Combined SAR monopulse and inverse monopulse weapon guidance

• US 5,473,331 A
• Filed: 10/31/1994
• Issued: 12/05/1995
• Est. Priority Date: 10/31/1994
• Status: Expired due to Term

• Current Assignee: Raytheon Company (Rtx Corporation)
• Original Assignee: Hughes Aircraft Company (Rtx Corporation)
• Inventors: Landau, Mark I., Nussbaum, Howard, Kennedy, Thomas A.
• Primary Examiner(s): BENTLEY, STEPHEN
• Application Number:
  US08/332,004
• Time in Patent Office: 400 Days
• Field of Search: 244/3.14, 244/3.19, 342/25, 342/62, 342/149, 342/152
• US Class Current: 342/62
• CPC Class Codes: F41G 7/226 Semi-active homing systems, i.e. comprising a receiver and involving auxiliary illuminating means, e.g. using auxiliary guiding missiles
• CPC Class Codes: F41G 7/2286 using radio waves
• CPC Class Codes: G01S 1/14 using amplitude comparison of signals transmitted simultaneously from antennas or antenna systems having differently oriented overlapping directivity-characteristics
• CPC Class Codes: G01S 13/86 Combinations of radar systems with non-radar systems, e.g. sonar, direction finder
• CPC Class Codes: G01S 13/9092 combined with monopulse techniques

Abstract

A system and method that provides for all-weather precision guidance of conventional air-to-surface weapons. The system and method employs a coherent monopulse radar disposed on a launch platform and a noncoherent passive (receive only) radar disposed on the weapon. The synthetic aperture radar generates a synthetic aperture radar monopulse map of an area around the target. The radar is used designate the location of the target, and transmit a sequence of alternating sum and simultaneous azimuth and elevation difference patterns centered on the target. The weapon includes a guidance system and seeker that is responsive to guidance commands transmitted by the synthetic aperture radar. The guidance system and seeker receives reflections of the alternating sum and combined azimuth and elevation difference pattern from the target, and the sum pulse is used by the weapon to acquire and track the azimuth and elevation difference pattern null on the target to fly an optimum trajectory to the target. One method for guiding a weapon to a target comprises the following steps. A synthetic aperture radar is used to generate a SAR monopulse map of a target area and designate a target therein. The weapon is then launched toward the target. The radar is used to transmit an interleaved sum and simultaneous azimuth and elevation difference pattern guidance pulse train at the target. The reflected interleaved sum and simultaneous azimuth and elevation difference pattern is received from the target at a seeker and guidance system on the weapon. The sum pattern is used by the weapon to lock onto the converging null, and is used by the launch platform to provide closed loop tracking of the target during guidance illumination. After weapon null lock-on, steering commands are generated to cause the weapon to fly an optimum trajectory to the target.

Claims

1. A SAR monopulse and inverse monopulse weapon guidance system for guiding a weapon to a target, said system comprising:

a launch platform;

a synthetic aperture radar disposed on a launch platform for generating a synthetic aperture radar monopulse map of an area surrounding the target, for designating the location of the target, and for transmitting an inverse monopulse illumination that is comprised of a sequence of alternating sum and simultaneous azimuth and elevation difference patterns centered on the target;

a weapon comprising a weapon guidance system and noncoherent radar seeker that is responsive to guidance commands transmitted by the launch platform, for receiving reflections of the alternating sum and combined azimuth and elevation difference pattern from the target, and for using these reflections to acquire and track the azimuth and elevation difference pattern null on the target so as to fly an optimum trajectory to the target.

2. The system of claim 1 wherein the guidance system comprises a passive noncoherent radar seeker.

3. The system of claim 1 wherein the radar generates the simultaneous azimuth and elevation difference patterns by dividing the radar antenna aperture into four quadrants and placing 90°

phase shifts between each adjacent quadrant during transmission.

4. The system of claim 3 wherein the 90°

relative phase between adjacent quadrants produces the three dimensional null pattern.

5. A method for guiding a weapon to a target, said method comprising the steps of:

using a synthetic aperture radar to generate a SAR monopulse map of a target area and designating a target therein;

launching the weapon toward the target;

using the synthetic aperture radar to transmit an interleaved sum and simultaneous azimuth and elevation difference pattern guidance pulse train at the target;

receiving a reflected interleaved sum and simultaneous azimuth and elevation difference pattern from the target at a seeker and guidance system on the weapon;

locking onto a converging null using the sum pattern; and

after null lock-on, generating steering commands to cause the weapon to fly an optimum trajectory to the target.

6. The method of claim 5 further comprising the step of:

continuously tracking the target by way of SAR monopulse maps generated by the synthetic aperture radar using the sum pattern returns.

7. The method of claim 5 further comprising the step of:

making additional maps to track the target and remove targeting errors due to navigation errors.

8. The method of claim 5 wherein four simultaneous beams, one from each quadrant, are transmitted to form the interleaved sum and simultaneous azimuth/elevation difference pattern.

9. The method of claim 5 wherein the sum pattern is used to ensure that the seeker acquires the three-dimensional null.

10. The method of claim 9 wherein the simultaneous azimuth and elevation difference patterns are transmitted with a null of each difference pattern placed on the target to provide the three dimensional null pattern.

11. The method of claim 10 wherein adjacent quadrants have a relative phase shift of 90°

to provide adjacent quadrant decoupling.