GB1568695A - Creation of Inventions and Patents with Artificial Intelligence

GB1568695A – Rudder angle indicator
– Google Patents

GB1568695A – Rudder angle indicator
– Google Patents
Rudder angle indicator

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Publication number
GB1568695A

GB1568695A
GB16504/79A
GB1650479A
GB1568695A
GB 1568695 A
GB1568695 A
GB 1568695A
GB 16504/79 A
GB16504/79 A
GB 16504/79A
GB 1650479 A
GB1650479 A
GB 1650479A
GB 1568695 A
GB1568695 A
GB 1568695A
Authority
GB
United Kingdom
Prior art keywords
rudder
signal
representative
signals
response
Prior art date
1975-11-10
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.)

Expired

Application number
GB16504/79A
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.)

Laitram LLC

Original Assignee
Laitram LLC
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.)
1975-11-10
Filing date
1976-11-02
Publication date
1980-06-04

1976-11-02
Application filed by Laitram LLC
filed
Critical
Laitram LLC

1980-06-04
Publication of GB1568695A
publication
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patent/GB1568695A/en

Status
Expired
legal-status
Critical
Current

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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

G05D1/02—Control of position or course in two dimensions

G05D1/0206—Control of position or course in two dimensions specially adapted to water vehicles

Description

PATENT SPECIFICATION
( 11) 1568695 ( 21) Application No 16504/79 ( 22) Filed 2 Nov 1976 ( 19) ( 62) Divided Out of No 1 568 694 ( 31) Convention Application No 630 539 ( 32) Filed 10 Nov 1975 in ( 33) United States of America (US) ( 44) Complete Specification published 4 June 1980 ( 51) INT CL 3 GO 1 C 21/00 ( 52) Index at acceptance GIN IA 3 A 1 A 4 ID 5 3 SIB 7 LIA 7 TIA AHU ( 54) RUDDER ANGLE INDICATOR ( 71) We, THE LAITRAM CORPORATION, a corporation of the State of Louisiana, United States of America, of 220 Laitram Lane, Harahan, Louisiana 70123, United States of America, do hereby declare the invention for which we pray that a patent may be granted to us and the method by which it is to be performed to be particularly described in and by the following
statement: –
This invention relates to a rudder angle indicator for use in automatic piloting systems, and more particularly in an electronic system for the steering of a marine or other vessel along an intended course.
This Application is divided from our copending Application No 45515/76 (Serial No 1,568,694).
In most piloting systems known in the art, a course transmitter is employed to provide a signal indication of an intended course to be steered and to provide steering command signals for rudder control to maintain an intended course A feedback signal representing rudder position is provided by a rudder angle sensor, this feedback signal being applied to the course transmitter which will be rotated or otherwise adjusted to seek a null condition Although such systems perform adequately for many purposes, their implementation is usually quite complex, requiring analog servomechanical apparatus including a specialized course transmitter for indicating an intended course and for generating steering commands Moreover, being null type servo systems, known automatic piloting systems are most sensitive at the null point and are of reduced accuracy for increasing course error.
The Application No 45515/76 (Serial No 1,568,694) discloses and claims:
a digital magnetic compass providing a digital output signal representative of magnetic compass heading; digital means operative in response to said compass output signal to produce a course error signal representative of the difference between said compass heading and a desired course heading; means operative in response to said course error signal to provide first and second signals representative of the integral and the derivative of course error, respectively; rudder angle means operative to provide a signal representative of the present angular position of the rudder; means for combining said first signal, said second signal, and said course error signal and for providing a control signal representative of the difference between the combined signal and said signal from said rudder angle means; means defining a range of output signals within which no rudder control is provided; and output gate means operative in response to said control signal and said range defining means for providing rudder control sig 70 nals representing course error outside of said range.
The present invention provides a rudder angle indicator for use in an automatic piloting system in which rudder control sig 75 nals are provided to control rudder position comprising:
a differential capacitor coupled to said rudder, and including a first and a second capacitor, respectively, providing a first 80 capacitance and a second capacitance; said first and second capacitances being equal for a zero rudder position, said first capacitance increasing and said second capacitance correspondingly decreasing for 85 rudder positions of one sense, said first capacitance decreasing and said second capacitance correspondingly increasing for rudder positions of opposite sense; and means operative in response to said first 90 and second capacitances for providing a pulse width modulated signal of average amplitude representative of rudder position.
A specific embodiment of the invention will now be described, by way of example, 95 with reference to the accompanying drawings in which:
Figure 1 is a diagrammatic representation of an automatic piloting system using the present invention; 100 Figure 2 is a schematic representation of 1 f O 1,568,695 a capacitive rudder angle indicator according to the present invention; Figure 3 is a schematic representation of capacitive rudder angle indicating circuitry according to the present invention; and Figure 4 is a diagrammatic representation of the course error circuitry of Figure 1.
Referring to Fig 1 there is shown a digital magnetic compass 10 providing digital output signals representative of compass heading which are applied to a course error circuit 12 which, in turn, provides a digital signal representative of the magnitude of course error and a digital signal indication of whether the error is to the right or left of intended course The digital compass is the subject of U S Patent 3,833,901 assigned to the assignee of this invention This compass provides serial output pulses of a number representative of compass heading as derived from an electro-optically sensed compass card The intended course to be maintained is provided in the course error circuit 12 typically by entering the reading from digital compass 10 when the vessel is on an intended course The signals from circuit 12 are applied to a digital-to-analog converter 14 which provides an analog output voltage representative of the magnitude and sense of course error This signal is coupled via a capacitor Cl to a differentiator 16 which is typically implemented by an operational amplifier 18 having an adjustable resistor 20 in feedback connection between the output and an input thereof.
