Patent US3905563A successfully refreshed from Google Patents.
US3905563A
Expired / Lapsed
US
⏱️ 0.0 years remaining
System for controlling a missile motion in the homing mode
Assignee: Subaru Corp
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Filing: 1973-04-25
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Granted: 1975-09-16
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Expires: 1993-04-25
Abstract
Abstract A system for controlling a missile motion in the homing mode comprises means for designating by an error signal a direction in which a missile is guided in the homing mode, and means for compounding with the error signal a predetermined biasing signal imparting acceleration in one or two dimensions normal to a direction of the missile derivation. The biasing signal causes shells from anti-aircraft guns and anti-missile missiles to increase the miss-distance to the missile, within the allowable maneuverability of the missile, whereby the missile evades defensive action and finally zeroes in on a target.
Inventors
- 👤 Saburo Nagoshi
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-10-27 17:36
CPC Classifications
F; F41; F41G; F41G7/00; F41G7/20; F41G7/22; F41G7/224; F41G7/34; G; G05; G05D; G05D1/00; G05D1/12
Claims Analysis
Total Claims: 12
Claim 1
Independent Claim
123 words
A system for guiding an in-flight homing missile to a target, comprising: sighting means for tracking the location of a line of sight from the missile to the target; detector means responsive to said sighting means for generating an error signal depending upon any deviation of the missile flight path from said line of sight; steering means for changing the course of the missile; control means for said steering means connected to said detector means for delivering a corrective signal deriveD from said error signal to said steering means; and biasing means connected to said control means for superimposing upon said corrective signal to a lateral-acceleration signal effective in a direction perpendicular to an invariable reference direction generally parallel to said flight path.
Claim 2
Independent Claim
123 words
A system for guiding an in-flight homing missile to a target, comprising: sighting means for tracking the location of a line of sight from the missile to the target; detector means responsive to said sighting means for generating an error signal depending upon any deviation of the missile flight path from said line of sight; steering means for changing the course of the missile; control means for said steering means connected to said detector means for delivering a corrective signal deriveD from said error signal to said steering means; and biasing means connected to said control means for superimposing upon said corrective signal to a lateral-acceleration signal effective in a direction perpendicular to an invariable reference direction generally parallel to said flight path.
Claim 3
Dependent Claim
39 words
A system as defined in claim 1, further comprising circuit means for generating a feedback signal subtracted by said lateral-acceleration signal to obtain a differential signal which is from said error signal so as to obtain a control signal.
Claim 4
Independent Claim
133 words
A system for guiding an in-flight homing missile to a target, comprising: sighting means for tracking the location of a line of sight from the missile to the target; detector means responsive to said sighting means for generating an error signal depending upon any deviation of the missile flight path from said line of sight; steering means for changing the course of the missile; control means for said steering means connected to said detector means for delivering a corrective signal derived from said error signal to said steering means; and biasing means connected to said control means for superimposing upon said corrective signal a lateral-acceleration signal effective in a direction perpendicular to an invariable reference direction generally parallel to said flight path and further adding an ecceleration bias to the missile derivation direction.
Claim 5
Independent Claim
133 words
A system for guiding an in-flight homing missile to a target, comprising: sighting means for tracking the location of a line of sight from the missile to the target; detector means responsive to said sighting means for generating an error signal depending upon any deviation of the missile flight path from said line of sight; steering means for changing the course of the missile; control means for said steering means connected to said detector means for delivering a corrective signal derived from said error signal to said steering means; and biasing means connected to said control means for superimposing upon said corrective signal a lateral-acceleration signal effective in a direction perpendicular to an invariable reference direction generally parallel to said flight path and further adding an ecceleration bias to the missile derivation direction.
Claim 6
Dependent Claim
40 words
A system as defined in claim 3, further comprising circuit means for generating a feedback signal subtracted by said lateral-acceleration signal to obtain a differential signal which is deducted from said error signal so as to obtain a control signal.
Claim 7
Independent Claim
140 words
A system for guiding an in-flight homing missile to a target, comprising: sighting means for tracking the location of a line of sight from the missile to the target; detector means responsive to said sighting means for generating an error signal depending upon any deviation of the missile flight path from said line of sight; steering means for changing the course of the missile; control means for said steering means connected to said detector means for delivering a corrective signal derived from said error signal to said steering means, said control means establishing a set of three coordinate axes including a first axis generally parallel to said flight path and two other axes orthogonal thereto; and biasing means connected to said control means for superimposing upon said corrective signal two lateral-acceleration signals effective in directions parallel to said other axes.
Claim 8
Independent Claim
140 words
A system for guiding an in-flight homing missile to a target, comprising: sighting means for tracking the location of a line of sight from the missile to the target; detector means responsive to said sighting means for generating an error signal depending upon any deviation of the missile flight path from said line of sight; steering means for changing the course of the missile; control means for said steering means connected to said detector means for delivering a corrective signal derived from said error signal to said steering means, said control means establishing a set of three coordinate axes including a first axis generally parallel to said flight path and two other axes orthogonal thereto; and biasing means connected to said control means for superimposing upon said corrective signal two lateral-acceleration signals effective in directions parallel to said other axes.
Claim 9
Dependent Claim
39 words
A system as defined in claim 5, further comprising circuit means for generating feedback signals substracted by said lateral-acceleration signals to obtain a differential signal which is deducted from said error signal so as to obtain a control signal.
Claim 10
Independent Claim
151 words
A system for guiding an in-flight homing missile to a target, comprising: sighting means for tracking the location of a line of sight from the missile to the target; detector means responsive to said sighting means for generating an error signal depending upon any deviation of the missile flight path from said line of sight; steering means for changing the course of the missile; control means for said steering means connected to said detector means for delivering a corrective signal derived from said error signal to said steering means, said control means establishing a set of three coordinate axes including a first axis generally parallel to said flight path and two other axes orthogonal thereto; and biasing means connected to said control means for superimposing upon said corrective signal two lateral-acceleration signals effective in directions parallel to said other axes and further adding in acceleration bias to the missile derivation direction.
Claim 11
Independent Claim
151 words
A system for guiding an in-flight homing missile to a target, comprising: sighting means for tracking the location of a line of sight from the missile to the target; detector means responsive to said sighting means for generating an error signal depending upon any deviation of the missile flight path from said line of sight; steering means for changing the course of the missile; control means for said steering means connected to said detector means for delivering a corrective signal derived from said error signal to said steering means, said control means establishing a set of three coordinate axes including a first axis generally parallel to said flight path and two other axes orthogonal thereto; and biasing means connected to said control means for superimposing upon said corrective signal two lateral-acceleration signals effective in directions parallel to said other axes and further adding in acceleration bias to the missile derivation direction.
Claim 12
Dependent Claim
40 words
A system as defined in claim 7, further comprising circuit means for generating a feedback signal subtracted by said lateral-acceleration signal to obtain a differential signal which is deducted from said error signal so as to obtain a control signal.
References Cited (Backward Citations)
USPTO Annuity & Maintenance Windows
| Annuity Stage | Window Opens | Payment Deadline | Surcharge Period Until | Estimated Fee | Status |
|---|---|---|---|---|---|
| 3.5 Years (Year 4) | 1978-09-15 | 1979-03-17 | 1979-09-16 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1982-09-15 | 1983-03-17 | 1983-09-16 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1986-09-15 | 1987-03-17 | 1987-09-16 | $7700.00 | Window Closed / Lapsed |