WO1995012153A1 - Amortissement de la vitesse dependant de la position dans un dispositif de commande manuel actif - Google Patents

Amortissement de la vitesse dependant de la position dans un dispositif de commande manuel actif Download PDF

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Publication number
WO1995012153A1
WO1995012153A1 PCT/US1993/010459 US9310459W WO9512153A1 WO 1995012153 A1 WO1995012153 A1 WO 1995012153A1 US 9310459 W US9310459 W US 9310459W WO 9512153 A1 WO9512153 A1 WO 9512153A1
Authority
WO
WIPO (PCT)
Prior art keywords
signal
control
dampening
motor
switch
Prior art date
Application number
PCT/US1993/010459
Other languages
English (en)
Inventor
William W. Gregory
James W. Kauffman
Original Assignee
Honeywell Inc.
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
Priority to US07/957,427 priority Critical patent/US5347204A/en
Priority claimed from US07/957,427 external-priority patent/US5347204A/en
Application filed by Honeywell Inc. filed Critical Honeywell Inc.
Priority to DE69310770T priority patent/DE69310770T2/de
Priority to PCT/US1993/010459 priority patent/WO1995012153A1/fr
Priority to CA002148481A priority patent/CA2148481C/fr
Priority to EP93925137A priority patent/EP0677184B1/fr
Publication of WO1995012153A1 publication Critical patent/WO1995012153A1/fr

Links

Classifications

    • G—PHYSICS
    • G05—CONTROLLING; REGULATING
    • G05D—SYSTEMS FOR CONTROLLING OR REGULATING NON-ELECTRIC VARIABLES
    • G05D1/00—Control of position, course or altitude of land, water, air, or space vehicles, e.g. automatic pilot
    • G05D1/0055—Control of position, course or altitude of land, water, air, or space vehicles, e.g. automatic pilot with safety arrangements
    • G05D1/0061—Control of position, course or altitude of land, water, air, or space vehicles, e.g. automatic pilot with safety arrangements for transition from automatic pilot to manual pilot and vice versa
    • 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
    • B64C13/04—Initiating means actuated personally
    • B64C13/042—Initiating means actuated personally operated by hand
    • B64C13/0421—Initiating means actuated personally operated by hand control sticks for primary flight controls

