CN104393394A - Knapsack emergency satellite communication servo system - Google Patents
Knapsack emergency satellite communication servo system Download PDFInfo
- Publication number
- CN104393394A CN104393394A CN201410682636.9A CN201410682636A CN104393394A CN 104393394 A CN104393394 A CN 104393394A CN 201410682636 A CN201410682636 A CN 201410682636A CN 104393394 A CN104393394 A CN 104393394A
- Authority
- CN
- China
- Prior art keywords
- antenna
- chip
- satellite communication
- pin
- satellite
- 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.)
- Pending
Links
Landscapes
- Variable-Direction Aerials And Aerial Arrays (AREA)
Abstract
The invention discloses a knapsack emergency satellite communication servo system. The knapsack emergency satellite communication servo system comprises a knapsack bag, an antenna structure unit and an antenna detection unit; the antenna structure unit is arranged in the knapsack bag; the antenna detection unit is used for installing an antenna seat frame; the antenna structure unit comprises a satellite communication antenna, an antenna seat frame, a feed source assembly supporting part and an antenna operation platform; the antenna operation platform is a mobile carrier of the satellite communication antenna; an antenna operation control unit is arranged in the antenna operation platform; a pitch transmission mechanism and an orientation transmission mechanism are connected with the antenna operation control unit; the antenna operation control unit comprises a microprocessor and a driving circuit; the antenna detection unit comprises an antenna angle position detection unit, a GPS (Global Positioning System) positioning unit, an antenna carrier attitude detection unit and a satellite signal strength detection unit. According to the knapsack emergency satellite communication servo system, the structure is simple, the design is reasonable, the single person bearing can be achieved, the use and the operation are simple and convenient, the using effect is good, the satellite search process can be automatically achieved, the accuracy of the satellite alignment is high, the communication performance is excellent, and the communication guarantee is provided for the emergency disposal.
Description
Technical field
The invention belongs to technical field of satellite communication, especially relate to a kind of backpack emergency satellite communication sky and watch system.
Background technology
Along with the fast development of economic society, worldwide accident gets more and more, more and more frequent, emergency event disposes requirement fast, effectively, general communication due to scene is destroyed or paralyse, and communications and transportation fast can not arrive at scene, but satellite communication is by the restriction of territorial environment, and backpack satellite communication earth station (hereinafter referred to as bearing station) can the single intelligent of the bearing scene that can enter, and sets up satellite communication link fast.During practical application, because of emergent on-the-spot geographical environment more complicated, Large-Scale Equipment is difficult to transport scene to, sets up on-the-spot communication link for arriving rapidly, bear station and reduced volume, weight reduction, minimizing must carry number of packages, and the single single-piece of corresponding solution bears the problems existed in process.To sum up, nowadays lack a kind of structure simple, reasonable in design, singlely can bear and use easy and simple to handle, that result of use is good backpack emergency satellite communication sky to watch system, automatically can complete and seek star process, and it is higher to the precision of satelloid, communication performance is excellent, for emergency disposal provides communication support.
Summary of the invention
Technical problem to be solved by this invention is for above-mentioned deficiency of the prior art, a kind of backpack emergency satellite communication sky is provided to watch system, its structure is simple, reasonable in design, can singlely bear and use easy and simple to handle, result of use good, automatically can complete and seek star process, and it is higher to the precision of satelloid, communication performance is excellent, for emergency disposal provides communication support.
For solving the problems of the technologies described above, the technical solution used in the present invention is: system is watched in a kind of backpack emergency satellite communication sky, it is characterized in that: comprise and bear bag and the antenna structure unit born described in being loaded on respectively in bag and antenna detection unit, the antenna mount that described antenna structure unit comprises satellite communication antena, install for described satellite communication antena, be arranged on antenna mount and the feed component support piece installed for the feed assembly of described satellite communication antena and operating platform for the antenna that antenna mount is installed, the described antenna platform that operates is the mobile vehicle of described satellite communication antena, described antenna running platform is built with the antenna operation control unit controlled pitch drive mechanism and Amimuth Transmission mechanism, described pitch drive mechanism is the transmission mechanism adjusted the angle of pitch of described satellite communication antena, described Amimuth Transmission mechanism is the transmission mechanism adjusted the azimuth of described satellite communication antena, and described pitch drive mechanism and Amimuth Transmission mechanism all connect with described antenna operation control unit and the two is all in transmission connection with described satellite communication antena, the drive circuit that described antenna operation control unit comprises microprocessor and drives described pitch drive mechanism and Amimuth Transmission mechanism, described microprocessor be laid in the parameter set unit that antenna operates on platform lateral wall and connect, described drive circuit connects with microprocessor, described antenna detection unit comprises antenna angle position detection unit, the longitude and latitude of described mobile vehicle present position is carried out to the GPS positioning unit detected in real time, the antenna carrier posture detecting unit detected in real time and the satellite-signal intensity detection unit intensity of described satellite communication antena institute receiving satellite signal being carried out to detection are in real time carried out to the attitude information of described mobile vehicle, described antenna angle position detection unit comprises carries out the antenna elevation angle detecting unit detected in real time and the antenna azimuth detecting unit azimuth of described satellite communication antena being carried out to detection in real time to the angle of pitch of described satellite communication antena, described antenna elevation angle detecting unit, antenna azimuth detecting unit, GPS positioning unit, antenna carrier posture detecting unit and satellite-signal intensity detection unit all connect microprocessor, described microprocessor is MSP430F149 chip.
System is watched in above-mentioned backpack emergency satellite communication sky, it is characterized in that: described antenna elevation angle detecting unit and antenna azimuth detecting unit are contactless Hall angular transducer, and described contactless Hall angular transducer is R25D encoder.
System is watched in above-mentioned backpack emergency satellite communication sky, it is characterized in that: also comprise the upper monitoring machine carrying out two-way communication with microprocessor, and described upper monitoring machine is connected by RS232 interface with between microprocessor.
System is watched in above-mentioned backpack emergency satellite communication sky, it is characterized in that: described GPS positioning unit, antenna carrier posture detecting unit and satellite-signal intensity detection unit are all connected by RS232 interface with between microprocessor, described GPS positioning unit is connected with chip U107, described antenna carrier posture detecting unit is connected with chip U105, and described satellite-signal intensity detection unit is connected with chip U104; Described upper monitoring machine is connected with chip U114; Described chip U107, chip U105, chip U104 and chip U114 are chip SP3220E;
Two data transmission terminals of described GPS positioning unit are connected with the 8th and the 13rd pin of chip U107 respectively, 1st pin of chip U107 is connected with the 30th pin of MSP430F149 chip, and the 9th of chip U107 is connected with the 33rd and the 32nd pin of MSP430F149 chip respectively with the 11st pin; Two data transmission terminals of described antenna carrier posture detecting unit are connected with the 8th and the 13rd pin of chip U105 respectively, 1st pin of chip U105 is connected with the 28th pin of MSP430F149 chip, and the 9th of chip U105 is connected with the 33rd and the 32nd pin of MSP430F149 chip respectively with the 11st pin; Two data transmission terminals of described satellite-signal intensity detection unit are connected with the 8th and the 13rd pin of chip U104 respectively, 1st pin of chip U104 is connected with the 29th pin of MSP430F149 chip, and the 9th of chip U104 is connected with the 33rd and the 32nd pin of MSP430F149 chip respectively with the 11st pin; Two data transmission terminals of described upper monitoring machine are connected with the 8th and the 13rd pin of chip U110 respectively, and the 9th of chip U110 is connected with the 35th and the 34th pin of MSP430F149 chip respectively with the 11st pin.
System is watched in above-mentioned backpack emergency satellite communication sky, it is characterized in that: described GPS positioning unit is GPS, and described GPS is GPS15XL-W module; Described antenna carrier posture detecting unit is electronic compass; Described satellite-signal intensity detection unit is the satellite signal receiver of described satellite communication antena, and described satellite signal receiver is KCXBR214-40 satellite beacon receiver.
System is watched in above-mentioned backpack emergency satellite communication sky, it is characterized in that: described satellite communication antena is single reflector antenna, and described single reflector antenna comprises antenna reflective face and the feed assembly for reception antenna reflecting surface institute reflector satellite signal; Described antenna reflective face is four distinguish carbon fiber antenna reflective faces, the upper secondary lobe that described four distinguish carbon fiber antenna reflective faces comprise main lobe, be positioned at the left secondary lobe of the main lobe left and right sides and right secondary lobe and be positioned at above main lobe, described left secondary lobe and the symmetrical laying of right secondary lobe, the left side wall of described main lobe, rear wall and upper side wall are straight side walls, and left side wall and the rear wall of described main lobe are parallel laying and the two is all vertical runs with the upper side wall of main lobe; Described main lobe is arranged on antenna mount, and described left secondary lobe, right secondary lobe and upper secondary lobe are arranged on the left side of main lobe, right side and top respectively by connector.
