System for retracting and extending airborne sensors
A retractable optical sensor system includes a sensor body (e.g., an electro-optical/infrared (EO/IR) remote sensor) connected to a sensor support structure that is actuated by an actuator. The sensor support structure accomplishes angular movement whose turning point is located in an end that is mounted to an articulation support. A bulkhead support is fastened to the aircraft structure. The actuator is electrically or hydraulically actuated and has an end united to a support member which is fastened to the aircraft structure. The opposite end of the actuator is connected for articulation to the sensor support structure so as to cause angular movement thereof. Articulation of the sensor support structure causes the sensor body to extend/retract while simultaneously causing the fairing door to be raised/lowered, respectively.
1. A system for retracting and extending an airborne sensor assembly comprising:
a sensor body containing an airborne sensor movable between retracted and extended positions thereof relative to a sensor bay;
a bearing support defining a transverse articulation axis;
a cantilevered sensor support structure having one end fixed to the sensor body and an opposite end connected to the bearing support at the transverse articulation axis thereof to allow for articulated movement of the sensor support structure between upper and lower positions thereof, wherein the cantilevered sensor support structure supports the sensor body for movement between the retracted and extended positions thereof in response to articulated movement of the cantilevered support structure between the upper and lower positions, respectively;
a sensor bay door movable between lowered and raised positions and having an edge partially surrounding the sensor body when in the lowered position thereof;
a linkage assembly operatively connecting the sensor bay door to the cantilevered sensor support structure for moving the sensor bay door between the lowered and raised positions thereof in response to the sensor support structure being moved between the upper and lower positions thereof, respectively; and
an actuator assembly operatively connected to the sensor support assembly for moving the sensor support structure between the upper and lower positions thereof to thereby responsively cause the sensor body to move between the retracted and extended positions thereof and the sensor bay door to move between the lowered and lowered positions thereof, respectively, such that the sensor bay door is in the raised position thereof within the sensor bay when the sensor body is in the extended position thereof, and the sensor bay door is in the lowered position thereof with the edge at least partially surrounding the sensor body when the sensor body is in the retracted position thereof within the sensor bay.
2. The system of claim 1 , wherein the linkage assembly comprises a hinge connected to the sensor bay door and a tie rod pivotally connected to the hinge at one end thereof and to the sensor support structure at an opposite end thereof.
3. The system of claim 1 , wherein the actuator is comprises a piston and a piston rod having an end connected pivotally to the sensor support structure.
4. The system of claim 1 , wherein the edge of the sensor bay door surrounds about one-half of the sensor bay body when in the retracted position thereof.
5. An aircraft comprising:
an airborne sensor assembly comprising a sensor body containing an airborne sensor;
a fuselage fairing defining a sensor bay for housing the airborne sensor assembly and a fairing opening to allow the sensor body to be moveably between a retracted position wherein the airborne sensor is positioned within the sensor bay and an extended position wherein the airborne sensor is positioned outside the sensor bay; and
a system for retracting and extending the airborne sensor assembly relative to the sensor opening of the fairing, wherein the system includes:
(i) a bearing support fixed to the fuselage and defining a transverse articulation axis;
(ii) a cantilevered sensor support structure having one end fixed to the sensor body and an opposite end connected to the bearing support at the transverse articulation axis thereof to allow for articulated movement of the sensor support structure between upper and lower positions thereof, wherein the cantilevered sensor support structure supports the sensor body for movement between the retracted and extended positions thereof in response to articulated movement of the cantilevered support structure between the upper and lower positions, respectively;
(iii) a sensor bay door movable between lowered and raised positions relative to the fairing opening and having an edge partially surrounding the sensor body when in the lowered position thereof;
(iv) a linkage assembly operatively connecting the sensor bay door to the cantilevered sensor support structure for moving the sensor bay door between the lowered and raised positions thereof in response to the sensor support structure being moved between the upper and lower positions thereof, respectively; and
(v) an actuator assembly operatively connected to the sensor support assembly for moving the sensor support structure between the upper and lower positions thereof to thereby responsively cause the sensor body to move between the retracted and extended positions thereof and the sensor bay door to move between the lowered and lowered positions thereof, respectively, such that the sensor bay door is in the raised position thereof within the sensor bay when the sensor body is in the extended position thereof, and the sensor bay door is in the lowered position thereof with the edge at least partially surrounding the sensor body when the sensor body is in the retracted position thereof within the sensor bay.
6. The aircraft of claim 5 , wherein the linkage assembly comprises a hinge connected to the sensor bay door and a tie rod pivotally connected to the hinge at one end thereof and to the sensor support structure at an opposite end thereof.
7. The aircraft of claim 5 , wherein the actuator is comprises a piston and a piston rod having an end connected pivotally to the sensor support structure.
8. The aircraft of claim 5 , wherein the edge of the sensor bay door surrounds about one-half of the sensor bay body when in the retracted position thereof.