fig1 shows a radar system 1 according to embodiments of the invention , comprising a power source 10 , a controller 12 , and a computer 14 , the power source and computer 10 , 14 being arranged to provide power to , and operational control over , the controller 12 . the controller 12 comprises a microprocessor and a set of instructions ( not shown ) for execution thereby , effectively generating control signals that cause the rf frequency source , or signal generator 16 , to output rf energy at a specified frequency f out , and this output signal , under control of switches 18 and amplifiers 20 , drives antenna 22 ( whilst the figure shows a switch component 18 , it will be appreciated that in this particular arrangement — in which there is only one antenna 22 — the switch 18 is inessential ). as will be described in more detail below , the rf frequency source 16 generates signals within a range of frequencies , causing the antenna 22 to transmit beams in different angular directions , thereby scanning over a region beyond the radar system 1 . the radar system 1 also includes a receiving antenna 32 , which receives radiated signals reflected back from objects , and passes the received radiation through switch and amplifier components 18 ′, 20 ′ to mixer 34 . the mixer 34 comprises two inputs : a first connected to the rf source 16 ; and a second connected to the receiving antenna 32 . the output of the mixer 34 is fed to an analogue to digital converter adc 36 , to produce a digitised signal for input to the signal processor 38 , which performs analysis of the received signal . the signal processor 38 performs a spectral analysis on the received signals , because the range between the radar system and external ( reflecting ) objects is contained as frequency information in the signal . aspects of the receiving and processing components are described in detail below , but first aspects of the rf frequency source and antenna will be described . fig2 shows components of the rf frequency generator 16 according to an embodiment of the invention , which is preferably used to generate signals having a range of frequencies . referring to fig2 , the frequency generator 16 comprises a frequency source 200 , first circuit portion 210 and a second circuit portion 220 . the first circuit portion 210 comprises a frequency divider 205 , a phase comparator 209 , a filter 211 , and a voltage controlled oscillator vco 213 , while the second circuit portion 220 comprises a frequency divider 207 , static multiplier 201 and a mixer 203 . the mixer 203 receives , as input , signals output from the vco 213 and signals from the high grade , static multiplier 201 , and generates signals of frequency equal to the difference between the frequencies of the two inputs ( f 3 ). the values r 1 , r 2 characterising the frequency dividers 205 , 207 are selectable , and the phase comparator 209 is arranged to compare the frequency and phase of signals output from the frequency dividers 205 , 207 ( f 3 / r 2 and f ref ), so as to output a phase - error signal , of magnitude dependent on the difference between f 3 / r 2 and f ref . the phase - error signal is input to the vco 213 , and the first circuit portion 210 operates so as to cause the output from the vco 213 to stabilise in dependence on the phase - error signal . thus different values of r 2 can be used to force the loop to stabilise at a frequency multiple of the input signal . in one arrangement the frequency source 200 is embodied as a crystal oscillator and in another arrangement as a saw oscillator . as stated above , an objective of the design of the rf frequency generator 16 is to minimise the amount of phase noise present in the output signal f out . as will be appreciated from earlier parts of this specification , multiplication of the phase noise of the reference oscillator and phase comparator is dependent on the magnitude of r 1 and r 2 , so an objective of the rf frequency generator 16 is to minimise the amount of multiplication of the oscillator output 200 — in other words to keep the values of r 1 and r 2 as low as possible . accordingly the frequency generator 16 includes high - quality multiplier 201 and mixer 203 , the former ( 201 ) being arranged to increase the frequency of the signal output from oscillator 200 to as high a value as possible ( e . g . the lower limit of the desired output frequency of vco 213 ), while the mixer 203 serves to output signals of frequency equal to the difference between f 2 and f 1 , thereby effectively stepping down the output of the vco 213 . as a result , the magnitude of the frequency input to divider 207 is relatively low , which means that for tuning of the output of vco 213 , the value of r 2 can be far lower than that possible with conventional arrangements . the advantages of embodiments of the invention can