Definitions

  • This application is related to application no. (attorney docket no. A34-14211 (15347-155)) and application no. (attorney docket no. A34-14307 (15347-153)).
  • This invention is related to an active hand control system of the ty ⁇ e wherein manual control input devices such as control sticks employed in a servo-coupled control system are provided with an electrically generated and controlled simulated variable rate feel.
  • the invention relates to a system having a control stick such as is employed in aircraft, which is servo-coupled to the control system of the aircraft through electronics and a motor mechanism.
  • the electronics and motor mechanism of these types of systems provide a simulated feel to the control stick when in operation which is similar to that of a purely mechanical system. Yet more specifically, in these types of systems when the control stick thereof is positioned near a null or center position, it begins to oscillate due to the high gain in the torque versus position curve used to achieve breakout forces by the motor which is driving and is in turn driven by the control stick, as well as oscillations caused by gear backlash at connection of the control stick to the motor.
  • the system in accordance with the invention eliminates such oscillations at about the null position for the control stick without degrading the force and feel characteristics of the control stick.
  • Servo-control technology is well developed as applied in the field of robotics. In particular, electrical motor and servo-control systems have been developed and employed in the past in the design of robotic hand controllers which are capable of reflecting forces experienced at the robotic end, back to, for example, a human operator.
  • U.S. Patent No. 4,150,803 which teaches a control stick for an operator having an electro-simulated variable rate feel.
  • the simulated feel of the device of U.S. Patent No. 4,150,803 is provided by a system which generates for the operator at the control stick the proper force and feel characteristics when used to command a boom employed during refueling operations between aircraft in flight.
  • controllers generally involve the use of a control stick which is actuatable in at least two mutually perpendicular planes to provide both vertical and lateral control of the device being controlled.
  • An example of such a control stick is shown in U.S. Patent No.
  • control stick of the device has electrical pickup means in plate form, for example, capacitance bridge circuits arranged in a symmetrical arrangement such that a force exerted on the stick having a symmetrical arrangement of circuits unbalances them and produces a signal which is proportional to the force being exerted on the stick.
  • the signals generated by the electrical pickups are used to generate output signals through appropriate electronics, with the electronics being used to command a control actuator to effect control of the device being controlled.
  • control stick is mechanically coupled at its axis to at least one motor which applies either a resisting force on the control stick or, in response to a signal produced by sensors that detect forces applied to the device surfaces being controlled, drives the control stick and in turn, drives the device being controlled to alleviate forces generated by the device under control as felt by the operator.
  • controllers are particularly desirable for use in the operation of modern day aircraft, in particular, in the form of control sticks or yokes.
  • the devices as used in the cockpit of aircraft are typically designed to exhibit some desired force versus displacement characteristics to the user whereby the magnitude of the control stick displacement is proportional to the force applied.
  • the controller produces as its output an electrical signal corresponding to the control stick position, and the signal is used to control the aircraft through the action of various motors and mechanical means, in a manner which is well known to those of ordinary skill in the art and is conventional.
  • Such systems provide an electronically controlled manual input control stick having force and feel characteristics like those of purely mechanically linked systems.
  • These applications in aircraft are typically referred to as "fly by wire” applications. Examples of presently existing applications of this technology are the systems employed in the Airbus A300 Transport Aircraft, the General Dynamics F16 Fighter aircraft and the NASA Space Shuttle.
  • controller electronics were employed in combination with sensors for detecting the position of the control stick. A signal was generated and processed by controller electronics to drive a motor which in turn drove the control stick to simulate the feel of a mechanical system.
  • controller electronics also included input from the system being controlled such as, for example, an auto pilot system or reflecting any external forces acting on the flight control surfaces of the aircraft which would, as a result of feedback and input from the surfaces, be input into the controller electronics to be reflected through the motor connected to the control stick at the user.
  • the invention is directed to an improvement in an active hand controller system which has manual input control means, i.e., a control stick, connected to a motor.
  • the motor serves to provide predetermined force and feel characteristics to the manual input control means to be reflected at a user.
  • the motor is connected to control electronics, i.e., a feedback loop, for generating signals which control the motor in response to input signals generated at the manual input control means as well as at the system being controlled, for example, at its flight control surfaces.
  • selective rate dampening means serves to provide a signal representing a higher amount of rate dampening to the control electronics means for generating a control signal which dampens the oscillations occurring as a result of the interaction between the motor through the gears with the manual input control means when the manual input control is at about its null position.
  • the selective rate dampening means provides a signal indicative of lesser rate dampening when the manual input control means is positioned at a location other than about its null position.
  • the selective rate dampening means in accordance with the invention comprises a switch movable between a first position and a second position which is controlled by a comparator connected to the manual input control means through position -etecting means.
  • the position detecting means detects the position of the manual input control means and generates a signal representative of the position for controlling the switch to be in the second position to provide a relatively high gain level signal to the controller electronics means when the manual input control means is at about its null position to increase rate dampening thereof.
