• 专利附录
  • 专利说明
  • 权利要求
  • 类似技术
  • 同族专利
  • 引用文献
  • 法律状态
  • 优先权
    • 专利摘要:
    1503211 Radio navigation OFFICE NATIONAL D'ETUDES ET DE RECHERCHES AEROSPATIALES 19 Feb 1975 [20 Feb 1974 (5)] 7031/75 Heading H4D First embodiment. This generally comprises an in line array of three aerials the centre of reference aerial 17, Fig. 2, being on the axis of a motor 72 and the outer aerials 21 and 22 being rotated about aerial 17 at respective distances R and R2 from it. Although Fig. 1 shows a signal generation system whereby with the reference aerial 17 transmitting a signal F0 the two outer aerials transmit respective signals F0-F and F0+F the main embodiment has the outer aerials transmitting respective signals F0+F3 and F0+F5. The rotation of the motor and aerial array is synchro controlled by means of a set of three discs attached to the motor shaft the first disc having one half transparent 75 and one half opaque 76, a second disc having 16 alternately transparent and opaque sectors 781, 782 and the third disc having 320 alternate transparent and opaque sectors 811, 812 each disc has a light source 85 and a light detector 82 associated with it whereby with the motor rotating at a normal 10 Hz the light detector of the first disc gives an output at 10 Hz that from the second disc is an output of 160 Hz and that from the third disc gives an output of 3200 Hz. These three outputs are compared with respective reference frequency signals FR1, FR2, FR3 and any error signals are used on line 95 to servo adjust rotation of the motor 72. To produce the reference frequency FR1, FR2, FR3, Fig. 5, together with the offset frequencies F3 and F5, three position oscillators 101, 102, 103 are used to produce three reference frequencies and by a combination of a mixer 107 and frequency multipliers 105, 111 the frequencies F3 and F5 are produced as phase slaved combinations of the reference frequencies. The reference signal aerial 17 is amplitude modulated with the signals FR1, FR2 and FR3, Fig. 4. Due to the rotation of the aerials 21 and 22 the signals therefrom as received by an aircraft will have a Doppler frequency spread on them giving the frequency spectrum of Fig. 4 two different beacons or runways being defined by two different differences #F1 and #F2 between the frequency of the reference signal FA and the centre frequencies F01 and F02 of the rotating aertials 21, 22. On the aircraft Fig. 6 assuming a beacon F01 to be transmitting, it is first of all necessary to re-establish all of the various fixed frequencies, e.g. FR1, FR2, FR3, F3, F5, F8. The received beacon signals are therefore reduced by two stages of mixing 124, 131 to a range of 100 to 500 kHz and the reference frequency with its sidebands are extracted by a tuned IF amplifier 134 and the sidebands detected by means of detector 137. The three signals FR1, FR2, FR3 are separated out of respective filters 139, 140, 141 and pass to a coincidence circuit 148 which gives an output pulse every time the aerial array aligns with 0. The three frequencies are also fed to a frequency synthesizer, Fig. 7, to reproduce the signals F3, F5, F8. To extract the Doppler shifts on the signals transmitted by the rotating aerials the phase of which Doppler shift will be indicative of the bearing of the aircraft the IF signal on line 130 is heterodyned by means of a local oscillator 174 tuned to the particular beacon being received so that the resultant signal falls within the pass band of an IF amplifier 176. The resultant signal is split up into three broadband IF amplifiers 182, 183, 184 having respective centre frequencies F0-F3 and F0-F5. The outputs of amplifiers 182, 183 are mixed at 185 to give a signal F3 those from 183 and 184 are mixed at 192 to give a signal F5 and those from amplifiers 182, 184 are mixed at 194 to give a signal F8. These three frequency signals carry respective bearing information based on the two rotating aerials and a fictitious aerial rotating at the sum of the radii of the two aerials, i.e. F8, have different carry frequencies and are therefore converted to a constant carrier F<SP>1</SP> in a heterodyning circuit Fig. 8 whereby the resulting signals S1, S2 and S3 are given by equations (1) a i , a j =amplitudes of sig over tracks i and j, w<SP>1</SP>=2#f<SP>1</SP>, #<SP>1</SP>=phase bias of w<SP>1</SP>, r i r j =lengths of tracks i, j, # i3 , # i5 = phase shift by rotations of 21 and 22 via track i. In the aircraft