GB2478522A - Aircraft pitot blockage / static warning system - Google Patents

Aircraft pitot blockage / static warning system Download PDF

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Publication number
GB2478522A
GB2478522A GB1003591A GB201003591A GB2478522A GB 2478522 A GB2478522 A GB 2478522A GB 1003591 A GB1003591 A GB 1003591A GB 201003591 A GB201003591 A GB 201003591A GB 2478522 A GB2478522 A GB 2478522A
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United Kingdom
Prior art keywords
tube
monitored
transducer
control module
signal
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
GB1003591A
Other versions
GB201003591D0 (en
GB2478522B (en
Inventor
Nicholas Peter Haddock
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Individual
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Individual
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Filing date
Publication date
Application filed by Individual filed Critical Individual
Priority to GB1003591.3A priority Critical patent/GB2478522B/en
Publication of GB201003591D0 publication Critical patent/GB201003591D0/en
Publication of GB2478522A publication Critical patent/GB2478522A/en
Application granted granted Critical
Publication of GB2478522B publication Critical patent/GB2478522B/en
Active legal-status Critical Current
Anticipated expiration legal-status Critical

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Classifications

    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
    • G01M3/00—Investigating fluid-tightness of structures
    • G01M3/02—Investigating fluid-tightness of structures by using fluid or vacuum
    • G01M3/04—Investigating fluid-tightness of structures by using fluid or vacuum by detecting the presence of fluid at the leakage point
    • G01M3/24—Investigating fluid-tightness of structures by using fluid or vacuum by detecting the presence of fluid at the leakage point using infrasonic, sonic, or ultrasonic vibrations
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D45/00—Aircraft indicators or protectors not otherwise provided for
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
    • G01M3/00—Investigating fluid-tightness of structures
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
    • G01N29/00—Investigating or analysing materials by the use of ultrasonic, sonic or infrasonic waves; Visualisation of the interior of objects by transmitting ultrasonic or sonic waves through the object
    • G01N29/02—Analysing fluids
    • G01N29/032—Analysing fluids by measuring attenuation of acoustic waves
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
    • G01N29/00—Investigating or analysing materials by the use of ultrasonic, sonic or infrasonic waves; Visualisation of the interior of objects by transmitting ultrasonic or sonic waves through the object
    • G01N29/04—Analysing solids
    • G01N29/06—Visualisation of the interior, e.g. acoustic microscopy
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
    • G01N29/00—Investigating or analysing materials by the use of ultrasonic, sonic or infrasonic waves; Visualisation of the interior of objects by transmitting ultrasonic or sonic waves through the object
    • G01N29/04—Analysing solids
    • G01N29/12—Analysing solids by measuring frequency or resonance of acoustic waves
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
    • G01N29/00—Investigating or analysing materials by the use of ultrasonic, sonic or infrasonic waves; Visualisation of the interior of objects by transmitting ultrasonic or sonic waves through the object
    • G01N29/34—Generating the ultrasonic, sonic or infrasonic waves, e.g. electronic circuits specially adapted therefor
    • G01N29/348—Generating the ultrasonic, sonic or infrasonic waves, e.g. electronic circuits specially adapted therefor with frequency characteristics, e.g. single frequency signals, chirp signals
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01P—MEASURING LINEAR OR ANGULAR SPEED, ACCELERATION, DECELERATION, OR SHOCK; INDICATING PRESENCE, ABSENCE, OR DIRECTION, OF MOVEMENT
    • G01P21/00—Testing or calibrating of apparatus or devices covered by the preceding groups
    • G01P21/02—Testing or calibrating of apparatus or devices covered by the preceding groups of speedometers
    • G01P21/025—Testing or calibrating of apparatus or devices covered by the preceding groups of speedometers for measuring speed of fluids; for measuring speed of bodies relative to fluids
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01P—MEASURING LINEAR OR ANGULAR SPEED, ACCELERATION, DECELERATION, OR SHOCK; INDICATING PRESENCE, ABSENCE, OR DIRECTION, OF MOVEMENT
    • G01P5/00—Measuring speed of fluids, e.g. of air stream; Measuring speed of bodies relative to fluids, e.g. of ship, of aircraft
    • G01P5/14—Measuring speed of fluids, e.g. of air stream; Measuring speed of bodies relative to fluids, e.g. of ship, of aircraft by measuring differences of pressure in the fluid
    • G01P5/16—Measuring speed of fluids, e.g. of air stream; Measuring speed of bodies relative to fluids, e.g. of ship, of aircraft by measuring differences of pressure in the fluid using Pitot tubes, e.g. Machmeter
    • G01P5/165—Arrangements or constructions of Pitot tubes
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
    • G01N2291/00—Indexing codes associated with group G01N29/00
    • G01N2291/04—Wave modes and trajectories
    • G01N2291/048—Transmission, i.e. analysed material between transmitter and receiver

