Aircraft probe with removable and replaceable embedded electronics

An aircraft probe includes a base, a strut that extends from the base, at least one port, and an electronics assembly insertable into the strut and removable from the strut. The electronics assembly includes at least one pressure sensor that is pneumatically connected to the at least one port to sense a first pressure when in the inserted position.

BACKGROUND

The present invention relates generally to air data probes, and in particular to embedded electronics for air data probes.

Current air data systems utilize pneumatic connections between probes and remotely located air data transducers or air data computers. Alternative architectures utilize integrated probes and air data computers, but these integrated probes can significantly intrude into the fuselage, and in some applications this intrusion is prohibitive based on conflicting structure or components of the aircraft. Current air data systems with pneumatic connections to air data transducers or air data computers may also suffer from inadequate ability to detect degraded performance due to architecture definition. It is desirable to provide computational and other digital capabilities at the air data probe without intruding into the fuselage while also simplifying maintenance.

SUMMARY

In one example embodiment, an aircraft probe includes a base, a strut that extends from the base, at least one port, and an electronics assembly insertable into the strut and removable from the strut. The electronics assembly includes at least one pressure sensor that is pneumatically connected to the at least one port to sense a first pressure when in an inserted position.

In another example embodiment, an electronics assembly insertable into, and removable from, an aircraft probe, includes a pressure sensor and an input/output interface. The pressure sensor is positioned to be pneumatically connected with a port of the aircraft probe while the electronics assembly is inserted into the aircraft probe. The pressure sensor is configured to sense a pressure, and the input/output interface is configured to provide the sensed pressure to a data bus of an aircraft that includes the aircraft probe.

In another example embodiment, an aircraft air data system includes an aircraft data bus, consuming systems connected to the aircraft data bus, and an aircraft probe. The aircraft probe includes a base connected to the aircraft, a strut that extends from the base, a port, and an electronics assembly positioned within the strut that includes at least a pressure sensor pneumatically connected to the port to sense a pressure. The electronics assembly is removable from the aircraft probe through the base.

DETAILED DESCRIPTION

A fully integrated digital probe is disclosed herein that includes removable and replaceable electronics. The digital probe does not require external transducer(s). Pressure sensing for the probe is performed integral to the probe by the replaceable electronics. An electronics card, for example, may be slidably inserted into a strut of the probe such that the electronics card is easily replaceable. The electronics card may connect through the base of the probe, which may be electronically connected to an aircraft interface connector.

FIG. 1is a schematic diagram that illustrates an aircraft10that includes air data probe12. Probe12may be a standalone probe, or may be part of a larger air data system that includes one or more further sensors and/or probes. Probe12may be positioned and configured to sense one or more pressures external to aircraft10, for example. The sensed pressure(s) may be used to calculate various parameters including, but not limited to, airspeed, altitude, angle of attack (AOA), and angle of sideslip (AOS). These parameters may be calculated by probe12, or by consuming systems14, which may be one or more computing systems located in aircraft10in an avionics or other electronics bay, for example. While illustrated as a pitot static probe, air data probe12may be any probe positioned on the exterior of aircraft10and may have any desirable shape based on the needs of the probe.

Air data probe12is connected to communicate with consuming systems14via aircraft data bus16. Aircraft data bus16can take the form of direct electrical couplings and/or data bus couplings configured to communicate according to one or more communication protocols, such as the Aeronautical Radio, Incorporated (ARINC)429communication protocol, controller area network (CAN) bus communication protocol, military standard 1553 (MIL-STD-1553) communication protocol, Ethernet, or other analog or digital communication protocols.

Air data probe12connects to aircraft data bus16without significant intrusion into the fuselage of aircraft10. Prior art systems utilized integrated probes and/or air data computers, but the structure of these devices, particularly the electronics, intruded significantly into the fuselage. This intrusion can be prohibitive for use on some aircraft due to conflicting structure. In contrast, probe12includes embedded electronics that are located within a strut of the probe, for example. Thus, significant intrusion into the fuselage of aircraft10by probe12is eliminated.

