CA2494050A1 - Electronic non-linear aircraft dynamic parameter display - Google Patents

Electronic non-linear aircraft dynamic parameter display Download PDF

Info

Publication number
CA2494050A1
CA2494050A1 CA002494050A CA2494050A CA2494050A1 CA 2494050 A1 CA2494050 A1 CA 2494050A1 CA 002494050 A CA002494050 A CA 002494050A CA 2494050 A CA2494050 A CA 2494050A CA 2494050 A1 CA2494050 A1 CA 2494050A1
Authority
CA
Canada
Prior art keywords
dynamic parameter
scale
aircraft
display unit
reading
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
CA002494050A
Other languages
French (fr)
Other versions
CA2494050C (en
Inventor
John Maris
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.)
Marinvent Corp
Original Assignee
Individual
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 Individual filed Critical Individual
Publication of CA2494050A1 publication Critical patent/CA2494050A1/en
Application granted granted Critical
Publication of CA2494050C publication Critical patent/CA2494050C/en
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

Links

Classifications

    • GPHYSICS
    • G01MEASURING; TESTING
    • G01DMEASURING NOT SPECIALLY ADAPTED FOR A SPECIFIC VARIABLE; ARRANGEMENTS FOR MEASURING TWO OR MORE VARIABLES NOT COVERED IN A SINGLE OTHER SUBCLASS; TARIFF METERING APPARATUS; MEASURING OR TESTING NOT OTHERWISE PROVIDED FOR
    • G01D7/00Indicating measured values
    • GPHYSICS
    • G01MEASURING; TESTING
    • G01CMEASURING DISTANCES, LEVELS OR BEARINGS; SURVEYING; NAVIGATION; GYROSCOPIC INSTRUMENTS; PHOTOGRAMMETRY OR VIDEOGRAMMETRY
    • G01C23/00Combined instruments indicating more than one navigational value, e.g. for aircraft; Combined measuring devices for measuring two or more variables of movement, e.g. distance, speed or acceleration

Abstract

A method and apparatus is disclosed for displaying a dynamic parameter of an aircraft, the apparatus comprises a display unit receiving a display signal and displaying a scale that changes dynamically and non-linearly in accordance with a selected display algorithm, the display unit further displaying a pointer pointing (36) to said scale (32) in accordance with a reading of said dynamic parameter, thereby emphasizing a range of said reading of said dynamic parameter.

Claims (27)

