CN101820307A - Wireless communication module and wireless communication satellite using module - Google Patents
Wireless communication module and wireless communication satellite using module Download PDFInfo
- Publication number
- CN101820307A CN101820307A CN201010167209A CN201010167209A CN101820307A CN 101820307 A CN101820307 A CN 101820307A CN 201010167209 A CN201010167209 A CN 201010167209A CN 201010167209 A CN201010167209 A CN 201010167209A CN 101820307 A CN101820307 A CN 101820307A
- Authority
- CN
- China
- Prior art keywords
- wireless communication
- radio
- control system
- communication module
- frequency
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
- 230000006854 communication Effects 0.000 title claims abstract description 132
- 238000004891 communication Methods 0.000 title claims abstract description 131
- 238000010276 construction Methods 0.000 claims description 12
- 238000013480 data collection Methods 0.000 claims description 8
- 238000009738 saturating Methods 0.000 claims description 4
- 238000012360 testing method Methods 0.000 abstract description 13
- 238000005259 measurement Methods 0.000 abstract description 10
- 230000002349 favourable effect Effects 0.000 abstract 1
- 238000000034 method Methods 0.000 description 13
- 238000013461 design Methods 0.000 description 10
- 230000008569 process Effects 0.000 description 9
- 230000006870 function Effects 0.000 description 8
- 230000006855 networking Effects 0.000 description 8
- 230000003993 interaction Effects 0.000 description 5
- 230000005540 biological transmission Effects 0.000 description 4
- 238000012545 processing Methods 0.000 description 4
- 230000008859 change Effects 0.000 description 3
- 238000012790 confirmation Methods 0.000 description 2
- 238000001514 detection method Methods 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- 238000007689 inspection Methods 0.000 description 2
- 230000007246 mechanism Effects 0.000 description 2
- 239000000126 substance Substances 0.000 description 2
- 238000012795 verification Methods 0.000 description 2
- 108091092878 Microsatellite Proteins 0.000 description 1
- 230000009471 action Effects 0.000 description 1
- 230000008901 benefit Effects 0.000 description 1
- 238000004364 calculation method Methods 0.000 description 1
- 238000012937 correction Methods 0.000 description 1
- 230000008878 coupling Effects 0.000 description 1
- 238000010168 coupling process Methods 0.000 description 1
- 238000005859 coupling reaction Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 230000007613 environmental effect Effects 0.000 description 1
- 239000000835 fiber Substances 0.000 description 1
- 238000001914 filtration Methods 0.000 description 1
- 238000009432 framing Methods 0.000 description 1
- 230000010365 information processing Effects 0.000 description 1
- 230000002452 interceptive effect Effects 0.000 description 1
- 238000012544 monitoring process Methods 0.000 description 1
- 230000004044 response Effects 0.000 description 1
- 238000001228 spectrum Methods 0.000 description 1
- 230000002195 synergetic effect Effects 0.000 description 1
- 230000002123 temporal effect Effects 0.000 description 1
- 238000010998 test method Methods 0.000 description 1
- 238000010977 unit operation Methods 0.000 description 1
Images
Landscapes
- Radio Relay Systems (AREA)
Abstract
The invention discloses a wireless communication module and a wireless communication satellite using the module, relates to a wireless communication module and a wireless communication satellite, and solves the problems that the conventional satellites have complex structure, poor reliability and poor safety and are not favorable for tests. In the wireless communication module, a radio frequency antenna is connected with a radio frequency signal transmitting/receiving end of a radio frequency chip circuit; a signal end of the radio frequency chip circuit is connected with a signal end of a microcontroller; and an external data acquisition and control signal end of the microcontroller is a baseband data input/output end of the wireless communication module. In the wireless communication satellite, a power supply provides working power for a measurement and control system, a satellite management system, an attitude and orbit control system and an effective load management and control system; and the measurement and control system, the satellite management system, the attitude and orbit control system and the effective load management and control system form a wireless network through four wireless communication modules. The wireless communication module and the wireless communication satellite using the module are applied to the field of high-reliability and high-safety satellite communication.
Description
Technical field
The present invention relates to the AEROSPACE APPLICATION field, be specifically related to a kind of wireless communication module and communication satellite.
Background technology
Between the inner subsystem of spacecraft celestial body or need interactive information between parts, between subsystem or parts effectively, safe and reliable operation has important effect to spacecraft in communication reliably.
In the celestial body intercommunication system of using at present, mainly finish information interaction as the carrier of communication between parts by cable, produced the topological structure between a lot of parts thus, bus type structure, point-to-point structure etc.At present main on the star what adopt is bus structures, and host computer is managed all the other all slave computers on the star, and complex interface between hypotactic design and parts has been brought a lot of problems: single main frame fault-tolerance is bad, and computational speed is slow, can not parallel processing; Number of cables is numerous, has increased the size, the weight that design on the star, and structural design need be considered numerous cables, has increased complexity; The interface circuit design complexity for preventing crosstalk between parts and subsystem, need to rely on complicated ground connection to guarantee, and the earth connection interference can bring noise; Interface Matching and protect design complexity etc. altogether on testing equipment and the star in the test process.