display apparatus, Fig. 9, the three rotating obturator discs at the beacon are reproduced as three concentric parts of a single disc 525, the two sectors, the sixteen sectors and the 320 sectors all being aligned up so that a common diameter 531 passes through all. A light source 536 co-operates with three detectors 537, 538, 539 to produce three signals at 10, 160 and 3200 Hz which are combined at 4, 541 to produce a pulse every time that the diameter line 529 passes through the line joining the sectors which pulses are time compared with the north pulses on line 149, Fig. 6. The result of the comparison is used to servo control rotation of motor M such that the disc 525 is rotating in synchronism with the aerials 21, 22. The motor M also rotates two discs having bands across them, disc 551 having an intensity variation in a direction perpendicular to the direction of the band given by equation (2) A light source and photodetector on opposite sides of disc 551 produce a signal given by equation (3) This last equation bears an affinity to the equation for the phase shift produced on the signal radiated by one of the antenna 21 or 22 and given by equation (4) i.e. in the term 2#p/# and 2#rcos#/#. The second disc 554 contains exactly the same bands as the disc 551 but phase shifted along by “ of the spacial wavelength. Equation (3) is then modified for this disc by having a sine term instead of a cosine term whereby the outputs of the detectors 553 and 556 are detected at 557, 559 the resultant AC components 561 to 569 are given by equation (5) These signals are used to amplitude modulate the quadrature signals at the aircraft reference frequency F<SP>1</SP>. The resultant reference signal, equation (6) is multiplied with the signals S1, S2 and S3 at 577, 578, 579 respectively, the three multiplication signals after elimination of the 2w<SP>1</SP> components by filters 584, 585, 586 are S<SP>1</SP>1, S<SP>1</SP>2, S<SP>1</SP>3 and are given by equation (7) Note similarity between equation (I) and equation (6) the similar terms w't and #<SP>1</SP> cancel out in the mixers 577, 578, 579. The fij functions of time in equation (7) represent phase differences resulting from path length differences from two sources. The signals S<SP>1</SP>1 &c. are applied to correspondingly vary the brightness of sources 592, 622, 632. For example the luminous intensity of source 592 varies in accordance with equation (8) Each light source has its light spread to cover a full radius of rotating disc 611, 621, 631 the light passing through the disc being reflected via a system of mirrors 613, 614, 627, 629, 638, 641 on to a vidicon target 617, the mirrors 629, 641 being semi silvered whereby the disc modulated light from all three sources are integrated on the target. The disc 611 has parallel opaque stripes with a law of transparency given by equation (9) The manner in which the rotating disc 611 modulates light passing through it is a spacial analogue of the manner in which the signal received from the rotating aerials is Doppler modulated. Therefore the fact that the light source 592 is amplitude modulated in dependence upon this Doppler modulation brings about in effect a cross correlation between the two functions, one function being contained in the modulation of the light and the other function being contained in the modulation by the rotating disc 611; therefore with the result of this correlation being given by equation (10) only discrete point or points of the cross-section of the beam 612 continuously pass through the rotating disc 611, whereby on the screen of vidicon 611 said point or points build up during the rotation. It is possible for the system to work using only one of the three signals S1, S2, S3, however the display on vidicon 617 using only one signal for example S1 would produce a bright spot surrounded by a considerable area of partial brightness whereas the accumulative effect of the use of the other two signals produces a cancelling out of this surrounding area. A variable transmissivity grid 642 is imposed in front of the vidicon to compensate for the variation in intensity of the light passing through the discs as a function of distance from the centre. The display on vidicon 617 will contain various parasitic images indicating ground reflected images and also images produced by the incorrect positioning of the various discs relative to each other, the latter images can be removed by