EP1005105A2 - Arrangement pour générer et poursuivre automatiquement des diagrammes d' antenne dans le sens de l' élévation pour des aéronefs pendant des manoeuvres de vol afin de transmettre des données - Google Patents

Arrangement pour générer et poursuivre automatiquement des diagrammes d' antenne dans le sens de l' élévation pour des aéronefs pendant des manoeuvres de vol afin de transmettre des données Download PDF

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Publication number
EP1005105A2
EP1005105A2 EP99122607A EP99122607A EP1005105A2 EP 1005105 A2 EP1005105 A2 EP 1005105A2 EP 99122607 A EP99122607 A EP 99122607A EP 99122607 A EP99122607 A EP 99122607A EP 1005105 A2 EP1005105 A2 EP 1005105A2
Authority
EP
European Patent Office
Prior art keywords
antenna
frequency
aircraft
generating
antennas
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Granted
Application number
EP99122607A
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German (de)
English (en)
Other versions
EP1005105B1 (fr
EP1005105A3 (fr
Inventor
Ludwig Mehltretter
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Airbus Defence and Space GmbH
Original Assignee
DaimlerChrysler AG
EADS Deutschland GmbH
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by DaimlerChrysler AG, EADS Deutschland GmbH filed Critical DaimlerChrysler AG
Publication of EP1005105A2 publication Critical patent/EP1005105A2/fr
Publication of EP1005105A3 publication Critical patent/EP1005105A3/fr
Application granted granted Critical
Publication of EP1005105B1 publication Critical patent/EP1005105B1/fr
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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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
    • H01Q3/2682—Time delay steered arrays
    • H—ELECTRICITY
    • H01—ELECTRIC ELEMENTS
    • H01Q—ANTENNAS, i.e. RADIO AERIALS
    • H01Q1/00—Details of, or arrangements associated with, antennas
    • H01Q1/27—Adaptation for use in or on movable bodies
    • H01Q1/28—Adaptation for use in or on aircraft, missiles, satellites, or balloons
    • 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
    • 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
    • H01Q3/30—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 varying the relative phase between the radiating elements of an array
    • H01Q3/34—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 varying the relative phase between the radiating elements of an array by electrical means
    • H01Q3/42—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 varying the relative phase between the radiating elements of an array by electrical means using frequency-mixing

