Patent Document

STATEMENT OF GOVERNMENT INTEREST 
     This invention was made with Government support under Contract N00024-03-C-6110 awarded by the Department of the Navy. The Government has certain rights in this invention. 
    
    
     BACKGROUND 
     Radar is used for detection and tracking of distant objects. In some cases it is important to know the location of a target with great accuracy, as might be the case when tracking a hostile incoming missile (a “target” in radar parlance). Under such conditions, various factors can adversely affect the radar-indicated location of the target. Among these factors are refraction of radio-frequency (RF) electromagnetic radiation by the atmosphere through which the electromagnetic signals propagate. 
     Traditional methods of determining atmospheric refraction include the use of a refractive index. This index can be determined based on the radar location and atmospheric conditions, and is usually available in a table. However, atmospheric conditions can change frequently, and up-to-date information may not always be available. Improved, real-time methods for determining atmospheric refraction are desired. Once the refraction is deemed to be known, the radar-indicated location of the target can be corrected for the refraction. 
     Improved or alternative methods are desired for determining the effects of refraction on a radar RF beam. 
     SUMMARY 
     A method according to an aspect of the disclosure is for determining radio-frequency (RF) beam refraction in the direction of a target. The method comprises the step of determining the location of a radio-frequency target. Ephemeris information relating to a star near the expected location is obtained. An optical telescope is pointed toward the star using the ephemeris data. The deviation of the star from the boresight of the optical telescope is deemed to be an indication of the optical refraction in the direction of the location. The indicated optical refraction is converted into radio-frequency refraction. 
     A method according to an aspect of the disclosure is for determining radio-frequency beam refraction in the direction of a target. The method comprises the step of pre-calibrating the pointing of an optical or infrared telescope. The expected location of a radio-frequency target is determined, and ephemeris information relating to a star near the expected target location is obtained. The optical telescope is pointed toward the star near the expected target location using the ephemeris data. The image of the star is observed in the field-of-view of the optical telescope. The deviation of the star from the boresight of the optical telescope is noted, and deemed to be an indication of the optical refraction in the direction of the expected target location. The indicated optical refraction is converted into radio-frequency refraction. The conversion may be based on predetermined conversion factors. 
     A method according to another aspect of the disclosure is for correcting for radio-frequency refraction of a radar beam. The method comprises the steps of determining the expected location of a radio-frequency target, and obtaining ephemeris information relating to a star near the expected target location. Using the ephemeris information, an optical or infrared telescope is pointed toward the star near the expected target location. The deviation of the image of the star from the boresight of the infrared telescope is noted as an indication of the infrared refraction in the direction of the expected target location. The indicated infrared refraction is converted into radio-frequency refraction, and the indicated radar-derived location of, the target is corrected by the radio-frequency refraction. 
    
    
     
       BRIEF DESCRIPTION OF THE DRAWINGS 
         FIG. 1  is a simplified scenario illustrating a ship fitted with a radar system and an infrared telescope, in the process of determining the location of a distant target in the presence of refraction; 
         FIG. 2  is a simplified diagram illustrating the system flow of the DST (Diurnal Star Tracker) used for taking the star measurements; 
         FIG. 3  is flow diagram illustrating steps according to some aspects of the disclosure; and 
         FIG. 4  is a diagram illustrating geometry and processing for determining the star angle relative to telescope line-of-sight, and some related equations. 
     
    
    