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  • Physics & Mathematics (AREA)
  • General Physics & Mathematics (AREA)
  • Analytical Chemistry (AREA)
  • Health & Medical Sciences (AREA)
  • Life Sciences & Earth Sciences (AREA)
  • Chemical & Material Sciences (AREA)
  • Biochemistry (AREA)
  • General Health & Medical Sciences (AREA)
  • Immunology (AREA)
  • Pathology (AREA)
  • Acoustics & Sound (AREA)
  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Geophysics And Detection Of Objects (AREA)
  • Investigating Or Analyzing Materials By The Use Of Ultrasonic Waves (AREA)

Abstract

The invention provides a system for detecting blockages or other anomalies in pitot tube (1) and static tube (14, fig. 2) of aircraft whether the aircraft is in the air, or on the ground, enabling the pilot, or the auto pilot, to take the necessary action in order to keep the aircraft safe. The system comprises a transducer (10) configured to transmit acoustic signals and a transducer (7) configured to receive the signals from the transducer (10) after the signal has been altered by the transmission characteristics of the tube (3) being monitored. The system also comprises a control module (9) configured to analyse the characteristics of the received signals at different frequencies whereby changes to the characteristics with frequency will indicate an anomaly within the tube (3) or environment being monitored by the system. The invention may comprise a single boxed unit, see fig. 3.