Summary of the invention
The present invention is in order to solve existing satellite structure complexity, poor reliability, poor stability, to be unfavorable for the problem of testing, and proposes a kind of wireless communication module and uses the radio communication satellite of this module.
A kind of wireless communication module, it comprises radio-frequency module and microcontroller, described radio-frequency module is made up of radio-frequency antenna and radio frequency chip circuit, radio-frequency antenna links to each other with the emission of radio frequency signals/receiving terminal of radio frequency chip circuit, the base band data I/O end of radio-frequency module links to each other with the control signal end with the external data collection of microcontroller, and the external data collection of microcontroller and control signal end are the base band data I/O end of described wireless communication module.
Use the radio communication satellite of above-mentioned wireless communication module, it comprises power supply, TT﹠C system, the Star Service management system, the attitude control system, useful load management and control system and 4 wireless communication modules, the power output end of power supply and TT﹠C system, the Star Service management system, the power supply input of attitude control system and useful load management and control system links to each other, be TT﹠C system, the Star Service management system, attitude control system and useful load management and control system provide working power, and the signal I/O end of described TT﹠C system connects the base band data I/O end of first wireless communication module; The signal I/O end of Star Service management system connects the base band data I/O end of second wireless communication module; The signal I/O end of attitude control system connects the base band data I/O end of the 3rd wireless communication module; The baseband signal I/O end of useful load management and control system connects the data I/O end of the 4th wireless communication module; Described 4 wireless communication modules are formed wireless network.
Radio communication satellite of the present invention adopts the wireless data interaction of carrying out reaching between satellite platform between platform and load, adopted the radio frequency chip that is installed in inside satellite to finish information interaction between satellite subsystem, in Star Service management, satellite configuration, remote measuring and controlling and attitude control, all broken through the traditional design of wired satellite, thereby realized a kind of brand-new satellite based on wireless system.Device inside cable of the present invention connects does not have other cables to connect except that power supply connects.Be applicable to reliability height, safe satellite communication field.
Description of drawings
Fig. 1 is a kind of structural representation of wireless communication module.Fig. 2 is the another kind of structural representation of wireless communication module.Fig. 3 is for using the radio communication satellite structure schematic diagram of wireless communication module.Fig. 4 is the radio communication satellite structure schematic diagram that has shielding construction 15, high frequency cable 16 and cabin section 17.Fig. 5 is the structural representation of embodiment five.
Embodiment
Embodiment one,In conjunction with Fig. 1 present embodiment is described, a kind of wireless communication module, it comprises radio-frequency module 1 and microcontroller 2, described radio-frequency module 1 is made up of radio-frequency antenna 1-1 and radio frequency chip circuit 1-2, radio-frequency antenna 1-1 links to each other with emission of radio frequency signals/receiving terminal of radio frequency chip circuit 1-2, the base band data I/O end of radio-frequency module 1 links to each other with the control signal end with the external data collection of microcontroller 2, and the external data collection of microcontroller 2 and control signal end are the base band data I/O end of described wireless communication module.
Wireless communication module is made of radio-frequency module 1 and microcontroller 2, has realized functions such as data acquisition, information processing and radio communication.
Embodiment two,In conjunction with Fig. 1 present embodiment is described, present embodiment is that the difference to embodiment one is that radio frequency chip circuit 1-2 is the RFIC integrated radio-frequency circuit, and microcontroller 2 is FPGA microprocessor or ASIC microprocessor.
Embodiment three,In conjunction with Fig. 1 present embodiment is described, present embodiment is that the difference to embodiment one is that radio-frequency antenna 1-1 is leaky cable or microstrip antenna or conformal antenna.
Embodiment four,In conjunction with Fig. 2 present embodiment is described, present embodiment is that the difference to embodiment one is, it also comprises a radio-frequency module 1, the signal end of a described radio-frequency module 1 links to each other with the emission of radio frequency signals end of microcontroller 2, and the signal end of another radio-frequency module 1 links to each other with the radiofrequency signal receiving terminal of microcontroller 2.
Radio-frequency module 1 is selected nRF2401 rf chip circuit for use, and microcontroller 2 is C8051F040.
Each nRF2401 rf chip all can be received and dispatched, but is the half-duplex state.In the course of work, must guarantee has a nRF2401 rf chip to be in the reception attitude.By the nRF2401 rf chip is set, can make one of them nRF2401 rf chip be operated in transmit status, and another nRF2401 rf chip is operated in accepting state, when sending, can receive, after received frame and transmit frame compared, can understand transmit frame and collision whether occur.The transmission of all parts is disposed identical with receiver address, guarantees to receive all communication frames, and destination address and source address are carried out filtering in the data field.
