CN110570711B - Satellite alignment strategy of satellite communication simulation training system - Google Patents

Satellite alignment strategy of satellite communication simulation training system Download PDF

Info

Publication number
CN110570711B
CN110570711B CN201910857754.1A CN201910857754A CN110570711B CN 110570711 B CN110570711 B CN 110570711B CN 201910857754 A CN201910857754 A CN 201910857754A CN 110570711 B CN110570711 B CN 110570711B
Authority
CN
China
Prior art keywords
satellite
training system
alignment
antenna
simulation training
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.)
Active
Application number
CN201910857754.1A
Other languages
Chinese (zh)
Other versions
CN110570711A (en
Inventor
李志明
从舒凯
杨敏
张应宪
张康康
王飞
汪家昌
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.)
Runze Kingsong Beijing Science And Technology Development Co ltd
Jiangsu Junzhishi Intelligent Technology Co ltd
Original Assignee
Runze Kingsong Beijing Science And Technology Development Co ltd
Jiangsu Junzhishi Intelligent Technology Co ltd
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 Runze Kingsong Beijing Science And Technology Development Co ltd, Jiangsu Junzhishi Intelligent Technology Co ltd filed Critical Runze Kingsong Beijing Science And Technology Development Co ltd
Priority to CN201910857754.1A priority Critical patent/CN110570711B/en
Publication of CN110570711A publication Critical patent/CN110570711A/en
Application granted granted Critical
Publication of CN110570711B publication Critical patent/CN110570711B/en
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Images

Classifications

    • G—PHYSICS
    • G09—EDUCATION; CRYPTOGRAPHY; DISPLAY; ADVERTISING; SEALS
    • G09B—EDUCATIONAL OR DEMONSTRATION APPLIANCES; APPLIANCES FOR TEACHING, OR COMMUNICATING WITH, THE BLIND, DEAF OR MUTE; MODELS; PLANETARIA; GLOBES; MAPS; DIAGRAMS
    • G09B9/00—Simulators for teaching or training purposes

Landscapes

  • Engineering & Computer Science (AREA)
  • Theoretical Computer Science (AREA)
  • Business, Economics & Management (AREA)
  • Physics & Mathematics (AREA)
  • Educational Administration (AREA)
  • Educational Technology (AREA)
  • General Physics & Mathematics (AREA)
  • Radio Relay Systems (AREA)

Abstract

The invention discloses a satellite communication simulation training system and a satellite alignment strategy thereof, which are used for simulating the satellite alignment process of actual equipment, wherein the system comprises a main control unit, a sensor unit, a display unit, a motor unit, an antenna hardware unit and a power supply unit; the strategy comprises the following steps: initializing a simulation training system, and calculating a theoretical satellite alignment direction according to the position information of the existing antenna and a quasi-alignment satellite; an operator carries out satellite alignment operation on the satellite directions according to a theory, and if the satellite alignment operation is completed, the simulation training system enters an effect evaluation stage; and adding a fading factor to simulate a satellite loss process in actual equipment, executing a satellite loss judgment module, and reminding an operator to aim at the satellite again if the satellite is lost. The satellite communication simulation training system and the satellite aiming strategy thereof provided by the invention have the advantages of capability of simulating the satellite aiming process of actual equipment, simple strategy design, stability, reliability and the like, can solve the key problem in the simulation training system, and have very important application value.

