In re Brown

477 F.2d 946, 177 U.S.P.Q. (BNA) 691, 1973 CCPA LEXIS 349
CourtCourt of Customs and Patent Appeals
DecidedMay 17, 1973
DocketPatent Appeal No. 8887
StatusPublished
Cited by2 cases

This text of 477 F.2d 946 (In re Brown) is published on Counsel Stack Legal Research, covering Court of Customs and Patent Appeals primary law. Counsel Stack provides free access to over 12 million legal documents including statutes, case law, regulations, and constitutions.

Bluebook
In re Brown, 477 F.2d 946, 177 U.S.P.Q. (BNA) 691, 1973 CCPA LEXIS 349 (ccpa 1973).

Opinion

ALMOND, Senior Judge.

This appeal is from the decision of the Patent Office Board of Appeals sustaining the examiner’s rejection of claims 9 through 13, all the remaining claims of appellant’s application serial No. 403,522, filed October 13, 1964, entitled “Terrestrial Navigation System.” No claim has been allowed.

The invention relates to a terrestrial nagivation system that is capable of all-weather operation. An object as stated is:

* * * to provide a marine navigation system comprising an inertial system including a computer, a non-inertial velocity reference, and a third means such as [a] radiometric tracker or some other means of obtaining celestial angular measurements. The elements are interconnected in such a way that the integrated system is an effective, all-weather navigational apparatus with bounded errors, even in the event that only one celestial body may be tracked over a portion of a 24-hour cycle.

The application sets out “a block-diagram representation of the apparatus constituting the inventive system” in Fig. 1, reproduced below:

[948]*948The application states:

In the drawing, it is seen that four natured components are employed in the basic navigation system. One is a pure inertial system which includes an inertial platform and sensors similar to that provided by the Autoneties Division of North American Aviation, Inc. under the designation N7.
Also provided is a computer which serves a multi-purpose role as a necessary part of the pure inertial system and as the data-processing center for all components of the system. This computer might take the form of a programmable, general-purpose digital computer, such as an IBM 7074 (but not necessarily as large physically or in memory capacity), with appropriate analog-to-digital interfacing to other components in the system where necessary. The computer must have the capability of solving a set of recursive equations according to the Kalman least-squares filtering theory, as will be explained presently. It also must have the capability of handling the other data-processing chores encountered in a conventional hybrid-inertial system application.
The inventive system also includes a celestial tracker which is capable of tracking one or more celestial bodies, and this might take the form of the radiometric sun-moon tracker supplied by Collins Radio Company under the designation AN/SRN-4.
The inventive system also includes a non-inertial velocity reference instrument which may, in a marine application, be an electromagnetic log similar to that currently used by the United States Navy.
Additionally, the system may receive from other sources, such as LORAN, discrete position information, and these pieces of information will be incorporated into [the] system through the computer.
All of system components just described need not be operative at the same time. For example, the invention described here is an effective navigational device if the tracker is operative for only a portion of a 24-hour day, as would be the ease in sun tracking.

The brief1 states that “the present invention corrects the data received from' the pure inertial system by estimating the propagation in time of the errors contained in that system and subtracting these error estimates from the signal outputs of the pure inertial system.” The manner in which appellant obtains the error estimates is best described in the brief as follows:

The present invention takes the output signals of the pure inertial system (with its attendant errors) and the output signals of the non-inertial sources of navigation information (with its own attendant errors); and it feeds this information into a data processor where a difference is taken between corresponding ones of the signals. Thus, a third set of signals is generated which is representative only of the difference between the errors in the inertial data and the errors in the non-inertial data. It is important to realize that the true navigation data, being identical for both inertial and non-inertial sources of like functioning will be subtracted out, so that only the difference in error signals is subsequently operated upon. These difference error signals are operated on according to least-squares digital filtering techniques which were developed by Kalman * * *, and hence referred to as “Kalman filtering”.

The application cites two published articles in connection with reference “to the recursive equations of Kalman’s least-squares filtering theory,” 2 according to which the system is operated.

[949]*949Claim 9 reads (with paragraphing as employed by appellant at oral argument) :

9. A system for terrestrial navigation comprising:
inertial means including a plurality of inertial sensors defining a platform, said sensors generating a first set of signals representative of navigation data in a reference co-ordinate frame;
non-inertial means for generating a second set of signals representative of navigation data having a predetermined relation to the navigation data generated by said inertial means;
signal processing means receiving said first and second sets of signals for generating signals representative respectively of estimates of corresponding sets of predetermined navigational parameters,
said signal processing means including
difference means for generating signals representative of the differences between corresponding parameters of said sets of navigational parameters,
said signal processing means further including
discrete-time recursive least-squares filter means receiving said difference signals for generating signals representative of estimates of errors in said first set of signals; and
correction means for correcting said first set of signals in response to said signals representative of the error estimates in said first set of signals to thereby provide a third set of signals representative of improved estimates of said navigational parameters,
said filter means characterized by a discrete-time linear state model
with uncorrelated stochastic driving functions,
said model representing the dynamic variation of the errors in platform orientation, position and velocity in said first set of signals,
said model further representing time-correlated errors in said inertial sensors and time-correlated errors in said first set of signals,
said filter means further characterized by defining a linear relation between the states- in said state model and said difference signals.

Claims 10-13 are either directly or indirectly dependent on claim 9 and, for reasons which will become apparent, require no further discussion.

The claims stand rejected for failure to comply with 35 U.S.C. § 112

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Bluebook (online)
477 F.2d 946, 177 U.S.P.Q. (BNA) 691, 1973 CCPA LEXIS 349, Counsel Stack Legal Research, https://law.counselstack.com/opinion/in-re-brown-ccpa-1973.