US20010006374A1 - Antenna arrangement and method for side-lobe suppression - Google Patents
Antenna arrangement and method for side-lobe suppression Download PDFInfo
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- US20010006374A1 US20010006374A1 US09/738,288 US73828800A US2001006374A1 US 20010006374 A1 US20010006374 A1 US 20010006374A1 US 73828800 A US73828800 A US 73828800A US 2001006374 A1 US2001006374 A1 US 2001006374A1
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- H—ELECTRICITY
- H01—ELECTRIC ELEMENTS
- H01Q—ANTENNAS, i.e. RADIO AERIALS
- H01Q21/00—Antenna arrays or systems
- H01Q21/06—Arrays of individually energised antenna units similarly polarised and spaced apart
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- H—ELECTRICITY
- H01—ELECTRIC ELEMENTS
- H01Q—ANTENNAS, i.e. RADIO AERIALS
- H01Q3/00—Arrangements for changing or varying the orientation or the shape of the directional pattern of the waves radiated from an antenna or antenna system
- H01Q3/26—Arrangements for changing or varying the orientation or the shape of the directional pattern of the waves radiated from an antenna or antenna system varying the relative phase or relative amplitude of energisation between two or more active radiating elements; varying the distribution of energy across a radiating aperture
- H01Q3/2605—Array of radiating elements provided with a feedback control over the element weights, e.g. adaptive arrays
Definitions
- the invention relates generally to phased antenna arrays and more particularly to side-lobe suppression systems as applied to phased antenna arrays.
- Antenna arrays consist of an arrangement of closely spaced antenna elements uniformly spread over the antenna area or aperture.
- the beam pattern for phased array antennas includes a principal or main lobe used for detecting a target and several side-lobes of reduced radiation energy grouped around the principal lobe.
- the direction and shape of the beam is controlled by altering the phase and amplitude of the individual elements.
- a problem with airborne antenna systems is that side-lobes directed towards the ground pick up ground clutter, which can interfere with echoes detected by the principal lobe and severely reduce the radar's ability to detect weak target echoes.
- side-lobe clutter is mitigated by reducing the side-lobe radiation power by amplitude weighting of the aperture. Amplitude weighting works well on reception, introducing only a limited and acceptable power loss.
- amplitude weighting on transmission involves an unacceptably high power loss, typically of around 5 to 6 dB.
- an antenna system having an array of antenna elements and phase control circuitry for setting the phase of signals that may be fed to and received by each element.
- the phase control circuitry includes a phase correction arrangement for correcting the phase of each element as a function of the position of the element within the array.
- the phase correction is proportional to a first function of the angular position of the element and proportional to a second function of the radial position of the element relative to a central point in the array.
- the first function is a sinusoid of angular position of the element and the second function is an odd polynomial of the radial position of the element having at least one term of third order or above.
- the phase correction arrangement may comprise several modules, wherein each module is associated with a single or more than one element.
- the invention also relates to a method for suppressing side-lobes.
- phase correction As a simple function of the position of each element expressed in radial and angular position, the implementation is rendered very simple; in particular, the phase correction may be calculated element by element. Furthermore, changes in the orientation of the antenna, such as during aircraft roll, for example, may be compensated for simply by a shift in the origin of the angular term of the function for each element in the array.
- the resulting beam pattern includes low side-lobes in the lower hemisphere and gives rise to only limited and acceptable power loss on transmission.
- FIG. 1 schematically depicts a simplified block diagram of an active electrically steered antenna
- FIG. 2 is a flow diagram illustrating the steps for obtaining an optimised phase function for the desired beam pattern
- FIG. 3 shows a contour plot of the two-dimensional beam pattern in the u, v plane obtained using a phase function expressed by the polynomial ⁇ r 7 ⁇ , and
- the electrically steered antenna array depicted in FIG. 1 includes an array of radiating elements 10 , 10 ′, two of which are shown in the figure. These elements 10 , 10 ′ are arranged in a grid to form the antenna area or aperture.
- the array is preferably planar, with each element being separated by a distance of less than a half wavelength from adjacent elements.
- the antenna is for an airborne radar system with the antenna aperture situated in the nose of the aircraft.
- the antenna array is preferably essentially circular in shape.
- Each element 10 , 10 ′ of the array is connected to a transmit/receive module 11 , 11 ′ that controls the phase and amplitude of the RF signals fed to the radiating elements 10 , 10 ′.
- a common RF feed network 12 is coupled to all transmit/receive modules 11 , 11 ′ for splitting and summing, RF signals on transmit and receive, respectively, to and from the radiating elements 10 , 10 ′.
