Methods and apparatuses for engagement management of aerial threats

Patent metadata

Field	Value
Publication number	US-10228689-B2
Application number	US-201615355839-A
Country	US
Kind code	B2
Filing date	Nov 18, 2016
Priority date	Mar 2, 2012
Publication date	Mar 12, 2019
Grant date	Mar 12, 2019

Abstract

Embodiments include engagement management systems and methods for managing engagement with aerial threats. Such systems include radar modules and detect aerial threats within a threat range of a base location. The systems also track intercept vehicles and control flight paths and detonation capabilities of the intercept vehicles. The systems are capable of communication between multiple engagement management systems and coordinated control of multiple intercept vehicles.

First claim

What is claimed is:

1. An engagement management module for an eject vehicle, the engagement management module comprising:
a sensor unit configured to identify a targeted object within a sensor range; and
a guidance processor configured to:
generate launch commands for causing the eject vehicle to be launched from a dispenser;
generate timing and firing requirements for pitch thrusters mounted on the eject vehicle to perform a pitch maneuver to modify orientation of the eject vehicle to substantially align a longitudinal axis of the eject vehicle to point toward the targeted object prior to initiating a rocket motor of the eject vehicle; and
transmit the timing and firing requirements for the pitch thrusters to the eject vehicle.

2. The engagement management module of claim 1 , further comprising a communication unit configured to communicate with the eject vehicle during its flight after launch from a dispenser, wherein the guidance processor is further configured to:
generate guidance commands for divert thrusters mounted on the eject vehicle to perform a divert maneuver to modify a flight path of the eject vehicle toward a target point after execution of the pitch maneuver; and
transmit the guidance commands via the communication unit.

3. The engagement management module of claim 2 , wherein the communication unit includes:
a transmit processing chain including a digital-to-analog converter and an up converter;
a receive processing chain including a down converter and an analog-to-digital converter; and
a duplexing device operably coupled between the transmit processing chain and the receive processing chain.

4. The engagement management module of claim 2 , wherein the guidance processor is further configured to transmit a detonation command to the eject vehicle via the communication unit for controlling detonation of a warhead carried by the eject vehicle.

5. The engagement management module of claim 2 , wherein the communication unit includes a command link radio.

6. The engagement management module of claim 1 , further comprising an inertial navigation unit configured to determine an initial attitude of the eject vehicle prior to launch of the eject vehicle from the dispenser.

7. The engagement management module of claim 1 , wherein the guidance processor is configured to transmit the timing and firing requirements for the pitch thrusters to the eject vehicle after launch of the eject vehicle.

8. The engagement management module of claim 1 , wherein the sensor unit includes at least one of a radar unit or an active laser.

9. The engagement management module of claim 1 , wherein the sensor unit is configured to operate in a track mode during which the engagement management module tracks the identified targeted object.

10. The engagement management module of claim 1 , wherein the sensor unit is configured to be operable in a search mode during which the engagement management module searches for an object to target.

11. The engagement management module of claim 1 , wherein the sensor unit is configured to be operable in a mixed track and search mode.

12. The engagement management module of claim 1 , wherein the sensor unit is configured to determine if the targeted object is an aerial threat and to launch the eject vehicle in response to such a determination.

13. An engagement management module for an eject vehicle, the engagement management module comprising:
a sensor unit configured to identify a targeted object within a sensor range;
a communication unit configured to communicate with the eject vehicle during flight thereof after launch from a dispenser; and
a guidance processor configured to:
generate guidance commands including divert thrust vectors for determining when to fire divert thrusters mounted on the eject vehicle to perform a divert maneuver after launch of the eject vehicle; and
transmit the guidance commands to the eject vehicle via the communication unit.

14. The engagement management module of claim 13 , wherein the guidance processor is configured to transmit the divert thrust vectors as inertial coordinates for conversion into body coordinates by the eject vehicle.

15. An eject vehicle, comprising:
a rocket motor configured to accelerate the eject vehicle along a longitudinal axis of the eject vehicle, and to impose a spin on the eject vehicle;
divert thrusters, each divert thruster configured to, upon activation, laterally divert the eject vehicle from a current flight path in a direction transverse to the longitudinal axis; and
a controller configured to receive guidance commands from a remote engagement management module and activate one or more of the plurality of divert thrusters at different times and at specific spin positions during the current flight path toward an intercept point.

16. The eject vehicle of claim 15 , further comprising a telemetry unit configured to determine operation parameters of the eject vehicle and transmit via the controller to the remote engagement management module for updating the guidance commands.

17. The eject vehicle of claim 15 , wherein the controller is configured to activate the one or more of the plurality of divert thrusters by:
selecting a next available divert thruster based, at least in part, on attitude information about the eject vehicle and a thrust vector command; and
activating the next available divert thruster responsive to being aligned in a determined direction for achieving a desired divert angle.

18. The eject vehicle of claim 15 , wherein the controller is configured to activate one or more of the plurality of divert thrusters at different times and at specific spin positions by:
waiting until a magnitude of a divert velocity increment in an y-z plane exceeds a predetermined factor of a guidance velocity vector in the y-z plane;
identifying a divert thruster that has not been fired that meets an offset requirement for a desired divert angle;
activating the identified divert thruster responsive to its orientation vector reaching the desired divert angle.

19. The eject vehicle of claim 18 , wherein the desired divert angle accounts for a smear angle due to body rotation of the eject vehicle.

20. The eject vehicle of claim 15 , wherein the controller is configured to:
receive guidance commands from a remote engagement management module as inertial coordinates; and
project the inertial coordinates onto a body coordinate system for the eject vehicle.

21. An eject vehicle, comprising:
pitch thrusters mounted in a nose region of the eject vehicle, the pitch thrusters configured and oriented to cause both a lateral and a rotational acceleration about a center of gravity of the eject vehicle;
a boost motor configured to accelerate the eject vehicle along a longitudinal axis of the eject vehicle and to impose a spin; and
a controller configured to activate one or more of the pitch thrusters responsive to receiving pitch commands from a remote engagement management module, and to orient a longitudinal axis of the eject vehicle to point toward a targeted object after ejection of the eject vehicle and prior to activation of the boost motor.

22. The eject vehicle of claim 21 , wherein the pitch commands include a timing sequence for determining, when to fire, and an order to fire, each of the pitch thrusters.

23. The eject vehicle of claim 21 , wherein the controller is configured to activate the pitch thrusters to orient a longitudinal axis of the e

Assignees

• Northrop Grumman Innovation Systems Inc

Inventors

• Kolanek James
• Baseghi Behshad
• Sharpin David
• Visco Anthony
• Shieh Falin

Classifications

• F41G7/308

  for guiding a plurality of missiles · CPC title

• F41H11/02

  Anti-aircraft or anti-guided missile {or anti-torpedo} defence installations or systems (cartridges or missiles for producing smoke or for dispensing radar chaff or infrared material F42B5/15, F42B12/48, F42B12/70; {informative reference: details of radar or sonar systems G01S7/00; jamming or electronic countermeasures G01S7/38, G01S7/495, H04K3/00}) · CPC title

• G05D1/0022 Primary

  characterised by the communication link (data switching networks in general H04L12/00) · CPC title

• F42B15/01

  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 title

• F41G7/306 Primary

  for transmitting guidance signals; (F41G7/308 takes precedence) · CPC title