Instrument for measuring an aircraft's roll, pitch, and heading by matching position changes along two sets of axes

• US 5,406,489 A
• Filed: 07/10/1992
• Issued: 04/11/1995
• Est. Priority Date: 07/10/1992
• Status: Expired due to Term

• Current Assignee: Unisys Corporation
• Original Assignee: Unisys Corporation
• Inventors: Timothy, John D., Timothy, LaMar K., Bowen, Douglas G., Ownby, Michael L.
• Primary Examiner(s): ZANELLI, MICHAEL J
• Application Number:
  US07/911,430
• Time in Patent Office: 1,005 Days
• Field of Search: 364/434, 364/559, 364/449, 342/357, 342/451, 340/974, 340/975, 340/979
• US Class Current: 701/4
• CPC Class Codes: G01C 21/165 combined with non-inertial navigation instruments
• CPC Class Codes: G01S 19/54 using carrier phase measurements; using long or short baseline interferometry

Abstract

An instrument for indirectly measuring the attitude of a moving aircraft includes three accelerometers, a GPS radio receiver, an electronic estimating module, and an electronic output module. The three accelerometers indicate three accelerations of the aircraft respectively along three aircraft body axes. The GPS radio receiver receives from GPS satellites the position and velocity of the aircraft along an earth fixed axis. The electronic estimating module estimates a vector such that a series of aircraft position changes along the three body axes that are caused by the measured accelerations, times the vector, approximately matches a corresponding series of position changes along the earth fixed axis as given by the receiver. The electronic output module generates a visual display of the roll, pitch, or heading of the aircraft by performing trigonometric functions on the vector.

Claims

1. An instrument for indirectly measuring the attitude of a moving aircraft;

said instrument comprising;

three accelerometers mounted on said aircraft such that they indicate three accelerations of said aircraft respectively along three aircraft body axes;

a radio receiver in said aircraft which receives from an external source, the position and velocity of said aircraft along an earth fixed axis;

an electronic estimating module, coupled to said accelerometers and said receiver, which a) estimates a vector such that a series of aircraft position changes along said three body axes that are caused by said measured accelerations, times said vector, approximately match a corresponding series of position changes along said earth fixed axis as indicated by said receiver, and b) estimates said vector in a recursire fashion such that the vector estimates at time instant "i" is a modification of the preceding vector estimate at time instant i-1; and

,

an electronic output module, coupled to said estimating module, which generates an output signal that indicates the roll, pitch, or heading of said aircraft by performing trigonometric functions on said vector.

2. An instrument according to claim 1 wherein said modification is of the form:

space="preserve" listing-type="equation">b(i)=b(i-1)+K[Δ

P.sub.aE (i)-A(i)b(i -1)]

where

b(i) is an estimate of said vector at time instant "i";

b(i-1) is a preceding estimate of said vector at time instant "i-1";

Δ

P_aE (i) is said series of position changes along said earth fixed axis;

A(i) is said series of position changes along said three aircraft body axes; and

,

K is a gain matrix.

3. An instrument according to claim 2 wherein said electronic estimating module is a special purpose sequential digital logic circuit.

4. An instrument according to claim 2 wherein said electronic estimating module is a programmable general purpose microprocessor with a special purpose estimating program.

5. An instrument according to claim 1 wherein said series of position changes consists of exactly three position changes per axis.

6. An instrument according to claim 1 wherein said series of position changes consists of from three to ten position changes per axis.

7. An instrument according to claim 1 wherein each position change of said series occurs during a time interval of from one-half to two seconds.

8. An instrument according to claim 1 wherein said radio receiver receives the position and velocity of said aircraft along multiple earth fixed axes;

and, said estimating module estimates a vector for each earth fixed axis such that a series of aircraft position changes along said three body axis times a respective one of said vectors approximately matches a series of position changes along a corresponding one of said earth fixed axes.

9. An instrument according to claim 1 wherein said accelerometers are mounted on said aircraft such that they measure accelerations in the direction of the aircraft'"'"'s nose and the aircraft'"'"'s wing and another axis which is perpendicular thereto.

10. An instrument according to claim 1 wherein each of said accelerometers is selected from a group which consists of a strain gauge accelerometer and a piezoelectric accelerometer.

11. An instrument according to claim 1 wherein said radio receiver has an input which receives said position and velocity of said aircraft along said earth fixed axis from global positioning satellites in orbit around the earth.