1. An apparatus for displaying a dynamic parameter of an aircraft, said apparatus comprising:
a processing unit receiving a selected display algorithm signal and a reading of said dynamic parameter, said processing unit determining a display signal; and a display unit receiving said display signal and displaying a scale having scale ends, said scale changing dynamically and non-linearly in accordance with the selected display algorithm together with a minimum dynamic parameter value and a maximum dynamic parameter value, said display unit further displaying a painter pointing to said scale in accordance with said reading of said dynamic parameter, such that said selected display algorithm constantly and exactly fits said reading, and the minimum and maximum dynamic parameter values to said scale, thereby emphasizing a range of said reading of said dynamic parameter while keeping said minimum and said maximum dynamic parameter values constantly and in view at respective scale exacts.
2. The apparatus as claimed in claim 1, further wherein said scale comprises a vertical portion displayed vertically by said display unit.
3. The apparatus as claimed in any one of claims 1 to 2, wherein said dynamic parameter comprises the speed of said aircraft.
4. The apparatus as claimed in claim 3, wherein said display unit displays said pointer with said speed of said aircraft.
5. The apparatus as claimed in any one of claims 3 to 4, wherein a plurality of corresponding speed values are displayed adjacently to said scale by said display unit.
6. The apparatus as claimed in any one of claims 1 to 5, further comprising a user interface providing said selected display algorithm signal.
7. The apparatus as claimed in claim 4, wherein said display unit further displays an adjacent bar to said scale, said adjacent bar comprising a first end corresponding to said speed of the aircraft and a variable end corresponding, on said scale, to a future speed to be reached by said aircraft if a current variation of said speed is maintained during a predetermined amount of time.
8. The apparatus as claimed in claim 7, wherein said display unit further displays a value indicative of said variation of said speed.
9. The apparatus as claimed in any one of claims 7 to 8, wherein said predetermined amount of time is 10 seconds.
10. The apparatus as claimed in claim 2, wherein said dynamic parameter comprises the altitude of said aircraft; further wherein an altitude reference signal is further provided to said processing unit, further wherein said processing unit determines said display signal using said altitude reference signal.
11. The apparatus as claimed in claim 10, wherein said display unit displays said pointer with said altitude of said aircraft.
12. The apparatus as claimed in any one of claims 10 to 11, wherein a plurality of corresponding altitude values are displayed, by said display unit, adjacently to said scale.
13. The apparatus as claimed in any one of claims 10 to 12, further comprising a user interface providing said selected display algorithm signal and said altitude reference signal.
14. The apparatus as claimed in any one of claims 10 to 13, wherein said display unit further displays an adjacent bar to said scale, said adjacent bar comprising a first end corresponding to said altitude of said aircraft and a variable end corresponding, on said scale, to a future altitude to be reached by said aircraft if a current variation of said altitude is maintained during a predetermined amount of time.
15. The apparatus as claimed in claim 14, wherein said display unit further displays a value indicative of said variation of said altitude.
16. The apparatus as claimed in any one of claims 14 to 15, wherein said predetermined amount of time is 60 seconds.
17. The apparatus as claimed in claim 1, wherein a plurality of corresponding dynamic parameter values are displayed adjacently to said scale by said display unit.
18. A method for displaying a dynamic parameter of an aircraft, said method comprising:
providing a reading of said dynamic parameter;
generating a scale having scale ends, said scale changing dynamically and non-linearly using said provided reading of said dynamic parameter and a selected display algorithm signal together with a minimum dynamic parameter value and a maximum dynamic parameter value, and a pointer pointing to said scale in accordance with said reading of said dynamic parameter of said aircraft; and displaying said scale, said minimum dynamic parameter value and said maximum dynamic parameter value, such that said selected display algorithm constantly and exactly fits said reading, and the minimum and maximum dynamic parameter values to said scale, thereby emphasizing a range of said reading of said dynamic parameter while keeping said minimum and said maximum dynamic parameter values constant and in view at respective scale ends.
19. The method as claimed in claim 18, further comprising generating a plurality of corresponding dynamic parameter values, corresponding to said scale, further comprising displaying said plurality of corresponding dynamic parameter values adjacently to said scale.
20. The method as claimed in any one of claims 18 to 19, further comprising selecting said selected display algorithm signal from a plurality of non-linear display algorithms.
21. The method as claimed in claim 20, wherein said plurality of non-linear display algorithms comprise a geometric-based algorithm, an exponential-based algorithm, a logarithm-based algorithm or the like.
22. The method as claimed in any one of claims 18 to 21, wherein said generating of said scale is performed using said provided reading of said dynamic parameter and more than one selected display algorithm signal, each of the more than one selected display algorithm signal being used for generating a corresponding part of said scale.
23. The method as claimed in any one of claims 18 to 22, further comprising generating an adjacent bar, said adjacent bar comprising a first end corresponding to said dynamic parameter of said aircraft and a variable end corresponding to a future dynamic parameter value of said aircraft, if a current variation of said dynamic parameter is maintained during a predetermined amount of time, further comprising displaying said adjacent bar adjacently to said scale.
24. The method as claimed in claim 23, wherein said displaying of said adjacent bar further comprises displaying a value of said current variation of said dynamic parameter.
25. The method as claimed in any one of claims 18 to 24, wherein said dynamic parameter comprises at least one of altitude, speed, revolutions per minute (RPM), oil pressure, oil temperature, engine temperature, fuel flow, tachometer and remaining fuel.
26. An apparatus for displaying a dynamic parameter of an aircraft, said apparatus comprising:
a display unit receiving a display signal and displaying a scale having scale ends, said scale changing dynamically and non-linearly, such that a selected algorithm constantly and exactly fits a reading, a minimum dynamic parameter value acid a maximum dynamic parameter value, said display unit further displaying a pointer pointing to said scale in accordance with said reading of said dynamic parameter, thereby emphasizing a range of said reading of said dynamic parameter while keeping said minimum and said maximum parameter value constant and in view at respective scale ends.
27. The apparatus as claimed in claim 26, further wherein a plurality of corresponding dynamic parameter values are displayed adjacently to said scale by said display unit.
CA2494050A 2002-10-04 2003-09-26 Electronic non-linear aircraft dynamic parameter display Expired - Lifetime CA2494050C (en)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
US41580702P 2002-10-04 2002-10-04
US60/415,807 2002-10-04
PCT/CA2003/001424 WO2004031833A2 (en) 2002-10-04 2003-09-26 Electronic non-linear aircraft dynamic parameter display

