FAULT DETECTION AND RECONFIGURATION OF AN AUTOMATED REFUELING BOOM

• US 20080270027A1
• Filed: 04/30/2007
• Published: 10/30/2008
• Est. Priority Date: 04/30/2007
• Status: Active Grant

• Current Assignee: Sysense Incorporated, The Boeing Co.
• Original Assignee: Sysense Incorporated
• Inventors: Takacs, John F., Stecko, Stephen M., Speyer, Jason L., Williamson, Walton
• Granted Patent: US 7,769,543 B2
• Time in Patent Office: Days
• US Class Current: 701/214
• CPC Class Codes: B64D 39/00 Refuelling during flight filling or emptying fuel tanks B64D37/14
• CPC Class Codes: G01S 19/14 specially adapted for specific applications
• CPC Class Codes: G01S 19/20 Integrity monitoring, fault detection or fault isolation of space segment
• CPC Class Codes: G01S 19/49 whereby the further system is an inertial position system, e.g. loosely-coupled
• CPC Class Codes: G01S 5/163 Determination of attitude using inertial means G01C9/00; control of attitude G05D1/49

Abstract

A system for automated control of a refueling boom coupled to a tanker aircraft is provided. The system includes sensors such as electro-optical sensor or GPS sensors that provide measurements used by the system to automatically control the refueling boom so as to mate with a receiver aircraft. The system is configured to monitor the health of the sensors and to reconfigure itself if any of the sensor are faulty.

Claims

1. A system for detection of sensor faults with regard to the automated control of a refueling boom coupled to a tanker aircraft, comprising:

a first GPS receiver adapted to process signals from a GPS antenna attached to the tanker aircraft, and

at least one processor adapted to calculate ranges from the GPS antenna to a constellation of GPS satellites transmitting the signals being processed by the GPS receiver, the processor being further adapted to order the GPS satellites into a plurality of subsets, wherein each subset includes all GPS satellites except one such that each subset uniquely corresponds to its excepted GPS satellite, the processor being further adapted to calculate ranges between the GPS antenna and each of the GPS satellites in each subset, and wherein the processor is adapted to analyze noise characteristics associated with the ranges to determine if an excluded satellite is faulty and to calculate a GPS location for the GPS antenna based upon the calculated ranges that do not depend upon the faulty GPS satellite.

2. The system of claim 1, wherein the process is further adapted to calculate the ranges between the GPS antenna and each of the GPS satellites in each subset using a least squares method.

3. The system of claim 1, further comprising:

a first inertial measurement unit (IMU) providing inertial measurements for the tanker aircraft;

wherein the processor is further adapted to calculate a first inertial navigation state for the tanker aircraft through integration of the inertial measurements, the processor being further adapted to calculate a first inertial navigation state error relative to the GPS location and to filter the first inertial navigation state error and the first inertial navigation state based upon noise characteristics of the first IMU and the first GPS receiver to provide an updated inertial navigation state for the tanker aircraft, the processor being further adapted to control actuation of the refueling boom relative to a receiver aircraft based upon the first and updated inertial navigation states.

4. The system of claim 3, wherein the processor is adapted to calculate the first inertial navigation error by translating an IMU location from the first inertial navigation state to the GPS location.

5. The system of claim 4, wherein the processor is adapted to filter the first inertial navigation state using a Kalman filter.

6. The system of claim 1, wherein the processor is adapted to analyze the noise characteristics associated with the ranges using a probability ratio test.

7. The system of claim 6, wherein the probability ratio test is a Multiple Hypothesis Shiryayev Sequential Probability Ratio Test (MHSSPRT).

8. The system of claim 5, wherein the Kalman filter is an extended Kalman filter.

9. A method for detection of sensor faults with regard to the automated control of a refueling boom coupled to a tanker aircraft, the tanker aircraft having a GPS receiver adapted to process signals from a GPS antenna attached to the tanker aircraft, the signals originating from a plurality of GPS satellites, the method comprising:

ordering the GPS satellites into sets, each set comprising all of the plurality of GPS satellites except one such that each set corresponds uniquely to an excluded GPS satellite;

for each set, calculating the ranges between the GPS antenna and the set'"'"'s GPS satellites;

analyzing the ranges to determine whether one of the excluded GPS satellites is faulty;

if an excluded GPS satellite is faulty, calculating a GPS position for the GPS antenna based upon the ranges from the set that excludes the faulty GPS satellite; and

actuating the refueling boom so as to mate with a receiver aircraft responsive to the calculated GPS position.

10. The method of claim 9, wherein calculating the ranges comprises using a least squares method.

11. The method of claim 9, wherein analyzing the ranges to determine whether one of the excluded GPS satellites is faulty comprises analyzing a noise characteristic of the ranges.

12. The method of claim 11, wherein analyzing the noise characteristic of the ranges comprises analyzing probability distribution of the ranges.

13. The method of claim 12, wherein analyzing the probability distributions comprises forming a probability ratio test.

14. The method of claim 13, wherein the probability ratio test is a Multiple Hypothesis Shiryayev Sequential Probability Ratio Test (MHSSPRT).

15. The method of claim 11, further comprising actuating the refueling boom responsive to inertial measurements from an inertial measurement unit.

16. A method for detection of sensor faults with regard to the automated control of a refueling boom coupled to a tanker aircraft, the tanker aircraft including an electro-optic sensor configured to provide optical measurements for a plurality of reference points, the method comprising;

ordering the optical measurements into a plurality of sets, each set comprising all the optical measurements except one such that each set uniquely corresponds to an excluded optical measurement;

analyzing a noise characteristic for each set to determine whether one of the excluded optical measurements is faulty; and

if there is a faulty optical measurement;

actuating the refueling boom so as to mate with a receiver aircraft using the optical measurements but not the faulty optical measurement.

17. The method of claim 16, wherein analyzing the noise characteristic comprises analyzing probability distribution of the optical measurements.

18. The method of claim 17, wherein analyzing the probability distributions comprises forming a probability ratio test.

19. The method of claim 18, wherein the probability ratio test is a Multiple Hypothesis Shiryayev Sequential Probability Ratio Test (MHSSPRT).

20. The method of claim 16, further comprising actuating the refueling boom responsive to inertial measurements from an inertial measurement unit.