# US 11,029,326 B2 · Aircraft airflow sensor probe and process of implementing an aircraft sensor probe

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- Number: US 11,029,326 B2
- Document ID: US11029326B2
- Status: Granted
- Kind: B2
- Application number: 16/270,200
- Filed: 2019-02-07
- Published: 2019-08-08
- Granted: 2021-06-08
- Earliest claimed: 2018-02-07
- Assignees: Aerosonic Corporation
- Applicants: Aerosonic Corporation
- Inventors: Charles Lang; Edgard Schulz; Jason Larkin; Dwight Turner
- Web page: https://patentgrep.com/patent/US11029326B2

## CPC

- G01P 13/025: {indicating air data, i.e. flight variables of an aircraft, e.g. angle of attack, side slip, shear, yaw}
- B64D 45/00: Aircraft indicators or protectors not otherwise provided for
- B64F 5/60: Testing or inspecting aircraft components or systems
- G01P 5/16: using Pitot tubes {, e.g. Machmeter}
- G01P 5/165: Arrangements or constructions of Pitot tubes
- B64D 2045/0085: {Devices for aircraft health monitoring, e.g. monitoring flutter or vibration}
- G01P 5/06: using rotation of vanes (measuring speed of rotating shafts G01P3/00)
- G01P: MEASURING LINEAR OR ANGULAR SPEED, ACCELERATION, DECELERATION, OR SHOCK; INDICATING PRESENCE, ABSENCE, OR DIRECTION, OF MOVEMENT (measuring or recording blood flow A61B5/02, A61B8/06; monitoring speed or deceleration of electrically-propelled vehicles B60L3/00; vehicle lighting systems adapted to indicate speed B60Q1/54; determining position or course in navigation, measuring ground distance in geodesy or surveying G01C; combined measuring devices for measuring two or more variables of movement G01C23/00; measuring velocity of sound G01H; measuring velocity of light G01J7/00; measuring direction or velocity of solid objects by reception or emission of radiowaves or other waves and based on propagation effects, e.g. Doppler effect, propagation time, direction of propagation, G01S; measuring speed of nuclear radiation G01T; measuring acceleration of gravity G01V; {measuring or recording the speed of trains B61L23/00; speed indicators incorporated in motor vehicles B60K35/00; measuring frequency or phase G01R; traffic control G08G})
- B64D: EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64F: GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR

## Abstract

An aircraft airflow sensor probe includes an airflow assembly or a cone assembly configured to sense a direction of local airflow outside an aircraft; a shaft configured to rotatably hold the assembly and allow rotational movement of the assembly; and a motor connected to the shaft and configured to generate a torque to damp the rotational movement of the shaft as well as the assembly. The sensor probe further includes an angle of attack processor configured to control the motor to generate the torque to damp the rotational movement of the shaft as well as the assembly and a sensor configured to sense a position of the assembly and provide the position of the assembly to the angle of attack processor. An aircraft airflow sensor process is disclosed as well.

## Claims

### Claim 1

An aircraft airflow sensor probe comprising:
an airflow assembly configured to sense a direction of local airflow outside an aircraft;
a shaft configured to rotatably hold the airflow assembly and allow rotational movement of the airflow assembly;
a motor connected to the shaft and configured to generate a torque to damp the rotational movement of the shaft as well as the airflow assembly;
an angle of attack processor configured to control the motor to generate the torque to damp the rotational movement of the shaft as well as the airflow assembly based on at least one of the following: a static air pressure, an airflow velocity, a pressure differential between an upper side of the airflow assembly and a lower side of the airflow assembly, a rate of change of a position of the airflow assembly, a position of the airflow assembly, or an ambient temperature; and
a sensor configured to sense a position of the airflow assembly and provide the position of the airflow assembly to the angle of attack processor,
wherein the airflow assembly comprises one of the following: a vane assembly configured to sense a direction of local airflow outside an aircraft and a cone assembly configured to sense a direction of local airflow outside an aircraft.

### Claim 2 (depends on 1)

The aircraft airflow sensor probe according to claim 1 further comprising:
at least one air pressure sensor configured to determine an air pressure received by an air pressure sensor port;
wherein the air pressure comprises at least one of the following: a static air pressure, an airflow velocity, and a pressure differential between an upper side of the airflow assembly and a lower side of the airflow assembly; and
wherein the angle of attack processor is further configured to control the motor to generate the torque to damp the rotational movement of the shaft as well as the airflow assembly in response to the air pressure determined by the at least one air pressure sensor.