  • the switch is arranged to be in the first position to provide a relatively low gain signal to the controller electronics means to provide relatively lower rate dampening when the control stick is not at about the null position.
  • the invention also includes differentiating means operating on the position signal which represents the position of the manual input control means, i.e., control stick, to generate a signal representative of velocity of movement of the manual control input control means.
  • the differentiating means is connected in a manner wherein the position signal detected and the velocity signal generated are each supplied separately to the selective rate dampening means to be factored into the control of the switch between the first and second positions to determine whether a higher or lower rate dampening is desired in response to the position of the control stick.
  • the selective rate dampening means in accordance with the invention comprises a dic tal computer.
  • the computer by operating software in accordance with the detected position of the manual input control means, calculates and generates a signal of relatively high gain when the manual input control is at about its null position to increase rate dampening thereof.
  • the signal generated by the software is of relatively lower gain.
  • the invention consists of a method of dampening oscillations in an active hand controller system having manual input control means, i.e., a control stick.
  • the manual input control means is connected to a motor which causes the oscillations to occur in response to feedback signals controlling the motor when the manual input control means is at about its null position.
  • FIGURE 1 is a block diagram illustrating the active hand controller system electronics in accordance with the invention, and further showing the means for providing the relatively selective higher dampening for the control stick when the control stick is at about the null position;
  • FIGURE 2 is a graph illustrating the force versus displacement non-linearities occurring on the control stick at different positions thereof including additional non- linearities of the type which occur, for example, at such locations as are conventionally known as "soft stop";
  • FI G URE 3 is a more detailed diagram illustrating the details of the block employed in the circuit diagram of FIGURE 1 to show how selective rate dampening is provided to control the motor connected to the control stick of the invention;
  • FIGURE 4 is a block diagram illustrating an alternate embodiment of the active hand controller system of the invention as modified to implement the software illustrated in the flowchart of FIGURE 5;
  • FI G URE 5 is a general flowchart diagram illustrating the position dependent rate dampening of the invention provided as a software version of a component of an endless control loop to provide rate dampening as a function of position.
  • FIGURE 1 there is disclosed a block diagram illustrating the selectible rate dampening circuit in accordance with the invention.
  • a control stick 11 with a hand grip thereon has an external force 13 applied thereto by a user, for example, a pilot.
  • the control stick 11 is connected to the motor 19 which provides certain force and feel characteristics back to the control stick 11 to simulate a conventional mechanical system.
  • the control stick 11 is connected through a gearhead 17 to the motor 19, and also has a force sensor 15 connected to the control stick 11 for detecting the magnitude of the force 13 applied to the control stick 11.
  • a resolver 23 which is back-driven by the gearhead
  • a command signal corresponding to the movement of the control stick 11 is provided by the resolver 23 to the system being controlled through line 25.
  • the position signal generated by resolver 23 which is indicative of control stick 11 position, as well as the signal generated by force sensor 15 indicative of any force applied to control stick 11, these signals are fed back into a control loop to be processed by controller electronics 73 to output a signal through line 75 to control the motor 19 torque to thereby provide appropriate force and feel characteristics to the control stick 11.
  • a problem with these types of hand controllers is that when the control stick 11 is located about its null or zero position, the control stick 11 begins to oscillate due to torque generated by the motor 19. Traditionally, such oscillations have been controlled by providing rate dampening in the control system for the---motor 19. Such rate dampening enhances stability of the control stick but at the high cost of degraded transient response. Excessive rate dampening in an active controller makes the hand controller feel viscous in an undesirable manner.
  • rate dampening is provided at a very high gain only when the control stick 11 is located within a small region about the center position. Thus, some stability is provided without degrading the overall feel in use of the control stick 11.
  • FIGURE 2 shows that the breakout force about the null position relative to control stick 11 displacement is much greater than at other positions. This is caused by high position loop gain in the torque versus position curve shown in FIGURE 2 for the motor 19, as well as because of other characteristics of operation, such as gear backlash at the interconnection between the control stick 11 through the gearhead 17 to the motor 19.
  • the force sensor 15 detects the force exerted on control stick 11 and provides a signal indicative of the force applied through line 65.
  • the signal 65 from the force sensor 15 is conditioned and scaled to create a high level ( ⁇ 5 or ⁇ IOV) bipolar analog signal 69 that changes linearly with force applied at the control stick 11.
  • a strain gauge type force sensor typically has an output signal of ⁇ 5 mV which is highly susceptible to noise.
  • Another example of a force sensor for use in the invention is a force sensor with a modulated AC output dependent on force.
  • the conditioning and scaling electronics 67 transforms the force sensor output 65 into a usable force signal 69.
  • the force signal is provided through line 69 to controller electronics 73 in a manner as disclosed in copending application no.
  • the feedback loop for the position of the control stick 11 on the upper half of FIG. 1 is similar to that of said copending application with the exception that the position signal generated by the resolver 23 through line 27 is passed through line 29 to differentiating block 37 to have the derivative of said signal taken therein.
