Methods and apparatuses for engagement management of aerial threats

Patent metadata

Field	Value
Publication number	US-10948909-B2
Application number	US-201916296742-A
Country	US
Kind code	B2
Filing date	Mar 8, 2019
Priority date	Mar 2, 2012
Publication date	Mar 16, 2021
Grant date	Mar 16, 2021

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 active protection system comprising:
an intercept vehicle carried by an aircraft; and
an engagement management system comprising a guidance processor configured to:
generate launch commands for causing the intercept vehicle to be launched from the aircraft;
generate timing and firing requirements for alignment thrusters of the intercept vehicle to perform a pitch maneuver to at least substantially align a longitudinal axis of the intercept vehicle with a intercept vector prior to initiating a rocket motor of the intercept vehicle; and
transmit the timing and firing requirements for the alignment thrusters to the intercept vehicle.

2. The active protection system of claim 1 , wherein the engagement management system further comprises a sensor configured to identify an aerial threat within a sensor range.

3. The active protection system of claim 2 , wherein the sensor comprises at least one of a radar unit or an active laser.

4. The active protection system of claim 2 , wherein the sensor is further configured to operate in a track mode during which the engagement management system tracks the identified aerial threat.

5. The active protection system of claim 2 , wherein the sensor is further configured to be operable in a search mode during which the engagement management system searches for an aerial threat.

6. The active protection system of claim 2 , wherein the sensor is further configured to be operable in a mixed track and search mode.

7. The active protection system of claim 1 , wherein the aircraft comprises an unmanned airborne vehicle, a light aircraft, a low speed aircraft, a remotely piloted vehicle, a helicopter, or a hovering platform.

8. The active protection system of claim 1 , further comprising a carrier disposed on the aircraft, the carrier carrying the intercept vehicle.

9. The active protection system of claim 1 , wherein the engagement management system further comprises a communication unit configured to communicate with the intercept vehicle during the intercept vehicle's flight after launch from the aircraft.

10. The active protection system of claim 9 , wherein the intercept vehicle further comprises divert thrusters configured to divert the intercept vehicle in a direction transverse to a flight path of the intercept vehicle.

11. The active protection system of claim 10 , wherein the guidance processor is further configured to:
generate guidance commands for the divert thrusters of the intercept vehicle to divert the intercept vehicle in a direction transverse to the flight path of the intercept vehicle after execution of the pitch maneuver; and
transmit the guidance commands via the communication unit.

12. The active protection system of claim 9 , wherein the communication unit comprises:
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.

13. The active protection system of claim 9 , wherein the communication unit further comprises a command link radio.

14. The active protection system of claim 9 , wherein the guidance processor is further configured to transmit a detonation command to the intercept vehicle via the communication unit for controlling detonation of a payload carried by the intercept vehicle.

15. The active protection system of claim 1 , wherein the engagement management system further comprises an inertial navigation unit configured to determine an initial attitude of the intercept vehicle prior to launch of the intercept vehicle from the aircraft.

16. The active protection system of claim 1 , wherein the guidance processor is further configured to transmit the timing and firing requirements for the alignment thrusters of the intercept vehicle to the intercept vehicle after launch of the intercept vehicle.

17. The active protection system of claim 9 , wherein the aircraft comprises an unmanned airborne vehicle, a light aircraft, a low speed aircraft, a remotely piloted vehicle, a helicopter, or a hovering platform.

18. An active targeting system, comprising:
an intercept vehicle configured to be released from a platform, the intercept vehicle comprising:
alignment thrusters configured to rotate the intercept vehicle about an axis orthogonal to a longitudinal axis of the intercept vehicle to at least substantially align the longitudinal axis of the intercept vehicle with an intercept vector via a pitch maneuver; and
divert thrusters configured to divert the intercept vehicle in a direction transverse to a flight path of the intercept vehicle

an engagement management system disposed on the platform, the engagement management system comprising a guidance processor configured to generate guidance commands including divert thrust vectors for determining when to fire the divert thrusters of the intercept vehicle to divert the intercept vehicle in a direction transverse to the flight path of the intercept vehicle after the intercept vehicle is released from the platform.

19. The active targeting system of claim 18 , wherein the intercept vehicle further comprises:
a rocket motor configured to accelerate the intercept vehicle along the intercept vector after the intercept vehicle performs the pitch maneuver; and
a heat generating payload.

20. The active targeting system of claim 18 , wherein the guidance processor of the engagement management system is furthermore configured to transmit the guidance commands to the intercept vehicle.

21. The active targeting system of claim 18 , wherein the engagement management system further comprises:
a sensor configured to detect and aerial threat within a sensor range of the sensor; and
a communication unit configured to communicate with the intercept vehicle during flight of the intercept vehicle after being released from the platform.

22. The active targeting system of claim 18 , wherein the platform is a mobile platform.

23. The active targeting system of claim 22 , wherein the mobile platform is selected from the group consisting of an aerial vehicle, a helicopter, an unmanned airborne vehicle (UAV), a remotely piloted vehicle (RPV), an aircraft, a light aircraft, a low speed aircraft, a hovering platform, a ground-based vehicle, a tank, an armored personnel carrier, and a personnel carrier.

24. The active targeting system of claim 18 , wherein the platform is a stationary platform.

25. The active targeting system of claim 18 , wherein the guidance processor is further configured to transmit the divert thrust vectors as inertial coordinates for conversion into body coordinates by the intercept vehicle.

26. A method of intercepting an aerial threat, comprising:
releasing an intercept vehicle from a platform during a first action of a launch sequence;
causing the intercept vehicle to perform a second different action of the launch sequence after releasing the intercept vehicle from the platform, the second different action comprising performing a pitch maneuver with a plurality of pitch thrusters of the intercept vehicle to align the intercept vehicle along an intercept vector pointed substantially toward a projected intercept point with an identified aerial threat; and
performing a divert maneuver with one or more divert thrusters of the i

Assignees

• Northrop Grumman Innovation Systems Inc

Inventors

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

Classifications

• F41G7/306 Primary

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

• F41G7/308

  for guiding a plurality of missiles · CPC title

• G01S13/883

  for missile homing, autodirectors (missile guidance systems F41G7/22) · 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

• 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