manière à permettre au levier de commande de prendre l'une d'une pluralité de positions différentes, chacune desdites positions commandant un régime particulier d'avancement dudit moteur,
est remarquable en ce qu'elle comporte, de plus, une piste de guidage auxiliaire permettant au levier de commande d'être déplacé de façon continue à partir de ladite position prédéterminée vers l'avant, pour commander de façon continue le régime d'avancement du moteur.For this purpose, according to the invention, said throttle of the type comprising:
  • a control lever which can be tilted on either side of a predetermined position respectively forward and rearward, under manual action of a pilot of the aircraft, and which comprises a guide means secured to said control lever and capable of cooperating with at least a first and a second guide tracks which limit the movements of said guide means and thus said control lever;
  • said first guide track which allows the control lever to be continuously moved from said predetermined rearward position to continuously control the thrust reversal regime; and
  • said second guide track, for the forward movement of the control lever, which has a plurality of notches capable of receiving said guide means so as to allow the control lever to take one of a plurality of positions different, each of said positions controlling a particular speed of advancement of said engine,
is remarkable in that it further comprises an auxiliary guide track enabling the control lever to be moved continuously from said predetermined forward position to continuously control the feed rate. of the motor.

Ainsi, grâce à ladite piste de guidage auxiliaire, le régime d'avancement du moteur peut être commandé de façon continue, ce qui permet d'obtenir une manette de gaz très sensible et ainsi de remédier aux inconvénients précités.Thus, thanks to said auxiliary guide track, the feed rate motor can be continuously controlled, which allows to obtain a very sensitive throttle and thus to remedy aforementioned drawbacks.

De plus, selon l'invention, ladite piste de guidage auxiliaire présente une plage de débattement qui est plus longue que la plage de débattement de ladite seconde piste de guidage. Ceci permet d'obtenir une très grande plage de commande du régime.In addition, according to the invention, said auxiliary guide track presents a range of travel that is longer than the range of travel of said second guide track. This allows to obtain a very large speed control range.

Bien entendu, grâce à la présence de ladite seconde piste de guidage comprenant des crans, on conserve l'avantage d'une gestion maítrisée pour un certain nombre de régimes particuliers.Of course, thanks to the presence of said second guide track with notches, the advantage of controlled management for a number of special plans.

De plus, comme grâce à l'invention les crans de ladite seconde piste de guidage ne sont plus gênants pour la sensibilité de la manette de gaz (obtenue grâce à ladite piste de guidage auxiliaire), on peut ajouter de nombreux crans dans ladite seconde piste de guidage, ce qui permet de faciliter la gestion d'un grand nombre de régimes particuliers. In addition, as thanks to the invention the notches of said second guide track are no longer troublesome for the sensitivity of the joystick gas (obtained by means of said auxiliary guide track), it is possible to add many notches in said second guide track, which allows facilitate the management of a large number of specific plans.

Ainsi, de façon avantageuse, ladite seconde piste de guidage comporte une pluralité de crans permettant de commander au moins certains des régimes suivants :

  • le régime de décollage/remise des gaz ;
  • le régime de ralenti en vol ;
  • le régime de ralenti au sol ;
  • le régime de croisière rapide ;
  • le régime de croisière ;
  • le régime de montée ; et
  • le régime correspondant à la perte d'un moteur.
Thus, advantageously, said second guide track comprises a plurality of notches for controlling at least some of the following regimes:
  • the take-off / go-around regime;
  • the idling speed in flight;
  • ground idle speed;
  • the fast cruising regime;
  • the cruise regime;
  • climbing regime; and
  • the regime corresponding to the loss of an engine.

