Target locating and missile guidance system

• US 4,315,609 A
• Filed: 06/16/1971
• Issued: 02/16/1982
• Est. Priority Date: 06/16/1971
• Status: Expired due to Term

• Current Assignee: the united states of america as represented by the secretary of the navy
• Original Assignee: the united states of america as represented by the secretary of the navy
• Inventors: Alpers, Frederick C., McLean, James D., Lanning, George R., Camphausen, Fred H.
• Primary Examiner(s): Jordan, Charles T.
• Application Number:
  US05/154,235
• Time in Patent Office: 3,898 Days
• Field of Search: 343/7 ED, 244/3.16, 244/3.14
• US Class Current: 244/3.14
• CPC Class Codes: F41G 7/30 Command link guidance systems homing F41G7/2206
• CPC Class Codes: F41G 7/34 based on predetermined target position data
• CPC Class Codes: G01S 13/91 for traffic control G01S13/93 takes precedence
• CPC Class Codes: G01S 2205/03 Airborne
• CPC Class Codes: G01S 5/02 using radio waves using satellite radio beacon systems for determining position G01S19/00

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.

Claims

1. 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.

2. The system of claim 1 wherein said plurality of ground stations comprise three clock-synchronized stations of the transceiver type.

3. The system of claim 1 wherein said plurality of ground stations comprise three relay type stations and a master station.

4. The system of claim 2 wherein two of said stations have precision delay circuits to provide the required pulse timing.

5. 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.

6. 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.

7. 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.

8. 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.

9. 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.

10. The system of claim 1 wherein said plurality of ground stations comprise only two clock-synchronized stations.

11. 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.

12. 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.

13. 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.