Patent Description:
Vehicle-borne sensors, and more particularly aerial sensors, are used for a wide variety of applications. For example, sensor platforms may be deployed on aircraft for military and civilian purposes, such as the C-<NUM> aircraft, such as for purposes of surveillance, targeting, chemical detection, weather monitoring, and a wide variety of other applications. Providing such airborne sensor platforms can significantly extend the range for monitoring or detecting a particular condition well beyond capabilities afforded by many ground-based sensor systems.

However, challenges exists in the deployment and use of such airborne sensor systems. For example, while certain aircraft may be readily able to carry a sensor platform of a particular configuration, outfitting of the aircraft with such a sensor system can be a time intensive process, creating significant challenge in emergency situations. Moreover, such sensor systems typically carry highly sensitive equipment that may quite easily loose calibration when subjected to vibrations or shocks as may be encountered in routine flights of the aircrafts that carry them. Even further, while many of such sensors must be calibrated for proper or at least optimal use, such through bore-sighting of an aircraft mounted laser or the like, such calibration when the aircraft is in flight can be a significant challenge. More particularly, as it is desirable to provide such sensors with as wide a view as possible, in use they will often deploy to a position that locates the sensor itself below the bottom of the fuselage of the aircraft. With such sensor platforms, carrying out calibration of such sensors on the ground is typically not an option, as deploying the sensor platform to its use position when the aircraft is on the ground would have the sensor impact the ground due to insufficient clearance between the bottom of the fuselage and the ground.

<CIT> relates to a sensor-carrying pod which has middle and readily detachable end sections. The end sections are chosen from a suite of different end sections, depending upon the sensors used in a mission. The sections may include panels, or windows specifically transmissive to predetermined wavelengths, such as visible and IR. A deployment arrangement allows the pod to move horizontally and vertically, from an aircraft, into the airstream, and back again after a mission. The door of the aircraft is sealed around a component of the deployment arrangement to allow for pressurization of the aircraft for high altitude reconnaissance missions.

<CIT> relates to an aircrew automation system that provides a pilot with high-fidelity knowledge of the aircraft's physical state, and notifies that pilot of any deviations in expected state based on predictive models. The aircrew automation may be provided as a non-invasive ride-along aircrew automation system that perceives the state of the aircraft through visual techniques, derives the aircraft state vector and other aircraft information, and communicates any deviations from expected aircraft state to the pilot.

Therefore, there remains a need in the art for a vehicle-born sensor system, such as an aerial sensor system carried by an aircraft and deployed from the aircraft during flight, that is easily installed onto and removed from the aircraft so as to allow varied sensors to be deployed for varying missions, that is sufficiently robust so as to be able to withstand the vibrations and shocks typically experienced during flight operations, and that allows for ground-based calibration, such as bore-sighting, of the sensor platform without damage to the sensor platform.

The present invention is defined in appended independent claim <NUM> to which reference should be made.

Disclosed herein is a modular, palletized, deployable sensor system configured for easy roll-on / roll-off installation and removal from a vehicle such as an aircraft. The system includes a pallet sized and otherwise configured for removable placement on a deck on the interior of an aircraft. A tray system is affixed to the pallet, which tray system carries a moveable carriage that moves a pivotable arm and sensor head toward and away from a door in the fuselage of the aircraft. The sensor head is mounted to the arm along an angled interface that allows angular displacement of the sensor head with respect to the arm that carries it, which significantly aids in ground-based bore sighting of instruments within the sensor head. A pivot assembly is carried by the moveable carriage that pivots the arm and sensor head into position after moving them outside of the aircraft, and holds them in such position in a manner that ensures that a natural frequency of the arm and the sensor head does not fall below <NUM> (thus maintaining the stability of the arm and sensor head assembly during use in flight operations). A wire guide is also provided between the tray system and a pallet-mounted control console, which wire guide controls the paths of cables extending form the console ultimately to the sensor head.

