Patent Description:
Traditional multi-axis rotation system may require heavy and power consuming alignment hardware. These complex mechanical scanning systems may continuously drive the ESA in azimuth or elevation and require algorithmically complex and power consuming computers to process the received radar signals.

Therefore, a need remains for a system and related method which may overcome these limitations and provide a novel solution to simply mechanically rotating a portion or an entirety of two or more ESA panels and electrically combining the rotated ESA panels to form a single aggregate ESA. ESA configurations are described in <CIT> and <CIT>.

In one embodiment of the inventive concepts disclosed herein, a system for mechanically positioning an electronically scanned array (ESA) panel is provided as defined by claim <NUM>.

To manipulate the rotational ESA panels, an actuator is coupled with each of the two rotational ESA panels, the actuator configured to mechanically cause the rotation. The system also includes a radar display available to one of a pilot and an autopilot of the aircraft.

For overall control, the system includes a controller operatively coupled with each of the two rotational ESA panels and the actuator and a tangible, non-transitory memory configured to communicate with the controller, the tangible, non-transitory memory having instructions stored therein that, in response to execution by the controller, cause the controller to carry out each function of the system.

The controller receives a rotation trigger for commanding the actuator to rotate the two rotational ESA panels and command the actuator to rotate the two rotational ESA panels from the first azimuthal position to the second azimuthal position without stopping in an intermediate azimuthal position. The controller further electronically couples the two rotational ESA panels while in the second azimuthal position to coherently operate as a single aggregate ESA having the common boresight and receive a radar signal from the single aggregate ESA having the common boresight.

For crew awareness, the system displays the radar signal on the radar display. Once the rotation trigger may no longer be active, the controller receives a de-rotation trigger to rotate the two rotational ESA panels from the second azimuthal position to the first azimuthal position and command the actuator to de-rotate the two rotational ESA panels from the second azimuthal position to the first azimuthal position.

An additional aspect of the invention provides a method for mechanically positioning an electronically scanned array (ESA) panel, as defined by claim <NUM>.

The method includes electronically coupling the two rotational ESA panels while in the second azimuthal position to coherently operate as a single aggregate ESA having a common boresight and receiving a radar signal from the single aggregate ESA having the common boresight. The method further includes displaying the radar signal on a radar display onboard the aircraft.

It is to be understood that both the foregoing general description and the following detailed description are exemplary and explanatory only and are not necessarily restrictive of the inventive concepts as claimed. The accompanying drawings, which are incorporated in and constitute a part of the specification, illustrate embodiments of the inventive concepts and together with the general description, serve to explain the principles of the inventive concepts disclosed herein.

In the drawings in which:.

As used herein the term "approximately" in claim language as well as specification language may refer to a range of values plus or minus twenty percent (+/- <NUM>%) of the claimed value. For example, "approximately <NUM>" may refer to, and therefore claim, the range of <NUM> to <NUM>.

This is done merely for convenience and to give a general sense of the inventive concepts, thus "a" and "an" are intended to include one or at least one and the singular also includes the plural unless it is obvious that it is meant otherwise.

Broadly, embodiments of the inventive concepts disclosed herein are directed to a system and method for ESA quadrant mechanical reconfiguration. The system functions to shift some of the complexity from algorithmic manipulation of received radar data to mechanical transformation of a simple panel structure to achieve desired performance in a desired ESA boresight. The system receives a rotation trigger based on an external event such as altitude and mission and causes two or more simple ESA panels to rotate from a first azimuthal position to a second common azimuthal position without stopping at an intermediate azimuth. Once positioned, each individual rotational ESA panel is combined to function as a single aggregate ESA enabling desired performance in field of view, resolution and range at a common boresight.

Referring to <FIG>, a diagram of a system <NUM> for mechanically positioning an electronically scanned array panel in accordance with an embodiment of the inventive concepts disclosed herein is shown. Generally, a system for mechanically positioning an electronically scanned array panel may include angularly, mechanically manipulating rotational ESA panels from a first azimuthal position to a second, common azimuthal position. Once rotated, the system may function to electronically couple the two rotational ESA panels while in the second azimuthal position to coherently operate as a single aggregate ESA having a common boresight.