Definitions

  • the invention relates to a device for generating and automatically tracking Antenna diagrams in the elevation direction for aircraft, such as airplanes or earthbound missiles, in flight maneuvers for the purpose of data transmission, in particular broadband data transmission.
  • the broadband data transmission between aircraft moving relative to each other must be in the higher frequency range, that is to say in the microwave range, because only there is a sufficient number Transmission channels with a larger bandwidth are available. But there Free space attenuation increases with increasing frequency and the transmission power does not can be increased arbitrarily, antennas with higher profit, ie directed antennas be used.
  • phased array antennas are used in the for fast tracking of directional antennas Known in the field of radar technology.
  • the disadvantage of these common phased array antennas is that use them to align the antenna diagrams phase shifters in the transmission frequency range use that, especially at higher frequencies, a considerable attenuation in the phase networks cause and due to the requirements for phase stability in proportion are expensive.
  • No. 5,493,306 describes a phase-controlled antenna for automatic scanning by tracking an antenna pattern over a given angular range described.
  • phase-shifting delay lines in the Intermediate frequency level arranged and the intermediate frequency is in the individual branches mixed with the signal of a local oscillator in a mixer before the high frequency Signal is fed to the individual antennas of the array.
  • the phase shift to The antenna diagram is tracked according to the principle of the Butler matrix, in its Network the delay lines are integrated.
  • the so-called frequency scanning method is known for use with radar devices, that dispenses with adjustable phase shifters and is therefore cheaper.
  • This frequency scanning method the individual antennas of an array with different lengths Feed lines, so that different depending on the fed frequency Set phase positions on the individual antennas, which results in different radiation angles surrender.
  • this method is unusable for data transmission because the Transmitted frequency changes depending on the required direction of radiation, so that the reception with a remote station is difficult to implement and antenna tracking after it Principle is completely impossible.
  • the required tracking rate is relatively low (a few seconds) is.
  • the tracking rate required to align the antennas in Elevation range due to the possible flight maneuvers mainly due to the usual rapidly changing flight positions in the roll axis of the aircraft can be much higher.
  • the definition of the respective elevation angle depends on the position angle, i.e. the roll and the Plane pitch angle and azimuth angle to the opposite side.
  • the invention has for its object to provide a device with which a user data transmission between aircraft during flight maneuvers and quick tracking of Antenna diagrams in the elevation direction with little functional and equipment expenditure is possible.
  • An advantage of the invention is that the data transmission regardless of the angle at which the aircraft communicating with each other are at a constant carrier frequency can be done. Another advantage is that the phase shift leading to Alignment of the antenna diagrams of the sub-antennas involved is required on low frequencies is generated, so that with the use of relatively inexpensive Components for the transmitting and receiving devices without great effort the stability of the Tracking can be achieved.
  • the remaining critical part of the circuit in the high frequency range is largely unproblematic with regard to the transmission quality, since the antenna assembly is compatible with the functions for generating and tracking the antenna diagrams in the immediate vicinity of the antenna feed point and extends in the smallest space. So they are Supply lines extremely short, therefore insensitive to phase changes and practical damping-free.
  • Another advantage is the fact that there is no expensive power amplifier for the transmitting part high performance is required, but a number of small inexpensive parallel connected Low power transmit amplifiers can be used. Through this parallel connection of The reliability is also increased by several transmitter output stages or antenna assemblies the device according to the invention.
  • FIG. 1 shows the arrangement 1 according to the invention for generation and tracking of antenna diagrams with a system controller 3, a modulator 5, a demodulator 6 and an oscillator unit 7, comprising a first 8 and a second 9 oscillator, which are expediently formed together in one module.
  • a system controller 3 controls the arrangement 1 according to the invention for generation and tracking of antenna diagrams with a system controller 3, a modulator 5, a demodulator 6 and an oscillator unit 7, comprising a first 8 and a second 9 oscillator, which are expediently formed together in one module.
  • Each transmission branch 21 is connected to the modulator 5 and each reception branch via a line 23 22 with a line 24 to the demodulator 6 in connection.
  • Both the first oscillator 8 and also the second oscillator 9 are connected to the system controller 3, via which the arrangement of Figure 1 with other aircraft systems, in particular the position reference system 25 des Airplane is connected.
  • the modulator 5 is used to transmit high-frequency signals with user data act upon. Accordingly, the demodulator 6 sets received modulated high-frequency signals into digital signals (user data), which are then processed can.
  • Each transmission branch 21 has on the side of the modulator 5 a first mixer 31, which of the first oscillator 8 received high-frequency signals with the modulator 5 coming signals mixes.