The other input of operational amplifier 18 is coupled to a reference voltage source 22.
The output of differentiator 16 is coupled via resistor RI to the negative input of a summing amplifier 24 which includes a feedback resistor R 2 therearound The output signal from converter 14 is also applied to the negative input of amplifier 24 by means of a resistor R 3 The output voltage from converter 14 is also applied via a gain control 26 to an integrator 28 composed of an operational amplifier 30 having a capacitor C 2 in feedback connection therewith The second input to amplifier 30 is coupled to a reference voltage (Vret), such as from source 22 The output signal from integrator 28 is coupled by way of a resistor R 4 to the negative input of amplifier 24.
A rudder angle indicator 32 provides a pulse width modulated signal representative of measured rudder angle to a pulse width demodulator 34 which provides an analog output signal representative of angular rudder position, and which signal is applied via a buffer amplifier 36 and a resistor R 5 to the positive input of amplifier 24.
A gain control 37 is provided in feedback connection around amplifier 36.
The output of amplifier 24 is applied to an input of respective comparators 38 and 40 The comparators 38 and 40 70 are connected to respective reference sources 42 and 44 which provide respective reference signals V q, 1 and Vref 2 to the corresponding comparators.
One of the reference sources provides a 75 relatively positive threshold level with respect to a zero course error reference value, while the other reference source provides a relatively negative reference level with respect to this reference value 80 The reference sources 42 and 44 provide bipolar threshold levels defining a range within which no error correction is performed, and these reference sources are adjustable to control the error range within 85 which no rudder control is provided.
Such adjustment serves as a weather control, the adjustable range usually being selected in accordance with sea and weather conditions 90 The output signals from comparators 38 and 40 are applied to respective AND gates 46 and 48, the respective outputs of which are applied to respective AND gates 50 and 52 The output signal from compara 95 tors 38 and 40 are also applied via an OR gate 54 to a multivibrator circuit 56, the output of which is applied to the second inputs of gates 46 and 48 The multivibrator circuit 56 is operative in response 100 to input signals less than a predetermined value to provide output pulses representative to the input signal level For course error signals of magnitude above the predetermined value, circuit 56 is operative 105 to provide a DC level as a gating signal for gates 46 and 48 Pulse signals are provided for course error signals which are relatively small, typically less than + 20 error A control 58 is provided for circuit 110 56 to adjust the output pulses thereof to produce intended rudder movement in response to a corresponding error signal.
This control 58 in effect adjusts the pulse output in accordance with the dynamics of 115 the particular rudder to be steered For larger error signals, typically greater than = 2 , a continuous, rather than a pulsed control signal is produced for rudder drive.
The output signal from amplifier 36 is 120 applied to respective inputs of comparators and 62 These comparators receive respective reference signals Vr 3 and Vre, 4 from reference sources 64 and 66.
The output signal from comparators 60 125 and 62 are applied to respective inputs of AND gates 50 and 52 The gates 50 and 52 provide respective right rudder and left rudder control signals to rudder drive anparatus 68 to cause movement of the rud 130 ally semicircular capacitor plates 76 and 78 disposed in a common plane and having a third capacitor plate 80, also of generally semicircular configuration, disposed in spaced relationship with respect to plates 70 76 and 78 and relatively movable with respect to plates 76 and 78 about a shaft 82.
The capacitor structure serves as a differential capacitor and is itself known in the electronics art Upon rotation of plate 80 75 with respect to plates 76 and 78, the capacitance of plates 76 and 80 will vary in a first sense, while the capacitance of plates 78 and 80 will vary in an opposite sense, the total capacitance remaining substan 80 tially constant The capacitive sensor is particularly advantageous for rudder angle indication as there is no physical contact between the movable and non-movable capacitor plates Typically, plate 80 is 85 linked to rudder shaft 72 for movement in association therewith Rotation of the rudder causes corresponding rotation of plate 80 relative to plates 76 and 78 to produce a differential capacitance representa 90 tive of rudder angle.
Referring to Fig 3, the capacitive sensor 70 is shown schematically, capacitor C 3 depicting the capacitor formed by plates 76 and 80, while the capacitor pro 95 vided by plates 78 and 80 is depicted as capacitor C 4 The common plate of the two capacitors is connected to ground, the respective plates of capacitors C 3 and C 4 being connected to an input of respective 100 comparators 84 and 86 A reference source 88 provides a voltage reference to the second input of each comparator 84 and 86 The output of comparator 84 is coupled to the set input of a flip-flop 90, 105 while the reset input of this flip-flop is coupled to the output of comparator 86.
The Q output of flip-flop 90 is coupled via a resistor RIO having a diode D 1 in shunt therewith to capacitor C 3 The Q output 110 of flip-flop 90 is coupled to the capacitor C 4 by way of resistor RI 1 and shunt diode D 2 The circuit output is provided by the Q terminal of flip-flop 90.