System is watched in above-mentioned backpack emergency satellite communication sky, it is characterized in that: described in bear handbag and draw together knapsack inclusion, described knapsack inclusion comprises inner support framework and is sleeved on the ladle cover outside described inner support framework, described ladle cover is sheet and it is made up of with the clad be laid on the cover body of bottom the bottom cover body of upper opening, and described bottom cover body is connected by slide fastener with between clad; Described clad arranged outside has the antenna distinguish putting bag for placing left secondary lobe, right secondary lobe and upper secondary lobe; Described bottom cover body is provided with braces; Described main lobe, antenna mount, feed component support piece and antenna running platform is all loaded in described ladle cover.
System is watched in above-mentioned backpack emergency satellite communication sky, it is characterized in that: the left and right sides of described antenna running platform is respectively arranged with a wind resistance and grabs the thin end of the scroll, described wind resistance is grabbed the thin end of the scroll and is carbon fiber support and its outer end is provided with the locking member be locked on the ground, it is by first body of rod that described wind resistance grabs the thin end of the scroll, the right-angled triangle support that second body of rod and the 3rd body of rod are formed by connecting, described first body of rod and the antenna platform that operates is parallel laying, described second body of rod and described first body of rod are vertical runs and its length is less than the length of described first body of rod, described 3rd body of rod is connected between described first body of rod and described second body of rod, described second body of rod be positioned at antenna running platform outside and its upper and lower two ends be arranged on all in hinged way antenna running platform lateral wall on, described locking member is positioned at the junction of described first body of rod and described 3rd body of rod.
System is watched in above-mentioned backpack emergency satellite communication sky, it is characterized in that: described antenna mount comprises the fixed mount be fixedly mounted on antenna running platform and the movement frame be positioned at above described fixed mount; Described pitch drive mechanism is arranged on described movement frame, described pitch drive mechanism comprises the first turbine worm reducer of carrying out with the power output shaft of pitching drive motors being in transmission connection and carries out with the power output shaft of the first turbine worm reducer the cycloid speed reducer that is in transmission connection, the antenna back frame of described satellite communication antena is arranged on elevation axis of antenna, and the power output shaft of described elevation axis of antenna and cycloid speed reducer is in transmission connection; Described Amimuth Transmission mechanism comprises the planetary reduction gear carrying out with the power output shaft of orientation drive motors being in transmission connection, the Timing Belt decelerator carrying out being in transmission connection with the power output shaft of planetary reduction gear, to carry out the second turbine and worm decelerator of being in transmission connection with the power output shaft of Timing Belt decelerator and carries out with the power output shaft of the second turbine and worm decelerator the steel wire drive assembly that is in transmission connection, described steel wire drive assembly is installed between described fixed mount and described movement frame, and described movement frame and described steel wire drive assembly are in transmission connection.
System is watched in above-mentioned backpack emergency satellite communication sky, it is characterized in that: described pitch drive mechanism and pitching drive motors are in transmission connection, and described Amimuth Transmission mechanism and orientation drive motors are in transmission connection; Described drive circuit is the chip 74HC07 connected with MSP430F149 chip, and described pitching drive motors and orientation drive motors are DC speed-reducing and the two all connects with the signal output part of chip 74HC07.
The present invention compared with prior art has the following advantages:
1, structure is simple, reasonable in design and input cost is lower, and processing and fabricating is easy.
2, use easy and simple to handle and antenna launch and collect simple and easy, after transporting the present invention's (station born in abbreviation) to scene, by simple erection, then by parameter set unit or the operation of upper monitoring machine, complete satellite communication antena Automatic-expanding process; Afterwards, antenna detection unit and antenna operation control unit have matched with microprocessor automatic star-seeking, arrive after theoretical position (after the satellite that namely aims at the mark) until satellite communication antena, according to satellite signal characteristics and antenna beam characteristics automatic search satellite, and automatic tracking satellite keeps communications status.After end-of-job, complete satellite communication and automatically collect, and bag is born in loading.
3, four distinguish carbon fiber antenna reflective faces adopt pintongs assembled, reduce antenna surface collection volume, material selection carbon fiber, decrease weight, antenna structure unit is collected in one to be born in bag, be convenient to single single-piece bear, therefore do not change pocket energy, the transmission of the on-the-spot two-way Large Copacity multimedia messages of emergency disposal can be met.Four distinguish carbon fiber antenna reflective faces are made up of main lobe, left secondary lobe, right secondary lobe and upper secondary lobe, when satellite communication antena is collected, left secondary lobe, right secondary lobe and upper secondary lobe will be pulled down, and be loaded on and bear in the antenna distinguish putting bag of bag, then main lobe is turn to downwards fit with antenna mount; Meanwhile, feed component support piece is turn to downwards and fits with antenna mount, so just complete the collection process of described satellite communication antena.Correspondingly, when satellite communication antena is launched, first feed component support piece and main lobe are upwards overturn and put in place, then bottom left secondary lobe, right secondary lobe and upper secondary lobe are arranged on main lobe.Practical operation is very easy, pulls down other distinguish (comprising bottom left secondary lobe, right secondary lobe and upper secondary lobe) during collection, spells upper each distinguish during work.
4, the bore of four distinguish carbon fiber antenna reflective faces is 1 meter, bears station for 1 meter and compares with 1 meter of conventional portable station, reduce volume, alleviate weight, achieve single single-piece and bear, complete machine weight is less than 16Kg, do not change communication performance, the on-the-spot two-way multimedia information transmission of emergency disposal can be met.After bearing station end-of-job, take antenna distinguish apart, control antenna is collected, by antenna main lobe, feed modular support frame and feed assembly, be folded on antenna running platform, more secondary for antenna distinguish pack is placed on bears in the antenna distinguish bag of bag, cover clad, weight is less than 16Kg, volume 400 × 300 × 150mm
3.
5, simple, the reasonable in design and processing and fabricating of the antenna mount structure adopted and use easy and simple to handle, primarily of movement frame and fixed mount two parts composition, wherein steel wire drive assembly is laid between movement frame and fixed mount, and the driven pulley of steel wire drive assembly is fixed on fixed mount.Pitch drive mechanism and Amimuth Transmission mechanism are installed on antenna mount, take volume little and install compact, and antenna mount, pitch drive mechanism and Amimuth Transmission mechanism composition antenna pedestal.
The pitch drive mechanism structure adopted is simple, reasonable in design and result of use is good, primarily of pitching drive motors, the first turbine worm reducer with form with cycloid speed reducer.Because the final stage of pitch drive mechanism adopts cycloid speed reducer, utilize the wind pressure of backlash function resistance from antenna face that disappear of cycloid speed reducer, keep the steady of antenna running; Penultimate stage adopts turbine worm reducer transmission, because turbine and worm has auto-lock function, thus the antenna surface wind pressure disturbing moment windward that final stage transmits can be eliminated further, strengthen the wind loading rating of antenna, reduce the turn error of pitch drive mechanism, thus pitch drive mechanism of the present invention has that torque resistant disturbing moment is strong, transmission turn error is little, running accuracy advantages of higher.The Amimuth Transmission mechanism structure adopted is simple, reasonable in design and result of use is good, forms primarily of orientation drive motors, planetary reduction gear, Timing Belt decelerator, the second turbine and worm decelerator and steel wire drive assembly.The steel wire drive assembly that Amimuth Transmission mechanism final stage adopts is steel wire frictional drive, frictional drive is belonged between driving wheel in steel wire drive assembly and driven pulley, the degrees of tensions of steel wire is adjusted automatically by butterfly spring, ensure that the turn error of Amimuth Transmission mechanism final stage is very little, even not there is turn error; Penultimate stage adopts turbine worm reducer, the antenna external disturbance moment utilizing the auto-lock function of turbine and worm to eliminate final stage further to transmit, and strengthens the anti-external disturbance ability of antenna, reduces the turn error of Amimuth Transmission.
Further, the antenna pedestal result of use that antenna mount and pitch drive mechanism and Amimuth Transmission mechanism form is good and practical value is high, has that wind loading rating is strong, running speed is fast, running accuracy high.