  • the signal coming from the modulator 5 the one Intermediate frequency represents, in a signal at around the alignment frequency different frequency implemented.
  • the first Mixer 31 Seen from the modulator 5 is the first Mixer 31 has a delay line 33a connected to it, which sends the signal through the transmit alignment frequency with a phase shift and that to a second Mixer 35 is guided.
  • the second mixer 35 mixes that from the delay line 33a coming signal with the signal generated by the second oscillator 9. This will make the the delay line 33a incoming signal into a signal with the transmission transmission frequency implemented.
  • This signal becomes a transmit power amplifier or a transmit power amplifier 37 out, which is connected to a transmitting antenna 39.
  • the Transmit branches 21 in terms of hardware on an antenna assembly, e.g. on a circuit board integrated.
  • receive branch 22 includes a receive antenna 49 and further from seen from this a receiving amplifier 47, a first mixer 45, one Delay line 43a, 43b, 43c, 43d, 43e and a second mixer 41.
  • first mixer 45 with the second oscillator 9 and the second mixer 41 with the first Oscillator 8 connected.
  • This Signal is through the delay line 43a, 43b, 43c, 43d, 43e with a Phase shift applied, supplied to the second mixer 41 and by this a signal coming from the first oscillator 8 mixed so that the signal is a receives constant transmission intermediate frequency.
  • the switch 8b and the switch 9b by the System control are switched, ensure that for the transmission phase, the mixer 31 or 35 of the transmission branch and for the reception phase, the mixers 41 and 45 of the reception branch are supplied with oscillator signals.
  • the receive transmission frequency is preferably the same as the transmission transmission frequency and is in the range of 10 GHz, for example.
  • the transmit alignment frequency or the receive alignment frequency is lower than that Transmit transmission frequency or the reception transmission frequency, both preferably are in the range of 1 GHz.
  • the antenna networks 12, 13, 14, 15 thus each have a first mixer 31 and a second one in their transmitting branch 21 Mixer 35, a transmit power amplifier or transmit output stage 37 and a transmit antenna 39 and in their receiving branch 22 a first mixer 45, a second mixer 41, one each Receive amplifier 47 and a receive antenna 49.
  • the lengths of the Delay lines are provided so that in the center position or another defined position of the antenna diagram of an antenna or an antenna network 11, 12, 13, 14, 15 the phase positions caused in the delay lines are relative differ from each other by a multiple of the wavelength. So the antenna network points 12 has a delay line 33b in its transmitting branch 21 and 22 in its receiving branch a delay line 43b. Analog are in the antenna network 13 Delay lines 33c and 43c, in the antenna network 14, the delay lines 33d and 43d and the delay lines 33e and 43e are provided in the antenna network 15.
  • the delay lines 33b and 43b are such that one in them Phase shift occurs that is at least one wavelength from that in the Delay lines 33a and 43a occurring phase shifts differs.
  • the Comparison to the phase shifts occurring in the delay line 33a or 43a occurs in the delay lines 33c and 43c by at least twice the wavelength larger phase shift, one in the delay lines 33d and 43d at least three times the wavelength larger phase shift and in the Delay lines 33e and 43e are larger by at least four times the wavelength Phase shift on.
  • the alignment or change of Antenna diagrams are made by vectorial addition of the individual signals of each transmitting antenna 39 or each receiving antenna 49, so that the signal level in a corresponding manner of the various antenna networks 11, 12, 13, 14, 15 when receiving or transmitting in add up vectorially to a specific send or receive direction.
  • phase shift in the different antenna networks 11, 12, 13, 14, 15 through the delay lines 33a, 33b, 33c, 33d, 33e or 43a, 43b, 43c, 43d of different lengths, 43e in cooperation with the supply frequencies generated by the first oscillator 8 is can by changing these supply frequencies of the first oscillator 8, which over the first mixer 31 are overlaid with the signal coming from modulator 5, respectively Formation of the main beam direction of the antenna can be effected in a defined direction. This direction is the direction to the aircraft that contains the user data or signals to be sent should receive.
  • the resulting target angle becomes the main antenna beam direction by the system control 3 or by a system assigned to it determined and from it the frequency of the first oscillator 8 changed so that an alignment the antenna main beam direction in the desired direction given by the desired angle becomes.
  • the setpoint angle is preferably determined by the aircraft reference system, e.g. the Inertial system, determined and with the azimuth angle to the opposite side in the elevation angle converted.
  • the second oscillator 9 in the transmitting part 21 causes that from the respective delay line 33a, 33b, 33c, 33d, 33e ultimately coming signal to the constant transmission transmission frequency is implemented.
  • the first from the first oscillator 8 Mixer 31 introduced to align the respective antenna diagrams frequency deviation is thus subtracted from the same frequency deviation by the second oscillator 9 and the respective second mixer 35 are eliminated. In this way they send respective transmit antennas 39 the relevant data with the same transmission frequency, regardless of the orientation of those belonging to the respective transmission antennas 39 Antenna diagrams.