With the rudder at a zero position, the 115 capacitive sensor provides two equal capacitances, causing an output signal at the Q terminal of flip-flop 90 which is a square wave of zero average amplitude When the rudder is moved to an angular position 120 other than zero, the capacitance of one of the capacitors C 3 and C 4 will be correspondingly increased, while the capacitance of the other will be correspondingly decreased, in accordance with the sense of 125 the rudder position to the right or to the left of its zero postiion The capacitor having increased capacitance will provide a longer charging time than the capacitor of decreased capacitance such that the com 130 der in the desired direction and by the desired amount The reference sources 64 and 66 are adjustable to provide a rudder limit control One of the reference S sources 64 and 66 provides a relatively positive reference level with respect to the zero reference position, while the other source provides a relatively negative reference level A range is thus defined within which rudder control is performed and -outside of which rudder control is inhibited The comparators 60 and 62 provide a first logic level in the presence of input signals within the threshold range which serves as a gating signal for gates and 52 to permit provision of rudder control signals to drive apparatus 68 In the event that a rudder angle signal from amplifier 36 is greater than the corresponding reference level, the associated one of comparators 60 and 62 provides an opposite logic level which inhibits the associated AND gate As a result, rudder control is inhibited for an indicated rudder angle greater than the selected amount.
The digital-to-analog converter 14 provides an analog signal having an intermediate value when no source error is sensed, and having a more positive or a more negative value in response to course errors of corresponding sense For example, positive analog output signals can denote course errors to the right, while negative output signals represent course errors to the left of desired course Typically, the output voltage from converted 14 varies between 0 and 5 volts with a level of 25 volts being provided in response to a zero error condition This output voltage typically varies by 0-1 volt for each degree of course error Similarly, the analog output signal from demodulator 34 representing indicated rudder angle can vary by 01 volt for each degree of rudder angle with an intermediate level of 25 volts for a zero or neutral rudder position More positive and more negative voltage levels are provided for respective right and left rudder angles.
The differentiator 16 provides a signal representing the rate of change of course error and which is subtracted from the error signal from converter 14 As the course error approaches zero, the derivative of the error also approaches zero, and, therefore, differentiator 16 is effective to dampen the error signal and minimize overshoot The integrator 28 is operative to average the error signal from converter 14 and in effect provides a system bias level about which the course error varies.
The rudder angle indicator is shown more particularly in Figs 2 and 3 As seen in Fig 2, a capacitive sensor 70 is coupled to a shaft 72 of a rudder 74 The sensor 70 includes first and second gener1,568,695 1,568,695 parator 84 or 86 associated with the capacitor of lesser capacitance will be triggered more often to provide switching of flip-flop A pulse width modulated signal is provided by flip-flop 90 which will be of positive average amplitude for rudder angles of one sense and negative average amplitude for rudder angles of opposite sense This pulse width modulated signal is relatively immune to noise and can be provided on a two wire cable to the demodulator For example, if the rudder is at an angular position at which capacitor C 3 is of increased capacitance and capacitor C 4 of corresponding decreased capacitance, the comparator 86 will be rapidly triggered by reason of the faster charging time of capacitor C 4 As a result, flip-flop is reset by the more rapid signals from comparator 86, in relation to the signals from comparator 84, such that an output signal is provided of a negative average amplitude representative of the angular position of the rudder.
The course error circuit 12 is shown more particularly in Fig 4 and is operative to provide digital output signals representative of the magnitude of course error and the sense of error to the right or left of an intended course This circuit is similar to the compass averaging circuit which is the subject of our U S Patent No 3,975,621.
The digital signal representative of cornpass heading and provided by digital compass 10 is, upon closure of switch 100, applied to a desired heading register 102 and to one input of a subtraction circuit 104 Circuit 104 also receives an input from register 102 and provides output signals representative of the magnitude and sense of the difference between the digital signals provided by compass 10 and register 102 The register 102 is initially loaded with a representation of the compass heading sensed by digital compass 10 This heading stored by register 102 can be employed as the intended course indication, or the intended course can be altered by trimming the stored heading in register 102 by means of trim control 103 This trim control is operative to increment or decrement the digital count stored in register 102 to provide a representation of intended heading to be maintained.
The digital error signal from subtractor 104 is applied to a detector circuit 106 operative to detect whether the error signal represents a heading difference greater than 180 degrees If the heading error is greater than 180 degrees, detector 106 provides an output signal to circuit 108 which is operative to subtract a representation of 360 degrees from the heading error to provide an output signal representative of the magnitude of the course error This output signal from subtractor 108 is provided via gate 110 as an output for application to converter 14 In the event that the course difference is 180 degrees or less, detector 106 provides a direct output indication of the magnitude of the heading error via gate 110 The sense of the course error is provided by sign correction circuit 112.
For a course error greater than 180 degrees, the signal from detector 106 applied to circuit 112 causes inversion of the output signal from circuit 112 to denote an opposite sense.
It will be appreciated that the system described herein can be readily implemented in either discrete or integrated circuit form and can be readily installed aboard a vessel without need for a specialized analog course transmitter or servomechanical apparatus The particular implementation of the invention can vary to suit intended performance requirements Accordingly, the invention is not to be limited by what has been particularly shown and described except as indicated in the appended claims.