Description

Aircraft Pitot/Static Warning System
Description
This invention is concerned with improvements in or relating to aircraft pitot/static warning system and is particularly concerned with warning systems indicating a blockage of a pitot port and/or static port.
Most aircraft employ a system of external air pressure ports in order to display information to the pilot about air speed and altitude. There are typically two types of port. Firstly there is a ram air pitot tube which faces into the air stream, the internal pressure increases in relation to air speed. Secondly there is a static port, which is effectively an outward facing orifice flush with the fuselage.
The pressure which is created by the pitot tube(s) is transmitted via tubing to cockpit instruments, as is the static external pressure derived by the static port(s). If one or more of the pitot or static ports becomes blocked, or is blocked prior to take off there is currently no means of identifying that there is a blockage. The cockpit instruments will continue to register but will display inaccurate information to the pilot.
The present invention solves this problem by giving a clear indication that one or more of the external ports is blocked and the pilot (or indeed autopilot) can account for the error. As part of pre flight checks the invention will ensure that taking off with a blocked pitot or static port is avoided.
If the aircraft is already in flight when a port is registered as blocked, the pilot (or autopilot) will be warned and can take the appropriate action rather than continue to read incorrect instrument display.
The invention utilises sound waves, which are created by a transducer and delivered into the tubing which links the external pitot and static ports to the cockpit instruments. A microphone is connected at another location along the same tube where the resulting sound waves are received and processed by an electronic control unit. The invention relies on the resonant qualities of sound waves within a tube and as such, through analysis of the sound waves, which are amplified and processed, a clear indication of the status of the external ports are received and displayed for the pilot.
There now follows by way of example of the invention a detail description, which is to be read with reference to the accompanying drawings in which:-Figure 1 is a diagrammatic representation of a first embodiment provided by the invention; and, Figure 2 is a diagrammatic representation of a second embodiment provided by the invention; and, Figure 3 is a diagrammatic representation of a third embodiment provided by the invention.
Figure 1 shows an external ram air pitot tube 1 for measuring the air speed of an aircraft in flight. The pitot tube 1 is mounted on the outside of the aircraft fuselage 2 and connected to a pressure tube 3. The pressure tube 3 has a microphone 7 connected to it via a tee piece' 4. Further along the tube 3 is connected to a transducer 10 via an additional tee piece 5.
The pressure tube 3 is then routed on to the airspeed indicator 6. An electronic control unit 9 delivers audio frequency sound waves to the transducer 10 via a connecting cable 11; this creates resultant sound waves within the pressure tube 3. The microphone 7 receives the resultant waves which are transmitted via a connecting cable 8 to an electronic control unit 9 for analysis, the status is sent via a connecting cable 12 to a cockpit display and/or the autopilot.
Figure 2 shows a similar installation to that in Figure 1 for measuring the air pressure of an aircraft in flight; in this case, a static port 14 is provided, which port 14 has it's inlet flush with the aircraft fuselage 2. The connecting tube 3 in this case is connected to an altimeter 13.
It is not a requirement of the invention that the transducer 10 or receiving microphone 7 are mounted at any particular location along the tube 3 since the resonant qualities of the tube 3 are a function of the tube length, air temperature, pressure and most importantly whether it is an open or blocked.
The invention can be installed on any static or pressurised air delivery tube or pipe system where knowledge of an open or blocked tube is required either for an in flight aircraft or for ground based applications.
The electronic control unit 9 of the invention employs both spot frequency generation as well as swept frequency generation of sound waves in order to map the resonant characteristics of the tube 3.
In figure 3 the invention is shown as a single boxed unit 13 in which is contained all the necessary components required to perform the function of the invention and thus removing the need for two separate connections to the existing pressure tube. This embodiment has a single inlet port and a single outlet port with suitable compression fittings to install between an existing or newly installed pitot or static port, and the pressure tube. The unit 13 has a data port 12 to be used in order to power the control unit 9 and also to send data regarding the status of the tube. The port 12 also serves to allow initial installation setup parameters to be programmed. The unit 13 containing the control board 9, pressure tube 3, transducer 10, microphone 7 and required interconnecting cables is hermetically sealed and free space within filled with a suitable potting compound to render it pressure tight and thus allowing operation through a wide range of operating environments.
The invention, by way of monitoring the acoustic changes within the pitot or static ports, can work in both noisy and quiet environments since the generated sound waves will be used for analysis where the noise levels within the tube are low. Noise created by the fast moving air stream at the external port will then itself be monitored once the amplitude of this noise becomes greater than that of the signal generated by the transducer within the invention. Once again, if a blockage occurs at the external port the noise level will decrease relative to the amount and type of blockage and the control unit within the invention will report this.

Claims (11)