the correct positioning of the various discs. The images due to ground reflection will tend to disappear as the integration time on the vidicon is allowed to increase. One exemplified use of the just described system is a landing approach aid Fig. 14 wherein the vidicon derived display 618 shows the position of beacons as well possibly of reflections thereof said display indicating the actual position of the incoming aircraft which actual position is also compared with the desired position as stored in flight plan device 700, the area of comparison being given by the shaded area 704 and the result of the comparison being fed on line 708 to the autopilot for correction of the flight path. The six discs 525, 551, 554, 611, 621, 631 of Fig. 9 may be replaced by a single disc Fig. 15 in which the central part is occupied by the disc 525 the next annular part by the equivalent of discs 551, 554 and the outer part by the equivalent of discs 611, 621, 631 the different spacial frequencies and relative phases required for the three discs being obtained by the relative positions and sizes of the beams 731, 732, 733 passing
    公开号:SU735192A3
    申请号:SU762355952
    申请日:1976-05-04
    公开日:1980-05-15
    发明作者:Дорей Жак
    申请人:Оффис Насьональ Д,Этюд Э Де Решерш Аэроспасьяль /О.Н.Э.Р.А./ (Фирма)；
    IPC主号:
    专利说明:

    (54) METHOD AND SYSTEM FOR DETERMINING COORDINATES OF AIRPLANE IN THE AERODROME ZONE
    I
    This invention relates to the field of near; In this case, the aircraft’s radio navigation, in particular, to the methods and systems for determining the polar coordinates of the aircraft using signals re-emitted by the aircraft transponder and received by the rotating aerodrome antenna device.
    A radar system for monitoring the position of moving objects is known, comprising a transmitter of probing signals and a method for determining coordinates by emitting signals, retransmitting them by a transponder to a mobile object, receiving signals emitted by a mobile object by a receiving device consisting of two antennas, and then transforming the received signals and displaying received information about the coordinates of a moving object 1. .
    The disadvantage of such a system is the complexity of the receiving antenna device and the significant area occupied by it.
    The closest technical solution to the present invention is a device for receiving and processing signals emitted by a moving object, containing two antennas synchronously rotated about the axis of rotation across the diameter, connected to the input of the converter, the output of which through an integrator is connected to an indicator of polar coordinates, which implements in the reception of the signals emitted by the source by the aerodrome synchronously rotated antenna device with their subsequent transformation, integration and display polar coordinates 2.
    However, such a system and such a method is not
    10 allows you to simultaneously determine the azimuth and angle.
    The purpose of the invention is to increase the accuracy of the simultaneous determination of the polar coordinates of the aircraft relative to the aerodrome antenna device.
    15
    The goal is achieved in that according to the proposed method, the conversion is carried out by shifting the signal from each antenna with the signal of the corresponding local oscillator, extracting their difference frequency, jointly detecting the converted signals of both antennas, filtering the resulting signal, multiplying with the signal of the frequency difference of the heterodyne , bass, double
    phase modulation similar to the phases of received signals with simultaneous two-dimensional correlation ..
    FIG. 1 shows a general scheme of the system; in fig. 2 - aerodrome receiving antenna; in fig. 3 is a block diagram of an aerodrome receiver; in fig. 4 - diagram of radio pulse exchange.
    The airfield is equipped with a transmitter 1 (Fig. 1), the antenna 2 of which emits high-frequency energy. Airplane 3, located in the aerodrome area, has a transceiver 4, which, in response to the aerodrome request signal received by the aircraft antenna 5, sends high-frequency response pulses received at the aerodrome by the antenna 7 connected to the receiver input 8 using the antenna 6.
    Each aircraft approaching the aerodrome is equipped with a transceiver, and the carrier pulse response frequencies of these different aircraft are close to each other.