Dans un mode de réalisation particulier :

  • ladite manette de gaz comporte, de plus, une première piste de raccord entre ladite seconde piste de guidage et ladite piste de guidage auxiliaire, et cette première piste de raccord est située au niveau d'un cran de ladite seconde piste de guidage, permettant de commander le régime de ralenti en vol ; et/ou
  • ladite manette de gaz comporte, de plus, une seconde piste de raccord entre ladite seconde piste de guidage et ladite piste de guidage auxiliaire, et cette seconde piste de raccord est située au niveau d'un cran de ladite seconde piste de guidage, permettant de commander le régime de croisière ; et/ou
  • ledit moyen de guidage comporte une cheville qui est susceptible de se déplacer dans des évidements longitudinaux coopérants formant respectivement lesdites pistes de guidage.
In a particular embodiment:
  • said throttle lever further includes a first coupling track between said second guide track and said auxiliary guide track, and said first coupling track is located at a notch of said second guide track, allowing control the idling speed in flight; and or
  • said throttle lever further includes a second splice track between said second guide track and said auxiliary guide track, and said second splice track is located at a notch of said second guide track, allowing control the cruise regime; and or
  • said guide means comprises a pin which is capable of moving in cooperating longitudinal recesses respectively forming said guide tracks.

Les figures du dessin annexé feront bien comprendre comment l'invention peut être réalisée. Sur ces figures, des références identiques désignent des éléments semblables.The figures of the annexed drawing will make clear how the invention can be realized. In these figures, identical references designate similar elements.

La figure 1 montre schématiquement une manette de gaz conforme à l'invention. Figure 1 schematically shows a throttle according to the invention.

Les figures 2 à 12 montrent différentes positions de commande du régime pour la manette de gaz de la figure 1.Figures 2 to 12 show different control positions of the regime for the throttle lever of Figure 1.

La manette de gaz 1 conforme à l'invention et représentée schématiquement sur les figures 1 à 12 est destinée à commander le régime d'au moins un moteur d'un aéronef, en particulier d'un avion de transport militaire.The throttle 1 according to the invention and shown schematically in FIGS. 1 to 12 is intended to control the at least one engine of an aircraft, in particular a transport aircraft military.

Bien que non exclusivement, ladite manette de gaz 1 s'applique plus particulièrement à la commande d'un turbopropulseur, c'est-à-dire d'un moteur comportant une turbine à gaz entraínant une ou plusieurs hélices par l'intermédiaire d'un réducteur.Although not exclusively, said throttle lever 1 applies more particularly to the control of a turboprop, that is to say an engine comprising a gas turbine driving one or more propellers via a reducer.

Ladite manette de gaz 1 est du type comportant :

  • un levier de commande 2 manuel usuel, qui est susceptible d'être basculé (autour d'un pivot 2A fixe) de part et d'autre d'une position prédéterminée PO respectivement vers l'avant (dans les deux sens illustrés par une double flèche A) et vers l'arrière (dans les deux sens illustrés par une double flèche B), sous une action manuelle d'un pilote de l'aéronef. Ledit levier de commande 2 comporte un moyen de guidage 3 (comprenant de préférence une cheville 4 précisée ci-dessous) solidaire dudit levier de commande 2 et susceptible de coopérer avec au moins des première et seconde pistes de guidage 5 et 6 concentriques qui limitent les déplacements dudit moyen de guidage 3 et ainsi dudit levier de commande 2 ;
  • ladite piste de guidage 5 qui permet au levier de commande 2 d'être déplacé de façon continue à partir de ladite position prédéterminée PO vers l'arrière (flèche B), pour commander de façon continue le régime en inversion de poussée ; et
  • ladite piste de guidage 6, pour le déplacement vers l'avant (flèche A) du levier de commande 2, qui comporte une pluralité de crans 7 susceptibles de recevoir ledit moyen de guidage 3 en présentant une forme adaptée de manière à permettre au levier de commande 2 de prendre l'une d'une pluralité de positions (angulaires) différentes P1, P2, P3, PA. Chacune desdites positions (angulaires) P1, P2, P3, PA commande un régime particulier d'avancement dudit moteur. Dans ce cas, le déplacement vers l'avant du levier de commande 2 n'est pas continu, mais est interrompu à chaque cran 7, chacun desdits crans 7 étant susceptible de maintenir en position ledit levier de commande 2.
Said gas lever 1 is of the type comprising:
  • a conventional manual control lever 2, which can be tilted (about a fixed pivot 2A) on either side of a predetermined position PO respectively forward (in both directions illustrated by a double arrow A) and towards the rear (in both directions illustrated by a double arrow B), under a manual action of a pilot of the aircraft. Said control lever 2 comprises a guiding means 3 (preferably comprising a pin 4 specified below) integral with said control lever 2 and capable of cooperating with at least first and second concentric guide tracks 5 and 6 which limit the displacements of said guide means 3 and thus of said control lever 2;
  • said guide track 5 which allows the control lever 2 to be moved continuously from said predetermined position PO rearwards (arrow B) to continuously control the thrust reversal regime; and
  • said guide track 6, for the forward movement (arrow A) of the control lever 2, which comprises a plurality of notches 7 capable of receiving said guide means 3 having a shape adapted to allow the lever of command 2 to take one of a plurality of different (angular) positions P1, P2, P3, PA. Each of said (angular) positions P1, P2, P3, PA controls a particular speed of advancement of said motor. In this case, the forward movement of the control lever 2 is not continuous, but is interrupted at each notch 7, each of said notches 7 being capable of holding said control lever 2 in position.

