WO1992007756A1 - Dispositif d'amortissement du levier de commande d'un avion - Google Patents

Dispositif d'amortissement du levier de commande d'un avion Download PDF

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Publication number
WO1992007756A1
WO1992007756A1 PCT/SE1991/000679 SE9100679W WO9207756A1 WO 1992007756 A1 WO1992007756 A1 WO 1992007756A1 SE 9100679 W SE9100679 W SE 9100679W WO 9207756 A1 WO9207756 A1 WO 9207756A1
Authority
WO
WIPO (PCT)
Prior art keywords
damping
shaft
resistance
control stick
rotational
Prior art date
Application number
PCT/SE1991/000679
Other languages
English (en)
Inventor
Ragnar Haglund
Original Assignee
Saab-Scania Aktiebolag
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 Saab-Scania Aktiebolag filed Critical Saab-Scania Aktiebolag
Publication of WO1992007756A1 publication Critical patent/WO1992007756A1/fr

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Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C13/00—Control systems or transmitting systems for actuating flying-control surfaces, lift-increasing flaps, air brakes, or spoilers
    • B64C13/02—Initiating means

Definitions

  • T.F.VT F FOR DAMPING THE CONTROL STICK OF AN AIRCRAFT
  • the present invention relates to a device for damping the con ⁇ trol stick of an aircraft, whose movements in pitch and roll, respectively, are transferred to a rotatable shaft, with a damping means for damping its rotational movement.
  • U.S. 2,523,579 describes a con ⁇ trol system comprising a wheel, corresponding to a control stick, which via links acts upon an inwardly extending shaft to a differential gear, whose outwardly extending shafts, via links, control two control surfaces.
  • the rotational movement of the inwardly extending shaft is damped by damping pistons with springs.
  • U.S. 2,695,145 a somewhat complex system is shown for transferring the movement in a control stick to two control surfaces, which comprises springs that counteract the stick movement.
  • the object of the present invention is therefore to provide a device of the kind mentioned in the introduction, which is simple in construction, and yet is reliable and, with a high degree of probability, allows a rotational movement by the rotatable shaft with damping, even if the damping means should show disturbed function.
  • the device of the kind mentioned in the introduction is characterized primarily by a differential gear with said shaft as an inwardly extending shaft, and a l:st and a 2:nd outwardly extending shaft, standing in mecha ⁇ nical rotational connection with the the l:st and 2:nd damping elements, respectively, of the damping means in the form of short-circuited electric motors .
  • the differential gear can be designed in many ways, with conical or cylindric gear wheels.
  • the l:st and 2:nd outwardly extending shafts are provided with equally large gear wheels in mesh with the differential gear wheels, which are of the same size in all constructions, the l:st and 2:nd outwardly extending shafts, respectively, will rotate with the same rotation speed, as long as both shafts are exposed to similar moment against ro ⁇ tation, at a certain rotation speed on the inwardly extending shaft.
  • variable resis- tance e.g. in the form of a potentiometer, is included in the short-circuiting circuits of the electric motors, so that the load on the motors, and thereby the moment they exert against a forced rotation, can be varied.
  • the mentioned motors show a linear relationship between the rotational speed and the moment against forced rotation.
  • the device comprises a unit, arranged to sense the potential drop over the respective resistance and at dif ⁇ ferences emit a signal to an indication means .
  • Said unit can also suitably be arranged so that on sensing the potential drop over the resistance at a predetermined value of the quo- tient between the respective potential drop and/or a certain relatively low threshold value for the potential drop on either resistance it connects one additional resistance in series with the other resistance, the additional resistance preferably being as great as the other resistance.
  • figure 1 shows a block diagram of a device according to the invention
  • figure 2 shows schematically a longitudinal section through a differential gear, included in a device according to the in ⁇ vention
  • figure 3 shows a block diagram of a part of an alternative de ⁇ vice according to the invention.
  • 1 designates a differential gear with an inwardly extending shaft 2, which stands in rotational connection with a control stick, in the figure schematically represented by a block 3 and a two-way arrow 4, which shows the possible move ⁇ ment patterns of the control stick.
  • the control stick is acted upon by a spring means 5, which works to return the control stick to a neutral position.
  • the position of the control stick is registered by a position indicator 6, which in a way not shown stands in connection with those means which are desira ⁇ ble to act upon with the rotational movement of the control stick. It can be e.g. the pitch or roll movements of an air ⁇ craft.
  • the differential gear is provided with a l:st outwardly extending shaft 7_, which via a l:st gear 8 stands in mechanic- al rotational connection with a l:st electric motor 9.
  • the differential gear 1 is also provided with a 2:nd outwardly ex ⁇ tending shaft 10, which via a 2:nd gear 11 stands in mechan ⁇ ical rotational connection with a 2:nd electric motor 12.
  • Each of the electric motors 9, 12 is short-circuited through short- circuiting circuits 13, 14 in which variable resistances 15, 16 are included. In one embodiment the motors can also be short-circuited in series.
  • the electric motors can be of different construction, but it is suitable to use motors provided with permanent magnetic rotor and windings in the stator, so that slip-rings or the like are avoided.
  • motors provided with permanent magnetic rotor and windings in the stator, so that slip-rings or the like are avoided.
  • said motors show a linear relationship between the rotational speed on the shaft of the motors and the appearing moment against the forced rotation.
  • a differential gear 1 is shown in more detail.
  • the inwardly extending shaft 2 is rigidly connected with a diffe- rential case 17, in which the outwardly extending shafts 7 and 10 are mounted concentrically, provided with the conical gear wheels 18 and 19 having both the same number of teeths.
  • two conical differential gear wheels 20 and 21 are mounted, each in mesh with the afore-mentioned gear wheels 18 and 19. With this construction the inwardly and outwardly extending shafts will thus rotate with the same rotation speed, as long as both outwardly extending shafts are acted upon by- equally large moments, acting against the rotation.
  • the device functions according to the following. It is under ⁇ stood, that the motors exert a moment against forced rotation, which rises linearly with the rotation speed.
  • FIG 3 it is schematically shown how a unit 22 for monitoring and resistance compensation can be connected to the short-circuiting circuits 13, 14 partly to monitor and indicate if the damping means functions normally or if there is a disturbance in the form of biting, and partly to compensate the electric resistance so that damp ⁇ ing effected by a motor becomes the same as with two functiono ⁇ ning motors.
  • a unit 22 for monitoring and resistance compensation can be connected to the short-circuiting circuits 13, 14 partly to monitor and indicate if the damping means functions normally or if there is a disturbance in the form of biting, and partly to compensate the electric resistance so that damp ⁇ ing effected by a motor becomes the same as with two functio ⁇ ning motors.
  • Over the resistance 15 two cables 23, 24 are con ⁇ nected and over the resistance 16 correspondingly connected cables 25, 26.
  • the cables 23-26 leads to the unit 22, which is arranged, in a way not shown, to sense the potential drop over the respective resistances 15, 16 and compare them.
  • a warning signal is emitted to an indication means 27.
  • a breaker 28 has been included, which has two positions, a first one where the short-circuiting circuit 13 remains unbroken and a second one, where the resistance 15 is connected in series with one addi ⁇ tional variable resistance 29, the resistances 15 and 29 mainly being intended to be set on principally the same electric resistance.
  • the unit 22 controls the breaker 28 via a switching means 30, not shown in detail.
  • the short-circuiting circuit 14 has similarly been completed by a breaker 31 and a variable resistance 23, which is controlled correspondingly by the unit 22 via a switching means 33.
  • the unit 22 is now so arranged, that when the detection of the potential drop over the resistances 15 and 16 partly shows different values for the two resistances and partly shows a certain predetermined quotient value or alternatively a cer ⁇ tain low threshold value for one resistance, i.e. the resis ⁇ tance 15, the switching means 32 in this case resets the breaker 31, so that the resistance 33 is connected in series with the resistance 16.
  • the doubled rotation speed of the motor 12 is compensated by a doubled load resistance, which approximately gives an unchanged damping moment on the inwardly extending shaft 2 of the differential gear.
  • the measuring of the potential drop over the resistances 15 and 16 shows that disturbance has occurred in the damping function of the motor 12.

