System and method for estimating the speed of a vehicle

Abstract

To provide a system and a method for estimating the speed of a vehicle (aircraft).SOLUTION: The system 100 includes an emitter electrode 106 positioned at a first location and configured to be exposed to a fluid stream 108. The emitter electrode 106 is configured to generate charged particles via a voltage pulse. The system 100 includes a collector electrode 104 positioned at a second location and configured to be exposed to the fluid stream 108. The second position is rearward of the first position. The collector electrode 104 is configured to detect a current associated with the flow of charged particles during relative movement of the fluid stream 108. The system 100 includes one or more processors coupled to the emitter electrode 106 and the collector electrode 104. The processor is configured to measure a time interval between a voltage pulse and a current, wherein the time interval is indicative of a speed of the vehicle.SELECTED DRAWING: Figure 1

Description

[Technical Field]

[0001]

[0001] The present disclosure relates generally to systems and methods for estimating the velocity of a vehicle. [Background technology]

[0002] As air traffic continues to grow, the safety and reliability of aircraft operations become correspondingly more important. One way that aircraft operators ensure safe and reliable operations is through various types of sensors onboard the aircraft. For example, speed sensors may provide information about the speed at which the aircraft is traveling. Speed ​​sensors may be configured to measure the speed of the aircraft relative to a frame of reference (e.g., the ground), the speed of the air through which the aircraft passes relative to the aircraft itself, or some combination thereof. This data is used for the proper functioning of flight control systems, especially during critical phases of flight such as takeoff, landing, and maneuvering.

[0003]

[0003] Aircraft sensors should be accurate, and redundant sources of accurate information should be available to the flight crew. For example, inaccurate ground speed or airspeed readings can confuse the flight crew and put them in a dangerous flight situation. Redundant sensors act as a fail-safe mechanism, allowing the flight crew to cross-check data from multiple sources and quickly identify inconsistencies or failures. This redundancy increases the overall reliability of the aircraft's systems and expands safety margins, especially in scenarios where accurate aircraft speed information is used to facilitate stable flight.

[0004]

[0004] Furthermore, redundant sensors contribute to the resilience of an aircraft when faced with various environmental factors. Adverse weather conditions, such as icing or turbulence, can affect sensor performance and lead to unreliable measurements. With multiple sensors installed, the aircraft can maintain accurate flight data even under harsh conditions. Therefore, redundant sensors can be important for the aircraft to operate in a variety of operating conditions. Summary of the Invention

[0005] In one particular embodiment, an aircraft includes an exterior skin. The aircraft also includes an emitter electrode disposed at a first location proximate the exterior skin and exposed to ambient air. The emitter electrode is configured to generate charged particles proximate the emitter electrode via a voltage pulse. The aircraft also includes a collector electrode disposed at a second location proximate the exterior skin and exposed to ambient air. The second location is aft of the first location. The collector electrode is configured to detect a current associated with the flow of charged particles during movement of the aircraft through the atmosphere. The aircraft also includes one or more processors coupled to the emitter electrode and the collector electrode. The one or more processors are configured to measure a time interval between the voltage pulse and the current, the time interval being indicative of a velocity of the aircraft.

[0006] In another particular embodiment, the sensor includes an emitter electrode disposed at a first location and exposed to the fluid airflow. The emitter electrode is configured to generate charged particles proximate the emitter electrode via a voltage pulse. The sensor also includes a collector electrode disposed at a second location and exposed to the fluid airflow. The second location is aft of the first location. The collector electrode is configured to detect a current associated with the flow of charged particles during relative movement of the fluid airflow. The sensor also includes one or more processors coupled to the emitter electrode and the collector electrode. The one or more processors are configured to measure a time interval between the voltage pulse and the current, the time interval being indicative of a velocity of the vehicle.

[0007] In another specific embodiment, a method includes emitting charged particles via a voltage pulse at an emitter electrode located at a first location and exposed to ambient air. The method also includes detecting a current at a collector electrode based on the flow of charged particles. The time interval between the voltage pulse and the current indicates a velocity of the airflow. The collector electrode is located at a second location and exposed to ambient air. The second location is behind the first location with respect to the airflow. [Brief explanation of the drawings]

[0008] [Figure 1] 1 illustrates an exemplary system for estimating the velocity of a vehicle, according to some embodiments of the present disclosure. [Figure 2]

[0009] 1 illustrates an example of a portion of an aircraft including a sensor for detecting the velocity of the aircraft, according to some embodiments of the present disclosure. [Figure 3]

[0010] 1 illustrates an exemplary system including an emitter electrode relative to a collector electrode, according to some embodiments of the present disclosure. [Figure 4]

[0011] 1 is a flowchart of an example method for estimating the velocity of a vehicle, according to some embodiments of the present disclosure. [Figure 5]

[0012] FIG. 1 is a block diagram of a computing environment including a computing device configured to support aspects of computer-implemented methods and computer-executable program instructions (or code) according to some embodiments of the present disclosure. [Figure 6]

[0013] 1 is a flowchart of an example method illustrating a life cycle of an aircraft including a sensor for estimating a velocity of the vehicle, according to some embodiments of the present disclosure. [Figure 7]

[0014] 1 illustrates an example aircraft including components for detecting aircraft velocity, according to some embodiments of the present disclosure. DETAILED DESCRIPTION OF THE INVENTION

[0009]

[0015] The systems and methods disclosed herein enable detection of vehicle speed by providing a sensor that can be implemented as a solid-state, non-mechanical sensor with no moving parts that can be integrated into a vehicle flush with a surface (e.g., the vehicle's skin) to improve sensor reliability and maintainability. The systems and methods disclosed herein emit charged particles (e.g., ions) exposed to the ambient air and detect a current at one or more collector electrodes based on the flow of charged particles, where the current is indicative of the vehicle's speed.

