Architecture for air data probe power supply control

Patent metadata

Field	Value
Publication number	US-10179654-B2
Application number	US-201514887925-A
Country	US
Kind code	B2
Filing date	Oct 20, 2015
Priority date	Oct 20, 2015
Publication date	Jan 15, 2019
Grant date	Jan 15, 2019

Abstract

A system for power management of air data probes is provided. The system comprises a power source in an aircraft, and two or more air data probes electrically connected to the power source. Each of the air data probes comprises a body structure coupled to a fuselage of the aircraft, and at least one electrical heater coupled to the body structure and in electrical communication with the power source. A switching mechanism is coupled between the power source and the electrical heater of each of the air data probes. The switching mechanism is controllable such that the electrical heater of each of the air data probes is electrically connectable to the power source in parallel or in series.

First claim

What is claimed is:

1. A system for power management of air data probes, the system comprising:
a power source configured to be mounted in an aircraft;
two or more air data probes electrically connected to the power source, wherein each of the air data probes comprises:
a body structure configured to be coupled to a fuselage of the aircraft; and
at least one electrical heater coupled to the body structure and in electrical communication with the power source; and

a switching mechanism coupled between the power source and the electrical heater of each of the air data probes;
wherein the switching mechanism is controllable such that the electrical heater of each of the air data probes is electrically connectable to the power source in parallel or in series;
wherein the switching mechanism is controllable such that the electrical heater in each of the air data probes is:
electrically connected to the power source in parallel when the aircraft is in flight and
electrically connected to the power source in series when the aircraft is on ground.

2. The system of claim 1 , wherein the switching mechanism is activated by an indication of weight on wheels of the aircraft.

3. The system of claim 1 , wherein the switching mechanism is activated by commands from a cockpit of the aircraft.

4. The system of claim 1 , wherein the switching mechanism is activated by an indication of airspeed around the aircraft.

5. The system of claim 1 , wherein the switching mechanism is activated by commands from an air data system computer or hosted air data software.

6. The system of claim 1 , further comprising a control unit operatively coupled to the switching mechanism.

7. The system of claim 6 , wherein the control unit comprises:
an air data heater control unit; or
a probe heat computer.

8. The system of claim 6 , wherein the control unit comprises:
a remote power distribution unit; or
an aircraft electrical power distribution system component.

9. The system of claim 1 , wherein one or more of the electrical heaters comprises a helical coil heater cable.

10. The system of claim 1 , wherein one or more of the electrical heaters comprises a positive temperature coefficient resistance material.

11. The system of claim 1 , wherein one or more of the electrical heaters comprises a material having a resistance that is substantially independent of temperature.

12. An air data probe, comprising:
a hollow body structure that includes a probe strut, a probe body, and a probe tip, wherein the probe strut is configured to be coupled to a fuselage of an aircraft, and the probe tip has an opening that allows outside air to pass from the probe tip into the probe body;
two or more electrical heaters coupled to the body structure and configured for electrical communication with an aircraft power source; and
a switching mechanism coupled to each of the electrical heaters and configured for electrical communication with the aircraft power source;
wherein the switching mechanism is controllable such that the electrical heaters are electrically connectable to the aircraft power source in parallel or in series;
wherein the switching mechanism is controllable such that the electrical heaters are:
electrically connected to the aircraft power source in parallel when the aircraft is in flight; and
electrically connected to the aircraft power source in series when the aircraft is on ground.

13. The air data probe of claim 12 , wherein each of the electrical heaters comprises a helical coil heater cable.

14. A method of fabricating an air data probe, the method comprising:
forming a hollow body structure that includes a probe strut, a probe body, and a probe tip, wherein the probe strut is configured to be coupled to a fuselage of an aircraft, and the probe tip has an opening that allows outside air to pass from the probe tip into the probe body;
coupling a plurality of electrical heaters to the body structure, the electrical heaters configured for electrical communication with an aircraft power source; and
coupling a switching mechanism to the electrical heaters, the switching mechanism configured for electrical communication with the aircraft power source, wherein the switching mechanism is controllable such that the electrical heaters are electrically connectable to the aircraft power source in parallel or in series, wherein the switching mechanism is controllable such that the electrical heaters are:
electrically connected to the aircraft power source in parallel when the aircraft is in flight; and
electrically connected to the aircraft power source in series when the aircraft is on ground.

15. The method of claim 14 , wherein one or more of the electrical heaters comprise a helical coil heater cable.

16. The method of claim 15 , wherein one or more of the helical coil heater cables is coupled to the body structure by brazing or soldering to an inner surface of the body structure.

17. The method of claim 15 , wherein one or more of the helical coil heater cables is coupled to the body structure by brazing or soldering to an outer surface of the body structure.

18. The method of claim 15 , wherein one or more of the helical coil heater cables is coupled to the body structure by brazing or casting the helical coil heater cable between inner and outer surfaces of the body structure.

Assignees

• Honeywell Int Inc

Inventors

• Anderson Morris G
• Cox James B
• Garde Jason
• Gordon Grant A
• Kimmel Danny Thomas

Classifications

• H05B2203/02

  Heaters using heating elements having a positive temperature coefficient · CPC title

• G01P13/025

  indicating air data, i.e. flight variables of an aircraft, e.g. angle of attack, side slip, shear, yaw · CPC title

• B64D15/20

  Means for detecting icing or initiating de-icing · CPC title

• B64D2221/00

  Electric power distribution systems onboard aircraft · CPC title

• G01P5/165 Primary

  Arrangements or constructions of Pitot tubes · CPC title