CN105676192B - A kind of implementation method of pulse reply machine gain controller - Google Patents
A kind of implementation method of pulse reply machine gain controller Download PDFInfo
- Publication number
- CN105676192B CN105676192B CN201610098018.9A CN201610098018A CN105676192B CN 105676192 B CN105676192 B CN 105676192B CN 201610098018 A CN201610098018 A CN 201610098018A CN 105676192 B CN105676192 B CN 105676192B
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- electrically controlled
- controlled attenuator
- answering machine
- attenuation
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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 present invention relates to a kind of realization of pulse reply machine gain controller, by gathering aircraft-position information, realize that answering machine uplink and downlink signals intensity is automatically adjusted, the described method comprises the following steps：Step 1: design hardware control circuit, realizes the branch regulation of uplink and downlink signals；Step 2: collection positional information, realizes position to the dynamic regulation of decay.Answering machine uplink and downlink signals intensity is automatically adjusted automatically according to aircraft position in task using the method for the present invention, cost and software development difficulty are low, with extremely strong application value.
Description
Technical field
The present invention relates to a kind of implementation method of pulse reply machine gain controller.Belong to control field of engineering technology.
Background technology
The task of pulse reply machine is mounted on all kinds space motion carrier, is cooperated with ground radar, is increased
Plus operating distance, the real-time measurement to carrier flight track is completed there is provided precision higher distance and velocity information, while being thing
Post analysis provide ballistic data.Its general principle is the upward signal for receiving ground radar, and the forwarding that is delayed, ground radar passes through
Measurement time delay measures radial distance, while by Tracking Angle Measurement, realizing Aerial vehicle position.In task, it is installed on aircraft,
Aircraft is flown according to desired trajectory, and ground control station is tracked to it, and aircraft is with ground control station relative position by remote
To closely, from the near to the remote, corresponding answering machine received signal strength is also ascending, descending, and hour is become in relative distance
Answering machine saturation will be caused, cause downstream pulses string to distort, influence tracking and range accuracy.It is uncontrollable during due to aircraft flight
Answering machine gain, a pad value is estimated according only to radar equation, carries out constant attenuation by fixed attenuator, decay can not be too
Greatly, too senior general causes answering machine is later can just capture upward signal, is badly in need of a kind of gain controller of exploitation, passes through dynamic adjustment
Answering machine uplink and downlink signals intensity, come ensure answering machine receive it is up occur without saturated phenomenon, transmitting downstream signal intensity will not
Cause ground control station saturation, so that preferably support mission.
In 2006,2007, in using aircraft certification ground radar precision, near boat victory（Radar point to
Aircraft trace is vertical, i.e., relative distance is minimum）Due to answering machine saturation, cause radar tracking abnormal, the prompt data nearby of all boats
Data processing can not be carried out, considerable influence is brought to Radar Accuracy Testing.
The present invention integrates a kind of design of pulse reply machine gain controller of multinomial Technology design, to solve this problem
A kind of practical, easy method is provided.
The content of the invention
The technical problems to be solved by the invention are to provide a kind of pulse reply machine gain control for above-mentioned prior art
The implementation method of device, completes controller by hardware circuit design and builds, up-downgoing intensity is realized by gathering GPS position information
Regulation, with cost is low, function strong, favorable expandability the characteristics of.
The present invention the used technical scheme that solves the above problems is：A kind of realization side of pulse reply machine gain controller
Method, by gathering aircraft-position information, realizes that answering machine uplink and downlink signals intensity is automatically adjusted, and methods described includes following step
Suddenly：
The first step, design hardware control circuit, realize the branch regulation of uplink and downlink signals
The gain controller by first annular device, the second circulator, up electrically controlled attenuator, descending electrically controlled attenuator and
Behind input port of the upward signal that singlechip group is received into, antenna by first annular device, exported by delivery outlet to up electricity
Controlled attenuator, the input port of the second circulator is added to after the decay of up electrically controlled attenuator, enters answering machine by delivery outlet；
After answering machine delay, it is changed into downstream signal, behind the input port of the second circulator, exports to downlink electrical to adjust by delivery outlet and decay
Device, arrives the input port of first annular device, antenna is sent to by delivery outlet, wherein up electricity after decaying through descending electrically controlled attenuator
Controlled attenuator and descending electrically controlled attenuator are connected with the I/O serial ports of single-chip microcomputer, are completed to control by single-chip microcomputer, attenuation range 30dB,
Stepping is 1dB, and single-chip microcomputer reads and writes the up-downgoing way point position stored in EEPROM and the percent information decayed by I2C buses；
Second step, collection positional information, realize position to the dynamic regulation of decay
The core of controller is adjustable attenuation strategy, and the control method of decay is mapped using position,
The attenuation of electrically controlled attenuator controls foundation to be radar equation：
It is descending：
Wherein：S/N is radar receiver input individual pulse signal to noise ratio；Pb is that answering machine exports 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 system
Number；Lr is system loss；Lb is answering machine feeder loss；K is Boltzmann constant；T0 absolute temperature；R is distance；
It is 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 navigating prompt, need to decline when uplink and downlink are triggered
The amount subtracted, Waypoint is divided into by origin of center and grown from weak to strong and by by force to weak two sections, by the latitude of two sections
Degree or longitude be divided by respectively with up-downgoing pad value, obtain ratio value, the GPS position information received by parsing obtain through
Degree and latitude value, are compared, the ratio of being multiplied by is worth to attenuation, more than 1 per sub-value with last numerical value, then control electricity to adjust and decline
Subtracting device increases the integer part of the attenuation, until decaying to setting value.