  • the derivative is done, for example, by monitoring the rate at which the resolver-to-digital converter increments its digital output up or down, to result in a velocity signal which is passed through line 39 to position dependent scaling block 41.
  • the velocity signal 39 is scaled according to the position of the control stick 11 as indicated by the position signal 47.
  • the position dependent scaling block 41 amplifies the rate signal 39 by a factor several times greater than the scale factor at other positions. This could be accomplished by any number of different methods. One such method would be by the circuit shown in FIGURE 3. At about null the switch at 105 remains open thereby increasing the gain of the rate signal 39. At other positions the switch remains closed. Similarly this function can be accomplished by software as described with reference to FIGURE 5 discussed hereinafter.
  • the resolver 23 produces a modulated ac output signal 31 which must be demodulated in signal conditioning block 43 in order to produce a usable control signal in a control system.
  • a resolver-to-digital converter is used as signal conditioning block 43 to transform the resolver output to a digital or binary representation of position.
  • This digital representation of position is then converted to a high level analog signal 45 by a digital-to-analog converter chip also in signal conditioning block 43.
  • the resulting position signal 45 is passed through line 47 to be operated on along with the velocity signal in position dependent scaling block 41.
  • the operation in position dependent scaling block 41 will be discussed in greater detail herein with the reference to FIGURE 3.
  • the resultant signal from block 41 is then passed through line 61 to summing device 63.
  • This signal from block 41 serves to have the controller electronics 73 provide either a high or a low gain dampening signal through line 75 to motor 19 depending upon whether the control stick 11 is at or about its null position, or outside of its null position.
  • the position signal is also passed through line 49 into scaling block 51 and after scaling in a conventional manner is passed through line 59 into summing device 63.
  • the position signal is also passed through line 53 to account for breakout force, characteristics of the control stick 11 by being processed in breakout signal generation block 55 and passed through line 57 in summing device 63 from where the combined signals are passed through line 71 into controller electronics 73 to provide the appropriate control signal to motor 19.
  • the amount f dampening provided to the control stick 11 is dependent on the magnitude of the signal resulting from position dependent scaling block 41 at line 61.
  • the dampening is controlled by the circuit of the position dependent scaling block 41 by means of the gain provided through operational amplifier 113, hereinafter op-amp 113.
  • the op-amp 113 is arranged in an inverting amplifier circuit configuration with the velocity signal through line 39 being passed through resistor 111 into the negative in; .t of op-amp 113.
  • Across the input and output of the op-amp 113 are located a pair of resistors 107 and 109 arranged in parallel with a switch 105 being controlled by control function block 101.
  • the control function block 101 serves to issue a signal through line 103 to switch 105 to either open or close the switch 105.
  • the switch 105 is closed the position signal is passed across resistor 107 along with the velocity signal incoming through line 39. Whether the switch 105 is opened or closed is dependent upon the position signal coming through line 47 from resolver 23.
  • the gain for the position dampening signal from position dependent scaling block 41 is controlled in accordance with the actual position of the control stick 11 detected.
  • FIGURE 4 illustrates an alternative implementation of the invention where a digital computer is used to close the control through a specific software implementation described with reference to FIGURE 5.
  • like elements are numbered the same as for FIGURE 1 and function the same unless otherwise noted.
  • the high level torque signal at line 69 and the rate signal at line 39 are converte d to digital signals by analog to digital converters 76 and 77.
  • a digital computer 201 shown in dashed lines replaces the elements shown enclosed thereby to calculate, through the software described with reference to FIGURE 5, and based on the input digital rate, position and torque signals, a desired and calculated motor torque signal which through line 78 is passed to digital to analog converter 7 9 to b e acted on by controller electronics 73 in a manner similar to FIGURE 1.
  • the signal conditioning block 43 is now shown as resolver to digital converter 4 3 ' which was previously discussed with reference to FIGURE 1 as an example of the type of device that could be used as the signal conditioning block 43.
  • FIGURE 4 operates as more particularly described with reference to the flowchart of FIGURE 5 wherein the software version of the invention is implemented in an endless loop which provides rate dampening as a function of position.
  • C omponents unrelated to rate dampening which are needed to form the complete control loop are shown for reference purposes in the block in dashed lines, but are not necessary to illustrate the concept of the invention.
  • Such component steps in the program are conventional and well known to those of ordinary skill in the art.
  • position and velocity in this implementation may be vector quantities, for example, for a conventional six axis active hand controller, the position and velocity will be six component vectors.
  • a list of pre-defined non-overlapping position bands or intervals are examined to determine in which band the current position is located.
  • a band is determined independently for each axis.
  • the "velocity - command - component" is the component of the output feedback command which is responsible for implementing rate dampening.
  • the amount of rate dampening is computed for each axis by multiplying the "rate-factor" for the current band with the velocity detected for movement of the control stick 11.
  • rate-factors are negative numbers used to achieve the dampening, i.e., a force in opposition to the current velocity.
  • the "rate-factors” are tabulated by the band for each axis independently.
  • the feedback command is then computed by summing the "velocity - command - component" with any other command components which may be needed for reasons other than rate dampening. The summed components result in a vector sum for a multi-axis active hand controller system. Finally, the feedback command is output to the system being controlled and the loop is closed by repeating the above sequence for the next iteration.