6, result of use is good and practical value is high, after satellite communication antena transports scene to, open and bear bag, launch by completing antenna after erection again, assembled antenna distinguish afterwards, and control star, satellite-signal enters receiving system by antenna feed assembly, ground transmitter signal, from feed to antenna reflective face, mails to satellite and carries out bidirectional information communication.The present invention structurally, reduces antenna pedestal volume by a relatively large margin, form the miniaturized integrative-structure of the driving-chain such as motor, decelerator, and antenna reflective face is made up of 4 distinguish, reduces volume; Antenna surface, feed modular support frame, antenna running platform and wind resistance are grabbed the thin end of the scroll and are all selected carbon fibre material, effectively alleviate weight, satellite communication earth station sky are watched systematic collection and bear in bag at one and be convenient to singlely bear carrying.Antenna operation control unit adopts embedded microprocessor, and with upper monitoring machine (as PC with the use of), complete the process such as antenna Automatic-expanding antenna, automatic star-seeking, automatically collection antenna.Practical operation is easy, and the course of work safely, reliably.Thus, the present invention, while reduced volume, weight reduction, can realize single single-piece and bear, automation mechanized operation, can be effective in accident emergency disposal process, singlely bears the scene of transporting to, set up satellite communication link between two places fast, for emergency disposal provides communication support.
7, the present invention is used in accident emergency disposal process, singlely bear to scene, set up satellite communication link between two places fast, for emergency disposal provides communication support, practical, result of use is good, and can be used for the single scene that transports in accident emergency disposal process and set up satellite communication link, thus popularizing application prospect is extensive.
In sum, structure of the present invention is simple, reasonable in design, can singlely bear and use easy and simple to handle, result of use good, automatically can complete and seek star process, and higher to the precision of satelloid, communication performance is excellent, for emergency disposal provides communication support.
Below by drawings and Examples, technical scheme of the present invention is described in further detail.
Accompanying drawing explanation
Fig. 1 is the deployed condition schematic diagram of inventive antenna construction unit.
Fig. 2 is the structural representation of inventive antenna construction unit when being in collecting state.
Fig. 3 is the structural representation that the present invention bears bag.
Fig. 4 is the schematic block circuit diagram of inventive antenna operation control unit.
Fig. 5 is the circuit theory diagrams of microprocessor of the present invention.
Fig. 6 is the circuit theory diagrams of RS232 interface chip of the present invention.
Fig. 7 is the structural representation of inventive antenna mounting.
Fig. 8 is the internal structure schematic diagram of inventive antenna mounting.
Fig. 9 is the installation site schematic diagram of steel wire drive assembly of the present invention.
Figure 10 is the installation site schematic diagram of manual type pitching adjusting mechanism of the present invention and manual type position adjusting mechanism.
Description of reference numerals:
1-1-pitching drive motors; 1-2-the first turbine worm reducer;
1-3-cycloid speed reducer; 1-4-the first manual link; 1-5-conveyer belt;
2-1-orientation drive motors; 2-2-planetary reduction gear; 2-3-Timing Belt decelerator;
2-4-the second turbine and worm decelerator;
2-51-steel wire drive driving wheel; 2-52-steel wire drive driven pulley;
2-53-transmission steel wire; 2-54-the 4th bearing; 2-6-the second manual link;
3-1-base plate; 3-11-mounting platform; 3-12-protective plate;
3-2-pitch axis bracing frame; 3-3-protective cover plate; 4-elevation axis of antenna;
5-fixed head; 6-hand crank; 7-mounting flange;
The erection joint of 8-crank; 9-antenna mount; 10-feed assembly;
11-feed component support piece; 12-antenna running platform; 13-1-microprocessor;
13-2-drive circuit; 13-3-parameter set unit; 14-upper monitoring machine;
14-1-antenna angle position detection unit;
14-11-antenna elevation angle detecting unit;
14-12-antenna azimuth detecting unit; 14-2-GPS positioning unit;
14-3-antenna carrier posture detecting unit;
14-4-satellite-signal intensity detection unit; 15-antenna reflective face;
15-1-main lobe; 15-2-left secondary lobe; 15-3-right secondary lobe;
15-4-upper secondary lobe; 16-1-bottom cover body; 16-2-clad;
16-3-antenna distinguish putting bag; 16-4-braces; 17-wind resistance grabs the thin end of the scroll;
18-set lever;
Embodiment
As shown in Figure 1 and Figure 2, the present invention includes and bear bag and the antenna structure unit born described in being loaded on respectively in bag and antenna detection unit.The antenna mount 9 that described antenna structure unit comprises satellite communication antena, install for described satellite communication antena, be arranged on antenna mount 9 and the feed component support piece 11 installed for the feed assembly 10 of described satellite communication antena and operating platform 12 for the antenna that antenna mount 9 is installed, the described antenna platform 12 that operates is the mobile vehicle of described satellite communication antena.Described antenna running platform 12 is built with the antenna operation control unit controlled pitch drive mechanism and Amimuth Transmission mechanism, described pitch drive mechanism is the transmission mechanism adjusted the angle of pitch of described satellite communication antena, described Amimuth Transmission mechanism is the transmission mechanism adjusted the azimuth of described satellite communication antena, and described pitch drive mechanism and Amimuth Transmission mechanism all connect with described antenna operation control unit and the two is all in transmission connection with described satellite communication antena.Composition graphs 4, the drive circuit 13-2 that described antenna operation control unit comprises microprocessor 13-1 and drives described pitch drive mechanism and Amimuth Transmission mechanism, described microprocessor 13-1 be laid in the parameter set unit 13-3 that antenna operates on platform 12 lateral wall and connect, described drive circuit 13-2 connects with microprocessor 13-1.Described antenna detection unit comprises antenna angle position detection unit 14-1, the longitude and latitude of described mobile vehicle present position is carried out to the GPS positioning unit 14-2 detected in real time, the antenna carrier posture detecting unit 14-3 detected in real time and the satellite-signal intensity detection unit 14-4 intensity of described satellite communication antena institute receiving satellite signal being carried out to detection is in real time carried out to the attitude information of described mobile vehicle, described antenna angle position detection unit 14-1 comprises the antenna azimuth detecting unit 14-12 carrying out to the angle of pitch of described satellite communication antena the antenna elevation angle detecting unit 14-11 that detects in real time and carry out the azimuth of described satellite communication antena detecting in real time, described antenna elevation angle detecting unit 14-11, antenna azimuth detecting unit 14-12, GPS positioning unit 14-2, antenna carrier posture detecting unit 14-3 and satellite-signal intensity detection unit 14-4 all meets microprocessor 13-1.Described microprocessor 13-1 is MSP430F149 chip, refers to Fig. 5.
In the present embodiment, the present invention also comprises the upper monitoring machine 14 carrying out two-way communication with microprocessor 13-1, and described upper monitoring machine 14 is connected by RS232 interface with between microprocessor 13-1.
During physical cabling, described GPS positioning unit 14-2, antenna carrier posture detecting unit 14-3 and satellite-signal intensity detection unit 14-4 are all connected by RS232 interface with between microprocessor 13-1.As shown in Figure 6, described GPS positioning unit 14-2 is connected with chip U107, and described antenna carrier posture detecting unit 14-3 is connected with chip U105, and described satellite-signal intensity detection unit 14-4 is connected with chip U104.Described upper monitoring machine 14 is connected with chip U114.Described chip U107, chip U105, chip U104 and chip U114 are chip SP3220E.
In the present embodiment, two data transmission terminals of described GPS positioning unit 14-2 are connected with the 8th and the 13rd pin of chip U107 respectively, 1st pin of chip U107 is connected with the 30th pin of MSP430F149 chip, and the 9th of chip U107 is connected with the 33rd and the 32nd pin of MSP430F149 chip respectively with the 11st pin.Two data transmission terminals of described antenna carrier posture detecting unit 14-3 are connected with the 8th and the 13rd pin of chip U105 respectively, 1st pin of chip U105 is connected with the 28th pin of MSP430F149 chip, and the 9th of chip U105 is connected with the 33rd and the 32nd pin of MSP430F149 chip respectively with the 11st pin.Two data transmission terminals of described satellite-signal intensity detection unit 14-4 are connected with the 8th and the 13rd pin of chip U104 respectively, 1st pin of chip U104 is connected with the 29th pin of MSP430F149 chip, and the 9th of chip U104 is connected with the 33rd and the 32nd pin of MSP430F149 chip respectively with the 11st pin.Two data transmission terminals of described upper monitoring machine 14 are connected with the 8th and the 13rd pin of chip U110 respectively, and the 9th of chip U110 is connected with the 35th and the 34th pin of MSP430F149 chip respectively with the 11st pin.