- the RF feed network 12 is connected to an upstream antenna RF signal input/output (not shown).
- the transmit/receive modules 11 , 11 ′ each include a phase shifter 111 , 111 ′ and an amplitude modulator 112 , 112 ′ for controlling the phase and amplitude of RF signals fed to the associated radiating element 10 , 10 ′.
- the phase shifter 111 , 111 ′ and amplitude modulator 112 , 112 ′ are controlled by an amplitude and phase setting unit 113 , 113 ′.
- the amplitude and phase setting unit 113 , 113 ′ will be described in more detail below.
- the RF signals to and from the radiating element 10 , 10 ′ are then split into a transmit and a receive path with a switch 114 , 114 ′.
- the transmit path includes an amplifier 115 , 115 ′, preferably a power amplifier, which amplifies the outgoing RF signals before sending these to the radiating element 10 , 10 ′.
- An amplifier 116 , 116 ′ is likewise arranged in the receive path for amplifying received signals.
- the two paths are connected to the radiating element 10 , 10 ′ via a further switch 117 , 117 ′, which is preferably a circulator.
- the amplitude and phase setting units 113 , 113 ′ of all modules 11 , 11 ′ are connected via a data bus 13 to a beam steering computer (BSC) 14 , which is coupled to a system control (not shown).
- BSC beam steering computer
- the BSC 14 controls the direction and shape of the antenna beam by setting the amplitude and phase of each radiating element 10 , 10 ′ individually.
- the antenna beam side-lobes directed towards ground will pick up spurious echoes, which can interfere with the echoes from a target, a effect that is termed side-lobe clutter.
- this problem is mitigated by amplitude tapering of the antenna array to reduce the side-lobes.
- amplitude weighting on transmission results in loss in effective radiated power.
- this problem is alleviated by phase-only tapering of the antenna array. Specifically, the phase across the antenna aperture is controlled to reduce the side-lobes that are directed towards ground.
- the lower hemisphere is defined as the hemisphere that is closest to ground when the aircraft is in a normal horizontal flight position.
- the area of the beam pattern requiring side-lobe suppression must be adjusted accordingly, as will be described further below.
- an expression for the phase function has been determined to correct the phase applied to each radiating element 10 , 10 ′ and so substantially reduce side-lobe energy in the lower hemisphere.
- the coefficients of the phase function are adjusted until the beam pattern obtained with the phase function matches a desired beam pattern.
- a Taylor diagram with a specified side-lobe level is utilised as a desired beam pattern, however, those skilled in the art will appreciate that some other appropriate model could be used.
- the optimization of the phase function may be performed in any known manner. A preferred manner is to minimize the error between the beam pattern obtained using the phase function and the desired beam pattern in a least squares sense using an appropriate algorithm.
- this set of directions corresponds to the lower hemisphere from which clutter returns are most likely.
- an asymmetric beam pattern suitable for suppressing side lobes in the lower hemisphere can be expressed in terms of the position of an element 10 , 10 ′ within the array.
- the element position is expressed in polar co-ordinates r, ⁇ , where r is the radial distance from a central point in the array and ⁇ is the angular deviation from an arbitrarily chosen reference direction, for example along the horizontal plane.
- phase function ⁇ of any one element 10 , 10 ′ within the array is proportional to the sinusoid of the angular position ⁇ of the element and also proportional to an odd polynomial of the radial position r of at least third order.
- the required phase correction for each element in terms of its angular and radial position in the antenna array is obtained by adjusting the value of the coefficients, a 2k+ 1 , and thus the order of the odd polynomial to obtain the desired beam pattern.
- the process is essentially one of optimisation, wherein final beam pattern may have to be a compromise between the complexity of the expression and the performance.
- step 201 The steps for obtaining a desired beam pattern utilising the expression in (1) are illustrated in the flow diagram given in FIG. 2.
- the process starts in step 201 with the selection of an appropriate template diagram for the area of side-lobe suppression, i.e. the lower hemisphere. As mentioned above, this may be a Taylor diagram with a specified side-lobe level in the lower hemisphere.
- step 202 the polynomial structure and order is set, i.e. the non-zero coefficients a 2k+ 1 are selected.
- a polynomial comprising a single term will suffice for obtaining the desired practical side-lobe levels. Any possible additional constraints will then also be incorporated in step 203 .
- step 204 the mean square error between the template and the resulting diagram in the lower hemisphere is minimised. Any numerical search algorithm may be used for this step.
- the minimisation involves a two-dimensional Fourier transformation step, since no analytical expression for the Fourier transform is available.