  1. Claims 1. A system for detecting anomalies within a tube, the system comprising: a transducer configured to transmit acoustic signals and a transducer configured to receive the signals from the transmitting transducer once that signal has been altered by the acoustic transmission characteristics of the tube being monitored; the system also comprising a control module configured to analyse the characteristics of the received signals at different frequencies whereby changes to the characteristics with frequency will indicate an anomaly within the tube or environment being monitored by the system.
  2. 2. A system according to Claim 1, characterised in that the control module generates a continuously varying audio frequency coupled to the transducer in order to transmit an acoustic signal at the said audio frequencies into the tube.
  3. 3. A system according to Claim 1, characterised in that the control module generates an audio frequency of fixed frequency and amplitude in order to transmit said audio signal into the tube by use of the transducer.
  4. 4. A system according to any one of Claims 1 to 3, characterised in that the control module is configured to analyse the signal characteristics at different frequencies of the received signal in order to ascertain the integrity, blockage or other anomaly within the tube being monitored.
  5. 5. A system according to any one of Claims 1 to 3, characterised in that the control module is configured to analyse the amplitude of an acoustic signal at specific frequency within a tube * * in order to ascertain the integrity, blockage or other anomaly within the tube being monitored. I. *4S I *
  6. 6. A system according to any one of Claims 1 to 5, characterised in that the signal generated from the transducer and the harmonic results are acoustic signals.S *S**. * S
  7. 7. A system according to any one of Claims 1 to 6, characterised in that the control module monitors the ambient acoustic noise within the tube being monitored. p
  8. 8. A system according to any one of Claims 1 to 7, characterised in that the tube being monitored is a conventional pitot tube of an aircraft whether in flight or stationary on the ground.
  9. 9. A system according to any one of Claims I to 7, characterised in that the tube being monitored is a conventional static tube of an aircraft whether in flight or stationary on the ground.
  10. 10. A system substantially as described with reference to Figures 1 and 2 of the accompanying drawings.
  11. 11. A system substantially as described with reference to Figure 3 of the accompanying drawings.II I.... * I * IS * *I S S...I *.S*S S..S SAmendments to the claims have been filed as follows Claims 1. A system for detecting anomalies within a pitot tube as hereinbefore defined, the system comprising: a transducer configured to transmit acoustic signals and a transducer configured to receive the signals from the transmitting transducer once that signal has been altered by the acoustic transmission characteristics of the pitot tube being monitored; the system also comprising a control module configured to analyse the characteristics of the received signals at different frequencies whereby changes to the characteristics with frequency will indicate an anomaly within the pitot tube being monitored by the system.2. A system according to Claim 1, characterised in that the control module generates a continuously varying audio frequency coupled to the transducer in order to transmit an acoustic signal at the said audio frequencies into the pitot tube.3. A system according to Claim 1, characterised in that the control module generates an audio frequency of fixed frequency and amplitude in order to transmit said audio signal into the pitot tube by use of the transducer.4. A system according to any one of Claims ito 3, characterised in that the control module is configured to analyse the signal characteristics at different frequencies of the received signal in order to ascertain the integrity, blockage or other anomaly within the pitot tube being monitored. * SS* 55555 * * 5. A system according to any one of Claims 1 to 3, characterised in that the control module is * configured to analyse the amplitude of an acoustic signal at specific frequency within a tube * ** in order to ascertain the integrity, blockage or other anomaly within the pitot tube being monitored. * S. * * 5 *.5 *6. A system according to any one of Claims 1 to 5, characterised in that the signal generated * : * from the transducer and the harmonic results are acoustic signals.7. A system according to any one of Claims 1 to 6, characterised in that the control module monitors the ambient acoustic noise within the pitot tube being monitored.8. A system according to any one of Claims 1 to 7, characterised in that the tube being monitored is a conventional ram air pitot tube of an aircraft whether in flight or stationary on the ground.9. A system according to any one of Claims 1 to 7, characterised in that the tube being monitored is a conventional static port tube of an aircraft whether in flight or stationary on the ground.10. A system substantially as described with reference to Figures 1 and 2 of the accompanying drawings.11. A system substantially as described with reference to Figure 3 of the accompanying drawings.SS..... * aSI.... * . * SS * S S * *I * *S * . S *SS *S S..S
GB1003591.3A 2010-03-04 2010-03-04 Aircraft pitot/static warning system Active GB2478522B (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
GB1003591.3A GB2478522B (en) 2010-03-04 2010-03-04 Aircraft pitot/static warning system

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB1003591.3A GB2478522B (en) 2010-03-04 2010-03-04 Aircraft pitot/static warning system

Publications (3)

Publication Number Publication Date
GB201003591D0 GB201003591D0 (en) 2010-04-21
GB2478522A true GB2478522A (en) 2011-09-14
GB2478522B GB2478522B (en) 2013-10-30

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Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20120118037A1 (en) * 2010-05-07 2012-05-17 Thales Device for Checking a Flow Pressure Measurement Probe, and Probe Comprising the Device
EP2878960A1 (en) * 2013-11-29 2015-06-03 Thales Device for controlling a probe for measuring the pressure of a flow
EP2878961A1 (en) * 2013-11-29 2015-06-03 Thales Method for controlling a probe for measuring the pressure of a flow
GB2583750A (en) * 2019-05-08 2020-11-11 Peter Haddock Nicholas Method for monitoring the status of a fluid flow measurement instrument

