Integrated GPS/inertial navigation apparatus providing improved heading estimates

• US 5,657,025 A
• Filed: 08/07/1995
• Issued: 08/12/1997
• Est. Priority Date: 08/07/1995
• Status: Expired due to Term

• Current Assignee: Litton Systems Incorporated (Northrop Grumman Corporation)
• Original Assignee: Litton Systems Incorporated (Northrop Grumman Corporation)
• Inventors: Brown, Ronald A., Ebner, Robert E.
• Primary Examiner(s): Issing, Gregory C.
• Application Number:
  US08/511,965
• Time in Patent Office: 736 Days
• Field of Search: 342/357, 342/394, 342/442, 364/453
• US Class Current: 701/300
• CPC Class Codes: G01C 21/165 combined with non-inertial navigation instruments
• CPC Class Codes: G01S 19/32 Multimode operation in a single same satellite system, e.g. GPS L1/L2
• CPC Class Codes: G01S 19/54 using carrier phase measurements; using long or short baseline interferometry

Abstract

The integrated GPS/inertial navigation apparatus utilizes satellite signals received with two spatially-separated antennas to achieve improved heading estimates for a mobile platform. Each satellite signal comprises one or more component signals with each component signal having a different carrier frequency. The integrated GPS/inertial navigation apparatus consists of a receiver and an inertial navigation system. The receiver measures the carrier phase of each of one or more component signals of one or more satellite signals received by each of the two antennas during successive time periods of duration T_p. Phase measured during a T_p time period is called T_p -phase. Only one component signal of one satellite signal received by one antenna is measured during any T_p time period. The receiver utilizes the T_p -phases of each component signal obtained during a T_k time period to estimate the phase of the component signal at the end of the T_k time period, the estimated phase at the end of the T_k time period being called the T_k -phase. The inertial navigation system, comprising inertial sensors and a digital processor, utilizes the T_k -phases in determining the heading of the vehicle and the displacement of each of the two antennas from the inertial sensors of the inertial navigation system. The measured phase of a component signal is subject to error as a result of the satellite signal traversing the ionosphere. The inertial navigation system achieves more accurate estimates of heading and antenna displacements by utilizing the T_k -phases in determining ionospheric corrections to phase.

Claims

1. Apparatus for use with two antennas on a mobile platform, the two antennas being capable of receiving signals from one or more satellites, each satellite signal comprising one or more component signals, each component signal having a different carrier frequency, the apparatus comprising:

a receiver which obtains satellite ephemeris data and measures the carrier phase of each of one or more component signals of one or more satellite signals received from one or more satellites by each of the two antennas during successive time periods of duration T_p, phase measured during a T_p time period being called T_p -phase, only one component signal of one satellite signal received by one antenna being measured during any single T_p time period, the receiver utilizing the T_p -phases of each component signal obtained during a T_k time period by each antenna to estimate the phase of the component signal at the end of the T_k time period, the estimated phase at the end of the T_k time period being called the T_k -phase, T_k being equal to or greater than T_p ;

an inertial navigation system comprising inertial sensors and a digital processor, the inertial navigation system utilizing measurements of platform acceleration and platform angular rotation rate in determining the positions of the two antennas and the heading of the platform, the inertial navigation system utilizing the satellite ephemeris data and the positions of the two antennas to obtain computed ranges from the two antennas to the satellites, the inertial navigation system utilizing the computed ranges and the T_k -phases in determining the error in the heading of the vehicle.

2. The apparatus of claim 1 wherein the nominal displacements of the two antennas from the inertial sensors are predetermined, the inertial navigation system utilizing the T_k -phases in determining the error in the displacement of each of the two antennas from the inertial sensors of the inertial navigation system.

3. The apparatus of claim 1 wherein the inertial navigation system utilizes the T_k -phases in determining the ionospheric corrections.

4. The apparatus of claim 1 wherein the inertial navigation system obtains estimates of navigation quantities including heading by utilizing a Kalman filter process, the time when new T_k -phases become available coinciding with the beginning of a Kalman filter iteration.

5. The apparatus of claim 1 wherein the inertial navigation system obtains estimates of navigation quantities including heading by utilizing a Kalman filter process, the new T_k -phases becoming available with the beginning of each Kalman filter iteration.

6. The apparatus of claim 1 wherein, the inertial navigation system obtains estimates of navigation quantities including heading by utilizing a Kalman filter process, one new T_k -phase becoming available with the beginning of each Kalman filter iteration.

7. The apparatus of claim 1 wherein the receiver comprises:

a component signal selector having a plurality of input ports, an output port, and a control input port, at least one of the input ports being connected to one antenna, the other input ports being connected to the other antenna, a control signal at the control input port causing the input ports to be successively connected to the output port for time periods T_p, the signal component selector causing a signal component of the signal entering the input port connected to the output port to be translated in frequency from an RF to an IF;

a processor having a signal input port, a control output port, and a data output port, the signal input port being connected to the output port of the signal component selector, the control output port being connected to the control input port of the component signal selector, the control signal being supplied to the component signal selector by the processor through the control output port, the data output port being connected to the inertial navigation system, the processor measuring the T_p -phase of the component signal entering the input port during each T_p time period and computing the T_k -phase for each component signal entering the input port during each T_k time period, the T_k -phases being supplied to the inertial navigation system through the data output port.

8. A method for determining the heading of a vehicle utilizing inertial sensors and at least one satellite signal, each satellite signal comprising one or more component signals, each component signal having a different carrier frequency, the method comprising the steps:

(a) obtaining satellite ephemeris data and measuring during successive time periods of duration T_p the phase of each of one or more component signals of one or more satellite signals received from one or more satellites at first and second predetermined points on the vehicle, the phase of only one component signal being measured during any T_p time period, a phase measured during a T_p time period being called a T_p -phase;

(b) computing the phase of each component signal of each satellite signal received at each of the first and second predetermined points at the end of a T_k time period utilizing the T_p -phases for that component signal measured during the T_k time period, the computed phase of a component signal at the end of a T_k time period being called a T_k -phase;

(c) utilizing measurements of platform acceleration and platform angular rotation rate referenced to a third predetermined point on the vehicle in determining the positions of the first and second predetermined points and the heading of the vehicle and then utilizing satellite ephemeris data and the positions of the first and second predetermined points to compute ranges from the first and second predetermined points to the one or more satellites at the end of a T_k time period;

(d) determining the error in vehicle heading at the end of a T_k time period utilizing the measurements and computations made in steps (a), (b), and (c);

(e) repeating steps (a), (b), (c), and (d) indefinitely.

9. The method of claim 8 wherein the nominal displacements of the first and second predetermined points from the third predetermined point are predetermined, the method further comprising the step:

(f) determining the errors in the displacements of the first and second predetermined points from the third predetermined point at the end of a T_k time period utilizing the measurements and computations made in steps (a), (b), and (c), step (f) being performed at the same time as step (d).

10. The method of claim 8 further comprising the step:

(g) determining the ionospheric corrections to the phases at the end of the T_k time period utilizing measurements, computations, and determinations made in steps (a), (b), and (c), the step (g) being performed at the same time as step (d).