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  • Engineering & Computer Science (AREA)
  • Automation & Control Theory (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Radar, Positioning & Navigation (AREA)
  • Remote Sensing (AREA)
  • Physics & Mathematics (AREA)
  • General Physics & Mathematics (AREA)
  • Control Of Position Or Direction (AREA)
  • Feedback Control In General (AREA)

Abstract

Un système de commande destiné à un dispositif de commande manuel actif, par exemple, utilise un manche de commande relié à un moteur par lequel il est commandé. Des éléments électroniques servent à commander le moteur pour éliminer les oscillations dues au couple du moteur et un gain élevé du à un décrochage au niveau du manche de commande lorsque celui-ci est presque en position zéro. Aussi bien le matériel que des logiciels peuvent permettre d'obtenir un amortissement dépendant de la position, pour un manche de commande, tel que lorsque le manche de commande est presque en position zéro, on obtient un taux d'amortissement plus élevé que lorsque le manche de commande est éloigné de sa position zéro, position dans laquelle le taux d'amortissement est plus bas. Grâce à ce système l'on obtient un dispositif de commande manuel actif stable, en l'occurrence un manche de commande, sans que les qualités du système relatives aux forces et aux sensations ne soient diminuées.
PCT/US1993/010459 1992-10-06 1993-10-29 Amortissement de la vitesse dependant de la position dans un dispositif de commande manuel actif WO1995012153A1 (fr)

Priority Applications (5)

Application Number Priority Date Filing Date Title
US07/957,427 US5347204A (en) 1992-10-06 1992-10-06 Position dependent rate dampening in any active hand controller
DE69310770T DE69310770T2 (de) 1993-10-29 1993-10-29 Positionsabhangige dampfung in einer aktiven handsteuerung
PCT/US1993/010459 WO1995012153A1 (fr) 1992-10-06 1993-10-29 Amortissement de la vitesse dependant de la position dans un dispositif de commande manuel actif
CA002148481A CA2148481C (fr) 1992-10-06 1993-10-29 Amortissement de la vitesse dependant de la position dans un dispositif de commande manuel actif
EP93925137A EP0677184B1 (fr) 1992-10-06 1993-10-29 Amortissement dependant de la position dans un dispositif de commande manuel actif