best be seen with reference to a particular example , considering firstly how signals are processed by conventional phase - locked loop circuits and then how signals are processed by embodiments of the invention , assuming frequency source 200 outputs signals with a frequency of 100 mhz : it can be seen that by stepping up the frequency of signals input from the frequency source 200 and mixing them with the output of the vco 213 , the amount of multiplication applied by the frequency dividers 205 , 207 , and thus amplification of phase noise in the oscillator output , is correspondingly reduced compared to conventional frequency synthesisers . it is to be noted that the circuit design shown in fig2 offers a 20 - 30 db reduction in noise contribution of the phase detector compared to conventional circuits operating loop frequencies of the order 200 mhz . the signals output from the second circuit portion are then modulated by output f dds of a third circuit portion 230 , which in one arrangement comprises a direct digital synthesiser 223 , a digital to analogue converter dac 225 and a low pass filter 227 . the third circuit portion 230 is configured , under control of the controller 12 shown in fig1 , to generate a repeating pattern comprising a linear frequency ramp . the ramp has a specified duration and magnitude , values of which are programmed via the controller 12 . fig3 shows an example of one such frequency ramp 301 1 for a given carrier frequency f c1 , the duration of which is approximately 64 μs , the magnitude of which , in terms of range of frequencies ( f dds , max − f dds , min ), is approximately 20 mhz , and is followed by a flyback ramp 303 , to prepare the third circuit portion 230 for the next ramp 301 2 . the pattern repeats at a predetermined rate — in the present example a rate of 8 khz ( thus a sweep repeat period 307 of 125 μs ( subject to the modifications described later in the specification )) is a convenient choice . such a modulation pattern is entirely conventional and the foregoing details are included as illustrative ; the skilled person will appreciate that any suitable values could be selected , dependent upon the use of the radar system ( e . g . the nature of the targets to be detected ). for each carrier frequency , the third circuit portion 230 is arranged to repeat the linear ramp pattern a specified number of times , e . g . 256 or 512 times , the number being dependent on the desired signal to noise ratio and therefore a design choice . whilst the third circuit portion 230 shown in fig2 comprises digital synthesiser components , it could alternatively be embodied using analogue components such as a sawtooth generator and vco or similar . preferably , and in order to save power , it is to be noted that the antenna 22 is not energised during either of the flyback ramp or dwell periods 303 , 305 . turning back to fig2 , the output f dds of the third circuit portion 230 is input to a fourth circuit portion 240 , which comprises a phase comparator 233 , a filter 235 , a voltage controlled oscillator 237 and a mixer 231 . the mixer receives signals output from the second circuit ( having frequency f 2 ) and signals output from the vco 237 ( having frequency f 5 ) and outputs a signal at a frequency equal to the difference in frequency between f 2 and f 5 . the phase comparator 233 outputs a phase - error signal , of magnitude dependent on the difference between ( f 2 - f 5 ) and f dds to the vco 237 , and the fourth circuit portion 240 operates so as to cause the output from the vco 237 to stabilise accordingly . the signals output from the fourth circuit portion 240 ( having frequency f 5 ) are then combined , by means of mixer 241 , with signals of a reference frequency f 4 , which are signals output from the oscillator 200 having been multiplied by a second static multiplier 251 , and the output is filtered ( filter 243 ) so as to generate a signal having an output frequency f out . it will be appreciated from fig2 that when the signal generator 16 is operable to output signals corresponding to a carrier frequency of between 15 . 5 ghz and 17 . 5 ghz , for a crystal oscillator 200 outputting signals of frequency 100 mhz , the second static multiplier 251 is of the order 130 . whilst the signal generator 16 could be used to generate frequencies within any selected range of frequencies , when used as a ground - based radar system , the frequency range can fall within the x band ( 8 ghz - 12 . 4 ghz ); the ku band ( 12 . 4 ghz - 18 ghz ); the k band ( 18 ghz - 26 . 5 ghz ); or the ka band ( 26 . 