According to the inventive concepts disclosed herein, the system for mechanically positioning an electronically scanned array panel <NUM> includes at least two rotational ESA panels which may include a left rotational ESA <NUM> and a right rotational ESA <NUM>. In some configurations, the two rotational ESA panels may be in a chevron configuration as shown in <FIG>. Additional configurations of the rotational ESA panels may fall directly within the scope of the inventive concepts disclosed herein.

The rotational ESA <NUM><NUM> may be installed onboard an aircraft and configured for a rotation which is about a vertical axis as well as a horizontal axis. In some embodiments, the rotational ESA panels may rotate about the vertical axis which is also aligned perpendicularly with a longitudinal axis of the aircraft.

As used herein, the vertical (Z) axis may be associated with a lift vector of the aircraft about which the aircraft may yaw. A Longitudinal (X) axis may be the axis about which the aircraft may roll (e.g., centerline). The horizontal (Y) axis may be the axis about which the aircraft may pitch.

In some embodiments, the left rotational ESA <NUM> may rotate about a vertical rotation axis <NUM> in a vertical rotation direction <NUM>. While in the first azimuthal position (here, shown at <NUM> degrees left of the longitudinal axis), the left rotational ESA <NUM> may maintain a left ESA scan volume <NUM> as well as a left ESA boresight <NUM>. Similarly, the right rotational ESA <NUM> may maintain a right ESA scan volume <NUM> and a right ESA boresight <NUM> when positioned to the first azimuthal position. According to the invention, each of the at least two rotational ESA panels is individually operational in the first azimuthal position having a first boresight and collectively operational in a second azimuthal position having a common boresight, the second azimuthal position of each of the at least two rotational ESA panels being equal, the first azimuthal position distant from the second azimuthal position by the rotation. In some embodiments, the first boresight <NUM> of the left rotational ESA panel <NUM> may be distant from the first boresight <NUM> of the right rotational ESA panel <NUM> by at least <NUM> degrees. In another embodiment, the rotation from the first azimuthal position to the second azimuthal position may be approximately <NUM>-<NUM> degrees.

As used herein, an azimuthal position may include a boresight of the rotational ESA panel <NUM> in azimuth. The azimuthal position may be physically limited by aircraft internal configuration (e.g. nose radome area, aircraft structure blocking radar energy). Generally, each azimuthal position herein may be discussed surrounding a forward-looking radar system (e.g. +/- <NUM> degrees of the nose). However, additional azimuthal positions (e.g., aft, side) and elevational positions (e.g. down, up) may fall directly within the scope of the inventive concepts disclosed herein.

According to the inventive concepts disclosed herein, the system for mechanically positioning an electronically scanned array panel <NUM> includes an actuator <NUM> coupled with each of the at least two rotational ESA panels, the actuator configured to mechanically cause the rotation. The actuator <NUM> may be a single actuator <NUM> functional to rotate both of the at least two rotational ESA panels as well as multiple actuators <NUM> configured to individually rotate an individual ESA panel or multiple rotational ESA panels.

According to the invention, the system for mechanically positioning an electronically scanned array panel <NUM> further includes a radar display <NUM> available to a pilot and / or an autopilot of the aircraft. The radar display <NUM> used herein may be defined as an information device configured for presenting radar information in a format recognizable by the intended recipient. Here, a pilot may be the intended recipient wherein a visual display may be appropriate. In some embodiments, the display may be an interface configured for information exchange in a format recognizable by a mission computer or autopilot processor for autonomous operation. In some embodiments, the system for mechanically positioning an electronically scanned array panel <NUM> may include a positioning system <NUM> configured for supplying a position as well as an altitude of the aircraft.

Also, as used herein, the term aircraft may apply to any aerial vehicle to which an ESA panel may be operationally coupled. Exemplary aerial vehicles may include a manned aircraft, an unmanned aircraft system (UAS), as well as a rotorcraft and multi (e.g., quad) rotor copter.

According to the inventive concepts disclosed herein, the system for mechanically positioning an electronically scanned array panel <NUM> includes a controller <NUM> operatively coupled with each of the at least two rotational ESA panels and the actuator. The controller <NUM> functions to control the radar operation of each ESA panel as well as the rotation of each ESA panel.

According to the invention, the system for mechanically positioning an electronically scanned array panel <NUM> further includes a tangible, non-transitory memory <NUM> configured to communicate with the controller <NUM>, the tangible, non-transitory memory <NUM> has instructions stored therein that, in response to execution by the controller, cause the controller to carry out each function of the systems herein.