Embodiment five,In conjunction with Fig. 5 present embodiment is described, present embodiment and embodiment one, two, three or fours' difference is that it also comprises high frequency cable 16, and described high frequency cable 16 is connected between emission of radio frequency signals/receiving terminal of radio-frequency antenna 1-1 and radio frequency chip circuit 1-2.
Embodiment six,In conjunction with Fig. 3 present embodiment is described, use the radio communication satellite of embodiment one to four any described wireless communication module of execution mode, it comprises power supply 10, TT﹠C system 11, Star Service management system 12, attitude control system 13, useful load management and control system 14 and 4 wireless communication module K, the power output end of power supply 10 and TT﹠C system 11, Star Service management system 12, the power supply input of attitude control system 13 and useful load management and control system 14 links to each other, be TT﹠C system 11, Star Service management system 12, attitude control system 13 and useful load management and control system 14 provide working power, and the signal I/O end of described TT﹠C system 11 connects the base band data I/O end of first wireless communication module K; The signal I/O end of Star Service management system 12 connects the base band data I/O end of second wireless communication module K; The signal I/O end of attitude control system 13 connects the base band data I/O end of the 3rd wireless communication module K; The signal I/O end of useful load management and control system 14 connects the base band data I/O end of the 4th wireless communication module K; Described 4 wireless communication module K form wireless network.
The design of radio communication satellite can have brand-new breakthrough for traditional satellite on architecture, except feed cable, satellite system does not have other cable to connect, it is a kind of novel system satellite based on radio communication, implementation method of the present invention is: in the radio communication satellite, each subsystem all has the function of radio communication, it is the elementary cell of radio communication satellite, communicate by wireless channel between subsystem, adopt wireless communication protocol, novel way to manage and distributed computing method, and improve configuration and method of testing, thus finish the change on the radio communication satellite architecture.Can fundamentally reject existing satellite structure complexity, poor reliability, poor stability, be unfavorable for the problem of testing, therefore have important practical value.
TT﹠C system 11 is passages of star ground communication, is responsible for receiving the instruction on ground and the telemetry intelligence (TELINT) on the star is sent to ground; Star Service management system 12 is responsible for the task scheduling of whole star, the work schedule of each subsystem of management platform; Attitude control system 13 is responsible for the attitude and the track of whole star, and windsurfing was to day when whole star need be charged, and load is finished the correct attitude and the control of track over the ground when executing the task; Power supply 10 subsystems are responsible for whole star power supply; Useful load management and control system 14 is responsible for carrying out the task of satellite at rail.
1) TT﹠C system 11:
The TT﹠C system 11 of radio communication satellite can adopt traditional USB observing and controlling system, also can adopt spread spectrum observing and controlling system, and its major function is to carry out the remote measurement of star ground, remote control and orbit determination to measure.The characteristics of radio communication satellite have determined the characteristics of TT﹠C system, and in remote control process, direct instruction is directly carried out by TT﹠C system, and main action is powering up and the control of cutting off the power supply of control subsystem or parts, and is identical with traditional direct instruction; The control difference of the execution of indirect instruction and conventional satellite is bigger, the indirect instruction of radio communication satellite is directly broadcasted in star by TT﹠C system, do not need through the Star Service management system, can directly receive the indirect instruction of explaining the TT﹠C system distribution by control subsystem or parts.Telemetry parameter directly sends to detection and control terminal by each subsystem or parts, by passing down behind detection and control terminal framing again.
2) the Star Service management system 12:
The Star Service management system 12 of radio communication satellite is a virtual system, can finish the control and management function by the processor that is embedded in each subsystem or the parts.
The formula management system is designed to distribute, need finish the control and management function by each subsystem or parts, at this moment, need GPS receiver airtime signal to come each subsystem or parts are carried out time management, each subsystem or parts send Frame according to certain time sequence to the purpose parts, do not need spaceborne computer that subsystem is carried out time management; When the GSP fault, by self of ground specified parts time as time reference.For equipment control, each subsystem or parts record self identification and the networking time, when identity is conflicted, the subsystem or the parts identify label that network early remain unchanged, again network after the identify label of initiate subsystem or parts change self, communication can adopt the mode of token ring or anticollision protocol to communicate between parts.
3) the attitude control system 13:
The attitude control system 13 of radio communication satellite is a kind of independent control system, because measurement component is image data and adopt wireless mode to send automatically, therefore each execution unit can receive metrical information and attitude control is carried out in control information simultaneously, and for the associating parallel processing, System Fault Tolerance is handled that the ideal control platform is provided.