     DETAILED DESCRIPTION 
       FIG. 1  illustrates a scenario  10  in which a ship  12  at sea  14  uses an on-board radar  12 R to measure characteristics of an airborne target  16  at a range R, following a trajectory designated  17 . The electromagnetic radio-frequency (RE) radar signal is illustrated as a “lightning bolt” symbol  18 . As known, atmospheric refraction tends to bend beams of electromagnetic radiation. The amount of refraction of a beam of radio-frequency (RF) radiation, such as beam  18  of  FIG. 1 , depends upon moisture content of the atmosphere and possibly upon other factors, and is an integral function, meaning that the amount of moisture and other factors at a particular location is not determinative of the amount of refraction, but instead the refraction is dependent upon the cumulation of moisture and other factors along the entire length of path  18 . 
     As illustrated in  FIG. 1 , ship  12  is fitted with a controllable or directionally controllable infrared (IR) telescope  20 , designated Diurnal Star Tracker (DST). The DST is used inter alia for ship navigation, but the salient aspect of the DST  20  for purposes of the disclosure is the controllable infrared viewer or camera having a field of view (FOV). The camera aspect of the infrared telescope allows angle measurements to be automated, but the principles of the disclosure may be achieved with manual observations. The infrared telescope is mounted for azimuth (AZ) and elevation (EL) motion, and can be automatically pointed and maintain the pointing in the face of, or in spite of, ship motion. 
     In  FIG. 1 , the field of view (FOV) of telescope  20  is illustrated as  30  for the case in which the telescope line-of-sight axis  34  is directed toward the zenith. This is the orientation which is used to calibrate the DST telescope against systemic or systematic errors. As illustrated, a star  32  is illustrated as being found in the FOV  30  at a location spaced away from the line-of-sight intercept  31 . The spacing of the star  32  from the FOV intercept point is by an azimuth amount d 0  and an elevation amount h 0 . If the pointing of the telescope follows the commanded pointing direction, the location of a star with known ephemeredes should be at a given location in the FOV  30 . Any deviation from the expected location in the FOV can be considered to be a systemic error, which can be compensated for. 
     Also in  FIG. 1 , a field-of-view (FOV)  40  of the telescope  20  is centered about a telescope line-of-sight  41  which is directed toward the location, as established by ephemeris data, of a known star  42  which is close to the expected location of the RF target. With line-of-sight  41 , in theory the FOV  40  should image the star  42  at its center. It must be understood that the light beam will be refracted, so there is no actual “straight line” extending from DST telescope  20  to the star  42 . The curved or refracted light ray is designated  44 . The actual star  42  location in FOV  40  is spaced away from the center of the FOV by an amount which is designated h in elevation and d in azimuth. This deviation represents the optical or infrared refraction immediately adjacent the anticipated location of the RF target  16 . In  FIG. 1 , h and d are the measured vertical and horizontal errors, h 0  and d 0  are the vertical and horizontal systematic errors, Ah=h−h 0  and Ad=d−d 0  are the vertical and horizontal optical or infrared refraction, respectively. 
       FIG. 2  is a simplified diagram  200  in block and schematic form, illustrating some details of the Diurnal Star Tracker (DST)  20  of  FIG. 1 . In  FIG. 2 , the actual optical or infrared telescope is designated  220 . Telescope  220  is mounted on a controllably movable platform or director  222 , the direction of which is controlled by pointing direction control signals generated by a coordinate transformation from deck frame to line-of-sight frame (T d   LOS ) function illustrated as a block  224 . Block  224  receives composite pointing direction commands from a director control block  226 . A star tracker image processor, illustrated as a block  228 , processes the telescope image information to produce star azimuth (Az s ) and star elevation (El s ) which are the DST measurements of the reference star being measured. The processed information from block  228  is applied to a block  230  representing coordinate transformation from ENU frame to line-of-sight frame (T LOS   0 ). Block  230  produces ship attitude correction in local coordinates, which are applied to a block  232 . Block  232 , using reference attitude triad information from a block  236 , converts the ship attitude correction calibration data in local coordinates to ship attitude correction in geodetic East North Up (ENU) coordinates. The ship attitude correction in ENU coordinates is applied to block  234 , which represents the ship Inertial Navigation System (INS). The INS  234  responds to ship motion by generating latitude, longitude, Universal Time Code (UTC) time and date, which are applied by a path  235   a  to a star ephemeris program illustrated as a block  238 . INS  234  also produces ship attitude information on a path  235   b  for application to a block  242 , representing coordinate conversion from ENU frame to deck frame (T 0   d ), and ship roll, pitch and heading motion on a path  235   c  for application to a block  248 . Block  248  represents coordinate conversion from deck frame to ENU frame (T 0   d ). The star ephemeris program  238  produces Az and El, which are the reference azimuth and elevation angles, respectively, of the star to be measured. The Az and El from block  238  are applied to block  236 , as well as to block  240 . Block  240  processes the Az and El to produce a star line-of-sight (LOS) pointing vector in the ENU frame for application to block  242 . Block  242  transforms the star line-of-sight pointing vector to the ship deck frame to produce an input signal for application to a director pointing command generator block  246 . Director control block  226  receives the pointing direction commands from block  246  and ship motion stabilization signals from block  248  to generate a composite director pointing command signal for pointing the telescope in toward the selected star. The net effect of the Diurnal Star Tracker  200  of  FIG. 2  is to generate navigational signals for the ship  12  of  FIG. 1  and to stabilize the pointing of the optical telescope  220 . 