FIGS. 2A and 2Bare schematic block diagrams of aircraft probe12having removable electronics card20.FIG. 2Aillustrates removable electronics card20in the removed position, andFIG. 2Billustrates removable electronics card20in the inserted position. Probe12includes strut22that extends from base24, and barrel portion25that includes ports26,28, and30. Removable electronics card20includes interface32, control and input/output (IO) circuit34, pressure sensing modules36a-36c, and health monitoring circuit38. Each pressure sensing module36a-36cincludes respective pressure sensing control circuit40a-40c, respective pressure sensors42a-42c, and respective interface circuits44a-44c. Health monitoring circuit38includes a health monitoring application specific integrated circuit (ASIC)46, for example. Removable electronics card20also includes pneumatic connectors48a,48b, and48cwhich provide pneumatic connection to respective pressure sensors42a,42b, and42c. Temperature sensor50is positioned within barrel portion25and connected to provide a sensed temperature to health monitoring circuit38. Pneumatic connections52a,52b, and52care configured to provide a pneumatic connection between ports26,28, and30, and respective pressure sensors42a,42b, and42c.

Removable electronics card20is configured to slide in and out of probe12. This allows for easy maintenance of the electronics of probe12, for example.FIG. 2Aillustrates removable electronics card20removed from probe12. Other components of removable electronics card20may also be easily replaceable. For example, each pressure sensing module36a-36cmay be swappable so that in the event of a failure of one of the modules, the respective module may be easily replaced, without requiring replacement of the entire removable electronics card20. This way, if any of the electronics of probe12fail or otherwise need maintenance, the failed components may be easily replaced without needing to replace the entire probe.

FIG. 2Billustrates removable electronics card20in the inserted position, embedded within probe12. In the embodiment illustrated inFIGS. 2A and 2B, removable electronics card20slides into strut22of probe12through base24. This may be accomplished using rails and snaps, or any other method. In other embodiments, removable electronics card20may slide into probe12through another location on probe12. In the embodiment illustrated inFIG. 2B, when in the inserted position, only interface32extends below base24, which minimizes intrusion of the components of probe12into the aircraft fuselage. Interface32may connect to aircraft data bus16(FIG. 1), for example, to allow communication of data from probe12to consuming systems14(FIG. 1). In other embodiments, a small portion of electronics card20or other components may extend below base24.

While illustrated as including three ports26,28, and30, and three respective pressure sensors42a,42b, and42c, probe12may include any number of pressure sensing ports. In one example embodiment, removable electronics card20may include a single pressure sensing module36a, and probe12may include a single port, such as port26, for example. The single pressure sensor42amay be configured to sense a pitot pressure. In this example, the entire interior of probe26may be hollow, and pneumatic connections52a,52b, and52cmay be eliminated. Pressure sensor42amay be positioned anywhere on removable electronics card20, positioned within the hollow chamber of probe12, to sense the pitot pressure as the ambient pressure within strut22. In one example, pressure sensing electronics40amay be configured to convert the analog pressure signal from pressure sensor42ainto a digital signal, and condition the digital signal for transmission to aircraft consuming systems14on digital data bus16, eliminating the need for a separate control and IO circuit34. In other examples, a single pressure sensing module36amay be utilized in conjunction with a control and IO circuit34.

In the embodiment illustrated inFIGS. 2A and 2B, probe12includes several ports26,28, and30, each positioned to allow sensing of various pressures. As seen inFIG. 2B, removable electronics card20includes pressure sensors42a,42b, and42c, that are pneumatically connected to a respective port26,28, and30when removable electronics card20is in the inserted position. In one example embodiment, for example, pneumatic connections52a,52b, and52cmay be pneumatic tubes, and connection of respective ports26,28, and30and pressure sensors42a,42b, and42cmay be achieved through blind mating of each pneumatic tube52a,52b, and52cwith respective pneumatic connectors48a,48b, and48c. While not illustrated, pneumatic connectors48a,48b, and48cprovide a pneumatic connection to each respective pressure sensor42a,42b, and42c. A radial seal (not shown) may be positioned at the end of the pneumatic tube, for example, to facilitate blind mating with pneumatic connectors48a,48b, and48c. This way, removable card20is inserted, each respective pressure sensor42a,42b, and42cis pneumatically connected to the respective port26,28, and30.