Description

Satellite alignment strategy of satellite communication simulation training system
Technical Field
The invention relates to the field of satellite communication simulation training, in particular to a satellite communication simulation training system and a satellite alignment strategy thereof.
Background
In recent years, satellite communication has been widely used in the commercial and military fields due to the advantages of wide coverage, high communication quality, convenient implementation of multiple access connection, and the like, and has important significance for national security and economic construction. The power resource of the satellite is often very precious due to the limitation of factors such as volume, weight and the like; meanwhile, in consideration of the requirements of miniaturization, portability, cost saving and the like, the ground terminal often has a large restriction on the transmitted power and the size of the antenna, so that the satellite communication system is usually a power-limited system. However, satellite communication is currently being developed toward large system capacity, miniaturization of terminals, and improvement of mobile communication capability.
After the practical application of satellite communication equipment, the primary task faced by equipment operators is to become familiar with various types of satellite equipment as soon as possible so as to play a role in the practical application as soon as possible, and the playing of the practical role depends to a great extent on the training and operation of the equipment organization, and the familiarity with the operation procedures and performance of various types of equipment. However, since the operation and training of the actual equipment causes severe loss of the satellite equipment, and is limited by the actual conditions, sites, expenses, etc. of each unit of use, the satellite equipment in the military field also involves core secrets, and the frequency and intensity of use and training of various types of equipment need to be strictly controlled.
In the process of starting a satellite communication system, the antenna-to-satellite is an important step, however, as the problems of limited site environment, serious equipment loss, limited expenditure, incapability of guaranteeing training strength and the like exist in the actual assembly operation, the operation training of the antenna-to-satellite in the actual assembly is difficult to complete, so that the satellite communication system is difficult to play in the actual application. Therefore, the training and operation of the satellite communication equipment are not usually performed directly on the real equipment, but are performed on a corresponding training simulation system, and after the performance of the equipment is trained and familiar repeatedly, the real equipment is actually operated.
However, the training simulator in the traditional sense is usually only the accumulation of hardware, and is supplemented with simple software, which can only provide training and operation simulation at a low level, and the research on related simulation training algorithms is less, such as star strategy, group training algorithm, etc., so that the application range is limited. Therefore, by researching the satellite aiming strategy, the method has important significance for solving the problems of complex operation, redundancy and the like of the traditional simulation satellite antenna system.
Disclosure of Invention
The purpose of the invention is as follows: the invention aims to solve the technical problems of high risk, high cost, uncontrollable operation and the like of the existing satellite communication system on satellite alignment operation of actual equipment, adopts a satellite communication simulation training system and a satellite alignment strategy thereof, has the advantages of capability of simulating the satellite alignment process of the actual equipment, simple strategy design, stability, reliability and the like, can solve the key problem in the simulation training system, and has very important application value.
The technical scheme is as follows: in order to solve the problems in the prior art, the invention adopts the following technical scheme:
a satellite communication simulation training system is characterized in that: the system comprises a main control unit, a sensor unit connected with the main control unit, a display unit, a motor unit, an antenna hardware unit and a power supply unit; the power supply unit supplies power to other unit modules in the system, the sensor unit is used for measuring position information between the antenna hardware unit and a satellite to be aligned in real time, the main control unit is used for detecting parameter information transmitted by the sensor unit in real time, updating and calculating azimuth angle and pitch angle theoretical values, controlling the motor unit to work, and controlling the display unit to display satellite alignment effects and satellite alignment state information, and the motor unit is used for driving the antenna hardware unit to adjust the azimuth angle and the pitch angle of the antenna.
The invention also discloses a satellite alignment strategy of the satellite communication simulation training system, which is characterized in that: the method comprises the following steps:
the method comprises the steps that firstly, a simulation training system is initialized, the beacon frequency of an antenna is set as the carrier frequency of a quasi-alignment satellite, and the pitch angle and the azimuth angle theoretical value of the antenna relative to the quasi-alignment satellite are calculated according to the longitude of the quasi-alignment satellite and the longitude and latitude of the antenna;
secondly, operating personnel perform satellite alignment operation on the satellite azimuth according to the theory calculated in the first step, and if the satellite alignment operation is completed, the simulation training system enters an effect evaluation stage;
step three, after the satellite operation of the personnel is evaluated in the step two, a satellite loss judgment module is executed: if the satellite is judged not to be lost, the simulation training system continues to evaluate the satellite aligning effect, and if the satellite is judged to be lost, the simulation training system reminds the operator to align the satellite again and returns to the step one.