Selon l'invention, ladite manette de gaz 1 comporte, de plus, une piste de guidage auxiliaire 8 concentrique, permettant au levier de commande 2 d'être déplacé de façon continue, à partir de ladite position prédéterminée PO vers l'avant (flèche A), pour commander de façon continue le régime d'avancement du moteur. Cette piste de guidage auxiliaire 8 ne comporte donc pas d'obstacles (crans, ...) qui perturbent le déplacement du levier de commande 2.According to the invention, said throttle lever 1 further comprises a 8 concentric auxiliary guide track, allowing the lever to command 2 to be moved continuously from said position predetermined PO forward (arrow A), to control continuously the speed of the engine. This auxiliary guide track 8 does not have any obstacles (notches, ...) that disrupt the movement of the control lever 2.

Grâce à cette piste de guidage auxiliaire 8, le régime d'avancement du moteur peut donc être commandé de façon continue, ce qui permet d'obtenir une manette de gaz 1 très sensible, présentant un maniement très souple, pour le régime d'avancement.With this auxiliary guide track 8, the feed rate motor can be controlled continuously, allowing to obtain a very sensitive gas handgrip 1, having a handling very flexible, for the advancement scheme.

De plus, selon l'invention, ladite piste de guidage auxiliaire 8 présente une plage de débattement qui est plus longue que la plage de débattement de ladite piste de guidage 6. La manette de gaz 1 présente ainsi une très grande plage de commande en continu du régime d'avancement.In addition, according to the invention, said auxiliary guide track 8 presents a range of travel that is longer than the range of travel of said guide track 6. The throttle lever 1 thus presents a very large continuous control range of the forward speed.

Par conséquent, grâce à l'invention, on combine en vol d'avancement les avantages d'une commande continue (piste de guidage auxiliaire 8) et d'une commande par paliers (crans 7 de la piste de guidage 6), à savoir respectivement :

  • une grande sensibilité ; et
  • une gestion maítrisée de régimes particuliers.
Therefore, thanks to the invention, the advantages of a continuous control (auxiliary guide track 8) and a stepwise control (notches 7 of the guide track 6) are combined in forward flight, namely respectively :
  • a great sensitivity; and
  • controlled management of special plans.

A cet effet, ladite manette de gaz 1 comporte, de plus, au moins une piste de raccord 9, 10 qui permet au moyen de guidage 3 de passer de la piste de guidage 6 à la piste de guidage auxiliaire 8, et inversement. Pour ce faire, dans un mode de réalisation préféré, la cheville 4 dudit moyen de guidage 3 est susceptible de se déplacer dans des évidements longitudinaux coopérants, de taille appropriée, formant respectivement lesdites pistes de guidage 5, 6 et 8 et lesdites pistes de raccord 9 et 10.For this purpose, said throttle lever 1 comprises, in addition, at least a connecting track 9, 10 which allows the guiding means 3 to pass from the guide track 6 to the auxiliary guide track 8, and vice versa. For this purpose, in a preferred embodiment, the pin 4 of said guide means 3 is able to move in recesses cooperating longitudinal members of appropriate size, respectively said guide tracks 5, 6 and 8 and said connecting tracks 9 and 10.

Dans un mode de réalisation particulier, la manette de gaz 1 comporte deux pistes de raccord 9 et 10, ce qui permet de doubler la possibilité de raccordement.In a particular embodiment, the throttle 1 comprises two connecting tracks 9 and 10, which makes it possible to double the possibility of connection.