     According to an aspect of the disclosure, a stabilized, controllable infrared or other optical telescope is pointed at the coordinates of a star located near the radar target as seen from the radar system. The stabilized telescope may be associated with a diurnal star tracker, or may be independent. The deviation of the star from the boresight of the telescope is determined. In a DST arrangement such as that of  FIG. 2 , this is readily accomplished by noting the azimuth and elevation deviation of the star from the center of the field of view. This deviation is deemed to represent the optical refraction. The optical refraction is converted to radio-frequency (RF) refraction to thereby establish the RF refraction. The RE refraction is used to correct the location of the target as indicated by the radar. 
       FIG. 3 , is a simplified logic flow chart or diagram illustrating some steps according to aspects of the disclosure. In  FIG. 3 , the logic  300  starts at a START block  310 , and flows to a block  312 . Block  312  represents identification of the target in radar track, the location of which is to be corrected for refraction. This identification can be by means of its location. The logic then flows to Block  314 , which is selection of a star or stars near zenith to be used for systematic error correction. Stars are typically selected based on preferred locations and brightness. Next, the logic flows to Block  316 , where the ephemerides of the star are obtained, and the director ( 222  of  FIG. 2 ) is pointed towards the star(s). From Block  316 , the logic flows to block  318 , which represents the measurement of the star(s) relative to boresight, and processing to correct for the systematic errors. From Block  318 , the logic flows to Block  320 , which is the selection of a star visible near the target location (as seen from the radar or the telescope) for refraction correction. From Block  320 , the logic flows to Block  322 , which represents obtaining the ephemeredes for the selected star and pointing the DST director toward the selected star. From Block  322 , the logic flows to Block  324 , where the measurements of the selected star are obtained and processed for optical refraction correction. From Block  324 , the logic flows to a block  326 , which represents the conversion of optical refraction to RF refraction. This can be accomplished with the use of predetermined or precalculated optical-to-RF-refraction data. This data can be obtained by taking apparent [position] measurements of an object with a known location, such as a test aircraft, with both RF and IR sensors, at various elevation angles and target ranges. The actual location of the test aircraft can be determined by GPS onboard the test aircraft. The atmospheric refraction in each band can then be observed and the relationship derived. The results can then be stored in tables for the real-time system to access. Next, in Block  328 , the RF refraction correction is applied to the target track in terms of a position correction. Finally, the logic ends at Block  330 . 
       FIG. 4  includes a telescope or camera field of view (FOV)  40  showing the line-of-sight line  34  and the line-of-sight intercept  31  with the FOV. The location of a star  32  relative to the intercept  31  is illustrated, with its horizontal displacement d and vertical displacement h. The corresponding included angles ΔEl and ΔAz are also shown. The azimuth angular displacement is given by ΔAz=Tan −1 (d/f) and the horizontal displacement by ΔEl=Tan −1 ((h/f)cos(ΔAz)), where f is the focal length of the telescope lens. 
     A method according to an aspect of the disclosure is for determining radio-frequency (RF) antenna beam ( 18 ) refraction in the direction of a target ( 16 ). The method comprises the step ( 314 ,  316 ,  318 ) of pre-calibrating the pointing of an infrared telescope ( 20 ). The expected location of a radio-frequency (RF) target ( 16 ) is determined, and ephemeris information relating to a star ( 42 ) near the expected location is obtained ( 320 ,  322 ). The infrared telescope ( 20 ) is pointed toward the star ( 42 ) near the expected location by using the ephemeris data. The image of the star is observed in the field-of-view ( 40 ) of the infrared telescope ( 20 ). The deviation (d, h) of the star ( 42 ) from the boresight ( 34 ) of the infrared telescope ( 20 ) is noted, and deemed ( 324 ) to be an indication of the infrared refraction in the direction of the expected location of the target ( 16 ). The indicated infrared refraction is converted ( 326 ) into radio-frequency refraction. The resulting radio-frequency refraction is applied to correct the beam direction. In a particular mode of the method, the conversion of infrared refraction to RF refraction is performed with a predetermined conversion table. The predetermined conversion table may be made by the additional steps of observing a target at different angles of elevation and different ranges with both infrared and RF sensors, and tabulating the results. 
     A method according to another aspect of the disclosure is for correcting for radio-frequency (RF) refraction of a radar beam. The method comprises the steps of determining the expected location ( 332 ) of a radio-frequency target, and obtaining ephemeris information ( 320 ) relating to a star near the expected location. Using the ephemeris information, an infrared telescope ( 20 ,  220 ) is pointed ( 322 ) toward the star near the expected location. The deviation of the image of the star (d, h) from the boresight ( 31 ) of the infrared telescope ( 20 ,  220 ) is noted as an indication of the infrared refraction ( 324 ) in the direction of the expected location. The indicated infrared refraction is converted ( 326 ) into radio-frequency refraction, and the indicated radar location of the target is corrected ( 328 ) by the radio-frequency refraction. In a particular mode of the method, the telescope is corrected for systemic errors ( 324 ,  316 ,  318 ). The step of converting the infrared refraction into. RF refraction in a particular mode of the method is accomplished by predetermining optical and RF refraction of a given object at a given elevation angle and range, and tabulating the data for use.

Technology Category: 3