Preferably, in the first step, the quasi-alignment satellite is set as an orbiting stationary satellite, and the theoretical azimuth angle of the antenna relative to the quasi-alignment satellite is determined
Figure BDA0002198273800000021
And theoretical pitch angle
Figure BDA0002198273800000022
Comprises the following steps:
Figure BDA0002198273800000023
Figure BDA0002198273800000024
wherein,
Figure BDA0002198273800000025
the variable represents the difference in longitude, θ, between the antenna and the point of vertical projection of the satellite to be aligned on the earth's surface1Indicates the latitude, h, of the location of the antennaEIndicating track height, RERepresenting the radius of the earth.
Preferably, in the second step, the flow of the effect evaluation stage is as follows:
the operator follows the azimuth angle calculated in the first step
Figure BDA0002198273800000026
Pitch angle
Figure BDA0002198273800000027
Theoretical value, after the operation of the satellite, the actual azimuth angle and the actual pitch angle of the antenna are respectively
Figure BDA0002198273800000028
And
Figure BDA0002198273800000029
simulated training system based on the increase to stars in the following equationBeneficial Δ G assessment on star effect:
Figure BDA00021982738000000210
where deltaa is the antenna gain of the analog training system,
Figure BDA0002198273800000031
and
Figure BDA0002198273800000032
in order to realize satellite alignment loss, if satellite alignment gain delta G exceeds a preset value, satellite alignment is effective; otherwise, the current satellite-to-satellite operation is considered to have an error.
Preferably, the antenna hardware unit of the analog training system adopts a multi-beam antenna, Δ a is 35.2dB, and if the satellite gain Δ G exceeds a preset value of 25dB, the satellite is valid; otherwise, the current satellite-to-satellite operation is considered to have an error.
Preferably, in the third step, a fading factor is added to simulate a satellite loss process in the actual device, and the determination process of the satellite loss determination module is as follows:
if the satellite aligning gain delta G' after the fading factor is added is lower than 0.6 times of the satellite aligning gain delta G, the simulation training system considers that the situation is in a satellite losing state and performs timing, and if the timing time lasts for more than 50s, the antenna is considered to be in the satellite losing state and needs to be aligned again; if the timing time is less than 50s, the antenna is considered to be only in short shielding, and the satellite does not need to be aimed again.
Preferably, the gain Δ G' to the satellite after adding the fading factor is
ΔG′＝ΔG-|Δr|dB
Wherein, Δ G is the satellite gain before adding the fading factor, and Δ r follows Rayleigh distribution
Figure BDA0002198273800000033
The mean value is 0, the variance is sigma, and the distribution is a classical channel fading model in satellite communication and is used for simulating a satellite loss process in actual equipment.
Has the advantages that:
1. the invention provides a satellite communication simulation training system and a satellite aiming strategy thereof, which are used for researching the flows of an initial satellite aiming stage, an effect evaluation stage, satellite loss judgment and the like in the simulation system, so that the satellite communication simulation training system can truly simulate the satellite aiming process of actual equipment;
2. the satellite communication simulation training system and the satellite aiming strategy thereof provided by the invention have the advantages of capability of simulating the satellite aiming process of actual equipment, simple strategy design, stability, reliability and the like, can solve the key problems in the simulation training system, and have very important application value;
3. the achievement of the invention can be applied to application scenes of various satellite communication system operators for daily satellite communication simulation training and assessment and the like, and is particularly suitable for situations that relevant departments lack satellite communication actual equipment or training fields are limited and the like.
Drawings
FIG. 1 is a schematic flow chart of the satellite-to-satellite strategy of the satellite communication simulation training system of the present invention;
FIG. 2 is a schematic diagram of the geometry of a quasi-satellite S and an antenna A in a simulated training system;
fig. 3 is a schematic diagram of a geometric relationship decomposition between a quasi-satellite S and an antenna a in a simulated training system.
Detailed Description
The preferred embodiments of the present invention will be described in conjunction with the accompanying drawings, and it will be understood that they are described herein for the purpose of illustration and explanation and not limitation.
The invention discloses a satellite communication simulation training system of a satellite strategy, which comprises a main control unit, a sensor unit, a display unit, a motor unit, an antenna hardware unit and a power supply unit, wherein the main control unit is used for controlling the main control unit to control the main control unit; the power supply unit supplies power to other unit modules in the system, the sensor unit measures position information between the antenna hardware unit and the satellite to be aligned in real time, the main control unit detects and updates parameter information transmitted by the sensor unit in real time, an azimuth angle and a pitch angle theoretical value are calculated, the motor unit is controlled to work, the display unit displays satellite alignment effect and satellite alignment state information, and the motor unit works to drive the antenna hardware unit to adjust the corresponding azimuth angle and pitch angle.
The satellite alignment strategy of the satellite communication simulation training system is developed around a satellite alignment process of a simulation satellite antenna, and comprises an initial satellite alignment stage, a satellite alignment evaluation stage, satellite loss judgment and other processes, wherein the satellite alignment strategy specifically comprises the following steps as shown in figure 1:
the method comprises the steps that firstly, a simulation training system is initialized, the beacon frequency of an antenna is set as the carrier frequency of a quasi-alignment satellite, and the theoretical values of a pitch angle and an azimuth angle are calculated according to the longitude of the quasi-alignment satellite and the longitude and latitude of the antenna;
fig. 2 is a schematic view of the geometry relationship between the antenna a and the satellite S to be aligned. Wherein, the point O is the center of the earth sphere, and the intersection point of the longitude line passing through the point A of the antenna and the equator is the point B
Figure BDA0002198273800000041
And theta1Longitude and latitude representing the location of antenna a; s 'is the vertical projection of the satellite S to be aligned on the earth' S surface with a longitude of
Figure BDA0002198273800000042
If it is used
Figure BDA0002198273800000043
The variable represents the longitude difference between the antenna A and the projection point S', there is
Figure BDA0002198273800000044
For simplicity, FIG. 2 may be decomposed into coordinate systems as shown in FIG. 3.
As shown in fig. 3, passing point a makes an arc pointing to point B
Figure BDA0002198273800000045
Is tangent to AQ, passing through point A as an arc pointing to point S
Figure BDA0002198273800000046
A tangent line AP of
Figure BDA0002198273800000047
Representing the azimuth of the antenna a relative to the satellite S to be aimed at,
Figure BDA0002198273800000048
the elevation angle of the antenna a relative to the intended satellite S is shown.
Considering that the satellite to be aligned by the analog training system is a stationary orbit satellite, the triangle ABS ' in fig. 3 is a spherical right-angle triangle (where < ABS ' > is 90 °), and a is < AOS ', then there are:
Figure BDA0002198273800000049
Figure BDA00021982738000000410
Figure BDA00021982738000000411
Figure BDA00021982738000000412
the simultaneous formation of the above formulas (1), (3) and (4)
Figure BDA0002198273800000051
Thus, the theoretical azimuth is:
Figure BDA0002198273800000052
an extension AA 'of OA is drawn on FIG. 3, and a perpendicular line drawn through point S as an extension of OA intersects point A'. Therefore, it can be seen that AP is parallel to SA ', and since the triangle AA' S is a right triangle, there are:
Figure BDA0002198273800000053
wherein R isEIs the radius of the earth, hEIs the height of the simulated pair of stars.
Substituting equation (2) into (7) yields:
Figure BDA0002198273800000054
in the simulation training system, if the quasi-alignment satellite is a geostationary orbit satellite, its orbit height hE35860km, radius of the earth RE6378km, then
Figure BDA0002198273800000055
The theoretical pitch angle of the antenna, which is substituted into equation (8), is:
Figure BDA0002198273800000056
secondly, operating personnel perform satellite alignment operation on the satellite azimuth according to the theory calculated in the first step, and if the satellite alignment operation is completed, the simulation training system enters an effect evaluation stage, wherein the evaluation flow is as follows:
the operator follows the azimuth angle calculated in the first step
Figure BDA0002198273800000057
Pitch angle
Figure BDA0002198273800000058
Theoretical value, after the operation of the satellite, the actual azimuth angle and the actual pitch angle of the antenna are respectively
Figure BDA0002198273800000059
And
Figure BDA00021982738000000510
the sensor unit is to
Figure BDA00021982738000000511
And
Figure BDA00021982738000000512
the value is transmitted back to the main control unit of the simulation training system;
when the simulation training system receives the azimuth angle of the actual antenna
Figure BDA00021982738000000513
Angle of elevation
Figure BDA00021982738000000514
The simulated training system then evaluates the satellite effects according to the satellite gain Δ G in the following equation:
Figure BDA00021982738000000515
wherein, Delta A is the antenna gain of the analog training system, and the analog training system considers that the antenna is a multi-beam antenna, then Delta A is 35.2dB,
Figure BDA0002198273800000061
and
Figure BDA0002198273800000062
loss for satellite;
if the satellite-to-satellite gain exceeds a preset value of 25dB, the satellite-to-satellite effect is achieved; otherwise, the current satellite-to-satellite operation is considered to have an error.
And step three, after the satellite alignment operation of the personnel is evaluated in the step two, executing a satellite loss judgment module, if the satellite is judged not to be lost, simulating the training system to continue evaluating the satellite alignment effect, and if the satellite is judged to be lost, reminding the operator to align the satellite again, and returning to the step one.
In the third step, a fading factor is added to simulate a satellite loss process in actual equipment, and the judgment flow of the satellite loss judgment module is as follows:
if the satellite gain Δ G' after the fading factor is added is lower than 0.6 times of the satellite gain Δ G in the step two, the simulation training system considers that the situation is a satellite losing state, and performs timing, if the timing time lasts for more than 50s, the antenna is considered to be in the satellite losing state, and the satellite needs to be aligned again, otherwise, if the timing time is less than 50s, the antenna is considered to be only in short shielding, and the satellite does not need to be aligned again.
Wherein, the satellite gain delta G' after the fading factor is added is
ΔG′＝ΔG-|Δr|dB
Wherein, Δ G is the satellite gain after adding the fading factor, and Δ r follows Rayleigh distribution
Figure BDA0002198273800000063
The mean value is 0, the variance is sigma, and the distribution is a classical channel fading model in satellite communication and is used for simulating a satellite loss process in actual equipment.
Finally, it should be noted that: although the present invention has been described in detail with reference to the foregoing embodiments, it will be apparent to those skilled in the art that changes may be made in the embodiments and/or equivalents thereof without departing from the spirit and scope of the invention. Any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.

