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US-12618863-B2 - Algorithm for independent detection of probe blockages

US12618863B2US 12618863 B2US12618863 B2US 12618863B2US-12618863-B2

Abstract

A blockage detection system for detecting aircraft probe blockages includes a processor, a communication device, and computer-readable memory. The computer-readable memory encoded with instructions that, when executed by the processor, cause the system to execute a blockage detection algorithm. The processor receives a static pressure and an impact pressure from one or more aircraft probes. The processor converts the static pressure and the impact pressure to a correlating variable, via the blockage detection algorithm. The processor evaluates the correlating variable, via the blockage detection algorithm, to determine if a value of the correlating variable exceeds a threshold indicative of a blockage. The processor outputs a blockage indicator, to a receiving system in response to the correlating variable exceeding the first threshold indicative of a blockage. The processor is further able to determine if the blockage has cleared by reference to an external comparative pressure measurement.

Inventors

  • Jacob Meyer
  • Jacob Brown

Assignees

  • ROSEMOUNT AEROSPACE INC.

Dates

Publication Date
20260505
Application Date
20240220

Claims (20)

  1. 1 . A blockage detection system for detecting aircraft probe blockages, the system comprising: a processor; a communication device operably connected to the processor; computer-readable memory operably connected to the processor, the computer-readable memory encoded with instructions that, when executed by the processor, cause the system to: receive a static pressure and an impact pressure from one or more aircraft probes; convert the static pressure and the impact pressure to a correlating variable, via a blockage detection algorithm; evaluate the correlating variable, via the blockage detection algorithm, to determine if a value of the correlating variable exceeds a threshold indicative of a blockage; and output a blockage indicator, via the communication device, to a receiving system in response to the correlating variable exceeding the first threshold indicative of a blockage.
  2. 2 . The system of claim 1 , wherein the one or more aircraft probes include a pitot tube and a static pressure port, the pitot tube and the static pressure port being spaced apart from each other and mounted on the side of an aircraft.
  3. 3 . The system of claim 1 , wherein the one or more aircraft probes include a pitot-static probe comprising a pitot tube and a static port.
  4. 4 . The system of claim 1 , wherein the computer-readable memory is further encoded with instructions that, when executed by the one or more processors, cause the system to: convert the correlating variable to the frequency domain; and remove, via the blockage detection algorithm, nuisance data, the nuisance data determined by examining flight test data.
  5. 5 . The system of claim 1 , wherein the threshold indicative of the blockage is determined by evaluating flight test data and flight simulation data.
  6. 6 . The system of claim 1 , wherein the threshold indicative of the blockage is specific to an architecture of the aircraft and to a mounting location of the one or more aircraft probes.
  7. 7 . The system of claim 1 , wherein the computer-readable memory is further encoded with instructions that, when executed by the one or more processors, cause the system to: receive an external comparative pressure, wherein the external comparative pressure is measured by an additional probe external to the one or more aircraft probes; and evaluate whether the blockage is cleared based upon the external comparative pressure.
  8. 8 . The system of claim 7 , wherein the additional probe external to the one or more aircraft probes is a static pressure port mounted on an opposite side of the aircraft from a mounting location of the one or more aircraft probes.
  9. 9 . The system of claim 1 , wherein the blockage detection system is housed within the one or more aircraft probes.
  10. 10 . The system of claim 9 , wherein the one or more aircraft probes are pitot-static probes, the pitot-static probes comprising an internal air data computer.
  11. 11 . The system of claim 1 , wherein the blockage detection system is housed within a vehicle management computer.
  12. 12 . The system of claim 11 , wherein the vehicle management computer is digitally connected to the communication device.
  13. 13 . The system of claim 1 , wherein the correlating variable is calculated, in part, by dividing the static pressure by the impact pressure.
  14. 14 . The system of claim 13 , wherein the correlating variable is calculated, in part, by evaluating the derivative of the static pressure divided by the impact pressure with respect to time.
  15. 15 . The system of claim 14 , wherein the correlating variable is calculated, in part, by converting the derivative of the static pressure divided by the impact pressure with respect to time to the frequency domain via power spectrum estimations.
  16. 16 . A method for detecting aircraft probe blockages, the method comprising: receiving a static pressure and an impact pressure from one or more aircraft probes; converting the static pressure and the impact pressure to a correlating variable, via a blockage detection algorithm; evaluating the correlating variable, via the blockage detection algorithm, to determine if a value of the correlating variable exceeds a threshold indicative of a blockage; and outputting a blockage indicator, via a communication device, to a receiving system in response to the correlating variable exceeding the first threshold indicative of a blockage.
  17. 17 . The method of claim 16 , further comprising: receiving an external comparative pressure, wherein the external comparative pressure is measured by an additional probe external to the one or more aircraft probes; and evaluating whether the blockage is cleared based upon the external comparative pressure.
  18. 18 . The method of claim 17 , wherein the additional probe external to the one or more aircraft probes is a static pressure port mounted on an opposite side of the aircraft from a mounting location of the one or more aircraft probes.
  19. 19 . The method of claim 16 , wherein the blockage detection system is housed within the one or more aircraft probes.
  20. 20 . The method of claim 19 , wherein the one or more aircraft probes are pitot-static probes, the pitot-static probes comprising an internal air data computer.