During physical cabling, two data transmission terminals of described GPS positioning unit 14-2 are connected with the 8th of chip U107 the and the 13rd pin respectively after resistance R115 with R121, 15th pin of chip U107 connects+3.3V power end and it the 15th draws ground connection after foot meridian capacitor C132, 16th pin of chip U107 connects+3.3V power end after resistance R124, the equal ground connection of 1st and the 14th pin of chip U107, 3rd and the 7th pin ground connection after electric capacity C137 and C125 respectively of chip U107, electric capacity C133 is connected between 5th and the 6th pin of chip U107, electric capacity C134 is connected between 2nd and the 4th pin of chip U107.
Two data transmission terminals of described antenna carrier posture detecting unit 14-3 are connected with the 8th of chip U105 the and the 13rd pin respectively after resistance R113 with R114, 15th pin of chip U105 connects+3.3V power end and it the 15th draws ground connection after foot meridian capacitor C121, 16th pin of chip U105 connects+3.3V power end after resistance R116, the equal ground connection of 1st and the 14th pin of chip U105, 3rd and the 7th pin ground connection after electric capacity C126 and C124 respectively of chip U105, electric capacity C122 is connected between 5th and the 6th pin of chip U105, electric capacity C123 is connected between 2nd and the 4th pin of chip U105.
Two data transmission terminals of described satellite-signal intensity detection unit 14-4 are connected with the 8th of chip U104 the and the 13rd pin respectively after resistance R101 with R102, 15th pin of chip U104 connects+3.3V power end and it the 15th draws ground connection after foot meridian capacitor C115, 16th pin of chip U104 connects+3.3V power end after resistance R103, the equal ground connection of 1st and the 14th pin of chip U105, 3rd and the 7th pin ground connection after electric capacity C119 and C118 respectively of chip U104, electric capacity C116 is connected between 5th and the 6th pin of chip U104, electric capacity C117 is connected between 2nd and the 4th pin of chip U105.
Two data transmission terminals of described upper monitoring machine 14 are connected with the 8th of chip U110 the and the 13rd pin respectively after resistance R122 with R123, 15th pin of chip U110 connects+3.3V power end and it the 15th draws ground connection after foot meridian capacitor C140, 16th pin of chip U110 connects+3.3V power end after resistance R127, the equal ground connection of 1st and the 14th pin of chip U105, 3rd and the 7th pin ground connection after electric capacity C138 and C136 respectively of chip U110, electric capacity C135 is connected between 5th and the 6th pin of chip U110, electric capacity C141 is connected between 2nd and the 4th pin of chip U105.
In the present embodiment, described antenna elevation angle detecting unit 14-11 and antenna azimuth detecting unit 14-12 is contactless Hall angular transducer, and described contactless Hall angular transducer is R25D encoder.
In the present embodiment, described GPS positioning unit 14-2 is GPS, and described GPS is GPS15XL-W module.
In the present embodiment, described antenna carrier posture detecting unit 14-3 is electronic compass.Further, described electronic compass is DCM368 electronic compass, is specially DCM368-232 compass.
In the present embodiment, described satellite-signal intensity detection unit 14-4 is the satellite signal receiver of described satellite communication antena, and described satellite signal receiver is KCXBR214-40 satellite beacon receiver.
In actual use procedure, described antenna elevation angle detecting unit 14-11 and antenna azimuth detecting unit 14-12 is arranged in described pitch drive mechanism and Amimuth Transmission mechanism respectively, and exporting the angle of pitch and the azimuth of described satellite communication antena, antenna azimuth detecting unit 14-12 and antenna elevation angle detecting unit 14-11 is specifically for measuring orientation and the position of pitching in local horizontal coordinate of described satellite communication antena; Described GPS positioning unit 14-2 measures the earth warp, the latitude of described satellite antenna position, calculates for seeking star; Described electronic compass measures the attitude (comprising course, pitching and roll) in horizontal coordinate mark of described satellite communication antena place, calculates for seeking star; Described satellite-signal intensity detection unit 14-4 measures the intensity of institute's receiving satellite signal, for seeking the degree judging antenna alignment satellite in star process.
During actual use, described microprocessor 13-1 is according to formula
synchronometer calculates azimuth of target Az and the target pitch angle El of the antenna beam target satellite of described satellite communication antena, in formula, and Δ φ=φ
s-φ
g, r is earth radius and r=6378km, R are target satellite apart from the height in earth the earth's core and R=42165km; Wherein, φ
sfor the substar longitude of target satellite, φ
gand ψ
gbe respectively longitude and the latitude of the current present position of described mobile vehicle that described GPS positioning unit 14-2 detects; In azimuth of target Az and target pitch angle El computational process, azimuth of target Az is with positive north for zero degree and clockwise direction just be, and target pitch angle El is zero degree with horizontal direction and is just above horizontal plane.Afterwards, described microprocessor 13-1 is according to the azimuth of target Az calculated and target pitch angle El, and by drive circuit 13-2, described pitch drive mechanism and Amimuth Transmission mechanism are controlled, make the angle of pitch of described satellite communication antena and azimuth and target pitch angle and El azimuth of target Az consistent, complete and seek star process.
As depicted in figs. 1 and 2, in the present embodiment, described satellite communication antena is single reflector antenna, and described single reflector antenna comprises antenna reflective face 15 and the feed assembly 10 for reception antenna reflecting surface 15 reflector satellite signals.Described antenna reflective face 15 is four distinguish carbon fiber antenna reflective faces, the upper secondary lobe 15-4 that described four distinguish carbon fiber antenna reflective faces comprise main lobe 15-1, are positioned at the left secondary lobe 15-2 of the main lobe 15-1 left and right sides and right secondary lobe 15-3 and are positioned at above main lobe 15-1, described left secondary lobe 15-2 and the symmetrical laying of right secondary lobe 15-3, the left side wall of described main lobe 15-1, rear wall and upper side wall are straight side walls, and the left side wall of described main lobe 15-1 is parallel laying with rear wall and the two is all vertical runs with the upper side wall of main lobe 15-1; Described main lobe 15-1 is arranged on antenna mount 9, and described left secondary lobe 15-2, right secondary lobe 15-3 and upper secondary lobe 15-4 are arranged on the left side of main lobe 15-1, right side and top respectively by connector.
In the present embodiment, the bore of described antenna reflective face 15 is 1 meter.
During actual use, can according to specific needs, the caliber size of antenna reflective face 15 be adjusted accordingly.
As shown in Figure 3, knapsack inclusion drawn together by described handbag of bearing, described knapsack inclusion comprises inner support framework and is sleeved on the ladle cover outside described inner support framework, described ladle cover is sheet and it is made up of with the clad 16-2 be laid on the cover body 16-1 of bottom the bottom cover body 16-1 of upper opening, and described bottom cover body 16-1 is connected by slide fastener with between clad 16-2.Described clad 16-2 arranged outside has the antenna distinguish putting bag 16-3 for placing left secondary lobe 15-2, right secondary lobe 15-3 and upper secondary lobe 15-4; Described bottom cover body 16-1 is provided with braces 16-4.Described main lobe 15-1, antenna mount 9, feed component support piece 11 and antenna running platform 12 is all loaded in described ladle cover.Meanwhile, described bottom cover body 16-1 is also provided with locking belt.
Actually add man-hour, described antenna reflective face 15 carbon fiber antenna reflective face, described main lobe 15-1 is connected with antenna mount 9 and is connected in hinged way therebetween, facilitates expansion and the collection of main lobe 15-1; Described feed assembly 10 comprise bell mouth surface to the Feed Horn of described antenna subreflector, the polarizer connected with Feed Horn and the duplexer connected with polarizer and connect with Feed Horn and for driving Feed Horn, polarization power drive mechanism that polarizer rotates together with duplexer, described feed assembly 10 (comprises polarization component, i.e. polarizer) on the feed component support piece 11 installed, and feed assembly 10 is connected as one by feed component support piece 11 and antenna mount 9.Described feed component support piece 11 is the bracing frame that a bottom is arranged on antenna mount 9 in hinged way.
During actual use, described feed assembly 10 is arranged on feed component support piece 11, completes the transmission of sending and receiving radiofrequency signal and mating of star polarization of the e angle, ground.In the present embodiment, antenna mount 9 and the junction of main lobe 15-1 are provided with electric expansion mechanism, for Automatic-expanding or collection main lobe 15-1.Described electric expansion mechanism is controlled by microprocessor 13-1.