  • the switches 8b, 9b are set so that the Signals of the first oscillator 8 to the assigned first mixer 31 or the signals of the second oscillator 9 to the respectively connected second mixer 35.
  • reception mode there is a superposition of those occurring in the respective reception part 22 Received signals on the one hand via the second oscillator 9 and the one assigned to it first mixer 45 and via the first oscillator 8 in connection with this assigned second mixer 41 instead.
  • the switches 8b, 9b must be set so that the Signals of the first oscillator 8 to the assigned second mixer 41 or the signals of the second oscillator 9 to the respective first mixers 45 connected.
  • the effect that into the respective receiving branches 22 via the first 8 and second oscillators 9 The phase shifts introduced are reversed to that in the respective transmission branches 21 intended mode of action.
  • That coming from the receiving antenna 49 and from Receiving amplifier 47 amplified signal is by means of the second oscillator 9 at a corresponding position of the switch 9b and by means of the respective first mixer 45 a signal superimposed, which is made up of a fundamental frequency and one for the diagram panning required variable frequency forms. This creates a signal with a Reception alignment frequency by the second mixer 41 to an intermediate frequency brought. The signal with the intermediate frequency is sent to the demodulator via line 24 6 fed. By the vectorial addition of those obtained after mixing twice As in the case of transmission, received signals 24 are generated by different phase shifts Chart panning.
  • the signals are behind the respective first mixers 45 via the delay lines 43a, 43b, 43c, 43d, 43e led to the phase delay resulting from these delay lines in a Convert diagram change to the reception of signals from the remote station horizontal direction, i.e. from a substantially parallel to the earth's surface trending direction.
  • the two mixes in the first Mixer 45 and in the second mixer 41 the reception frequency to that in line 24 present constant intermediate frequency implemented and supplied to the demodulator 6.
  • the system controller 3 calculates the elevation angle from the position angles, i.e. the rolling, Nick and azimuth angles, and places them in the required frequency offset for generation which together with the delay lines 33a, 33b, 33c, 33d, 33e or 43a, 43b, 43c, 43d, 43e caused phase shifts in the transmission or reception alignment frequency also effected um by the control signals for the first oscillator 8 and the second oscillator 9 generated.
  • the phase shifts between the antenna networks occur, are provided so that there is a for sending or receiving
  • the antenna main beam direction of the alignment arrangement 1 results in a target angle relative to an aircraft-fixed reference axis, i.e. is aligned with the remote station in every flight position.
  • the phase shift to be provided for this in each antenna network depends on the Distances between the respective transmit 39 or the respective receive 49 antennas the antenna networks 11, 12, 13, 14, 15. These are preferably the same size. Are these different, determine the required phase positions for generation or education and Alignment of the antenna main beam direction according to known algorithms.
  • FIG. 2 shows an example of an antenna main beam direction 70. With the help of described device can this in other pivot positions 71, 72, 73, 74, 75, 76th be moved.
  • system controller 3 is provided for switching the control signals from Send on receive and vice versa as well as switch-on and switch-off signals for amplifier modules (not shown). It can also be provided that the system control 3 Send or receive frequency selection by specifying or changing the second Oscillator 9 controls the fundamental frequency.
  • switches 8b and 9b With the help of the switches 8b and 9b, between the modes of transmission and reception switched. Alternatively, however, if different for sending and receiving Frequencies are used (frequency diversity), parallel transmission and reception be provided. Two first 8 or second 9 oscillators can then be provided.
  • the modulator 5 and the demodulator 6 can for the data to be sent or received all common types of modulation, such as AM (amplitude modulation), FM (Frequency Modulation), PM (Phase Modulation) or Spread Spectrum.
  • AM amplitude modulation
  • FM Frequency Modulation
  • PM Phase Modulation
  • Spread Spectrum amplitude modulation
  • the entire circuit of the antenna networks 11, 12, 13, 14, 15, possibly also including the antennas 39, 49 is expediently on a common or PCB 80 common to at least one transmitting or receiving branch (FIG. 3) housed, which can be designed as a multilayer.
  • the transmitting antennas can also be used 39 and receiving antennas 49 can be accommodated on this common plate, the antennas e.g. Patch or slot antennas can be and the active components are implemented in SMD or chip technology.
  • the transmitting 39 and receiving antennas 49 can be parts of the Aircraft structure.
  • this arrangement results in particular in the Advantage that the radar backscatter cross section and the aerodynamic conditions are not or change only relatively little.
  • each antenna field of the antenna networks 11, 12, 13, 14, 15 for the transmitting (21) and the receiving branch (22) also with only one antenna field be realized.
  • Such an antenna field would then have a corresponding one for each antenna Switches or a circulator can be assigned to these antennas in case of sending the corresponding functions of the transmission branch 21 and in the event of reception to assign corresponding functions of the receiving branch 22.
  • the antenna networks or assemblies 11, 12, 13, 14, 15 can be in aircraft structural parts be integrated.