Claims (5)

1. A satellite alignment strategy of a satellite communication simulation training system is characterized in that: the method comprises the following steps:
the method comprises the steps that firstly, a simulation training system is initialized, the beacon frequency of an antenna is set as the carrier frequency of a quasi-alignment satellite, and the pitch angle and the azimuth angle theoretical value of the antenna relative to the quasi-alignment satellite are calculated according to the longitude of the quasi-alignment satellite and the longitude and latitude of the antenna;
secondly, operating personnel perform satellite alignment operation on the satellite azimuth according to the theory calculated in the first step, and if the satellite alignment operation is completed, the simulation training system enters an effect evaluation stage;
step three, after the satellite operation of the personnel is evaluated in the step two, a satellite loss judgment module is executed: if the satellite is judged not to be lost, the simulation training system continues to evaluate the satellite aiming effect, and if the satellite is judged to be lost, the simulation training system reminds the operator to aim the satellite again, and the same procedure is followed as the step one;
wherein, the process of the effect evaluation stage in the step two is as follows:
the operator follows the azimuth angle calculated in the first step
Figure FDA0002538913170000011
Pitch angle
Figure FDA0002538913170000012
Theoretical value, after the operation of the satellite, the actual azimuth angle and the actual pitch angle of the antenna are respectively
Figure FDA0002538913170000013
And
Figure FDA0002538913170000014
the simulated training system evaluates the satellite-to-satellite effect according to the satellite-to-satellite gain Δ G in the following equation:
Figure FDA0002538913170000015
where deltaa is the antenna gain of the analog training system,
Figure FDA0002538913170000016
and
Figure FDA0002538913170000017
in order to realize satellite alignment loss, if satellite alignment gain delta G exceeds a preset value, satellite alignment is effective; otherwise, the current satellite-to-satellite operation is considered to have an error.
2. The satellite-directed strategy of a satellite communication simulation training system of claim 1, wherein: in the first step, the quasi-alignment satellite is set as an orbital geostationary satellite, and the theoretical azimuth angle of the antenna relative to the quasi-alignment satellite
Figure FDA0002538913170000018
And theoretical pitch angle
Figure FDA0002538913170000019
Comprises the following steps:
Figure FDA00025389131700000110
Figure FDA00025389131700000111
wherein,
Figure FDA00025389131700000112
the variable represents the difference in longitude, θ, between the antenna and the point of vertical projection of the satellite to be aligned on the earth's surface1Indicates the latitude, h, of the location of the antennaEIndicating track height, RERepresenting the radius of the earth.
3. The satellite-directed strategy of a satellite communication simulation training system of claim 1, wherein: if the antenna hardware unit of the analog training system adopts a multi-beam antenna, the delta A is 35.2dB, and if the satellite gain delta G exceeds a preset value of 25dB, the satellite is effective; otherwise, the current satellite-to-satellite operation is considered to have an error.
4. The satellite-directed strategy of a satellite communication simulation training system of claim 1, wherein: in the third step, a fading factor is added to simulate a satellite loss process in actual equipment, and a judgment flow of the satellite loss judgment module is as follows:
if the satellite aligning gain delta G' after the fading factor is added is lower than 0.6 times of the satellite aligning gain delta G, the simulation training system considers that the situation is in a satellite losing state and performs timing, and if the timing time lasts for more than 50s, the antenna is considered to be in the satellite losing state and needs to be aligned again; if the timing time is less than 50s, the antenna is considered to be only in short shielding, and the satellite does not need to be aimed again.
5. The satellite-to-satellite strategy of the satellite communication simulation training system according to claim 4, wherein: the gain Δ G' to the satellite after adding the fading factor is
ΔG′＝ΔG-|Δr|dB
Wherein, Δ G is the satellite gain before adding the fading factor, and Δ r follows Rayleigh distribution
Figure FDA0002538913170000021
CN201910857754.1A 2019-09-11 2019-09-11 Satellite alignment strategy of satellite communication simulation training system Active CN110570711B (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
CN201910857754.1A CN110570711B (en) 2019-09-11 2019-09-11 Satellite alignment strategy of satellite communication simulation training system