De plus :

  • ladite piste de raccord 9 est agencée au niveau d'un cran 7 permettant de commander, avec une position associée P1 du levier de commande 2, le régime de ralenti en vol ; et
  • ladite piste de raccord 10 est agencée au niveau d'un cran 7 permettant de commander, avec une position associée P2 du levier de commande 2, le régime de croisière.
Moreover :
  • said connecting track 9 is arranged at a notch 7 for controlling, with an associated position P1 of the control lever 2, the idle speed in flight; and
  • said connecting track 10 is arranged at a notch 7 for controlling, with an associated position P2 of the control lever 2, the cruising speed.

Comme grâce à l'invention les crans 7 de ladite piste de guidage 6 ne sont plus gênants pour la sensibilité de la manette de gaz 1 (obtenue grâce à ladite piste de guidage auxiliaire 8), on peut ajouter de nombreux crans 7 dans ladite piste de guidage 6, ce qui permet de faciliter la gestion d'un grand nombre de régimes particuliers.As thanks to the invention the notches 7 of said guide track 6 are no longer troublesome for the sensitivity of the throttle lever 1 (obtained thanks to said auxiliary guide track 8), it is possible to add numerous notches 7 in said guide track 6, which facilitates the management of a large number of special regimes.

Ainsi, dans un mode de réalisation particulier, ladite piste de guidage 6 comporteune pluralité de crans 7 permettant de commander au moins certains des régimes suivants :

  • le régime de décollage / remise des gaz ;
  • le régime de ralenti en vol ;
  • le régime de ralenti au sol ;
  • le régime de croisière rapide ;
  • le régime de croisière ;
  • le régime de montée ; et
  • le régime correspondant à la perte d'un moteur.
Thus, in a particular embodiment, said guide track 6 comprisesa plurality of notches 7 for controlling at least some of the following regimes:
  • the take-off / go-around regime;
  • the idling speed in flight;
  • ground idle speed;
  • the fast cruising regime;
  • the cruise regime;
  • climbing regime; and
  • the regime corresponding to the loss of an engine.

Sur les figures 2 à 12, on présente différentes positions de la manette de gaz 1, permettant de mettre en évidence tous les avantages de cette dernière.Figures 2 to 12 show different positions of the joystick of gas 1, to highlight all the advantages of the latter.

Sur les figures 2 et 3, la manette de gaz 1 se trouve dans des positions permettant de commander le régime de ralenti en vol. Dans la position de la figure 2, le moyen de guidage 3 est en face d'une piste de raccord 11 raccordée aux pistes de guidage 6 et 8, alors que dans la position de la figure 3, il se trouve en face de la piste de guidage 5. Pour passer de la position de la figure 2 à celle de la figure 3, il convient de tirer le levier de commande 2 vers le haut, comme illustré par une flèche C. Pour ce faire, ledit levier de commande 2 comporte un évidement 12 en fuseau, qui reçoit ledit pivot fixe 2A.In FIGS. 2 and 3, the throttle lever 1 is in positions to control idle speed in flight. In the position of Figure 2, the guide means 3 is in front of a connecting track 11 connected to the guide tracks 6 and 8, while in the position of Figure 3, it is in front of the guide track 5. To go from the position of Figure 2 to that of Figure 3, it is appropriate to pull the lever command 2 upwards, as shown by an arrow C. For this to do, said control lever 2 comprises a recess 12 in a spindle, which receives said fixed pivot 2A.

A partir de la position de la figure 3, le levier de commande 2 peut être déplacé en continu vers l'arrière (flèche B), comme représenté sur la figure 4, pour commander en continu le régime en inversion de poussée.From the position of FIG. 3, the control lever 2 can be moved continuously backward (arrow B), as shown on the Figure 4, to continuously control the reverse thrust regime.