- the process is terminated in step 205 when the mean square error is less than a prescribed level and the coefficients are obtained.
- Table 1 illustrates simulated beam patterns obtained utilising the phase function defined in (2) with different orders and structures of polynomial.
- the polynomial coefficients were determined by optimising the beam pattern with a desired beam pattern in the lower hemisphere.
- the optimisation process was performed using the built-in least squares function “leastsq” in MATLAB, however it will be understood that any suitable optimisation process may be employed to determine the coefficients for a desired beam pattern.
- the magnitude of the first side-lobe i.e. the peak amplitude
- the mean side-lobe level is proportional to the total clutter power received, and is therefore a more appropriate measure of performance level than the peak side-lobe level.
- FIG. 3 shows a contour plot of the two-dimensional beam pattern in the u, v plane obtained using the ⁇ r 7 ⁇ phase function.
- the value of the coefficient a 7 used in this phase function was ⁇ 1.5326 ⁇ 10 4 .
- the side-lobe reduction in the lower hemisphere is clearly visible.
- phase tapering resulted in a small pointing error when compared to the nominal beam pattern without tapering.
- This directional deviation can be compensated for in the beam control implemented by the beam steering computer 14 (FIG. 1).
- phase and amplitude setting units 113 , 113 ′ in each transmit/receive module 11 , 11 ′ set the phase of the RF signals fed to the radiating elements 10 , 10 ′.
- the optimum phase function i.e. the optimum coefficient values, for any given antenna utilised for any given application with required side-lobe suppression is determined on fabrication as described with reference to FIG. 2 and programmed into the antenna system.
- the coefficient values are then utilised to correct the phase applied to the associated radiating element 10 , 10 ′ via the associated phase shifter 111 , 111 ′ as a function of the element's 10 , 10 ′ position.
- phase correction to be applied to each element 10 , 10 ′ may be accomplished centrally by the beam steering computer BSC 14 and the individual control signals distributed to the respective setting unit 113 , 113 ′ through the data bus 13 .
- the coefficient values determined on manufacture would preferably be programmed in suitable storage circuitry easily accessible by a processor in the BSC 14 .
- the control signals could then usefully combine the individual phase correction required to suppress side-lobes in a specified area of the beam pattern as well as the phase adjustment for steering the antenna beam.
- the setting units 113 , 113 ′ need include only storage means for holding the correct value of phase for each radiating element 10 , 10 ′.
- each setting unit may be essentially constituted by a memory or alternatively a particular location in a central memory, which is programmed with the desired phase values through the data bus 13 by the BSC 14 .
- the calculated phase correction would also take account of the roll angle of the aircraft. As discussed above, this is achieved by adjusting the angular term in the phase function by the angular shift in the aircraft orientation.
- the units 113 , 113 ′ are designed as intelligent units and incorporate processing means such as a microprocessor or the like to calculate the phase correction required to suppress side-lobes in a desired portion of the beam pattern.
- the setting units 113 , 113 ′ would then incorporate, or have access to, storage circuitry holding the coefficient values of the antenna specific phase function programmed prior to deployment.
- Each unit 113 , 113 ′ would naturally also contain or have access to the positional data defining the associated element 10 , 10 ′ to permit the element specific phase to be calculated.
- each unit is additionally provided with an input indicating the roll of the aircraft i.e.
- the setting units 113 , 113 ′ are associated with individual elements 10 , 10 ′. It will be understood, however, that a single setting unit 113 , 113 ′ could control the phase and possibly also the amplitude of signals fed to and received by more than one element 10 , 10 ′.
- phase function developed according to the present invention which expresses a phase correction for suppressing side-lobes in terms of the position of the radiating elements in polar co-ordinates
- this phase function may be applied equally well to other antenna aperture shapes, but best results are obtained with shapes that resemble the circular shape, such as an elliptical or polygonal aperture.
- the invention has been described in connection with an air-to-ground aircraft radar system, it will be understood that the phase function according to the present invention is equally well suited to antenna arrangements for communication between aircraft.
- the invention is not limited to airborne applications, but may be utilised for any application requiring suppression of side-lobes in a desired hemisphere, such as for example antenna installations for mobile communications.
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Abstract
In an antenna system having an array of antenna elements (10, 10′) and circuitry (111, 14) for controlling the phase of each element an arrangement (113) is provided for correcting the phase setting of each element as a function of the position of each element within the array expressed in polar co-ordinates. The phase correction is proportional to the sinusoid of the angular position of the element and proportional to an odd polynomial of radius having at least one term of third order or above. The resulting beam pattern includes low side-lobes in the lower hemisphere and gives rise to only limited and acceptable power loss on transmission. Furthermore, the implementation is rendered very simple, as the phase correction may be calculated element by element.