5 ghz - 40 ghz ), and most preferably within the ku band , or a portion within one of the afore - mentioned bands . thus for each carrier frequency the frequency generator 16 generates a repeating pattern of frequency modulated signals of various carrier frequencies . whilst in preferred arrangements the first and second circuit portions 210 , 220 of frequency generator 16 are embodied as shown in fig2 , the frequency generator 16 could alternatively be based on an arrangement comprising a plurality of fixed frequency oscillators , as shown in fig4 , one of which is selected via switch 400 so as to generate a signal at frequency f 2 . judicial selection of an appropriate fixed frequency oscillator ( e . g . a crystal oscillator ) means that the frequency generator 16 can incur minimal phase noise , since the signals are taken directly from one of the oscillators . however , this advantage is accompanied by a corresponding limitation , namely that there is no means for fine - tune adjustment of the carrier frequency , which can be a disadvantage when working with antennas 22 that require fine tuning of the carrier frequency to achieve optimal beamwidth distribution ( in terms of distribution of radiation within the lobes ). it will be appreciated from the foregoing that the antennas 22 , 32 transmit and receive radiation in response to input signals of varying frequencies ; accordingly the antennas 22 , 32 are of the frequency scanning antenna type . in a preferred embodiment , the frequency scanning antenna is embodied as a travelling wave antenna structure comprising at least two array antennas , one such antenna array 500 being shown in fig5 a . in one arrangement , the antenna array comprises a mesh structure 501 and a dielectric base 503 and has input means 507 for inputting energy to the mesh structure 501 . preferably the antenna array 500 also includes a ground plane . the input means 507 can comprise coaxial feeds positioned orthogonal to the plane of the antenna array 500 , but the skilled person will appreciate that alternative feeds could be used . in the arrangement shown in fig5 a , each mesh structure 501 comprises a plurality of rectangular interconnected elements 509 that are disposed on a surface of the dielectric base 503 ; each rectangular element 509 comprises two sides 513 a , 513 b and two ends 511 a , 511 b , the length l of the sides 513 a , 513 b being greater than the length s of the ends 511 a , 511 b . the physics underlying the operation of the travelling wave antenna are well known , having first been investigated by john kraus and described in u . s . pat . no . 3 , 290 , 688 . suffice to say that the length l of the sides 513 is of the order of one wavelength of the mean carrier frequencies , and the length s of the ends 511 is of the order one half of the wavelength of the mean carrier frequencies . it will be appreciated from the teaching in u . s . pat . no . 3 , 290 , 688 that mesh configurations other than rectangular and planar can be used . in relation to the particular configuration adopted for embodiments of the invention , when current is fed through the mesh structure 501 via feed 507 , currents passing through the ends 511 a , 511 b are in phase with one another . the current flowing through a respective side 513 a of a given element 509 is received from an end 511 a of an adjacent element ( shown as input 517 ) and splits into two current flows , each flowing in a different direction and being out of phase with one another . as is also shown in fig5 a , the width of the mesh making up sides 213 a , 213 b is progressively decreased from the centre of the mesh to each respective end thereof , thereby effectively increasing the length of the sides 213 a , 213 b from the centre of the array towards its ends . in a preferred arrangement the antenna can be embodied as a micro circuit strip . the configuration of the antenna structure 701 according to an embodiment of the invention will now be described with reference to fig6 and 7 . fig6 shows a development of the radar system 1 shown in fig1 , including two antennas 22 a , 22 b rather than one . turning also to fig7 , each of the antennas 22 a , 22 b is embodied in the form of antenna array 500 a , 500 b shown in fig5 a and 5 b , and the antenna structure 701 is responsive to input from the controller 12 for controlling input of energy to respective feeds i 1 , i 2 of the antenna arrays 500 a , 500 b . referring also to fig8 a , the two planar array antennas 500 a , 500 b are disposed within the structure 701 such that , for any given radio frequency , the antenna structure 701 is capable of transmitting the radio frequency energy within different angular regions 801 a , 801 b . referring back to fig7 , the antenna structure 701 can be characterised by a longitudinal axis a 1 and a transverse axis a 2 , which provides a convenient frame of reference for describing the arrangement of the planar antenna arrays 500 a , 500 b . as can be seen from fig7 , the first array antenna 500 a is inclined at an angle α relative to the transverse axis a 2 and the second planar