US4315609A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Target locating and missile guidance system
Assignee: United States Department of the Navy
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Filing: 1971-06-16
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Granted: 1982-02-16
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Expires: 1991-06-16
Abstract
Abstract A target locating and missile guidance system comprising reconnaissance araft equipped with laser or radar range-measuring apparatus in conjunction with a plurality of selectively predetermined ground stations. Range and altitude of the aircraft relative to a detected surface target are obtained at two or more points on its flight path. The positions of the aircraft with respect to the ground stations are simultaneously determined by pulse-time-of-arrival technique. Using triangulation techniques the location of the target is determined with respect to a pulse grid coordinate system associated with the ground stations. At any time after the determination of the location of the target, properly timed signals from the ground stations or command signals based upon time-of-arrival data with respect to pulses from the missile are used to provide accurate guidance of the missile to the target.
Inventors
- 👤 James D. McLean
- 👤 Frederick C. Alpers
- 👤 George R. Lanning
- 👤 Fred H. Camphausen
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-11-03 09:56
CPC Classifications
F; F41; F41G; F41G7/00; F41G7/20; F41G7/30; F41G7/34; G; G01; G01S; G01S13/00; G01S13/88; G01S13/91; G01S5/00; G01S5/02; G01S2205/00; G01S2205/01; G01S2205/03
Claims Analysis
Total Claims: 14
Claim 1
Independent Claim
214 words
In a missile guidance system for guiding one of a plurality of missiles to a surface target or targets the combination comprising: (a) an aircraft having target location equipment including a laser range finder, an altimeter, and a microwave pulse transmitter that are operated in synchronism for transmitting data for fixing a target location with respect to an artificial coordinate system; (b) a plurality of ground stations, each of which receives the microwave pulse signals from the aircraft, and supplies output signals from which the target location relative to the ground station positions can be determined based on pulse time of arrival data and the said laser ranging and altimeter data; (c) transmission means associated with at least one of the said ground stations for transmitting guidance information to at least one missile; (d) receiving, sorting, and signal processing means within said missile for receiving and extracting said guidance information from said ground station in order to direct the missile in yaw toward a point approximately above the target and then downward toward the target in pitch; and (e) directional information resolver circuit means for using the differences in times of arrival of pulses in order to establish the instantaneous position of the missile in terms of coordinates that constitute said artificial coordinate system.
Claim 2
Dependent Claim
214 words
In a missile guidance system for guiding one of a plurality of missiles to a surface target or targets the combination comprising: (a) an aircraft having target location equipment including a laser range finder, an altimeter, and a microwave pulse transmitter that are operated in synchronism for transmitting data for fixing a target location with respect to an artificial coordinate system; (b) a plurality of ground stations, each of which receives the microwave pulse signals from the aircraft, and supplies output signals from which the target location relative to the ground station positions can be determined based on pulse time of arrival data and the said laser ranging and altimeter data; (c) transmission means associated with at least one of the said ground stations for transmitting guidance information to at least one missile; (d) receiving, sorting, and signal processing means within said missile for receiving and extracting said guidance information from said ground station in order to direct the missile in yaw toward a point approximately above the target and then downward toward the target in pitch; and (e) directional information resolver circuit means for using the differences in times of arrival of pulses in order to establish the instantaneous position of the missile in terms of coordinates that constitute said artificial coordinate system.
Claim 3
Dependent Claim
19 words
The system of claim 1 wherein said plurality of ground stations comprise three clock-synchronized stations of the transceiver type.
Claim 4
Dependent Claim
20 words
The system of claim 1 wherein said plurality of ground stations comprise three relay type stations and a master station.
Claim 5
Dependent Claim
20 words
The system of claim 2 wherein two of said stations have precision delay circuits to provide the required pulse timing.
Claim 6
Dependent Claim
153 words
The system of claim 1 wherein said directional information resolver circuit is located in the missile and comprises a plurality of information channel circuit means, each of said channel circuit means including: (a) a gated amplifier having an input coupled to the output of said signal sorter and having an output, (b) a time of arrival threshold circuit having an input coupled to the output of said gated amplifier and having an output, (c) a bistable multivibrator having an input coupled directly to the output of said time of arrival threshold circuit, an off input coupled indirectly to the output of said time of arrival threshold circuit and having an output, (d) an integrator circuit having an input coupled to the output of said bistable multivibrator and having an output, (e) a boxcar detector having an input coupled to the output of said integrator and having an output coupled to an output terminal.
Claim 7
Dependent Claim
36 words
The system of claim 5 wherein said directional information resolver includes means for gating off reception of input signals for a predetermined time duration when a set of pulses has been received from said ground stations.
Claim 8
Dependent Claim
89 words
The system of claim 5 wherein said information channel circuit means includes a turn right channel, a turn left channel and a pitch channel, the outputs of the bistable multivibrators of said turn right and turn left channels of said information channels are coupled to the gated amplifier of the pitch channel of said information channels for preventing a pulse signal to enter said pitch channel when the pulse transmitted by said second station arrives at a time between the arrivals of the pulses of the other two stations.
Claim 9
Dependent Claim
35 words
The system of claim 5 wherein said ground station transmit pulses simultaneously to more than one missile, each missile having a time delay circuit adjusted to cause each missile to guide to a different target.
Claim 10
Dependent Claim
45 words
The system of claim 3 wherein said missile includes a pulse transmitter for transmitting pulses to said relay stations where the pulses are re-transmitted, signal processing means located at said master station for receiving said pulses and transmitting guidance command signals back to said missile.
Claim 11
Dependent Claim
16 words
The system of claim 1 wherein said plurality of ground stations comprise only two clock-synchronized stations.
Claim 12
Dependent Claim
33 words
The system of claim 10 where said signal processing means within said missile includes a circuit for generating yaw control signals to direct said missile to the target directly from the launch point.
Claim 13
Dependent Claim
33 words
In the system of claim 10, each of said ground stations being pulsed simultaneously and two precision delay circuits included in said signal processing means within said missile for establishing the target coordinates.
Claim 14
Dependent Claim
54 words
The system of claim 1 wherein said plurality of ground stations comprise a master station including precision delay circuits and said direction information resolver and a command encoder and transmitter for transmitting guidance command signals to the missile, and a slave station for relaying transponder pulses received from said missile to said master station.
References Cited (Backward Citations)
US3073550A
Cited
US3560971A
Cited
USPTO Annuity & Maintenance Windows
| Annuity Stage | Window Opens | Payment Deadline | Surcharge Period Until | Estimated Fee | Status |
|---|---|---|---|---|---|
| 3.5 Years (Year 4) | 1985-02-15 | 1985-08-17 | 1986-02-16 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1989-02-15 | 1989-08-17 | 1990-02-16 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1993-02-15 | 1993-08-17 | 1994-02-16 | $7700.00 | Window Closed / Lapsed |