Sur les figures 5 et 6, la manette de gaz 1 se trouve dans des positions permettant de commander le régime de ralenti au sol (position angulaire P1 du levier de commande 2). Dans la position de la figure 5, le moyen de guidage 3 est en face de la piste de raccord 11, alors que dans la position de la figure 6, il se trouve en face de la piste de guidage 6. Pour passer de la position de la figure 5 à celle de la figure 6, il convient de pousser le levier de commande 2 vers le bas le long de la piste de raccord 9, comme illustré par une flèche D.In FIGS. 5 and 6, the throttle lever 1 is in positions for controlling the idle speed on the ground (angular position P1 of the control lever 2). In the position of Figure 5, the guide means 3 is in front of the connecting track 11, whereas in the position of Figure 6, it is in front of the guide track 6. To move from the position of Figure 5 to that of Figure 6, it is necessary to push the control lever 2 down along the connecting track 9, as illustrated by an arrow D.

A partir de la position de la figure 6, le levier de commande 2 peut être déplacé par paliers vers l'avant, comme représenté sur les figures 7 à 9. La figure 7 correspond à la figure 6, et les figures 8 et 9 représentent la commande de régimes particuliers définis par des crans 7 particuliers de la piste de guidage 6.From the position of Figure 6, the control lever 2 can to be moved in steps forward, as shown in Figures 7 to 9. Figure 7 corresponds to Figure 6, and Figures 8 and 9 show the control of particular regimes defined by special notches 7 of the guide track 6.

Sur la figure 10, le levier de commande 2 se trouve à la position P2 (correspondant à un cran 7 sur la piste de guidage 6 pour la cheville 4) permettant de commander le régime de croisière. De cette position, le levier de commande 2 peut être déplacé dans la position de la figure 11 en tirant sur ce dernier, comme illustré par une flèche E de sorte que la cheville 4 se déplace le long de la piste de raccord 10 pour rejoindre la piste de guidage auxiliaire 8. A partir de cette dernière position, le levier de commande 2 peut être déplacé de façon continue vers l'avant pour commander de façon continue le régime d'avancement, comme représenté sur la figure 12.In FIG. 10, the control lever 2 is in the position P2 (corresponding to a notch 7 on the guide track 6 for the ankle 4) to control the cruising speed. From this position, the lever 2 can be moved to the position of FIG. pulling on the latter, as illustrated by an arrow E so that the ankle 4 moves along runway 10 to rejoin the runway 8. From this last position, the lever of command 2 can be moved continuously forward for continuously control the advancement regime, as shown in Figure 12.

Claims (7)