### Claim 3 (depends on 1)

The aircraft airflow sensor probe according to claim 1:
wherein the sensor is further configured to sense a rate of change of the position of the airflow assembly and provide the rate of change of the position of the airflow assembly to the angle of attack processor; and
wherein the angle of attack processor is further configured to control the motor to generate the torque to damp the rotational movement of the shaft as well as the airflow assembly in response to the rate of change of the position of the airflow assembly.

### Claim 4 (depends on 1)

The aircraft airflow sensor probe according to claim 1 further comprising:
at least one air pressure sensor configured to determine an air pressure received by an air pressure sensor port;
wherein the air pressure comprises a static air pressure, an airflow velocity, and a pressure differential between an upper side of the airflow assembly and a lower side of the airflow assembly; and
wherein the angle of attack processor is further configured to control the motor to generate the torque to damp the rotational movement of the shaft as well as the airflow assembly in response to the air pressure determined by the at least one air pressure sensor.

### Claim 5 (depends on 1)

The aircraft airflow sensor probe according to claim 1 further comprising:
at least one air pressure sensor configured to determine an air pressure received by an air pressure sensor port;
wherein the air pressure comprises a pressure differential between an upper side of the airflow assembly and a lower side of the airflow assembly; and
wherein the angle of attack processor is further configured to control the motor to generate the torque to damp the rotational movement of the shaft as well as the airflow assembly in response to the air pressure determined by the at least one air pressure sensor.

### Claim 6 (depends on 1)

The aircraft airflow sensor probe according to claim 1 further comprising:
at least one air pressure sensor configured to determine an air pressure received by an air pressure sensor port;
wherein the air pressure comprises airflow velocity; and
wherein the angle of attack processor is further configured to control the motor to generate the torque to damp the rotational movement of the shaft as well as the airflow assembly in response to the air pressure determined by the at least one air pressure sensor.

### Claim 7 (depends on 1)

The aircraft airflow sensor probe according to claim 1 further comprising:
at least one air pressure sensor configured to determine an air pressure received by an air pressure sensor port;
wherein the air pressure comprises a static air pressure; and
wherein the angle of attack processor is further configured to control the motor to generate the torque to damp the rotational movement of the shaft as well as the airflow assembly in response to the air pressure determined by the at least one air pressure sensor.

### Claim 8 (depends on 1)

The aircraft airflow sensor probe according to claim 1:
wherein the sensor is further configured to sense the position of the airflow assembly and provide the position of the airflow assembly to the angle of attack processor; and
wherein the angle of attack processor is further configured to control the motor to generate the torque to damp the rotational movement of the shaft as well as the airflow assembly in response to the position of the airflow assembly.

### Claim 9 (depends on 1)

The aircraft airflow sensor probe according to claim 1:
wherein the angle of attack processor is configured to receive an ambient temperature from a temperature sensor; and
wherein the angle of attack processor is further configured to control the motor to generate the torque to damp the rotational movement of the shaft as well as the airflow assembly in response to the ambient temperature.

### Claim 10

An aircraft airflow sensor probe comprising:
an airflow assembly configured to sense a direction of local airflow outside an aircraft;
a shaft configured to rotatably hold the airflow assembly and allow rotational movement of the airflow assembly;
a motor connected to the shaft and configured to generate a torque to damp the rotational movement of the shaft as well as the airflow assembly;
an angle of attack processor configured to control the motor to generate the torque to damp the rotational movement of the shaft as well as the airflow assembly; and
a sensor configured to sense a position of the airflow assembly and provide the position of the airflow assembly to the angle of attack processor,
wherein the airflow assembly comprises one of the following: a vane assembly configured to sense a direction of local airflow outside an aircraft and a cone assembly configured to sense a direction of local airflow outside an aircraft;
wherein the angle of attack processor is configured to receive aircraft configuration data from the aircraft; and
wherein the angle of attack processor is further configured to control the motor to generate the torque to damp the rotational movement of the shaft as well as the airflow assembly in response to the aircraft configuration data.