array antenna 500 b is inclined at angle β relative to the transverse axis a 2 . as can also be seen from the figure , a side portion of the second array antenna 500 b abuts a side portion of the first array antenna 500 a ( in the figure the side portions are located on the dot indicating axis a 1 ) such that when viewed face on , the antenna arrays 500 b are located in adjacent longitudinal planes . it will be appreciated from the schematic shown in fig8 a that the orientation of the respective antenna arrays 500 a , 500 b — that is to say angles α and β — determine the direction in which radiation is emitted from the antenna structure 701 . thus , by varying the relative positions of the respective antenna arrays 500 a , 500 b , different portions of an angular region can be scanned for a given output frequency , f out , 1 . fig8 b shows radiation emitted 801 a - 801 d from the antenna arrays for two different output frequencies f out , 1 , and f out , 2 , and it can be seen that appropriate selection of the values of f out , 1 and f out , 2 , results in the antenna structure 701 outputting radiation so as to cover a substantially contiguous region , thereby scanning over a greater angular region than is possible with a single antenna array , or even two arrays that are positioned in the same plane , such as that described in u . s . pat . no . 4 , 376 , 938 . the arrangements shown in fig5 a , 6 , 7 , 8 a and 8 b relate to an arrangement in which the antenna arrays 500 a , 500 b comprise a single feed i 1 , i 2 at one end of respective antenna arrays . however , and referring to fig5 b and 10 , each antenna array could comprise an additional feed at its other end ( i 1 , 2 , i 2 , 2 ). each antenna 22 a , 22 b can then be considered to be capable of emitting radiation in two directions for a given frequency f out , since the transceive - behaviour of the antenna array 500 a is dependent on the direction from which energy is fed into the antenna . in fig9 , this is indicated by the presence of two antennas for each of antenna parts 22 a and 22 b . turning to fig1 , it can be seen that by feeding energy to two input feed points for each antenna array , the region r within which radiation can be transceived is effectively doubled . it will be appreciated from the foregoing that the frequency f out of signals output from the signal generator 16 is controlled by the controller 12 . in addition to controlling the duration and rate of the ramp as described above , the controller 12 is arranged to select a different value for carrier frequency after the ramp pattern has been repeated a specified number of times for a given carrier frequency ( examples of 256 and 512 were given above ). in one arrangement the values for the carrier frequency can be selected from a look - up table accessible to the controller 12 ( e . g . stored in local memory or on the computer 14 ), this look - up table being particular to a given antenna array 500 a , 500 b . operation of the radar system 1 described above will now be described with reference to fig1 , which is a schematic flow diagram showing steps carried out by the controller 12 . at step s 12 . 1 the controller 12 energises one of the input feeds i k , n of the antenna structure 701 , e . g . by appropriate configuration of the switch 18 ; at s 12 . 3 the controller 12 retrieves the value of the first carrier frequency f c1 ( e . g . from the look - up table mentioned above ), and at step s 12 . 5 the controller 12 sets the values of r 1 and r 2 accordingly ( to set the carrier frequency ) and causes the third circuit portion 230 to generate the ramp pattern a predetermined number of times rmp max ( s 12 . 7 ), to repeatedly modulate the carrier frequency . having reached rmp max , the controller retrieves the value of the next carrier frequency f c2 and sets the values r 1 , r 2 . preferably the overall duration of step s 12 . 7 — in other words the duration of any given set of repetitions of the linear ramp 301 i pattern — is the same for all values of the carrier frequency , f cj . these steps are repeated , as shown in fig1 , for each feed point i 1 , 1 i 2 , 1 i 2 , 2 i 2 , 1 to the antenna structure 701 , thereby causing the antenna structure 701 to progressively scan over the angular extent r . the description has thus far focussed on the generation and transmission of signals from the radar system 1 ; referring to fig1 , 6 , 7 , 9 and 10 , aspects of with receiving and processing of signals will now be described . as can be seen from these figures the radar system 1 preferably also includes a separate antenna 32 embodied as structure 703 for receiving radiation , which corresponds to the transmitting antenna structure 701 described above . referring to fig6 or 9 , the signals received by antenna structure 703 are input to mixer 34 , together with the