Methods and apparatuses for aerial interception of aerial threats

Patent metadata

Field	Value
Publication number	US-11313650-B2
Application number	US-201916584378-A
Country	US
Kind code	B2
Filing date	Sep 26, 2019
Priority date	Mar 2, 2012
Publication date	Apr 26, 2022
Grant date	Apr 26, 2022

Abstract

Embodiments include active protection systems and methods for an aerial platform. An onboard system includes radar modules, detects aerial vehicles within a threat range of the aerial platform, and determines if any of the aerial vehicles are an aerial threat. The onboard system also determines an intercept vector to the aerial threat, communicates the intercept vector to an eject vehicle, and causes the eject vehicle to be ejected from the aerial platform to intercept the aerial threat. The eject vehicle includes alignment thrusters to rotate a longitudinal axis of the eject vehicle to substantially align with the intercept vector, a rocket motor to accelerate the eject vehicle along an intercept vector, divert thrusters to divert the eject vehicle in a direction substantially perpendicular to the intercept vector, and attitude control thrusters to make adjustments to the attitude of the eject vehicle.

First claim

What is claimed is:

1. An active protection system, comprising:
an aircraft;
an intercept vehicle carried by the aircraft, the intercept vehicle comprising:
a rocket motor for accelerating the intercept vehicle along a flight path of the intercept vehicle;
alignment thrusters configured to perform a pitch maneuver by rotating the intercept vehicle about an axis orthogonal to the longitudinal axis of the intercept vehicle to at least substantially align the longitudinal axis of the intercept vehicle with an intercept vector prior to the rocket motor being fired to accelerate the intercept vehicle along the flight path of the intercept vehicle; and
divert thrusters configured to divert the intercept vehicle in a direction transverse to the flight path of the intercept vehicle.

2. The active protection system of claim 1 , wherein the intercept vehicle further comprises a nose thruster module proximate a front end of the intercept vehicle.

3. The active protection system of claim 2 , wherein the nose thruster module of the intercept vehicle comprises the alignment thrusters.

4. The active protection system of claim 1 , wherein the intercept vehicle further comprises:
a controller; and
one or more sensors operably coupled to the controller, wherein the controller is configured to initiate flight corrections to the intercept vehicle during flight based on feedback from the one or more sensors.

5. The active protection system of claim 4 , further comprising a guidance system disposed on the aircraft configured to transmit guidance signals to the intercept vehicle to direct the intercept vehicle on the flight path of the intercept vehicle.

6. The active protection system of claim 5 , further comprising a detection system disposed on the aircraft and comprising at least one sensor configured to detect aerial threats with threat range of the aircraft.

7. The active protection system of claim 6 , wherein the detection system is further configured to track aerial threats detected by the at least one sensor.

8. The active protection system of claim 6 , further comprising an intercept vehicle carrier for carrying the intercept vehicle.

9. A method of intercepting an aerial threat, comprising:
causing an intercept vehicle to perform a first action of a launch sequence to leave a platform;
causing the intercept vehicle to perform a second action of the launch sequence after the first launch sequence, the second 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
subsequent to the second action of the launch sequence, firing a rocket motor of the intercept vehicle to cause the intercept vehicle to accelerate along a flight path of the intercept vehicle.

10. The method of claim 9 , wherein the first action of a launch sequence comprises releasing the intercept vehicle from the platform.

11. The method of claim 9 , wherein the first action of a launch sequence comprises launching the intercept vehicle from the platform.

12. The method of claim 9 , wherein the intercept vehicle is launched via a dispenser of the platform.

13. The method of claim 9 , further comprising performing a divert maneuver with one or more divert thrusters of the intercept vehicle to divert the intercept vehicle from the intercept vector one or more times after commencement of accelerating the intercept vehicle.

14. The method of claim 9 , further comprising causing the intercept vehicle to perform the second action of the launch sequence after the intercept vehicle has changed position relative to the platform by a particular distance.

15. The method of claim 9 , wherein the first action of the launch sequence comprises releasing the intercept vehicle from a carrier disposed on the platform into air deflected by the platform.

16. The method of claim 9 , further comprising initiating the first action of the launch sequence in response to identifying the aerial threat.

17. The method of claim 9 , further comprising determining the intercept vector in response to identifying the aerial threat.

18. A method of intercepting an aerial threat, comprising:
causing an intercept vehicle to exit a vicinity of an aerial platform, the intercept vehicle originally being coupled to the aerial platform;
causing the intercept vehicle to perform 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
subsequent to causing the intercept vehicle to perform the pitch maneuver, firing a rocket motor of the intercept vehicle to cause the intercept vehicle to accelerate along a flight path of the intercept vehicle.

19. The method of claim 18 , wherein causing the intercept vehicle to perform the pitch maneuver comprises transmitting at least one pitch command to the intercept vehicle.

20. The method of claim 19 , further comprising transmitting at least one guidance command to the intercept vehicle during flight to perform a divert maneuver via one or more divert thrusters.

21. The method of claim 18 , further comprising identifying the aerial threat as a potential threat to at least one object.

22. The method of claim 21 , wherein the at least one object is one of the aerial platform, a ground vehicle, another aerial platform, or a ground structure.

Assignees

• Northrop Grumman Systems Corp

Inventors

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

Classifications

• F42B10/661

  using several transversally acting rocket motors, each motor containing an individual propellant charge, e.g. solid charge · CPC title

• F41G7/303

  Sighting or tracking devices especially provided for simultaneous observation of the target and of the missile · CPC title

• F42B10/66

  Steering by varying intensity or direction of thrust (thrust vector control of rocket engine plants F02K9/80 {; guiding or controlling apparatus using jets adapted for cosmonautic vehicles B64G1/26}) · CPC title

• F41H11/02 Primary

  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

• F41G7/007

  Preparatory measures taken before the launching of the guided missiles · CPC title