    An antenna device 9 (FIG. 2) is also installed at the aerodrome, which contains a holder 10 mounted on a shaft 11, which is brought into uniform rotation by the engine 12. At one end of the holder 10 a first antenna 13 is mounted and at the opposite end a second antenna 14. Antennas 13 and 14 provide signal reception in a given angular sector.
    The signal received by antennas 13 and 14 is supplied to preamplifiers 15 and 16, respectively (Fig. 3). Each of the amplifiers with its output is connected to its mixer, respectively 17 and 18.
    The second input of the mixer 17 is connected to the local oscillator 19, which generates the frequency coi and has a cpi phase relative to the origin. The second input of the mixer 18 is connected to the local oscillator 20, which generates the frequency with a and has a phy phase relative to the origin. The signals taken from mixers 17 and 18 pass through bandpass filters 21 and 22 tuned to the difference frequency, respectively W -coi and 0-0) 2. The outputs of the filters 21 and 22 are connected together to one input of the amplifier 23 intermediate frequency. Further, the amplified signals, through a quadratic element, such as diode 24, which multiplies them, filter 25 tuned to a frequency of 1 - coi Cij and whose bandwidth is sufficiently wide to cover the maximum deviation of the phase modulation phase produced by antennas 13 and 14 , as well as the amplitude spectrum arising due to the pulsed nature of the received signals, the movable connection 26 rotating with the shaft 11 is fed to one of the inputs of the nonlinear element 27 ..,:, i: the movable connection provides the communication part system mounted on a 735192
    the common part of the antenna device 9 with the rest of the circuit placed on the non-rotating part of the ground antenna kit ..
    In addition, the outputs of the local oscillators 19 and 20 are connected to the mixer 28, the output of which is associated with a narrowband filter 29 tuned to the frequency co,. The filter 29 through the movable connection 30, which is associated with the rotating shaft I, is connected to the second input of the nonlinear element 27.
    The signals S (t) from the output of the filter 25 and r (t) from the output of the filter 29 in the non-linear element 27 are multiplied. Its output is connected to a low-pass filter 31, which eliminates the 2 W harmonic. The filter output signal is through a gate device 32 and an amplifier 33 with an automatic gain control regulator and is supplied to an electroluminescent diode 34, which creates a luminous intensity proportional to the magnitude of the signal.
    The electroluminescent diode 34 is installed in the focus of the lens 35, which creates a beam of parallel rays directed to the disk 36 mounted on the shaft 11 of the rotation of the tangent device 9. The disk is made with variable transparency in the direction indicated by the arrow J, and with constant transparency perpendicular the direction indicated by the arrow Y.
    The law of transparency of the disk 36 provides the necessary light energy at some point in space behind the disk having the polar coordinates f nV.
    The light of the beam generated as a result of its passage through the disk 36 is directed by an optical device 37 to an integrating sensor, such as a vidicon 38. The vidicon is connected to an imaging device such as an electronic indicator 39 with a screen 40.
    A change in the disk transparency causes a correlation of the flow changes only at the point with polar coordinates, V 9 and at the point with polar coordinates (y), v in + l, whereas in no other point does this take place.
    In order to eliminate the ambiguity, the electrical lengths of the antenna arms of the antenna device 9 differ from one another by an amount which ensures the phase mismatch between the signals passing through them. ,
    The disk 36 is mounted on the shaft 11 in such a way that the direction of the parallel axes is perpendicular to the direction of the rotating holder of the antenna device when the holder is installed in the direction of geographic north (Fig. 2).
    The proposed device makes it possible to visualize on the screen 40 airplanes whose radiation is received by a device with rotating omnidirectional antennas 13 and 14.
    The device also allows selection among these aircraft.
    The gate device 32 is supplied with signals from the clock device 41, which controls the pulses supplied by the transmitter 1 to the antenna 2. These request pulses are shown in FIG. 4 a.