[0010]

[0016] A technical advantage of the present disclosure is that it enables efficient and reliable sensor operation. For example, speed sensors implemented using the systems and methods disclosed herein may substantially eliminate known vulnerabilities of certain other types of speed sensors, such as damage and failure due to ground intrusion, bird strikes, ice, improper maintenance, etc.

[0011]

[0017] Another technical advantage of the present disclosure is that it allows for the use of charged current to provide multiple types of air data, such as angle of attack, airspeed, static pressure, and total temperature.

[0012]

[0018] The drawings and the following description illustrate several specific, exemplary embodiments. Those skilled in the art will recognize that, even if not explicitly described or shown herein, they may devise various configurations that embody the principles described herein and are within the scope of the claims that follow. Furthermore, any examples described herein should be understood to be intended to aid in understanding the principles of the disclosure and not to be limiting. Consequently, the disclosure is not limited to the specific embodiments or examples described below, but rather by the claims and their equivalents.

[0013]

[0019] Certain embodiments are described herein with reference to the drawings. In the description, common features are designated with common reference numerals throughout the drawings. Various terms are used herein only to describe particular implementations and are not intended to be limiting. For example, the singular forms "a" and "the" are intended to include the plural (unless the context clearly dictates otherwise). Furthermore, some features described herein exist in the singular in some embodiments and in the plural in other embodiments. To illustrate, FIG. 1 illustrates a sensor 102 that includes one or more processors ("processor(s) 110" in FIG. 1). This indicates that in some embodiments, the sensor 102 includes a single processor 110, and in other embodiments, the sensor 102 includes multiple processors 110. For ease of reference herein, such features are generally introduced as "one or more" features, followed by a single or optionally multiple features (typically indicated by "s"). This is unless it is explicitly stated that multiple aspects relate to multiple features.

[0014]

[0020] Furthermore, the terms "comprise," "comprises," and "comprising" are used interchangeably with "include," "includes," and "including." Furthermore, the term "wherein" is used interchangeably with the term "where." As used herein, "exemplary" denotes an example, implementation, and / or aspect and should not be construed as limiting or indicating a preferred or preferred implementation. As used herein, ordinal terms (e.g., "first," "second," "third," etc.) modifying elements such as structures, components, acts, etc. do not themselves indicate a priority or order of one element over another, but merely distinguish one element from another element having the same name (apart from its use as an ordinal term). As used herein, the term "set" refers to a grouping of one or more elements, and the term "plurality" refers to a plurality of elements.

[0015]

[0021] As used herein, "generating," "calculating," "using," "selecting," "accessing," and "determining" are interchangeable unless the context indicates otherwise. For example, "generating," "calculating," or "determining" a parameter (or signal) can refer to actively generating, calculating, or determining a parameter (or signal), or can refer to using, selecting, or accessing a parameter (or signal) that has already been generated, for example, by another component or device. As used herein, "coupled" may include "communicatively coupled," "electrically coupled," or "physically coupled," or may also (or alternatively) include any combination thereof. Two devices (or components) can be directly or indirectly coupled (communicatively coupled, electrically coupled, or physically coupled) via one or more other devices, components, wires, buses, networks (wired networks, wireless networks, or combinations thereof), etc. Two devices (or components) that are electrically coupled can be included in the same device or different devices and can be connected via electronics, one or more connectors, or inductive coupling, as illustrative, non-limiting examples. In some implementations, two devices (or components) that are communicatively coupled, such as via electrical communication, can send and receive electrical signals (digital signals or analog signals) directly or indirectly via one or more wires, buses, networks, etc. As used herein, "directly coupled" is used to describe two devices that are coupled (e.g., communicatively coupled, electrically coupled, or physically coupled) without any intervening components.

[0016]

[0022] 1 illustrates an exemplary system 100 for estimating the velocity of a vehicle, in accordance with some embodiments of the present disclosure. In some implementations, the system 100 includes a sensor 102. The sensor 102 includes an emitter electrode 106 and a collector electrode 104.

[0017]

[0023] In some embodiments, the sensor(s) 102 may include, correspond to, or be contained within one or more vehicles (e.g., aircraft, unmanned aerial vehicles, etc.), as described below with respect to FIG. 2. In the same or alternative embodiments, the sensor(s) 102 may include, correspond to, or be contained within one or more other surfaces (e.g., aircraft models used in wind tunnels, test surfaces, etc.). In the same or alternative embodiments, the sensor is a solid-state velocity sensor. The sensor includes an emitter electrode 106, a collector electrode 104, and a DC high-voltage power supply, as described below with respect to FIG. 5.

[0018]

[0024] In some implementations, the emitter electrode 106 is configured to provide an electric potential between the emitter electrode 106 and the collector electrode 104. The emitter electrode 106 is configured to generate charged particles proximate the emitter electrode 106. For example, the emitter electrode 106 may be configured to generate positively charged particles to generate a plasma cloud around the emitter electrode 106. In some aspects, the emitter electrode 106 is configured to generate charged particles proximate the emitter electrode 106 via a voltage pulse. The voltage pulse used to generate the charged particles is relatively high voltage. For example, the voltage pulse may include a pulse having a voltage magnitude greater than 5 kilovolts and a duration less than 1 microsecond. In one particular example, the voltage pulse may have a duration of 50 nanoseconds. In one particular aspect, the pulse duration is long enough to produce a detectable current at the sensor 102 under vehicle operating conditions (e.g., vehicle speed, altitude, etc.), but short enough to allow multiple current readings during the period of interest (e.g., multiple readings per minute). A pulse duration of approximately 50 nanoseconds allows multiple readings at a speed of approximately 343 m / s, with an error rate in the speed estimation of approximately 1.5%.