Referring now to <FIG>, diagrams of a top view full panel center rotation in accordance with an embodiment of the inventive concepts disclosed herein are shown. A full panel center rotation diagram <NUM> may indicate a rotation of each of the left rotational ESA panel <NUM> and the right rotational ESA panel <NUM> about a vertical rotation axis <NUM> aligned with the longitudinal axis of the aircraft.

According to the inventive concepts disclosed herein, the controller <NUM> receives a rotation trigger for commanding the actuator <NUM> to rotate the at least two rotational ESA panels <NUM><NUM> and command the actuator <NUM> to rotate the at least two rotational ESA panels <NUM><NUM> from the first azimuthal position to the second azimuthal position without stopping in an intermediate azimuthal position. In one embodiment, the first azimuthal position and the second azimuthal position are separated by approximately <NUM> degrees.

In embodiments, the rotation trigger may be related to a plurality of factors causing a change in the boresight of the left <NUM> and right <NUM> rotational ESA panels. According to the invention, the rotation trigger is any of an altitude trigger, a mission trigger, a threat trigger including a radar warning receiver (RWR) indication, a ground proximity warning, a traffic trigger, a manual trigger via pilot interaction with the radar display, and an environmental trigger such as weather, windshear, turbulence, etc. For example, an altitude trigger may be associated with a specific altitude (e.g., below <NUM> ft AGL) of the aircraft received by the positioning system <NUM>. At low altitude, one employment operation may include a forward-looking radar where each rotational ESA panel <NUM><NUM> may be positioned to the second azimuthal position. The altitude related trigger may offer the ability to automatically position the rotational ESA panels to the desired common boresight <NUM>.

In one embodiment, the mission trigger may include a specific desired common boresight <NUM> for accomplishing a specific mission. For example, one mission may be a ground mapping radar mission where a forward common boresight <NUM> may be desirable. A terrain following mission may also provide a mission trigger to cause the controller <NUM> to command a specific common boresight <NUM>. Additionally, the controller <NUM> may receive a windshear or traffic alert and cause the controller <NUM> to take action. In one embodiment, the controller may automatically rotate and de-rotate the rotational ESA panels <NUM><NUM> based on the altitude.

In one embodiment, the common boresight may be aligned with the longitudinal axis of the aircraft to enable a forward-looking radar system for a plurality of mission related purposes (e.g., ground proximity, traffic awareness, weather awareness).

In one embodiment, the controller <NUM> may depower each of the rotational ESA panels <NUM><NUM> during the rotation. This depower action may function to create a two-position operation of either operation in the first azimuthal position or operation in the second azimuthal position without scanning an azimuth between the two. For example, the left rotational ESA panel <NUM> may function in the first azimuthal position with a boresight centered <NUM> degrees left of the aircraft nose (longitudinal axis). During rotation to the second azimuthal position the left rotational ESA panel <NUM> may be depowered during the rotation and unable to scan any azimuth during rotation. Once in the second azimuthal position, the controller <NUM> may repower the left rotational ESA panel <NUM> to scan the common boresight <NUM> aligned with the longitudinal axis.

Once the rotational ESA panels <NUM><NUM> are in the second azimuthal position, the controller <NUM> electronically couples the at least two rotational ESA panels while in the second azimuthal position to coherently operate as a single aggregate ESA <NUM> having the common boresight <NUM> and a combined ESA scan volume <NUM>. This may effectively create a larger synthetic planar array whose horizontal size is a plan back projection of the conformal structure. While the rotational ESA panels <NUM><NUM> are in the second azimuthal position, the controller <NUM> may apply similar controlling logic to the single aggregate ESA <NUM> as applied to each individual rotational ESA prior to the rotation. In this manner, a simple configuration of two rotational ESA panels <NUM><NUM> may increase function of the system for mechanically positioning an electronically scanned array panel <NUM> by shifting system complexity from a powerful computing device to a simple mechanical actuator <NUM>.

According to the invention, the controller <NUM> receives a radar signal from the single aggregate ESA panel <NUM> having the common boresight <NUM> and displays the radar signal on the radar display. Once the rotation trigger may be no longer valid, the controller <NUM> receives a de-rotation trigger to rotate the at least two rotational ESA panels <NUM><NUM> from the second azimuthal position back to the first azimuthal position and command the actuator <NUM> to rotate the at least two rotational ESA panels <NUM><NUM> from the second azimuthal position to the first azimuthal position without stopping in the intermediate azimuthal position.