Manette de gaz pour commander le régime d'au moins un moteur d'un aéronef, ladite manette de gaz (1) comportant : un levier de commande (2) qui est susceptible d'être basculé de part et d'autre d'une position prédéterminée (PO) respectivement vers l'avant et vers l'arrière, sous une action manuelle d'un pilote de l'aéronef, et qui comporte un moyen de guidage (3) solidaire dudit levier de commande (2) et susceptible de coopérer avec au moins une première et une seconde pistes de guidage (5, 6) qui limitent les déplacements dudit moyen de guidage (3) et ainsi dudit levier de commande (2) ; ladite première piste de guidage (5) qui permet au levier de commande (2) d'être déplacé de façon continue à partir de ladite position prédéterminée (PO) vers l'arrière, pour commander de façon continue le régime en inversion de poussée ; et ladite seconde piste de guidage (6), pour le déplacement vers l'avant du levier de commande, qui comporte une pluralité de crans (7) susceptibles de recevoir ledit moyen de guidage (3) de manière à permettre au levier de commande (2) de prendre l'une d'une pluralité de positions différentes, chacune desdites positions commandant un régime particulier d'avancement dudit moteur, caractérisée en ce qu'elle comporte, de plus, une piste de guidage auxiliaire (8) permettant au levier de commande (2) d'être déplacé de façon continue à partir de ladite position prédéterminée (PO) vers l'avant, pour commander de façon continue le régime d'avancement du moteur.A throttle lever for controlling the speed of at least one engine of an aircraft, said throttle (1) comprising: a control lever (2) which can be tilted on either side of a predetermined position (PO) respectively forward and backward, under manual action of a pilot of the aircraft, and which comprises a guiding means (3) integral with said control lever (2) and capable of cooperating with at least a first and a second guide tracks (5, 6) which limit the displacements of said guiding means (3). ) and thus said control lever (2); said first guide track (5) which allows the control lever (2) to be continuously moved from said predetermined position (PO) rearwardly to continuously control the thrust reversal regime; and said second guide track (6), for the forward movement of the control lever, which has a plurality of notches (7) capable of receiving said guide means (3) so as to allow the control lever (2 ) to take one of a plurality of different positions, each of said positions controlling a particular speed of advancement of said engine, characterized in that it further comprises an auxiliary guide track (8) enabling the control lever (2) to be moved continuously from said predetermined position (PO) forwards to control continuously the engine speed. Manette de gaz selon la revendication 1,
caractérisée en ce que ladite piste de guidage auxiliaire (8) présente une plage de débattement qui est plus longue que la plage de débattement de ladite seconde piste de guidage (6). Gas throttle according to claim 1,
characterized in that said auxiliary guide track (8) has a range of deflection which is longer than the range of travel of said second guide track (6). Manette de gaz selon l'une des revendications 1 et 2,
caractérisée en ce que ladite seconde piste de guidage (6) comporteune pluralité de crans (7) permettant de commander au moins certains des régimes suivants : le régime de décollage / remise des gaz ; le régime de ralenti en vol ; le régime de ralenti au sol ; le régime de croisière rapide ; le régime de croisière ; le régime de montée ; et le régime correspondant à la perte d'un moteur. Throttle lever according to one of claims 1 and 2,
characterized in that said second guide track (6) hasa plurality of notches (7) for controlling at least some of the following regimes: the take-off / go-around regime; the idling speed in flight; ground idle speed; the fast cruising regime; the cruise regime; climbing regime; and the regime corresponding to the loss of an engine. Manette de gaz selon l'une quelconque des revendications précédentes,
caractérisée en ce qu'elle comporte, de plus, une première piste de raccord (9) entre ladite seconde piste de guidage (6) et ladite piste de guidage auxiliaire (8), et en ce que cette première piste de raccord (9) est située au niveau d'un cran (7) de ladite seconde piste de guidage (6), permettant de commander le régime de ralenti en vol.Gas throttle according to one of the preceding claims,
characterized in that it further comprises a first connection track (9) between said second guide track (6) and said auxiliary guide track (8), and in that said first connection track (9) is located at a notch (7) of said second guide track (6) for controlling the idling speed in flight. Manette de gaz selon l'une quelconque des revendications précédentes,
caractérisée en ce qu'elle comporte, de plus, une seconde piste de raccord (10) entre ladite seconde piste de guidage (6) et ladite piste de guidage auxiliaire (8), et en ce que cette seconde piste de raccord (10) est située au niveau d'un cran (7) de ladite seconde piste de guidage (6), permettant de commander le régime de croisière.Gas throttle according to one of the preceding claims,
characterized in that it further comprises a second connecting track (10) between said second guide track (6) and said auxiliary guide track (8), and in that said second connecting track (10). is located at a notch (7) of said second guide track (6) for controlling the cruising speed. Manette de gaz selon l'une quelconque des revendications précédentes,
caractérisée en ce que ledit moyen de guidage (3) comporte une cheville (4) qui est susceptible de se déplacer dans des évidements longitudinaux coopérants formant respectivement lesdites pistes de guidage (5, 6, 8).Gas throttle according to one of the preceding claims,
characterized in that said guide means (3) comprises a pin (4) which is capable of moving in cooperating longitudinal recesses respectively forming said guide tracks (5, 6, 8). Aéronef,
caractérisé en ce qu'il comporte une manette de gaz (1) telle que celle spécifiée sous l'une quelconque des revendications 1 à 6.Aircraft,
characterized in that it comprises a throttle lever (1) as specified in any one of claims 1 to 6.
EP05290676A 2004-04-21 2005-03-29 Throttle lever for controlling the operation of at least one engine of an aircraft Not-in-force EP1588942B1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR0404206A FR2869291B1 (en) 2004-04-21 2004-04-21 GAS LEVER FOR CONTROLLING THE REGIME OF AT LEAST ONE ENGINE OF AN AIRCRAFT
FR0404206 2004-04-21

Publications (2)

Publication Number Publication Date
EP1588942A1 true EP1588942A1 (en) 2005-10-26
EP1588942B1 EP1588942B1 (en) 2006-08-09

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ID=34942040

Family Applications (1)