Compared with prior art, the advantage of the invention is that：
（1）The hardware design that the present invention is designed has inexpensive feature.
（2）The characteristics of decay amount control method that the present invention is designed has simple be easily achieved.
（3）The present invention takes into account the design problem for considering system extension.
Brief description of the drawings
Fig. 1 is a kind of flow chart of the design of pulse reply machine gain controller of the invention.
Fig. 2 is systematic schematic diagram in a kind of design of pulse reply machine gain controller of the invention.
Fig. 3 is routeing figure in a kind of design of pulse reply machine gain controller of the invention.
Fig. 4 is software flow pattern in a kind of design of pulse reply machine gain controller of the invention.
Wherein：
First annular device 1, the second circulator 2, up electrically controlled attenuator 3, descending electrically controlled attenuator 4, single-chip microcomputer 5,
EEPROM6。
Embodiment
The present invention is described in further detail below in conjunction with accompanying drawing embodiment.
The present invention relates to a kind of implementation method of pulse reply machine gain controller, function is to be believed by gathering aircraft position
Breath, realizes that answering machine uplink and downlink signals intensity is automatically adjusted, it is ensured that radar accuracy identification result, detailed process is：
The first step, design hardware control circuit, realize the branch regulation of uplink and downlink signals
The pulse reply machine uses transmitting-receiving common antenna, prevention at radio-frequency port also only one of which, due to answering machine and ground radar
Receiving sensitivity it is different, i.e. uplink and downlink signals intensity is not suitable, it is necessary to carries out branch control and can be only achieved optimum control effect
Really, system principle diagram is as shown in Figure 2.Controller is by 2 circulators, 2 30dB electrically controlled attenuators（1dB steppings）With
STC89C52 singlechip groups are into circulator effect is that uplink downlink is separated and combined, and electrically controlled attenuator is used to control
Up-downgoing two paths of signals intensity, single-chip microcomputer is used to receive GPS position information by serial ports, is adjusted and decayed by I/O port controllings electricity
The pad value of device, EEPROM information is read and write by I2C buses.After the upward signal that antenna is received is by 1 mouthful of 1# circulators, pass through
2 mouthfuls of outputs, 1 mouthful of 2# attenuators is added to after the decay of up electrically controlled attenuator, enters answering machine by 2 mouthfuls；Answering machine is prolonged
Shi Hou, is changed into downstream signal, after 2 mouthfuls of 2# circulators, by 3 mouthfuls of outputs, and 1# rings are arrived after decaying through descending electrically controlled attenuator
3 mouthfuls of shape device, antenna is sent to by 1 mouthful.The control of wherein electrically controlled attenuator is completed by single-chip microcomputer, and electrically controlled attenuator uses I/
O is controlled, and attenuation range 30dB, stepping is 1dB, it is seen that have 30 states, and control can be completed with 5 I/O ports of single-chip microcomputer
System, STC89C52 provides user 32 I/O ports, conventional P0, P1, P2 port（Totally 24 I/O ports）Needs can be met,
And have larger redundancy.AT24C08 user storage up-downgoing way point position and the percent information of decay, are easy to program to judge, at the beginning of it
Beginning data are write by serial ports.Whole hardware circuit design is clear, reasonable, and control is simple, with low cost.
Second step, collection positional information, realize position to the dynamic regulation of decay
The core of controller is adjustable attenuation strategy, and this patent maps the control method of decay using position, and reason has two：
First, Waypoint designs for rule, the relativeness with ground radar is as shown in figure 3, inlet point and turning point are fixed bit
Put；Second, being provided with the gps system for accuracy evaluation on aircraft, positional information is facilitated.
The attenuation of electrically controlled attenuator controls foundation to be radar equation：
It is descending：
Wherein：S/N is radar receiver input individual pulse signal to noise ratio；Pb is that answering machine exports 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 system
Number；Lr is system loss；Lb is answering machine feeder loss；K is Boltzmann constant；T0 absolute temperature；R is distance.