output f out from the rf frequency generator 16 , and , in accordance with standard homodyne operation , the output from the mixer 34 is fed through an adc 36 to produce a digitised intermediate frequency ( f if ) signal as input to the signal processor 38 . energising of the receiving antenna structure 703 is performed under control of the controller 12 , via switch 18 ′, and , as for the transmitting antenna structure 703 , this occurs during the linear ramp period only 301 i . the signal processor 38 is conveniently embodied as a programmable logic controller ( plc ) and a plurality of software components , which run locally on the plc 38 in response to signals received from a conventional pc computer 14 and which are written using the proprietary programming language associated with the plc 38 . as described above , the radar system 1 operates according to homodyne principles , which means that the intermediate frequency f if is equal to differences between the received signal frequency and the transmitted signal frequency . in embodiments of the invention , as will be appreciated from the foregoing and fig2 and 3 in particular , the output of the radar system 1 is a sequence of frequency sweeps 301 i . it is a well known principle of radar that targets located in the path of a given transmitted beam will reflect the transmitted signals ; since the transmitted signal in embodiments of the present invention comprises a linear frequency sweep 301 i , the reflected signals also comprise a linear frequency sweep . targets that are stationary will generate reflected signals that are identical to the transmitted signals ( albeit somewhat attenuated ), but separated therefrom at a constant frequency difference referred to herein as a tone . referring to fig1 , it will be appreciated from the figure that different targets t 1 , t 2 — located at different distances from the radar system 1 — reflect the transmitted sweep 301 i at different delays in relation to the time of transmission , and that therefore targets t 1 , t 2 at these different locations will be associated with different tones δf 1 , δf 2 . in view of the fact that the signals output from the mixer 34 contain tones , the signal processor 38 is arranged to delay the processing of signals until the ramp 301 has travelled to the extents of the detection region and back . thus for example , if the detection region extended to 4 . 5 km from the radar system 1 , the signal processor 38 would start processing signals output from the mixer 34 at : 4500 × 2 3 × 10 8 = 30 ⁢ ⁢ µs from the start of transmission of a given ramp 301 i . considering , for the sake of clarity , one processing period 1301 1 , the signal processor 38 essentially calculates the doppler frequency of targets within range of the transmitted beam — and which reflect the transmitted beam . this is achieved by sampling the received tones δf 1 , δf 2 . . . δf m at a predetermined sampling rate . the sampling rate is selected so as to as ensure that phase shifts of the transmitted signal , which are induced by moving targets , can be captured . the skilled person will appreciate that this is dependent on the ramp rate , since the doppler frequency is dependent on the frequency of the transmitted signal : thus , the output of the adc 36 falling within the processing period 1301 1 will be processed a predetermined number of times ( corresponding to the sampling rate ) by the signal processor 38 . each sample will contain zero , one or a plurality of tones , each relating to signals reflected from targets . as will be appreciated from the foregoing , the linear ramp 301 i is transmitted a plurality of times for each carrier frequency . accordingly the signal processor 38 processes data received during a corresponding plurality of processing periods 1301 i , and generates , by means of a range fft , a set of return samples , individual members of which are assigned to a respective set of range gates for each processing period 1301 i . thus the output of the range fft , for a given processing period 1301 1 , is frequency information distributed over so - called range gates . as is well known in the art , range gates represent successive distances from the radar system 1 , such that if return samples fall within a given range gate , this indicates the presence of a target located at a distance equal to the range gate within which the return sample falls . having transformed the received signals into range gates the signal processor 38 is arranged to take the fft of the return samples assigned to each given range gate . in the current example it will be appreciated that each set of range gates corresponds to transmission of a linear ramp 301 i ( for a given carrier frequency ), and that the sampling rate in relation to range gates — the rate at which data falling within a given range