When described satellite communication antena is collected, left secondary lobe 15-2, right secondary lobe 15-3 and upper secondary lobe 15-4 will be pulled down, and be loaded on antenna distinguish putting bag 16-3, then main lobe 15-1 is turn to downwards fit with antenna mount 9; Meanwhile, feed component support piece 11 is turn to downwards and fits with antenna mount 9, so just complete the collection process of described satellite communication antena.Correspondingly, when described satellite communication antena is launched, first feed component support piece 11 and main lobe 15-1 are upwards overturn and put in place, more left secondary lobe 15-2, right secondary lobe 15-3 and upper secondary lobe 15-4 are arranged on main lobe 15-1.Practical operation is very easy, pulls down other distinguish (comprising left secondary lobe 15-2, right secondary lobe 15-3 and upper secondary lobe 15-4) during collection, spells upper each distinguish during work.
In the present embodiment, the left and right sides of described antenna running platform 12 is respectively arranged with a wind resistance and grabs the thin end of the scroll 17, and described wind resistance is grabbed the thin end of the scroll 17 and is carbon fiber support and its outer end is provided with the locking member be locked on the ground.It is by first body of rod that described wind resistance grabs the thin end of the scroll 17, the right-angled triangle support that second body of rod and the 3rd body of rod are formed by connecting, described first body of rod and antenna operate platform 12 in parallel laying, described second body of rod and described first body of rod are vertical runs and its length is less than the length of described first body of rod, described 3rd body of rod is connected between described first body of rod and described second body of rod, described second body of rod be positioned at antenna running platform 12 outside and its upper and lower two ends be arranged on all in hinged way antenna running platform 12 lateral wall on, described locking member is positioned at the junction of described first body of rod and described 3rd body of rod.
Described feed component support piece 11, antenna mount 9 and antenna running platform 12 is carbon fibre materials.
In the present embodiment, when described satellite communication antena is collected, two described wind resistances are grabbed the lateral wall that the thin end of the scroll 17 rotates the platform 12 and the two all operates with antenna to the left and right sides of main lobe 15-1 to be close to, and bear described in being loaded in bag, so just singlely can bear carrying.
Actually add man-hour, described wind resistance is grabbed the thin end of the scroll 17 and is adopted carbon fibre materials, and described locking member is for grabbing with set lever 18.Actual when using, two described wind resistances are grabbed the thin end of the scroll 17 and turn to corresponding Support Position on rear side of antenna running platform 12 respectively, and adjust by set lever 18 degree that wind resistance grabs the thin end of the scroll 17 and earth surface.
In the present embodiment, described parameter set unit 13-3 controls button or control panel and it is laid on the lateral wall of antenna running platform 12,
In the present embodiment, described pitch drive mechanism and pitching drive motors 1-1 are in transmission connection, and described Amimuth Transmission mechanism and orientation drive motors 2-1 are in transmission connection.Described drive circuit 13-2 is the chip 74HC07 connected with MSP430F149 chip, and described pitching drive motors 1-1 and orientation drive motors 2-1 is DC speed-reducing and the two all connects with the signal output part of chip 74HC07.
As shown in Figure 5, the control circuit that it is central processing unit with MSP430F149 embedded programmable microprocessor that described antenna operation control unit adopts, described pitching drive motors 1-1 and orientation drive motors 2-1 all adopts PG36BL36244900-721K DC speed-reducing, access respectively in pitch drive mechanism and Amimuth Transmission mechanism, under drive circuit 13-2 driving effect, described satellite communication antena is driven to carry out orientation, pitching running.
Actual when using, described antenna mount 9 is fixed by upper shaft (i.e. elevation axis of antenna 4) and described satellite communication antena (specifically main lobe 15-1), and the lower end pedestal of antenna mount 9 and the antenna platform 12 that operates is fixing.
As shown in Figure 7, Figure 8, described antenna mount 9 comprises the fixed mount be fixedly mounted on antenna running platform 12 and the movement frame be positioned at above described fixed mount.Described pitch drive mechanism is arranged on described movement frame, described pitch drive mechanism comprises the first turbine worm reducer 1-2 of carrying out with the power output shaft of pitching drive motors 1-1 being in transmission connection and carries out with the power output shaft of the first turbine worm reducer 1-2 the cycloid speed reducer 1-3 that is in transmission connection, the antenna back frame of described satellite communication antena is arranged on elevation axis of antenna 4, and described elevation axis of antenna 4 is in transmission connection with the power output shaft of cycloid speed reducer 1-3.Described Amimuth Transmission mechanism comprises the planetary reduction gear 2-2 carrying out with the power output shaft of orientation drive motors 2-1 being in transmission connection, the Timing Belt decelerator 2-3 that is in transmission connection is carried out with the power output shaft of planetary reduction gear 2-2, carry out with the power output shaft of Timing Belt decelerator 2-3 the second turbine and worm decelerator 2-4 of being in transmission connection and carry out with the power output shaft of the second turbine and worm decelerator 2-4 the steel wire drive assembly that is in transmission connection, described steel wire drive assembly is installed between described fixed mount and described movement frame, described movement frame and described steel wire drive assembly are in transmission connection.
During actual use, in described pitch drive mechanism, the first turbine worm reducer 1-2 is used for the first time deceleration of pitching drive motors 1-1 running speed and turning to of driving force; Described cycloid speed reducer 1-3 is used for the final reduction of pitching drive motors 1-1 running speed, and drives the angle of pitch of elevation axis of antenna 4 to described satellite communication antena to adjust.
The elementary deceleration of the planetary reduction gear 2-2 orientation drive motors 2-1 running speed in described Amimuth Transmission mechanism, Timing Belt decelerator 2-3 is used for the second time deceleration of orientation drive motors 2-1 running speed and turning to of driving force, second turbine and worm decelerator 2-4 be used for orientation drive motors 2-1 running speed third time slow down and driving force again turn to, described steel wire drive assembly completes the final reduction of orientation drive motors 2-1 running speed.
In the present embodiment, described movement frame comprises the pitch axis bracing frame 3-2 that base plate 3-1 and two is arranged on the left and right sides above base plate 3-1 respectively, the two ends, left and right of described elevation axis of antenna 4 are arranged on two described pitch axis bracing frame 3-2 respectively, two described pitch axis bracing frame 3-2 all have the first installing hole installed for elevation axis of antenna 4, be all connected by clutch shaft bearing between described elevation axis of antenna 4 with two described pitch axis bracing frame 3-2.During actual use, described movement frame synchronous axial system under the drive of described steel wire drive assembly.
During actual installation, described antenna back frame is arranged on elevation axis of antenna 4 by mounting flange 7, and described mounting flange 7 is positioned at outside pitch axis bracing frame 3-2.
In the present embodiment, mounting platform 3-11 for installing for described pitch drive mechanism in the middle part of described base plate 3-1, the left and right sides of described mounting platform 3-11 respectively set by be equipped with protective plate 3-12, two described protective plate 3-12 are all between two described pitch axis bracing frame 3-2, described protective plate 3-12 has the second installing hole installed for elevation axis of antenna 4, described elevation axis of antenna 4 is connected by the second bearing with between protective plate 3-12.
Meanwhile, described movement frame also comprises the protective cover plate 3-3 mounted cover above between two described protective plate 3-12, and described mounting platform 3-11, protective cover plate 3-3 and two described protective plate 3-12 forms a closed protective chamber.
During actual installation, described orientation drive motors 2-1, planetary reduction gear 2-2, Timing Belt decelerator 2-3 and the second turbine and worm decelerator 2-4 are installed on mounting platform 3-11, and described pitch drive mechanism, orientation drive motors 2-1, planetary reduction gear 2-2, Timing Belt decelerator 2-3 and the second turbine and worm decelerator 2-4 are all positioned at described closed protective chamber.
In the present embodiment, two described pitch axis bracing frame 3-2 are parallel laying.Described protective plate 3-12 is parallel laying with pitch axis bracing frame 3-2.Described protective plate 3-12 uses as the auxiliary mounting deck of elevation axis of antenna 4 simultaneously.
In the present embodiment, described pitch axis bracing frame 3-2 and base plate 3-1 processing and fabricating are integrated.