It is 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 needs the 43dB that decays when navigating prompt during uplink triggering
（Answering machine closes on triggering state）, to ensure that surplus is set to decay 28dB；Downstream signal needs the 55dB that decays（Ground radar closes on
Triggering state）, to ensure that surplus is set to decay 15dB.Waypoint is north-south or East and West direction, otherwise that is, longitude is constant, or
Latitude is constant, and using this feature, Waypoint is divided into two sections by origin of center（Grow from weak to strong, by by force to
It is weak）, if longitude is constant, and the latitude value for the section that grows from weak to strong is divided by with up-downgoing pad value respectively, ratio value is obtained, this
Ratio value is exactly the thresholding of SCM program control decay, and its flow is as shown in Figure 4.The GPS position information received passes through solution
Analysis obtains longitude and latitude value, is compared per sub-value with last numerical value, the ratio of being multiplied by is worth to attenuation, more than 1, then controls
Electrically controlled attenuator processed increases the integer part of the attenuation, until decaying to setting value（Up 28dB, descending 15dB）, afterwards
Into by by force to weak section, control principle ibid, only reduces attenuation.
In addition to the implementation, present invention additionally comprises have other embodiment, all use equivalent transformation or equivalent replacements
The technical scheme that mode is formed, all should fall within the scope of the hereto appended claims.
Claims (1)
1. a kind of implementation method of pulse reply machine gain controller, by gathering aircraft-position information, is realized above and below answering machine
Row signal intensity is automatically adjusted, it is characterised in that：It the described method comprises the following steps：
The first step, design hardware control circuit, realize the branch regulation of uplink and downlink signals
The gain controller is by first annular device（1）, the second circulator（2）, up electrically controlled attenuator（3）, downlink electrical adjust decline
Subtract device（4）And single-chip microcomputer（5）Composition, the upward signal that antenna is received passes through first annular device（1）Input port after, pass through first
Circulator（1）Delivery outlet export to up electrically controlled attenuator（3）, by up electrically controlled attenuator（3）Second is added to after decay
Circulator（2）Input port, pass through the second circulator（2）Delivery outlet enter answering machine；After answering machine delay, it is changed into descending letter
Number, through the second circulator（2）Input port after, pass through the second circulator（2）Delivery outlet is exported to descending electrically controlled attenuator（4）,
Through descending electrically controlled attenuator（4）First annular device is arrived after decay（1）Input port, pass through first annular device（1）Delivery outlet hair
Antenna is sent to, wherein up electrically controlled attenuator（3）With descending electrically controlled attenuator（4）With single-chip microcomputer（5）I/O serial ports be connected, by
Single-chip microcomputer（5）Complete control, up electrically controlled attenuator（3）With descending electrically controlled attenuator（4）Attenuation range be 30dB, stepping is
1dB, single-chip microcomputer（5）EEPROM is read and write by I2C buses（6）Up-downgoing way point position and the percent information decayed of middle storage；
Second step, collection positional information, realize position to the dynamic regulation of decay
The core of controller is adjustable attenuation strategy, and the control method of decay is mapped using position,
The attenuation of electrically controlled attenuator controls foundation to be radar equation：
It is descending：
Wherein：S/N is radar receiver input individual pulse signal to noise ratio；Peak power is exported for answering machine；For radar
Antenna gain；For transponder aerial gain；λ is operation wavelength；B is receiver bandwidth；For work effective noise system
Number；For system loss；For answering machine feeder loss；K is Boltzmann constant；For absolute temperature；R is distance；
It is up：
Wherein：For answering machine input power；For radar transmission power；For system loss；
By above-mentioned two radar equation, it is estimated that answering machine is when navigating prompt, need what is decayed when uplink and downlink are triggered
Amount, Waypoint is divided into by origin of center and grown from weak to strong and by by force to weak two sections, by the latitude of two sections or
Longitude is divided by with upstream attenuation value and downstream attenuation values respectively, obtains ratio value, and the GPS position information received passes through parsing
Longitude and latitude value are obtained, the longitude and latitude value obtained every time is compared with last numerical value, and comparative result is multiplied by ratio
Attenuation is worth to, if attenuation is more than 1, control electrically controlled attenuator increases the integer part of the 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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| 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 |
| CN111404518B (en) * | 2020-02-25 | 2023-04-14 | 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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| JP2714153B2 (en) * | 1989-06-29 | 1998-02-16 | 日本無線株式会社 | Gain control device |
| JP2778564B2 (en) * | 1995-12-27 | 1998-07-23 | 日本電気株式会社 | Takan equipment |
| CN104135299B (en) * | 2014-07-18 | 2016-10-19 | 中国电子科技集团公司第四十一研究所 | A kind of dual pathways two-stage frequency conversion broadband receiver and auto 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 |
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