Application Number Title Priority Date Filing Date
EP05290676A Not-in-force EP1588942B1 (en) 2004-04-21 2005-03-29 Throttle lever for controlling the operation of at least one engine of an aircraft

Country Status (7)

Country Link
US (1) US7143984B2 (en)
EP (1) EP1588942B1 (en)
AT (1) ATE335658T1 (en)
CA (1) CA2502501C (en)
DE (1) DE602005000065T2 (en)
ES (1) ES2268678T3 (en)
FR (1) FR2869291B1 (en)

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WO2009053753A1 (en) * 2007-10-24 2009-04-30 English Welsh & Scottish Railway Holdings Limited A locomotive power throttle with limiter
FR2946017A1 (en) * 2009-05-29 2010-12-03 Airbus France SYSTEM FOR CONTROLLING AT LEAST ONE AIRCRAFT AND AIRCRAFT ENGINE COMPRISING SUCH A CONTROL SYSTEM
FR2946016A1 (en) * 2009-05-29 2010-12-03 Airbus France SYSTEM FOR CONTROLLING AT LEAST ONE AIRCRAFT AND AIRCRAFT ENGINE COMPRISING SUCH A CONTROL SYSTEM
FR2950862A1 (en) * 2009-10-06 2011-04-08 Sagem Defense Securite DEVICE FOR CONTROLLING GASES OF AN AIRCRAFT, INCORPORATING A CONNECTION BY CAMS
CN105035331A (en) * 2015-08-18 2015-11-11 江西洪都航空工业集团有限责任公司 Soft trainer engine control system clutch device

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US7793890B2 (en) * 2007-01-31 2010-09-14 Patrick L. Scherer Control system for an aircraft
US8235330B2 (en) * 2008-03-12 2012-08-07 Usercentrix, Llc Rotational aircraft throttle interface
US9043050B2 (en) * 2008-08-13 2015-05-26 The Boeing Company Programmable reverse thrust detent system and method
FR2950861B1 (en) * 2009-10-06 2011-10-28 Sagem Defense Securite DEVICE FOR CONTROLLING THE GASES OF AN AIRCRAFT, INCORPORATING A CONNECTION WITH CRANKING GALET
CN111846250B (en) * 2020-07-23 2022-02-22 中国商用飞机有限责任公司 Method and system for controlling speed and attitude modes of an aircraft
CN112623234B (en) * 2020-12-29 2022-10-28 中国航空工业集团公司西安飞机设计研究所 Mechanical interlocking protection device of double-rod-shaped throttle platform of turboprop aircraft

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Publication number Priority date Publication date Assignee Title
WO2009053753A1 (en) * 2007-10-24 2009-04-30 English Welsh & Scottish Railway Holdings Limited A locomotive power throttle with limiter
FR2946017A1 (en) * 2009-05-29 2010-12-03 Airbus France SYSTEM FOR CONTROLLING AT LEAST ONE AIRCRAFT AND AIRCRAFT ENGINE COMPRISING SUCH A CONTROL SYSTEM
FR2946016A1 (en) * 2009-05-29 2010-12-03 Airbus France SYSTEM FOR CONTROLLING AT LEAST ONE AIRCRAFT AND AIRCRAFT ENGINE COMPRISING SUCH A CONTROL SYSTEM
FR2950862A1 (en) * 2009-10-06 2011-04-08 Sagem Defense Securite DEVICE FOR CONTROLLING GASES OF AN AIRCRAFT, INCORPORATING A CONNECTION BY CAMS
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CN105035331A (en) * 2015-08-18 2015-11-11 江西洪都航空工业集团有限责任公司 Soft trainer engine control system clutch device

Also Published As

Publication number Publication date
EP1588942B1 (en) 2006-08-09
ATE335658T1 (en) 2006-09-15
DE602005000065D1 (en) 2006-09-21
FR2869291B1 (en) 2006-06-30
US20050236525A1 (en) 2005-10-27
FR2869291A1 (en) 2005-10-28
US7143984B2 (en) 2006-12-05
ES2268678T3 (en) 2007-03-16
CA2502501C (en) 2012-01-03
CA2502501A1 (en) 2005-10-21
DE602005000065T2 (en) 2007-01-11

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