Publications (2)

Publication Number Publication Date
CA2494050A1 true CA2494050A1 (en) 2004-04-15
CA2494050C CA2494050C (en) 2011-10-18

Family

ID=32069906

Family Applications (1)

Application Number Title Priority Date Filing Date
CA2494050A Expired - Lifetime CA2494050C (en) 2002-10-04 2003-09-26 Electronic non-linear aircraft dynamic parameter display

Country Status (11)

Country Link
US (1) US7062364B2 (en)
EP (1) EP1546655B1 (en)
JP (1) JP4246155B2 (en)
CN (1) CN100547353C (en)
AT (1) ATE320588T1 (en)
AU (1) AU2003266895A1 (en)
BR (1) BR0314374B1 (en)
CA (1) CA2494050C (en)
DE (1) DE60304053T2 (en)
ES (1) ES2260639T3 (en)
WO (1) WO2004031833A2 (en)

Families Citing this family (17)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US7205907B2 (en) * 2003-09-15 2007-04-17 Universal Avionics Systems Corporation Non linear tape display
US7095338B2 (en) * 2003-10-07 2006-08-22 Ted Naimer TCAS VSI display
US7412308B2 (en) * 2003-10-07 2008-08-12 Universal Avionics Systems Corp. Dynamic VSI display
DE102004045094B4 (en) * 2004-09-17 2012-05-03 Deutsches Zentrum für Luft- und Raumfahrt e.V. Method for automatically generating graphically displayed display instruments
WO2006041479A1 (en) * 2004-10-07 2006-04-20 Universal Avionics Systems Corporation Dynamic vsi display
DE102006013695A1 (en) * 2006-03-24 2007-09-27 Robert Bosch Gmbh Electro-optical display unit for hand-held length measuring device e.g. roller-tape, has digital display comprising variable scale with scale point and numerical value, where orientation of scale is changed relative to display unit
US20090189787A1 (en) * 2008-01-30 2009-07-30 Honeywell International Inc. System and method for generating an altimeter mis-set alert on a primary flight display
EP2177882B1 (en) * 2008-10-20 2016-03-16 Volvo Car Corporation A display device for a vehicle
US20120010765A1 (en) * 2010-07-07 2012-01-12 Honeywell International Inc. System for displaying a procedure to an aircraft operator during a flight of an aircraft
US9529010B2 (en) 2013-06-17 2016-12-27 Honeywell International Inc. Flight deck display systems and methods for visually indicating low speed change conditions during takeoff and landing
FR3010975B1 (en) * 2013-09-20 2015-11-06 Thales Sa NAVIGATION INFORMATION DISPLAY SYSTEM FOR AN AIRCRAFT AND PRIMARY FLIGHT SCREEN FOR AN AIRCRAFT
US9950805B2 (en) * 2015-10-26 2018-04-24 The Boeing Company Aircraft engine fan speed display improvements for enhanced monitoring and thrust setting ability
US9669941B1 (en) * 2016-01-31 2017-06-06 Rockwell Collins, Inc. Weather indicator system and method
CN106970644B (en) * 2017-05-16 2019-10-22 西安爱生技术集团公司 A kind of aobvious prosecutor method of unmanned plane height
CN108168520A (en) * 2017-12-19 2018-06-15 中联重科股份有限公司 Angle incidence indicator, inclination angle indicating means, device and engineering machinery
US20210009281A1 (en) * 2019-07-08 2021-01-14 Honeywell International Inc. System and method for adjusting a dynamic scale indicator on a flight display of an aircraft
FR3129719B1 (en) 2021-11-29 2024-02-16 Airbus Helicopters Pitch indicator having a piecewise linear pitch scale

