ADAPTIVE ELECTRONICALLY STEERABLE ARRAY (AESA) SYSTEM FOR INTERCEPTOR RF TARGET ENGAGEMENT AND COMMUNICATIONS

• US 20160084623A1
• Filed: 09/23/2014
• Published: 03/24/2016
• Est. Priority Date: 09/23/2014
• Status: Active Grant

• Current Assignee: Raytheon Company (Rtx Corporation)
• Original Assignee: Raytheon Company (Rtx Corporation)
• Inventors: Facciano, Andrew B., Krebs, Rodney H., Bielas, Michael S., Tretschok, Cody D., Spangler, Michael S., Mitchell, Benjamin
• Granted Patent: US 9,541,364 B2
• Time in Patent Office: Days
• US Class Current: 1/1
• CPC Class Codes: F41G 7/008 Combinations of different guidance systems
• CPC Class Codes: F41G 7/2246 Active homing systems, i.e. comprising both a transmitter and a receiver
• CPC Class Codes: F41G 7/2253 Passive homing systems, i.e. comprising a receiver and do not requiring an active illumination of the target
• CPC Class Codes: F41G 7/2286 using radio waves
• CPC Class Codes: F41G 7/2293 using electromagnetic waves other than radio waves
• CPC Class Codes: F42B 15/01 Arrangements thereon for guidance or control steering arrangements F42B10/60; aircraft flight control B64C; guidance systems other than those installed aboard F41G7/00, F41G9/00; locating by use of radio or other waves G01S; flight control in general G05D1/00; computer aspects G06]
• CPC Class Codes: F42B 30/006 Mounting of sensors, antennas or target trackers on projectiles
• CPC Class Codes: H01Q 1/28 Adaptation for use in or on aircraft, missiles, satellites, or balloons
• CPC Class Codes: H01Q 1/287 integrated in a wing or a stabiliser
• CPC Class Codes: H01Q 1/42 Housings not intimately mechanically associated with radiating elements, e.g. radome
• CPC Class Codes: H01Q 21/061 Two dimensional planar arrays
• CPC Class Codes: H01Q 3/24 varying the orientation by switching energy from one active radiating element to another, e.g. for beam switching

Abstract

An AESA system comprises a plurality of arrays, each comprising a plurality of radiating elements, each array configured for placement on a forward-facing surface of a different one of a plurality of aerodynamic control surfaces on an interceptor. A plurality of RF transmissive radome elements, each having an aerodynamic shape complementary to the aerodynamic control surface, are placed over one of the arrays. Control circuitry configures the arrays, independently or in concert, for RF target engagement and communication. Additional arrays may be positioned on side or aft-facing surfaces of the aerodynamic control surfaces for RF communication. The AESA system may be paired with an ER system for dual-mode operation.

Claims

1. An adaptive electronically steerable array (AESA) system suitable for use on an interceptor, said interceptor comprising a plurality of aerodynamic control surfaces position about an airframe, each control surface having a forward-facing surface, said AESA system comprising:

a plurality of arrays, each comprising a plurality of radiating elements, each said array configured for placement on the forward-facing surface of a different one of said plurality of aerodynamic control surfaces;

a plurality of RF transmissive radome elements, each radome element configured for placement over one of said arrays, each said radome element having an aerodynamic shape complementary to said aerodynamic control surface; and

control circuitry to configure the arrays for RF target engagement.

2. The AESA system of claim 1, wherein said aerodynamic control surfaces have side-facing surfaces, further comprising:

an additional plurality of arrays, each comprising a plurality of radiating elements, each said array configured for placement on the side-facing surface of a different one of said plurality of aerodynamic control surfaces,

wherein said control circuitry configures the additional plurality of arrays for RF communication.

3. The AESA system of claim 1, wherein said aerodynamic control surfaces have aft-facing surfaces, further comprising:

an additional plurality of arrays, each comprising a plurality of radiating elements, each said array configured for placement on the aft-facing surface of a different one of said plurality of aerodynamic control surfaces,

wherein said control circuitry configures the additional plurality of arrays for RF communication.

4. The AESA system of claim 1, wherein the control circuitry configures the arrays with independent beam patterns.

5. The AESA system of claim 4, wherein the control circuitry configures the arrays to scan the independent beam patterns over different regions of a field-of-regard (FOR) to search for and acquire a target.

6. The AESA system of claim 5, wherein once acquired, the control circuitry configures the arrays to produced a combined beam pattern to track the target, said combined beam pattern having a greater sensitivity than said individual beam patterns.

7. The AESA system of claim 6, wherein the interceptor comprises a boresight strap down IR seeker having a FOR less than the AESA system FOR, wherein at terminal, said control circuitry activates the IR seeker to engage the target.

8. The AESA system of claim 1, wherein the control circuitry configures the arrays to produce a combined beam pattern.

9. The AESA system of claim 1, wherein the control circuitry configures the arrays for RF target engagement and RF communications with a communication station.

10. The AESA system of claim 9, wherein the control circuitry configures at least one said array for RF target engagement and at least one said array for RF communications with the communication station for simultaneous RF target engagement and RF communications.

11. The AESA system of claim 10, wherein the control circuitry configures the arrays for serial RF target engagement and RF communications.

12. The AESA system of claim 10, wherein the control circuitry configures the arrays for multi-band operations.

13. The AESA system of claim 1, wherein the interceptor comprises a forward looking non-gimbaled IR seeker mounted on the front of the airframe and an axis-symmetric IR transmissive dome mounted over the IR seeker.

14. An interceptor comprising:

an airframe;

a plurality of aerodynamic control surfaces position about the airframe, each control surface having a forward-facing surface,

an adaptive electronically steerable array (AESA) system comprising a plurality of arrays, each comprising a plurality of radiating elements, each said array positioned on the forward-facing surface of a different one of said plurality of aerodynamic control surfaces;

a plurality of RF transmissive radome elements placed over different ones of said arrays, each said radome element having an aerodynamic shape complementary to said aerodynamic control surface; and

control circuitry to configure the arrays for RF target engagement.

15. The interceptor of claim 14, wherein the control circuitry configures the arrays both independently and in concert for RF target engagement and configures the arrays for both RF target engagement and RF communications.

16. The interceptor of claim 14, wherein the interceptor comprises a forward looking non-gimbaled IR seeker mounted on the front of the interceptor and an axis-symmetric IR transmissive dome mounted over the IR seeker.

17. A method of RF target engagement comprising:

positioning arrays on the forward-facing surfaces of a plurality of aerodynamic control surfaces positioned about an interceptor, each array comprising a plurality of radiating elements that together define an adaptive electronically steerable array (AESA) system;

placing a plurality of RF transmissive radome elements over different ones of said arrays, each said radome element having an aerodynamic shape complementary to said aerodynamic control surface; and

configuring the arrays for RF target engagement.

18. The method of claim 17, wherein the arrays are configured both independently and in concert for RF target engagement.

19. The method of claim 17, wherein the arrays are configured for both RF target engagement and RF communications.

20. The method of claim 17, further comprising mounting a forward looking non-gimbaled IR seeker on the front of the airframe and mounting an axis-symmetric IR transmissive dome over the IR seeker.