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  • Physics & Mathematics (AREA)
  • Engineering & Computer Science (AREA)
  • Astronomy & Astrophysics (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • General Physics & Mathematics (AREA)
  • Remote Sensing (AREA)
  • Variable-Direction Aerials And Aerial Arrays (AREA)
  • Details Of Aerials (AREA)
  • Radar Systems Or Details Thereof (AREA)
EP99122607A 1998-11-23 1999-11-13 Arrangement pour générer et poursuivre automatiquement des diagrammes d' antenne dans le sens de l' élévation pour des aéronefs pendant des manoeuvres de vol afin de transmettre des données Expired - Lifetime EP1005105B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE19853933A DE19853933B4 (de) 1998-11-23 1998-11-23 Verfahren zur Erzeugung und automatischen Nachführung von Antennen-Diagrammen in der Elevationsrichtung für Luftfahrzeuge bei Flugmanövern zum Zwecke der Datenübertragung
DE19853933 1998-11-23

Publications (3)

Publication Number Publication Date
EP1005105A2 true EP1005105A2 (fr) 2000-05-31
EP1005105A3 EP1005105A3 (fr) 2002-01-02
EP1005105B1 EP1005105B1 (fr) 2005-01-12

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Family Applications (1)

Application Number Title Priority Date Filing Date
EP99122607A Expired - Lifetime EP1005105B1 (fr) 1998-11-23 1999-11-13 Arrangement pour générer et poursuivre automatiquement des diagrammes d' antenne dans le sens de l' élévation pour des aéronefs pendant des manoeuvres de vol afin de transmettre des données

Country Status (3)

Country Link
EP (1) EP1005105B1 (fr)
AT (1) ATE287128T1 (fr)
DE (2) DE19853933B4 (fr)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN106887706A (zh) * 2017-03-17 2017-06-23 王家齐 全自动卫星跟踪通信天线电子极化跟踪方法和装置
CN114725682A (zh) * 2022-04-19 2022-07-08 广州程星通信科技有限公司 一种相控阵波束指向设计方法、系统、装置及存储介质

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
AU2003245809A1 (en) 2002-04-27 2003-11-17 Eads Deutschland Gmbh Method for data transmission between military aeroplanes and devices for carrying out said method

Family Cites Families (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
BE792171A (fr) * 1971-09-17 1973-06-01 Int Standard Electric Corp Antenne d'exploration de trame
US3833904A (en) * 1973-02-05 1974-09-03 Hughes Aircraft Co Airborne switched array radar system
US4731614A (en) * 1986-08-11 1988-03-15 Crane Patrick E Phased array scanning system
US5493306A (en) * 1987-08-28 1996-02-20 Eaton Corporation Phased array antenna system to produce wide-open coverage of a wide angular section with high directive gain and moderate capability to resolve multiple signals
US5353031A (en) * 1993-07-23 1994-10-04 Itt Corporation Integrated module controller
US5587714A (en) * 1995-03-10 1996-12-24 Space Systems/Loral, Inc. Spacecraft antenna pointing error correction
JP3204111B2 (ja) * 1996-08-28 2001-09-04 松下電器産業株式会社 指向性制御アンテナ装置

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN106887706A (zh) * 2017-03-17 2017-06-23 王家齐 全自动卫星跟踪通信天线电子极化跟踪方法和装置
CN106887706B (zh) * 2017-03-17 2020-06-30 王家齐 全自动卫星跟踪通信天线电子极化跟踪方法和装置
CN114725682A (zh) * 2022-04-19 2022-07-08 广州程星通信科技有限公司 一种相控阵波束指向设计方法、系统、装置及存储介质

Also Published As

Publication number Publication date
DE59911440D1 (de) 2005-02-17
DE19853933A1 (de) 2000-06-08
DE19853933B4 (de) 2004-04-29
EP1005105B1 (fr) 2005-01-12
ATE287128T1 (de) 2005-01-15
EP1005105A3 (fr) 2002-01-02

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