GROUND PROXIMITY SENSOR

• US 20110264314A1
• Filed: 04/27/2010
• Published: 10/27/2011
• Est. Priority Date: 04/27/2010
• Status: Active Grant

• Current Assignee: Honeywell International Inc.
• Original Assignee: Honeywell International Inc.
• Inventors: Parras, Gerald
• Granted Patent: US 8,135,503 B2
• Time in Patent Office: Days
• US Class Current: 701/16
• CPC Class Codes: G05D 1/0676 specially adapted for landing

Abstract

An unmanned aerial vehicle comprises a housing, a rotor that is rotated to propel the housing, a pressure sensor that generates a signal indicative of an air pressure proximate a bottom surface of the housing, and a processor configured to determine, based on the signal, when an increase in air pressure proximate the bottom surface is greater than or equal to a threshold value associated with the ground effect of the rotor, wherein the processor controls the rotor to cease rotating or decrease rotational speed to land the unmanned aerial vehicle upon determining that the increase in pressure is greater than or equal to the threshold value.

Claims

1. An unmanned aerial vehicle comprising:

a housing;

a rotor that is rotated to propel the housing;

a pressure sensor that generates a signal indicative of an air pressure proximate a bottom surface of the housing; and

a processor configured to determine, based on the signal, when an increase in air pressure proximate the bottom surface is greater than or equal to a threshold value associated with the ground effect of the rotor, wherein the processor controls the rotor to cease rotating or decrease rotational speed to land the unmanned aerial vehicle upon determining that the increase in pressure is greater than or equal to the threshold value.

2. The unmanned aerial vehicle of claim 1, wherein the processor determines when the increase in pressure proximate the bottom surface is greater than or equal to the threshold value by at least determining a difference between a first sample pressure and a second sample pressure, wherein the processor determines the first sample pressure based on the signal at initiation of a landing sequence of the unmanned aerial vehicle and determines the second sample pressure based on the signal during the landing sequence.

3. The unmanned aerial vehicle of claim 1, wherein the signal comprises a first signal generated by the pressure sensor at a first point in time and a second signal generated by the pressure sensor at a second point in time, wherein the processor determines when the increase in pressure proximate the bottom surface is greater than or equal to the threshold value by at least determining a first sample pressure value based on the first signal, determining a second sample pressure value based on the second signal, and determining if a difference between the first sample pressure value and the second sample pressure value is greater than or equal to the threshold value, wherein the processor controls the rotor to cease rotating or decrease rotational speed to land the unmanned aerial vehicle when the difference is equal to or greater than the threshold value.

4. The unmanned aerial vehicle of claim 1, wherein the threshold value is based on at least one of:

air density of air surrounding the unmanned air vehicle or a density altitude of air surrounding the unmanned air vehicle, a size of the housing, a weight of the unmanned aerial vehicle, or a thrust generated by the rotor.

5. The unmanned aerial vehicle of claim 1, wherein the threshold value is a function of an estimated weight of the unmanned aerial vehicle when a fuel container of the unmanned aerial vehicle is empty, a weight of fuel added to the fuel container of the unmanned aerial vehicle, and an estimated weight of fuel consumed.

6. The unmanned aerial vehicle of claim 1, further comprising a port defined by the bottom surface of the housing, the pressure sensor being pneumatically plumbed to the port.

7. The unmanned aerial vehicle of claim 6, further comprising a second port defined by the bottom surface of the housing, wherein the pressure sensor is also pneumatically plumbed to the second port.

8. The unmanned aerial vehicle of claim 1, wherein the threshold value corresponds to a predetermined height of the bottom surface of the housing relative to a landing surface.

9. The unmanned aerial vehicle of claim 8, wherein the predetermined height corresponds to a diameter of the rotor.

10. The unmanned aerial vehicle of claim 8, wherein the predetermined height is between about 0.15 meters and about 1 meter.

11. The unmanned aerial vehicle of claim 1, wherein the processor is configured to determine, based on the signal, when the increase in air pressure proximate the bottom surface is greater than or equal to the threshold value associated with the ground effect of the rotor during a landing sequence of the unmanned aerial vehicle.

12. A method comprising:

determining a pressure proximate a bottom surface of an air vehicle, the air vehicle comprising a rotor for propelling the air vehicle;

determining if an increase in air pressure proximate the bottom surface of the air vehicle is greater than or equal to a threshold value associated with ground effect of the rotor; and

controlling the rotor to cease rotation or slow rotational speed to land the air vehicle upon determining that the increase in pressure is greater than or equal to the threshold value.

13. The method of claim 12, wherein determining if the increase in pressure is equal to the threshold value comprises:

determining a first sample pressure proximate the bottom surface at a first point in time;

determining a second sample pressure proximate the bottom surface at a second point in time; and

determining if the difference between the first sample pressure and the second sample pressure is equal to or greater than the threshold value.

14. The method of claim 13, further comprising descending the air vehicle in a landing sequence, wherein the first sample pressure is taken prior to or at the initiation of the landing sequence of the air vehicle, and the second sample pressure is taken while the air vehicle is descending.

15. The method of claim 12, further comprising determining the threshold value based on a characteristic of air surrounding the air vehicle prior to determining if the increase in air pressure proximate the bottom surface of the air vehicle is greater than or equal to the threshold value.

16. The method of claim 15, wherein the characteristic of the air surrounding the air vehicle is at least one of an air density of the air surrounding the air vehicle or a density altitude of the air surrounding the air vehicle.

17. The method of claim 12, wherein the threshold value is based on at least one of:

a size of the air vehicle, a weight of the air vehicle, or a thrust created by the rotor.

18. The method of claim 12, wherein the threshold increase in pressure corresponds to a predetermined height of the bottom surface of the air vehicle relative to a landing surface.

19. The method of claim 12, wherein determining the pressure proximate the bottom surface of the air vehicle comprises receiving a signal generated by a pressure sensor, wherein the signal is indicative of the pressure proximate the bottom surface of the air vehicle.

20. A computer-readable medium comprising instructions for causing a programmable processor to:

determine a pressure proximate a bottom surface of an air vehicle, the air vehicle comprising a rotor for propelling the air vehicle;

determine if an increase in air pressure proximate the bottom surface of the air vehicle is greater than or equal to a threshold value associated with ground effect of the rotor; and

control the rotor to cease rotation or slow rotational speed to land the air vehicle upon determining that the increase in pressure is greater than or equal to the threshold value.