CA2494050A1 - Electronic non-linear aircraft dynamic parameter display - Google Patents
Electronic non-linear aircraft dynamic parameter display Download PDFInfo
- 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
Links
- 238000000034 method Methods 0.000 claims abstract 10
- 239000000446 fuel Substances 0.000 claims 2
- 239000002253 acid Substances 0.000 claims 1
Classifications
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01D—MEASURING 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
- G01D7/00—Indicating measured values
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01C—MEASURING DISTANCES, LEVELS OR BEARINGS; SURVEYING; NAVIGATION; GYROSCOPIC INSTRUMENTS; PHOTOGRAMMETRY OR VIDEOGRAMMETRY
- G01C23/00—Combined 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.
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.
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.
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.
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)
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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 |
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FR2742226B1 (en) * | 1995-12-08 | 1998-02-06 | Eurocopter France | VERTICAL ALTITUDE AND SPEED INDICATOR FOR AIRCRAFT |
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-
2003
- 2003-09-26 AT AT03747776T patent/ATE320588T1/en not_active IP Right Cessation
- 2003-09-26 WO PCT/CA2003/001424 patent/WO2004031833A2/en active IP Right Grant
- 2003-09-26 DE DE60304053T patent/DE60304053T2/en not_active Expired - Lifetime
- 2003-09-26 AU AU2003266895A patent/AU2003266895A1/en not_active Abandoned
- 2003-09-26 US US10/670,780 patent/US7062364B2/en not_active Expired - Lifetime
- 2003-09-26 ES ES03747776T patent/ES2260639T3/en not_active Expired - Lifetime
- 2003-09-26 CN CNB038236753A patent/CN100547353C/en not_active Expired - Lifetime
- 2003-09-26 CA CA2494050A patent/CA2494050C/en not_active Expired - Lifetime
- 2003-09-26 JP JP2004540400A patent/JP4246155B2/en not_active Expired - Lifetime
- 2003-09-26 BR BRPI0314374-0A patent/BR0314374B1/en active IP Right Grant
- 2003-09-26 EP EP03747776A patent/EP1546655B1/en not_active Expired - Lifetime
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 |
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Legal Events
Date | Code | Title | Description |
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EEER | Examination request | ||
MKEX | Expiry |
Effective date: 20230926 |