Midbody camera/sensor navigation and automatic target recognition

Patent metadata

Field	Value
Publication number	US-11371806-B2
Application number	US-201916531224-A
Country	US
Kind code	B2
Filing date	Aug 5, 2019
Priority date	Aug 5, 2019
Publication date	Jun 28, 2022
Grant date	Jun 28, 2022

Abstract

A guidance assembly and method for guiding an ordnance to a target. The assembly can operated in navigation and targeting modes and has an imager/seeker including an objective lens assembly and an imaging sensor array which provide image data for mapping and terminal seeker performance. The imager/seeker is pivotally mounted on the ordnance. An actuator is coupled to the imager/seeker and can be actuated to pivot the imager/seeker relative to a longitudinal axis of the ordnance from a navigation position to a targeting position. A flight control unit communicates with the imager/seeker and the actuator, and has a processor which analyses the image data to provide navigation flight control signals for guiding the ordnance in the navigation mode of operation and determining a target direction via automatic target recognition or aimpoint algorithms for directing the ordnance to the target in the targeting mode of operation.

First claim

What is claimed:

1. A guidance assembly being operable in a navigation mode and targeting mode for guiding an ordnance to a target, the guidance assembly comprising:
an imager/seeker having an objective lens assembly and an imaging sensor array which capture light energy and provide image data for the navigation and targeting modes of operation, the imager/seeker being pivotally mounted on a mid-body location of the ordnance;
an actuator being coupled to the imager/seeker and actuatable to pivot the imager/seeker relative to a longitudinal axis of the ordnance from a navigation position to a targeting position;
a flight control unit communicating with the imager/seeker, the flight control unit having a processor which analyses the image data and provides navigation flight control signals for guiding the ordnance in the navigation mode of operation and determines a target direction via automatic target recognition algorithms for directing the ordnance to the target in the targeting mode of operation;
wherein the flight control unit, during the navigation mode of operation, collects images from the imager/seeker while the imager/seeker is arranged in the navigation position, the flight control unit scales the collected images based on an altitude of the ordnance and de-warps the images, the flight control unit compares the collected images to a data base of images to determine ground position; and
during a transition from the navigation mode of operation to the targeting mode of operation, the actuator pivots the imager/seeker to the targeting position based on a range of the flight or by detecting the target within the field of view of the imager/seeker.

2. The guidance assembly according to claim 1 , wherein the imager/seeker being arranged in the navigation position during the navigation mode of operation and being pivoted, relative to the longitudinal axis, to the targeting position for the targeting mode of operation;
the imager/seeker having a field of view that, in the navigation position of the imager/seeker, is directed laterally relative to the longitudinal axis of the ordnance, and in the targeting position of the imager/seeker, the field of view is directed forward relative to a direction of flight of the ordnance.

3. The guidance assembly according to claim 1 , wherein the imager/seeker having a field of view and a central axis, the central axis defining a center of the field of view,
in the navigation position of the imager/seeker, the central axis of the imager/seeker extends either substantially perpendicular to the longitudinal axis or at an obtuse angle relative to the longitudinal axis in a direction of flight of the ordnance; and
in the targeting position of the imager/seeker, the central axis of the imager/seeker extends at an acute angle relative to the longitudinal axis in the direction of flight of the ordnance.

4. The guidance assembly according to claim 3 , wherein in the targeting position of the imager/seeker, the central axis of the imager/seeker extends forward in the direction of flight of the ordnance such that an entirety of the field of view of the imager/seeker extends forward in the direction of flight of the ordnance.

5. The guidance assembly according to claim 1 , wherein the imager/seeker is mounted on the ordnance by an articulation such that, in the navigation position, the imager/seeker is entirely located within an interior of the ordnance, and, in the targeting position, at least a portion of the imager/seeker extends through an opening in the ordnance to an exterior of the ordnance.

6. The guidance assembly according to claim 5 , wherein the articulation being arranged at a leading end of the opening relative to the direction of flight; and
a window being mounted on the ordnance enclosing the opening when the imager/seeker is arranged in the navigation position, and at least a leading end of the window being biased out of the opening away from the longitudinal axis when the imager/seeker is arranged in the targeting position.

7. The guidance assembly according to claim 1 , wherein the flight control unit communicating with an inertial measuring unit during the navigation mode of operation to determine an attitude of the ordnance based on the image data of the imager/seeker and measurements of the inertial measuring unit.

8. The guidance assembly according to claim 2 , wherein the ordnance comprises an opening in which a window is mounted, the window being transparent to the light energy, the imager/seeker is mounted to the ordnance by an articulation such that, in both the navigation and the targeting positions, the imager/seeker is located within an interior of the ordnance.

9. The guidance assembly according to claim 8 , wherein the articulation couples the imager/seeker at a trailing end of the window relative to the direction of flight of the ordnance, and the imager/seeker is located entirely within the interior of the ordnance in both the navigation and the targeting positions.

10. The guidance assembly according to claim 1 , wherein the imager/seeker is supported within the ordnance and the objective lens assembly comprises a window that is mounted to an outer surface of the ordnance, the window being sealed to the outer surface of the ordnance by a window seal to protect the imager/seeker from an exterior of the ordnance.

11. The guidance assembly according to claim 1 , further comprising a global positioning system, an inertial measuring unit, and a laser range finder which collect at least one of mapping, navigation, motion, force, range and distance readings/data which are processed by the processor to facilitate guiding the ordnance in the navigation mode of operation and determining the target direction and directing the ordnance to the target in the targeting mode of operation.

12. A method of guiding an ordnance with a guidance assembly that operates in a navigation mode and a targeting mode, the method comprising:
providing on the mid-body of the ordnance a guidance assembly having a single imager/seeker that is pivotable depending on an operating mode of the guidance assembly;
installing the imager/seeker in a navigation position within the ordnance;
operating the guidance assembly in the navigation mode;
determining, with a flight control unit, an attitude of the ordnance;
controlling, with the flight control unit, a trajectory of the ordnance;
switching operation of the guidance assembly from the navigation mode of operation to the targeting mode of operation;
pivoting the imager/seeker from the navigation position to a targeting position;
capturing and detecting light energy relating to the target with the imager/seeker;
determining specific target information with the flight control unit; and
guiding the ordnance with the flight control unit to impact with the target;

wherein the flight control unit, during the navigation mode of operation, collects images from the imager/seeker while the imager/seeker is arranged in the navigation position, the flight control unit scales the collected images based on an altitude of the ordnance and de-warps the images, the flight control unit compares the collected images to a data base of images to determine ground position; and
during a transition from the navigation mode of operation to the targeting mode of operation, the actuator pivots the imager/seeker to the targeting position based on a range of the flight or by detecting the target within the field of view of the imager/seeker.

13. The method according to claim 12 , further comprising installing the imager/seeker in the navigation position in which a center axis of the imager/seeker i

Assignees

• Bae Sys Inf & Elect Sys Integ

Inventors

• Choiniere Michael J

Classifications

• F41G7/2253 Primary

  Passive homing systems, i.e. comprising a receiver and do not requiring an active illumination of the target · CPC title

• F41G7/008

  Combinations of different guidance systems · CPC title

• F41G7/346

  using global navigation satellite systems, e.g. GPS, GALILEO, GLONASS · CPC title

• F41G7/2293

  using electromagnetic waves other than radio waves · CPC title

• F41G7/26

  Optical guidance systems · CPC title