[0019]

[0025] In some implementations, the emitter electrode 106 is positioned at a first location 107 and exposed to the fluid gas flow 108. In some aspects, as described in more detail below with respect to FIG. 3 , the first location 107 is a location that extends above a boundary layer associated with the relative movement of the fluid gas flow 108. In the same or alternative aspects, the emitter electrode 106 is shaped to define an apex to focus field ionization. For example, the emitter electrode 106 may have a substantially conical shape. In further the same or alternative aspects, at least one collector electrode 104 has a blunted shape. The blunted shape may be configured to increase the surface area of ​​the portion of the collector electrode 104 configured to receive charged particles.

[0020]

[0026] In some implementations, the collector electrode 104 is disposed at a second location 109 and configured to be exposed to the fluid airflow 108. The second location 109 may be offset from the first location 107. For example, if the sensor 102 is mounted on an aircraft, the second location 109 may be aft of the first location 107. In some aspects, the second location 109 is sufficiently spaced relative to the first location 107 to substantially prevent arcing between the emitter electrode 106 and the collector electrode 104, as described in more detail below with respect to FIG. 3 .

[0021]

[0027] In some implementations, the collector electrodes 104 are configured to detect a current associated with the flow of charged particles during relative movement of the fluidic airflow 108. For example, if the emitter electrode 106 generates positively charged particles around the emitter electrode 106, the relative movement of the fluidic airflow 108 will cause a corresponding movement of the charged particles toward the collector electrodes 104. The collector electrodes 104 may be configured to detect a current associated with the flow of charged particles received at the corresponding collector electrodes 104. In some aspects, the collector electrodes 104 are substantially arc-shaped with a focal point located at or near the first position 107. In the same or alternative aspects, the collector electrode 104 may be a single-point collector electrode located at the second position 109. In further the same or alternative aspects, the collector electrode 104 may include an array of collector electrodes angularly arranged around a first collector electrode at a reference position.

[0022]

[0028] In some implementations, the sensor(s) 102 may also include one or more processors 110 coupled to the emitter electrode 106 and the collector electrode 104. In some aspects, the processor(s) 110 may be integrated into the sensor(s) 102. In the same or alternative aspects, the processor(s) 110 may be separate from the solid-state sensor 102 and coupled to the emitter electrode 106 and the collector electrode 104. The processor(s) 110 are configured to measure the time interval between the voltage pulse and the current. The time interval is indicative of the vehicle's velocity.

[0023]

[0029] In some embodiments, the system 100 may also include a charge measurement circuit coupled to the collector electrode 104 and the processor(s) 110. The charge measurement circuit may be configured to measure the current at the collector electrode 104. For example, the charge measurement circuit may be configured to sample the current at a sampling rate of 10 megahertz or greater. The sampling rate may be selected based on the frequency and width of the voltage pulses at the emitter electrode 106. The sampling rate enables the charge measurement circuit to respond fast enough to receive the charge with a velocity estimation resolution high enough to fall within an acceptable error rate. For example, measuring a 50 nanosecond high-voltage pulse at a velocity of approximately 343 m / s and spacing between the emitter electrode 106 and the collector electrode 104 with a 10 megahertz sampling rate allows for a velocity error rate of approximately 1.5%.

[0024]

[0030] As an example operation, the relative movement of the fluid airflow 108 may include the operation of the sensor 102 within the atmosphere. For example, the sensor 102 may be coupled to the skin of an aircraft moving through the atmosphere. The emitter electrode 106 may be configured to generate a plasma of positively charged particles via a voltage pulse. The charged particles are moved by the relative movement of the fluid airflow 108 toward the collector electrodes 104. As the charged particles are received at the collector electrodes 104, current sensors and / or charge measurement circuitry coupled to each of the collector electrodes 104 may detect and / or measure the current induced at each collector electrode 104 and output a plurality of sensor signals. The processor(s) 110 may receive the sensor signals and measure the time interval between the voltage pulse and the current. The time interval then indicates the speed of the vehicle through the atmosphere. If the emitter electrode 106 generates a voltage pulse at T0 and the collector electrode 104 detects a current associated with the flow of charged particles generated by the voltage pulse at T1, the time interval D can be measured as follows: D=T1−T0. When the distance L between the emitter electrode 106 and the collector electrode 104 is known, the velocity V of the charged particles between the emitter electrode 106 and the collector electrode 104 can be calculated as follows: V=L / D. The velocity V indicates the speed of the vehicle relative to the airflow 108.

[0025]

[0031] In one particular embodiment, collector electrode 104 is part of an array of collector electrodes positioned at second location 109 and configured to be exposed to fluid airflow 108. The array of collector electrodes may include a first set of collector electrodes angularly offset from collector electrode 104 in a first direction and a second set of collector electrodes angularly offset from collector electrode 104 in a second direction. An output from the array of collector electrodes indicates the angular direction of relative movement of fluid airflow 108.

[0026]

[0032] In one particular configuration, the collector electrode 104 is aligned with the emitter electrode 106 at a reference position. The sensor 102 may be implemented to return angle-of-attack measurements over a range of interest (e.g., ±60 degrees) relative to the reference position. The sensor 102 may also include an array of current sensors. Each sensor in the array of current sensors is coupled to a corresponding collector electrode in the array of collector electrodes. Each sensor in the array of current sensors may also be configured to output a sensor signal. The processor(s) 110 may be configured to receive the sensor signals from the array of current sensors and to calculate an angular direction parameter value based at least in part on a relationship between the respective magnitudes of the currents associated with the sensor signals. The direction of relative movement of the fluid airflow 108 is indicated by the angular direction parameter value.