Can adopt the mode of no rail control computer, directly carry out the mutual of information between measurement component and execution unit, adopt the calculating of distributed rail control algorithm, each measurement component and execution unit are all gathered the information of all rail control parts, finish the part of rail control algorithm, carry out the rail control computing simultaneously, and the computational process feedback information come out, in control procedure, the process of algorithm is revised according to different component computes results, improved arithmetic speed and controlled computational process and intermediate object program at any time, to reach parallel processing and fault-tolerant purpose.
4) the useful load management and control system 14:
It is independently systems that the radio communication satellite is imitated load management and control system 14, because the characteristics of radio communication satellite, satellite platform and payload only exist mechanical interface and wave point, therefore payload can realize powering up the i.e. application target of usefulness, test job can independently be finished, and has the application interface of simplifying most.
Communication protocol is the basis that subsystem realizes associated working in the radio communication satellite, need export measurement data and state as measurement component, need receive order parameter and output block state as execution unit.
Radio communication inside satellite communication protocol comprises the content of following several respects:
(1) link layer: realize the reception and the transmission of wireless signal, basic communication check and correction process;
(2) application layer: basic communication administration module, special applications module, general administration module.
For link layer protocol, in order to guarantee communication effectively reliably between parts, need basic communication inspection and error correcting and detecting function, on the agreement of link layer, guarantee the effective and reliable of data, substance is:
(1) contains id information in the link layer form, be used for distinguishing different parts and subsystem, when visiting these parts, adopt different ID;
(2) contain check information or to data codings in the link layer form, be used for judging the transmission data data that whether correctly or directly right a wrong, also can send the request retransmission order, the request transmit leg retransmits;
(3) contain frame counting information in the link layer form, be used for preventing losing of Frame,, have the frame losing retransmission mechanism if the recipient judges that received frame is discontinuous.
In the radio communication satellite, when entering wireless network, each subsystem need carry out initialization procedure, by each subsystem that has networked the subsystem or the parts of new networking are carried out equipment control, this process is independently started by subsystem, after receiving confirmation, subsystem or parts are promptly entered Radio Network System by approval.
The process that a plurality of wireless communication module K form wireless network is as follows: flow chart is seen Fig. 4;
After TT﹠C system 11, Star Service management system 12, attitude control system 13 or useful load management and control system 14 power up or reset, in above-mentioned four subsystems one or several sends greeting information and temporary identity identification information to wireless network, application adds wireless network, and the subsystem that is allowed to add wireless network enters wait state;
The subsystem that is not allowed to add wireless network sends to each subsystem that enters wireless network and greets and temporary identity identification information, and enters wait state;
Identify label and self identify label that each subsystem that has entered wireless network will newly apply for adding the subsystem of wireless network compare, if identical then send query information;
If the subsystem that new application adds wireless network is received query information in official hour, show that this identify label is used, change temporary identity sign, application adds wireless network again;
Otherwise this subsystem uses this identify label to enter wireless network, adds the wireless network success, and uses this identification information in communication, and this identification information is constant after the outage;
After all subsystems all added the wireless network success, the wireless network of this radio communication satellite was set up successfully.
After the radio communication satellite powers up, each system synergistic working, finish the various functions of satellite jointly, the tie of each subsystem information interaction is a radio communication channel, communication mode is the basis that subsystem or unit parts are realized associated working, measurement data and state need be exported as measurement component, order parameter and output block state need be received as execution unit.
In order to guarantee communication effectively reliably between parts, the radio communication satellite needs basic communication inspection and error correcting and detecting function, and substance comprises:
(1) contains id information in the Content of Communication, be used for distinguishing different parts and subsystem, when different subsystems or parts are visited these parts, adopt different ID;
(2) contain check information or to data codings in the Content of Communication, be used for judging the transmission data data that whether correctly or directly right a wrong, also can send the request retransmission order, the request transmit leg retransmits;
(3) contain frame counting information in the Content of Communication, be used for preventing losing of Frame,, have the frame losing retransmission mechanism, guarantee the reliability of communicating by letter if the recipient judges that received frame is discontinuous.
Except that Star Service management system 12, the radio communication satellite also comprises equipment control, and the characteristics of wireless connections make equipment room add cordless communication network when whole star powers up and do not influence whole star safety.
In the radio communication satellite, when entering wireless network, each subsystem or parts need carry out initialization procedure, by each subsystem that has networked or parts the subsystem or the parts of new networking are carried out equipment control, this process is independently started by subsystem or parts, after receiving confirmation, subsystem or parts are promptly entered Radio Network System by approval, after subsystem or parts enter Radio Network System, then can the cycle in accordance with regulations carry out information interaction, or under the control of management system, carry out acknowledge communication.
Withdrawing from Radio Network System does not need extra communication frame, both can be normally to withdraw from Radio Network System, can be to withdraw from Radio Network System because of fault yet.
