CN105676192A - Pulse responder gain controller implementation method - Google Patents
Pulse responder gain controller implementation method Download PDFInfo
- Publication number
- CN105676192A CN105676192A CN201610098018.9A CN201610098018A CN105676192A CN 105676192 A CN105676192 A CN 105676192A CN 201610098018 A CN201610098018 A CN 201610098018A CN 105676192 A CN105676192 A CN 105676192A
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- Prior art keywords
- controlled attenuator
- answering machine
- attenuation
- electrically controlled
- radar
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01S—RADIO DIRECTION-FINDING; RADIO NAVIGATION; DETERMINING DISTANCE OR VELOCITY BY USE OF RADIO WAVES; LOCATING OR PRESENCE-DETECTING BY USE OF THE REFLECTION OR RERADIATION OF RADIO WAVES; ANALOGOUS ARRANGEMENTS USING OTHER WAVES
- G01S7/00—Details of systems according to groups G01S13/00, G01S15/00, G01S17/00
- G01S7/02—Details of systems according to groups G01S13/00, G01S15/00, G01S17/00 of systems according to group G01S13/00
- G01S7/28—Details of pulse systems
- G01S7/285—Receivers
- G01S7/34—Gain of receiver varied automatically during pulse-recurrence period, e.g. anti-clutter gain control
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01S—RADIO DIRECTION-FINDING; RADIO NAVIGATION; DETERMINING DISTANCE OR VELOCITY BY USE OF RADIO WAVES; LOCATING OR PRESENCE-DETECTING BY USE OF THE REFLECTION OR RERADIATION OF RADIO WAVES; ANALOGOUS ARRANGEMENTS USING OTHER WAVES
- G01S13/00—Systems using the reflection or reradiation of radio waves, e.g. radar systems; Analogous systems using reflection or reradiation of waves whose nature or wavelength is irrelevant or unspecified
- G01S13/74—Systems using reradiation of radio waves, e.g. secondary radar systems; Analogous systems
- G01S13/76—Systems using reradiation of radio waves, e.g. secondary radar systems; Analogous systems wherein pulse-type signals are transmitted
- G01S13/767—Responders; Transponders
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- Engineering & Computer Science (AREA)
- Radar, Positioning & Navigation (AREA)
- Remote Sensing (AREA)
- Computer Networks & Wireless Communication (AREA)
- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Radar Systems Or Details Thereof (AREA)
Abstract
The invention relates to a pulse responder gain controller implementation method, and the method achieves the automatic adjustment of the intensity of uplink and downlink signals of a responder through collecting the position information of an airplane. The method comprises the following steps: 1, designing a hardware control circuit, and achieving the separated adjustment of the uplink and downlink signals; 2, collecting the position information, and achieving the dynamic adjustment from position to attenuation. The method is used for the automatic adjustment of the intensity of uplink and downlink signals of the responder in a task according to the position of the airplane, is lower in cost and software development difficulty, and is great in application value.
Description
Technical field
What the present invention relates to a kind of pulse reply machine gain controller realizes method. Belong to control field of engineering technology.
Background technology
The task of pulse reply machine is mounted on all kinds space motion carrier, with ground radar collaborative work, increasing action distance, complete the real-time measurement to carrier flight track, distance and velocity information that precision is higher are provided, provide ballistic data for postmortem analysis simultaneously. Its ultimate principle is to receive the upward signal of ground radar, and time delay forwards, and ground radar measures radial distance by measuring time delay, passes through Tracking Angle Measurement, it is achieved Aerial vehicle position simultaneously. In task, it is installed on aircraft, aircraft flies according to desired trajectory, it is tracked by ground control station, aircraft and ground control station relative position are by as far as closely, from the near to the remote, and corresponding answering machine received signal strength is also ascending, descending, will cause that when relative distance diminishes answering machine is saturated, causing that downstream pulses string distorts, impact is followed the tracks of and range accuracy. Uncontrollable answering machine gain during due to aircraft flight, a pad value is estimated according only to radar equation, constant attenuation is carried out by fixed attenuator, decay can not be too big, too senior general causes the later upward signal that just can capture of answering machine, is badly in need of a kind of gain controller of exploitation, by dynamically adjusting answering machine uplink and downlink signals intensity, ensure that answering machine receives up to occur without saturated phenomenon, launch downstream signal intensity ground control station will not be caused saturated, thus support mission better.
In 2006,2007, in using aircraft certification ground radar precision, near boat is prompt, (radar points to vertical with aircraft trace, namely relative distance is minimum) due to answering machine saturated, cause that radar tracking is abnormal, near all boats are prompt, data all cannot be carried out data process, brings considerable influence to Radar Accuracy Testing.
