EP1588942A1 - Schubhebel zur Steuerung des Betriebs von mindestens einem Triebwerk eines Flugzeugs - Google Patents

Schubhebel zur Steuerung des Betriebs von mindestens einem Triebwerk eines Flugzeugs 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
Authority
EP
European Patent Office
Prior art keywords
guide track
track
control lever
lever
regime
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Granted
Application number
EP05290676A
Other languages
English (en)
French (fr)
Other versions
EP1588942B1 (de
Inventor
Dany Marjanski
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Airbus Operations SAS
Original Assignee
Airbus Operations SAS
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Airbus Operations SAS filed Critical Airbus Operations SAS
Publication of EP1588942A1 publication Critical patent/EP1588942A1/de
Application granted granted Critical
Publication of EP1588942B1 publication Critical patent/EP1588942B1/de
Not-in-force legal-status Critical Current
Anticipated expiration legal-status Critical

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Classifications

    • 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

Definitions

  • the present invention relates to a throttle lever for controlling the speed of at least one engine of an aircraft.
  • 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.
  • the presence of said notches allows a controlled management of certain particular engine speeds, such as the take-off / gas for example.
  • 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.
  • the present invention relates to a throttle lever for remedy these disadvantages.
  • the feed rate motor can be continuously controlled, which allows to obtain a very sensitive throttle and thus to remedy aforementioned drawbacks.
  • 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.
  • 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.
  • FIG. 1 schematically shows a throttle according to the invention.
  • FIGS 2 to 12 show different control positions of the regime for the throttle lever of Figure 1.
  • 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.
  • 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.
  • 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.
  • 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.
  • 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.
  • 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.
  • 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.
  • the throttle 1 comprises two connecting tracks 9 and 10, which makes it possible to double the possibility of connection.
  • 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.
  • FIGS 2 to 12 show different positions of the joystick of gas 1, to highlight all the advantages of the latter.
  • the throttle lever 1 is in positions to control idle speed in flight.
  • 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.
  • said control lever 2 comprises a recess 12 in a spindle, which receives said fixed pivot 2A.
  • control lever 2 can be moved continuously backward (arrow B), as shown on the Figure 4, to continuously control the reverse thrust regime.
  • the throttle lever 1 is in positions for controlling the idle speed on the ground (angular position P1 of the control lever 2).
  • the guide means 3 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.
  • 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.
  • 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.

Landscapes

  • 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)
  • Mechanical Control Devices (AREA)
  • Control Of Vehicle Engines Or Engines For Specific Uses (AREA)
  • Output Control And Ontrol Of Special Type Engine (AREA)
EP05290676A 2004-04-21 2005-03-29 Schubhebel zur Steuerung des Betriebs von mindestens einem Triebwerk eines Flugzeugs Not-in-force EP1588942B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR0404206A FR2869291B1 (fr) 2004-04-21 2004-04-21 Manette de gaz pour commander le regime d'au moins un moteur d'un aeronef
FR0404206 2004-04-21

Publications (2)

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

Family

ID=34942040

Family Applications (1)

Application Number Title Priority Date Filing Date
EP05290676A Not-in-force EP1588942B1 (de) 2004-04-21 2005-03-29 Schubhebel zur Steuerung des Betriebs von mindestens einem Triebwerk eines Flugzeugs

Country Status (7)

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

Cited By (5)

* Cited by examiner, † Cited by third party
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 (fr) * 2009-05-29 2010-12-03 Airbus France Systeme pour la commande d'au moins un moteur d'aeronef et aeronef comportant un tel systeme de commande.
FR2946016A1 (fr) * 2009-05-29 2010-12-03 Airbus France Systeme pour la commande d'au moins un moteur d'aeronef et aeronef comportant un tel systeme de commande.
FR2950862A1 (fr) * 2009-10-06 2011-04-08 Sagem Defense Securite Dispositif de commande des gaz d'un aeronef, incorporant une liaison par cames
CN105035331A (zh) * 2015-08-18 2015-11-11 江西洪都航空工业集团有限责任公司 一种软式教练机发动机操纵系统离合装置