GPS receiver per second broadcasting one bag time frame, each subsystem is proofreaied and correct the response time of self according to gps time, and writes down the networking gps time of self; If certain parts or subsystem receive in communication process and self identify label common identity sign, then send the query frame, query the identify label and the networking temporal information that comprise self in the frame, networking information in the query frame that the recipient will receive and self networking information compare, the identify label that keeps networking time equipment early, otherwise network again after the replacing identify label, to guarantee the fail safe of system.
In the radio communication satellite, each subsystem or parts are responsible for the validity and the correctness of communication frame voluntarily, for transmit frame, the sender is monitoring reception simultaneously, if find to send inconsistent with reception, then answer random delay to send after a period of time, random delay time minimum is the time-delay of a communication frame again, is the time-delay that subsystem in the wireless network or components number are taken advantage of a communication frame to the maximum.For received frame, should calculate received frame verification and, if verification and correct thinks that then this frame is correct, can use this frame, if incorrect, then need not carry out any processing.
Embodiment seven,In conjunction with Fig. 4 present embodiment is described, present embodiment is that the difference to embodiment six is, described radio communication satellite also comprises shielding construction 15, described shielding construction 15 makes TT﹠C system 11, Star Service management system 12, shielding mutually between attitude control system 13 and useful load management and control system 14 each subsystem, be in series with high frequency cable 16 between emission of radio frequency signals/receiving terminal of radio-frequency antenna 1-1 and radio frequency chip circuit 1-2 among each wireless communication module K, make that the radio-frequency antenna 1-1 among each wireless communication module K is positioned at outside the shielding construction 15.
Embodiment eight,In conjunction with Fig. 4 present embodiment is described, present embodiment is that the difference to embodiment six is that it also comprises shielding construction 15, described shielding construction 15 makes and shields mutually between TT﹠C system 11, Star Service management system 12, attitude control system 13 and useful load management and control system 14 each subsystem, porose or saturating ripple window on the described shielding construction 15, make the radio-frequency antenna 1-1 of the wireless communication module K in each subsystem be positioned at described hole or saturating ripple window place, realize electromagnetic coupling.
Embodiment nine,In conjunction with Fig. 4 present embodiment is described, present embodiment is the radio communication satellite that embodiment six, seven or eight difference is to use wireless communication module, it also comprises cabin section 17, and the radio-frequency antenna 1-1 among each wireless communication module K is positioned at cabin section 17.
Radio communication satellite of the present invention conveniently carries out single machine test, and radio communication satellite single machine test need satisfy the requirement of internal communication protocol using, carries out the environmental test of unit on this basis.Since approaching in whole star stage and unit operation state, therefore the test and the test period of whole star can be shortened, even the Test Application requirement can be realized exempting from.
Radio communication satellite of the present invention conveniently carries out general assembly, and the radio communication satellite assembly is simple relatively, owing to only there is feed cable, saved the weight of cable system, simultaneously, owing to eliminated signal line cable, therefore the EMC environment becomes simple relatively, can simplify the EMC test.
Radio communication satellite of the present invention conveniently carries out thermal control, and the control of radio communication microsatellite active heat is a virtual system, is finished by power-supply system, payload system or propulsion system respectively.Passive thermal control was finished in the design phase.
The thermal design of radio communication satellite can be adopted temperature design on the low side, in the temperature controlled parts of needs, can adopt the fiber optic conduction scheme that luminous energy is sent on the parts even device that need temperature control, thereby realizes local temperature control.
Claims (9)
1. wireless communication module, it is characterized in that it comprises radio-frequency module (1) and microcontroller (2), described radio-frequency module (1) is made up of radio-frequency antenna (1-1) and radio frequency chip circuit (1-2), radio-frequency antenna (1-1) links to each other with the emission of radio frequency signals/receiving terminal of radio frequency chip circuit (1-2), the base band data I/O end of radio-frequency module (1) links to each other with the control signal end with the external data collection of microcontroller (2), and the external data collection of microcontroller (2) and control signal end are the base band data I/O end of described wireless communication module.
2. a kind of wireless communication module according to claim 1 is characterized in that radio frequency chip circuit (1-2) is the RFIC integrated radio-frequency circuit, and microcontroller (2) is FPGA microprocessor or ASIC microprocessor.
3. a kind of wireless communication module according to claim 1 is characterized in that radio-frequency antenna (1-1) is leaky cable or microstrip antenna or conformal antenna.
4. a kind of wireless communication module according to claim 1, it is characterized in that it also comprises another radio-frequency module (1), the base band data I/O end of a described radio-frequency module (1) links to each other with the control signal end with the external data collection of microcontroller (2), and the base band data I/O end of another radio-frequency module (1) links to each other with the control signal end with the external data collection of microcontroller (2).