The design of a kind of pulse reply machine gain controller of the present invention comprehensive multinomial Technology design, provides a kind of practicality, easy method for solving this problem.
Summary of the invention
The technical problem to be solved be for above-mentioned prior art provide a kind of pulse reply machine gain controller realize method, complete controller by hardware circuit design to build, realize up-downgoing intensity adjustments by gathering GPS position information, have that cost is low, function strong, the feature of favorable expandability.
This invention address that the technical scheme that the problems referred to above adopt is: a kind of pulse reply machine gain controller realize method, by gather aircraft-position information, it is achieved answering machine uplink and downlink signals intensity is automatically adjusted, and said method comprising the steps of:
The first step, design hardware control circuit, it is achieved the branch of uplink and downlink signals regulates
Described gain controller is made up of first annular device, the second circulator, up electrically controlled attenuator, downlink electrical controlled attenuator and single-chip microcomputer, the upward signal that antenna receives is by behind the input port of first annular device, by delivery outlet output to up electrically controlled attenuator, after up electrically controlled attenuator is decayed, it is added to the input port of the second circulator, enters answering machine by delivery outlet;After answering machine time delay, become downstream signal, behind the input port of the second circulator, by delivery outlet output to downlink electrical controlled attenuator, to the input port of first annular device after downlink electrical controlled attenuator is decayed, it is sent to antenna by delivery outlet, wherein up electrically controlled attenuator is connected with the I/O serial ports of single-chip microcomputer with downlink electrical controlled attenuator, completed to control by single-chip microcomputer, attenuation range 30dB, stepping is 1dB, and single-chip microcomputer is by the percent information of the up-downgoing way point position of storage in I2C bus read-write EEPROM with decay;
Second step, collection positional information, it is achieved position regulates to the dynamic of decay
The core of controller is adjustable attenuation strategy, adopts position to map the control method of decay,
The attenuation of electrically controlled attenuator controls foundation for radar equation:
Descending:
Wherein: S/N is radar receiver input individual pulse signal to noise ratio; Pb is answering machine output peak power; Gt is radar antenna gain; Gb is transponder aerial gain; λ is operation wavelength; B is receiver bandwidth; NFo is work effective noise coefficient; Lr is system loss; Lb is answering machine feeder loss; K is Boltzmann constant; T0 absolute temperature; R is distance;
Up:
Wherein: Sp is answering machine input power; Pt is radar transmission power; Lt is system loss.
By above-mentioned two radar equation, it is estimated that answering machine is when boat is prompt, the amount of decay is needed when uplink and downlink trigger, Waypoint is divided into center for initial point and grows from weak to strong and by by force to weak two sections, the latitude of two sections or longitude are divided by with up-downgoing pad value respectively, obtain ratio value, the GPS position information received obtains longitude and latitude value by parsing, every sub-value compares with last numerical value, it is multiplied by ratio value and obtains attenuation, more than 1, then control electrically controlled attenuator and increase the integer part of this attenuation, until decaying to setting value.
Compared with prior art, it is an advantage of the current invention that:
(1) hardware designs of present invention design has low cost feature.
(2) the attenuation control method of present invention design has the advantages that simply be easily achieved.
(3) present invention takes into account the design problem considering system extension.
Accompanying drawing explanation
Fig. 1 is the flow chart of the design of a kind of pulse reply machine gain controller of the present invention.
Fig. 2 be a kind of pulse reply machine gain controller of the present invention design in systematic schematic diagram.
Fig. 3 be a kind of pulse reply machine gain controller of the present invention design in routeing figure.
Fig. 4 be a kind of pulse reply machine gain controller of the present invention design in software flow pattern.
Wherein:
First annular device the 1, second circulator 2, up electrically controlled attenuator 3, downlink electrical controlled attenuator 4, single-chip microcomputer 5, EEPROM6.
Detailed description of the invention
Below in conjunction with accompanying drawing embodiment, the present invention is described in further detail.