Description

BACKGROUND Aircraft can contain several air data probes for measuring parameters such as static and impact pressure. While measuring such parameters, air data probes are susceptible to various failure modes which can cause erroneous data readings or loss of air data readings altogether. One such failure mode is a probe blockage condition that can occur due to conditions such as icing, excessive moisture, volcanic ash, sand/dirt, insect nesting, and/or other such conditions. The erroneous nature or loss of such readings can have downstream impacts on systems within the aircraft that consume such readings. Therefore, it is desirable to have a system which indicates when such air data probes are in a failure mode, such that consuming systems do not rely on the erroneous readings. SUMMARY A blockage detection system for detecting aircraft probe blockages includes a processor. The system further includes a communication device operably connected to the processor. The system further includes computer-readable memory operably connected to the processor, the computer-readable memory encoded with instructions that, when executed by the processor, cause the system to perform the following steps. The system receives a static pressure and an impact pressure from one or more aircraft probes. The system converts the static pressure and the impact pressure to a correlating variable, via a blockage detection algorithm. The system evaluates the correlating variable, via the blockage detection algorithm, to determine if a value of the correlating variable exceeds a threshold indicative of a blockage. The system outputs a blockage indicator, via the communication device, to a receiving system in response to the correlating variable exceeding the first threshold indicative of a blockage. A method for detecting aircraft probe blockages includes receiving a static pressure and an impact pressure from one or more aircraft probes. The method further includes converting the static pressure and the impact pressure to a correlating variable, via a blockage detection algorithm. The method further includes evaluating the correlating variable, via the blockage detection algorithm, to determine if a value of the correlating variable exceeds a threshold indicative of a blockage. The method further includes outputting a blockage indicator, via the communication device, to a receiving system in response to the correlating variable exceeding the first threshold indicative of a blockage. BRIEF DESCRIPTION OF THE DRAWINGS FIG. 1 is a diagram of a system for detecting a blockage on a probe. FIG. 2A is a schematic diagram of an air data system architecture including an algorithm for detecting probe blockage. FIG. 2B is a schematic diagram of an alternative air data system architecture including the algorithm for detecting probe blockages. FIG. 3 is an example graph depicting a correlating variable response indicative of a blockage condition. FIG. 4 is a flowchart depicting a method for detecting a blockage within a probe. DETAILED DESCRIPTION The techniques of this disclosure utilize an algorithm housed within an air data computer to determine whether a pressure probe is experiencing a blockage. The system operates by applying a blockage detection algorithm. The blockage detection algorithm receives the static pressure and the impact pressure measured by, for example, a pitot-static probe, and converts such measured values to a single correlating variable. The system then evaluates the correlating variable to determine if it exceeds a threshold indicative of a blockage condition. The techniques of this disclosure do not rely on external sources to determine a blockage condition, and instead use probe measurements from the probe being evaluated to detect a blockage. Upon detecting a blockage, the system can conduct further analysis, using measurements received from one or more additional external probes, to determine whether the blockage has cleared. FIG. 1 is a diagram of system 100 for detecting a blockage on a probe. System 100 includes aircraft probe(s) 102, blockage detection system 104, and consuming systems 106. Blockage detection system 104 includes processor 108, communication device 110, and computer readable memory 112. Computer readable memory includes a plurality of executable modules including data receiving module 114, correlating variable module 116, evaluation module 118, blockage indication module 120, and blockage clearance module 122. Processor 108, in some examples, is configured to implement functionality and/or process instructions for execution within system 100. For instance, processor 108 can be capable of processing instructions stored in computer-readable memory 112. Examples of processor 108 can include any one or more of a microprocessor, a controller, a digital signal processor (DSP), an application specific integrated circuit (ASIC), a field-programmable gate array (FPGA), or other equivalent discrete or integrated