Description
- The invention relates generally to phased antenna arrays and more particularly to side-lobe suppression systems as applied to phased antenna arrays.
- Antenna arrays consist of an arrangement of closely spaced antenna elements uniformly spread over the antenna area or aperture. The beam pattern for phased array antennas includes a principal or main lobe used for detecting a target and several side-lobes of reduced radiation energy grouped around the principal lobe. The direction and shape of the beam is controlled by altering the phase and amplitude of the individual elements. A problem with airborne antenna systems is that side-lobes directed towards the ground pick up ground clutter, which can interfere with echoes detected by the principal lobe and severely reduce the radar's ability to detect weak target echoes. Conventionally, side-lobe clutter is mitigated by reducing the side-lobe radiation power by amplitude weighting of the aperture. Amplitude weighting works well on reception, introducing only a limited and acceptable power loss. However, in a system employing an active phased array, amplitude weighting on transmission involves an unacceptably high power loss, typically of around 5 to 6 dB.
- An alternative technique to amplitude weighting is described in U.S. Pat. No. 4,939,523. This involves weighting or tapering the phase of the antenna elements only. The resulting beam has a sharply focussed main lobe and an asymmetric arrangement of side-lobes, with the side-lobes in the lower hemisphere of the antenna, that is the side-lobes directed towards the ground, being low. However, the implementation suggested in this reference is very complex. The phase distribution across the antenna aperture is obtained using an inverse Fourier transform, and the phase variation across the aperture must be recalculated, or table-interpolated, during the roll of the aircraft to maintain low side-lobes towards ground.
- There is thus a need for an antenna implementation which minimises side-lobe clutter with acceptable power-loss on transmission, which also performs well on reception and which is simple to implement.
- According to the invention, an antenna system is proposed having an array of antenna elements and phase control circuitry for setting the phase of signals that may be fed to and received by each element. The phase control circuitry includes a phase correction arrangement for correcting the phase of each element as a function of the position of the element within the array. Preferably the phase correction is proportional to a first function of the angular position of the element and proportional to a second function of the radial position of the element relative to a central point in the array. The first function is a sinusoid of angular position of the element and the second function is an odd polynomial of the radial position of the element having at least one term of third order or above. The phase correction arrangement may comprise several modules, wherein each module is associated with a single or more than one element. The invention also relates to a method for suppressing side-lobes.
- By providing the phase correction as a simple function of the position of each element expressed in radial and angular position, the implementation is rendered very simple; in particular, the phase correction may be calculated element by element. Furthermore, changes in the orientation of the antenna, such as during aircraft roll, for example, may be compensated for simply by a shift in the origin of the angular term of the function for each element in the array. The resulting beam pattern includes low side-lobes in the lower hemisphere and gives rise to only limited and acceptable power loss on transmission.
- Further objects and advantages of the present invention will become apparent from the following description of the preferred embodiments that are given by way of example with reference to the accompanying drawings. In the figures:
- FIG. 1 schematically depicts a simplified block diagram of an active electrically steered antenna,
- FIG. 2 is a flow diagram illustrating the steps for obtaining an optimised phase function for the desired beam pattern,
- FIG. 3 shows a contour plot of the two-dimensional beam pattern in the u, v plane obtained using a phase function expressed by the polynomial {r7}, and
- FIG. 4 shows a slice of a phase function in the x, y plane through x= 0 using the {r7} phase function.
- The electrically steered antenna array depicted in FIG. 1 includes an array of
radiating elements elements - Each
element module radiating elements RF feed network 12 is coupled to all transmit/receivemodules radiating elements RF feed network 12 is connected to an upstream antenna RF signal input/output (not shown). The transmit/receivemodules phase shifter amplitude modulator radiating element phase shifter amplitude modulator phase setting unit phase setting unit radiating element switch amplifier radiating element amplifier radiating element further switch - The amplitude and
phase setting units modules data bus 13 to a beam steering computer (BSC) 14, which is coupled to a system control (not shown). TheBSC 14 controls the direction and shape of the antenna beam by setting the amplitude and phase of eachradiating element - When mounted in an aircraft, the antenna beam side-lobes directed towards ground will pick up spurious echoes, which can interfere with the echoes from a target, a effect that is termed side-lobe clutter. Conventionally, this problem is mitigated by amplitude tapering of the antenna array to reduce the side-lobes. However, in an active phased array antenna, amplitude weighting on transmission results in loss in effective radiated power. In accordance with the invention, this problem is alleviated by phase-only tapering of the antenna array. Specifically, the phase across the antenna aperture is controlled to reduce the side-lobes that are directed towards ground. Viewed in relation to the radiation pattern in the u,v plane, u and v being the directional cosines, this means that those side-lobes located in the lower hemisphere are reduced. In an aircraft, the lower hemisphere is defined as the hemisphere that is closest to ground when the aircraft is in a normal horizontal flight position. Naturally, when the aircraft rolls, the area of the beam pattern requiring side-lobe suppression must be adjusted accordingly, as will be described further below.