[0027]

[0033] In one particular example, the sensor 102 may be configured to generate charged particles that, when received by the array of collector electrodes, may be used to generate a current indicative of the velocity of the vehicle and an angular direction of the relative movement of the fluidic airflow 108. The emitter electrode 106 may be configured to generate the charged particles proximate the emitter electrode 106 via a first voltage pulse of a first duration and to generate the charged particles proximate the emitter electrode 106 via a second voltage pulse of a second duration. The second duration may be longer than the first duration. The first voltage pulse may be associated with an output of the collector electrode 104 indicative of the velocity of the vehicle relative to the fluidic airflow 108, and the second voltage pulse may be associated with an output of the collector electrode 104 indicative of the angular direction of the relative movement of the fluidic airflow 108.

[0028]

[0034] In one particular configuration, movement of the aircraft through the atmosphere includes movement of the aircraft's lateral axis and movement of the airfoil's chord line relative to the airflow as the airfoil moves through the atmosphere. The lateral movement results in a change in the aircraft's angle of attack. In one such configuration, the reference position includes a zero-angle reference position, the first direction includes a positive angular direction, and the second direction includes a negative angular direction.

[0029]

[0035] 2 illustrates an example of a portion of an aircraft 200 including a sensor for detecting the speed of the aircraft relative to an airflow, in accordance with some embodiments of the present disclosure. Optionally, the sensor may also be configured to detect the angle of the airflow relative to the aircraft. In some implementations, the aircraft 200 includes an exterior skin 202 and a sensor 204 coupled to the exterior skin 202. The sensor 204 generally corresponds to the sensor 102 of FIG. 1.

[0030]

[0036] In some implementations, sensor 204 includes an emitter electrode (e.g., emitter electrode 106 of FIG. 1 ) positioned at a first location 206 proximate exterior skin 202 and exposed to ambient air. In one particular aspect, first location 206 is elevated from exterior skin 202 and extends above a boundary layer associated with the ambient air during movement of aircraft 200 through the atmosphere. The emitter electrode is configured to generate charged particles proximate to the emitter electrode, as described in more detail above with respect to FIG. 1 .

[0031]

[0037] The sensor 204 may also include one or more collector electrodes (e.g., collector electrode 104 of FIG. 1 ) disposed at a second location 208 proximate the exterior skin 202 and exposed to ambient air. The second location 208 may be aft of the first location 206. In some aspects, the second location 208 is sufficiently spaced relative to the first location 206 to substantially prevent arcing between the emitter electrodes 106 and the array of collector electrodes 104, as described in more detail below with respect to FIG. 3 .

[0032]

[0038] In some embodiments, data from sensors 204 may be provided to components of the vehicle to inform an operator of the vehicle of operating conditions associated with the vehicle based on the data from sensors 204. For example, airspeed, angle of attack, or both may be provided to a cockpit display of aircraft 200 to inform the flight crew of the speed, angle of attack, or both, provided to a flight computer of aircraft 200 to identify flight conditions and / or generate control signals for aircraft 200, provided to measurement and / or test circuitry to monitor the performance of a test vehicle, etc.

[0033]

[0039] 2 illustrates certain features of aircraft 200, there may be more, fewer, and / or different components of aircraft 200 without departing from the scope of this disclosure. For example, aircraft 200 may include an array of current sensors. Each sensor in the array of current sensors is coupled to a respective collector electrode in the array of collector electrodes and configured to output a sensor signal. Aircraft 200 may also include one or more processors connected to receive the sensor signals from the array of current sensors.

[0034]

[0040] 3 illustrates an example system 300 including an emitter electrode 302 relative to a collector electrode 304, according to some embodiments of the present disclosure. Generally, the emitter electrode 302 corresponds to the emitter electrode 106 of FIG. 1, and the collector electrode 304 corresponds to the collector electrode 104 of FIG. 1.

[0035]

[0041] In some implementations, the emitter electrode 302 is positioned at a first position (e.g., first position 107 in FIG. 1 , first position 206 in FIG. 2 , etc.), and the collector electrode 304 is positioned at a second position (e.g., second position 109 in FIG. 1 , second position 208 in FIG. 2 , etc.). Both the emitter electrode 302 and the collector electrode 304 are exposed to the fluid airflow 108 in FIG. 1. For example, as described above with respect to FIG. 2, the emitter electrode 302 and the collector electrode 304 may be positioned proximate to the exterior skin of the aircraft and exposed to ambient air. In such a configuration, the second position is aft of the first position.

[0036]

[0042] In some aspects, the second location of the collector electrode 304 is sufficiently spaced from the first location of the emitter electrode 302 to substantially prevent arcing between the emitter electrode 302 and the collector electrode 304. For example, the distance 306 between the emitter electrode 302 and the collector electrode 304 may be approximately 5 centimeters. In the same or alternative aspects, the first location, the second location, or both, extend above a boundary layer associated with the relative movement of the fluid gas stream 108. For example, the distance 308 between the emitter electrode 302 and the surface 312 on which the emitter electrode 302 is disposed may be approximately 2.54 mm. The distance between each electrode and the surface 312 may be the same or different for the emitter electrode 302 and the collector electrode 304. For example, the distance 310 between the collector electrode 304 and the surface 312 on which the collector electrode 304 is disposed may be approximately 2.0 mm. Furthermore, the distance 310 may be the same or different for multiple collector electrodes 304 in a particular configuration of the array of collector electrodes 104 in FIG.

[0037]

[0043] In some embodiments, the collector electrode 304, the emitter electrode 302, or both, may include a plasma-resistant material, such as tungsten. In the same or alternative embodiments, the collector electrode 304, the emitter electrode 302, or both, may include a dielectric material. The dielectric material may include a ceramic material, a plastic material, a fiberglass material, or a combination thereof.

