Mid body seeker payload

Patent metadata

Field	Value
Publication number	US-10345087-B2
Application number	US-201715665656-A
Country	US
Kind code	B2
Filing date	Aug 1, 2017
Priority date	Aug 1, 2017
Publication date	Jul 9, 2019
Grant date	Jul 9, 2019

Abstract

A mid-body which a cylindrical housing which defines a longitudinal axis and has an interior compartment. A guidance controller is housed within the mid-body for controlling flight. A plurality of wings are connected to the housing and each of the wings is movable into a deployed position to provide guidance during flight. The mid-body has an access window which facilitates communication between the interior compartment of the housing and an external environment. A normally door covers the access window, but when the door is moved, relative to the access window, into an open position, communication between the interior compartment and the external environment is established. An optical sensor is accommodated within the interior compartment and the optical sensor, once the door is moved relative to the access window, can view the external environment and supply data to the guidance controller for controlling operation of the plurality of wings during flight.

First claim

What is claimed is:

1. A mid-body for an airframe, both the mid-body and the airframe having a leading end and a trailing end, and the mid-body comprising:
a cylindrical housing defining a longitudinal axis and having an interior compartment;
a guidance controller being housed within the mid-body for controlling flight of an airframe;
a plurality of wings having a first end pivotably coupled to the housing adjacent a leading end of each of the plurality of wings, and each of the plurality of wings being movable from a retracted position into a deployed position in which a second end of each of the plurality of wings extends away the housing to provide guidance during flight;
the housing of the mid-body having an access window which facilitates communication between the interior compartment of the housing and an external environment;
a door panel having a closed position, in which the door panel covers the access window, and an open position, in which the door panel is moved relative to the access window to facilitate communication between the interior compartment of the housing and the external environment, wherein both the access window and the door panel are located between the plurality of wings and a rocket motor interface which facilitates connection of the mid-body to a rocket motor; and
an optical sensor being accommodated within the interior compartment of the housing and having a forward field of view, and the optical sensor, once the door panel is moved into its deployed position, facilitates viewing the external environment and supplying data to the guidance controller for controlling operation of the plurality of wings during flight.

2. The mid-body of the airframe according to claim 1 , wherein the door panel, when in its normally closed position, seals and covers the access window and protects the optical sensor accommodated within the internal compartment.

3. The mid-body of the airframe according to claim 2 , wherein the optical sensor is connected to a driver and the guidance controller, the driver moves the optical sensor relative to the access window such that the optical sensor partially extends through the access window.

4. The mid-body of the airframe according to claim 1 , wherein the leading end of the mid-body has a warhead interface which facilitates connection of the mid-body to a warhead, and the trailing end of the mid-body has the rocket motor interface which facilitates connection of the mid-body to the rocket motor.

5. The mid-body of the airframe according to claim 4 , wherein the plurality of wings comprise four guidance wings, wherein each wing has a first end which is pivotably secured to the housing, while an opposite second end of each wing is pivotable into a deployed position following launch.

6. The mid-body of the airframe according to claim 1 , wherein the plurality of wings, when in a stored position, are at least partially accommodated within a wing recess, formed in an exterior surface of the mid-body, to facilitate storage and loading of the airframe into a launch magazine.

7. The mid-body of the airframe according to claim 1 , wherein each of the plurality of wings have at least one movable/pivotable flap that is controlled by the guidance controller for adjusting a yaw and pitch, and thus a trajectory of the airframe during flight.

8. The mid-body of the airframe according to claim 1 , wherein the mid-body comprises only a single optical sensor which has a horizontally forward field of view ranging between 30 and 60 degrees and a vertical forward field of view ranging between 30 and 60 degrees.

9. The mid-body of the airframe according to claim 1 , wherein a fuse and a warhead are connected to the leading end of the mid-body while a rocket motor is connected to the trailing end of the mid-body.

10. The mid-body of the airframe according to claim 1 , wherein the door panel is coupled to the housing by a hinge, the hinge is fixedly attached along a longitudinal edge of the door panel and the access window to facilitating pivoting of the door panel from its closed to its deployed position.

11. The mid-body of the airframe according to claim 1 , wherein the door panel is coupled to the housing by a hinge, and the hinge is fixed attached along a trailing edge of the door panel and the access window to facilitating pivoting of the door panel from its closed to its deployed position.

12. The mid-body of the airframe according to claim 1 , wherein the door panel is detachably coupled to the access window such that the door panel, when deployed by the door panel actuator, becomes completely separated from the mid-body.

13. The mid-body of the airframe according to claim 1 , wherein the mid-body has a pair of opposed tracks which mate with opposed edges of the door panel to facilitate sliding movement of the door panel, relative to the access window, and movement of the door panel from its closed to its deployed position.

Assignees

• Bae Sys Inf & Elect Sys Integ
• Bae Systems Informaticn And Electronic Systems Integration Inc

Inventors

• Choiniere Michael J
• Batchelder Jason H
• Evans Peter J
• Hallerman Gregory R

Classifications

• F42B15/10

  Missiles having a trajectory only in the air · CPC title

• F42B15/08 Primary

  for carrying measuring instruments; {Arrangements for mounting sensitive cargo within a projectile}(adaptations for meteorology G01W1/08); {Arrangements for acoustic sensitive cargo within a projectile} · 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

• F42B10/14 Primary

  using fins spread or deployed after launch, e.g. after leaving the barrel · CPC title

• F42B30/006

  Mounting of sensors, antennas or target trackers on projectiles · CPC title