The accompanying drawings, which are included to provide further understanding of the invention and are incorporated in and constitute a part of this specification, illustrate embodiments of the present invention and together with the below description, serve to explain the principles of the invention.

The invention may be understood by referring to the following description, claims, and accompanying drawings. This description of an embodiment, set out below to enable one to practice an implementation of the invention, is not intended to limit the preferred embodiment, but to serve as a particular example thereof. Those skilled in the art should appreciate that they may readily use the conception and specific embodiments disclosed as a basis for modifying or designing other methods and systems for carrying out the same purposes of the present invention. Those skilled in the art should also realize that such assemblies do not depart from the scope of the invention in its broadest form.

Disclosed herein is a modular, palletized, roll-on / roll-off system for a deployable sensor that provides for easy deployment with minimal interconnection to the vehicle carrying such system, and with no requirement for modification to the vehicle carrying such system. As shown in <FIG>, a system in accordance with certain aspects of an embodiment provides for a deployable sensor head <NUM> mounted to the end of a moveable arm <NUM>, which in use extends through the fuselage of an aircraft <NUM>, and more particularly through an opening in a door panel of the aircraft <NUM>. The sensor head <NUM>, when fully deployed, extends downward from the opening in the door panel of the aircraft <NUM> preferably by a sufficient distance to provide a wide field of view, and more preferably a <NUM>° view, without being blocked by any part of the aircraft's fuselage. In such position, moveable arm <NUM> is generally vertical with respect to the aircraft's fuselage (i.e., oriented such that a major axis extending through the length of arm <NUM> is perpendicular to a major axis extending from the front end to the back end of the aircraft), with the portion of arm <NUM> closest to sensor head <NUM> being similarly vertically aligned with the rest of arm <NUM>.

<FIG> shows a modular, palletized, deployable sensor system <NUM> in accordance with certain aspects of an embodiment of the invention including sensor head <NUM> and arm <NUM> as described above and positioned on the interior deck <NUM> of aircraft <NUM>. Likewise, <FIG> shows a close-up rear view of deployable sensor system <NUM> with sensor head <NUM> in the fully deployed position, and <FIG> shows a detailed, partially exploded perspective view of deployable sensor system <NUM> with sensor head <NUM> in the fully deployed position. While the following elements of system <NUM> are described in greater detail below, by way of summary the major components of such system include sensor head <NUM>, arm <NUM>, a pallet <NUM> mounted to the deck <NUM> of aircraft <NUM>, and a tray system <NUM> mounted to the pallet <NUM>, which tray system <NUM> moveably mounts a moveable carriage <NUM> to move sensor head <NUM> and arm <NUM> toward its deployed position and back to its stowed position. A door system (shown generally at <NUM>) seals the interior of aircraft <NUM> when sensor system <NUM> is stowed and not in use (as shown in <FIG>), and allows sensor head <NUM> and arm <NUM> to extend through when deployed. In this configuration when intended for use, door system <NUM> may be opened, and sensor head <NUM> and arm <NUM> may be moved through door system <NUM> from its stowed position (shown in <FIG>) to its deployed position (shown in <FIG>). In that deployed position, sensor head <NUM> (which may by way of non-limiting example comprise a camera system, a radiation detection system, an infrared system, or such other sensor systems as may occur to those skilled in the art) may be employed to perform its intended function and collect the intended data. After use, the sensor head <NUM> and arm <NUM> may be retracted back into the fuselage of aircraft <NUM>, door system <NUM> may be closed, and flight operations may continue as normal.