During actual use, as shown in Figure 9, described pitch axis bracing frame 3-2 is used for the face of fixing up an aerial wire and elevation axis of antenna 4.In the present embodiment, described steel wire drive assembly comprises steel wire drive driving wheel 2-51 and steel wire drive driven pulley 2-52, is in transmission connection between described steel wire drive driving wheel 2-51 and steel wire drive driven pulley 2-52 by transmission steel wire 2-53.Described steel wire drive driven pulley 2-52 comprises driven pulley wheel body and is coaxially arranged on the upper transmission axle on described driven pulley wheel body top, described driven pulley wheel body is fixed on described fixed mount, described movement frame is positioned at directly over described upper transmission axle, is connected between described movement frame with described upper transmission axle by the 4th bearing 2-54.Described steel wire drive driving wheel 2-51 comprises initiative drive shaft and the driving wheel wheel body of coaxial package on described initiative drive shaft, and the power output shaft of described initiative drive shaft and the second turbine and worm decelerator 2-4 is in transmission connection.Described initiative drive shaft is the power input shaft of described steel wire drive assembly.
In the present embodiment, the quantity of described transmission steel wire 2-53 is many, many described transmission steel wire 2-53 from top to bottom lay, described in every root, the equal cross winding of transmission steel wire 2-53 is on steel wire drive driving wheel 2-51 and steel wire drive driven pulley 2-52, and the two ends of every root transmission steel wire 2-53 are fixed on steel wire drive driven pulley 2-52 with butterfly spring respectively.That is, transmission steel wire 2-53 described in every root is all in 8-shaped.
In the present embodiment, described fixed mount comprises the fixed head 5 being fixed on antenna running platform 12 top by securing member embedding, and described driven pulley wheel body is fixed on fixed head 5.
During actual installation, described steel wire drive driving wheel 2-51 is installed on below described movement frame.Described steel wire drive driving wheel 2-51 drives described movement frame to rotate around described upper transmission axle (being equivalent to orientation rotation axle) by transmission steel wire 2-53.
In the present embodiment, as shown in Figure 10, hand crank 6 is also comprised.Described pitch drive mechanism also comprises manual type pitching adjusting mechanism, described manual type pitching adjusting mechanism comprises the first manual link 1-4, the outer end of described first manual link 1-4 is the crank installation end installed for hand crank 6, and the inner of described first manual link 1-4 is in transmission connection by the power output shaft of conveyer belt 1-5 and pitching drive motors 1-1.
Described Amimuth Transmission mechanism also comprises manual type position adjusting mechanism, described manual type position adjusting mechanism comprises the second manual link 2-6, the outer end of described second manual link 2-6 is the crank installation end installed for hand crank 6, and the inner of described second manual link 2-6 and the turbine wheel shaft of the second turbine and worm decelerator 2-4 are in transmission connection.
During actual installation, described first manual link 1-4 and the second manual link 2-6 is all arranged on described movement frame by supporting bracket, and described first manual link 1-4 and the second manual link 2-6 is all connected by the 5th bearing with between described supporting bracket.
In the present embodiment, one end of described first manual link 1-4 is by being connected with the power output shaft of pitching drive motors 1-1 by conveyer belt 1-5, and the other end supporting bracket of described first manual link 1-4 is fixed on mounting platform 3-11.During actual use, just can realize manually carrying out antenna elevation angle adjustment by the hand crank 6 be arranged on the first manual link 1-4.
One end of described second manual link 2-6 is connected with the turbine wheel shaft of the second turbine and worm decelerator 2-4, and the other end supporting bracket of the second manual link 2-6 is fixed on mounting platform 3-11.During actual use, just can realize manually carrying out antenna azimuth adjustment by the hand crank 6 be arranged on the second manual link 2-6.
In the present embodiment, the crank installation end of described first manual link 1-4 and the second manual link 2-6 all extend out to outside protective cover plate 3-3, and the crank erection joint 8 of the crank installation end of the first manual link 1-4 and the second manual link 2-6 being all equipped with for installing hand crank 6, described crank erection joint 8 is positioned on protective cover plate 3-3.
The power output shaft of described pitching drive motors 1-1 and the worm shaft of the first turbine worm reducer 1-2 are in transmission connection, the turbine wheel shaft of the first turbine worm reducer 1-2 and the power input shaft of cycloid speed reducer 1-3 are in transmission connection, the power output shaft of described cycloid speed reducer 1-3 is equipped with Power output axle sleeve, and described elevation axis of antenna 4 is in transmission connection with described Power output axle sleeve.
In the present embodiment, for key is connected between described elevation axis of antenna 4 with described Power output axle sleeve.
The described power output shaft of orientation drive motors 2-1 and the power input shaft of planetary reduction gear 2-2 are in transmission connection; The driving-belt that described Timing Belt decelerator 2-3 comprises active synchronization belt wheel, driven synchronous pulley and is connected between active synchronization belt wheel and driven synchronous pulley, described active synchronization belt wheel is coaxially arranged on drive sprocket axle, and described drive sprocket axle is connected with the pto of planetary reduction gear 2-2; Described driven synchronous pulley is coaxially arranged on follower shaft, worm shaft and the described follower shaft of described second turbine and worm decelerator 2-4 are in transmission connection, and the described turbine wheel shaft of the second turbine and worm decelerator 2-4 and the power input shaft of described steel wire drive assembly are in transmission connection.
During actual installation, described orientation drive motors 2-1 is positioned at the right front in described closed protective chamber, described planetary reduction gear 2-2 is positioned at the dead astern of orientation drive motors 2-1, described active synchronization belt wheel is positioned at the dead astern of planetary reduction gear 2-2, described driven synchronous pulley is positioned on the left of described active synchronization belt wheel, and described second turbine and worm decelerator 2-4 is positioned on front side of described driven synchronous pulley.
Described pitching drive motors 1-1 is positioned at the dead astern of described active synchronization belt wheel, and described first turbine worm reducer 1-2 is positioned at the dead astern of pitching drive motors 1-1.
The above; it is only preferred embodiment of the present invention; not the present invention is imposed any restrictions, every above embodiment is done according to the technology of the present invention essence any simple modification, change and equivalent structure change, all still belong in the protection range of technical solution of the present invention.
Claims (10)
1. a system is watched in backpack emergency satellite communication sky, it is characterized in that: comprise and bear bag and the antenna structure unit born described in being loaded on respectively in bag and antenna detection unit; The antenna mount (9) that described antenna structure unit comprises satellite communication antena, install for described satellite communication antena, be arranged on antenna mount (9) upper and the feed component support piece (11) installed for the feed assembly (10) of described satellite communication antena and antenna running platform (12) installed for antenna mount (9), the mobile vehicle that described antenna running platform (12) is described satellite communication antena; Described antenna running platform (12) is built with the antenna operation control unit controlled pitch drive mechanism and Amimuth Transmission mechanism, described pitch drive mechanism is the transmission mechanism adjusted the angle of pitch of described satellite communication antena, described Amimuth Transmission mechanism is the transmission mechanism adjusted the azimuth of described satellite communication antena, and described pitch drive mechanism and Amimuth Transmission mechanism all connect with described antenna operation control unit and the two is all in transmission connection with described satellite communication antena; The drive circuit (13-2) that described antenna operation control unit comprises microprocessor (13-1) and drives described pitch drive mechanism and Amimuth Transmission mechanism, described microprocessor (13-1) be laid in the parameter set unit (13-3) that antenna operates on platform (12) lateral wall and connect, described drive circuit (13-2) connects with microprocessor (13-1); described antenna detection unit comprises antenna angle position detection unit (14-1), the longitude and latitude of described mobile vehicle present position is carried out to the GPS positioning unit (14-2) detected in real time, the antenna carrier posture detecting unit (14-3) detected in real time and the satellite-signal intensity detection unit (14-4) intensity of described satellite communication antena institute receiving satellite signal being carried out to detection are in real time carried out to the attitude information of described mobile vehicle, described antenna angle position detection unit (14-1) comprises carries out the antenna elevation angle detecting unit (14-11) detected in real time and the antenna azimuth detecting unit (14-12) azimuth of described satellite communication antena being carried out to detection in real time to the angle of pitch of described satellite communication antena, described antenna elevation angle detecting unit (14-11), antenna azimuth detecting unit (14-12), GPS positioning unit (14-2), antenna carrier posture detecting unit (14-3) and satellite-signal intensity detection unit (14-4) all connect microprocessor (13-1), described microprocessor (13-1) is MSP430F149 chip.
2. watch system according to backpack emergency satellite communication sky according to claim 1, it is characterized in that: described antenna elevation angle detecting unit (14-11) and antenna azimuth detecting unit (14-12) are contactless Hall angular transducer, described contactless Hall angular transducer is R25D encoder.
3. watch system according to the backpack emergency satellite communication sky described in claim 1 or 2, it is characterized in that: also comprise the upper monitoring machine (14) carrying out two-way communication with microprocessor (13-1), described upper monitoring machine (14) is connected by RS232 interface with between microprocessor (13-1).
