Integrity limit apparatus and method

• US 5,512,903 A
• Filed: 05/23/1994
• Issued: 04/30/1996
• Est. Priority Date: 05/23/1994
• Status: Expired due to Term

• Current Assignee: Honeywell Incorporated (Honeywell International Inc.)
• Original Assignee: Honeywell Incorporated (Honeywell International Inc.)
• Inventors: Schmidtke, Keith B.
• Primary Examiner(s): Issing, Gregory C.
• Application Number:
  US08/247,787
• Time in Patent Office: 708 Days
• Field of Search: 342/357, 364/454
• US Class Current: 342/357.31
• CPC Class Codes: G01S 19/20 Integrity monitoring, fault detection or fault isolation of space segment
• CPC Class Codes: G01S 19/47 the supplementary measurement being an inertial measurement, e.g. tightly coupled inertial

Abstract

An apparatus and method for determining the hybrid integrity limit of a system which receives inputs from a Global Positioning System Receiver indicative of measurement information, autonomous position information and autonomous integrity limit information and receives inputs from an independent source means indicative of motion by determining the hybrid position from the measurement information and the motion inputs and then adding the difference between the autonomous position and the hybrid position to the autonomous integrity limit.

Claims

1. Apparatus for use with a plurality of GPS satellites for determining a hybrid integrity limit relative to a calculated hybrid position of an object comprising:

GPS receiver means proximate to the object to receive signals from the satellites and to produce a plurality of signals containing measurement information, information indicative of GPS position for the object and information indicative of GPS integrity limit relative to the GPS position;

sensing means proximate the object producing a plurality of signals containing information indicative of motion of the object;

hybrid function means connected to the sensing means and to the GPS receiver means to derive a signal indicative of hybrid position from the signals produced by the GPS receiver means and sensing means, deriving a value indicative of the difference between the hybrid position and the GPS position and deriving the hybrid integrity limit by adding the value indicative of the difference between the hybrid position and the GPS position to the GPS integrity limit.

2. Apparatus according to claim 1 wherein the object is an aircraft and the plurality of signals from the GPS receiver include information relative to the GPS position of the aircraft and the plurality of signals from the sensing means include information relative to the motion of the aircraft.

3. Apparatus according to claim 2 wherein the signals from the sensing means include information relative to aircraft attitude and rate of change of aircraft position.

4. Apparatus according to claim 1 wherein signals from the GPS receiver means, signals from the sensing means and signals from the hybrid function means are presented to a flight management system on an aircraft.

5. The method of determining a hybrid integrity limit from 1) signals from GPS receiver means containing satellite measurement information, GPS position information and GPS integrity limit information and 2) signals from sensing means containing motion information comprising the steps of:

a) computing a hybrid position from the signals in

     1) and

     2)

b) computing the difference between the GPS position and the hybrid position; and

;

c) adding the difference from step b) to the GPS integrity limit.

6. Apparatus for use in a hybrid GPS system which includes GPS receiver means to supply signals indicative of GPS position and GPS integrity limit, and includes hybrid function means to supply signals indicative of hybrid position, comprising in combination:

processor means to compute the difference between the GPS position and the hybrid position and to add the difference to the GPS integrity limit to produce a signal indicative of the hybrid integrity limit.

7. Apparatus according to claim 6 wherein the apparatus is mounted on an aircraft and the signals indicative of GPS position, GPS integrity limit, hybrid position and hybrid integrity limit are used in the operation of the aircraft.