With continuing reference to <FIG>, deployable sensor system <NUM> is mounted on a base <NUM>, such as a pallet that provides a base on which the entire deployable sensor system <NUM> is mounted, thus providing a ready roll-on / roll-off function for quick and easy installation and removal from an aircraft. In certain configurations, pallet <NUM> may comprise a <NUM> type air cargo handling pallet, which provides a ready-to-install base for fixed positioning on the deck <NUM> of an aircraft <NUM>, such as a C130 aircraft deck, and which provides a ready roll-on / roll-off capability for easy installation and removal of the entire deployable sensor system <NUM>. Brackets <NUM> for use in attaching a <NUM> pallet to the deck of a C130 (and which are of known configuration) are provided to fix deployable sensor system <NUM> to deck <NUM> once pallet <NUM> is properly positioned within the aircraft fuselage. For example, brackets <NUM> allow pallet <NUM>, and thus all of deployable sensor system <NUM>, to be bolted or otherwise rigidly affixed to the body of the aircraft <NUM>, and more particularly to deck <NUM> within the fuselage of aircraft <NUM>.

Mounted at the rear edge of pallet <NUM> (i.e., the portion of pallet <NUM> closest to the rear of aircraft <NUM>) is tray system <NUM>. As discussed in greater detail below, tray system <NUM> moveably mounts moveable carriage <NUM> for lateral movement (i.e., side to side movement with respect to deck <NUM> on which pallet <NUM> is positioned) from a stowed position (shown in <FIG>) to a deployed position (shown in <FIG> and <FIG>). Moveable carriage <NUM> in turn carries arm <NUM> and sensor head <NUM>, such that as moveable carriage <NUM> moves toward its deployed position, sensor head <NUM> and arm <NUM> extend outward through door system <NUM> toward their deployed position. Moveable carriage <NUM> also carries a pivot assembly (shown generally at <NUM>) that pivots arm <NUM> and sensor head <NUM> from the generally horizontal, stowed position of <FIG> to the generally vertical, deployed position of <FIG> and <FIG>. Pivot assembly <NUM>, as discussed in greater detail below, includes an extensible shaft <NUM> that is pivotably mounted to moveable carriage <NUM>, and that joins to arm <NUM> at a pivot knuckle <NUM> so that extension of shaft <NUM> pivots arm <NUM> and sensor head <NUM> at pivot knuckle <NUM> downward toward their deployed position, and so that retraction of shaft <NUM> pivots arm <NUM> and sensor head <NUM> at pivot knuckle <NUM> upward toward their stowed position. Additionally, pallet <NUM> carries instrumentation and control consoles <NUM> that may include all controls necessary for operating deployable sensor system <NUM>, and preferably operator stations (including seats), all positioned at the forward side of pallet <NUM> (best shown in <FIG>). Also as discussed in more detail below, a wire guide <NUM> is positioned on pallet <NUM> between tray system <NUM> and instrumentation and control consoles <NUM>, which wire guide <NUM> directs a length of wires from instrumentation and control consoles <NUM> to moveable carriage <NUM> for data communication as moveable carriage <NUM> moves from its stowed to its deployed position, and vice versa.

Next, <FIG> show the progressive movement of arm <NUM> and sensor head <NUM> from the stowed position (shown in <FIG>), to an intermediate position (shown in <FIG>), and ultimately to the fully deployed position (shown in <FIG>) (all with certain elements of deployable sensor system <NUM> not shown for clarity). With reference to <FIG>, in the stowed position, moveable carriage <NUM> is positioned so that the end of sensor head <NUM> is contained within the footprint of pallet <NUM> (i.e., with moveable carriage <NUM> positioned furthest toward the end of tray system <NUM> that is opposite door system <NUM>). In this position, arm <NUM> is positioned so that a major axis extending through the length of arm <NUM> is generally parallel to the length of tray system <NUM>. A door sealing panel <NUM> is mounted to pivot knuckle <NUM>, which will seal an opening <NUM> in door system <NUM> when the deployable sensor system <NUM> is fully deployed. In the fully stowed position of <FIG>, such door sealing panel <NUM> sits at an upward angle pointing away from door system <NUM>, and will ultimately pivot to an upward angle pointing toward door system <NUM> as deployable sensor system <NUM> is deployed (as shown in <FIG>). Next, and with reference to <FIG>, during deployment of sensor head <NUM> to the exterior of the aircraft, moveable carriage <NUM> travels laterally (with respect to aircraft <NUM>) along tray system <NUM> toward door system <NUM>. Before advancing moveable carriage <NUM> toward door system <NUM>, and with reference again to <FIG>, hatch <NUM> (which fully seals door system <NUM> when deployable sensor system <NUM> is stowed and not in use) is opened to provide an opening <NUM> in the fuselage (sized to sealingly receive door sealing panel <NUM>) that will allow sensor head <NUM> and arm <NUM> to pass through to the exterior of the aircraft. Finally, and with reference to <FIG>, arm <NUM> and sensor head <NUM> are pivoted downward by pivot assembly <NUM>, as pivot knuckle <NUM> carries door sealing panel <NUM> into alignment with and ultimately sealing of opening <NUM> in door system <NUM>. In this position, sensor head <NUM> may be operated to collect the intended data from outside of aircraft <NUM>.