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US10948511B2 (en) 2018-03-05 2021-03-16 Honeywell International Inc. Apparatus and method for verifying operation of air data probes

Citations (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPS5985953A (en) * 1982-11-08 1984-05-18 Honda Motor Co Ltd Through hole inspecting device for manifold
GB2191860A (en) * 1986-06-19 1987-12-23 Central Electr Generat Board Method of detecting an obstruction or a discontinuity in a tube
US4811595A (en) * 1987-04-06 1989-03-14 Applied Acoustic Research, Inc. System for monitoring fluent material within a container
US5331967A (en) * 1993-02-05 1994-07-26 Playa De Los Vivos S.A. Tracheal intubation monitoring apparatus and method
WO2001091843A1 (en) * 2000-05-26 2001-12-06 Purdue Research Foundation Acoustical guidance and monitoring system for endotrachea
WO2003048713A1 (en) * 2001-11-30 2003-06-12 The Victoria University Of Manchester Remote pipeline acoustic inspection
US20050193818A1 (en) * 2004-02-03 2005-09-08 University Of Denver Method and Apparatus for Acoustic Sensing of Structures
US20070280046A1 (en) * 2006-05-31 2007-12-06 The Boeing Company Feedback protection of pressure measurement devices
EP2273275A1 (en) * 2009-07-09 2011-01-12 Lutz Nolte Pressure Probe

Patent Citations (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPS5985953A (en) * 1982-11-08 1984-05-18 Honda Motor Co Ltd Through hole inspecting device for manifold
GB2191860A (en) * 1986-06-19 1987-12-23 Central Electr Generat Board Method of detecting an obstruction or a discontinuity in a tube
US4811595A (en) * 1987-04-06 1989-03-14 Applied Acoustic Research, Inc. System for monitoring fluent material within a container
US5331967A (en) * 1993-02-05 1994-07-26 Playa De Los Vivos S.A. Tracheal intubation monitoring apparatus and method
WO2001091843A1 (en) * 2000-05-26 2001-12-06 Purdue Research Foundation Acoustical guidance and monitoring system for endotrachea
WO2003048713A1 (en) * 2001-11-30 2003-06-12 The Victoria University Of Manchester Remote pipeline acoustic inspection
US20050193818A1 (en) * 2004-02-03 2005-09-08 University Of Denver Method and Apparatus for Acoustic Sensing of Structures
US20070280046A1 (en) * 2006-05-31 2007-12-06 The Boeing Company Feedback protection of pressure measurement devices
EP2273275A1 (en) * 2009-07-09 2011-01-12 Lutz Nolte Pressure Probe

Cited By (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20120118037A1 (en) * 2010-05-07 2012-05-17 Thales Device for Checking a Flow Pressure Measurement Probe, and Probe Comprising the Device
EP2878960A1 (en) * 2013-11-29 2015-06-03 Thales Device for controlling a probe for measuring the pressure of a flow
EP2878961A1 (en) * 2013-11-29 2015-06-03 Thales Method for controlling a probe for measuring the pressure of a flow
FR3014202A1 (en) * 2013-11-29 2015-06-05 Thales Sa METHOD FOR MONITORING A PRESSURE MEASUREMENT PROBE OF A FLOW
FR3014204A1 (en) * 2013-11-29 2015-06-05 Thales Sa DEVICE FOR MONITORING A PRESSURE MEASURING PROBE OF A FLOW
US9846177B2 (en) 2013-11-29 2017-12-19 Thales Method for checking a probe for measuring the pressure of a flow
GB2583750A (en) * 2019-05-08 2020-11-11 Peter Haddock Nicholas Method for monitoring the status of a fluid flow measurement instrument
GB2583750B (en) * 2019-05-08 2022-11-09 Intelligent Sensors Ltd Method for monitoring the status of a fluid flow measurement instrument

Also Published As

Publication number Publication date
GB201003591D0 (en) 2010-04-21
GB2478522B (en) 2013-10-30

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