5. according to claim 1,2,3 or 4 described a kind of wireless communication modules, it is characterized in that it also comprises high frequency cable (16), described high frequency cable (16) is connected between the emission of radio frequency signals/receiving terminal of radio-frequency antenna (1-1) and radio frequency chip circuit (1-2).
6. use the radio communication satellite of the described wireless communication module of claim 1, it is characterized in that it comprises power supply (10), TT﹠C system (11), Star Service management system (12), attitude control system (13), useful load management and control system (14) and (4) individual wireless communication module (K), the power output end of power supply (10) and TT﹠C system (11), Star Service management system (12), attitude control system (13) links to each other with the power supply input of useful load management and control system (14), be TT﹠C system (11), Star Service management system (12), attitude control system (13) and useful load management and control system (14) provide working power, and the signal I/O end of described TT﹠C system (11) connects the base band data I/O end of first wireless communication module (K); The signal I/O end of Star Service management system (12) connects the base band data I/O end of second wireless communication module (K); The signal I/O end of attitude control system (13) connects the base band data I/O end of the 3rd wireless communication module (K); The signal I/O end of useful load management and control system (14) connects the base band data I/O end of the 4th wireless communication module (K); Described 4 wireless communication modules (K) are formed wireless network.
7. radio communication satellite according to claim 6, it is characterized in that it also comprises shielding construction (15), described shielding construction (15) makes and shields mutually between TT﹠C system (11), Star Service management system (12), attitude control system (13) and each subsystem of useful load management and control system (14).
8. radio communication satellite according to claim 6, it is characterized in that it also comprises shielding construction (15), described shielding construction (15) makes and shields mutually between TT﹠C system (11), Star Service management system (12), attitude control system (13) and each subsystem of useful load management and control system (14), described shielding construction (15) is gone up porose or saturating ripple window, and the radio-frequency antenna (1-1) of the wireless communication module in each subsystem (K) is positioned at described hole or saturating ripple window place.
9. according to claim 6,7 or 8 described radio communication satellites, it is characterized in that it also comprises cabin section (17), the radio-frequency antenna (1-1) in each wireless communication module (K) is positioned at cabin section (17).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201010167209 CN101820307B (en) | 2010-05-10 | 2010-05-10 | Wireless communication module and wireless communication satellite using module |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201010167209 CN101820307B (en) | 2010-05-10 | 2010-05-10 | Wireless communication module and wireless communication satellite using module |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN101820307A true CN101820307A (en) | 2010-09-01 |
| CN101820307B CN101820307B (en) | 2013-07-03 |
Family
ID=42655270
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN 201010167209 Active CN101820307B (en) | 2010-05-10 | 2010-05-10 | Wireless communication module and wireless communication satellite using module |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN101820307B (en) |
Cited By (14)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103699069A (en) * | 2013-12-06 | 2014-04-02 | 上海卫星工程研究所 | Advanced electronic integrated system for microsatellite |
| CN105007109A (en) * | 2015-07-07 | 2015-10-28 | 中国人民解放军第二炮兵工程大学 | Adaptive combination navigation antenna beam control method for satellite communication in motion system |
| CN105099504A (en) * | 2014-05-20 | 2015-11-25 | 中国科学院空间科学与应用研究中心 | Ultra-wideband pulse-based satellite-bone high-speed data network system |
| CN106445674A (en) * | 2016-10-14 | 2017-02-22 | 上海微小卫星工程中心 | Satellite architecture with autonomous running and governing functions |
| CN106788674A (en) * | 2016-12-02 | 2017-05-31 | 航天东方红卫星有限公司 | A kind of data broadcasting Dispatching Unit for moonlet |
| CN106936491A (en) * | 2015-12-30 | 2017-07-07 | 北京空间飞行器总体设计部 | Satellite-carried wireless information system |
| CN108512590A (en) * | 2018-03-23 | 2018-09-07 | 中国空间技术研究院 | A kind of joint-trial system and method for satellite attitude and orbit control subsystem and GNSS subsystems |
