Missile guidance system

• US 5,917,442 A
• Filed: 01/22/1998
• Issued: 06/29/1999
• Est. Priority Date: 01/22/1998
• Status: Expired due to Term

• Current Assignee: Raytheon Company (Rtx Corporation)
• Original Assignee: Raytheon Company (Rtx Corporation)
• Inventors: Manoogian, David V.
• Primary Examiner(s): Sotomayor, John B.
• Application Number:
  US09/010,695
• Time in Patent Office: 523 Days
• Field of Search: 342/62, 342/75, 342/76, 342/78, 342/81, 342/96, 342/97, 244/3.13, 244/3.14, 244/3.15, 244/3.16, 244/3.19
• US Class Current: 342/62
• CPC Class Codes: F41G 7/008 Combinations of different guidance systems
• CPC Class Codes: F41G 7/2213 maintaining the axis of an orientable seeking head pointed at the target, e.g. target seeking gyro
• CPC Class Codes: F41G 7/2246 Active homing systems, i.e. comprising both a transmitter and a receiver
• CPC Class Codes: F41G 7/2266 Systems comparing signals received from a base station and reflected from the target
• CPC Class Codes: F41G 7/2286 using radio waves
• CPC Class Codes: G01S 13/426 Scanning radar, e.g. 3D radar G01S13/66 takes precedence
• CPC Class Codes: G01S 13/58 Velocity or trajectory determination systems; Sense-of-movement determination systems
• CPC Class Codes: G01S 13/72 for two-dimensional tracking, e.g. combination of angle and range tracking, track-while-scan radar
• CPC Class Codes: G01S 13/86 Combinations of radar systems with non-radar systems, e.g. sonar, direction finder
• CPC Class Codes: G01S 13/87 Combinations of radar systems, e.g. primary radar and secondary radar

Abstract

A method for guiding a missile to a target. The method includes the step of providing a surface-based radar system having an electronically beam steerable antenna system adapted for continuous mechanical rotation about an axis. During a pre-terminal, semi-active missile homing guidance phase, the beam produced by the antenna system is electronically rotated by the antenna system in a direction counter to the direction of the mechanical rotation of the antenna system to thereby increase radar system illumination time on the target. Further, during the increased illumination time, the beamwidth of the surface-based radar system beam is increased. During, a subsequent terminal, active homing missile guidance phase, guiding the missile to the target with the pre-terminal, semi-active missile homing guidance phase using the surface-based radar system and establishing an angular orientation for a missile-borne antenna system at the commencement of the terminal, active missile homing guidance system phase.

Claims

1. A method of operating a radar system, comprising the steps of:

providing a surface-based radar system having an electronically beam steerable antenna system adapted for continuous mechanical rotation about an axis; and

electronically rotating a beam produced by the antenna system in a direction counter to the direction of the mechanical rotation of the antenna system; and

increasing the beamwidth of the beam produced by the radar system when such beam is electronically rotated in the direction counter to the direction of the mechanical rotation of the antenna system.

2. The method recited in claim 1 wherein the beam is electronically rotated in the direction counter to the direction of the mechanical rotation of the antenna system a plurality of times during each mechanical rotation of the antenna system.

3. A method of operating a radar system, comprising the steps of:

providing a surface-based radar system having an electronically beam steerable antenna system adapted to continuously scan a horizon rotationally in azimuth by mechanically rotating the antenna system about an azimuthal axis, such antenna system electronically producing a beam having a nominal, predetermined angular orientation with respect to the mechanically rotating antenna system; and

electronically deviating the beam from the nominal angular orientation by rotating the beam with respect to the antenna system in a direction counter to the direction of the mechanical rotation of the antenna system to thereby direct the beam towards a target for illumination by the radar system during a sector of each rotating scan by the antenna system and then returning the beam to the nominal, predetermined angular orientation after the antenna system has rotated through such sector; and

increasing the beamwidth of the beam produced by the radar system when such beam is electronically rotated in the direction counter to the direction of the mechanical rotation of the antenna system.

4. The method recited in claim 3, wherein the beam is electronically rotated in the direction counter to the direction of the mechanical rotation of the antenna system a plurality of times during each mechanical rotation of the antenna system.

5. A method of guiding a missile to a target, comprising the steps of:

providing a surface-based radar system having an electronically beam steerable antenna system adapted for continuous mechanical rotation about an axis;

during a pre-terminal, semi-active missile homing guidance phase, electronically rotating a beam produced by the antenna system in a direction counter to the direction of the mechanical rotation of the antenna system;

during a subsequent terminal, active homing missile guidance phase, guiding the missile to the target; and

wherein the pre-terminal, semi-active missile homing guidance phase establishes an angular orientation for a missile-borne antenna system at the commencement of the terminal, active missile homing guidance system phase.

6. The method recited in claim 5 including the step of increasing the beamwidth of the beam produced by the radar system when such beam is electronically rotated in the direction counter to the direction of the mechanical rotation of the antenna system.

7. The method recited in claim 6 wherein the beam is electronically rotated in the direction counter to the direction of the mechanical rotation of the antenna system a plurality of times during one mechanical rotation of the antenna system.

8. The method recited in claim 7 including the step of increasing the beamwidth of the beam produced by the radar system when such beam is electronically rotated in the direction counter to the direction of the mechanical rotation of the antenna system.