### Claim 11

A process of operating an aircraft airflow sensor probe comprising:
sensing a direction of local airflow outside an aircraft with an airflow assembly;
allowing rotational movement of the airflow assembly with a shaft configured to rotatably hold the airflow assembly;
generating a torque to damp the rotational movement of the shaft as well as the airflow assembly with a motor connected to the shaft;
controlling the motor to generate the torque to damp the rotational movement of the shaft as well as the airflow assembly with an angle of attack processor based on at least one of the following: a static air pressure, an airflow velocity, a pressure differential between an upper side of the airflow assembly and a lower side of the airflow assembly, a rate of change of a position of the airflow assembly, a position of the airflow assembly, or an ambient temperature; and
sensing a position of the airflow assembly and providing the position of the airflow assembly to the angle of attack processor with a sensor,
wherein the airflow assembly comprises one of the following: a vane assembly configured to sense a direction of local airflow outside an aircraft and a cone assembly configured to sense a direction of local airflow outside an aircraft.

### Claim 12 (depends on 11)

The process of operating an aircraft airflow sensor probe according to claim 11 further comprising:
determining an air pressure received by an air pressure sensor port with at least one air pressure sensor;
wherein the air pressure comprises at least one of the following: a static air pressure, an airflow velocity, and a pressure differential between an upper side of the airflow assembly and a lower side of the airflow assembly; and
wherein the angle of attack processor is further configured to control the motor to generate the torque to damp the rotational movement of the shaft as well as the airflow assembly in response to the air pressure determined by the at least one air pressure sensor.

### Claim 13 (depends on 11)

The process of operating an aircraft airflow sensor probe according to claim 11:
wherein the sensor is further configured to sense a rate of change of the position of the airflow assembly and provide the rate of change of the position of the airflow assembly to the angle of attack processor; and
wherein the angle of attack processor is further configured to control the motor to generate the torque to damp the rotational movement of the shaft as well as the airflow assembly in response to the rate of change of the position of the airflow assembly.

### Claim 14 (depends on 11)

The process of operating an aircraft airflow sensor probe according to claim 11 further comprising:
determining an air pressure received by an air pressure sensor port with at least one air pressure sensor;
wherein the air pressure comprises a static air pressure, an airflow velocity, and a pressure differential between an upper side of the airflow assembly and a lower side of the airflow assembly; and
wherein the angle of attack processor is further configured to control the motor to generate the torque to damp the rotational movement of the shaft as well as the airflow assembly in response to the air pressure determined by the at least one air pressure sensor.

### Claim 15 (depends on 11)

The process of operating an aircraft airflow sensor probe according to claim 11 further comprising:
determining an air pressure received by an air pressure sensor port with at least one air pressure sensor;
wherein the air pressure comprises a pressure differential between an upper side of the airflow assembly and a lower side of the airflow assembly; and
wherein the angle of attack processor is further configured to control the motor to generate the torque to damp the rotational movement of the shaft as well as the airflow assembly in response to the air pressure determined by the at least one air pressure sensor.

### Claim 16 (depends on 11)

The process of operating an aircraft airflow sensor probe according to claim 11 further comprising:
determining an air pressure received by an air pressure sensor port with at least one air pressure sensor;
wherein the air pressure comprises airflow velocity; and
wherein the angle of attack processor is further configured to control the motor to generate the torque to damp the rotational movement of the shaft as well as the airflow assembly in response to the air pressure determined by the at least one air pressure sensor.

### Claim 17 (depends on 11)

The process of operating an aircraft airflow sensor probe according to claim 11 further comprising:
determining an air pressure received by an air pressure sensor port with at least one air pressure sensor;
wherein the air pressure comprises a static air pressure; and
wherein the angle of attack processor is further configured to control the motor to generate the torque to damp the rotational movement of the shaft as well as the airflow assembly in response to the air pressure determined by the at least one air pressure sensor.

### Claim 18 (depends on 11)

The process of operating an aircraft airflow sensor probe according to claim 11:
wherein the sensor is further configured to sense the position of the airflow assembly and provide the position of the airflow assembly to the angle of attack processor; and
wherein the angle of attack processor is further configured to control the motor to generate the torque to damp the rotational movement of the shaft as well as the airflow assembly in response to the position of the airflow assembly.

### Claim 19 (depends on 11)

The process of operating an aircraft airflow sensor probe according to claim 11:
wherein the angle of attack processor is configured to receive an ambient temperature from a temperature sensor; and
wherein the angle of attack processor is further configured to control the motor to generate the torque to damp the rotational movement of the shaft as well as the airflow assembly in response to the ambient temperature.

### Claim 20 (depends on 11)

The process of operating an aircraft airflow sensor probe according to claim 11:
wherein the angle of attack processor is configured to receive aircraft configuration data from the aircraft; and
wherein the angle of attack processor is further configured to control the motor to generate the torque to damp the rotational movement of the shaft as well as the airflow assembly in response to the aircraft configuration data.