Method and apparatus of integrating Global Positioning System and Inertial Navigation System without using accelerometers

• US 5,193,064 A
• Filed: 10/09/1990
• Issued: 03/09/1993
• Est. Priority Date: 10/09/1990
• Status: Expired due to Term

• Current Assignee: Lockheed Martin Corporation (Martin Marietta Corporation)
• Original Assignee: General Dynamics Corporation
• Inventors: Maki, Stanley C.
• Primary Examiner(s): Black, Thomas G.
• Application Number:
  US07/594,894
• Time in Patent Office: 882 Days
• Field of Search: 364/449, 364/453, 364/443, 364/459, 364/434, 364/454, 244/176
• US Class Current: 701/221
• CPC Class Codes: G01C 21/165 combined with non-inertial navigation instruments
• CPC Class Codes: G01S 19/49 whereby the further system is an inertial position system, e.g. loosely-coupled
• CPC Class Codes: G01S 19/53 Determining attitude
• CPC Class Codes: G05D 1/0825 using mathematical models

Abstract

A method and arrangement for integrating a Global Positioning System and an Inertial Navigating System without the use of accelerometers to provided a velocity steering signal that is utilized in the guidance of a flying vehicle, such as a space craft. The method and arrangement do not require the use of accelerometers. A mechanization for interfacing the integrated Global Positioning System and the Inertial Navigating System with a flight control system which controls a flying vehicle is disclosed.

Claims

1. A guidance system for a flying vehicle which includes:

means to sense from the dynamics of the flying vehicle information relating to the position and the velocity of the vehicle;

a GPS means responsive to the position and velocity information to provide velocity and position vectors and components of the velocity vector;

a guidance algorithm means responsive to the current position and velocity vectors of the vehicle to provide certain steering information and to provide a velocity vector to be gained;

a velocity steering means responsive to the velocity vector to be gained provided by the guidance algorithm means and to components of the velocity vector provided by the GPS to generate a steering rate vector, and

means responsive to the steering rate vector provided by the velocity steering means to adjust accordingly the attitude of the flight vehicle.

2. The flying vehicle guidance system of claim 1 wherein the means responsive to the steering rate vector includes:

gyroscope means, and

transformation means to tightly couple the velocity steering signal to the gyroscopic means.

3. The flying vehicle guidanoe system of claim 2 wherein the gyroscope means are strapped down to the body of the flight vehicle.

4. The flying vehicle guidance means of claim 1 wherein the means responsive to the steering rate vector includes a gyroscope means which directly receives the velocity steering signal.

5. The flying vehicle guidance means of claim 1 wherein the flying vehicle is a spacecraft which has an engine gimbal control means and the means responsive to the steering rate vector provided by the velocity steering means is coupled to the engine gimbal control means.