gate are measured — is the frequency at which the pattern of transmission of linear ramps 301 i is repeated ( commonly referred to as the pulse repetition frequency ( prf )). in the example given above , and with reference to fig3 , this is nominally 8 khz . accordingly , for each carrier frequency , the signal processor 38 effectively generates an array of data , each row in the array corresponding to a given processing period 1301 i , and each column in the array corresponding to a given range gate . the fft output comprises amplitudes and phases of various components of signal energy which fall on frequencies spaced linearly at the inverse of the duration of a complete signal sample set ( in embodiments of the invention , the signal set comprises tones , not absolute frequency values ). in the current example , therefore , and assuming the signal sample set for a given carrier frequency to comprise the 512 linear ramps 301 1 . . . 301 512 transmitted at a rate of 8 khz , there are 512 fft output bins spaced at a doppler frequency of 8000 / 512 = 15 . 625 hz ; for a carrier frequency of 15 ghz , this is equivalent to 0 . 15625 m / s . thus each fft output bin represents a different velocity ; stationary targets will appear in bin 0 , while moving targets will appear in a bin dependent on their velocity ( a target travelling at 10 m / s will appear in bin 64 ). as is known in the art , the signal processor 38 can be arranged to store each set of range gate samples in a “ row ” of a conceptually rectangularly - organised memory , referred to as a corner store , each row corresponding to range gates falling within a given processing periods 130 i and thus to a particular linear ramp 301 i . once all 512 linear ramps 301 1 . . . 301 512 have been transmitted , each column — i . e . each range gate — is read out and input to a fft for processing thereby in the manner described above . from equation 1 , it will be appreciated that the doppler frequency is directly proportional to the carrier frequency f c . therefore when the carrier frequency varies — as is the case with frequency scanning antennas — the variation in carrier frequency will modify the derived doppler frequencies so as to effectively scale the magnitude of the frequencies . for example , a radar system that operates between 15 . 5 ghz to 17 . 5 ghz can generate doppler frequencies , for a given target , which vary by ± 6 %. this equates to a system - generated shift in doppler frequency of more than 2 semitones , and a variation in ambiguous doppler velocity from 70 mph to 79 mph , which can complicate the task of removing velocity ambiguity from targets moving at these speeds and above . referring back to fig1 it will be appreciated that in certain configurations of the radar system 1 the carrier frequency can jump from the maximum carrier frequency to the minimum carrier frequency , causing the signal processor 38 to output a change in tone of more than 2 semitones . accordingly the controller 12 is arranged to modify the sweep repeat period 307 ( or sweep repetition frequency ) such that the sweep repetition frequency is proportional to the carrier frequency , thereby effectively removing this systematic aberration . turning back to fig1 , this means that step s 12 . 5 performed by the controller 12 in relation to carrier frequency f cj retrieved at step s 12 . 3 is accompanied by calculation of a sweep period 307 for the particular value of this carrier frequency f cj . in preferred embodiments of the invention the linear sweep period 301 remains unchanged ( so that the effect of this adjustment does not affect the signal processor 38 ), and the controller 12 adjusts the duration of the flyback and / or dwell periods 303 , 305 ; most preferably the dwell period 305 is modified . of course all of the repetitions of the sweep repeat period 307 1 , f cj . . . 307 512 , f cj are identical for a given carrier frequency f cj ( step s 12 . 7 ). in one embodiment the controller 12 has access to a look - up table , which lists sweep repeat periods 307 j for discrete carrier frequencies f cj . conveniently such data could be stored in the look - up table that is accessed by the controller at step s 12 . 3 , when identifying a next carrier frequency f cj . as described above in relation to fig1 , the overall duration d of step s 12 . 7 is preferably maintained constant . when , as is the case with embodiments of the invention , the sweep repeat period 307 j varies in accordance with carrier frequency f cj the duration of 512 repetitions applied in respect of each different carrier frequency varies ; thus , of itself , the period associated with 512 repetitions would not be of duration d for all carrier frequencies . in order to ensure that the duration is nevertheless constant , the controller 12 is configured to wait for a period equal to the time difference between the end of 512 repetitions and duration d before moving onto the next instance of steps s 12 . 