| CN109194555A (en) * | 2018-07-20 | 2019-01-11 | 航天东方红卫星有限公司 | A kind of improved moonlet data transmission subsystem bus scheduling system |
| CN109586391A (en) * | 2018-10-26 | 2019-04-05 | 中国电子科技集团公司第十八研究所 | Deep space exploration aircraft power supply system |
| CN111917453A (en) * | 2020-07-15 | 2020-11-10 | 中国科学院微小卫星创新研究院 | Satellite integrated electronic system |
| CN112052540A (en) * | 2020-09-09 | 2020-12-08 | 哈尔滨工业大学 | Architecture of small satellite for supporting ultrahigh power consumption |
| CN112425092A (en) * | 2018-05-04 | 2021-02-26 | 波音公司 | Managed payload operation |
| CN112446053A (en) * | 2020-11-25 | 2021-03-05 | 中国科学院微小卫星创新研究院 | Device for ground test verification of communication satellite |
| US11595360B2 (en) | 2017-03-06 | 2023-02-28 | The Boeing Company | Hosted payload operations with private telemetry and command |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1161610A (en) * | 1995-11-29 | 1997-10-08 | 摩托罗拉公司 | Radio subcriber unit having switched antenna diversity apparatus and method therefor |
| WO2004068742A1 (en) * | 2003-01-31 | 2004-08-12 | Fujitsu Limited | Mobile radio terminal device |
| CN1589041A (en) * | 2004-08-06 | 2005-03-02 | 白江 | Radio honeycomb base station device with VDSL interface |
-
2010
- 2010-05-10 CN CN 201010167209 patent/CN101820307B/en active Active
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1161610A (en) * | 1995-11-29 | 1997-10-08 | 摩托罗拉公司 | Radio subcriber unit having switched antenna diversity apparatus and method therefor |
| WO2004068742A1 (en) * | 2003-01-31 | 2004-08-12 | Fujitsu Limited | Mobile radio terminal device |
| CN1589041A (en) * | 2004-08-06 | 2005-03-02 | 白江 | Radio honeycomb base station device with VDSL interface |
Cited By (21)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103699069A (en) * | 2013-12-06 | 2014-04-02 | 上海卫星工程研究所 | Advanced electronic integrated system for microsatellite |
| CN105099504A (en) * | 2014-05-20 | 2015-11-25 | 中国科学院空间科学与应用研究中心 | Ultra-wideband pulse-based satellite-bone high-speed data network system |
| CN105007109A (en) * | 2015-07-07 | 2015-10-28 | 中国人民解放军第二炮兵工程大学 | Adaptive combination navigation antenna beam control method for satellite communication in motion system |
| CN105007109B (en) * | 2015-07-07 | 2019-10-15 | 中国人民解放军第二炮兵工程大学 | The adaptive integrated navigation antenna beam control method of satellite communications system |
| CN106936491A (en) * | 2015-12-30 | 2017-07-07 | 北京空间飞行器总体设计部 | Satellite-carried wireless information system |
| CN106445674A (en) * | 2016-10-14 | 2017-02-22 | 上海微小卫星工程中心 | Satellite architecture with autonomous running and governing functions |
| CN106788674A (en) * | 2016-12-02 | 2017-05-31 | 航天东方红卫星有限公司 | A kind of data broadcasting Dispatching Unit for moonlet |
| CN106788674B (en) * | 2016-12-02 | 2019-07-12 | 航天东方红卫星有限公司 | A kind of data broadcasting Dispatching Unit for moonlet |
| US11595360B2 (en) | 2017-03-06 | 2023-02-28 | The Boeing Company | Hosted payload operations with private telemetry and command |
| CN108512590A (en) * | 2018-03-23 | 2018-09-07 | 中国空间技术研究院 | A kind of joint-trial system and method for satellite attitude and orbit control subsystem and GNSS subsystems |
| CN108512590B (en) * | 2018-03-23 | 2020-08-14 | 中国空间技术研究院 | Joint test system of satellite attitude and orbit control subsystem and GNSS subsystem |
| CN112425092B (en) * | 2018-05-04 | 2023-04-11 | 波音公司 | Managed payload operation |
| CN112425092A (en) * | 2018-05-04 | 2021-02-26 | 波音公司 | Managed payload operation |
| CN109194555B (en) * | 2018-07-20 | 2020-11-10 | 航天东方红卫星有限公司 | Improved bus scheduling system of small satellite data transmission subsystem |
| CN109194555A (en) * | 2018-07-20 | 2019-01-11 | 航天东方红卫星有限公司 | A kind of improved moonlet data transmission subsystem bus scheduling system |
| CN109586391B (en) * | 2018-10-26 | 2021-11-09 | 中国电子科技集团公司第十八研究所 | Deep space exploration aircraft power supply system |
| CN109586391A (en) * | 2018-10-26 | 2019-04-05 | 中国电子科技集团公司第十八研究所 | Deep space exploration aircraft power supply system |
| CN111917453A (en) * | 2020-07-15 | 2020-11-10 | 中国科学院微小卫星创新研究院 | Satellite integrated electronic system |
| CN112052540A (en) * | 2020-09-09 | 2020-12-08 | 哈尔滨工业大学 | Architecture of small satellite for supporting ultrahigh power consumption |
| CN112446053A (en) * | 2020-11-25 | 2021-03-05 | 中国科学院微小卫星创新研究院 | Device for ground test verification of communication satellite |
| CN112446053B (en) * | 2020-11-25 | 2021-06-29 | 中国科学院微小卫星创新研究院 | Device for ground test verification of communication satellite |
Also Published As
| Publication number | Publication date |
|---|---|
| CN101820307B (en) | 2013-07-03 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN101820307B (en) | Wireless communication module and wireless communication satellite using module | |