Family Cites Families (29)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3747409A (en) * 1971-12-07 1973-07-24 Intercontinental Dynamics Corp Altimeter baro-setting mechanism
US3806934A (en) * 1972-08-07 1974-04-23 Teledyne Inc Inertial lead vertical speed indicator/glide slope director
DE2724860C2 (en) * 1977-06-02 1979-04-12 Bodenseewerk Geraetetechnik Gmbh, 7770 Ueberlingen Flight display instrument for aircraft
US4495806A (en) * 1982-04-02 1985-01-29 Smiths Industries Public Limited Company Indicator instruments
US4539843A (en) * 1983-12-05 1985-09-10 Aerologic, Inc. Altimeter and vertical speed indicator
US4860007A (en) * 1988-01-15 1989-08-22 The Boeing Company Integrated primary flight display
US5136301A (en) * 1989-08-30 1992-08-04 Rockwell International Corporation Primary flight display system having a vertical linear altimeter
FR2666428B1 (en) * 1990-09-05 1994-09-23 Aerospatiale METHOD OF VIEWING ON A SCREEN ON BOARD AN AIRPLANE, SYMBOLS FOR PILOTAGE.
US5250947A (en) * 1992-03-16 1993-10-05 Honeywell Inc. Altitude tape for aircraft displays
US5396425A (en) * 1993-08-27 1995-03-07 The United States Of America As Represented By The Secretary Of The Air Force Vertical velocity indicator
US5412382A (en) * 1993-12-30 1995-05-02 Honeywell Inc. Integrated electronic primary flight display
US5438880A (en) * 1994-05-17 1995-08-08 United Technologies Corporation Electrostatic linear airspeed transducer
US5614897A (en) * 1995-03-29 1997-03-25 The Secretary Of State For Defence In Her Britannic Majesty's Government Of The United Kingdom Of Great Britain And Northern Ireland Aircraft flight instrument displays
US5745863A (en) * 1995-09-22 1998-04-28 Honeywell Inc. Three dimensional lateral displacement display symbology which is conformal to the earth
US6028536A (en) * 1995-11-16 2000-02-22 Northrop Grumman Corporation Integrated flight control indicator
FR2742226B1 (en) * 1995-12-08 1998-02-06 Eurocopter France VERTICAL ALTITUDE AND SPEED INDICATOR FOR AIRCRAFT
US5719581A (en) * 1996-02-12 1998-02-17 Alliedsignal, Inc. Low-cost radio altimeter
US5844504A (en) * 1997-07-22 1998-12-01 Rockwell International Compressed circle flight display
US6259378B1 (en) * 1997-09-22 2001-07-10 Sandel Avionics Display system for airplane cockpit or other vehicle
US6112141A (en) * 1997-10-15 2000-08-29 Dassault Aviation Apparatus and method for graphically oriented aircraft display and control
US6057786A (en) * 1997-10-15 2000-05-02 Dassault Aviation Apparatus and method for aircraft display and control including head up display
FR2770903B1 (en) * 1997-11-13 1999-12-31 Eurocopter France COMBINED GROUND AND HEIGHT INDICATOR FOR AIRCRAFT
US6154151A (en) * 1998-06-16 2000-11-28 Rockwell Collins, Inc. Integrated vertical situation display for aircraft
US6567014B1 (en) * 1998-11-05 2003-05-20 Rockwell Collins, Inc. Aircraft head up display system
US6683541B2 (en) * 1999-01-21 2004-01-27 Honeywell International Inc. Vertical speed indicator and traffic alert collision avoidance system
FR2801967B1 (en) * 1999-12-07 2002-04-12 Eurocopter France VARIABLE INDICATOR FOR AIRCRAFT
US6727912B1 (en) 2000-07-17 2004-04-27 Honeywell International Inc. Methods and apparatus for viewing variable resolution information on a display
US6381519B1 (en) * 2000-09-19 2002-04-30 Honeywell International Inc. Cursor management on a multiple display electronic flight instrumentation system
US6405107B1 (en) * 2001-01-11 2002-06-11 Gary Derman Virtual instrument pilot: an improved method and system for navigation and control of fixed wing aircraft