    Response pulses received by the aerodrome receiver from aircraft I are shown in bold lines, and from the more distant aircraft P, double thin lines (Fig. 46). The gap between the request and response pulses corresponds to the time of the full path of the radio beam, plus the systematic delay introduced by the onboard equipment itself. When the gate device 32 is open for the time shown in FIG. 4c, in the form of flat strobe pulses, the middle of which is shifted by time -c relative to the request pulse, only those signals that come from aircraft I are processed, while the strobe pulse repetition period is equal to the request pulse repetition period.
    If, as indicated by the dotted line, the gate device 32 is unlocked for a period of time from the middle to the t, then signals from aircraft II are received and pulses from aircraft I are excluded.
    Thus, an aerodrome can undertake the task of controlling the movement of one or several airplanes, the significance of which is remote from the aerodrome lies between two predetermined values.
    Leaving the gating device permanently open, on the screen 40 an image of all the planes located near the aerodrome at distances corresponding to the range of the radio communication and in some cases in a certain angular sector is obtained.
    The device allows determining for each aircraft its azimuth © and the elevation angle y. This data is transmitted from the airfield. to the appropriate aircraft using the data transmission system.
    权利要求:
    Claims (2)
    [1]
    1. A method for determining the coordinates of an aircraft in an aerodrome area by emitting probe signals, retransmitting them to an airplane responder, receiving said signals by an aerodrome synchronously rotated antenna device and then transforming them, integrating and displaying polar coordinates, different in that. That, in order to improve the accuracy of simultaneously determining the polar coordinates of the aircraft relative to the aerodrome antenna device, the conversion is carried out by shifting the signals of each antenna with the signal of the corresponding local oscillator, extracting their difference frequency, combining quadratic detection of the converted signals of both antennas, filtering the resulting signal, over , Q multiplication with the signal of the difference between the frequencies of the local oscillators, the allocation of low frequencies, double modulation in phase, similar to the phases of the received si gnals, with simultaneous two-dimensional correlation.
    - 2. The system for determining the coordinates of the aircraft in the aerodrome area, containing an aerodrome transceiver, an onboard transponder and an aerodrome receiving antenna device containing two antennas synchronously rotated around the axis of rotation along the diameter, connected to the converter input, the output of which through the integrator is connected to the indicator of polar coordinates , characterized in that, in order to increase the accuracy of the simultaneous determination of the polar coordinates S of the aircraft relative to the aerodrome antenna device, The recipient is made in the form of two mixers, one input of each of which is connected to its antenna, the second input is connected to its local oscillator, and the outputs are through filters of difference frequencies to a common quadratic detector, the output of which is connected to the first input of a nonlinear element through a bandpass filter, the second the input of which through the narrowband filter is connected with the output of the mixer of the frequencies of the local oscillators, and
    J output through a serially connected low-pass filter, a gating device, an amplifier with automatic gain control connected to the emitter of an optical modulator consisting of a rotation mounted on the shaft
     the airfield receiving antenna device of a disc with transparency sinusoidally perpendicularly perpendicular to one direction, the output of which is optically coupled to the integrator.
    Sources of information
    taken into account in the examination
    1. US Patent No. 3531801, cl. 343-15, published. 09.29.70.
    [2]
    2. Astafyev, G.P., et al. Radiotechnical means of nav1 (aircraft formations.
    “Soviet Radio, 1962, ch. 9 (prototype).