In some embodiments, including the embodiment illustrated inFIGS. 2A and 2B, removable electronics card20includes control and IO circuit34. This circuit may include one or more of a microcontroller, microprocessor, ASIC, field programmable gate array (FPGA), one more volatile and/or non-volatile memories, data bus interface, and/or any other control or IO circuitry. In some embodiments, control and IO circuit34may only be configured to condition data sensed by pressure sensors42a-42cfor output on aircraft data bus16(FIG. 1) through interface32. In other embodiments, control and IO circuit34may be configured to execute software to perform functions that include, for example, calculating air data parameters using the sensed values from pressure sensors42a-42c.

In one embodiment, control and IO circuit34may be configured to determine an altitude, airspeed, and AOA from the sensed pressure data. For example, control and IO circuit34may receive raw pressure data from each of pressure sensors42a,42b, and42cthrough respective interface circuits44a,44b, and44c. Interface circuits44a,44b, and44cmay be configured, for example, to condition the sensed data for control and IO circuit34. Control and IO circuit34may determine a pitot pressure from the raw pressure data from pressure sensor42a, and static pressures from the raw pressure data from pressure sensors42band42c. Using the pitot pressure and the two static pressures, control and IO circuit34can then calculate an altitude, airspeed, and AOA based on the pitot and static pressures. These parameters may then be provided to consuming systems14on aircraft data bus16through interface32. In other embodiments, pressure sensing control circuit40a,40b, and40cmay be configured to convert the analog signal output by the respective pressure sensor42a,42b, and42cinto a digital signal.

While illustrated as a dedicated pressure sensor for each port, in other embodiments, one or more pressure sensing modules36a-36cmay include a differential pressure sensor pneumatically connected to two or more ports capable of sensing a differential pressure which may be used to determine, for example, AOA or AOS. While also illustrated as three ports and three pressure sensors, other embodiments may include six or more ports and six or more pressure sensors.

Temperature sensor50may be positioned within probe12for health monitoring, for example. During operation of probe12, icing conditions can occur. To prevent icing, probes often include heaters, such as resistive heating elements, routed throughout the probe to provide heating for the probe. However, the probe can become hotter than is necessary to prevent icing, and this heat can have adverse effects on the other components of the probe. Temperature sensor50may be positioned to sense the temperature within probe12and provide the sensed temperature to health monitoring circuit38. ASIC46of health monitoring circuit38may be configured, for example, to monitor the temperature of probe12to determine if the temperature is too hot or too cold, and provide instructions to adjust the control of the heating element. While not shown, removable electronics card20may also include one or more current sensors to monitor a current provided to a resistive heating element to provide health monitoring for the heater. Control and IO circuit34may also be configured to provide control for a resistive heating element of probe12.

Removable electronics card20provides significant advantages. The removability and replaceability of both removable electronics card20itself, as well as components of removable electronics card20improves maintenance and lifespan of probe12. Further, by embedding all electronics within strut22, the amount that probe12intrudes into the fuselage of aircraft10can be limited.

Discussion of Possible Embodiments

An aircraft probe includes a base, a strut that extends from the base, at least one port, and an electronics assembly insertable into the strut and removable from the strut. The electronics assembly includes at least one pressure sensor that is pneumatically connected to the at least one port to sense a first pressure when in an inserted position.

A further embodiment of the foregoing aircraft probe, wherein the electronics assembly is insertable into the strut through the base.

A further embodiment of any of the foregoing aircraft probes, wherein the electronics assembly includes an input/output interface configured to interface with an aircraft data bus, and wherein the electronics assembly is configured to provide the first pressure on the aircraft data bus.

A further embodiment of any of the foregoing aircraft probes, further including a barrel portion that extends from the strut, wherein the at least one port comprises a first port, a second port, and a third port positioned on the barrel portion.

A further embodiment of any of the foregoing aircraft probes, wherein the at least one pressure sensor includes a first pressure sensor, a second pressure sensor, and a third pressure sensor, and wherein, while in the inserted position, the first pressure sensor is pneumatically connected to the first port to sense the first pressure, the second pressure sensor is pneumatically connected to the second port to sense a second pressure, and the third pressure sensor is pneumatically connected to the third port to sense a third pressure.