<FIG> shows a rear, cross-sectional view of pivot assembly <NUM> engaging pivot knuckle <NUM> to pivot and ultimately hold arm <NUM> and sensor head <NUM> in their fully deployed position outside of aircraft <NUM>. Pivot assembly <NUM> includes a housing <NUM> that is pivotably mounted at pivot joint <NUM> to moveable carriage <NUM>. Housing <NUM> preferably comprises a screw jack operated by a screw jack motor <NUM> (<FIG>) that extends and retracts shaft <NUM>. A shaft head <NUM> affixed to the distal end of shaft <NUM> pivotably attaches to pivot knuckle <NUM> at knuckle connector shaft <NUM>. Shaft head <NUM> abuts a bottom portion of a curved notch <NUM> (having a complementary shape to shaft head <NUM>) in pivot knuckle <NUM> when arm <NUM> and sensor head <NUM> are in the fully deployed position shown in <FIG>. Pivot knuckle <NUM> is in turn pivotably mounted to moveable carriage <NUM> at knuckle shaft <NUM>. Thus, as shaft <NUM> is extended, pivot knuckle <NUM> rotates about knuckle shaft <NUM>, in turn causing arm <NUM> and sensor head <NUM> to be pivoted into their deployed positions shown in <FIG>. In such fully deployed position, a bottom, forward edge <NUM> of pivot knuckle <NUM> comes in contact with a stop wedge <NUM> to stop further forward pivoting movement of pivot knuckle <NUM>. As an added security measure, positioning switches <NUM> are preferably provided, such as (by way of non-limiting example) limit switches, crash switches, encoders, and the like, to ensure proper positioning and orientation of arm <NUM> and sensor <NUM> in their fully deployed positions.

<FIG> show various close-up views of knuckle <NUM>. Knuckle <NUM> includes arms <NUM> that pivotably mount main body <NUM> to moveable carriage <NUM>, which main body <NUM> receives the top (or proximal) end of arm <NUM>. A bottom end of arms <NUM> includes openings <NUM> that receive knuckle shaft <NUM>. An upper end of arms <NUM> include openings <NUM> that receive knuckle connector shaft <NUM> (joining knuckle <NUM> to shaft head <NUM> of shaft <NUM>). Curved notch <NUM> sits between arms <NUM> and provides a point of contact with the outer face of shaft head <NUM> as knuckle <NUM> is rotated from the stowed position to the deployed position. A cable pass-through <NUM> is situated at the top of main body <NUM> of knuckle <NUM>, allowing electrical cables (not shown) to pass from instrumentation and control consoles <NUM> ultimately into arm <NUM> and sensor head <NUM>, all while keeping a tight seal so as to maintain pressurization within the aircraft. A flange <NUM> extends around knuckle <NUM> at the interface of arms <NUM> and main body <NUM>, which flange <NUM> provides a mounting surface for door sealing panel <NUM> so as to carry door sealing panel <NUM> into its closed and sealed position upon full deployment of knuckle <NUM>.

