Methods and apparatuses for aerial interception of aerial threats

Patent metadata

Field	Value
Publication number	US-11994367-B2
Application number	US-202217728624-A
Country	US
Kind code	B2
Filing date	Apr 25, 2022
Priority date	Mar 2, 2012
Publication date	May 28, 2024
Grant date	May 28, 2024

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 aerial vehicle carried by the aircraft, the aerial vehicle comprising:
a rocket motor configured to accelerate the aerial vehicle in a direction having a component parallel to a longitudinal axis of the aerial vehicle; and
a terminal section including alignment thrusters configured to cause the aerial vehicle to perform a pitch maneuver by rotating the aerial vehicle about an axis orthogonal to the longitudinal axis of the aerial vehicle prior to the rocket motor being fired, the rocket motor configured to detach from the terminal section after accelerating the aerial vehicle.

2. The active protection system of claim 1 , wherein the terminal section further comprises divert thrusters configured to divert the terminal section in a direction transverse to the longitudinal axis of the aerial vehicle subsequent to the rocket motor being fired and detached from the terminal section.

3. The active protection system of claim 1 , wherein the terminal section further comprises a nose thruster module proximate an airframe nose, the airframe nose at a front end of the aerial vehicle and the nose thruster module including the alignment thrusters.

4. The active protection system of claim 1 , wherein the terminal section further comprises:
a controller; and
one or more sensors operably coupled to the controller, wherein the controller is configured to, subsequent to the rocket motor detaching from the terminal section, initiate flight corrections to the aerial 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 carried by the aircraft and configured to transmit guidance signals to the aerial vehicle during flight of the aerial vehicle.

6. The active protection system of claim 1 , further comprising a detection system carried on the aircraft and comprising at least one sensor configured to detect aerial threats within 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 aerial vehicle carrier disposed on the aircraft.

9. A method of neutralizing an aerial threat, comprising:
performing a first action of a launch sequence comprising an aerial vehicle leaving a platform;
subsequent to the first action of the launch sequence, performing a second action of the launch sequence, the second action comprising performing a pitch maneuver by rotating the aerial vehicle about an axis orthogonal to a longitudinal axis of the aerial vehicle;
subsequent to the second action of the launch sequence, firing a rocket motor of the aerial vehicle to cause the aerial vehicle to accelerate in a direction having a component parallel to the longitudinal axis of the aerial vehicle;
subsequent to firing the rocket motor, detaching the rocket motor from a terminal section of the aerial vehicle.

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

11. The method of claim 9 , wherein performing the first action of the launch sequence comprises propelling the aerial vehicle from the platform.

12. The method of claim 9 , wherein performing the first action of the launch sequence comprises launching the aerial vehicle 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 aerial vehicle to divert the aerial vehicle one or more times subsequent to: firing the rocket motor; and detaching the rocket motor from the terminal section.

14. The method of claim 9 , further comprising performing the second action of the launch sequence after the aerial vehicle is a particular distance away from the platform.

15. The method of claim 9 , wherein performing the first action of the launch sequence comprises releasing the aerial 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 responsive to identifying the aerial threat.

17. A method of countering an aerial threat, comprising:
causing an aerial vehicle to exit a vicinity of an aerial platform;
causing the aerial vehicle to perform a pitch maneuver by rotating the aerial vehicle about an axis orthogonal to a longitudinal axis of the aerial vehicle;
subsequent to causing the aerial vehicle to perform the pitch maneuver, causing a rocket motor of the aerial vehicle to fire and accelerate the aerial vehicle in a direction having a component parallel to the longitudinal axis of the aerial vehicle; and
subsequent to firing the rocket motor, causing the rocket motor to detach from a terminal section of the aerial vehicle.

18. The method of claim 17 , further comprising identifying the aerial threat as a potential threat to at least one object.

19. The method of claim 18 , wherein the at least one object is one of the aerial platform, a ground vehicle, another aerial platform, or a ground structure.

20. The method of claim 18 , further comprising causing a payload of the aerial vehicle to detonate upon interception of the aerial threat with the aerial vehicle.

Assignees

• Northrop Grumman Systems Corp

Inventors

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

Classifications

• F41G7/34 Primary

  based on predetermined target position data · CPC title

• F41G7/007

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

• F41G7/303

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

• 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