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
US07/957,427 US5347204A (en) 1992-10-06 1992-10-06 Position dependent rate dampening in any active hand controller
PCT/US1993/010459 WO1995012153A1 (fr) 1992-10-06 1993-10-29 Amortissement de la vitesse dependant de la position dans un dispositif de commande manuel actif
CA002148481A CA2148481C (fr) 1992-10-06 1993-10-29 Amortissement de la vitesse dependant de la position dans un dispositif de commande manuel actif

Publications (1)

Publication Number Publication Date
WO1995012153A1 true WO1995012153A1 (fr) 1995-05-04

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Citations (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3270260A (en) * 1963-11-18 1966-08-30 Measurement Systems Inc Stick-operated diaphragm control
US3945590A (en) * 1975-01-23 1976-03-23 Sperry Rand Corporation Semi-automatic takeoff control system for aircraft
US4095763A (en) * 1977-02-25 1978-06-20 Textron, Inc. Fail safe augmentation system
US4150803A (en) * 1977-10-05 1979-04-24 Fernandez Carlos P Two axes controller
EP0160834A2 (fr) * 1984-05-08 1985-11-13 Messerschmitt-Bölkow-Blohm Gesellschaft mit beschränkter Haftung Dispositif de stabilisation de la force de commande dans un giravion
EP0175883A2 (fr) * 1984-08-28 1986-04-02 Messerschmitt-Bölkow-Blohm Gesellschaft mit beschränkter Haftung Dispositif pour améliorer la stabilité de commande longitudinale des aéronefs
EP0179209A2 (fr) * 1984-08-28 1986-04-30 Eurocopter Deutschland Gesellschaft mit beschränkter Haftung Dispositif automatique de commande pour aéronef en particulier pour hélicoptère
EP0384806A1 (fr) * 1989-02-20 1990-08-29 AEROSPATIALE Société Nationale Industrielle Dispositif de commande à manche basculant, notamment pour aéronef, et système comportant deux tels dispositifs
EP0401079A1 (fr) * 1989-05-31 1990-12-05 Sextant Avionique S.A. Dispositif de commande électromécanique utilisable pour le pilotage d'un véhicule
US5264768A (en) * 1992-10-06 1993-11-23 Honeywell, Inc. Active hand controller feedback loop
US5291113A (en) * 1992-10-06 1994-03-01 Honeywell Inc. Servo coupled hand controllers

Patent Citations (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3270260A (en) * 1963-11-18 1966-08-30 Measurement Systems Inc Stick-operated diaphragm control
US3945590A (en) * 1975-01-23 1976-03-23 Sperry Rand Corporation Semi-automatic takeoff control system for aircraft
US4095763A (en) * 1977-02-25 1978-06-20 Textron, Inc. Fail safe augmentation system
US4150803A (en) * 1977-10-05 1979-04-24 Fernandez Carlos P Two axes controller
EP0160834A2 (fr) * 1984-05-08 1985-11-13 Messerschmitt-Bölkow-Blohm Gesellschaft mit beschränkter Haftung Dispositif de stabilisation de la force de commande dans un giravion
EP0175883A2 (fr) * 1984-08-28 1986-04-02 Messerschmitt-Bölkow-Blohm Gesellschaft mit beschränkter Haftung Dispositif pour améliorer la stabilité de commande longitudinale des aéronefs
EP0179209A2 (fr) * 1984-08-28 1986-04-30 Eurocopter Deutschland Gesellschaft mit beschränkter Haftung Dispositif automatique de commande pour aéronef en particulier pour hélicoptère
EP0384806A1 (fr) * 1989-02-20 1990-08-29 AEROSPATIALE Société Nationale Industrielle Dispositif de commande à manche basculant, notamment pour aéronef, et système comportant deux tels dispositifs
EP0401079A1 (fr) * 1989-05-31 1990-12-05 Sextant Avionique S.A. Dispositif de commande électromécanique utilisable pour le pilotage d'un véhicule
US5264768A (en) * 1992-10-06 1993-11-23 Honeywell, Inc. Active hand controller feedback loop
US5291113A (en) * 1992-10-06 1994-03-01 Honeywell Inc. Servo coupled hand controllers

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