Also Published As

Publication number Publication date
DE60304053T2 (en) 2006-11-09
JP4246155B2 (en) 2009-04-02
DE60304053D1 (en) 2006-05-11
CN1688868A (en) 2005-10-26
WO2004031833A3 (en) 2004-07-15
EP1546655B1 (en) 2006-03-15
US20040113816A1 (en) 2004-06-17
JP2006501097A (en) 2006-01-12
ATE320588T1 (en) 2006-04-15
US7062364B2 (en) 2006-06-13
WO2004031833A2 (en) 2004-04-15
AU2003266895A1 (en) 2004-04-23
ES2260639T3 (en) 2006-11-01
AU2003266895A8 (en) 2004-04-23
CN100547353C (en) 2009-10-07
BR0314374B1 (en) 2015-01-13
CA2494050C (en) 2011-10-18
BR0314374A (en) 2005-11-29
EP1546655A2 (en) 2005-06-29

Similar Documents

Publication Publication Date Title
CA2494050A1 (en) Electronic non-linear aircraft dynamic parameter display
EP2525281B1 (en) Improved progress bar
CN101467012B (en) Electronic balance
US6208944B1 (en) Method for determining and displaying spectra for vibration signals
CN101231830A (en) Method for generating LCD device gamma correction table
US8669986B2 (en) Method for visualizing data extracted from a population of data
KR100458593B1 (en) Method and apparatus to control power of the address data for plasma display panel and a plasma display panel device having that apparatus
GB2380112A (en) Method and apparatus for zooming on non-positional display attributes
US20040075660A1 (en) Apparatus and method for line drawing
EP2631727B1 (en) Multivalue bar graph displays and methods of implementing same
CN105139345B (en) A kind of automatic search method of high-quality non-standard gamma curve
EP2672240B1 (en) Campbell diagram displays and methods and systems for implementing same
GB2604539A (en) Hierachical building performance dashboard with key performance indicators alongside relevant service cases
US20060235639A1 (en) Method for calculating temperature as a function of time
CN108760986A (en) The prediction technique of viscoelastic material dynamic antivibration dissipation characteristic
JP6379278B2 (en) Data processing apparatus, program, and recording medium for managing data measured in ship
CN106351836B (en) Method and apparatus on helical-lobe compressor
US20070203619A1 (en) Method and apparatus for calculating engine power and best power
JPH0914180A (en) Method and device for detecting delivery flow rate of variable speed pump
US11181457B2 (en) Hydraulic and lubricating fluid contamination sensor system
CN101551417A (en) Real time operation specification calculation system that provides specifications to a user interface
US7443912B2 (en) Method and system for displaying the amplitude distortions of a transmission channel
WO2002007094A3 (en) Methods and apparatus for viewing information on a display
US20040254968A1 (en) Interpolation for waveform and vector displays
JPH0981112A (en) Graph display processing device and graph display processing method

Legal Events

Date Code Title Description
EEER Examination request
MKEX Expiry

Effective date: 20230926