3 , s 12 . 5 and s 12 . 7 ( i . e . for a different carrier frequency ). in the present example the value of d is preferably set to the sum of 512 sweep repeat periods 307 corresponding to the duration of the longest sweep repeat period ( and thus that associated with the lowest carrier frequency f cj ). this feature of the controller 12 is advantageous for configurations in which the linear ramp period 301 is constant ( in fig3 it is shown as 64 μs ), incurring a fixed transmitter power dissipation : maintaining duration d for the overall duration of step s 12 . 7 means that the average transmitter dissipation is constant and independent of variations to the sweep repeat period 307 ( prf ). as a result the temperature of the transmitter t x is maintained at a constant level , which , in turn , minimises the variations in parameters that are temperature dependent . preferably the doppler frequencies are scaled and output as tones within the audible range and at a fixed audio sample rate . playing back the tones at a fixed rate is a convenient approach in view of the fact that the doppler frequencies have been normalised in relation to the variation in carrier frequency . as an alternative to selecting sweep repeat periods 307 j as a function of carrier frequency f cj , the sweep repeat period 307 j could be varied incrementally , for example linearly , based on the approximation 1 + α ≈ 1 /( 1 − α ) for α & lt ;& lt ; 1 . for the example frequency range of 15 . 5 ghz - 17 . 5 ghz , the sweep repeat period 307 for a carrier frequency of 15 . 5 ghz could be 140 . 65 μs , and period 307 for a carrier frequency of 17 . 5 ghz could be 125 μs , while the sweep repeat period 307 for carrier frequencies between the extents of this range can be selected so as to vary linearly between 125 μs and 140 . 65 μs . as for the first alternative — where the sweep repeat period 307 is varied discretely as the carrier frequency varies — the linear ramp 301 and thus the processing periods 1301 remain unchanged for all values of the sweep repeat period 307 . the net change in doppler frequency is then reduced to ± 0 . 2 % and the ambiguous doppler velocity varies from 78 . 7 mph to 79 . 0 mph . as described above , a radar system according to embodiments of the invention can conveniently be used for transceiving radio frequency energy and processing the same so as to output an audible representation of doppler frequencies and thus identifying moving targets . the signal processor 38 is arranged to transmit data indicative of the doppler frequencies to the computer 14 , which comprises a suite of software components 39 arranged to convert the doppler frequencies to audible signals and to playback the same . as described above , the doppler frequencies are normalised by processing the received signals at a variable rate , the rate being selected in dependence on the carrier frequency of the transceived signal , while the rate at which the audio is played back is substantially constant . preferably the post processing software components 39 are arranged to ensure smooth transition between respective audio bursts by controlling the playback rate in relation to the rate at which , for a given range gate , data have been processed by the signal processor 38 ( i . e . the frequency at which the pattern of transmission of linear ramps 301 i is repeated ). if the prf is varied between 7 khz and 8 khz and the audio playback rate is 8 . 5 khz , then in the absence of suitable phased - audio control , there will be gaps in the audio output , which presents an interruption to any audible analysis of the doppler data ; one way of mitigating this is to recycle doppler data during periods that would otherwise be silent , until such time as further doppler data are made available from the signal processor 38 . in order to ensure a smooth transition between respective sets of doppler data , the computer 14 would be arranged to fade - out previous , and fade - in and current , sets of doppler data . as an alternative , the audio playback rate could be set at a value lower than the prf ( e . g . for the current example , 6 . 