Claims (1)

WHAT WE CLAIM IS:
1 A rudder angle indicator for use in an automatic piloting system in which rud 95 der control signals are provided to control rudder position comprising:
a differential capacitor coupled to said rudder and including a first and a second capacitor, respectively, providing a first 100 capacitance and a second capacitance; said first and second capacitances being equal for a zero rudder position, said first capacitance increasing and said second capacitance correspondingly decreasing for 105 rudder positions of one sense, said first capacitance decreasing and said second capacitance correspondingly increasing for rudder positions of opposite sense; and means operative in response to said first 110 and second capacitances for providing a pulse width modulated signal of average amplitude representative of rudder position.
2 A rudder angle indicator according 115 to Claim 1, wherein said pulse width modulated signal means includes:
means for deriving first and second voltages representative of the charging time of said respective capacitors; 120 comparator means operative to provide first and second signals upon exceedance of a threshold level by said first and second voltages; and gate means operative in response to said 125 signals to provide a pulse width modulated signal representative of rudder position.
3 An automatic piloting system using the rudder angle indicator of Claim 1 or Claim 2, comprising: 130 1,568,695 a digital magnetic compass providing a digital output signal representative of magnetic compass heading; digital means operative in response to said compass output signal to produce a course error signal representative of the difference between said compass heading and a desired course heading; means operative in response to said course error signal to provide first and second signals representative of the integral and the derivative of course error, respectively; rudder angle means operative to provide a signal representative of the present angular position of the rudder; means for combining said first signal, said second signal, and said course error signal and for providing a control signal representative of the difference between the combined signal and said signal from said rudder angle means; means defining a range of output signals within which no rudder control is provided; and output gate means operative in response to said control signal and said range defining means for providing rudder control signals representing course errors outside of said range.
4 An automatic piloting system according to Claim 3, further including:
means defining a second range of control signals within which said rudder control signals are provided and outside of which rudder control is inhibited.
An automatic piloting system according to Cla im 3 or Claim 4, wherein said range defining means includes:
first comparator means having a positive relative reference threshold; second comparator means having a negative relative reference threshold; said first and second comparator means being operative to provide an output signal in response to a received control signal respectively greater or less than the associated reference threshold.
6 An automatic piloting system according to Claim 5 including pulse generating means operative to receive output signals from said first and second comparator means and to provide output pulse signals in response to comparator output signals of magnitude less than a predetermined level, and DC output signals in response to comparator output signals of magnitude greater than said predetermined level.
1 An automatic piloting system according to Claim 5 or Claim 6 wherein said digital means includes:
a course error circuit operative in response to said digital signal representative from said magnetic compass and having means for storing a representation of a desired course heading, said course error circuit providing intermediate digital output siynals representative of the magnitude and sense of course error.
8 An automatic piloting system according to any one of Claims 3 to 7, wherein said rudder angle means includes:
a rudder angle indicator coupled to a rudder to be controlled and operative to provide a pulse width modulated signal representative of the angular position of said rudder; demodulator means operative in response to said pulse width modulated signal to provide an output signal of magnitude representative of the angular position of said rudder.
9 A rudder angle indicator according to Claim 1, substantially as hereinbefore described with reference to, and as illustrated in Figures 2 and 3 of the accompanying drawings.
WITHERS & ROGERS, Chartered Patent Agents, 4 Dyer’s Buildings, Holborn, London ECIN 2 JT.
Agents for the Applicant.
Printed for Her Majesty’s Stationery Office by Burgess & Son (Abingdon), Ltd -1980.
Published at The Patent Office, 25 Southampton Buildings, London, WC 2 A l AY from which copies may be obtained.