Families Citing this family (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
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 (fr) * 2009-10-06 2011-10-28 Sagem Defense Securite Dispositif de commande des gaz d'un aeronef, incorporant une liaison par galet cranteur
CN111846250B (zh) * 2020-07-23 2022-02-22 中国商用飞机有限责任公司 用于控制飞机的航速和姿态模式的方法及系统
CN112623234B (zh) * 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 一种涡桨飞机双杆形式油门台的机械互锁保护装置

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2789418A (en) * 1950-09-20 1957-04-23 Bendix Aviat Corp Single lever controlled starting and power control device for an aircraft engine
US2865171A (en) * 1954-08-25 1958-12-23 Gen Motors Corp Engine governor setting mechanism
US2901919A (en) * 1954-09-07 1959-09-01 Republic Aviat Corp Engine throttle
US2945347A (en) * 1955-12-13 1960-07-19 Rolls Royce Fuel control
US4651954A (en) * 1984-11-19 1987-03-24 Lockheed Corporation Autothrottle system
EP0431655A2 (de) * 1989-12-04 1991-06-12 The Boeing Company Gassteuerungssystem mit in Echtzeit gerechnetem Schub in Abhängigkeit von der Gassteuerungsposition

Family Cites Families (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2417691A (en) * 1943-06-03 1947-03-18 United Aircraft Corp Aircraft flight control
US2999355A (en) * 1957-12-03 1961-09-12 Martin Co Control apparatus for aircraft having thrust reversing means
US2967436A (en) * 1959-03-04 1961-01-10 Eric J Steinlein Throttle and clutch control head
WO1984001446A1 (en) * 1982-09-30 1984-04-12 Boeing Co Modular multi-engine thrust control assembly

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2789418A (en) * 1950-09-20 1957-04-23 Bendix Aviat Corp Single lever controlled starting and power control device for an aircraft engine
US2865171A (en) * 1954-08-25 1958-12-23 Gen Motors Corp Engine governor setting mechanism
US2901919A (en) * 1954-09-07 1959-09-01 Republic Aviat Corp Engine throttle
US2945347A (en) * 1955-12-13 1960-07-19 Rolls Royce Fuel control
US4651954A (en) * 1984-11-19 1987-03-24 Lockheed Corporation Autothrottle system
EP0431655A2 (de) * 1989-12-04 1991-06-12 The Boeing Company Gassteuerungssystem mit in Echtzeit gerechnetem Schub in Abhängigkeit von der Gassteuerungsposition

Cited By (8)

* Cited by examiner, † Cited by third party
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 (fr) * 2009-05-29 2010-12-03 Airbus France Systeme pour la commande d'au moins un moteur d'aeronef et aeronef comportant un tel systeme de commande.
FR2946016A1 (fr) * 2009-05-29 2010-12-03 Airbus France Systeme pour la commande d'au moins un moteur d'aeronef et aeronef comportant un tel systeme de commande.
FR2950862A1 (fr) * 2009-10-06 2011-04-08 Sagem Defense Securite Dispositif de commande des gaz d'un aeronef, incorporant une liaison par cames
WO2011042147A1 (fr) * 2009-10-06 2011-04-14 Sagem Defense Securite Dispositif de commande des gaz d'un aeronef, incorporant une liaison par cames
CN102574585A (zh) * 2009-10-06 2012-07-11 萨甘安全防护公司 包括凸轮联接的飞机油门控制装置
CN102574585B (zh) * 2009-10-06 2014-12-03 萨甘安全防护公司 包括凸轮联接的飞机油门控制装置
CN105035331A (zh) * 2015-08-18 2015-11-11 江西洪都航空工业集团有限责任公司 一种软式教练机发动机操纵系统离合装置

Also Published As

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

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