Method for determining the heading of an aircraft

• US 4,930,085 A
• Filed: 10/15/1987
• Issued: 05/29/1990
• Est. Priority Date: 10/16/1986
• Status: Expired due to Fees

• Current Assignee: Litef GmbH (Northrop Grumman Corporation)
• Original Assignee: Litef GmbH (Northrop Grumman Corporation)
• Inventors: Kleinschmidt, Michael
• Primary Examiner(s): Chin, Gary
• Application Number:
  US07/109,238
• Time in Patent Office: 957 Days
• Field of Search: 364/449, 364/434, 364/453, 364/454, 364/459, 342/451, 342/357, 342/358, 73/178 R
• US Class Current: 701/207
• CPC Class Codes: G01C 21/165 combined with non-inertial navigation instruments

Abstract

A method is disclosed for determining the heading of an aircraft which is equipped with both an inertial navigation system and a device capable of receiving navigation satellite signals and computing the aircraft'"'"'s position, speed and acceleration therefrom. While the aircraft is still on the ground and before flight operations begin, an initial alignment of the inertial navigation system with an earth-fixed coordinate system is performed, and during this alignment, data corresponding to the initial attitude of an aircraft-fixed coordinate system relative to the earth-fixed coordinate system is also determined and stored. Thereafter, during flight operations, the acceleration vector of the aircraft relative to the aircraft-fixed coordinate system is measured by the inertial navigation system and then transposed into a coordinate system which has been horizontally aligned with the earth-fixed system using the initial attitude data. second acceleration vector, corresponding to the acceleration of the aircraft in the earth-fixed system, is computed using the navigation satellite system. The aircraft'"'"'s heading is then determined by computing the difference, i.e., the angle between, the two acceleration vectors. The method is amenable to Kalman filtering techniques and, by eliminating the need for highly accurate gyroscopes or magnetic compasses, permits rapid and highly accurate heading determinations to be made at much less expense.

Claims

1. A method for determining the heading of an aircraft equipped with at least one inertial navigation system that includes two accelerometers, and a device for receiving data obtained from the signals of navigation satellites and for computing the aircraft'"'"'s position, velocity, and acceleration therefrom, said method comprising the steps of:

(a) determining data corresponding to the initial attitude of an aircraft-fixed coordinate system relative to an earth-fixed coordinate system during a pre-flight alignment of the aircraft'"'"'s inertial navigation system;

then

(b) storing said initial attitude data;

then

(c) measuring the acceleration data occurring during operation with respect to the aircraft-fixed coordinate system;

then

(d) converting the acceleration data from the aircraft-fixed coordinate system into a coordinate system which has been horizontally aligned with the earth-fixed coordinate system using the initial attitude data;

then

(e) determining the heading from the difference angle (φ

_Z) between the acceleration vector (a_I^N,E), as converted into the horizontally-aligned inertial coordinate system, and an acceleration vector (a_S^N,E), as computed in the earth-fixed coordinate system from the satellite data.

2. A method as defined in claim 1, wherein the difference angle (φ

_Z) is the angular difference between a velocity vector, as determined in the horizontally-aligned, aircraft-fixed coordinate system by integrating the acceleration vector (a_I^N,E), and a velocity vector, as computed in the earth-fixed coordinate system from the satellite data.

3. A method as defined in claim 1 wherein the difference angle (φ

_Z) is formed continuously and is supplied to an azimuth filter.

4. A method as defined in claim 1 wherein the difference angle is formed at time intervals and is supplied to an azimuth filter.

5. A method as defined in claim 1, wherein the difference angle (φ

_Z) is the angular difference between a position vector, as determined in the horizontally-aligned, aircraft-fixed coordinate system by twice integrating the acceleration vector (a_I^N,E), and a position vector, as computer in the earth-fixed coordinate system from the satellite data.