[0038]

[0044] As an exemplary operation, at a speed of approximately 343 m / s and a distance 306 of approximately 5 centimeters, a sub-microsecond high voltage pulse at the emitter electrode 302 should produce a current at the collector electrode 304 after approximately 145 microseconds. This provides an estimate of the vehicle's velocity relative to the fluid stream 108. The estimate then has an error rate of approximately 1.5%. Generally, the estimate may be more accurate at slower speeds and less accurate at faster speeds.

[0039]

[0045] 4 is a flowchart of an example method 400 for estimating the velocity of a vehicle, according to some embodiments of the present disclosure. Method 400 may be initiated, performed, or controlled by one or more processors executing instructions, such as by processor(s) 520 of FIG. 5 executing instructions 536 from memory 530. Method 400 may also be initiated, performed, or controlled by sensor 102 or processor(s) 110 of FIG. 1, sensor 204 of FIG. 2, system 300 of FIG. 3, or a combination thereof.

[0040]

[0046] In some implementations, method 400 includes emitting charged particles via a voltage pulse at an emitter electrode disposed at a first location and exposed to ambient air, at block 402. For example, sensor 102 of FIG. 1 may be configured to emit charged particles at emitter electrode 106 disposed at first location 107 and exposed to fluid airflow 108.

[0041]

[0047] At block 404, the method 400 includes detecting a current at a collector electrode based on the flow of charged particles. A time interval between the voltage pulse and the current indicates a velocity of the airflow, and the collector electrode is disposed at a second position and exposed to ambient air. The second position is behind the first position with respect to the airflow. For example, the sensor 102 of FIG. 1 may be configured to detect a current at the collector electrode 104 based on the flow of charged particles. A time interval between the voltage pulse and the current indicates a velocity of the fluid airflow 108. The collector electrode 104 is disposed at a second position 109 and exposed to the fluid airflow 108. The second position 109 is behind the first position 107 with respect to the fluid airflow 108.

[0042]

[0048] In some implementations, method 400 may include more, fewer, and / or different steps without departing from the scope of the present disclosure. For example, method 400 may also include receiving sensor signals from an array of current sensors coupled to respective collector electrodes of the array of collector electrodes. Method 400 may also include generating angular orientation parameter values ​​based at least in part on a relationship between respective magnitudes of the currents associated with the sensor signals.

[0043]

[0049] As another example, method 400 may provide data to a vehicle component to inform an operator of the vehicle of an operating condition associated with the vehicle based on the data. For example, airspeed, angle of attack, or both may be provided to a cockpit display of an aircraft (e.g., aircraft 200 of FIG. 2 ) to inform the flight crew of the speed, angle of attack, or both, provided to a flight computer of aircraft 200 to identify flight conditions and / or generate control signals for aircraft 200, provided to measurement and / or test circuitry to monitor the performance of a test vehicle, etc.

[0044]

[0050] 4 may be implemented to achieve one or more of the technical advantages described in more detail above. For example, method 400 may enable a more reliable and maintainable speed sensor.

[0045]

[0051] 5 is a block diagram of a computing environment 500 including a computing device 510 configured to support aspects of computer-implemented methods and computer-executable program instructions (or code) according to some embodiments of the present disclosure. For example, computing device 510, or portions thereof, are configured to execute instructions to initiate, perform, or control one or more of the operations described in more detail above with reference to FIGS. 1-4. In one particular aspect, computing device 510 may include, correspond to, or be included in a computing device, one or more servers, one or more virtual devices, or a combination thereof.

[0046]

[0052] The computing device 510 includes one or more processors 520. The processor(s) 520 are configured to communicate with a system memory 530, one or more storage devices 550, one or more input / output interfaces 540, one or more communication interfaces 560, or any combination thereof. The system memory 530 includes volatile memory devices (e.g., random access memory (RAM) devices), non-volatile memory devices (e.g., read-only memory (ROM) devices, programmable read-only memory, and flash memory), or both. The system memory 530 stores an operating system 532, which may include a basic input / output system for booting the computing device 510 and a full operating system for enabling the computing device 510 to interact with a user, other programs, and other devices. The system memory 530 stores system (program) data 538, such as a time interval 539 between a voltage pulse and a current from a sensor signal 581.

[0047]

[0053] System memory 530 includes one or more applications 534 (e.g., sets of instructions) executable by processor(s) 520, such as a time interval calculator 537. As one example, one or more applications 534 include instructions 536 executable by processor(s) 520 to initiate, control, or perform one or more of the operations described with reference to FIGS. 1-4. Illustratively, one or more applications 534 include instructions 536 executable by processor(s) 520 to initiate, control, or perform one or more of the operations described with respect to measuring the time interval between a voltage pulse and a current, where the time interval is indicative of the vehicle's velocity. The time associated with the voltage pulse and the current may be received via sensor signal 581 in some implementations.

[0048]

[0054] In one particular implementation, the system memory 530 includes a non-transitory computer-readable medium (e.g., a computer-readable storage device) having stored thereon instructions 536 that, when executed by the processor(s) 520, cause the processor(s) 520 to initiate, perform, or control operations to estimate the velocity of the vehicle, including receiving sensor signals from an array of current sensors (e.g., one or more charge measurement circuits) and calculating the time interval between a voltage pulse at the emitter electrode and an incident current at the collector electrode.

[0049]

[0055] In the same or alternative specific embodiments, system memory 530 includes a non-transitory computer-readable medium (e.g., a computer-readable storage device) having stored thereon instructions 536 that, when executed by processor(s) 520, cause processor(s) 520 to initiate, perform, or control operations to detect the angle of the airflow, including measuring the time interval between the voltage pulse and the current, where the time interval is indicative of the vehicle's velocity.

