Apparatus for an automated aerial refueling boom using multiple types of sensors

• US 8,757,548 B2
• Filed: 04/30/2007
• Issued: 06/24/2014
• Est. Priority Date: 04/30/2007
• Status: Expired due to Fees

• Current Assignee: Sysense Incorporated, The Boeing Co.
• Original Assignee: Sysense Incorporated, The Boeing Co.
• Inventors: Stecko, Stephen M., Williamson, Walton, Takacs, John F., Speyer, Jason L.
• Primary Examiner(s): DINH, TIEN QUANG
• Application Number:
  US11/742,409
• Publication Number:
  US 20080265097A1
• Time in Patent Office: 2,612 Days
• Field of Search: 244/135.A, 701/214, 701/200
• US Class Current: 244/135.A
• CPC Class Codes: B64D 39/00 Refuelling during flight filling or emptying fuel tanks B64D37/14
• CPC Class Codes: G01C 21/188 for accumulated errors, e.g. by coupling inertial systems with absolute positioning systems
• CPC Class Codes: G01S 19/14 specially adapted for specific applications
• CPC Class Codes: G01S 19/49 whereby the further system is an inertial position system, e.g. loosely-coupled

Abstract

A system for automated control of a refueling boom coupled to a tanker aircraft is provided. The system includes: a first inertial measurement unit (IMU) providing inertial measurements for the tanker aircraft; a first GPS receiver providing a GPS location for a GPS antenna attached to the tanker aircraft; and a processor 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 the refueling boom relative to a receiver aircraft based upon the first and updated inertial navigation states.

Claims

1. A method of controlling a refueling boom relative to a tanker aircraft and a receiver aircraft, comprising:

deriving an inertial navigation state for the tanker aircraft;

deriving an inertial navigation state for the receiver aircraft;

determining a GPS-sensor-derived position estimate for a GPS sensor on the tanker aircraft;

determining an inertial measurement unit (IMU)-derived position estimate for the GPS sensor on the tanker aircraft using an IMU on the tanker aircraft;

determining a UPS-sensor-derived position estimate for a GPS sensor on the receiver aircraft;

determining an IMU-derived position estimate for the GPS sensor on the receiver aircraft using an IMU on the receiver aircraft;

determining a GPS relative difference between the GPS-sensor-derived position estimates;

determining an IMU relative difference between the IMU-derived position estimates;

determining an absolute difference between the IMU-derived position estimate and the GPS-sensor-derived position estimate for a first one of the tanker and receiver GPS sensors;

filtering the absolute difference, the IMU relative difference, and the GPS relative difference to derive an absolute navigation state error for the aircraft having the first GPS sensor and to derive a relative navigation state error between the aircraft having the first GPS sensor and a remaining one of the tanker and receiver aircrafts;

correcting the inertial navigation states using the absolute and relative navigation state errors; and

controlling the refueling boom based upon the corrected inertial navigations states so as to automatically mate with the receiver aircraft.

2. The method of claim 1, wherein the filtering comprises a Kalman filtering.

3. The method of claim 2, wherein the Kalman filtering comprises an extended Kalman filtering.

4. The method of claim 1, wherein deriving the inertial navigation states for the receiver and tanker aircrafts comprising integrating inertial measurements from inertial measurement units.

5. The method of claim 4, wherein integrating the inertial measurements comprises a non-linear integrating of the inertial measurements.

6. The method of claim 1, further comprising transferring fuel from the tanker aircraft to the receiver aircraft.

7. The method of claim 1, wherein deriving the absolute and relative navigation errors includes processing electro-optic measurements of a reference point on either the tanker or the receiver aircraft.

8. A method of controlling a refueling boom relative to a tanker aircraft and a receiver aircraft, comprising:

deriving an inertial navigation state for the tanker aircraft;

deriving an inertial navigation state for the receiver aircraft;

determining a GPS-sensor-derived position estimate for a GPS sensor on the tanker aircraft;

determining an inertial measurement unit (IMU)-derived position estimate for the GPS sensor on the tanker aircraft using an IMU on the tanker aircraft;

determining a GPS-sensor-derived position estimate for a GPS sensor on the receiver aircraft;

determining an IMU-derived position estimate for the GPS sensor on the receiver aircraft using an IMU on the receiver aircraft;

determining a GPS relative difference between the GPS-sensor-derived position estimates;

determining an IMU relative difference between the IMU-derived position estimates;

determining an absolute difference between the IMU-derived position estimate for the tanker aircraft and the GPS-sensor-derived position estimate for the tanker aircraft;

filtering the absolute difference, the IMU relative difference, and the GPS relative difference to derive an absolute navigation state error for the tanker aircraft and to derive a relative navigation state error between the tanker aircraft and the receiver aircraft;

correcting the inertial navigation states using the absolute and relative navigation state errors; and

controlling the refueling boom based upon the corrected inertial navigations states so as to automatically mate with the receiver aircraft.

9. A method of controlling a refueling boom relative to a tanker aircraft and a receiver aircraft, comprising:

deriving an inertial navigation state for the tanker aircraft;

deriving an inertial navigation state for the receiver aircraft;

determining a UPS-sensor-derived position estimate for a GPS sensor on the tanker aircraft;

determining an inertial measurement unit (IMU)-derived position estimate for the GPS sensor on the tanker aircraft using an IMU on the tanker aircraft;

determining a GPS-sensor-derived position estimate for a GPS sensor on the receiver aircraft;

determining an IMU-derived position estimate for the GPS sensor on the receiver aircraft using an IMU on the receiver aircraft;

determining a GPS relative difference between the GPS-sensor-derived position estimates;

determining an IMU relative difference between the IMU-derived position estimates;

determining an absolute difference between the IMU-derived position estimate for the receiver aircraft and the GPS-sensor-derived position estimate for the receiver aircraft;

filtering the absolute difference, the IMU relative difference, and the GPS relative difference to derive an absolute navigation state error for the receiver aircraft and to derive a relative navigation state error between the receiver aircraft and the tanker aircraft;

correcting the inertial navigation states using the absolute and relative navigation state errors; and

controlling the refueling boom based upon the corrected inertial navigations states so as to automatically mate with the receiver aircraft.