Of note, the indicated scan volume <NUM> may be exemplary only wherein a typical scan volume of an ESA panel may reach <NUM> degrees either side of the boresight. Here for clarity of diagrams, a scan volume <NUM> may be displayed in the figures for illustrative purposes only.

In one embodiment of the inventive concepts disclosed herein, the controller <NUM> may be configured to command the actuator to perform a calibration of the at least two rotational ESA panels <NUM><NUM> to each of the first azimuthal position and the second azimuthal position. Here, as the controller <NUM> may precisely rotate each of the rotational ESA panels <NUM><NUM>, a calibration function embedded within the controller <NUM> may offer a system calibration for ensuring the first azimuthal position and the second azimuthal position are precisely planar.

Referring now to <FIG>, diagrams of a partial panel center rotation <NUM> exemplary of an embodiment of the inventive concepts disclosed herein are shown. In some embodiments, the system for mechanically positioning an electronically scanned array panel <NUM> may be constrained by an internal shape of an aircraft radome <NUM>. In this situation, the system for mechanically positioning an electronically scanned array panel <NUM> may not be able to rotate each full panel rotational ESA as in <FIG>. In the first azimuthal position shown in <FIG>, each of the four ESA panels is functional and radiating with the two ESA panels on the left having the left boresight <NUM> and the two ESA panels on the right having the right boresight <NUM>. Once the controller <NUM> begins the rotation, <FIG> may indicate a stationary left ESA <NUM> and a stationary right ESA <NUM> remaining in position while the rotational ESA panels <NUM><NUM> begin to rotation to the second azimuthal position.

<FIG> may indicate each of the rotational ESA panels <NUM><NUM> complete in the rotation to the second azimuthal position and radiating as the single aggregate ESA <NUM> having the common boresight <NUM> and the scan volume <NUM>.

Referring now to <FIG>, diagrams of a partial panel lateral rotation <NUM> exemplary of one embodiment of the inventive concepts disclosed herein are shown. In one embodiment of the inventive concepts disclosed herein, the system for mechanically positioning an electronically scanned array panel <NUM> may function within a radome <NUM> of smaller size yet still enabling full rotation of the partial rotational ESA panels <NUM><NUM> from the first to the second azimuthal position.

Here, a left actuator <NUM> and a right actuator <NUM> may function to rotate the left <NUM> and right <NUM> rotational ESA panels about the vertical axes <NUM> (left and right) laterally displaced from the longitudinal axis of the aircraft. In this manner, internal space required for rotation may be less than a centerline vertical axis of rotation as in <FIG> and <FIG>.

In one embodiment of the inventive concepts disclosed herein, the single aggregate ESA <NUM> may include an overlap of the individual rotational ESA panels <NUM><NUM> once the rotation is complete. The controller <NUM> may electrically determine a partial radiation pattern of one of the panels to enable accurate ESA operation. For example, the left rotational ESA panel <NUM> may partially function with the partial radiation pattern while the right rotational ESA panel <NUM> may fully radiate.

<FIG> may indicate an additional embodiment where each of the four ESA panels may rotate about a vertical axis <NUM> displaced from the longitudinal axis. Here, a left outer rotational ESA panel <NUM> and a right outer rotational ESA panel <NUM> coupled respectively with the rotational ESA panels <NUM><NUM> may further rotate the ESA panels to the second azimuthal position.

In one embodiment, the rotational ESA panels may be directed or "aimed" to align their individual boresights at a point in space. Here, a boresight focus may intersect at a single point in the distance or the boresights may be aimed at particular points of an object in the distance.

In this embodiment, the left and right outer rotational ESA panels may combine to form the single aggregate ESA <NUM> when rotated to the second azimuthal position. Although laterally displaced from the longitudinal axis, the left <NUM> and right <NUM> outer rotational ESA panels may electrically function as the single aggregate ESA panel <NUM> with an appropriate time delay/phase shift applied between the arrays.