[0050]

[0056] The one or more storage devices 550 include non-volatile storage devices such as magnetic disks, optical disks, or flash memory devices. In one particular embodiment, the storage devices 550 include both removable and non-removable memory devices. The storage devices 550 are configured to store an operating system, operating system images, applications (e.g., one or more applications 534), and program data (e.g., program data 538). In one particular aspect, the system memory 530, the storage devices 550, or both, comprise tangible computer-readable media. In one particular aspect, one or more of the storage devices 550 reside external to the computing device 510.

[0051]

[0057] The one or more input / output interfaces 540 enable the computing device 510 to communicate with one or more input / output devices 570 to facilitate interaction with a user. For example, the one or more input / output interfaces 540 may include a display interface, an input interface, or both. For example, the input / output interface 540 may be adapted to receive input from a user, receive input from another computing device, or a combination thereof. In some embodiments, input / output interface 540 conforms to one or more standard interface protocols, including a serial interface (e.g., a universal serial bus (USB) interface or (IEEE (Institute of Electrical and Electronics Engineers) interface standard), a parallel interface, a display adapter, an audio adapter, or a custom interface ("IEEE" is a registered trademark of the Institute of Electrical and Electronics Engineers, Inc. of Piscataway, NJ). In some embodiments, input / output device(s) 570 include one or more user interface devices and displays, including any combination of buttons, keyboards, pointing devices, displays, speakers, microphones, touchscreens, and other devices.

[0052]

[0058] In some implementations, input / output device(s) 570 include one or more components of a vehicle configured to receive data from a sensor (e.g., sensor 102 of FIG. 1 ) and further apply the data. For example, a cockpit display of an aircraft (e.g., aircraft 200 of FIG. 2 ) may receive airspeed data, angle of attack data, or both and display the data (or a modified version of the data) to inform the flight crew of the speed, angle of attack, or both. A flight computer of aircraft 200 may be configured to identify flight conditions and / or generate control signals for aircraft 200. Measurement and / or test circuitry may be configured to monitor the performance of a test vehicle, etc.

[0053]

[0059] The processor(s) 520 are configured to communicate with a device or controller 580 via one or more communication interfaces 560. For example, the one or more communication interfaces 560 may include a network interface. The device or controller 580 may include, for example, the sensor(s) 102 of FIG. 1 , the sensor 204 of FIG. 2 , the system 300 of FIG. 3 , or some combination thereof. In some implementations, the device or controller 580 may include a direct current (“DC”) high-voltage power supply 525 and an array of current sensors 515, or a combination thereof. For example, as described in more detail above with respect to FIG. 1 , the sensor 102 configured as a solid-state velocity sensor may include the DC high-voltage power supply 525. The DC high-voltage power supply 525 may be configured to generate a voltage pulse at the emitter electrode. As another example, the sensor 102 may include one or more current sensors 515. In this case, the current sensor(s) is / are coupled to the collector electrode 104 of FIG. 1 and configured to output a sensor signal 581.

[0054]

[0060] In some implementations, a non-transitory computer-readable medium (e.g., a computer-readable storage device) stores instructions that, when executed by one or more processors, cause the one or more processors to initiate, perform, or control operations to perform some or all of the functions described above. For example, the instructions may be executable to perform one or more of the operations or methods of FIGS. 1-4. In some implementations, some or all of one or more of the operations or methods of FIGS. 1-4 may be performed by one or more processors (e.g., one or more central processing units (CPUs), one or more graphics processing units (GPUs), one or more digital signal processors (DSPs)), or any combination thereof, that execute instructions using dedicated hardware circuitry.

[0055]

[0061] 6 is a flowchart of an example method 600 illustrating a life cycle of an aircraft including a sensor for estimating vehicle velocity, according to some embodiments of the present disclosure. During pre-production, method 600 includes, at 602, specification and design of an aircraft, such as the portion of aircraft 200 described with reference to FIG. 2 . During the specification and design of the aircraft, method 600 may include specification and design of sensor 102. At 604, method 600 includes sourcing materials. The sourcing of materials may include sourcing materials for sensor 102.

[0056]

[0062] During production, method 600 includes, at 606, manufacturing of components and subassemblies and, at 608, system integration with the aircraft. For example, method 600 may include manufacturing of components and subassemblies of sensor 102 and system integration of sensor 102. At 610, method 600 includes certification and delivery of the aircraft and, at 612, placing the aircraft in service. Certification and delivery may include certification of sensor 102 for use. While in service by a customer, the aircraft may be scheduled for periodic maintenance and service (which may include modifications, reconfigurations, refurbishments, etc.). At 614, method 600 includes performing maintenance and service on the aircraft. The maintenance and service may include performing maintenance and service on sensor 102.

[0057]

[0063] Each of the processes of method 600 may be performed or implemented by a system integrator, a third party, and / or an operator (e.g., a customer). For purposes of this description, a system integrator may include, but is not limited to, any number of aircraft manufacturers and major system subcontractors, a third party may include, but is not limited to, any number of vendors, subcontractors, and suppliers, and an operator may be an airline, a leasing company, a military organization, a service organization, etc.

[0058]

[0064] 7 illustrates an example aircraft 700 including a component 740 for estimating vehicle velocity (e.g., using method 400 of FIG. 4 ), according to some embodiments of the present disclosure. In one embodiment of FIG. 7 , aircraft 700 includes an airframe 718 having a plurality of systems 720 and an interior 722. Examples of the plurality of systems 720 include one or more of a propulsion system 724, an electrical system 726, an environmental system 728, and a hydraulic system 730. Any number of other systems may be included.