<FIG> show close-up sectional and perspective views, respectfully, of the connection between knuckle <NUM> and arm <NUM>. As shown in <FIG>, deployable sensor system <NUM>, in accordance with certain features of a particular embodiment, may be configured with a <NUM>-point contact on knuckle <NUM>, which <NUM>-point contact prevents the natural frequency of the arm <NUM> and sensor head <NUM> assembly from dropping below <NUM>, and thus maintaining an optimal operational environment for sensor head <NUM> when it is deployed and collecting data. More particularly, when fully deployed, knuckle <NUM> is compressed between the pressure of screw jack shaft <NUM> (and specifically shaft head <NUM>) and stop wedge <NUM>. Optionally, a sacrificial plate <NUM>(a) may be situated between stop wedge <NUM> and knuckle <NUM>, which for instance may be formed from lower grade aluminum, and thus easily able to be replaced periodically on an as-needed basis without significant cost or effort. In such configuration, during the pivoting of knuckle <NUM> toward its fully deployed position, a controller slows the knuckle <NUM> as it approaches sacrificial plate <NUM>(a). Limit switch <NUM> completely stops knuckle <NUM> from further movement toward the deployed position when knuckle <NUM> contacts sacrificial plate <NUM>(a). This configuration provides the <NUM>-point contact on knuckle <NUM> without adding significant force on stop wedge <NUM> on moveable carriage <NUM>, again providing the deployable sensor system <NUM> a natural frequency that will not drop below <NUM>. Those three points of contact thus include: (i) the main pivot (knuckle shaft <NUM> joining knuckle <NUM> to moveable carriage <NUM>); (ii) knuckle connector shaft <NUM> joining screw jack shaft <NUM> (and more particularly head <NUM> of shaft <NUM>) to knuckle <NUM> (rotating about a PTFE bushing); and (iii) stop wedge <NUM>, or sacrificial plate <NUM>(a) if provided. If knuckle <NUM> is moved beyond the position allowed by limit switch <NUM>, a crash switch may additionally be provided which would activate at that point to avoid damage to stop wedge <NUM>.

<FIG> provides a close-up perspective view, and <FIG> an exploded view, of pivot assembly <NUM>. As shown in <FIG> and <FIG>, motor <NUM> powers screw jack shaft <NUM> to extend shaft <NUM> (and shaft head <NUM>) from housing <NUM>, and likewise to retract shaft <NUM>. A brake assembly <NUM> is also provided that disengages motor <NUM> from screw jack shaft <NUM>, thus allowing manual movement of knuckle <NUM> for manual pivoting of arm <NUM> and sensor head <NUM>. <FIG> provides a perspective, detail view of pivot assembly <NUM> mounted on moveable carriage <NUM>, and <FIG> provides a partially exploded view of the same. As shown in <FIG>, moveable carriage <NUM> includes mounting pins <NUM> which pivotably receive pivot assembly <NUM>, thus allowing pivotable movement of shaft <NUM> as arm <NUM> is pivoted from the stowed to the deployed positions.

Next, <FIG> shows a perspective view, and <FIG> a side view, of arm <NUM> and sensor head <NUM>. Arm <NUM> includes a main shaft <NUM> having an upper rim that attaches to main body <NUM> of knuckle <NUM>, such as by way of threaded connectors such as standard bolts. At the bottom of main body <NUM>, arm <NUM> includes an upper collar <NUM>. and a lower collar <NUM>. Lower collar <NUM> is rotatably mounted to upper collar <NUM> along an angled interface <NUM> (best shown in the close-up view of <FIG>). Sensor head <NUM>, in turn, is affixed to lower collar <NUM>, such as by way of threaded connectors such as standard bolts. A latch <NUM> locks the position of lower collar <NUM> with respect to upper collar <NUM> to prevent relative rotation between them. However, as shown in <FIG>, when latch <NUM> is open, lower collar <NUM> may be manually rotated with respect to upper collar <NUM> along angled interface <NUM>. Because the interface between upper collar <NUM> and lower collar <NUM> is angled, such rotation causes lower collar <NUM> and sensor head <NUM> to change their linear orientation with respect to main shaft <NUM> of arm <NUM>, thus creating an angular offset A between a first axis <NUM> extending through main shaft <NUM> and upper collar <NUM>, and a second axis <NUM> extending through lower collar <NUM> and sensor head <NUM>. Such configuration is useful for bore-sighting instrumentation positioned within sensor head <NUM>.