Referring now to <FIG>, diagrams of a partial panel center translation rotation <NUM> in accordance with one embodiment of the inventive concepts disclosed herein are shown. In one embodiment of the inventive concepts disclosed herein, the system for mechanically positioning an electronically scanned array panel <NUM> may further reduce a size necessary to perform the rotation by translating as well as rotating the rotational ESA panels <NUM><NUM>. Here, the actuator <NUM> may be positioned on the longitudinal axis of the aircraft and translate a translating axis of rotation <NUM> along the longitudinal axis. While the translating axis of rotation moves aft in this scenario, the rotational ESA panels <NUM><NUM> may also translate outboard along a translation rotation direction <NUM> to the second azimuthal position.

In one embodiment, the system for mechanically positioning an electronically scanned array panel <NUM> may employ a variety of mechanical subsystems to cause the rotational ESA panels <NUM><NUM> to translate as well as rotate. For example, an actuator <NUM> including a precision jackscrew may cause the translating axis of rotation <NUM> to translate along the longitudinal axis.

Referring now to <FIG>, diagrams of an exemplary full panel lateral rotation in accordance with one embodiment of the inventive concepts disclosed herein are shown. In one embodiment, the vertical axis of rotation <NUM> may be aligned with the longitudinal axis of the aircraft (e.g., <FIG>), proximally offset from the longitudinal axis of the aircraft (e.g., <FIG>), and distally offset from the longitudinal axis (e.g., <FIG>).

Here, the vertical axis of rotation <NUM> may be laterally displaced at an outboard edge of the rotational ESA panels <NUM><NUM>. The full panel lateral rotation <NUM> may maintain a significant inside overlap once the rotational ESA panels <NUM><NUM> are rotated to the second azimuthal position. In this embodiment, the single aggregate ESA panel <NUM> may comprise a partial left radiating ESA <NUM> and a full right radiating ESA <NUM>.

Referring now to <FIG>, diagrams of a right-side view <NUM> associated with one embodiment of the inventive concepts disclosed herein are shown. The right-side view <NUM> may indicate an additional embodiment wherein the system for mechanically positioning an electronically scanned array panel <NUM> may further rotate the rotational ESA panels <NUM><NUM> in elevation about a horizontal axis of rotation <NUM> in a horizontal rotation direction <NUM>. Here, <FIG> may indicate the right panel <NUM> prior to the rotation about the vertical axis. <FIG> may indicate the single aggregate ESA <NUM> after the rotation about the vertical axis is complete, and <FIG> may detail the elevational rotation about the horizontal rotation axis <NUM>.

Once the controller <NUM> commands the single aggregate ESA <NUM> to the second azimuthal position the controller <NUM> may further rotate the single aggregate ESA <NUM> about the horizontal rotation axis <NUM>. Once complete, the single aggregate ESA <NUM> may function with a common boresight <NUM> angularly displaced from the longitudinal axis. As above, during rotation in both azimuth and elevation, the controller <NUM> may depower each rotational ESA panel <NUM><NUM> and repower each once in the desired position.

In some embodiments, the system <NUM> may identify or "tune" the distance between a wall of the radome <NUM> and the ESA panel to attempt to compensate for radome imperfections and compensation. In this manner, the controller <NUM> may determine each signature of the radome <NUM> to which it is installed and compensate for various abnormalities within the radome <NUM> structure. For example, each radome <NUM> may include a frame structure, a lighting mitigation structure, and possible fasteners of variable composition (e.g., metallic, ferrous, reflective) through which radar energy may deviate from a perfect boresight. The controller <NUM> may compensate for these imperfections in processing the reflected radar energy within a specific azimuth of these imperfections.

Referring now to <FIG>, diagrams of a multi-panel rotation diagram <NUM> exemplary of one embodiment of the inventive concepts disclosed herein are shown. In one embodiment of the inventive concepts disclosed herein, the system for mechanically positioning an electronically scanned array panel <NUM> may include a six-panel rotational ESA configuration wherein the controller <NUM> may command a plurality of second azimuthal positions to enable a desired common boresight <NUM>.

<FIG> may indicate the six panel ESA array in a first configuration capable of a three boresight <NUM><NUM><NUM> operation. In an additional configuration, <FIG> may indicate an additional azimuthal position of each of the six ESA panels offering the controller <NUM> an optional beam boresight where a left ESA second boresight <NUM> and a right ESA second boresight <NUM> may provide additional function.

In some embodiments, the ESA panels may be fitted within the radome <NUM> in a onetime fit of a "conformal" ESA and optimized conformal aperture size within an arbitrary radome. The subpanels may be coherently combined through time deal compensation to effectively create a conformal ESA. In other embodiments, the rotational ESA panels may be equal or unequal in size as indicated in the previous figures. In each configuration, simultaneous independent beams are possible across all the subpanels.