- In accordance with the present invention, an expression for the phase function has been determined to correct the phase applied to each
radiating element - In accordance with the present invention, it has been determined that an asymmetric beam pattern suitable for suppressing side lobes in the lower hemisphere can be expressed in terms of the position of an
element - where a2k+ 1 is a coefficient. According to this expression the phase function φ of any one
element - Utilising the relationship defined in (1) the required phase correction for each element in terms of its angular and radial position in the antenna array is obtained by adjusting the value of the coefficients, a2k+ 1, and thus the order of the odd polynomial to obtain the desired beam pattern. The process is essentially one of optimisation, wherein final beam pattern may have to be a compromise between the complexity of the expression and the performance.
- The steps for obtaining a desired beam pattern utilising the expression in (1) are illustrated in the flow diagram given in FIG. 2. The process starts in
step 201 with the selection of an appropriate template diagram for the area of side-lobe suppression, i.e. the lower hemisphere. As mentioned above, this may be a Taylor diagram with a specified side-lobe level in the lower hemisphere. In thefollowing step 202 the polynomial structure and order is set, i.e. the non-zero coefficients a2k+ 1 are selected. As will be shown below, in general a polynomial comprising a single term will suffice for obtaining the desired practical side-lobe levels. Any possible additional constraints will then also be incorporated instep 203. These may include specifying the gain in the main-lobe direction and specifying the maximum peak or mean side-lobe level. Instep 204 the mean square error between the template and the resulting diagram in the lower hemisphere is minimised. Any numerical search algorithm may be used for this step. The minimisation involves a two-dimensional Fourier transformation step, since no analytical expression for the Fourier transform is available. The process is terminated instep 205 when the mean square error is less than a prescribed level and the coefficients are obtained. - By virtue of the separate term defining the relationship to angular position, α, in the phase function of equation (1), it is very simple to adjust the phase correction for different roll angles of the aircraft. Specifically, this is achieved by shifting the angle α by an amount equal to the roll angle of the aircraft prior to calculating the sinusoidal term sin(α). In this way the resulting beam pattern can easily be adjusted to have low side-lobes in the lower hemisphere, that is the hemisphere directed towards ground.
- Table 1 below illustrates simulated beam patterns obtained utilising the phase function defined in (2) with different orders and structures of polynomial. In each case the polynomial coefficients were determined by optimising the beam pattern with a desired beam pattern in the lower hemisphere. In the present example the optimisation process was performed using the built-in least squares function “leastsq” in MATLAB, however it will be understood that any suitable optimisation process may be employed to determine the coefficients for a desired beam pattern. For each phase function the magnitude of the first side-lobe, i.e. the peak amplitude, is given in a slice through the u, v plane defined by u= 0. A further quantity listed is the mean side-lobe level through the same slice where u= 0. This is calculated as the two-dimensional mean of the antenna gain in the side-lobe area of the lower hemisphere. Finally, the table also gives the damping of gain. The mean side-lobe level is proportional to the total clutter power received, and is therefore a more appropriate measure of performance level than the peak side-lobe level.
- In Table 1, the notation {ri, ri} is short for the expression sinα (airi+ ajrj).