4. watch system according to backpack emergency satellite communication sky according to claim 3, it is characterized in that: described GPS positioning unit (14-2), antenna carrier posture detecting unit (14-3) and be all connected by RS232 interface between satellite-signal intensity detection unit (14-4) with microprocessor (13-1), described GPS positioning unit (14-2) is connected with chip U107, described antenna carrier posture detecting unit (14-3) is connected with chip U105, and described satellite-signal intensity detection unit (14-4) is connected with chip U104; Described upper monitoring machine (14) is connected with chip U114; Described chip U107, chip U105, chip U104 and chip U114 are chip SP3220E;
Two data transmission terminals of described GPS positioning unit (14-2) are connected with the 8th and the 13rd pin of chip U107 respectively, 1st pin of chip U107 is connected with the 30th pin of MSP430F149 chip, and the 9th of chip U107 is connected with the 33rd and the 32nd pin of MSP430F149 chip respectively with the 11st pin; Two data transmission terminals of described antenna carrier posture detecting unit (14-3) are connected with the 8th and the 13rd pin of chip U105 respectively, 1st pin of chip U105 is connected with the 28th pin of MSP430F149 chip, and the 9th of chip U105 is connected with the 33rd and the 32nd pin of MSP430F149 chip respectively with the 11st pin; Two data transmission terminals of described satellite-signal intensity detection unit (14-4) are connected with the 8th and the 13rd pin of chip U104 respectively, 1st pin of chip U104 is connected with the 29th pin of MSP430F149 chip, and the 9th of chip U104 is connected with the 33rd and the 32nd pin of MSP430F149 chip respectively with the 11st pin; Two data transmission terminals of described upper monitoring machine (14) are connected with the 8th and the 13rd pin of chip U110 respectively, and the 9th of chip U110 is connected with the 35th and the 34th pin of MSP430F149 chip respectively with the 11st pin.
5. watch system according to the backpack emergency satellite communication sky described in claim 1 or 2, it is characterized in that: described GPS positioning unit (14-2) is GPS, and described GPS is GPS15XL-W module; Described antenna carrier posture detecting unit (14-3) is electronic compass; The satellite signal receiver that described satellite-signal intensity detection unit (14-4) is described satellite communication antena, described satellite signal receiver is KCXBR214-40 satellite beacon receiver.
6. watch system according to the backpack emergency satellite communication sky described in claim 1 or 2, it is characterized in that: described satellite communication antena is single reflector antenna, described single reflector antenna comprises antenna reflective face (15) and the feed assembly (10) for reception antenna reflecting surface (15) institute reflector satellite signal, described antenna reflective face (15) is four distinguish carbon fiber antenna reflective faces, described four distinguish carbon fiber antenna reflective faces comprise main lobe (15-1), be positioned at the left secondary lobe (15-2) of main lobe (15-1) left and right sides and right secondary lobe (15-3) and be positioned at the upper secondary lobe (15-4) of main lobe (15-1) top, described left secondary lobe (15-2) and right secondary lobe (15-3) symmetrical laying, the left side wall of described main lobe (15-1), rear wall and upper side wall are straight side walls, the left side wall of described main lobe (15-1) is parallel laying with rear wall and the two is all vertical runs with the upper side wall of main lobe (15-1), described main lobe (15-1) is arranged on antenna mount (9), and described left secondary lobe (15-2), right secondary lobe (15-3) and upper secondary lobe (15-4) are arranged on the left side of main lobe (15-1), right side and top respectively by connector.
7. watch system according to backpack emergency satellite communication sky according to claim 6, it is characterized in that: described in bear handbag and draw together knapsack inclusion, described knapsack inclusion comprises inner support framework and is sleeved on the ladle cover outside described inner support framework, described ladle cover is sheet and it is made up of the bottom cover body (16-1) of upper opening and the clad (16-2) be laid on bottom cover body (16-1), is connected between described bottom cover body (16-1) with clad (16-2) by slide fastener; Described clad (16-2) arranged outside has the antenna distinguish putting bag (16-3) for placing left secondary lobe (15-2), right secondary lobe (15-3) and upper secondary lobe (15-4); Described bottom cover body (16-1) is provided with braces (16-4); Described main lobe (15-1), antenna mount (9), feed component support piece (11) and antenna running platform (12) are all loaded in described ladle cover.
8. watch system according to the backpack emergency satellite communication sky described in claim 1 or 2, it is characterized in that: the left and right sides of described antenna running platform (12) is respectively arranged with a wind resistance and grabs the thin end of the scroll (17), described wind resistance grabs the thin end of the scroll (17) for carbon fiber support and its outer end is provided with the locking member be locked on the ground, it is by first body of rod that described wind resistance grabs the thin end of the scroll (17), the right-angled triangle support that second body of rod and the 3rd body of rod are formed by connecting, described first body of rod and antenna operate platform (12) in parallel laying, described second body of rod and described first body of rod are vertical runs and its length is less than the length of described first body of rod, described 3rd body of rod is connected between described first body of rod and described second body of rod, described second body of rod is positioned at antenna running platform (12) outside and its upper and lower two ends are arranged on the lateral wall of antenna running platform (12) all in hinged way, described locking member is positioned at the junction of described first body of rod and described 3rd body of rod.
9. watch system according to the backpack emergency satellite communication sky described in claim 1 or 2, it is characterized in that: described antenna mount (9) comprises the fixed mount be fixedly mounted on antenna running platform (12) and the movement frame be positioned at above described fixed mount, described pitch drive mechanism is arranged on described movement frame, described pitch drive mechanism comprises the first turbine worm reducer (1-2) of carrying out with the power output shaft of pitching drive motors (1-1) being in transmission connection and carries out with the power output shaft of the first turbine worm reducer (1-2) cycloid speed reducer (1-3) that is in transmission connection, the antenna back frame of described satellite communication antena is arranged on elevation axis of antenna (4), and described elevation axis of antenna (4) is in transmission connection with the power output shaft of cycloid speed reducer (1-3), described Amimuth Transmission mechanism comprises the planetary reduction gear (2-2) carrying out with the power output shaft of orientation drive motors (2-1) being in transmission connection, the Timing Belt decelerator (2-3) that is in transmission connection is carried out with the power output shaft of planetary reduction gear (2-2), carry out with the power output shaft of Timing Belt decelerator (2-3) the second turbine and worm decelerator (2-4) of being in transmission connection and carry out with the power output shaft of the second turbine and worm decelerator (2-4) the steel wire drive assembly that is in transmission connection, described steel wire drive assembly is installed between described fixed mount and described movement frame, described movement frame and described steel wire drive assembly are in transmission connection.