A further embodiment of any of the foregoing aircraft probes, wherein the first pressure is a pitot pressure and wherein the second pressure and the third pressure are static pressures.

A further embodiment of any of the foregoing aircraft probes, wherein the electronics assembly further includes a control circuit configured to calculate one or more of an airspeed of an aircraft that includes the aircraft probe, an altitude of the aircraft, an angle of attack of the aircraft, and an angle of sideslip of the aircraft, and wherein the control circuit is configured to provide the airspeed, the altitude, the angle of attack, and the angle of sideslip on an aircraft data bus connected to the electronics assembly.

A further embodiment of any of the foregoing aircraft probes, further including a temperature sensor positioned within the probe and connected to provide a sensed temperature to the electronics assembly.

A further embodiment of any of the foregoing aircraft probes, wherein the electronics assembly includes a health monitoring circuit configured to monitor the sensed temperature to monitor a temperature of the probe.

An electronics assembly insertable into, and removable from, an aircraft probe, includes a first pressure sensor and an input/output interface. The first pressure sensor is positioned to be pneumatically connected with a first port of the aircraft probe while the electronics assembly is inserted into the aircraft probe. The first pressure sensor is configured to sense a first pressure, and the input/output interface is configured to provide the first pressure to a data bus of an aircraft that includes the aircraft probe.

A further embodiment of the foregoing electronics assembly, further including a second pressure sensor positioned to be pneumatically connected to a second port of the aircraft probe while the electronics assembly is inserted into the aircraft probe, wherein the second pressure sensor is configured to sense a second pressure, and wherein the first pressure is a pitot pressure and the second pressure is a static pressure.

A further embodiment of any of the foregoing electronics assemblies, further including a third pressure sensor positioned to be pneumatically connected to a third port of the aircraft probe while the electronics assembly is inserted into the aircraft probe, wherein the third pressure sensor is configured to sense a third pressure, and wherein the third pressure is a static pressure.

A further embodiment of any of the foregoing electronics assemblies, further including a control circuit configured to determine an airspeed, altitude, and an angle of attack from the first pressure, the second pressure, and the third pressure; wherein the input/output interface is further configured to provide the airspeed and the angle of attack on the data bus.

A further embodiment of any of the foregoing electronics assemblies, further including a health monitoring circuit configured to receive a sensed temperature from a temperature sensor positioned within the aircraft probe.

A further embodiment of any of the foregoing electronics assemblies, further including a pneumatic connector configured to mate with a pneumatic connection of the first port when the electronics assembly is inserted in the probe.

An aircraft air data system includes an aircraft data bus, consuming systems connected to the aircraft data bus, and an aircraft probe. The aircraft probe includes a base connected to the aircraft, a strut that extends from the base, a first port, and an electronics assembly positioned within the strut that includes at least a first pressure sensor pneumatically connected to the first port to sense a first pressure. The electronics assembly is removable from the aircraft probe through the base.

A further embodiment of the foregoing aircraft air data system, wherein the aircraft probe further includes a barrel portion that extends from the strut, wherein the at least one port comprises a first port, a second port, and a third port positioned on the barrel portion.

A further embodiment of any of the foregoing aircraft air data systems, wherein the at least one pressure sensor comprises a first pressure sensor, a second pressure sensor, and a third pressure sensor, and wherein, while in an inserted position, the first pressure sensor is pneumatically connected to the first port to sense the first pressure, the second pressure sensor is pneumatically connected to the second port to sense a second pressure, and the third pressure sensor is pneumatically connected to the third port to sense a third pressure.

A further embodiment of any of the foregoing aircraft air data systems, wherein the first pressure is a pitot pressure and wherein the second pressure and the third pressure are static pressures.

A further embodiment of any of the foregoing aircraft air data systems, wherein the electronics assembly further includes a control circuit configured to calculate one or more parameters derived from at least the first pressure, and wherein the control circuit is configured to provide the one or more parameters on the aircraft data bus.