| CN103473196B (en) | Remote measuring and controlling data transmission device in a kind of 1553B bus and star between device bus | |
| CN102809937B (en) | PLC and 1553B based portable equivalent device for carrier rocket test-launch control system | |
| CN202632091U (en) | Three-satellite constellation distributed parallel test system | |
| CN102624439B (en) | Integrated detection equipment for pico-satellite | |
| CN103530211A (en) | PCIE loop back self-test method based on UVM platform | |
| CN102540143A (en) | Accurate positioning method and system for target | |
| CN103529820A (en) | Fault injection testing system and testing method applied to embedded equipment | |
| CN104333408A (en) | Inter-satellite communication system used for realizing high-dynamic and low-delay space teleoperation | |
| CN109547974B (en) | Redundant communication positioner of train binary channels | |
| CN103646524B (en) | A kind of communication means of double-mode local communication module device of electric energy meter | |
| CN106598037A (en) | UAV identity recognition system based on electronic information UAV control | |
| CN102096657A (en) | System-on-chip (SOC)-based micro information processing module | |
| Xiong et al. | FlyingLoRa: Towards energy efficient data collection in UAV-assisted LoRa networks | |
| CN102355378A (en) | Carrier channel testing system | |
| CN104252137B (en) | A kind of general in-orbit upper note minimum system of microsatellite | |
| CN113593307A (en) | Unmanned aerial vehicle-based data acquisition system and method for aviation navigation equipment | |
| CN117650824A (en) | Integrated comprehensive electronic unit of small satellite | |
| CN108880948B (en) | Equipment test verification system and method based on FC network | |
| CN110104028A (en) | Train car number identification system and its operation method | |
| CN202523089U (en) | Underground positioning system | |
| CN109144090A (en) | Distributed unmanned aerial vehicle self-driving instrument with networked communication | |
| CN112187597B (en) | Vehicle-mounted ground end data chain based on FlexRay bus | |
| CN104361299A (en) | Security system, multilevel security controlling system and location information reading method thereof | |
| Leccese et al. | Cluster layout for an optical wireless sensor network for aerospace applications |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| TR01 | Transfer of patent right | ||
| TR01 | Transfer of patent right |
Effective date of registration: 20170907 Address after: 150001 No. 434, postal street, Nangang District, Heilongjiang, Harbin Patentee after: Harbin Institute of Technology National University Science Park Development Co., Ltd. Address before: 150001 Harbin, Nangang, West District, large straight street, No. 92 Patentee before: Harbin Institute of Technology |
|
| TR01 | Transfer of patent right | ||
| TR01 | Transfer of patent right |
Effective date of registration: 20171102 Address after: 510250 72 South Jinhui Road, Haizhuqu District Industrial Avenue, Guangdong, Guangzhou Patentee after: Harbin robotics group (Guangzhou) intellectual property Klc Holdings Ltd Address before: 150001 No. 434, postal street, Nangang District, Heilongjiang, Harbin Patentee before: Harbin Institute of Technology National University Science Park Development Co., Ltd. |
|
| TR01 | Transfer of patent right | ||
| TR01 | Transfer of patent right |
Effective date of registration: 20180115 Address after: 150000 Heilongjiang Province, Harbin City Economic Development Zone haping Road District Dalian road and Xingkai road junction Patentee after: Hagongda robot group (Harbin) Asset Management Co., Ltd. Address before: 510250 72 South Jinhui Road, Haizhuqu District Industrial Avenue, Guangdong, Guangzhou Patentee before: Harbin robotics group (Guangzhou) intellectual property Klc Holdings Ltd |
|
| TR01 | Transfer of patent right | ||
| TR01 | Transfer of patent right |
Effective date of registration: 20181101 Address after: 414002 room 538, Yungang Road Customs Service building, Chenglingji new port, Yueyang, Hunan Patentee after: Hakda robotics group Yueyang Co., Ltd. Address before: 150000 Dalian Road North and Xingkai Road, Harbin, Heilongjiang province. Patentee before: Hagongda robot group (Harbin) Asset Management Co., Ltd. |
|
| TR01 | Transfer of patent right | ||
| TR01 | Transfer of patent right |
Effective date of registration: 20181225 Address after: 414002 Fourth Floor, Building 2, Xindeng Incubation Building, Yungang Road Military-Civil Integration Industrial Park, Chenglingji New Port District, Yueyang City, Hunan Province Patentee after: Harbin University of Technology Robot (Yueyang) Research Institute Co., Ltd. Address before: 414002 room 538, Yungang Road Customs Service building, Chenglingji new port, Yueyang, Hunan Patentee before: Hakda robotics group Yueyang Co., Ltd. |