[0059]

[0065] In the example of Figure 7, component 740 includes sensor 102 of Figure 1, sensor 204 of Figure 2, or a combination thereof. In some implementations, component 740 may be configured to perform specific operations, such as those described above with respect to method 400 of Figure 4.

[0060]

[0066] To illustrate, in some embodiments, component 740 is included within airframe 718. In one embodiment, component 740 includes or corresponds to an exterior component of aircraft 700, such as a skin portion of aircraft 700. Alternatively, or in addition, in other embodiments, component 740 includes or corresponds to another component of aircraft 700, such as a component of interior 722 that includes sensor 102, sensor 204, or a combination thereof.

[0061]

[0067] The illustrations of the various embodiments described herein are intended to provide a general understanding of the structure of various embodiments. These illustrations are not intended to exhaustively describe all elements and features of apparatus and systems that utilize the structures or methods described herein. Many other embodiments may become apparent to those skilled in the art upon review of this disclosure. Other embodiments may be utilized and derived from this disclosure, such that structural and logical substitutions and changes may be made without departing from the scope of the disclosure. For example, method actions may be performed in a different order than shown in the figures, or one or more method actions may be omitted. Therefore, the present disclosure and the figures should be considered illustrative rather than restrictive.

[0062]

[0068] Furthermore, while specific examples have been shown and described herein, any subsequent configurations designed to achieve the same or similar results may be substituted for the specific embodiment shown. The present disclosure is intended to cover any subsequent adaptations or variations of the various embodiments. Combinations of the above embodiments, as well as other embodiments not specifically described herein, will be apparent to those of skill in the art upon review of the present disclosure.

[0063]

[0069] The Abstract of the Disclosure is submitted with the understanding that it will not be used to interpret or limit the scope or meaning of the claims. Additionally, in the above Detailed Description, various features may be grouped together or described within a single embodiment for the purpose of conciseness of the disclosure. The above examples are illustrative of the disclosure, not limiting. Furthermore, many modifications and variations are possible in accordance with the principles of the disclosure. As reflected in the following claims, claimed subject matter may not be directed to all features of any disclosed embodiment. Accordingly, the scope of the disclosure is defined by the following claims and their equivalents.

[0064]

[0070] Furthermore, the present disclosure includes embodiments according to the following examples.

[0065]

[0071] According to Example 1, an aircraft includes an exterior skin and an emitter electrode disposed at a first location proximate the exterior skin and exposed to ambient air. The emitter electrode is configured to generate charged particles proximate the emitter electrode via a voltage pulse. The aircraft includes a collector electrode disposed at a second location proximate the exterior skin and exposed to ambient air. The second location is aft of the first location. The collector electrode is configured to detect a current associated with the flow of the charged particles during movement of the aircraft through the atmosphere. The aircraft includes one or more processors coupled to the emitter electrode and the collector electrode. The one or more processors are configured to measure a time interval between the voltage pulse and the current. The time interval indicates a velocity of the aircraft.

[0066]

[0072] Example 2 includes the aircraft of example 1, wherein the voltage pulse includes a pulse greater than 5 kilovolts.

[0067]

[0073] Example 3 includes the aircraft of example 1 or 2, wherein the voltage pulse has a duration of less than 1 microsecond.

[0068]

[0074] Example 4 includes the aircraft of any one of examples 1-3, wherein the voltage pulse has a duration of approximately 50 nanoseconds.

[0069]

[0075] Example 5 includes the aircraft of any one of examples 1-4, wherein the emitter electrode is shaped to define an apex for concentrating electric field ionization.

[0070]

[0076] Example 6 includes the aircraft of any one of examples 1 to 5, wherein the second location is approximately 5 centimeters aft of the first location.

[0071]

[0077] Example 7 includes the aircraft of any one of examples 1-6, wherein the collector electrode has a blunted shape.

[0072]

[0078] Example 8 includes the aircraft of any one of examples 1-7, wherein the first location includes a position elevated from the exterior skin and extending above a boundary layer associated with ambient air during movement of the aircraft through the atmosphere.

[0073]

[0079] Example 9 includes the aircraft of any one of examples 1-8, further including a charge measurement circuit coupled to the collector electrode and to the one or more processors.

[0074]

[0080] Example 10 includes the aircraft of example 9, wherein the charge measurement circuit is configured to sample the current at a sampling rate of 10 megahertz or greater.

[0075]

[0081] Example 11 includes the aircraft of any one of examples 1-10, wherein the collector electrode, the emitter electrode, or both, include a plasma-durable material.

[0076]

[0082] Example 12 includes the aircraft of example 11, in which the plasma-durable material includes tungsten.

[0077]

[0083] Example 13 includes the aircraft of any one of examples 1 to 12, wherein the collector electrode, the emitter electrode, or both, include a dielectric material.

[0078]

[0084] Example 14 includes the aircraft of example 13, wherein the dielectric material includes a ceramic material, a plastic material, a fiberglass material, or a combination thereof.

[0079]

[0085] According to Example 15, a sensor includes an emitter electrode disposed at a first location and configured to be exposed to a fluid airflow. The emitter electrode is configured to generate charged particles proximate the emitter electrode via a voltage pulse. The sensor includes a collector electrode disposed at a second location and configured to be exposed to the fluid airflow. The second location is aft of the first location. The collector electrode is configured to detect a current associated with the flow of charged particles during relative movement of the fluid airflow. The sensor includes one or more processors coupled to the emitter electrode and the collector electrode. The one or more processors are configured to measure a time interval between the voltage pulse and the current. The time interval indicates a velocity of a vehicle.

[0080]

[0086] Example 16 includes the sensor of example 15, wherein the output of the collector electrode indicates the angular direction of the relative movement of the fluid stream.

