Inertial system having correction means for effects of gravitational anomalies

• US 4,173,784 A
• Filed: 08/29/1977
• Issued: 11/06/1979
• Est. Priority Date: 08/29/1977
• Status: Expired due to Term

• Current Assignee: Kearfott Guidance and Navigation Corporation
• Original Assignee: Singer Company (SVP Holdings Ltd.)
• Inventors: Heath, William H., Richman, Jack
• Primary Examiner(s): Gruber, Felix D.
• Application Number:
  US05/828,730
• Time in Patent Office: 799 Days
• Field of Search: 364/453, 364/454, 364/443, 364/571, 235/307, 244/165, 244/175, 244/177, 244/3.2
• US Class Current: 701/220
• CPC Class Codes: G01C 21/185 for gravity
• CPC Class Codes: G06G 7/78 for direction-finding, locating, distance or velocity measuring, or navigation systems

Abstract

Conventional first and second Schuler tuned inertial platforms, that are physically displaced from each other by a predetermined distance, are employed in an inertial system to reduce navigation errors caused by the uncertainty in the earth'"'"'s gravitational field. In addition to the two Schuler tuned platforms, a conventional velocity measuring instrument is employed to provide damping to the inertial system. The invention takes advantage of the fact that for a pair of ideal platforms if the relative velocity between them as displaced sensors can be measured with moderate accuracy then performance rivaling that obtainable with a gradiometer aided inertial platform can be achieved.

Claims

1. An inertial navigation system for correcting the effects of gravitational anomalies comprising:

a first inertial navigation sensor,

a second inertial navigation sensor displaced from said first sensor by a predetermined distance,

means for providing correction signals to the output signals of said first and second inertial navigation sensors by processing the output signals of said first and second inertial sensors whereby said navigation system is corrected for the effects of gravitational errors.

2. The inertial system of claim 1 further comprising:

a multiplicity of N inertial sensors displaced a predetermined distance from each other, and

means for providing correction signals to the output signals of each of said sensors by processing the output signals of each of said sensors whereby said navigation system is corrected for the effects of gravitational errors, wherein N is equal to 3 or more.

3. An inertial system for correcting the effects of gravitational anomalies comprising:

a first Schuler tuned inertial platform,

a second Schuler tuned inertial platform displaced a predetermined distance from said first inertial platform,

means for providing an independent measurement of velocity,

means responsive to said independent velocity measurement for providing damping correction signals to the output of said first and second inertial platforms, and

means for providing delta correction signals to the output of said first and second inertial platforms.

4. The inertial system of claim 3 wherein the first and second Schuler tuned platform provides output velocity signals and comprises:

means for comparing the output velocity signals of said first and second Schuler tuned platforms for developing the inertial platform velocity residual signal.

5. The inertial system of claim 4 comprising:

means for summing said output velocity signals of said first and second Schuler tuned platforms for developing the average inertial platform velocity signal and average inertial platform position signal.

6. The inertial system of claim 5 comprising:

means for summing said damping and delta correction signals with said average inertial platform velocity signal and said average inertial platform position signal for providing estimated system velocity signal and estimated system position signal.

7. In an inertial navigation system having a first Schuler tuned platform and a second Schuler tuned platform displaced a predetermined distance apart, a plurality of summing, differencing and gain circuits interconnecting the output signals of each Schuler tuned platform, a plurality of identical transfer function circuits comprising summing, differencing and gain circuit and a velocity measuring circuit, the method of correcting for the effects of gravitational anomaly errors comprising:

separating the first and second Schuler tuned platforms a predetermined distance apart,

using the summing, differencing and gain circuits to combine the position and velocity output signals of said first Schuler tuned platform with the position and velocity output signals of said second Schuler tuned platform to obtain signals representative of average inertial platform velocity, average inertial platform position and inertial platform residual velocity,

using summing and differencing circuits of the transfer circuits to combine said average inertial platform position signal with a first and second position correcting signal, and

using said summing and differencing circuits of said transfer function circuit to combine said average inertial platform velocity signal with a first and second velocity correcting signal to obtain estimated system position and velocity signals corrected for gravitational anomalies.

8. The method of claim 7 comprising:

feeding back said estimated velocity signal and combining it with a signal from said velocity measuring circuit to provide a reference velocity residual signal as the input signal to the first velocity correcting circuit which provides said first velocity correcting signal,

feeding said reference velocity residual signal to a first position correcting circuit to provide said first position correcting signal,

feeding forward said platform velocity residual signal to provide the input signal to the second velocity correcting circuit which provides said second velocity correcting signal, and

feeding forward said platform velocity residual signal to provide the input signal to the second position correcting circuit which provides said second position correction signal.