TABLE 1 Peak side-lobe level, mean side- Peak side-lobe level, lobe level, damping mean side-lobe level, Polynomial (dB) Polynomial damping (dB) {r3} −28.3, −46.3, 0.26 {r5, r7} −33.5, −47.8, 0.88 {r3, r5} −33.3, −46.9, 0.98 {r5, r9} −33.7, −48.0, 0.92 {r3, r5, r7} −36.5, −49.6, 0.95 {r5, r11} −34.9, −48.3, 0.96 {r3, r5, r7, −38.7, −49.9, 1.48 {r7} −33.9, −48.1, 1.10 r9} {r3, r5, r7, −41.2, −51.2, 1.09 {r7, r9} −32.6, −47.6, 0.94 r9, r11 } {r3, r7} −34.9, −47.8, 0.85 {r7, r11} −32.6, −47.6, 0.97 {r3, r9} −37.9, −48.4, 0.93 {r9} −32.1, −49.0, 1.27 {r3, r11} −39.5, −49.2, 0.95 {r9, r11} −31.8, −46.9, 0.99 {r5} −32.4, −47.5, 0.77 {r11} −27.8, −49.6, 1.49 - It is expected that beam pattern will improve in terms of peak and mean side-lobe level and damping of the gain with an increasing numbers of terms a2k+ 1 r2k+1 in the polynomial expression. However, it is apparent from the values of mean side-lobe level given in Table 1 that the improvement when using a large number of terms as opposed to one or two terms is not very significant. A very reasonable result can be obtained when using two terms, for example the expression {r3, r11} or even only one term, for example the expression {r7}.
- Indeed in some cases, the simple cubic relationship between phase and radial position given by the expression {r3} may provide adequate side-lobe suppression. It will be understood that the fewer the number of terms contained in the polynomial expression, the easier the implementation will be.
- FIG. 3 shows a contour plot of the two-dimensional beam pattern in the u, v plane obtained using the {r7} phase function. The value of the coefficient a7 used in this phase function was −1.5326×104. The side-lobe reduction in the lower hemisphere is clearly visible. FIG. 4 shows a slice of the phase function in the x, y plane through x= 0.
- In all the cases tabulated above, phase tapering resulted in a small pointing error when compared to the nominal beam pattern without tapering. This directional deviation can be compensated for in the beam control implemented by the beam steering computer14 (FIG. 1).
- Returning again to FIG. 1, the phase and
amplitude setting units module elements element phase shifter element steering computer BSC 14 and the individual control signals distributed to therespective setting unit data bus 13. In this case the coefficient values determined on manufacture would preferably be programmed in suitable storage circuitry easily accessible by a processor in theBSC 14. The control signals could then usefully combine the individual phase correction required to suppress side-lobes in a specified area of the beam pattern as well as the phase adjustment for steering the antenna beam. In such an arrangement wherein the phase correction of allantenna elements units element data bus 13 by theBSC 14. The calculated phase correction would also take account of the roll angle of the aircraft. As discussed above, this is achieved by adjusting the angular term in the phase function by the angular shift in the aircraft orientation. - In an alternative embodiment, the
units units unit element setting unit units BSC 14 through thebus 13, together with any phase adjustment parameters required for altering the beam direction and any parameters relative to the beam width, all of which are common to allelements units individual elements single setting unit element - While the phase function developed according to the present invention, which expresses a phase correction for suppressing side-lobes in terms of the position of the radiating elements in polar co-ordinates, has been discussed and implemented for circular antenna arrays, those skilled in the art will recognise that this phase function may be applied equally well to other antenna aperture shapes, but best results are obtained with shapes that resemble the circular shape, such as an elliptical or polygonal aperture. Furthermore, while the invention has been described in connection with an air-to-ground aircraft radar system, it will be understood that the phase function according to the present invention is equally well suited to antenna arrangements for communication between aircraft. Moreover, the invention is not limited to airborne applications, but may be utilised for any application requiring suppression of side-lobes in a desired hemisphere, such as for example antenna installations for mobile communications.
Claims (17)
1. Antenna system including an array of antenna elements (10) and phase control circuitry (111, 113, 14) for setting the phase of signals that may be fed to and/or received by each element (10), characterised in that said control circuitry includes a phase correction arrangement (113) for correcting the phase setting of each element (10) as a function of the position of each element within the array to generate an asymmetric side-lobe pattern, wherein side-lobes on at least one side of a principal lobe are substantially suppressed.
2. Antenna system as claimed in , characterised in that said phase correction arrangement (113) corrects the phase setting of each element (10) in a manner proportional to a first function of the angular position of the element and proportional to a second function of the radial position of the element relative to a central point in the array.
claim 1
3. Antenna system including an array of antenna elements (10) including phase control circuitry (111, 113, 14) for setting the phase of signals that may be fed to and/or received by each element (10), characterised in that said control circuitry includes a phase correction arrangement (113) for correcting the phase setting of each the elements (10) as a function of the position of each element expressed in polar co-ordinates to substantially suppress side-lobes on at least one side of a principal lobe, wherein for each element said corrected phase setting is proportional to a sinusoid of the angular position of said element within the array.