More particularly and as mentioned above, arm <NUM> and sensor head <NUM> are provided a sufficient length so that when they are in their fully deployed position outside of the aircraft, sensor head <NUM> extends preferably below the bottom of the fuselage of the aircraft to provide a maximized field of view. Of course, when the aircraft is positioned on the ground, such full deployment of arm <NUM> and sensor head <NUM> would not be possible, as lowering sensor head <NUM> toward that fully deployed position would cause it to impact the ground surface on which the grounded aircraft is located. However, vertical orientation of at least sensor head <NUM> is desirable when the aircraft is on the ground to allow bore-sighting of the sensors within sensor head <NUM>. Thus, when aircraft <NUM> is positioned on the ground, arm <NUM> and sensor head <NUM> may be extended out of the aircraft's fuselage as detailed above, and particularly to the intermediate position shown in <FIG>. At this point, arm <NUM> and sensor head <NUM> may be moved by pivot assembly <NUM> only partially toward the fully deployed position, and preferably to a position in which the first axis <NUM> extending through main shaft <NUM> of arm <NUM> and second axis <NUM> extending through sensor head <NUM> (being collinear) are positioned at approximately <NUM>° degrees to horizontal. In this position, latch <NUM> may be released, and sensor head <NUM> may be pivoted (by rotating lower collar <NUM> with respect to upper collar <NUM>) so that second axis <NUM> is vertically aligned while first axis <NUM> remains angled with respect to horizontal. In this intermediately deployed position, the bottom of sensor head <NUM> is positioned vertically above what its position would otherwise be if lower collar <NUM> had not been rotated with respect to upper collar and the entire assembly of arm <NUM> and sensor head <NUM> were in their fully deployed positions. In such position with sensor head <NUM> now vertically aligned but with its bottom edge above the surface of the ground, instruments within sensor head <NUM> may be bore sighted to a fixed, ground-based target, vastly simplifying the bore-sighting process from those that must be carried out during airborne operations.

Next, <FIG> provides a detail perspective view of tray system <NUM>. As mentioned above and with reference to both <FIG> and <FIG>, tray system <NUM> moveably mounts moveable carriage <NUM> for lateral movement with respect to pallet <NUM> on which tray system <NUM> is mounted. More particularly, moveable carriage <NUM> engages a drive assembly <NUM> that moves along screw <NUM>, which screw <NUM> in turn is driven by motor assembly <NUM> on tray system <NUM>. Moveable carriage <NUM> is also preferably mounted to guide blocks <NUM> that slide along guide rails <NUM>. Motor assembly <NUM> includes a brake <NUM> that, as above, allows disengagement of motor assembly <NUM> from screw <NUM>, thus allowing manual movement of moveable carriage <NUM> with respect to tray system <NUM> when necessary. Tray system <NUM> preferably has a length that matches the width dimension of pallet <NUM>, and thus extends from one side to the other of pallet <NUM> at the back end of pallet <NUM>. Limit switches <NUM> are provided and configured to automatically terminate movement of moveable carriage <NUM> when it reaches the designated limit positions. <FIG> provides a perspective view of tray system <NUM> with moveable carriage <NUM> moved along rails <NUM> to its deployed position.

