US 11,994,367 B2
Methods and apparatuses for aerial interception of aerial threats
James Kolanek, Goleta, CA (US); Behshad Baseghi, Santa Barbara, CA (US); David Sharpin, Simi Valley, CA (US); Anthony Visco, Woodland Hills, CA (US); and Falin Shieh, Calabasas, CA (US)
Assigned to Northrop Grumman Systems Corporation, Plymouth, MN (US)
Filed by Northrop Grumman Systems Corporation, Falls Church, VA (US)
Filed on Apr. 25, 2022, as Appl. No. 17/728,624.
Application 17/728,624 is a continuation of application No. 16/584,378, filed on Sep. 26, 2019, granted, now 11,313,650.
Application 16/584,378 is a continuation of application No. 15/411,324, filed on Jan. 20, 2017, granted, now 10,436,554, issued on Oct. 8, 2019.
Application 15/411,324 is a continuation of application No. 13/839,637, filed on Mar. 15, 2013, granted, now 9,551,552, issued on Jan. 24, 2017.
Application 13/839,637 is a continuation in part of application No. 13/455,831, filed on Apr. 25, 2012, granted, now 9,170,070, issued on Oct. 27, 2015.
Claims priority of provisional application 61/606,010, filed on Mar. 2, 2012.
Prior Publication US 2022/0412694 A1, Dec. 29, 2022
Int. Cl. F41G 7/34 (2006.01); F41G 7/00 (2006.01); F41G 7/30 (2006.01); F41H 11/02 (2006.01); F42B 10/66 (2006.01); F42B 15/01 (2006.01); F42B 15/10 (2006.01); G05D 1/00 (2006.01); G05D 1/08 (2006.01); G06T 7/246 (2017.01); F42B 15/00 (2006.01)
CPC F41G 7/34 (2013.01) [F41G 7/007 (2013.01); F41G 7/303 (2013.01); F41H 11/02 (2013.01); F42B 10/66 (2013.01); F42B 10/661 (2013.01); F42B 15/01 (2013.01); F42B 15/105 (2013.01); G05D 1/0808 (2013.01); G06T 7/246 (2017.01)] 20 Claims
OG exemplary drawing
 
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.