4. Antenna system as claimed in , further characterised in that the corrected phase setting for each element is proportional to an odd polynomial of the radial position of said element, wherein said polynomial has at least one term of third order or above.
claim 3
5. Antenna system as claimed in or , further characterised in that said control circuitry (14, 113) is adapted to adjust the relationship between phase setting and angular position of an element (10) as a function of the orientation of the antenna array.
claim 3
4
6. Antenna system as claimed in any previous claim, characterised in that said phase correction arrangement comprises several modules (113), each module being associated with at least one element (10, 11) in the array.
7. Antenna system as claimed in any previous claim, characterised in that said array is substantially circular.
8. Antenna system including an array of antenna elements (10), phase control circuitry (11, 113, 14) for setting the phase of signals that may be fed to and/or received by each element, characterised in that said control circuitry includes a phase correction arrangement (113) for correcting the phase setting of each element as a function of the angular and radial position of each element (10) relative to a central point in the array to generate an asymmetric side-lobe pattern wherein side-lobes on at least one side of a principal lobe are substantially suppressed, said function defining the corrected phase as proportional to an odd polynomial of radial position of each element, wherein said polynomial has at least one term of third order or above.
9. Antenna system as claimed in , characterised in that said function defines the corrected phase as proportional to the sinusoid of the angular position of each element.
claim 8
10. Antenna system as claimed in , further characterised in that said control circuitry (14, 113) is adapted to adjust the relationship between corrected phase setting and angular position of an element (10) as a function of the orientation of the antenna array.
claim 9
11. Antenna system as claimed in any one of to , characterised in that said phase correction arrangement includes several modules (113), each module (113) being associated with at least one element (10, 11) in the array.
claims 8
10
12. Antenna system as claimed in any one of to , characterised in that said array is substantially circular.
claims 8
11
13. A method of suppressing side-lobes on at least one side of a principal lobe in the beam pattern of an antenna arrangement having a plurality of antenna elements disposed to form an array, wherein each element is adapted to receive or radiate signals of a specific phase, the method including:
for each antenna element, adjusting the phase of the element in a manner proportional to a first function of the angular position of the element and proportional to a second function of the radial position of the element relative to a central point in the array.
14. A method as claimed in , characterised by adjusting the angular position of each element in said first function as a function of the absolute orientation of the array.
claim 13
15. A method as claimed in or , characterised in that said first function is a sinusoid.
claim 13
14
16. A method as claimed in any one of to , characterised in that said second function is an odd polynomial including at least one term of third order or above.
claims 13
15
17. A method of suppressing side-lobes on at least one side of a principal lobe in the beam pattern of an antenna arrangement having a plurality of antenna elements (10, 10′) disposed to form an array, the method including:
for each antenna element, adjusting the phase of radio frequency signals that may be fed to and received by the element according to the expression:
where α is the angular position of the element (10, 10′) within the array and r is the radial position of the element (10, 10′) within the array, a2k+1 is a coefficient and p is a variable, wherein the at least one coefficient is non-zero and determined by,
pre-selecting a template of beam pattern with a desired asymmetric side-lobe configuration, and
for a selection of variables p, minimising the mean square error between a beam pattern generated with said polynomial and said template to determine the at least one coefficient a2k+ 1.
Applications Claiming Priority (3)
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SE9904718-5 | 1999-12-22 | ||
SE9904718A SE515471C2 (en) | 1999-12-22 | 1999-12-22 | Antenna device and method for side lobe suppression |
SE9904718 | 1999-12-22 |
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US20010006374A1 true US20010006374A1 (en) | 2001-07-05 |
US6384782B2 US6384782B2 (en) | 2002-05-07 |