GB16504/79A
1975-11-10
1976-11-02
Rudder angle indicator

Expired

GB1568695A
(en)

Applications Claiming Priority (1)

Application Number
Priority Date
Filing Date
Title

US05/630,539

US4038528A
(en)

1975-11-10
1975-11-10
Automatic piloting system

Publications (1)

Publication Number
Publication Date

GB1568695A
true

GB1568695A
(en)

1980-06-04

Family
ID=24527578
Family Applications (2)

Application Number
Title
Priority Date
Filing Date

GB45515/76A
Expired

GB1568694A
(en)

1975-11-10
1976-11-02
Automatic piloting system

GB16504/79A
Expired

GB1568695A
(en)

1975-11-10
1976-11-02
Rudder angle indicator

Family Applications Before (1)

Application Number
Title
Priority Date
Filing Date

GB45515/76A
Expired

GB1568694A
(en)

1975-11-10
1976-11-02
Automatic piloting system

Country Status (8)

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US
(2)

US4038528A
(en)

JP
(1)

JPS5261099A
(en)

CA
(1)

CA1046863A
(en)

DE
(1)

DE2650958A1
(en)

FR
(1)

FR2331085A1
(en)

GB
(2)

GB1568694A
(en)

NL
(1)

NL7612478A
(en)

NO
(1)

NO763780L
(en)

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1975

1975-11-10
US
US05/630,539
patent/US4038528A/en
not_active
Expired – Lifetime

1976

1976-11-02
GB
GB45515/76A
patent/GB1568694A/en
not_active
Expired

1976-11-02
GB
GB16504/79A
patent/GB1568695A/en
not_active
Expired

1976-11-08
DE
DE19762650958
patent/DE2650958A1/en
not_active
Withdrawn

1976-11-08
NO
NO763780A
patent/NO763780L/no
unknown

1976-11-09
CA
CA265,272A
patent/CA1046863A/en
not_active
Expired

1976-11-10
FR
FR7634011A
patent/FR2331085A1/en
not_active
Withdrawn

1976-11-10
JP
JP51135116A
patent/JPS5261099A/en
active
Pending

1976-11-10
NL
NL7612478A
patent/NL7612478A/en
not_active
Application Discontinuation

1977

1977-04-13
US
US05/787,271
patent/US4103638A/en
not_active
Expired – Lifetime

Also Published As

Publication number
Publication date

US4038528A
(en)

1977-07-26

NO763780L
(en)

1977-05-11

JPS5261099A
(en)

1977-05-20

US4103638A
(en)

1978-08-01

FR2331085A1
(en)

1977-06-03

NL7612478A
(en)

1977-05-12

DE2650958A1
(en)

1977-05-18

CA1046863A
(en)

1979-01-23

GB1568694A
(en)

1980-06-04

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