Landscapes

  • Engineering & Computer Science (AREA)
  • Automation & Control Theory (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Mechanical Control Devices (AREA)
  • Motor Power Transmission Devices (AREA)

Abstract

Un dispositif sert à amortir les mouvements du levier de commande d'un avion, dont les mouvements lors du tangage et des roulis, respectivement, sont transmis à un arbre rotatif pourvu d'un moyen d'amortissement servant à amortir son mouvement de rotation. Le dispositif est principalement caractérisé par un engrenage différentiel (1) comprenant ledit arbre (2) se présentant sous forme d'un arbre s'étendant vers l'intérieur, et un premier et un second arbre s'étendant vers l'extérieur (7, 10) respectivement, qui sont connectés de manière rotative et mécanique avec les premier et second éléments d'amortissement, lesquels se présentent sous la forme de moteurs électriques court-circuités (9, 12).
PCT/SE1991/000679 1990-10-30 1991-10-09 Dispositif d'amortissement du levier de commande d'un avion WO1992007756A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
SE9003450-5 1990-10-30
SE9003450A SE9003450D0 (sv) 1990-10-30 1990-10-30 Anordning vid en vridbar axel med daempningsorgan

Publications (1)

Publication Number Publication Date
WO1992007756A1 true WO1992007756A1 (fr) 1992-05-14

Family

ID=20380764

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/SE1991/000679 WO1992007756A1 (fr) 1990-10-30 1991-10-09 Dispositif d'amortissement du levier de commande d'un avion

Country Status (2)

Country Link
SE (1) SE9003450D0 (fr)
WO (1) WO1992007756A1 (fr)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2858967A1 (fr) * 2003-08-21 2005-02-25 Ratier Figeac Soc Dispositif de commande de vol a amortissement electrique
US8087619B2 (en) * 2008-07-30 2012-01-03 Honeywell International, Inc. Active control stick assembly including traction drive

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2523579A (en) * 1946-10-21 1950-09-26 Armstrong Whitworth Co Eng Control of aircraft
US2695145A (en) * 1950-05-04 1954-11-23 Lear Inc Boost control system
DE3201408C2 (fr) * 1982-01-19 1989-05-11 Siemens Ag, 1000 Berlin Und 8000 Muenchen, De

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2523579A (en) * 1946-10-21 1950-09-26 Armstrong Whitworth Co Eng Control of aircraft
US2695145A (en) * 1950-05-04 1954-11-23 Lear Inc Boost control system
DE3201408C2 (fr) * 1982-01-19 1989-05-11 Siemens Ag, 1000 Berlin Und 8000 Muenchen, De

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2858967A1 (fr) * 2003-08-21 2005-02-25 Ratier Figeac Soc Dispositif de commande de vol a amortissement electrique
US8087619B2 (en) * 2008-07-30 2012-01-03 Honeywell International, Inc. Active control stick assembly including traction drive

Also Published As

Publication number Publication date
SE9003450D0 (sv) 1990-10-30

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