10. watch system according to the backpack emergency satellite communication sky described in claim 1 or 2, it is characterized in that: described pitch drive mechanism and pitching drive motors (1-1) are in transmission connection, described Amimuth Transmission mechanism and orientation drive motors (2-1) are in transmission connection; Described drive circuit (13-2) is the chip 74HC07 connected with MSP430F149 chip, and described pitching drive motors (1-1) and orientation drive motors (2-1) are DC speed-reducing and the two all connects with the signal output part of chip 74HC07.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410682636.9A CN104393394A (en) | 2014-11-21 | 2014-11-21 | Knapsack emergency satellite communication servo system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410682636.9A CN104393394A (en) | 2014-11-21 | 2014-11-21 | Knapsack emergency satellite communication servo system |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN104393394A true CN104393394A (en) | 2015-03-04 |
Family
ID=52611255
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201410682636.9A Pending CN104393394A (en) | 2014-11-21 | 2014-11-21 | Knapsack emergency satellite communication servo system |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN104393394A (en) |
Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105609966A (en) * | 2015-09-25 | 2016-05-25 | 北京爱科迪通信技术股份有限公司 | Sectional-type antenna reflection surface and design method thereof |
| CN105987131A (en) * | 2015-03-06 | 2016-10-05 | 吴小杰 | Zero-return-difference hypocycloid speed reducer |
| CN109110158A (en) * | 2018-07-26 | 2019-01-01 | 西北工业大学 | A kind of chip satellite group and its distributing method |
| CN109270496A (en) * | 2018-10-31 | 2019-01-25 | 安徽四创电子股份有限公司 | A kind of blank pipe primary radar antenna-feeder system |
| CN110048734A (en) * | 2019-05-06 | 2019-07-23 | 新昌冰银智能技术有限公司 | It is a kind of can amplified signal communication apparatus of seeking help |
| CN111082820A (en) * | 2019-12-23 | 2020-04-28 | 江苏久高电子科技有限公司 | Satellite communication transceiver with simple installation and installation method thereof |
| CN112103615A (en) * | 2020-09-16 | 2020-12-18 | 深圳市威富通讯技术有限公司 | Antenna automatic folding and unfolding leveling device and antenna leveling method |
| CN113726421A (en) * | 2021-11-01 | 2021-11-30 | 亚太卫星宽带通信（深圳）有限公司 | Emergency backpack satellite communication control equipment and use method thereof |
| CN113810065A (en) * | 2021-10-29 | 2021-12-17 | 徐州智畅机器人系统有限公司 | Wireless optical frequency transmitter with signal increasing performance |
Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH11183582A (en) * | 1997-12-19 | 1999-07-09 | Nec Eng Ltd | Method and apparatus for tracking satellite by small antenna for satellite communication |
| CN2731567Y (en) * | 2004-06-01 | 2005-10-05 | 维深巨合（北京）科技有限责任公司 | Front end processing system for RF identifying system |
| CN1808207A (en) * | 2006-02-09 | 2006-07-26 | 南京艾迪尔科技有限公司 | Automatic star search control device for portable astronomical telescope and control method thereof |
| CN101577367A (en) * | 2008-05-08 | 2009-11-11 | 南京理工大学 | Stable tracking control system for satellite communication antenna for motion carrier |
| CN201466217U (en) * | 2009-06-10 | 2010-05-12 | 成都双流富华电子有限公司 | Ka band satellite communication antenna |
| CN101950843A (en) * | 2010-07-21 | 2011-01-19 | 北京市信息技术应用研究所 | Portable satellite antenna system and star finding method thereof |
| US8200150B2 (en) * | 2006-07-25 | 2012-06-12 | Norsat International Inc. | Automatic satellite acquisition system for a portable satellite terminal |
| CN202275927U (en) * | 2011-10-15 | 2012-06-13 | 江阴市彭利天线有限公司 | Backpack-type satellite communication antenna |
| CN102983902A (en) * | 2012-11-30 | 2013-03-20 | 西安欧赛通信科技有限公司 | 1.2m feedback full-automatic portable emergency satellite communication antenna servo system |
-
2014
- 2014-11-21 CN CN201410682636.9A patent/CN104393394A/en active Pending
Patent Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH11183582A (en) * | 1997-12-19 | 1999-07-09 | Nec Eng Ltd | Method and apparatus for tracking satellite by small antenna for satellite communication |
| CN2731567Y (en) * | 2004-06-01 | 2005-10-05 | 维深巨合（北京）科技有限责任公司 | Front end processing system for RF identifying system |
| CN1808207A (en) * | 2006-02-09 | 2006-07-26 | 南京艾迪尔科技有限公司 | Automatic star search control device for portable astronomical telescope and control method thereof |
| US8200150B2 (en) * | 2006-07-25 | 2012-06-12 | Norsat International Inc. | Automatic satellite acquisition system for a portable satellite terminal |
| CN101577367A (en) * | 2008-05-08 | 2009-11-11 | 南京理工大学 | Stable tracking control system for satellite communication antenna for motion carrier |
| CN201466217U (en) * | 2009-06-10 | 2010-05-12 | 成都双流富华电子有限公司 | Ka band satellite communication antenna |
| CN101950843A (en) * | 2010-07-21 | 2011-01-19 | 北京市信息技术应用研究所 | Portable satellite antenna system and star finding method thereof |
| CN202275927U (en) * | 2011-10-15 | 2012-06-13 | 江阴市彭利天线有限公司 | Backpack-type satellite communication antenna |
| CN102983902A (en) * | 2012-11-30 | 2013-03-20 | 西安欧赛通信科技有限公司 | 1.2m feedback full-automatic portable emergency satellite communication antenna servo system |
Cited By (14)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105987131A (en) * | 2015-03-06 | 2016-10-05 | 吴小杰 | Zero-return-difference hypocycloid speed reducer |
| CN105609966A (en) * | 2015-09-25 | 2016-05-25 | 北京爱科迪通信技术股份有限公司 | Sectional-type antenna reflection surface and design method thereof |
| CN105609966B (en) * | 2015-09-25 | 2019-04-19 | 北京爱科迪通信技术股份有限公司 | Split-type antenna reflective face and its design method |
| CN109110158A (en) * | 2018-07-26 | 2019-01-01 | 西北工业大学 | A kind of chip satellite group and its distributing method |
| CN109270496A (en) * | 2018-10-31 | 2019-01-25 | 安徽四创电子股份有限公司 | A kind of blank pipe primary radar antenna-feeder system |
| CN110048734B (en) * | 2019-05-06 | 2019-10-01 | 新昌冰银智能技术有限公司 | It is a kind of can amplified signal communication apparatus of seeking help |
| CN110048734A (en) * | 2019-05-06 | 2019-07-23 | 新昌冰银智能技术有限公司 | It is a kind of can amplified signal communication apparatus of seeking help |
| CN111082820A (en) * | 2019-12-23 | 2020-04-28 | 江苏久高电子科技有限公司 | Satellite communication transceiver with simple installation and installation method thereof |
| CN112103615A (en) * | 2020-09-16 | 2020-12-18 | 深圳市威富通讯技术有限公司 | Antenna automatic folding and unfolding leveling device and antenna leveling method |
| CN112103615B (en) * | 2020-09-16 | 2022-12-23 | 深圳市威富通讯技术有限公司 | Antenna automatic folding and unfolding leveling device and antenna leveling method |
| CN113810065A (en) * | 2021-10-29 | 2021-12-17 | 徐州智畅机器人系统有限公司 | Wireless optical frequency transmitter with signal increasing performance |
| CN113810065B (en) * | 2021-10-29 | 2022-08-23 | 徐州智畅机器人系统有限公司 | Wireless optical frequency transmitter with signal increasing performance |
| CN113726421A (en) * | 2021-11-01 | 2021-11-30 | 亚太卫星宽带通信（深圳）有限公司 | Emergency backpack satellite communication control equipment and use method thereof |
| CN113726421B (en) * | 2021-11-01 | 2022-03-01 | 亚太卫星宽带通信（深圳）有限公司 | Emergency backpack satellite communication control equipment and use method thereof |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN104393394A (en) | Knapsack emergency satellite communication servo system | |
| AU2015200879B2 (en) | Heliostat repositioning system and method | |
| CN102983902B (en) | 1.2m feedback full-automatic portable emergency satellite communication antenna servo system | |
| CN101577367A (en) | Stable tracking control system for satellite communication antenna for motion carrier | |
| CN202737105U (en) | Boat-carrying antenna stabilized platform beam communication system | |
| CN107203863A (en) | Intelligent unattended machine express system | |
| CN107539429A (en) | A kind of unmanned surveying vessel of overturn-preventing | |
| CN205304274U (en) | Wireless charging system of electric vehicle with remove high -altitude flight operation | |
| US7938364B2 (en) | Apparatus and method for making optimal use of a photovoltaic array on an airborne power system | |
| CN208284644U (en) | A kind of unmanned plane automatic tracing antenna | |
| CN104898710A (en) | Mobile solar tracker | |
| CN201887143U (en) | Small-sized antenna pedestal with compact structure | |
| CN212685260U (en) | Novel unmanned shipborne unmanned aerial vehicle charging bin device | |
| CN211618123U (en) | Geological survey is with unmanned aerial vehicle's shooting mechanism | |
| KR200475580Y1 (en) | Solar Power Generator Installed on Pole with Solar Tracking Function | |
| CN109533303B (en) | Split type all-terrain multi-rotor aircraft with anti-collision function | |
| CN207141332U (en) | A kind of unmanned surveying vessel of overturn-preventing | |
| CN215184508U (en) | Multi-functional Mini SAR system biax servo structure | |
| CN104518271B (en) | A kind of Portable Automatic star searching system | |
| CN212956206U (en) | A intelligent way awl for bridge maintenance management | |
| CN113276977A (en) | Multi-freedom-degree spherical robot | |
| KR101991204B1 (en) | Ship lifting device with solar power generation function | |
| CN110880909A (en) | Solar power supply device for environment detection | |
| Ksenzenko et al. | DESIGN THE CONTACTLESS CHARGER AND CONTACTLESS DATA TRANSFER BETWEEN UNDERWATER ROBOT-SATELLITS AND UNDERWATER 6-LEGGED VEHICLE. | |
| CN219610723U (en) | Explosion-proof type book An Tianxian |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20150304 |
|
| RJ01 | Rejection of invention patent application after publication |