9 khz ) so that respective sets of doppler data overlap ; the periods of overlap can be managed using appropriately selected fade - in and fade - out functions . in arrangements where the duration of sets of repetitions of the linear ramp period 301 i is constant ( duration d ), any set of doppler data ( corresponding to a given carrier frequency f cj ) will arrive at the signal processor 38 a constant rate , which means that the software components 39 can be configured to apply the same conditions in relation to overlaps and / or gaps in the doppler data ( since the amount of overlap or gap can always be calculated from duration d ). an advantage of this arrangement is that it simplifies the logic associated with the post - processing software components 39 and enables more constant audio output over the varying prf . a particular feature of a radar system according to embodiments of the invention is that the software components 39 are arranged to transmit data output from the signal processor 38 to a remote processing system , for tracking and monitoring of targets . most preferably the software components 39 are arranged to transmit data output from the signal processor 38 each time the carrier frequency — and thus region being scanned — changes . this means that the computer 14 acts primarily as a conduit for data , while the data intensive processes of correlating targets between successive scans , rendering of targets upon a display and prediction of target behaviour can be performed by a separate processing system . in a preferred arrangement the data are transmitted wirelessly , but it will be appreciated that any suitable transmission means could be used . whilst in the foregoing the linear ramp 301 is independent of variations in the sweep repeat period , the controller 12 could alternatively modify the duration and / or slope of the linear ramp . whilst this is not a preferred method , because operation of the signal processor 38 ( in particular in relation to the processing periods 1301 ) would have to be modified , modifying the slope is a convenient method when more than one radar system is being utilised in a given region , since the difference in slopes of the linear ramp can be used to distinguish between output from respective radar systems . fig1 shows an alternative configuration of the radar system 1 comprising antenna structures according to embodiments of the invention , in which the single amplifiers 20 , 20 ′ are replaced by individual amplifiers , each being associated with a respective antenna . in the above passages the radar system 1 is assumed to comprise a separate transmit and receive antenna structure 701 , 703 . however , and turning to fig1 , the radar system 1 could alternatively comprise a single antenna structure 701 and a circulator 40 , which , as is known in the art effectively combines signals that are transmitted and received from the antenna structure 701 . as an alternative to the circulator 40 , the radar system 1 could include a switch or an alternative antenna utilising a turnstile junction or orthomode junction ( not shown ). fig1 shows an alternative configuration of the antenna arrays 500 a , 500 b within an antenna structure 701 , in which each the antenna array 500 a , 500 b is located on a respective support structure , an outer edge 531 a of one support structure abutting a corresponding outer edge 531 b of another support structure so as to form an antenna structure having a generally isosceles shape ; since the supports of respective antenna arrays abut one another the radar system can be fabricated such that receiving antenna structure 701 abuts transmitting antenna structure 703 , thereby generating a physically smaller radar system , in terms of depth occupied by the antenna structure , compared to that shown in fig7 . it will be appreciated that other configurations are possible , involving two , three or several such antenna arrays mounted on suitable support structures . whilst in embodiments of the invention the radar system 1 preferably uses antenna structure 701 described above , which is based on travelling wave antenna technology , the radar system 1 could alternatively use a waveguide in the form of a serpentine antenna or similar as the frequency scanning antenna . a suitable antenna is described in u . s . pat . no . 4 , 868 , 574 . whilst the above embodiments describe use of a frequency scanning antenna for beam steering , it will be appreciated that the configurations and methods described above could be applied for the purposes of avoidance detection , and / or in the presence of other radar systems , and / or to counteract frequency jamming equipment ( e . g . by hopping between operating frequencies in order to avoid detection of , interference with , or jamming of , the radar system ). the above embodiments are to be understood as illustrative examples of the invention . further embodiments of the invention are envisaged . it is to be understood that any feature described in relation to any one embodiment may be used alone , or in combination with other features described , and may also be used in combination with one or more features of any other of the embodiments , or any combination of any other of the embodiments . furthermore , equivalents and modifications not described above may also be employed without departing from the scope of the invention , which is defined in the accompanying claims .