9. A method of guiding a missile to a target, comprising the steps of:

providing a surface-based radar system having an electronically beam steerable antenna system adapted to continuously scan a horizon rotationally in azimuth by mechanically rotating the antenna system about an azimuthal axis, such antenna system electronically producing a beam having a nominal, predetermined angular orientation with respect to the mechanically rotating antenna system;

during a pre-terminal, semi-active missile homing guidance phase, tracking a target with a missile-borne antenna system using target return signals received by the missile-borne antenna in response to such target being illuminated with radar energy transmitted by the surface-based radar system, such electronically beam steerable antenna system electronically deviating the beam from the nominal angular orientation by rotating the beam with respect to the antenna system in a direction counter to the direction of the mechanical rotation of the antenna system to thereby direct the beam towards the target for illumination by the radar system during a sector of each rotating scan by the antenna system and then returning the beam to the nominal, predetermined angular orientation after the antenna system has rotated through such sector;

during a subsequent terminal, active missile homing guidance phase, guiding the missile to the target using target return signals received by the missile-borne antenna in response to such target being illuminated with radar energy transmitted by a missile-borne transmitter; and

wherein the pre-terminal, semi-active missile homing guidance phase establishes an angular orientation for the missile-borne antenna system at the commencement of the terminal, active missile homing guidance system phase.

10. A missile guidance system, comprising:

a radar antenna system, gimballed within the missile and adapted to receive radar signals in a first frequency band and in a second, different frequency band;

an missile-borne active radar system comprising;

a radar transmitter and receiver coupled to the antenna system and adapted for operation at the first frequency band;

a missile-borne semi-active radar system receiver coupled to the antenna system and adapted for operation at the second frequency band;

a missile-borne signal processor adapted to produce target tracking signals from radar signals fed thereto through the antenna system from either the active radar system receiver or the semi-active radar system receiver, such target tracking signals being fed to the antenna system to gimbal the antenna system and thereby direct the antenna system towards the target;

a switch fed by radar signals produced by the active radar system receiver and radar signals produced the semi-active radar system receiver, such switch feeding one of such radar signals to the signal processor selectively in a control signal; and

wherein the control signal operates the switch to feed the semi-active radar system receiver to the signal processor during a pre-terminal, semi-active guidance phase to thereby direct the missile-borne antenna system towards the target during such pre-terminal phase and to subsequently feed the active radar system receiver to the signal processor at commencement of a terminal, active guidance system phase.

11. A missile guidance system, comprising:

(a) a radar transmitter disposed at a surface-based and adapted to transmit radar signals in a first frequency band, such radar transmitter having a search antenna adapted for mechanical rotation about an axis at a predetermined rotational rate to search for a target;

(b) a missile having disposed therein;

(i) an active radar system comprising;

a radar transmitter and receiver adapted for operation at a second, different frequency band;

(ii) a semi-active radar system receiver adapted for operation at the first frequency band;

(iii) a missile radar antenna system, gimballed within the missile and adapted to receive radar signals transmitted by the surface-based antenna, after reflection by the target, in the first frequency band during a pre-terminal, semi-active guidance phase and to receive radar signals transmitted by the active radar transmitter, after reflection by the target, in the second frequency band during a subsequent terminal, active guidance phase;

(iv) a signal processor adapted to produce target tracking signals from radar signals fed thereto from either the active radar system receiver during the terminal, active guidance phase or from the semi-active radar system receiver during the pre-terminal, semi-active guidance phase, such target tracking signals being fed to the missile radar antenna system to gimbal the antenna system and direct the missile radar antenna system towards the target; and

(iv) a switch fed by radar signals produced by the active radar system receiver and radar signals produced the semi-active radar system receiver, such switch feeding one of such radar signals to the signal processor selectively in a control signal; and

(c) wherein the control signal operates the switch to feed the semi-active radar system to the signal processor during the semi-active guidance phase prior to feeding the active radar system receiver to the signal processor during the active guidance phase, such signal processor producing the target tracking signals for the missile radar antenna system to direct the antenna system towards the target from the semi-active radar signals during the semi-active phase and thereby establish an initial radar missile antenna system orientation at commencement of the subsequent terminal, active guidance phase.

12. The missile guidance system recited in claim 11 wherein the surface-based radar system includes a controller for controlling a beamwidth of the search antenna system, such beamwidth being relatively narrow during an initial target search mode and being relatively wide during a subsequent target tracking mode.

13. The missile guidance system recited in claim 12 wherein the pre-terminal, semi-active guidance phase occurs during the surface-based radar system target tracking mode.

14. The missile guidance system recited in claim 13 wherein the surface-based radar system operates in a substantially continuous-wave mode during the semi-active guidance phase and wherein the missile has disposed therein a notch filter disposed between the missile radar antenna system and the switch, such notch filter being tuned to clutter radar return signals during the pre-terminal, semi-active guidance phase.

15. The missile system recited in claim 14 wherein the missile has disposed therein an up-link receiver adapted for communication with the surface-based radar system and wherein the surface-based radar system transmits an active phase initiation signal to the up-link receiver and wherein the control signal for the switch is produced in response to the active phase initiation signal.

16. The missile system recited in claim 15 wherein the surface-based radar system produces the terminal phase initiation signal in accordance with a calculation of target cross-section.

17. The missile system recited in claim 16 wherein the surface-based radar system produces the terminal phase initiation signal in accordance with a calculation of a predetermined probability of the active radar system locking onto the target.