[0081]

[0087] Example 17 includes the sensor of examples 15 or 16, wherein the collector electrode is one of an array of collector electrodes disposed at the second location and configured to be exposed to the fluid airflow, the array of collector electrodes including a first set of collector electrodes angularly offset from the collector electrode in a first direction, the array of collector electrodes including a second set of collector electrodes angularly offset from the collector electrode in a second direction, and an output from the array of collector electrodes indicative of an angular direction of relative movement of the fluid airflow.

[0082]

[0088] Example 18 includes the sensor of example 17, wherein the collector electrode is aligned with the emitter electrode in a reference position.

[0083]

[0089] Example 19 includes the sensor of examples 17 or 18, wherein the voltage pulse is of a first duration, and the emitter electrode is configured to generate charged particles proximate the emitter electrode via a second voltage pulse of a second duration, the second duration being longer than the first duration, and the second voltage pulse is associated with the output of the collector electrode indicative of the angular direction of the relative movement of the fluid stream.

[0084]

[0090] According to Example 20, a method includes emitting charged particles via a voltage pulse at an emitter electrode located at a first location and exposed to ambient air. The method also includes detecting a current at a collector electrode based on the flow of the charged particles. A time interval between the voltage pulse and the current indicates a velocity of the airflow. The collector electrode is located at a second location and exposed to ambient air. The second location is behind the first location with respect to the airflow.

Claims

1. An aircraft (200), Exterior skin (202), an emitter electrode (106) disposed at a first location (206) proximate the exterior skin and exposed to ambient air (108), the emitter electrode configured to generate charged particles proximate the emitter electrode via a voltage pulse; a collector electrode (104) disposed at a second location (208) adjacent the exterior skin and exposed to ambient air; the second position is rearward of the first position; a collector electrode configured to detect a current associated with the flow of charged particles during movement of the aircraft through the atmosphere; and 1. An aircraft comprising: one or more processors (110) coupled to the emitter electrode and the collector electrode, the one or more processors configured to measure a time interval between the voltage pulse and the current, the time interval being indicative of a velocity of the aircraft.

2. The aircraft of claim 1 , wherein the voltage pulse comprises a pulse greater than 5 kilovolts.

3. The aircraft of claim 1 , wherein the voltage pulse has a duration of less than 1 microsecond.

4. The aircraft of claim 1 , wherein the voltage pulse has a duration of approximately 50 nanoseconds.

5. The aircraft of claim 1 , wherein the emitter electrode is shaped to define an apex for concentrating electric field ionization.

6. 2. The aircraft of claim 1, wherein the second location is approximately 5 centimeters aft of the first location.

7. The aircraft of claim 1 , wherein the collector electrode has a blunted shape.

8. 2. The aircraft of claim 1, wherein the first location comprises a location elevated from the exterior skin and extending above a boundary layer associated with ambient air during movement of the aircraft through the atmosphere.

9. The aircraft of claim 1 , further comprising a charge measurement circuit coupled to the collector electrode and the one or more processors.

10. 10. The aircraft of claim 9, wherein the charge measurement circuitry is configured to sample the current at a sampling rate of 10 megahertz or greater.

11. The aircraft of claim 1 , wherein the collector electrode, the emitter electrode, or both, comprise a plasma-resistant material.

12. The aircraft of claim 11 , wherein the plasma-durable material comprises tungsten.

13. The aircraft of claim 1 , wherein the collector electrode, the emitter electrode, or both, comprise a dielectric material.

14. The aircraft of claim 13 , wherein the dielectric material comprises a ceramic material, a plastic material, a fiberglass material, or a combination thereof.

15. A sensor (102), an emitter electrode (106) disposed at a first position (107) and configured to be exposed to a fluid gas stream (108), the emitter electrode configured to generate charged particles proximate to the emitter electrode via a voltage pulse; a collector electrode (104) disposed at a second position (109) and configured to be exposed to the fluid stream, the second position is rearward of the first position; a collector electrode configured to detect a current associated with the flow of charged particles during relative movement of the fluid stream; and 10. The sensor of claim 9, further comprising: one or more processors (110) coupled to the emitter electrode and the collector electrode, the one or more processors configured to measure a time interval between the voltage pulse and the current, the time interval being indicative of a velocity of a vehicle.

16. 16. The sensor of claim 15, wherein the output of the collector electrode indicates the angular direction of the relative movement of the fluid stream.

17. the collector electrode is one of an array of collector electrodes disposed at the second location and configured to be exposed to the fluid stream; The array of collector electrodes comprises: a first set of collector electrodes angularly offset from the collector electrodes in a first direction; and a second set of collector electrodes angularly offset from the collector electrodes in a second direction; 16. The sensor of claim 15, wherein the output from the array of collector electrodes indicates the angular direction of the relative movement of the fluid streams.

18. 18. The sensor of claim 17, wherein the collector electrode is aligned with the emitter electrode in a reference position.

19. the voltage pulse is of a first duration; the emitter electrode is configured to generate charged particles proximate the emitter electrode via a second voltage pulse of a second duration; the second duration is longer than the first duration; 18. The sensor of claim 17, wherein the second voltage pulse is associated with the output of the collector electrode indicative of the angular direction of the relative movement of the fluid stream.

20. 1. A method (400) comprising: emitting (402) charged particles via a voltage pulse at an emitter electrode (106) disposed at a first position (107) and exposed to ambient air (108); detecting (404) a current at a collector electrode (104) based on the flow of charged particles; the time interval between the voltage pulse and the current indicates the velocity of the airflow; the collector electrode is disposed at a second position (109) and exposed to ambient air; The method, wherein the second location is aft of the first location relative to the airflow.

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