<FIG> shows a perspective view of a wire guide <NUM> with moveable carriage <NUM> having moved sensor head <NUM> and arm <NUM> to the deployed positions, such that moveable carriage <NUM> is positioned at a limit end of tray system <NUM>. <FIG> shows a perspective view wire guide <NUM> with the full deployable sensor system <NUM> in the same position as <FIG>. As shown in <FIG> and <FIG>, control cables <NUM> (interconnecting the electronics of carriage <NUM>, and ultimately of sensor head <NUM>, with control electronics of instrumentation and control consoles <NUM>, as shown in <FIG>) are routed from instrumentation and control consoles <NUM> through a wire guide (shown generally at <NUM>) that controls the path of control cables <NUM> between instrumentation and control consoles <NUM> and moveable carriage <NUM> as moveable carriage <NUM> moves along tray system <NUM>. Wire guide <NUM> includes a window <NUM> that receives cables <NUM> from the console side of deployable sensor system <NUM> and directs them toward a lower channel <NUM> on wire guide <NUM>. A chain assembly <NUM> comprised of rigid, hollow links receive and carries cables <NUM> therein. Chain assembly <NUM> has a first end positioned within lower channel <NUM>, and chain assembly <NUM> curves upward toward and is retained by an upper chain guide <NUM>, with a second end of chain assembly <NUM> being positioned adjacent upper chain guide <NUM>. From that second end of chain assembly <NUM>, cables <NUM> are directed downward toward moveable carriage <NUM>. With this configuration, as moveable carriage moves toward the deployed position shown in <FIG> and <FIG>, the path of cables <NUM> is contained within chain assembly <NUM>, which itself is contained between lower channel <NUM> and upper chain guide <NUM> of wire guide <NUM>, in turn maintaining all such control cables <NUM> cleanly deployable and stowable throughout all movement of moveable carriage <NUM>.

As shown throughout the figures, door system <NUM> is configured for easy movement from the closed position (shown in <FIG>) to the open position via pivoting mounting arms <NUM>, which cause the aircraft door to swing both inward and to the side when the door is pulled. Once the door is opened and the system <NUM> is deployed, door sealing panel <NUM> seals the opening left by open door system <NUM>.

Those skilled in the art will recognize that the foregoing offers a modular, palletized system for a deployable sensor that provides for easy deployment with minimal interconnection to the vehicle carrying such system, and with no requirement for modification to the vehicle carrying such system. The system is configured so that it is hidden from sight when the vehicle, and more particularly an aircraft, carrying such system is not in use - such as when such aircraft is on the ground, taking off, or landing, thus aiding in maintaining security during covert operations. As a palletized system, it may be easily positioned on an aircraft when desired simply through loading as any other pallet would be loaded on the aircraft, thus allowing easy installation without modification to the aircraft body.

Claim 1:
A deployable sensor system (<NUM>), comprising:
a pallet (<NUM>);
a moveable carriage (<NUM>) moveably mounted on said pallet;
an arm (<NUM>) having a first arm end adjacent said moveable carriage (<NUM>) and a second arm end opposite said first arm end and defining a longitudinal axis extending from said first arm end to said second arm end;
a sensor head (<NUM>) rotatably mounted to said second arm end and defining a second longitudinal axis extending from said arm to a distal end of said sensor head; and
a knuckle (<NUM>) pivotably mounted to said moveable carriage (<NUM>), wherein said first arm end is affixed to said knuckle;
said arm (<NUM>) further comprising:
a main shaft (<NUM>) having a first main shaft end affixed to said knuckle, and a second main shaft end opposite said first main shaft end;
an upper collar (<NUM>) having a first upper collar end attached to said second main shaft end, and a second upper collar end defining a first angled face; and a lower collar (<NUM>) having a first lower collar end rotatably attached to said second upper collar end and defining a second angled face configured to mate with said first angled face on said upper collar and a second lower collar end mounting said sensor head (<NUM>);
wherein said sensor head (<NUM>) is rotatable with respect to said main shaft (<NUM>) of said arm (<NUM>) to change an orientation of said first and second longitudinal axes from collinear to angled.