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CN201910857754.1A CN110570711B (en) 2019-09-11 2019-09-11 Satellite alignment strategy of satellite communication simulation training system

Publications (2)

Publication Number Publication Date
CN110570711A CN110570711A (en) 2019-12-13
CN110570711B true CN110570711B (en) 2020-09-08

Family

ID=68779143

Family Applications (1)

Application Number Title Priority Date Filing Date
CN201910857754.1A Active CN110570711B (en) 2019-09-11 2019-09-11 Satellite alignment strategy of satellite communication simulation training system

Country Status (1)

Country Link
CN (1) CN110570711B (en)

Family Cites Families (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20100259458A1 (en) * 2009-04-14 2010-10-14 Qualcomm Incorporated Dual-angle adjustment of a satellite-tracking antenna with a single motor
CN101916915B (en) * 2010-08-04 2013-06-19 中国人民解放军第二炮兵工程学院 Antenna beam tracking device and method of moving communication satellite communication system
CN105591686B (en) * 2015-12-29 2018-09-28 天通盛邦通信科技（苏州）有限公司 A kind of adaptive anti-interference for mobile satellite communication system is to star method
CN206179294U (en) * 2016-09-27 2017-05-17 公安消防部队士官学校 Fire control satellite communication portable station simulates training system

Also Published As

Publication number Publication date
CN110570711A (en) 2019-12-13

Similar Documents

Publication Publication Date Title
CN101577367A (en) Stable tracking control system for satellite communication antenna for motion carrier
CN109412673B (en) Real-time simulation method of geometric random channel model for unmanned aerial vehicle communication
CN105515689B (en) A kind of system and method for intelligent mobile terminal auxiliary directional antenna direction adjustment
US11611404B2 (en) Four-dimensional over the air performance test method for dynamic scene channel
CN101650570B (en) Intelligent console alignment system
CN107315182B (en) Passive positioning load positioning capability test method based on semi-physical simulation
CN101719802B (en) Device and calculation method for predicting maximum usable frequency (MUF) of short-wave communication
CN104243070A (en) Wireless channel realtime simulator and simulation method oriented to deep space communication
CN209804898U (en) Directional tracking antenna capable of searching signal
CN109188380A (en) A kind of key index test macro and method for low slow small detection radar
CN106299725A (en) A kind of communication vehicle carried station antenna based on Big Dipper dual-mode terminal is to Barebone
CN106505318A (en) A kind of Double directional aerial self adaptation is directed at communication means
US20230040432A1 (en) Signal continuous coverage method, device and apparatus for target area, and antenna system
CN110570711B (en) Satellite alignment strategy of satellite communication simulation training system
CN115327499B (en) Radar target track simulation method based on load unmanned aerial vehicle
CN102540177A (en) Target positioning method based on 3D ray-tracing algorithm
CN109581081A (en) Car antenna test method and single probe spherical surface near field sampling device
CN104820441A (en) Automatic direction finding and adjusting method and system of wireless network bridge
CN112422214B (en) Communication effect demonstration verification system suitable for aviation channel
CN106299697A (en) A kind of simple method automatically controlling tracking antenna
CN109100769A (en) The localization method and system of vehicle connection bluetooth key
CN105509704A (en) Longitude and latitude location method of outdoor shortwave antenna
CN101707578A (en) Method for designing self-tracking signal source with single channel and single pulse system
CN111413664A (en) Directional precision testing method of in-situ testing system of ultrashort wave direction finder
CN110657790A (en) Method for measuring vertical target coordinates by using total station

Legal Events

Date Code Title Description
PB01 Publication
PB01 Publication
SE01 Entry into force of request for substantive examination
SE01 Entry into force of request for substantive examination
GR01 Patent grant
GR01 Patent grant
CB03 Change of inventor or designer information
CB03 Change of inventor or designer information

Inventor after: Li Zhiming

Inventor after: Cong Shukai

Inventor after: Yang Min

Inventor after: Zhang Yingxian

Inventor before: Li Zhiming

Inventor before: Cong Shukai

Inventor before: Yang Min

Inventor before: Zhang Yingxian

Inventor before: Zhang Kangkang

Inventor before: Wang Fei

Inventor before: Wang Jiachang