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US09/738,288 Expired - Lifetime US6384782B2 (en) | 1999-12-22 | 2000-12-18 | Antenna arrangement and method for side-lobe suppression |
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US (1) | US6384782B2 (en) |
EP (1) | EP1250726B1 (en) |
AU (1) | AU2416101A (en) |
IL (1) | IL150075A0 (en) |
SE (1) | SE515471C2 (en) |
WO (1) | WO2001047061A1 (en) |
ZA (1) | ZA200204159B (en) |
Cited By (6)
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US20050003864A1 (en) * | 2003-07-03 | 2005-01-06 | Elliot Robert Douglas | Antenna system |
US20060012518A1 (en) * | 2002-08-30 | 2006-01-19 | Michael Numminen | Method for enhancing the measuring accuracy in an antenna array |
US8427387B1 (en) * | 2010-09-30 | 2013-04-23 | The United States Of America As Represented By The Secretary Of The Navy | Broadband spiral transmission line phase shifting power splitter |
US9780446B1 (en) * | 2011-10-24 | 2017-10-03 | The Boeing Company | Self-healing antenna arrays |
CN110532631A (en) * | 2019-08-01 | 2019-12-03 | 西安电子科技大学 | Method is determined based on the 6G communication antenna element position tolerance of channel capacity sensitivity |
US11967766B2 (en) * | 2019-08-26 | 2024-04-23 | Bdcm A2 Llc | Antenna array with amplitude tapering and method therefor |
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US7619562B2 (en) * | 2002-09-30 | 2009-11-17 | Nanosys, Inc. | Phased array systems |
US6982670B2 (en) * | 2003-06-04 | 2006-01-03 | Farrokh Mohamadi | Phase management for beam-forming applications |
US7042388B2 (en) * | 2003-07-15 | 2006-05-09 | Farrokh Mohamadi | Beacon-on-demand radar transponder |
US8144051B2 (en) | 2008-09-05 | 2012-03-27 | Raytheon Company | Adaptive sidelobe blanking for motion compensation |
US8988279B2 (en) * | 2012-01-13 | 2015-03-24 | Raytheon Company | Antenna sidelobe reduction using phase only control |
PL3596780T3 (en) | 2017-03-13 | 2022-01-31 | Telefonaktiebolaget Lm Ericsson (Publ) | Self-calibration of antenna array system |
WO2020064128A1 (en) * | 2018-09-28 | 2020-04-02 | Telefonaktiebolaget Lm Ericsson (Publ) | Systems and methods for correction of beam direction due to self-coupling |
US11404797B2 (en) | 2020-01-02 | 2022-08-02 | International Business Machines Corporation | Time-based beam switching in phased arrays |
Family Cites Families (3)
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US4638320A (en) * | 1982-11-05 | 1987-01-20 | Hughes Aircraft Company | Direction finding interferometer |
DE3716858A1 (en) * | 1987-05-20 | 1988-12-15 | Licentia Gmbh | AIRPLANE RADAR AERIAL |
FR2663469B1 (en) * | 1990-06-19 | 1992-09-11 | Thomson Csf | DEVICE FOR SUPPLYING RADIANT ELEMENTS TO A NETWORK ANTENNA, AND ITS APPLICATION TO AN ANTENNA OF AN MLS TYPE LANDING AID SYSTEM. |
-
1999
- 1999-12-22 SE SE9904718A patent/SE515471C2/en not_active IP Right Cessation
-
2000
- 2000-12-13 EP EP00987890.1A patent/EP1250726B1/en not_active Expired - Lifetime
- 2000-12-13 WO PCT/SE2000/002513 patent/WO2001047061A1/en active Application Filing
- 2000-12-13 AU AU24161/01A patent/AU2416101A/en not_active Abandoned
- 2000-12-13 IL IL15007500A patent/IL150075A0/en active IP Right Grant
- 2000-12-18 US US09/738,288 patent/US6384782B2/en not_active Expired - Lifetime
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Cited By (7)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US20060012518A1 (en) * | 2002-08-30 | 2006-01-19 | Michael Numminen | Method for enhancing the measuring accuracy in an antenna array |
US7372402B2 (en) * | 2002-08-30 | 2008-05-13 | Telfonaktiebolaget Lm Ericsson (Publ) | Method for enhancing the measuring accuracy in an antenna array |
US20050003864A1 (en) * | 2003-07-03 | 2005-01-06 | Elliot Robert Douglas | Antenna system |
US8427387B1 (en) * | 2010-09-30 | 2013-04-23 | The United States Of America As Represented By The Secretary Of The Navy | Broadband spiral transmission line phase shifting power splitter |
US9780446B1 (en) * | 2011-10-24 | 2017-10-03 | The Boeing Company | Self-healing antenna arrays |
CN110532631A (en) * | 2019-08-01 | 2019-12-03 | 西安电子科技大学 | Method is determined based on the 6G communication antenna element position tolerance of channel capacity sensitivity |
US11967766B2 (en) * | 2019-08-26 | 2024-04-23 | Bdcm A2 Llc | Antenna array with amplitude tapering and method therefor |
Also Published As
Publication number | Publication date |
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ZA200204159B (en) | 2003-07-30 |
SE515471C2 (en) | 2001-08-13 |
AU2416101A (en) | 2001-07-03 |
SE9904718D0 (en) | 1999-12-22 |
EP1250726A1 (en) | 2002-10-23 |
EP1250726B1 (en) | 2017-06-14 |
WO2001047061A1 (en) | 2001-06-28 |
IL150075A0 (en) | 2002-12-01 |
SE9904718L (en) | 2001-06-23 |
US6384782B2 (en) | 2002-05-07 |
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