    Sh
    /
    ir; / 3
    FTs 2.1
    /
    类似技术:
    公开号 | 公开日 | 专利标题
    US3790939A|1974-02-05|Real time synthetic radar
    SU695586A3|1979-10-30|Instrumental aeronavigation system
    US2406953A|1946-09-03|System for determining the position of an object in space
    SU735192A3|1980-05-15|Method and system for determining coordinates of aircraft in airfield area
    US3144646A|1964-08-11|Doppler system
    GB2046059A|1980-11-05|Coded coherent transponder
    GB875369A|1961-08-16|Improvements in or relating to apparatus for a doppler radar system
    US3334344A|1967-08-01|Doppler radar altimeter
    US6870499B2|2005-03-22|System and method for increasing resistance to target vibrations in synthetic aperture radar signals
    US2947985A|1960-08-02|Navigation systems
    US3254341A|1966-05-31|Systems for calculating the coordinates of a point at the surface of the earth
    KR100794533B1|2008-01-17|Method and device for magnetic guidance, especially for tracking targets
    RU2620359C9|2017-07-25|Method for determining aircraft position with respect to runway at landing and system for its implementation
    SU686641A3|1979-09-15|Device for determining angular position of helicopter with respect to radio beacon
    US3569967A|1971-03-09|Echo processing apparatus of side looking detection systems operating with frequency modulated transmitted pulses
    US3662384A|1972-05-09|Doppler mapping radar
    RU2018864C1|1994-08-30|Method of measuring distance in doppler speed vector meters for flying vehicles
    US4485384A|1984-11-27|Microwave system
    RU2411532C1|2011-02-10|Device for determining distance between aircraft
    US3882500A|1975-05-06|System for the automatic tracking of a moving target
    US2536728A|1951-01-02|System of position finding by electromagnetic waves
    SU709013A3|1980-01-05|Receiving device of an aircraft navigation system over signal tower radiosignals
    RU2275746C1|2006-04-27|Radio-technical reconnaissance station
    Ananenkov et al.2019|Interferometric rsa for the ice situation monitoring
    RU2159447C1|2000-11-20|Flying vehicle radio direction finding method
    同族专利:
    公开号 | 公开日
    CA1026465A|1978-02-14|
    US4019184A|1977-04-19|
    SU728735A3|1980-04-15|
    DE2507401C3|1980-10-09|
    DE2507401A1|1976-01-29|
    DE2507401B2|1980-02-21|
    GB1503211A|1978-03-08|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    US2644158A|1946-11-06|1953-06-30|Sterling R Thrift|Directive antenna system|
    DE1123000B|1958-07-16|1962-02-01|Standard Elektrik Lorenz Ag|Arrangement for wireless determination of direction based on the Doppler effect|
    GB1207092A|1969-03-19|1970-09-30|Standard Telephones Cables Ltd|Phase shift detector|FR2357911B1|1976-07-09|1980-08-01|Onera |
    US4371873A|1977-12-08|1983-02-01|Nasa|Clutter free synthetic aperture radar correlator|
    FR2629213B1|1981-07-28|1991-10-25|Onera |PHASE SCAN RADAR|
    US4489326A|1982-03-15|1984-12-18|Canadian Marconi Company|Time reference scanning beam microwave landing system|
    US4845502A|1988-04-07|1989-07-04|Carr James L|Direction finding method and apparatus|
    JPH0744512B2|1990-03-23|1995-05-15|株式会社小電力高速通信研究所|Space division type multiplex communication system|
    US6346912B1|2000-04-20|2002-02-12|The Johns Hopkins University|Radio frequency beacon|
    US8400350B2|2007-08-08|2013-03-19|Fujitsu Ten Limited|Radar device and azimuth angle detection method|
    US10585185B2|2017-02-03|2020-03-10|Rohde & Schwarz Gmbh & Co. Kg|Security scanning system with walk-through-gate|
    CN108375752A|2018-02-05|2018-08-07|中国人民解放军战略支援部队信息工程大学|Amplitude phase error single radiation source direction-finding method based on full angle search|
    法律状态:
    优先权:
    申请号 | 申请日 | 专利标题
    FR7405808A|FR2261628B1|1974-02-20|1974-02-20|
    FR7405811A|FR2261540B1|1974-02-20|1974-02-20|
    FR7405810A|FR2261664B1|1974-02-20|1974-02-20|
    FR7405812A|FR2261538B1|1974-02-20|1974-02-20|
    FR7405809A|FR2261578B1|1974-02-20|1974-02-20|
    [返回顶部]