The present invention relates to a kind of method that realizes of pulse reply machine gain controller, function is by gathering aircraft-position information, it is achieved answering machine uplink and downlink signals intensity is automatically adjusted, it is ensured that radar accuracy identification result, and detailed process is:
The first step, design hardware control circuit, it is achieved the branch of uplink and downlink signals regulates
This pulse reply machine uses transmitting-receiving common antenna, prevention at radio-frequency port is only one of which also, and owing to answering machine is different from the receiving sensitivity of ground radar, namely uplink and downlink signals intensity is unsuitable, must carrying out branch to control to can be only achieved optimal control results, system principle diagram is as shown in Figure 2.Controller is made up of 2 circulators, 2 30dB electrically controlled attenuators (1dB stepping) and STC89C52 single-chip microcomputer, circulator effect is to be easily separated by uplink downlink and combine, electrically controlled attenuator is used for controlling up-downgoing two paths of signals intensity, single-chip microcomputer, for receiving GPS position information, pad value by I/O port controlling electrically controlled attenuator by serial ports, reads and writes EEPROM information by I2C bus. The upward signal that antenna receives by, after 1# circulator 1 mouthful, by 2 mouthfuls of outputs, being added to 1 mouthful of 2# attenuator, enter answering machine by 2 mouthfuls after up electrically controlled attenuator is decayed; After answering machine time delay, become downstream signal, after 2 mouthfuls of 2# circulator, by 3 mouthfuls of outputs, to 3 mouthfuls of 1# circulator after downlink electrical controlled attenuator is decayed, be sent to antenna by 1 mouthful. Wherein the control of electrically controlled attenuator is completed by single-chip microcomputer, electrically controlled attenuator adopts I/O to control, attenuation range 30dB, stepping is 1dB, visible have 30 states, and 5 I/O ports of available single-chip microcomputer just can complete to control, and STC89C52 provides 32 I/O ports of user, conventional P0, P1, P2 port (totally 24 I/O ports) can meet needs, and has bigger redundancy. AT24C08 user stores the percent information of up-downgoing way point position and decay, it is simple to program judges, its primary data is read by serial ports. Whole hardware circuit design is clear, reasonable, controls simple, with low cost.
Second step, collection positional information, it is achieved position regulates to the dynamic of decay
The core of controller is adjustable attenuation strategy, and this patent adopts position to map the control method of decay, and reason has two: one, and Waypoint is rule design, with the relativeness of ground radar as it is shown on figure 3, inlet point and turning point are fixed position; Its two, aircraft is provided with the GPS system for accuracy evaluation, positional information obtain facility.
The attenuation of electrically controlled attenuator controls foundation for radar equation:
Descending:
Wherein: S/N is radar receiver input individual pulse signal to noise ratio; Pb is answering machine output peak power; Gt is radar antenna gain; Gb is transponder aerial gain; λ is operation wavelength; B is receiver bandwidth; NFo is work effective noise coefficient; Lr is system loss; Lb is answering machine feeder loss; K is Boltzmann constant; T0 absolute temperature; R is distance.
Up:
Wherein: Sp is answering machine input power; Pt is radar transmission power; Lt is system loss.
By above-mentioned two radar equation, it is possible to estimate answering machine when boat is prompt, decay 43dB(answering machine during uplink triggering, is needed to close on triggering state), for ensureing that surplus is decided to be decay 28dB; Downstream signal needs decay 55dB(ground radar to close on triggering state), for ensureing that surplus is decided to be decay 15dB. Waypoint is north-south or East and West direction, or longitude is constant namely, latitude is constant, utilizes this feature, for initial point, Waypoint is divided into two sections with center and (grows from weak to strong, by by force to weak), if longitude is constant, the latitude value of the section that grows from weak to strong is divided by with up-downgoing pad value respectively, obtains ratio value, this ratio value is exactly the thresholding that Single Chip Microcomputer (SCM) program controls decay, and its flow process is as shown in Figure 4. The GPS position information received obtains longitude and latitude value by parsing, every sub-value compares with last numerical value, it is multiplied by ratio value and obtains attenuation, more than 1, then control electrically controlled attenuator and increase the integer part of this attenuation, until decaying to setting value (up 28dB, descending 15dB), being put into afterwards by by force to weak section, control principle ibid, is only minimizing attenuation.
In addition to the implementation, present invention additionally comprises the technical scheme that other embodiments, all employing equivalents or equivalence substitute mode are formed, all should fall within the protection domain of the claims in the present invention.