<FIG> may indicate a folded configuration offering a chevron configuration while <FIG> may indicate each ESA panel operational and radiating in an extended chevron configuration.

In some embodiments, the plurality of rotational ESA may provide a maximum reuse with a standard ESA panel assembly that can be used and reconfigured to be compatible a host of radomes as well as additional applications (e.g., ground vehicles, watercraft, etc.) The reconfiguration may be either a onetime installation or mission dependent dynamic as described above.

In some embodiments, the mechanical rotation may be asymmetric as the application may demand. Although <FIG> may indicate a symmetric rotation, it is contemplated herein an asymmetric rotation (e.g., a left side rotation only) may fall well within the scope of the inventive concepts disclosed herein.

In embodiments, the mechanical rotation may be not at a <NUM>% duty cycle, unlike existing electromechanically scanned systems, so compared with a traditional continuously scanning radar, embodiments of the inventive concepts disclosed herein may consume less DC power and maintain an increase in reliability.

In some embodiments, the separate sub-panels shown in the drawings may be made time/phase coherent to operate as a composite conformal aperture if the appropriate time delays are incorporated between the subpanels. Subpanels may function having an independently steered beam, may be a coherent conformal array, as well as toggle back and forth between these modes.

Referring now to <FIG>, a diagram of a method flow <NUM> exemplary of one embodiment of the inventive concepts disclosed herein is shown. The method flow <NUM> may include, at a step <NUM>, receiving a rotation trigger for commanding an actuator to rotate at least two rotational ESA panels onboard an aircraft, and, at a step <NUM>, commanding an actuator to mechanically rotate the at least two rotational ESA panels about a vertical axis from a first azimuthal position to a second azimuthal position.

The method may include, at a step <NUM>, electronically coupling the at least two rotational ESA panels while in the second azimuthal position to function as a single aggregate ESA having a common boresight. The method may further include, at a step <NUM>, receiving a radar signal from the single aggregate ESA having the common boresight and, at a step <NUM>, displaying the radar signal on a radar display onboard the aircraft.

As will be appreciated from the above description, embodiments of the inventive concepts disclosed herein may provide a novel solution to simply mechanically rotating a portion or an entirety of two or more ESA panels and electrically combining the rotated ESA panels to form a single aggregate ESA.

Claim 1:
An aircraft system for mechanically positioning an electronically scanned array, ESA, panel, comprising:
at least two rotational ESA panels (<NUM>, <NUM>) provided, in use, onboard the aircraft, the at least two rotational ESA panels configured for a rotation, the rotation at least about a vertical axis (<NUM>);
each of the at least two rotational ESA panels individually operational in a first azimuthal position having a first boresight (<NUM>, <NUM>) and collectively operational in a second azimuthal position having a common boresight (<NUM>), the second azimuthal position of each of the at least two rotational ESA panels being equal, the first azimuthal position distant from the second azimuthal position by the rotation;
an actuator (<NUM>) coupled with each of the at least two rotational ESA panels, the actuator configured to mechanically cause the rotation;
a radar display (<NUM>) available to one of a pilot and an autopilot of the aircraft, in use;
a controller (<NUM>) operatively coupled with each of the at least two rotational ESA panels and the actuator;
a tangible, non-transitory memory (<NUM>) configured to communicate with the controller, the tangible, non-transitory memory having instructions stored therein that, in response to execution by the controller, cause the controller to:
receive a rotation trigger for commanding the actuator to rotate the at least two rotational ESA panels, the rotation trigger being one of an altitude trigger, a mission trigger and a threat trigger;
command the actuator to rotate the at least two rotational ESA panels from the first azimuthal position to the second azimuthal position without stopping in an intermediate azimuthal position;
electronically couple the at least two rotational ESA panels while in the second azimuthal position to coherently operate as a single aggregate ESA having the common boresight;
receive a radar signal from the single aggregate ESA having the common boresight;
display the radar signal on the radar display (<NUM>);
receive a de-rotation trigger to rotate the at least two rotational ESA panels from the second azimuthal position to the first azimuthal position; and
command the actuator to de-rotate the at least two rotational ESA panels from the second azimuthal position to the first azimuthal position.