Using the global positioning satellite system to determine attitude rates using doppler effects

• US 6,593,879 B1
• Filed: 08/09/2001
• Issued: 07/15/2003
• Est. Priority Date: 08/10/2000
• Status: Expired due to Fees

• Current Assignee: United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration
• Original Assignee: United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration
• Inventors: Campbell, Charles E.
• Primary Examiner(s): Blum, Theodore M.
• Application Number:
  US09/928,700
• Time in Patent Office: 705 Days
• Field of Search: 342/357.05, 342/357.11, 701/215
• US Class Current: 342/357.59
• CPC Class Codes: G01S 19/53 Determining attitude

Abstract

In the absence of a gyroscope, the attitude and attitude rate of a receiver can be determined using signals received by antennae on the receiver. Based on the signals received by the antennae, the Doppler difference between the signals is calculated. The Doppler difference may then be used to determine the attitude rate. With signals received from two signal sources by three antennae pairs, the three-dimensional attitude rate is determined.

Claims

1. A method of determining the attitude rate of a receiver comprising:

sending a first signal from a first signal source;

receiving the first signal with a first antenna on a receiver;

receiving the first signal with a second antenna on the receiver;

sending a second signal from a second signal source;

receiving the second signal with the first antenna;

receiving the second signal with the second antenna;

receiving the first signal with a third antenna on the receiver;

receiving the second signal with the third antenna;

determining the Doppler difference between the first signal and the second signal; and

determining a component of the attitude rate based on the Doppler difference between the first signal and second signal, wherein the first, second and third antennae are non-collinear.

2. The method of claim 1, wherein the first signal source is a first Global Positioning System satellite.

3. The method of claim 1, further comprising:

sending a second signal from a second signal source;

receiving the second signal with the first antenna;

receiving the second signal with the second antenna;

receiving the first signal with a third antenna on the receiver;

receiving the second signal with the third antenna;

receiving the first signal with a fourth antenna on the receiver;

receiving the second signal with the fourth antenna;

determining the Doppler difference from the received signals;

determining the attitude rate based on the Doppler difference between all of the received signals.

4. The method of claim 3, wherein the second signal source is a second Global Positioning System satellite.

5. The method of claim 3, wherein the first, second, third and fourth antennae are non-collinear and the fourth antennae is non-coplanar with the first second and third antennae.

6. A method of determining the attitude rate of a receiver comprising:

sending a first signal from a first signal source;

sending a second signal from a second signal source;

receiving the first signal with a first antenna on a receiver;

receiving the second signal with the first antenna;

receiving the first signal with a second antenna on the receiver;

receiving the second signal with the second antenna;

receiving the first signal with a third antenna on the receiver;

receiving the second signal with the third antenna;

receiving the first signal with a fourth antenna on the receiver;

receiving the second signal with the fourth antenna;

determining the Doppler difference between the received signals;

determining the three-dimensional attitude rate based on the Doppler difference between all of the received signals.