Claims (2)
1. pulse reply machine gain controller realize a method, by gather aircraft-position information, it is achieved answering machine uplink and downlink signals intensity is automatically adjusted, it is characterised in that: said method comprising the steps of:
The first step, design hardware control circuit, it is achieved the branch of uplink and downlink signals regulates
Described gain controller is made up of first annular device (1), the second circulator (2), up electrically controlled attenuator (3), downlink electrical controlled attenuator (4) and single-chip microcomputer (5), the upward signal that antenna receives is by behind the input port of first annular device (1), by delivery outlet output to up electrically controlled attenuator (3), after up electrically controlled attenuator (3) is decayed, it is added to the input port of the second circulator (2), enters answering machine by delivery outlet, after answering machine time delay, become downstream signal, behind the input port of the second circulator (2), by delivery outlet output to downlink electrical controlled attenuator (4), to the input port of first annular device (1) after downlink electrical controlled attenuator (4) is decayed, it is sent to antenna by delivery outlet, wherein up electrically controlled attenuator (3) is connected with the I/O serial ports of downlink electrical controlled attenuator (4) with single-chip microcomputer (5), completed to control by single-chip microcomputer (5), attenuation range 30dB, stepping is 1dB, single-chip microcomputer (5) reads and writes EEPROM(6 by I2C bus) in the percent information of up-downgoing way point position and decay of storage,
Second step, collection positional information, it is achieved position regulates to the dynamic of decay
The core of controller is adjustable attenuation strategy, adopts position to map the control method of decay,
The attenuation of electrically controlled attenuator controls foundation for radar equation:
Descending:
Wherein: S/N is radar receiver input individual pulse signal to noise ratio; Pb is answering machine output peak power; Gt is radar antenna gain; Gb is transponder aerial gain; λ is operation wavelength; B is receiver bandwidth; NFo is work effective noise coefficient; Lr is system loss; Lb is answering machine feeder loss; K is Boltzmann constant; T0 absolute temperature; R is distance;
Up:
Wherein: Sp is answering machine input power; Pt is radar transmission power; Lt is system loss.
2. by above-mentioned two radar equation, it is estimated that answering machine is when boat is prompt, the amount of decay is needed when uplink and downlink trigger, Waypoint is divided into center for initial point and grows from weak to strong and by by force to weak two sections, the latitude of two sections or longitude are divided by with up-downgoing pad value respectively, obtain ratio value, the GPS position information received obtains longitude and latitude value by parsing, every sub-value compares with last numerical value, it is multiplied by ratio value and obtains attenuation, more than 1, then control electrically controlled attenuator and increase the integer part of this attenuation, until decaying to setting value.
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| CN201610098018.9A CN105676192B (en) | 2016-02-23 | 2016-02-23 | A kind of implementation method of pulse reply machine gain controller |
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| CN105676192B CN105676192B (en) | 2017-10-27 |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107271967A (en) * | 2016-11-26 | 2017-10-20 | 西南电子技术研究所（中国电子科技集团公司第十研究所） | pulse coherent transponder co-channel interference processing system |
| CN111404518A (en) * | 2020-02-25 | 2020-07-10 | 成都天奥测控技术有限公司 | Flexible and adjustable time delay comparison method and system |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH0331785A (en) * | 1989-06-29 | 1991-02-12 | Japan Radio Co Ltd | Gain control device |
| JPH09178843A (en) * | 1995-12-27 | 1997-07-11 | Nec Corp | Tactical air navigation device |
| CN104135299A (en) * | 2014-07-18 | 2014-11-05 | 中国电子科技集团公司第四十一研究所 | Two-channel two-stage variable frequency broadband receiver and automatic gain control method thereof |
| CN104330775A (en) * | 2014-10-17 | 2015-02-04 | 西安电子工程研究所 | Attenuation control method of digital STC attenuation circuit |
| CN104777470A (en) * | 2015-03-20 | 2015-07-15 | 中国科学院合肥物质科学研究院 | Circuit for expanding range of pulse laser short-range dynamic gain |
-
2016
- 2016-02-23 CN CN201610098018.9A patent/CN105676192B/en not_active Expired - Fee Related
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH0331785A (en) * | 1989-06-29 | 1991-02-12 | Japan Radio Co Ltd | Gain control device |
| JPH09178843A (en) * | 1995-12-27 | 1997-07-11 | Nec Corp | Tactical air navigation device |
| CN104135299A (en) * | 2014-07-18 | 2014-11-05 | 中国电子科技集团公司第四十一研究所 | Two-channel two-stage variable frequency broadband receiver and automatic gain control method thereof |
| CN104330775A (en) * | 2014-10-17 | 2015-02-04 | 西安电子工程研究所 | Attenuation control method of digital STC attenuation circuit |
| CN104777470A (en) * | 2015-03-20 | 2015-07-15 | 中国科学院合肥物质科学研究院 | Circuit for expanding range of pulse laser short-range dynamic gain |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107271967A (en) * | 2016-11-26 | 2017-10-20 | 西南电子技术研究所（中国电子科技集团公司第十研究所） | pulse coherent transponder co-channel interference processing system |
| CN107271967B (en) * | 2016-11-26 | 2020-03-31 | 西南电子技术研究所（中国电子科技集团公司第十研究所） | Pulse coherent transponder same-frequency interference processing system |
| CN111404518A (en) * | 2020-02-25 | 2020-07-10 | 成都天奥测控技术有限公司 | Flexible and adjustable time delay comparison method and system |
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